DCL-15-131, Diablo Canyon, Unit 1, Pressurizer Spray Line Pipe Weld Flaw Evaluation, Calculation Package, Part 1

Diablo Canyon, Unit 1, Pressurizer Spray Line Pipe Weld Flaw Evaluation, Calculation Package, Part 1

ML15307A752
Person / Time
Site:	Diablo Canyon
Issue date:	11/03/2015
From:	Allen B S, Lohse C S Pacific Gas & Electric Co, Structural Integrity Associates
To:	Document Control Desk, Office of Nuclear Reactor Regulation
Shared Package
ML15308A184	List: DCL-15-131, Diablo Canyon, Unit 1, Pressurizer Spray Line Pipe Weld Flaw Evaluation, Calculation Package, Part 1 DCL-15-131, Pressurizer Spray Line Pipe Weld Flaw Evaluation, Calculation Package, Part 2 ML15307A752
References
DCL-15-131 1501350.301
Download: ML15307A752 (122)

Text

Pacific Gas and Electric Company November 3, 2015 PG&E Letter DCL-15-131 U.S. Nuclear Regulatory Commission ATIN: Document Control Desk Washington, DC 20555-0001 Docket No. 50-275, OL-DPR-80 Diablo Canyon Power Plant (DCPP) Unit 1 Pressurizer Spray Line Pipe Weld Flaw Evaluation Dear Commissioners and Staff: B arry S. Allen Vice President, Nuclear Services Diablo Canyon Power Plant Mail Code 104/6 P. 0. Box 56 Avila Beach, CA 93424 805.545.4888 Internal: 691.4888 Fax: 805.545.6445 In accordance with the requirements of the American Society of Mechanical Engineers (ASME) Boiler and Pressure Vessel Code Section XI, 2001 Edition through 2003 Addenda, Paragraphs IWB-3132.3, IWB-3134(b), and IWB-3640, Pacific Gas &.Electric Company is submitting to the NRC the attached structural flaw evaluation of a flaw found in Diablo Canyon Unit 1, ASME Code Class 1 pressurizer spray line pipe weld. IWB-3134(b) states, "Analytical evaluation of examination results as required by IWB-3132.3 shall be submitted to the regulatory authority having jurisdiction at the plant site." Ultrasonic exam-inations performed during the Unit 1 nineteenth refueling outage (1R19) identified a flaw in the pressurizer spray line pipe weld WIB-378, a 4-inch nominal pipe size, 0.437 -inch nominal thickness, pipe-to-elbow weld in the pressurizer spray line. The flaw was characterized per Section XI, Paragraph IWA-3310 and Figure IWA-3310-1 of the ASME Code as a planar flaw. Flaw characteristic calculations were performed to determine acceptability on the basis of IWB-3500, Paragraph IWB-3514.3.

The flaw was initially dispositioned as unacceptable.

Further analytical evaluation, performed in accordance with the methods prescribed in IWB-3600, demonstrate that the weld containing the flaw is acceptable for continued service. The pressurizer spray line pipe weld WIB-378 flaw evaluation report prepared by Structural Integrity Associates is enclosed.

PG&E makes no new or revised regulatory commitments (as defined by NEI 99-04) in this letter. If you have any questions or require additional information, please contact Mr. Hossein Hamzehee at (805) 545-4720.

A member of the STARS (Strategic Teaming and Resource Sharing) Alliance Callaway

• Diablo Canyon

• Palo Verde

• Wolf Creek Document Control Desk November 3, 2015 Page 2-Sincerely, 5 4£L--Barry S. Allen rntt/4231/SAPN 50033145 Enclosure cc: Diablo Distribution cc/enc: Marc L. Dapas, NRC Region IV Administrator PG&E Letter DCL-15-131 Thomas R. Hipschman, NRC Senior Resident Inspector Siva P. Lingam, NRR Project Manager Gonzalo L. Perez, Branch Chief, California Department of Public Health State of California, Pressure Vessel Unit A member of the STARS (Strategic Teaming and Resource Sharing) Alliance Callaway

• Diablo Canyon

• Palo Verde

• Wolf Creek Enclosure PG&E Letter DCL-15-131 Structural Integrity Associates Report No. 1501350.301 Diablo Canyon Power Plant Spray Line Flaw Evaluation Diablo Canyon Power Plant, Unit 1 Evaluation of the Flaw in the 4-inch Spray Line Weld WIB-378 Structural Integrity Associates, Inc. File No.: 1501350.301 Project No.: 1501350 CALCULATION PACKAGE Quality Program Type: Nuclear D Commercial PROJECT NAME: Diablo Canyon Power Plant Spray Line Flaw Evaluation CONTRACT NO.: 3501065975 CLIENT: PLANT: Pacific Gas & Electric Diablo Canyon Power Plant, Unit 1 CALCULATION TITLE: Evaluation of the Flaw in the 4-inch Spray Line Weld WIB-378 Document Revision 0 Affected Pages 1-24 A-1-A-3 B-1 -B-3 C-1 -C-173 Revision Description Initial Issue Project Manager Approval ature & Date N.G.Cofie NGC 1112/15 Pre parer( s) & Checker(s) tures & Date Preparers: C. S. Lohse CSL 1112/15 W. Wong ww 1112/15 Checkers: S. S. Tang SST 1112115 M.Fong MF 1112/15 Page 1 of24 F030 6-01R2 e Structural Integrity Associates, Inc."' Table of Contents

1.0 INTRODUCTION

.........................................................................................................

4 2.0 TECIINICAL APPROACH ..........................................................................................

4 3.0 DESIGN INPUTS ..........................................................................................................

5 3.1 Geo1netry

...........................................................................................................

5 3.2 Loads ..................................................................................................................

5 3.3 Operating Conditions

.........................................................................................

6 3.4 Material ..............................................................................................................

6 3.5 I11dication Size ...................................................................................................

6 3.6 Cause of Cracking ..............................................................................................

6 3.7 Thermal Transients

............................................................................................

7 3.8 Residual Stress ...................................................................................................

8 4.0 CALCULATIONS

.........................................................................................................

8 4.1 Flaw Characterization

........................................................................................

8 4.2 Determination of Stresses and Load Combinations

...........................................

9 4.3 Thermal Transient Stress Analyses and Stress Intensity Factors Determination

.............

.....................................................................................

1 0 4.4 Crack Growth Evaluation

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11 4.4.1 Stress Intensity Factors ..........................

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11 4.4.2 Austenitic Stainless Steel Fatigue Crack Growth Law ......................

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12 4. 4. 3 Loading Combinations and Stresses ................................................................

13 4. 4. 4 Allowable Flaw Size Determination

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................

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13 5.0 RESULTS ....................................................................................................................

13

6.0 CONCLUSION

S

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14

7.0 REFERENCES

.* ...........................................................................................................

15 APPENDIX A NDE lSI EXAMINATION DATA ..............................................................

A-1 APPENDIX B COMPUTER FILE LISTING .......................................................................

B-1 APPENDIX C PC-CRACK OUTPUT FILES ..........................................

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C-1 File No.: 1501350.301 Revision:

0 Page 2 of24 F0 3 06-0 I R 2 e Structural integrity Associates, Inc. List of Tables Table 1: Piping Loads at Node 165 ...............

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16 Table 2: Piping Loads for Calculation of Stresses (Node 165) ..............................................

17 Table 3: Load Combinations for Stress Calculations

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18 Table 4: Primary Stresses .......................................................................................................

19 Table 5: Secondary Stresses ...................................................................................................

19 Table 6: Transient Cycles and Groupings

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20 Table 7: Transients Analyzed in SI-TIFFANY

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21 Table 8: Material Propetiies for A-376 TP 316 ......................................................................

22 Table 9: Fatigue Crack Growth Loadings ..............................................................................

22 Table 10: Initial, Final, and Allowable Flaw Sizes ................................................................

22 List of Figures Figure 1. Is01netric Drawing of the Spray Line ......................................................................

23 Figure 2. Setni-Elliptic Flaw on Inside Surface of a Cylinder ..................................... .........

24 File No.: 1501350.301 Revision:

0 Page 3 of24 F0306-0 I R2 e Structural Integrity Associates, Inc.

1.0 INTRODUCTION

During routine in service inspection of pressurizer spray line welds at Diablo Canyon Power Plant (DCPP), Unit 1 in the Fall2015 1R19 outage, a circwnferential flaw was identified at Weld WIB-378 [1]. The location of this weld is shown in Figure 1 (isometric drawing of the spray line). As can be seen frmn this figure, this weld is located two elbows away frmn the pressurizer.

There is a short vertical line that goes upwards from the pressurizer, followed by a horizontal section and then another vertical pmiion that goes downwards.

The flawed elbow is on the upstream side of the second elbow on the down vet1ical pmiion of the spray line. The possible cause of cracking is discussed in Section 3 .6. This calculation documents an evaluation to determine the acceptability of the circumferential flaw identified in the spray line S6-15, weld WIB-378 at DCPP Unit 1 for continued operation.

Included in the calculation is documentation of loadings, calculation of stresses and stress intensity factors, determination of fatigue crack growth, and the allowable flaw size. Based on the evaluation contained herein, the flawed component is acceptable for continued operation.

The crack will not exceed the ASME Code,Section XI allowable flaw size for the life of the plant (asswning a 60-year operating life). 2.0 TECHNICAL APPROACH The technical approach used for the flaw evaluation consists of using the ASME Code,Section XI, IWB-3600 and Appendix C requiretnents sumtnarized in the following steps: 1. Characterize the flaw and use the Acceptance Standards ofiWB-3500 (specifically Table IWB-3514-2) of the ASME Code,Section XI [3] to determine if a detailed flaw evaluation is required per IWB-3600.

If required, perfonn a detailed flaw evaluation.

As will be explained later, the rules of IWB-3600 are used in this evaluation.

2. Determine the stresses at the flaw location.

Since the flaw is in the circmnferential direction, the stresses required are the axial stresses.

The loadings considered in this evaluation include pressure, deadweight, thermal expansion, seismic (inetiial and anchor movements), residual, and thermal transient stresses.

3. Determine the ASME Code,Section XI allowable flaw size for austenitic stainless steel piping in IWB-3640 and Appendix C [3]. 4. Determine thennal transients applicable to this piping location.

5. Calculate stress intensity factors for the thermal transients and other loadings.

6. Perform a crack growth evaluation to determine how long it will take the as-found flaw to reach the ASME Code,Section XI allowable flaw size determined in Step 3. 7. Cmnpare the end of the evaluation period flaw (after fatigue crack growth) to the ASME Code,Section XI allowable flaw size to determine acceptability for operation tlu*ough the evaluation period. The current version of ASME Code,Section XI used at DCPP is the 2001 Edition with Addenda tlu*ough 2003 [3]. File No.: 1501350.301 Revision:

0 Page 4 of24 F0306-0 I R2 e Structural Integrity Associates, Inc. Two computer 'programs verified under Structural Integrity Associates (SI) Quality Assurance (QA) program are used to facilitate the calculations in this evaluation.

These cmnputer programs are TIFFANY [8] and pc-CRACK [9]. The software SI-TIFFANY

[8] perfonns thermal stress and stress intensity factor analysis of a pipe with a specified temperature/flow history of the fluid inside the pipe. The end result of the software output is tables of the 1naxin1um and 1ninimum stress intensity factor for ID part-through circumferential or axial flaws for selected crack sizes. In this calculation, SI-TIFFANY is used to calculate the thermal transient stress and tninimuin and maximum stress intensity factor distributions for the bounding thermal transient(s).

These 1naximwn and 1ninimum stress intensity factors are used for the fatigue crack growth evaluation.

The fatigue crack growth evaluation is performed using pc-CRACK [9]. pc-CRACK [9] is a Windows-based software for the fracture 1nechanics analysis of cracks in materials.

Analysis procedures are based on linear elastic fracture tnechanics (LEFM) or elastic-plastic fracture tnechanics (EPFM). The code can be used for a very wide range of crack geometries subjected to a variety of stress states. Smne 35 LEFM and 15 EPFM crack configurations are included, several with influence functions that allow consideration of arbitrary stress distributions.

pc-CRACK can compute critical crack size, allowable flaw size based on the ASME Code, and the life of a cmnponent subjected to sub-critical crack growth such as fatigue, stress corrosion cracking (SCC) or primary water stress corrosion cracking (PWSCC). In this calculation, pc-CRACK is used to calculate the fatigue crack growth and to detennine the flaw acceptability (stability) using the rules of ASME Code,Section XI, Appendix C [3]. 3.0 DESIGN INPUTS 3.1 Geounetry Nmninal pipe size (NPS) = 4 inch [5] Pipe outside diameter (OD) = 4.5 inches [5] Nominal pipe thickness=

0.437 inches [5] Actualtneasured pipe thickness are all thicker than 0.452 inches [1] In this evaluation, the nmninal thickness will be conservatively used as it results in a larger a/t and larger stre&B;J s. -3.2 Loads All piping loads for this analysis are taken from Reference

7. The location of the flaw is shown in Figure 1. The node in the piping analysis [7] is node 165. Multiple load cases are provided in Reference

7. All the load cases in Reference 7 are contained in Table 1. To account for any future updates of the piping loads due to changes in the piping analysis, the loads are conservatively increased by a 50% factor. Table 2 presents the loads in different units and includes the 50% increase.

The loads are fwiher explained in the calculation of stresses.

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0 Page 5 of24 F0306-0IR2 e Structural Integrity Associates, Inc.'" 3.3 Operating Conditions Reference 6 defines the operating conditions for the spray line. The spray line is line 15 in Reference

6. Four operating conditions are defined [6, pg. 11]. Page 46 of Reference 6 defines the temperatures and pressures for the four conditions.

In order to bound all the operating conditions, the enveloped condition listed in Reference 6 is used and the pressure and tetnperature are shown below. Discussion of the thermal transients applicable to this location is contained in Section 3.7. Internal Pressure=

2510 psig [6, pg. 46, enveloped condition used] Tetnperature

= 650°F [6, pg. 46, enveloped condition used] 3.4 Material The tnaterial of the piping is A-376 TP 316 austenitic stainless steel and the elbow is A-403 Type 316 [5]. Reference 2 identifies the weld as being stainless steel (Type 308) and using both GTA Wand SMA W welding processes.

As a flux type weld is used, the elastic plastic fracture tnechanics method of the ASME Code,Section XI, Appendix C will be required for the allowable flaw size detennination.

For the flaw evaluation, the flow stress of the material is required.

At a temperature of 650°F, the stainless steel material properties are as follows (SA-376 TP 316 properties used): Sy = 18.5 ksi [4] Su = 71.8 ksi [ 4] ay= 45.15 ksi (average of Sy and Su) 3.5 Indication Size One circumferential indication was identified in the weld [1]. A page frmn the NDE report and the indication sketch is contained in Appendix A of this calculation.

Length= 0.625 inch [1] Maxitnmn flaw depth= 0.08 inch [1] Flaw depth-to-thickness ratio (a/t) = 0.183 (based on nominal thickness) 3.6 Cause of Cracking A thorough root cause of the cracking cmmot be undetiaken since the flawed component was not retnoved from service. Possible causes of the cracking include:

• Thennal fatigue from thennal transients and thermal stratification

• Stress corrosion cracking

• Fabrication defect File No.: 1501350.301 Revision:

0 Page 6 of24 F0306-0 I R2 e Structural Integrity Associates, Inc. Although not very conclusive, the crack like indication identified in Reference 1 is noted as being ID connected for conservatism.

The indication plot [1] (Appendix A) shows the indication located 90 degrees frmn the intrados and extrados of the elbow. One of the concerns is that stratification may occur in the spray line. Stratification would occur if there was low flow in the spray line that did not fill up the horizontal portion of the piping. If the flow did not fill the pipe, hot steam from the pressurizer could fill up the top portion of the spray line and create a stratified condition with hot steam on the top and colder water on the bottom. If stratification were to occur, it would cause a bending moment in the upper portion of the spray line. This would cause high stresses in the intrados or extrados of the elbow. As the indication is located 90 degrees frmn the intrados and extrados, it does not appear that stratification would be the cause as the location is at the neutral axis for the bending moment. As noted in Reference 10, the plant is operated with a constant spray flow for normal operations with main spray always available.

Having a constant spray flow reduces the risk of stratifying the upper spray line. One other possible apparent cause could be stress corrosion cracking.

However as the system is in constant operation and there is very little oxygen in the system, the risk of stress corrosion cracking is small. DCPP has also perfonned other evaluations that has eliminated stress corrosion cracking as a plausible degradation mechanism in the reactor coolant systetn. During the NDE of this weld, PGE examiners observed that the flaw produced a very sharp signal with limited reflection at any skew angle indicating that it is likely planar and "smooth surfaced" like a lack of fusion, and not like a multi-faceted stress corrosion flaw or thermal fatigue striations.

The flaw was not seen on the original construction radiograph mostly ruling out a volumetric inclusion type defect. As thennal stratification and SCC are not likely causes and the defect appears to be associated with a lack of fusion, the only mechanistn that will lead to flaw growth is due to thermal transients and thermal cycling. As such, the fatigue crack growth evaluation is appropriate as the thermal transient cycles are considered.

3. 7 Thermal Transients The spray line is used for pulling water off of the cold legs and injecting it into the top of the pressurizer through the spray nozzle. The pressurizer runs at a higher temperature than the cold leg of the reactor coolant systetn. As shown in Figure 1, this location is two elbows retnoved fron1 the spray nozzle ofthe pressurizer.

Therefore, it is conservatively assumed that this location will see transients sitnilar to the pressurizer spray nozzle. The pressurizer spray nozzle is located in the steam space of the pressurizer.

As such, it is subject to a steatn condition at the pressurizer temperature.

As the flaw is located on the lower half of the 2nd elbow, it would be expected to be full of water as some constant flow of water is present in the spray line. Therefore, this location would not be subjected to a cold shock (due to the cold fluid from the cold leg) and then a hot shock (due to reflood of the steam in the pressurizer space) which is typical for a pressurizer spray nozzle. However, it is still subjected to a cold shock of water as this potiion of the spray line will be closer to the pressurizer tetnperature and will see colder water frmn the cold leg side of File No.: 1501350.301 Revision:

0 Page 7 of24 F 0 30 6-0 I R 2 e Structural integrity Associates, Inc.'" the plant. Since it will retnain filled with water, after flow stops, it would slowly transition back to near the pressurizer temperature.

For this evaluation a few bounding thermal transients for the pressurizer spray nozzle are considered at the flaw location.

Reference 1 0 lists the pressurizer spray nozzle transients, nmnber of cycles, and temperature changes for the DCPP life of 50 years. The transients sta11 at a constant temperature and then a shock of cold water occurs for some time duration until the flow of water stops. As all transients are sitnilar, a group of five transients is developed based on the temperature change value. Table 6 lists the group of transients and number of cycles. The maxilnmn flow rate for the spray nozzle is used for all transients which is 800 gpm [10]. Each event is assumed to stat1 at 650°F. The actual operating pressurizer te1nperature is 653°F, but since this location is slightly removed frmn the pressurizer, a value of 650°F is reasonable and chosen for shnplicity.

Note that all transients do not occur at full temperature.

Some of the heatup and cooldown transients occur at a lower tetnperature, however, using the higher temperature is conservative. The five transient definitions to be analyzed are listed in Table 7. The tilnes, te1nperatures, pressures, and flow rates are defined in this table. As shown in the table, the full pressure is assmned for all conditions.

This will be conservative as the spray nozzle does not see pressure variations during the transients, so using the higher pressure will give a higher tnean stress (higher constant stress intensity factor) which is conservative.

The ramp back to full te1nperature is assumed to occur over 300 seconds. 3.8 Residual Stress The residual stresses in the weld are required for the crack growth evaluation.

For this evaluation, a constant tensile residual stress will be assumed. The value assumed is the room temperature yield strength of the tnaterial, which is 30 ksi [4] for Type 316 stainless steel. Using this value is conservative as the axial residual stresses in piping are required to balance through the wall thickness to retnain in equilibrium which is represented by a linear through-wall bending stress that is compressive on the ID and tensile on the OD. Assuming a constant tensile stress is not realistic, but is conservative as it gives a higher mean stress for the evaluation which leads to higher crack growth rates. 4.0 CALCULATIONS 4.1 Flaw Characterization .... *.Since oniy one circumferential flaw was identified

,.the flaw cmnbination rules of ASME Code,Section XI, IW A-3300 do not apply. The characterized flaw length is 0.625 inch and the flaw depth is 0.08 inch [1] (see Appendix A). The actualtneasured thickness at the flaw location varies, but is greater than 0.452 inches, therefore, the nmninal pipe wall thickness of 0.437 inches is conservatively used for a flaw-depth to-thickness ratio of0.183 and an aspect ratio of0.128. Using Table IWB-3514-2 of ASME Code Section XI, this flaw does not meet the Acceptance Standards and, therefore, will need to be evaluated per the flaw evaluation procedures of IWB-3600.

File No.: 1501350.301 Revision:

0 Page 8 of24 F 0 30 6-0 I R2 lJ Structural Integrity Associates, Inc. 4.2 Determination of Stresses and Load Combinations The stresses are calculated based on the piping loads frmn Reference 7 and contained in Tables 1 and 2. A description of the loads is given below. After the description, the load cmnbinations for all service levels are described.

Deadweight (DW)-Deadweight of piping syste1n Thermal I through 4-Four thennal expansion conditions described in Reference

6. The bounding condition is used. The bounding thennalload is labeled at TH. SAM DE-Seismic anchor tnovements from DE condition (Shnilar to OBE) SAM DD-Seismic anchor movements from DD condition (Siinilar to SSE) SAM HS-Seismic anchor movetnents frmn HS condition (Faulted seistnic condition specific to DCPP) Seismic DX/DZ-Inet1ia seismic loads for DE conditions.

Only the bounding loads frmn DX or DZ are used. This is labeled as DE in the text. Seismic XD/ZD-Inertia seismic loads from DD condition.

Only the bounding loads from XD or ZD are used. This is labeled as DD in the text. Seismic HX/HZ -Inertia seistnic loads frmn HS condition.

Only the bounding loads from HX or HZ are used. This is labeled as HS in the text. With the definition of the piping loadings, the load combinations for each service level are defined as: Primary Loads Service Level A -D W + Pressure (P) Service Level B-DW + P +DE Service Level C-DW + P + DD Service Level D-DW + P + HS Secondary Loads Service Level A-TH Service Level B-TH + SAM DE Service Level C-TH + SAM DD Service Level D -TH + SAM HS The load cotnbinations are shown in Table 3. The piping stresses are calculated based on pressure and external bending tnoments using equations frmn Appendix C, Section C-2500 [3] as described as follows. Primary tnetnbrane stress ( Oin) is given by: Oin = PD/(4t) + F/A, where: P operating pressure for the service level being considered D outside diatneter of the component t thickness, consistent with the location at which the outside diameter is taken File No.: 1501350.301 Page 9 of24 Revision:

0 F0306-0 I R2

!\SJ Structural Integrity Associates, Inc. F resultant force for the appropriate primary load cmnbination for each Service Level A cross sectional area of the pipe Primary bending stress ( m) is given by: m = DMb/(21), where: D outside dimneter of the component d inside diameter, consistent with the point at which the outside diameter is taken Mb resultant tnmnent for the appropriate primary load co'mbination for each Service Level I moment of inertia, (n:/64) (D 4-cf) Secondary bending stress (a-e) is given by: O"e = DMe/(21), where: D outside dimneter of the component d inside diameter, consistent with the point at which the outside diameter is taken Me resultant moment for the appropriate secondary load combination for each Service Level (includes seis1nic anchor loads and thermal expansion)

I tnmnent of inertia, (n:/64) (D 4-cf) For this evaluation, the forces are conservatively considered a tnembrane stress and added to the pressure cmnponent.

Secondary forces are also added to the secondary bending stress tenn for conservatism.

The stress for the secondary forces are calculated as F I A, where F is the resultant force and A is the area of the piping. The calculation of stresses is shown in Tables 4 and 5. 4.3 Thermal Transient Stress Analyses and Stress Intensity Factors Determination Tables 6 and 7 list the transients that are evaluated for the flawed location.

The transients in Table 7 are *evaluated with SI-TIFFANY to detennine the transient stresses and stress intensity factors. A total of five SI-TIFFANY runs are made. Construction of the input files for each transient involves inserting each transient titne history into an input file. A ti1ne step ofO.Ol seconds is used in all SI-TIFFANY runs. Alltnaterial properties used for the SI-TIFFANY runs are contained in Table 8. Each SI-TIFF ANY run with the corresponding filenmne has the following relevant files, which are included as supporting files to this calculation:

• .dat SI-TIFFANY input file * .rpt SI-TIFFANY output file, which echoes the inputs. File No.: 1501350.301 Page 10 of 24 Revision:

0 F0306-0l R2 e Structural Integrity Associates, Inc. *.mnn SI-TIFFANY output file with tabulated Kmin values. *.Inxn SI-TIFFANY output file with tabulated Kmm( values. The tabulated values of the Ininitnum and maximum stress intensity factors, Kmin and Kmax, for specific crack sizes are used for fatigue crack growth analysis.

All SI-TIFFANY files are listed in Appendix B. SI-TIFFANY uses tetnperature history of the transient to compute the thermal stress due to the radial gradient of the temperature in the pipe wall. At the beginning of the transient, the piping location is taken to be at a uniform temperature equal to the first line in the transient history. The radial gradient thermal stress is then cmnbined with the pressure stress and thermal expansion stresses due to tensile and bending loads (restraint of thermal expansion) to provide stresses that are used to calculate stress intensity factors. The thermal expansion tension and bending stress at the beginning of the transient is taken to be the stress due to the resultant force and mmnent of the restraint of thetmal expansion, which are obtained from the loads in Table 2, scaled up or down from the normal operating tetnperature using the following relation: (T ) Ta ve -70 (J ave = (Jno T,IO -70 This relation is applied to tension and bending thermal expansion stresses to scale the values during the transient.

Tno is 650.0oF (normal operation tetnperature).

Tave is the average wall temperature, which is evaluated in SI-TIFFANY.

The values of (Jno(nominal stress) for tension and bending were calculated using the equations from Section 4.2 and the loads from Table 2. The values of (Jno t e nsion and (Jno b e ndin g frmn thermal expansion input to SI-TIFFANY are 0.077 ksi and 1.241 ksi, respectively.

Stresses due to deadweight and OBE are input separately in the subsequent crack growth calculation.

Pressure stresses do not need to be input to SI-TIFFANY separately.

Only the pressure term is included as SI-TIFFANY calculates the stresses due to pressure.

SI-TIFFANY treats the piping as insulated and the insulation is considered perfect which tneans that no heat transfer is considered to the surrounding enviromnent.

The piping is insulated as noted in the ison1etric drawing shown in Figure 1. 4.4 Crack Growth Evaluation 4.4.1 Stress Intensity Factors SI-TIFF ANY calculated stress intensity factors (K) and determined tnaxiinuin applied K (Kmax) and 1ninhnmn applied l( (Kmin) for a semi-elliptical inside-surface flaw in a cylinder for various flaw depths and aspect ratios. The Kmax and Kmin values include the effects of internal pressure, thermal expansion piping loads, and thermal transient stresses.

Kmax and Kmin represent the range of applied K for each transient whose difference, = Kmax-Kmin, are used by pc-CRACK for the fatigue crack growth (FCG) calculations.

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0 Page 11 of24 F0306-0 I R2 e Structural Integrity Associates, Inc ... The constant stress intensity values for deadweight and residual stress were not included in SI-TIFFANY.

As such, they are input as constant stress values for each load cycle. The semi-elliptical flaw model is used in pc-CRACK to determine the fatigue crack growth. The flaw model is shown in Figure 2. 4.4.2 Austenitic Stainless Steel Fatigue Crack Growth Law The ASME Code has developed new fatigue crack growth laws for austenitic stainless steels in PWR water environments.

However, these new laws have not been published and as such, they have not been endorsed by the US NRC. As such, the fatigue crack growth law for austenitic steels in air currently approved in ASME Section XI, Appendix C is used in the FCG calculation with an appropriate environmental factor to account for the PWR environment (see below). This crack growth law is built into pc-CRACK and is based on the crack growth law for austenitic steels published in Appendix C of Section XI of the ASME Code [3]. Since the built-in crack growth law is for stainless steel in air, a tnultiplication factor of2 for the PWR environment

[11] is employed.

This factor of2 is accounted for in the crack growth evaluation by multiplying the number of cycles for each transient by 2. This factor of 2 is included in the number of cycles used for evaluation in Table 6. Crack growth is computed on a yearly basis to determine how long it will take the initial flaw size to reach the allowable flaw size. The nutnber of cycles is given in Table 6. da =C (M)n dN a where: Co =CS log 10 C = -10.009 + 8.12x1 0-4 T -1.13x1 0-6 T 2 + 1.02x1 0-9 T 3 l l R 0 S = 1 + 1.8R 0 < R 0.79 -43.35 + 57.97 R 0.79 < R < 1.0 n = 3.3 Tis temperature in °F, which is taken to be the maximmn temperature during the transient.

For this evaluation the temperature value is 650°F. The above constants provide crack growth rates in inches per File No.: 1501350.301 Revision:

0 Page 12 of24 F0306-0 1 R 2 S} Structural Integrity Associates, Inc."' cycle when K is in ksi-in 112* The evaluation is performed with a constant aspect ratio and also a variable aspect ratio. The limiting result from both evaluations is used. 4. 4. 3 Loading Combinations and Stresses SI-TIFFANY was used to obtain tables oftnaxiinum applied K (Kmax) and miniinum applied K (Kmin) for various flaw depths and aspect ratios due to system transients.

The Kmax values are contained in the filenames with MXN file extension and the Kmin values are contained in the filenames with MNN file extension.

The maximmn and minimum K for crack growth cycles are sitnply the Kmax and Kmin tables output frmn SI-TIFFANY, with deadweight and weld residual stress added to both the max and min of the cycle. Deadweight stresses are calculated from the loads given in Table 2. Deadweight and residual stress loads do not cycle, but are present in both the maximum and minimum of the cycle. The fatigue crack growth also needs to include OBE(DE). OBE(DE) is assumed to occur at the steady state plant condition, but steady state results were not calculated in any SI-TIFFANY runs. Therefore, OBE(DE) was considered to occur with the loading/unloading bounding transient.

Four hundred ( 400) OBE(DE) cycles are considered over the 50 year plant life [1 0]. Therefore, eight (8) cycles are considered each year. This number is doubled to account for a PWR environment, so sixteen (16) cycles are considered in the evaluation for each year. Table 9 defines the loading combinations used for each event evaluated in pc-CRACK. 4. 4. 4 Allowable Flaw Size Determination After the fatigue crack growth is performed, the final flaw size has to be checked against th.e allowable flaw sizes in the ASME Code,Section XI, Appendix C. pc-CRACK is used to determine the allowable flaw sizes. As stated earlier, the weld was manufactured partly with a SMA W process and, therefore, requires the use of elastic plastic fracture tnechanics (EPFM). The EPFM rules are contained in Article C-6000 of Section XI [3]. Each service level is checked by inputting pipe gemnetry, crack paratneters, and stresses appropriate for the service level. For this calculation, the initial flaw size is input into the progratn.

Based on the stress ratios, it gives the allowable flaw size tables (a/t (flaw depth/pipe thickness) and 1/c (flaw length/pipe circmnference) values), which can be used to determine the maximmn length and depth of the flaw. The pc-CRACK output files for the allowable flaw sizes are contained in Appendix C. 5.0 RESULTS The results of the evaluation are contained in Table 10. Table 10 contains the initial flaw size and the final flaw sizes using the two aspect ratio assmnptions.

It also contains a single bounding limiting allowable flaw size from all service levels. For the loadings, the limiting flaw size is from the tnembrane only check for Service Level A (see Appendix C) and this is the value reported in Table 10. As can be seen from this table, the allowable flaw depth is relatively large (75% of pipe wall thickness which is the tnaximum allowed by the ASME Code,Section XI). File No.: 1501350.301 Revision:

0 Page 13 of24 F0306-0 I R2 SJ Structural Integrity Associates, Inc."' For the fatigue crack growth evaluation, the flaw was grown under two conditions.

The first approach used a fixed-aspect ratio where the flaw aspect ratio remains constant as the flaw grows. The second approach used a variable aspect ratio where the length and depth of the flaws are allowed to grow independently from one another. As shown in Table 10, both the variable and fixed aspect ratios yield about the smne results. Looking at the output files in Appendix C, using a fixed aspect ratio is slightly n1ore conservative.

Nevertheless, the results show that using the grouped loadings, the flaw does not exceed the ASME Code,Section XI allowable flaw size for the remainder of the plant life (assuming a 60-year operating period). All files used in the analysis are listed in Appendix B. The results in Table 10 include the end of evaluation period flaw sizes for both growth conditions.

In order to show flaw acceptability, both the flaw depth and length must be acceptable as the ASME Code,Section XI has depth li1nits for defined flaw lengths. The flaw depth ratio (a/t) is compared to the ASME Code,Section XI allowable depth. If that depth is acceptable, then the flaw length ratio (1/circ) is compared to the ASME Code,Section XI allowable length. As shown in Table 10, both of these values are acceptable.

6.0 CONCLUSION

S The evaluation presented in this report has shown that the flawed weld in the spray line at DCPP, Unit 1 is acceptable for continued operation.

Using the bounding loads assumption, the flaw is acceptable for the remainder of the plant life (assuming a 60-year operating period). File No.: 1501350.301 Revision:

0 ... :.;, ,: Page 14 of24 F0 3 06-0 1 R 2 e Structural Integrity Associates, Inc.

7.0 REFERENCES

1. DCPP Design Input Transtnittal No. DIT-50809162-001-00, "Diablo Canyon Unit 1 Pressurizer Spray Line Flaw Evaluation," Attachment 7, Exam Data Sheet and Indication Sketch for Weld No. WIB-378, SI File No. 1501350.206.

2. DCPP Design Input Transmittal No. DIT-50809162-001-00, "Diablo Canyon Unit 1 Pressurizer Spray Line Flaw Evaluation," Attachment 6, Spray Line Welding Records, SI File No. 1501350.206.

3. ASME Boiler and Pressure Vessel Code,Section XI, 2001 Edition, with Addenda through 2003. 4. ASME Boiler and Pressure Vessel Code,Section II, Part D, 2001 Edition, with Addenda tluough 2003. 5. DCPP Design Input Transmittal No. DIT-50809162-001-00, "Diablo Canyon Unit 1 Pressurizer Spray Line Flaw Evaluation," Attachment 5, Engineering Calculation No. 3-104 and attached specification and isometric, SI File No. 1501350.206.

6. DCPP Design Input Transmittal No. DIT-50809162-001-00, "Diablo Canyon Unit 1 Pressurizer Spray Line Flaw Evaluation," Attachment 4, PG&E DCM No. M-46, Rev. 44, "Design Criteria!

Memorandmn M-46, Piping Pressure, Tetnperatures and Operation Modes," SI File No. 1501350.206.

7. DCPP Design Input Transmittal No. DIT-50809162-001-00, "Diablo Canyon Unit 1 Pressurizer Spray Line Flaw Evaluation," ME101 File, Problem No. 3-104, Rev. 5, SI File Nos. 1501350.203 and 1501350.206.

8. SI-TIFFANY 3.0, Structural Integrity Associates, Septetnber 15,2015. 9. pc-CRACK 4.1 CS, Version Control No. 4.1.0.0, Structural Integrity Associates , Decen1ber 31, 2013. 10. DCPP Design Input Transtnittal No. DIT-50809162-001-00, "Diablo Canyon Unit 1 Pressurizer Spray Line Flaw Evaluation," Attachments 1 through 3, FSAR and Transient Definitions, SI File No. 1501350.206.

11.Section XI Task Group for Piping Flaw Evaluation, ASME Code, "Evaluation of Flaws in Austenitic Steel Piping," Journal ofPressure Vessel Technology, Vol. 108, August 1986. File No.: 1501350.301 Revision:

0 Page 15 of24 F0306-0 1 R2 e Structural Integrity Associates, Inc.'" Table 1: Piping Loads at Node 165 Load Case FA (lb) FB (lb) Deadweight 211 18 Thermal! 316 52 Thermal2 12 113 Therma13 276 69 Therma14 9 15 SAM DE 57 43 SAMDD 115 86 SAMHS 41 25 Seismic DX 83 177 Seismic DZ 31 152 Seismic XD 139 301 Seismic ZD 53 271 Seismic HX 146 598 Seismic HZ 100 680 Note: Absolute values are used for all loads. File No.: 1501350.301 Revision:

0 FC (lb) MA (ft-lb) MB (ft-lb) 9 3 73 8 6 117 37 15 120 '* 14 5 125 4 0 16 12 20 53 24 40 105 8 12 35 682 738 229 227 235 87 1136 1230 381 384 396 148 864 906 407 443 362 264 MC (ft-lb) Page Number from ME101 File [7] 179 A-536 312 A-578 307 A-618 334 A-658 44 A-698 96 A-740 192 A-782 56 A-824 104 A-1073 69 A-1125 179 A-1177 122 A-1229 278 A-1281 296 A-1333 Page 16 of24 F0 306-0 I R 2

(}Structural Integrity Associates, Inc. Table 2: Piping Loads for Calculation of Stresses (Node 165) Load Case FA (lb) FB (lb) FC (lb) MA (in-lb) MB (in-lb) MC (in-lb) Fsrss {lb) Msrss (in-lb) Deadweight 317 27 14 54 1314 3222 318 3480 Thermal1 474 78 12 108 2106 5616 481 5999 Thermal2 18 170 56 270 2160 5526 179 5939 Thermal3 414 104 21 90 2250 6012 427 6420 Thermal4 14 23 6 0 288 792 27 843 SAM DE 86 65 18 360 954 1728 109 2006 SAMDD 173 129 36 720 1890 3456 218 4004 SAMHS 62 38 12 216 630 1008 73 1208 Seismic DX 125 266 1023 13284 4122 1872 1064 14034 Seismic DZ 47 228 341 4230 1566 1242 412 4678 Seismic XD 209 452 1704 22140 6858 3222 1775 23401 Seismic ZD 80 407 576 7128 2664 2196 709 7920 Seismic HX 219 897 1296 16308 7326 5004 1591 18565 Seismic HZ 150 1020 665 6516 4752 5328 1227 9666 Notes: 1. The bounding thermal case is determined fi*om the largest square root of the sum of the squares of the moments and is shown in bold. 2. Only the bounding seismic direction is required to be evaluated.

For the DE, DD, and HS seismic loadings, the bounding loads from either the X or Z direction are used. These are shown in bold. 3. These piping loads are given in the local coordinate system. A is the axial direction, so FA is the axial force and MB and MC are the bending moments. 4. All loads are increased by a factor of 1.5 to account for any potential changes in the piping analyses.

File No.: 1501350.301 Revision:

0 Page 17 of24 F 0306-0 I R 2 SJ Structural Integrity Associates, Inc.'" Table 3: Load Combinations for Stress Calculations Load Combinations FA (lb) Service Level A Service Level B Service Level C Service Level D Service Level A Service Level B Service Level C Service Level D File No.: 1501350.301 Revision:

0 317 441 525 536 414 500 587 476 Load Combinations for Primary Loads FB (lb) FC (lb) MA (in-lb) MB (in-lb) MC (in-lb) 27 14 54 1314 3222 293 1037 13338 5436 5094 479 1718 22194 8172 6444 924 1310 16362 8640 8226 Load Combinations for Secondary Loads 104 21 90 2250 6012 168 39 450 3204 7740 233 57 810 4140 9468 141 33 306 2880 7020 Fms (lb) Mms (in-lb) 318 3480 1164 15277 1859 24513 1690 20249 427 6420 528 8389 633 10365 497 7594 Page 18 of24 F0306-0 I R2 e Structural Integrity Associates, Inc. Table 4: Primary Stresses Load Combinations Pressure (psi) Force (psi) Moment (psi) Service Level A 6462 57 672 Service Level B 6462 209 2952 S ervice Level C 6462 333 4737 Service Level D 6462 303 3913 Table 5: Secondary Stresses File No.: 15 013 5 0.301 Revision:

0 Load Combinations Service Level A Service Level B Service Level C Service Level D Force (psi) Moment (psi) 77 1241 95 1621 114 2003 89 1467 Gm (psi) Gb (psi) 6519 672 6670 2952 6795 4737 6765 3913 Ge (psi) 1317 1716 2117 1557 Page 19 of24 F0306-0 I R2

{J Structural Integrity Associates, Inc. Table 6: Transient Cycles and Groupings Transients Cycles for 50 years Spray Nozzle COF) Normal Heatup 1200 320 Cooldown (Case I) 1200 320 Cooldown (Case II) 200 405 Cooldown (Case II) 1000 320 Unit Loading 18300 125 Unit Unloading 18300 125 Large Step Decrease 250 128 Step Load Increase 2500 128 Step Load Decrease 2500 126 Boron Concentration Equalization 32000 125 Upset Loss ofLoad 7 100 143 Inadvertent Aux Spray 12 553 Bounding Event Cycles Total Events with 125°F 68600 Total Events with 320°F T 4 3500 Total Events with 128°F 5250 Inadvertent Aux Spray 12 Cooldown Case II 200 Number of Cycles for 1 Year (=Total cycles/50)

Total Events with 125°F 1372 Total Events with 320°F T 4 70 Total Events with l28°F 105 Inadvetient Aux Spray 2 0.24 Cooldown Case II 4 Number of Cycles for 1 Year (used in analysis)1 Total Events with l25°F T 5 2744 Total Events with 320°F T 4 140 Total Events with l28°F T 6 210 Inadvetient Aux Spray 2 Cooldown Case II 8 .. Notes: 1. The number of cycles used m the analysts IS doubled to account for a PWR water environment.

This is required as the stainless steel fatigue crack growth law is given in air. 2. The inadvetient auxiliary spray event has less than one cycle per year. Therefore, it is conservatively assumed that one cycle per year occurs. 3. All infonnation is obtained from Reference

10. 4. This event is referred to as heatup/cooldown (HU/CD) in the analysis files. 5. This event is referred to as unload or load in the analysis files. 6. This event is referred to as step load inc or dec in the analysis files. 7. The loss of load transient is included with the 320°F T events. File No.: 1501350.301 Revision:

0 Page 20 of24 F 0 3 06-0 1 R 2 e Structural Integrity Associates, Inc. Table 7: Transients Analyzed in SI-TIFFANY Transient Time (sec) Temperature eF) Pressure (psig) Flow Rate (gpm) Heatup/Cooldown 0 650 2510 800 L).T (°F) = 320 0.1 330 2510 800 60.1 330 2510 800 360.1 650 2510 800 960.1 650 2510 800 Cooldown II 0 650 2510 800 L).T (°F) = 405 0.1 245 2510 800 60.1 245 2510 800 360.1 650 2510 800 960.1 650 2510 800 Loading/Unloading 0 650 2510 800 L).T (°F) = 125 0.1 525 2510 800 60.1 525 2510 800 360.1 650 2510 800 960.1 650 2510 800 Step Load Inc/Dec 0 650 2510 800 L).T (°F) = 128 0.1 522 2510 800 60.1 522 2510 800 360.1 650 2510 800 960.1 650 2510 800 Inadvertent Aux 0 650 2510 800 1 Spray L).T (°F) = 553 0.1 97 2510 800 1 300.1 97 2510 800 1 600.1 650 2510 800 1 1200.1 650 2510 800 1 Notes: 1. The inadvetient aux spray transient actually occurs at 200 gpm [1 0]. 800 gpm is used here for conservatism.

2. For information on transient development, see Section 3.7. File No.: 1501350.301 Revision:

0 Page 21 of24 F030 6-0 IR 2 e Structural Integrity Associates, Inc. Table 8: Material Properties for A-376 TP 316 Material Prope1iy Units Spray Line Normal Operating Temperature op 650 Young's Modulus ksi 25050 Poisson's Ratio --0.3 Density lb/in 3 0.283 Specific Heat BTU/lb-°F 0.133 Coefficient of Thermal Expansion op-1 9.9 x w-6 Thermal Conductivity BTU/sec-in-°F 2.52 x Io-4 Note: 1. Material prope1iies are taken at a temperature of 650 op from Reference

[ 4]. Table 9: Fatigue Crack Growth Loadings Event Kmax Kmin Heatup/Cooldown HUCDmax, DW, Residual HUCDmin, DW, Residual Cooldown II CDIImax, DW, Residual CDIImin, DW, Residual Loading/Unloading Unloadm ax , DW, Residual Unloadmin, DW, Residual Step Load Inc/Dec SLIDma x , DW, Residual SLIDmin, DW, Residual Inadve1ient Aux IASma x , DW, Residual IASmin, DW, Residual Spray OBE Unloadmax, DW, Residual, 2*0BE Unloadmax, DW, Residual Table 10: Initial, Final, and Allowable Flaw Sizes Flaw Depth (in) Length (in) Initial 0.08 0.625 Final-Fixed 0.3258 2.545 Final-Variable 0.3276 1.553 Allowable 0.3278 4.241 Notes: 1. aft is the ratio of the flaw depth to the pipe wall thickness.

2. )/eire is the ratio of the flaw length to the pipe circumference.

File No.: 1501350.301 Revision:

0 a/t<I) l/circ<2) Years 0.18 0.044 N/A 0.75 0.180 75 0.75 0.110 81 0.75 0.300 N/A Page 22 of24 F0306-01 R2 SJ S tructural Integrity Associates, Inc.'" Figure 1. Isometric Drawing of the Spray Line L(!E , END. _____.£_

.. Pt'.>_, ,....------t

jl(E D ;

;,,; Note: Location of the flaw is circles in the picture. The node of interest is # 165. Dr a wing is from Reference

5. File No.: 1501350.301 Revision:

0 Page 23 of24 F0306-0 I R2 e Structural Integrity Associates, Inc. cr Figure 2. Semi-Elliptic Flaw on Inside Surface of a Cylinder File No.: 1501350.301 Revision:

0 Page 24 of24 F0306-0 I R2 e Structural Integrity Associates, Inc."' APPENDIX A NDE lSI EXAMINATION DATA File No.: 1501350.301 Revision:

0 Page A-I of A-3 F0306-0IR2 S} Structural Integrity Associates, Inc."' 69-21802 10/01/14 DlirnLOCANYONPOWERPLANT NDEPDI-UT-2 ATTACHMENTll.3 TITLE: Exam Data Sheet DCPPUnit:

1 Procedtu"e Revision 111 Outage: j1RI9 I *Line#: I ISO#: I WeldlD: S6-15-4 1.4-29 WIB-378 Component Configuration Diameter.

4" nominal Thickness Upsb*e am: T.,Nom.: 0.437" Thickness Centerline:

Config.: Pipe to Elbow Thiclmess Downstream:

Crown 0.8" Coun te rbore Width: Upstream:

Covemge: >99% (Note 3) Counterbore Downstream:

Scan Information SearcltUnit Upstream. Weld Downstream Scan Angle Mode Ax Circ. Ax Clrc. Ax Ciro. dB Nole 45° sw X X X X X X 35.5 I 60° sw X X X X X X 41.0 1&2 70° sw X X X 48.5 I Notes l Sketcll: I. Linear flaw, see attached indication sheet and plot. 2. Very low amplitude root geometry noted witlt the 60° D IT-50809162-001-00 Page 27 of28 Attachment 7, Page 1 of 2 Page 1 of! Page: I 6 I of I 10 0.413" 0.487" 0.470" None None Exam Indications Flaw flaw None Oeom Ace. Reject X X X 3. 70"limited on intrados of elbow for 4" circumferential dist11nce. 60" angle at the intrados did not cover a triangular area of 0.1" x 0.05" (0.0025 sqlin). Exam box area 3.1" x 0.15" = 0.465 sq/in. Exam Strut Time: 2340 Personnel Name Examiner:

Michael Leger Exnminer:

J amie I(l!pela Reviewer:

I r ANU: Cv'!)Y Gv!I\>A!:.1JDLI NDE_PDI-UT-2uJrll.DOC 18 0930.1259 File No.: 1501350.301 Revision:

0 I Exam Completion Time: 01 09 "Signature Level lu -.'-1:: ,_ III Tr. I/C//2SZ-.

iZ]:

1/ I Dale /o/stt/ L!i

_lo/ti.J/1>

\ Page A-2 of A-3 F0306-0 I R2 e Structural Integrity Associates, Inc. Weld # WIB-378 UneS6-15-4 4" Nominal Pipe Size 0.437" nominal thickness Indication Sizing Sketch 7ll*lipsgtJ

ll _ _ . I #1.o..ro* IDS!cit> '"* w '"'\§ r ODsutf

: 0:nded iu'" ;, mdkatloo a<ea fo<S;,;0 g 'I' Row '--... Pipe Indication Sound Distance to Iden tifi cation Path W!l!d r.s:o-n!er 1A 0.94" 0.85" 18 1.40" 1.35" 1C 1.09 1.10 Note: Indication ID 1A, 18, & 1C are different ultrasonic sound plots to the same Indication o.4&J o.4 S4 o.45'2 o.4M o.4o9 o.45 9 o.454 k!uli'Thld;mss 0.08" lrxfiCalion throu;,twJa!l "0" at eioow extrados Indication Length= 0.62S' (3-1/8" to 3-3/4") 10/0D ratio = 0.8 Length on 10 = O.S' Indication height= 0.08" Looking Downstream Indication

---*-------------------NDE exam report and indication sketch are from Reference 1 File No.: 1501350.301 Revision:

0 Page A-3 of A-3 F 0306-0 1R 2 e Structural Integrity Associates, Inc. APPENDIXB COMPUTER FILE LISTING File No.: 1501350.301 Revision:

0 Page B-1 ofB-3 F0306-0 I R2 SJ Structural Integrity Associates, Inc."' SI-TIFFANY Files **.dat SI-TIFF ANY input file ** .rpt SI-TIFF ANY output file, which echoes the inputs **.tnnn SI-TIFF ANY output file with tabulated Kmin values **.mxn SI-TIFF ANY output file with tabulated Kmax values **-HUCD-Heatup and Cooldown, CDII-Cooldown II, INAUX-Inadvertent Aux Spray, Loading/Unloading, SLID -Step Load Inc/Dec File No.: 1501350.301 Revision:

0 Page B-2 ofB-3 F0306-0 I R 2 e Structural Integrity Associates, Inc. pc-CRACK Files SLA.pcf SLB.pcf SLC.pcf SLD.pcf SLA.rpt SLB.rpt SLC.rpt SLD.rpt FCG-Fixed.pcf FCG-Fixed.rpt FCG-Fixed.kva FCG-Fixed.avn FCG-Variable.pcf FCG-Variable.rpt FCG-Variable.kva FCG-Variable.avn File No.: 1501350.301 Revision:

0 pc-CRACK input file for Service Level A EPFM evaluation pc-CRACI( input file for Service Level B EPFM evaluation pc-CRACK input file for Service Level C EPFM evaluation pc-CRACK input file for Service Level D EPFM evaluation pc-CRACK output file for Service Level A EPFM evaluation pc-CRACK output file for Service Level B EPFM evaluation pc-CRACK output file for Service Level C EPFM evaluation pc-CRACK output file for Service Level D EPFM evaluation pc-CRACK input file for fatigue crack growth for fixed aspect ratio pc-CRACK output file for fatigue crack growth for fixed aspect ratio pc-CRACK file including K vs A for fatigue crack growth with fixed aspect ratio pc-CRACK file including crack depth vs time for fatigue crack growth with fixed aspect ratio pc-CRACK input file for fatigue crack growth for variable aspect ratio pc-CRACK output file for fatigue crack growth for variable aspect ratio pc-CRACK file including K vs A for fatigue crack growth with variable aspect ratio pc-CRACK file including crack depth vs time for fatigue crack growth with variable aspect ratio Page B-3 of B-3 F0306-0 I R2 e Structural Integrity Associates, Inc. A PPENDIXC PC-CRACK OUTPUT FILES File No.: 1501350.301 Revision:

0 Page C-1 of C-1 73 F0.306-0 I R2 e Structural Integrity Associates, Inc. pc-CRACK 4.1 CS Version Control No. 4.1.0.0 Structural Integrity Associates, Inc. www.structint.com pccrack@structint.com Date: 10/09/2015 15:31 Service Level A Input Data read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\pcCRACK\SLA.pcf Analysis Title: DCPP Spray Units Selected:

US Customary Linear Dimensions

-inches Stress -ksi Load -kips Temperature

-deg F Time -hours Jic -in-lbs/inA2 Analysis Type: ASME Section XI IWB-3640 (2004) Crack Geometry Orientation:

Circumferential Crack Depth= 0.0800 Crack Length 0.6250 Pipe Geometry Nominal Pipe Size Outer Diameter Wall Thickness Service Level: A 4.0000 4.5000 0.4370 The allowable flaw size is determined using Formulae Stresses Pm Pb Pe 6.5190 (safety factor 0.6720 (safety factor 1.3170 K (Residual Stress) = 0.0000 Material:

Stainless Steel Flux weld Flow Stress 45.1500 Number of Warnings in Inputs: 0 Analysis Results File No.: 1501350.301 Revision:

0 2.7000) 2.3000) Page C-2 of C-173 F0306-0 I R2

{J Structural Integrity Associates, Inc. Failure Mode per Screening Criteria:EPFM (Class l screening rules used) Stress Ratio Z factor 1/circumference a/t allowable 1/Circumference Allowable 0.0000 0.7500 0.1000 0.7 500 0.2000 0.7500 0.3000 0.7500 0.4000 0.7500 0.5000 0.7500 0.6000 0.6934 0.7000 0.6642 0.8000 0.6535 Stress Ratio Z factor 1/circumference a/t a l lowable 1/Circumference Allowable 0.0000 0.7500 0.1000 0.7500 0.2000 0.7500 0.3000 0.7500 0.4000 0.6961 0.5000 0.5991 0.6000 0.5442 0.7000 0.5141 0.8000 0.4993 0.2235 1.3000 0.0442 0.7500(Combined Loading) a/t 0.5068 1.3000 0.0442 0.7500(Membrane Loading) a/t Note: Allowable crack size is calculated based on the failure mode indicated by the screening criteria which is based on the input crack size Number of Runtime Warn i ngs: 0 *** End of pc-CRACK output *** File No.: 1501350.301 Revision:

0 Page C-3 of C-173 F 0306-0 IR 2 e Structural Integrity Associates, Inc.* pc-CRACK 4.1 CS Version Control No. 4.1.0.0 Structural Integrity Associates, Inc. www.structint.com pccrack@structint.com Date: 10/09/2015 15:32 Service Level B Input Data read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\pcCRACK\SLB.pcf Analysis Title: DCPP Spray Units Selected:

US Customary Linear Dimensions

-inches Stress -ksi Load -kips Temperature

-deg F Time -hours Jic -in-lbs/inA2 Analysis Type: ASME Section XI IWB-3640 (2004) Crack Geometry Orientation:

Circumferential Crack Depth = 0.0800 Crack Length Pipe Geometry Nominal Pipe Size Outer Diameter Wall Thickness Service Level: B 0.6250 4.0000 4.5000 0.4370 The allowable flaw size is determined using Formulae Stresses Pm Pb 6.6700 (safety factor 2.9520 (safety factor Pe 1.7160 K (Residual Stress) = Material:

Stainless Steel Flux weld 0.0000 Flow Stress 45.1500 Number of Warnings in Inputs: 0 Analysis Results File No.: 1501350.301 Revision:

0 2.4000) 2.0000) Page C-4 of C-1 73 F0306-0I R2 e Structural Integrity Associates, Inc."' Failure Mode per Screening Criteria:EPFM (Class 1 screening rules used) Stress Ratio Z factor 1/circumference a/t allowable 1/Circumference Allowable 0.0000 0.7500 0.1000 0.7500 0.2000 0.7500 0.3000 0.7500 0.4000 0.7500 0.5000 0.6832 0.6000 0.6309 0.7000 0.6063 0.8000 0.5988 Stress Ratio Z factor 1/circumference a/t allowable 1/Circumference Allowable 0.0000 0.7500 0.1000 0.7500 0.2000 0.7500 0.3000 0.7500 0.4000 0.7500 0.5000 0.6540 0.6000 0.5944 0.7000 0.5617 0.8000 0.5457 0.3017 1.3000 0.0442 0.7500(Cornbined Loading) a/t 0.4609 1.3000 0.0442 0.7500(Mernbrane Loading) a/t Note: Allowable crack size is calculated based on the failure mode indicated by the screening criteria which is based on the input crack size Number of Runtime Warnings:

0 *** End of pc-CRACK output *** File No.: 1501350.301 Revision:

0 Page C-5 of C-173 F030 6-0\Rl e Structural Integrity Associates, Inc. pc-CRACK 4.1 CS Version Control No. 4.1.0.0 Structural Integrity Associates, Inc. www.structint.com pccrack@structint.com Date: 10/09/2015 15:33 Service Level C Input Data read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\pcCRACK\SLC.pcf Analysis Title: DCPP Spray Units Selected:

US Customary Linear Dimensions

-inches Stress -ksi Load -kips Temperature

-deg F Time -hours Jic -in-lbs/inA2 Analysis Type: ASME Section XI IWB-3640 (2004) Crack Geometry Orientation:

Circumferential Crack Depth= 0.0800 Crack Length 0.6250 Pipe Geometry Nominal Pip e Size Outer Diameter Wall Thickness Service Level: C 4.0000 4.5000 0.4 3 70 The allowable flaw size is determined using Formulae Stresses Pm 6.7950 (safety factor Pb 4.7370 (saf e ty factor Pe 2.1170 K (Residual Stress) = 0.0000 Material:

Stainless Steel Flu x weld Flow Stress 45.1500 Number of Warnings in Inputs: 0 Analysis Results File No.: 1501350.301 Revision:

0 1.8000) 1.6000) Page C-6 of C-1 73 F0 306-0 I R2 e Structural Integrity Associates, Inc. Failure Mode per Screening Criteria:EPFM (Class 1 screening rules used) Stress Ratio Z factor 1/circumference a/t allowable 1/Circumference Allowable 0.0000 0.7500 0.1000 0.7500 0.2000 0.7500 0.3000 0.7500 0.4000 0.7500 0.5000 0.6967 0.6000 0.6429 0.7000 0.6172 0.8000 0.6089 Stress Ratio Z factor 1/circumference a/t allowable 1/Circumference Allowable 0.0000 0.7500 0.1000 0.7500 0.2000 0.7500 0.3000 0.7500 0.4000 0.7500 0.5000 0.7500 0.6000 0.7128 0.7000 0.6742 0.8000 0.6555 0.3701 1.3000 0.0442 0.7500(Cornbined Loading) a/t 0.3522 1.3000 0.0442 0.7500(Mernbrane Loading) a/t Note: Allowable crack size is calculated based on the failure mode indicated by the screening criteria which is based on the input crack size Number of Runtime Warnings:

0 *** End of pc-CRACK output *** File No.: 1501350.301 Revision:

0 Page C-7 ofC-173 F0306-0I R2 e Structural Integrity Associates, Inc. pc-CRACK 4.1 CS Version Control No. 4.1.0.0 Structural Integrity Associates, Inc. www.structint.com pccrack@structint.com Date: 10/09/2015 15:34 Service Level D Input Data read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\pcCRACK\SLD.pcf Analysis Title: DCPP Spray Units Selected:

US Customary Linear Dimensions

-inches Stress -ksi Load -kips Temperature

-deg F Time -hours Jic -in-lbs/inA2 Analysis Type: ASME Section XI IWB-3640 (2004) Crack Geometry Orientation:

Circumferential Crack Depth = 0.0800 Crack Length 0.6250 Pipe Geometry Nominal Pipe Size Outer Diameter Wall Thickness Service Level: D 4.0000 4.5000 0.4370 The allowable flaw size is determined using Formulae Stresses Pm 6.7650 (safety factor Pb 3.91 30 (safety factor Pe 1.5570 K (Residual Stress) = 0.0000 Material:

Stainless Steel Flux weld Flow Stress 45.1500 Number of Warnings in Inputs: 0 Analysis Results File No.: 1501350.301 Revision:

0 1.3000) 1.4000) Page C-8 of C-1 73 F0306-0 I R2 e Structural Integrity Associates, Inc."' Failure Mode per Screening Criteria:EPFM (Class 1 screening rules used) Stress Ratio Z factor 1/circumference a/t allowable 1/Circumference Allowable 0.0000 0.7500 0.1000 0.7500 0.2000 0.7500 0.3000 0.7500 0.4000 0.7500 0.5000 0.7500 0.6000 0.7377 0.7000 0.7048 0.8000 0.6915 Stress Ratio Z factor 1/circumference a/t allowable 1/Circumference Allowable 0.0000 0.7500 0.1000 0.7500 0.2000 0.7500 0.3000 0.7500 0.4000 0.7500 0.5000 0.7500 0.6000 0.7500 0.7000 0.7500 0.8000 0.7500 .0.3395 1.3000 0.0442 0.7500(Cornbined Loading) a/t 0.2532 1.3000 0.0442 0.7500(Mernbrane Loading) a/t Note: Allowable crack size is calculated based on the failure mode indicated by the screening criteria which is based on the input crack size Number of Runtime Warnings:

0 *** End of pc-CRACK output *** File No.: 1501350.301 Revision:

0 Page C-9 of C-173 F030 6-01R2 e Structural Integrity Associates, Inc.'" Fatigue Crack Growth-Fixed Aspect Ratio pc-CRACK 4.1 CS Version Control No. 4.1.0.0 Structural Integrity Associates, Inc. www.structint.com pccrack@structint.com Date: 10/29/2015 10:55 Input Data read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\pcCRACK\FCG-Fixed.pcf Analysis Title: DCPP Spray Line Units Selected:

US Customary Linear Dimensions

-inches Stress -ksi Load -kips Temperature

-deg F Time -hours Analysis Type: Crack Growth (LEFM) Crack Growth Calculation Method -Crack Stepping Crack Model: 306-Semi-Elliptical Circumferential Crack in Cylinder on the Inside Surface (API 579) Crack Depth, a= 0.0800 Half Crack Length, c 0.3125 Wall Thickness, t = 0.4370 Inside Radius, Ri = 1.8130 Aspect ratio fixed Maximum a/t = 0.75 Crack Depth Print Increment for SIF Tabulation 0.01 Total Load Cases: 13 Load Case 1:HU/CD Max 2-d SIF Input by User The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\HUCD.MXN No. of aspect ratios (a/c) in the tables = 8 a/c = 0.1250 Crack Depth Kdeepest Ksurface 4.370E-03 10.4510 3.9032 0.0437 26.8310 11.8060 0.0656 29.5570 14.0540 0.0874 30.7780 15.7380 0.1093 32. 0710 17.4750 0.1311 32.75 2 0 19.0020 0.1530 32. 9650 2 0.3650 0.1748 32.8050 21.5940 0.1967 32.7170 22.8730 0.2185 32.3480 24.0670 0.2404 31.7350 25.1860 0.2622 30.9160 26.2380 0.2841 29.7890 27.7710 0.3059 28.2260 29.2630 0.3278 2 6.2690 30.7150 0.3496 23.9630 32.1260 a/c = 0.1667 Crack Depth Kdeepest Ksurface File No.: 1501350.301 Revision:

0 Page C-1 0 of C-173 F03 0 6-0 I R2 e Structural Integrity Associates, Inc. 4.370E-03 10.2590 4.5078 0.0437 26.2190 13.5920 0.0656 28.8130 16.1640 0.0874 29.9340 18.0900 0.1093 30.9780 20.1180 0.1311 31.3940 21.9160 0.1530 31.3250 23.5370 0.174 8 30.8710 25.0150 0.1967 30.5010 26.4860 0.2185 29.8620 2 7.84 70 0.2404 28.9970 29.1100 0.2622 27.9440 30.2830 0.284 1 26.7090 31.8800 0.3059 25.126 0 33.4090 0.32 78 23.2340 34.8710 0.3496 21.07 50 36.2690 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 10.0940 4. 9720 0.0437 25.7010 14.9640 0.0656 28.1890 17.7850 0.0874 29.2300 19.8970 0.1093 30.0790 22.1480 0.1311 30.2870 24.1550 0.1530 30.0010 25.9760 0.1748 29.3190 27.6450 0.1967 28.7290 29.2660 0.2185 27.8830 30.7570 0.2404 26.8240 32 .1310 0. 2 622 25.5900 33.3990 0.2841 24.2720 3 5.0450 0.3059 22.6760 36.6020 0.3278 20.8370 38.0720 0.3496 18.7960 39.4580 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 9.8321 5.6352 0.0437 24.8910 16.9230 0.0656 2 7.2 190 20.1000 0.0874 28.1420 22.4770 0.1093 28.7070 25.0490 0.1311 28.6150 2 7.3560 0.1530 28.0140 29.4610 0.1748 2 7.0060 3 1.4060 0.1967 26.1010 33.2410 0.2185 24.9580 34.9190 0.2404 23.6 2 10 36.4540 0. 2622 22.1 290 3 7.8580 0.2841 20.6920 39.5 750 0.3059 19.0780 41.1720 0.3278 17.3 190 42.6510 0.3496 15.4500 44.0180 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 9.4074 6.1941 0.0437 23.6990 18.5910 0.0656 25.8360 22.0860 0.0874 26.6190 24.7140 0.1093 26.9910 2 7.4090 0.1311 26.7330 2 9.7930 0.1530 25.9910 31.9370 0.1748 24.8 640 33.8890 FileNo.: 1501350.301 Page C-11 ofC-173 Revision:

0 F0306-0I R2 e Structural Integrity Associates, Inc."' 0.1967 23.7690 35.8250 0.2185 22.4550 37.5950 0.2404 20.9690 39.2140 0.2622 19.3490 40.6950 0.2841 17.7170 42.1800 0.3059 15.9420 43.5360 0.3278 14.0550 44.7680 0.3496 12.0880 45.8850 ale = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 8.5324 7.1113 0.0437 21.2790 21.3290 0.0656 23.0480 25.3480 0.0874 23.5740 28.3890 0.1093 23.6000 31.2740 0.1311 23.0510 33.7670 0.1530 22.0680 35.9560 0.1748 20.7490 37.9000 0.1967 19.3320 39.9930 0.2185 17.7370 41.9050 0.2404 16.0090 43.6540 0.2622 14.1880 45.2550 0.2841 12.2420 46.3080 0.3059 10.2180 47.2180 0.3278 8.1538 47.9960 0.3496 6.5215 48.6530 .. ale = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 7.3428 7.3615 0.0437 18.0280 21.9460 0.0656 19.3480 25.9910 0.0874 19.5900 29.0030 0.1093 19.5280 31.8580 0.1311 18.9900 34.3100 0.1530 18.0990 36.4540 0.1748 16.9350 38.3530 0.1967 15.4390 40.2090 0.2185 13.7840 41.8890 0.2404 12.0140 43.4150 0. 2 622 10.1680 44.8030 0.2841 8.2553 45.9590 0.3059 6.3129 46.9930 0.3278 5.1927 47.9160 0.3496 5.5896 48.7370 ale = 1.0000 Crack Depth Kdeepest Ksurface 4.370E-03 6.3496 7.4789 0.0437 15.3380 22.1970 0.0656 16.3000 26.2200 0.0874 16.3230 29.1800 0.1093 16.1940 31.9830 0.1311 15.6720 34.3790 0.1530 14.8600 36.4670 0.1748 13.8290 38.3130 0.1967 12.2920 39.9680 0.2185 10.6140 41.4520 0.2404 8.8402 42.7910 0.2622 7.0094 44.0030 0.2841 5.1774 45.2280 0.3059 4.1674 46.3490 0.3278 4.4973 47.3760 0.3496 4.8250 48.3170 File No.: 1501350.301 Page C-12 of C-173 Revision:

0 F0306-0 I R2 e Structural Integrity Associates, Inc. Load Case 2:HU/CD Min 2-d SIF Input by User The SIF originally read from C:\Users\clohse\Docurnents\ANSYS\PGE\1501350\TIFFANY\HUCD.MNN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-03 0 .1714 0.0437 0.8047 0.0656 1.1531 0.0874 1. 5159 0.1093 1.9355 0.1311 2.3815 0.1530 2.8518 0.1748 3.3440 0.1967 3.8949 0.2185 4. 4723 0.2404 5.0743 0.2622 5.6988 0.2841 6. 5727 0.3059 7.4985 0.3278 8. 4 722 0.3496 9.4884 ale= 0.1667 Crack Depth Kdeepest 4.370E-03 0.1684 0.0437 0.7895 0.0656 1.1299 0.0874 1.4831 0.1093 1.8909 0.1311 2.3240 0.1530 2.7803 0.1748 3.2575 0.1967 3.7827 0.2185 4.3308 0.2404 4.8999 0. 2 622 5.4880 0.2841 6.2723 0.3059 7.0977 0.3278 7.9603 0.3496 8.8555 a/c = 0.2000 Crack Depth Kdeepest 4.370E-03 0.1657 0.0437 0.7765 0.0656 1.1100 0.0874 1. 4553 0.1093 1. 8532 0.1311 2.2756 0.1530 2.7203 0.1748 3.1850 0.1967 3.6893 0.2185 4. 2137 0.2404 4.7563 0.2622 5.3150 0.2841 6.0281 0.3059 6.7738 0.3278 7.5485 0.3496 8.3479 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 0.0594 0.1993 0.2538 0.3058 0.3579 0.4106 0.4646 0.5202 0.5767 0.6353 0.6961 0.7593 0.8424 0.9303 1. 0233 1.1213 Ksurface 0.0688 0.2347 0.3011 0.3649 0.4310 0.4983 0.5675 0.6388 0. 7183 0.8022 0.8904 0.9833 1.1020 1.2285 1. 3627 1. 504 7 Ksurface 0.0760 0. 2620 0.3375 0.4104 0.4873 0.5659 0.6467 0.7302 0.8275 0.9308 1.0403 1.1560 1. 3022 1.4584 1. 6244 1.8003 Page C-13 ofC-173 F030 6-0J R2 lJ Struc/ural/nlegrity Associates, Inc. ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 0.1615 0.0863 0.0437 0.7558 0.3009 0.0656 1.07 8 7 0.3896 0.0874 1. 4116 0.4756 0.1093 1. 7 943 0.5680 0.1311 2.2002 0.6627 0.1530 2. 6270 0.7603 0.1748 3. 0726 0.8612 0.1967 3.5454 0.9841 0.2185 4.0342 1.1154 0.2404 4.5369 1.2553 0.2622 5.0516 1.4039 0.2841 5.6599 1.5897 0.3059 6.2881 1. 7885 0.3278 6.9332 2.0002 0.3496 7. 5913 2.2247 a/c = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 0.1547 0.0951 0.0437 0. 7257 0.3358 0.0656 1.0364 0. 4371 0.0874 1. 3567 0.5360 0.1093 1.7209 0.6410 0.1311 2.1057 0.7488 0.1530 2.5088 0.8600 0.1748 2.9280 0.9749 0.1967 3.3674 1.1147 0.2185 3.8194 1.2636 0.2404 4.2818 1. 4217 0. 2 622 4.7526 1.5890 0.2841 5.2981 1.7808 0.3059 5.8575 1.9843 0.3278 6.4277 2.1992 0.3496 7.0035 2.4253 a/c = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 0.1406 0.1094 0.0437 0.6628 0.3935 0.0656 0.9479 0.5161 0.0874 1.2419 0.6367 0.1093 1.5684 0. 7629 0.1311 1.9107 0. 8926 0.1530 2.2664 1.0 265 0.1748 2.6333 1.1650 0.1967 3.0077 1.333 1 0.2185 3.3881 1. 5113 0.2404 3. 7725 1. 6996 0.2622 4.1589 1. 8981 0.2841 4.5847 2.0983 0.3059 5.0127 2.3073 0.3278 5.4362 2.5 249 0.3496 5.1316 2.7510 a/c = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 0.1215 0.1134 0.0437 0.5788 0.4087 0.0656 0.8295 0.5366 0.0874 1.0877 0.6628 0.1093 1.3757 0.7927 File No.: 1501350.301 Page C-14 ofC-173 Revision:

0 F0306-01R2 e Structural Integrity Associates, Inc. 0.1311 1. 6771 0.1530 1.9896 0.1748 2. 3112 0.1967 2.6356 0.2185 2.9639 0.2404 3.2941 0. 2 622 3.6241 0.2841 3.9792 0.3059 3.7631 0.3278 2.9125 0.3496 1.6720 a/c = 1.0000 Crack Depth Kdeepest 4.3 7 0E-03 0.1055 0.0437 0.5080 0.0656 0.7296 0.0874 0.9576 0.1093 1.2129 0.1311 1. 4795 0.1530 1. 7554 0.1748 2.0387 0.1967 2. 3211 0.2185 2.6056 0.2404 2.8902 0. 2622 2.9045 0.2841 2.2874 0.3059 1. 4158 0.3278 0.2709 0.3496 -1.1900 Load Case 3:CD II Max 2-d SIF Input by User 0.9252 1. 0611 1.2008 1. 3592 1. 5246 1. 6968 1.8760 2.0636 2.2584 2.4601 2.6686 Ksurface 0.1153 0.4162 0.5470 0.6 7 61 0.8075 0.9408 1.0769 1.2160 1.3653 1. 5190 1.67 7 0 1.8394 2.0154 2.1971 2.3843 2. 5771 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\CDII.MXN No. of aspect ratios (a/c) ale= 0.1250 Crack Depth Kdeepest 4.370E-03 12.7140 0.0437 32.6970 0.0656 35.9930 0.0874 37.4290 0.1093 38.9310 0.1311 39.6700 0.1530 39.8220 0.1748 39.5090 0.1967 39.2660 0.2185 38.6680 0.2404 37.7630 0.2622 36.5970 0.2841 34.9880 0.3059 32.8280 0.3278 30.1680 0.3496 27.0670 ale = 0.1667 Crack Depth Kdeepest 4.370E-03 12.4810 0.0437 31.9510 0.0656 35.0860 0.0874 36.4010 0.1093 37.6000 0.1311 38.0150 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 4.7459 14.3690 17.1130 19.1700 21.2930 23.1600 24.8260 26.3270 27.8900 29.3490 30.7150 31.9990 33.8670 35.6840 37.4520 39.1690 Ksurface 5.4811 16.5440 19.6840 22.0360 24.5130 26.7100 Page C-15 of C-173 F0 3 0 6-0l R2 l} Structural integrity Associates, Inc. 0 .1530* 37.8260 28.6890 0.1748 37.1530 30.4930 0.1967 36.5690 32.2880 0.2185 35.6470 33.9480 0.2404 34.4400 35.4850 0.2622 32.9940 36.9110 0.2841 31.27 40 38.8510 0.3059 29.1150 40.7050 0.3278 26.5640 42.4760 0.3496 23.6740 44.1650 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 12.2810 6.0457 0.0437 31.3190 18.2150 0.0656. 34.3250 21.6580 0.0874 35.5430 24.2380 0.1093 36.5050 26.9860 0.1311 36.6680 29.4380 0.1530 36.2130 31.6590 0.1748 35.2640 33.6950 0.1967 34.4150 35. 6710 0.2185 33.2430 37.4860 0.2404 31.8030 39.1560 0.2622 30.1430 40.6930 0.2841 28.3380 42.6880 0.3059 26.1820 44.5700 0.3278 23.7190 46.3430 0.3496 20.9970 48.0100 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 11.9620 6.8520 0.0437 30.3330 20.6000 0. 0656 33.1440 24.4770 0.0874 34.2190 27.3820 0.1093 34.8350 30.5200 0.1311 34.6330 33.3360 0.1530 33.7950 35.9040 0.1748 32.4480 38.2750 0.1967 31.2190 40.5090 0.2185 29.6900 42.5480 0.2404 27.9180 44.4090 0.2622 25.9510 46.1060 0.2841 24.0260 48.1790 0.3059 21.8770 50.1010 0.3278 19.5450 51.8740 0.3496 17.0720 53.5060 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 11.4450 7.5318 0.0437 28.8800 22.6330 0.0656 31.4580 26.8990 0.0874 32.3630 30.1080 0.1093 32.7450 33.3980 0.1311 32.3430 36.3060 0.1530 31.3370 38.9200 0.1748 29.8510 41.2980 0.1967 28.3950 43.6520 0.2185 26.6650 45.8000 0.2404 24.7190 47.7600 0. 2 622 22.6050 49.5470 0.2841 20.4560 51.3330 0.3059 18.1260 52.9570 File No.: 1501350.301 Page C-16 of C-173 Revision:

0 F0306-0IR2 lJ Structural Integrity Associates, Inc. 0.3278 15.6540 0.3496 13.0810 a/c = 0.5000 Crack Depth Kdeepest 4.370E-03 10.3810 0.0437 25.9290 0.0656 28.0600 0.0874 28.6530 0.1093 28.6170 0.1311 27.8660 0.1530 26.5750 0.1748 24.8640 0.1967 23.0280 0.2185 20.9680 0.2404 18.7430 0. 2 622 16.4020 0.2841 13.8960 0.3059 11.2920 0.3278 8.6359 0.3496 6.5215 a/c = 0.7500 Crack Depth Kdeepest 4.370E-03 8.9337 0.0437 21.9670 0.0656 23.5500 0.0874 23.8000 0.1093 23.6620 0.1311 22.9330 0.1530 21.7630 0.1748 20.2530 0.1967 18.3310 0.2185 16.2110 0.2404 13.9480 0.2622 11.5890 0.2841 9.1408 0.3059 6.6539 0.3278 5.1983 0.3496 5.6320 ale = 1.0000 Crack Depth Kdeepest 4.370E-03 7. 7256 0.0437 18.6870 0.0656 19.8350 0.0874 19.8200 0.1093 19.6060 0.1311 18.9030 0.1530 17.8380 0.1748 16.5010 0.1967 14.5380 0.2185 12.4010 0.2404 10.1430 0. 2 622 7.8145 0.2841 5.4789 0.3059 4.1760 0.3278 4.5406 0.3496 4.9028 Load Case 4:CD II Min 2-d SIF Input by User The SIF originally read File No.: 1501350.301 Revision:

0 from 54.4260 55.7480 Ksurface 8. 64 72 25.9670 30.8750 34.5880 38.1090 41.1480 43.8150 46.1800 48.7200 51.0350 53.1470 55.0740 56.3270 57.4000 58.3090 59.0650 Ksurface 8.9515 26.7200 31.6580 35.3370 38.8210 41.8100 44.4210 46.7 300 48.9810 51.0130 52.8540 54.5230 55.9050 5 7.1330 58.223 0 59.1840 Ksurface 9.0943 27.0270 31.9390 35.5540 38.9 7 30 41.8940 44.4360 46.6790 48.6850 50.4790 52.0920 53.5480 55.0170 56.3550 57.5750 58.6880 C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\CDII.MNN Page C-17 of C-173 F0306-0 I R2 e Slruclurallnlegrily Associates, Inc. No. of aspect ratios (a/c) in the tables 8 ale = 0.1250 Crack Depth Kdeepest Ksurface 4.370E-03 0.0222 4.244E-03 0.0437 0.3938 0.0303 0.0656 0.6885 0.0512 0.0874 1.0215 0. 0772 0.1093 1. 4110 0.1033 0.1311 1.8373 0.1331 0.1530 2.2957 0.1666 0.1748 2.7826 0.2038 0.1967 3.3270 0.2419 0.2185 3.9025 0.2836 0.2404 4.5067 0.3288 0. 2 622 5.1370 0.3775 0.2841 6.0192 0.4389 0.3059 6.9599 0.5059 0.3278 7.9539 0.5786 0.3496 8.9950 0.6571 ale = 0.1667 Crack Depth Kdeepest Ksurface 4.370E-03 0.0218 5.058E-03 0.0437 0.3879 0.0395 0.0656 0.6767 0. 0 67 0 0.0874 1.0020 0.1007 0.1093 1.3839 0.1358 0.1311 1. 8017 0.1754 0.1530 2.2510 0.2194 0.1748 2.7280 0.2678 0.1967 3.2515 0.3248 0.2185 3.8026 0.3878 0.2404 4.3785 0.4569 0.2622 4.9766 0.5320 0.2841 5.7719 0. 6266 0.3059 6. 6134 0.7301 0.3278 7.4964 0.8425 0.3496 8.4152 0.9638 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 0.0216 5.686E-03 0.0437 0.3826 0.0467 0.0656 0.6665 0.0792 0.0874 0.9852 0.1188 0.1093 1.3605 0.1609 0.1311 1.7711 0.2080 0.1530 2.2126 0.2602 0.1748 2. 6811 0.3172 0.1967 3.1876 0.3887 0.2 185 3.7187 0.4682 0.2404 4. 2715 0.5557 0. 2 622 4.8436 0.6512 0.2841 5.5699 0. 7714 0.3059 6.3327 0.9030 0.3278 7.1277 1.0460 0.3496 7.9495 1.2002 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03

0. 0211 6.584E-03 0.0437 0.3741 0.0569 0.0656 0.6501 0. 0967 File No.: 1501350.301 Page C-18 ofC-173 Revision:

0 F0306-0IR2 e Struc/urallnlegrily Associates, Inc.'" 0.0874 0.9587 0.1449 0.1093 1.3236 0.1969 0.1311 1. 7228 0.2550 0.1530 2.1519 0.3188 0.1748 2.6070 0.3882 0.1967 3.0876 0.4806 0.2185 3.5884 0.5838 0.2404 4.1066 0.6978 0.2622 4.6393 0.8224 0.2841 5.2637 0.9794 0.3059 5.9103 1.1513 0.3278 6.5755 1.3382 0.3496 7.2543 1. 5397 a/c = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 0.0203 7.392E-03 0.0437 0.3619 0.0671 0.0656 0.6291 0.1144 0.0874 0.9277 0.1712 0.1093 1.2775 0.2334 0.1311 1. 6587 0.3027 0.1530 2.0668 0.3789 0.1748 2.4979 0.4616 0.1967 2.9488 0.5687 0.2185 3.4159 0.6873 0.2404 3.8966 0.8174 0.2622 4.3880 0.9589 0.2841 4.9533 1.1248 0.3059 5.5343 1.3044 0.3278 6.1268 1.4974 0.3496 6.7245 1. 7038 a/c = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 0.0187 8.739E-03 0.0437 0.3357 0.0844 0.0656 0.5836 0.1445 0.0874 0.8607 0.2159 0.1093 1.1793 0.2954 0.1311 1. 5235 0.3839 0.1530 1. 8890 0.4810 0.1748 2.2719 0.5865 0.1967 2.6638 0. 7182 0.2185 3.0649 0. 8 62 7 0.2404 3.4725 1.0198 0.2622 3.8834 1.1894 0.2841 4.3352 1. 368 9 0.3059 4.7894 1.5596 0.3278 5.2374 1. 7 611 0.3496 4.8097 1.9731 a/c = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 0.0165 9.139E-03 0.0437 0.3007 0.0903 0.0656 0.5224 0.1549 0.0874 0.7693 0.2319 0.1093 1. 0520 0.3153 0.1311 1. 3562 0. 4071 0.1530 1.6781 0.5069 0.1748 2.0141 0.6142 0.1967 2.3581 0.7399 0.2185 2.7091 0.8753 0.2404 3.0639 1. 0200 File No.: 1501350.301 Page C-19 ofC-173 Revision:

0 F030 6-0I R2 Structural Integrity Associates, Inc. 0. 2622 0.2841 0.3059 0.3278 0.3496 a/c = Crack Depth 4.370E-03 0.0437 0.0656 0.0874 0.1093 0.1311 0.1530 0.1748 0.1967 0.2185 0.2404 0.2622 0.2841 0.3059 0.3278 0.3496 3.4195 3.8004 3.5065 2.3892 0.7737 1.0000 Kdeepest 0.0147 0.2706 0.4698 0.6909 0.9429 1. 2131 1.4979 1. 7942 2.0976 2.4060 2. 7160 2. 7269 1. 9188 0.7885 -0.6909 -2.5753 Load Case 5:Unload Max 2-d SIF Input by User 1.1738 1.3397 1. 514 7 1.6986 1. 8911 Ksurface 9.353E-03 0.0939 0.1614 0.2419 0.3274 0.4208 0.5216 0.6291 0.7489 0.8758 1.0094 1.1493 1.3030 1. 4641 1.6324 1. 8077 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\UNLD.MXN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-03 4.5828 0.0437 12.0180 0.0656 13.4190 0.0874 14.1820 0.1093 15. 0110 0.1311 15.5920 0.1530 15.9850 0.1748 16.2300 0.1967 16.5440 0.2185 16.7510 0.2404 16.8690 0. 2622 16.9120 0.2841 16.9790 0.3059 16.8920 0.3278 16.6650 0.3496 16.3180 a/c = 0.1667 Crack Depth Kdeepest 4.370E-03 4.4990 0.0437 11.7460 0.0656 13.0850 0.0874 13.7990 0.1093 14.5130 0.1311 14.9710 0.1530 15.2340 0.1748 15.3430 0.1967 15.5180 0.2185 15.5910 0.2404 15.5790 0.2622 15.4980 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 1.7085 5.1801 6.1774 6.9317 7.7071 8.3929 9.0089 9.5682 10.1480 10.6920 11.2040 11. 6900 12.3930 13.0810 13.7550 14.4150 Ksurface 1.9733 5.9679 7.1119 7.9780 8.8877 9.7001 10.4380 11.1150 11.7930 12.4270 13.0200 13.5780 Page C-20 of C-173 F030 6-01 R2 SJ Structural Integrity Associates, Inc."' 0.2841 15.4620 14.3340 0.3059 15.3030 15.0640 0.3278 15.0360 15.7710 0.3496 14.6760 16.4540 a/c = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 4.4266 2.1766 0.0437 11.5160 6.5730 0.0656 12.8050 7.8297 0.0874 13.4790 8.7818 0.1093 14.1030 9.7950 0.1311 14.4650 10.7050 0.1530 14.6260 11.5360 0.1748 14.6290 12.3040 0.1967 14.6960 13.0590 0.2 185 14.6650 13.7620 0.2404 14.5530 14.4190

0. 2622 14.3750 15.0330 0.2841 14.2590 15.8290 0.3059 14.0440 16.5920 0.3278 13.7440 17.3230 0.3496 13.3740 18.0240 a/c = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03

4. 3118 2. 4 67 0 0.0437 11.1560 7.4371 0.0656 12.3690 8.8550 0.0874 12.9850 9.9301 0.1093 13.4760 11.0910 0.1311 13. 6980 12.1410 0.1530 13.7130 13.1060 0.1748 13.5620 14.0050 0.1967 13.4730 14.8700 0.2185 13.2910 15.6740 0.2404 13.0340 16.4210 0.2622 12.7180 17.1170 0.2841 12.4840 17.9700 0.3059 12.1880 18.7790 0.3278 11.8410 19.5460 0.3496 11.4580 20.2720 a/c = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-:-03 4.1257 2.7118 0.0437 10.6260 8.1738 0.0656 11.7490 9.7367 0.0874 12.2960 10.9270 0.1093 12.6930 12.1510 0.1311 12.8300 13.2420 0.1530 12.7680 14.2 330 0.1748 12.5490 15.1440 0.1967 12.3570 16.0650 0.2 185 12.0790 16.9200 0.2 404 11.7320 17.7150 0.2 622 11.3330 18.4580 0.2841 10.9760 19.2170 0.3059 10.5680 19.9270 0.3278 10.1200 20.5920 0.3496 9.6453 21.2130 ale = 0.5000 Crack Depth Kdeepest Ksurface File No.: 1501350.301 Page C-21 of C-173 Revision:

0 F0 3 0 6-0l R2 e Structural Integrity Associates, Inc. 4.370E-03 3.7421 0.0437 9.5479 0.0656 10.4970 0.0874 10.9160 0.1093 11.1390 0.1311 11.1240 0.1530 10.9280 0.1748 10.5930 0.1967 10.2210 0.2185 9.7759 0.2404 9.2758 0. 2622 8. 7372 0.2841 8.1707 0.3059 7.5742 0.3278 6.9626 0.3496 6.5215 a/c = 0.7500 Crack Depth Kdeepest 4.370E-03 3.2207 0.0437 8.1012 0.0656 8.8345 0.0874 9.1085 0.1093 9.2680 0.1311 9.2303 0.1530 9.0456 0.1748 8.7486 0.1967 8.3106 0.2185 7.8064 0.2404 7.2539 0.2622 6.6687 0.2841 6.0729 0.3059 5.4651 0.3278 5.1798 0.3496 5.4923 ale = 1.0000 Crack Depth Kdeepest 4.370E-03 2.7854 0.0437 6.9029 0.0656 7.4631 0.0874 7.6230 0.1093 7.7325 0.1311 7.6786 0.1530 7.5046 0.1748 7.2401 0.1967 6.7572 0.2185 6.2153 0.2404 5.6318 0. 2 622 5.0232 0.2841 4.4249 0.3059 4.1478 0.3278 4.3980 0.3496 4.6465 Load Case 6:Unload Min 2-d SIF Input by User 3.1136 9.3831 11.1850 12.5680 13.8860 15.0390 16.0650 16.9890 17.9970 18.9330 19.8060 20.6210 21.2030 21.7290 22.2030 22.6290 Ksurface 3.2232 9.6574 11.4740 12.8480 14.1570 15.2940 16.3020 17.2070 18.1070 18.9360 19.7030 20.4150 21.0320 21.6020 22.1270 22.6130 Ksurface 3.2746 9.7700 11.57 90 12.9330 14.2200 15.3350 16.3190 17.2010 18.0090 18.7460 19.4240 20.0500 20.6890 21.2860 2 1.8470 22.3740 L The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\UNLD.MNN No. of aspect ratios (a/c) in the tables = 8 ale= 0.1250 Crack Depth Kdeepest 4.370E-03 0.5123 File No.: 1501350.301 Revision:

0 Ksurface 0.1855 Page C-22 of C-173 F0306-0 I R2 e Structural Integrity Associates, Inc. 0.0437 1. 7438 0.5852 0.0656 2.2156 0. 7166 0.0874 2. 6471 0.8279 0.1093 3 .13 60 0.9394 0.1311 3.6276 1.0445 0.1530 4.1249 1.1452 0.1748 4.6293 1.2429 0.1967 5.1954 1.3412 0.2185 5.7770 1.4383 0.2404 6.3738 1.5347 0.2622 6.9854 1. 6307 0.2841 7.8412 1.7631 0.3059 8.7341 1.8987 0.3278 9.6619 2.0377 0.3496 10.6220 2.1801 ale = 0.1667 Crack Depth Kdeepest Ksurface 4.370E-03 0.5030 0.2145 0.0437 1.7076 0.6806 0.0656 2.1662 0.8359 0.0874 2.5840 0.9685 0.1093 3.0515 1.1054 0.1311 3.5200 1. 2360 0.1530 3.9923 1. 3625 0.1748 4.4699 1. 4863 0.1967 4.9989 1. 6173 0.2185 5.5403 1.7486 0.2404 6.0940 1.8806 0.2622 6.6595 2.0138 0.2841 7.4193 2.1876 0.3059 8.2086 2.3665 0.3278 9.0255 2.5505 0.3496 9. 8 67 8 2.7397 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 0.4950 0.2367 0.0437 1. 67 67 0.7538 0.0656 2.1243 0.9276 0.0874 2.5308 1.0767 0.1093 2.9810 1.2332 0.1311 3.4306 1.3834 0.1530 3.8827 1.5298 0.1748 4.3388 1.6737 0.1967 4.8379 1.8299 0.2185 5.3472 1.9876 0.2404 5.8663 2.1472 0.2622 6.3950 2.3091 0.2841 7.0789 2.5149 0.3059 7.7862 2. 7272 0.3278 8.5153 2.9460 0.3496 9.2642 3.1713 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 0.4823 0.2685 0.0437 1.6282 0.8585 0.0656 2.0589 1. 058 6 0.0874 2.4479 1.2313 0.1093 2. 8719 1.4159 0.1311 3.2932 1.5943 0.1530 3.7149 1.7692 0.1748 4.1386 1.9420 0.1967 4.5935 2.1346 File No.: 1501350.301 Page C-23 of C-1 73 Revision:

0 F030 6-0 I R2 e Structural Integrity Associates, Inc. 0.2185 5.0549 2.3303 0.2404 5.5227 2.5295 0.2622 5.9966 2.7327 0.2841 6.5688 2.9845 0.3059 7.1554 3.2447 0.3278 7.7552 3.5135 0.3496 8.3668 3.7906 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 0.4617 0.2954 0.0437 1. 5571 0.9495 0.0656 1.9679 1.1742 0.0874 2.3385 1.3694 0.1093 2.7360 1.5724 0.1311 3.1291 1. 7 680 0.1530 3.5207 1. 9593 0.1748 3.9127 2.1479 0.1967 4.3261 2. 362 6 0.2185 4.7433 2.5807 0.2404 5.1642 2.8028 0.2622 5.5886 3.0291 0.2841 6.0894 3.2807 0.3059 6.6002 3.5389 0.3278 7 .1197 3.8038 0.3496 7.6461 4.0755 ale = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 0.4191 0.3395 0.0437 1. 4107 1.0996 0.0656 1. 7810 1.3651 0.0874 2 .1142 1.5982 0.1093 2.4594 1. 8312 0.1311 2.7972 2.0550 0.1530 3.1305 2.2730 0.1748 3.4609 2.4873 0.1967 3.7952 2.7387 0.2185 4.1283 2.9940 0.2404 4.4603 3.2539 0. 2 622 4.7909 3.5186 0.2841 5.1581 3.7664 0.3059 5. 52 67 4.0177 0.3278 5.8943 4. 2725 0.3496 5.9705 4.5310 ale = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 0.3613 0.3516 0.0437 1.2145 1.1361 0.0656 1.5318 1.4088 0.0874 1. 8163 1.6473 0.1093 2.1170 1.8835 0.1311 2.4117 2.1091 0.1530 2.7028 2.3278 0.1748 2.9916 2.5417 0.1967 3. 2710 2.7749 0.2185 3.5478 3.0089 0.2404 3.8222 3.2443 0.2622 4.0939 3.4817 0.2841 4.3907 3.7193 0.3059 4.4556 3.9595 0.3278 4.2761 4.2022 0.3496 3.9452 4.4478 File No.: 1501350.301 Page C-24 of C-173 Revision:

0 F0306-0 I R2 .

Structural Integrity Associates, Inc. ale = 1.0000 Crack Depth Kdeepest 4.370E-03 0.3130 0.0437 1.0506 0.0656 1. 3238 0.0874 1.5679 0.1093 1. 8311 0.1311 2.0894 0.1530 2.3450 0.1748 2.5987 0.1967 2.8328 0.2185 3.0634 0.2404 3.2904 0.2622 3.4015 0.2841 3.2795 0 .. 3059 3.0569 0.3278 2. 7272 0.3496 2.2743 Load Case 7:IAS Max 2-d SIF Input by User Ksurface 0.3573 1.152 6 1.4280 1. 668 4 1.9045 2.1292 2.3461 2.5575 2.7743 2.9894 3.2036 3.4174 3.6447 3.8737 4.1047 4.3377 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\INAUX.MXN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-03 15.2760 0.0437 39.8790 0.0656 44.0560 0.0874 45.8970 0.1093 47.7650 0.1311 48.6540 0.1530 48.7860 0.1748 48.3150 0.1967 47.9010 0.2185 47.0250 0.2404 45.7510 0.2622 44.1360 0.2841 41.8980 0.3059 38.9510 0.3278 35.3580 0.3496 31.1950 a/c = 0.1667 Crack Depth Kdeepest 4.370E-03 14.9970 0.0437 38.9710 0.0656 42.9480 0.0874 44.6370 0.1093 46.1330 0.1311 46.6220 0.1530 46.3300 0.1748 45.4150 0.1967 44.5790 0.2185 43.3060 0.2404 41. 6610 0.2622 39.7050 0.2841 37.3500 0.3059 34.4270 0.3278 30.9990 0.3496 27 .1320 a/c = 0.2000 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 5.68 7 5 17.2900 20.6390 23.1720 25.7840 28.0900 30.1530 32.0170 33.9550 35.7660 37.4630 39.05 7 0 41.3660 43. 6110 45.7950 47.9150 Ksurface 6.5691 19.9180 23.7560 26.6550 29.7040 32.4170 34.86 7 0 37.1030 39.3340 41.3980 43.3100 45.0830 47.4830 49.7740 51.9600 54.0420 Page C-25 of C-173 F0306-01 R2

(;Structural Integrity Associates, Inc. Crack Depth Kdeepest Ksurface 4.370E-03 14.7560 7.2461 0.0437 38.2030 21.9370 0.0656 42.0180 26.1480 0.0874 43.5860 29.3300 0.1093 44.7890 32.7150 0.1311 44.9670 35.7410 0.1530 44.3470 38.4900 0.1748 43.0880 41.0120 0.1967 41.9260 43.4690 0.2185 40.3460 45.7290 0.2404 38.4160 47.8070 0.2622 36.1990 49.7180 0.2841 33.7540 52.1880 0.3059 30.8550 54.5140 0.3278 27.5590 56.7000 0.3496 23.9280 58.7500 a/c = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 14.3730 8. 2130 0.0437 37.0030 24.8190 0.0656 40.5750 29.5660 0.0874 41.9640 33.1510 0.1093 42.7400 37.0150 0.1311 42.4660 40.4910 0.1530 41.3730 43.6660 0.1748 39.6210 46.6010 0.1967 37.9900 49.3820 0.2185 35.9690 51.9210 0.2404 33.6330 54.2380 0. 2 622 31.0430 56.3490 0.2841 28.4730 58.9170 0.3059 25.6130 61.2900 0.3278 22.5150 63.4740 0.3496 19.2330 65.4740 a/c = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 13.7530 9.0284 0.0437 35.2350 27.2800 0.0656 38.5150 32.5080 0.0874 39.6910 36.4720 0.1093 40.1760 40.5320 0.1311 39.6530 44.1290 0.1530 38.3510 47.3680 0.1748 36.4280 50.3180 0.1967 34.5200 53.2 470 0.2185 32.2570 55.9190 0.2404 29.7110 58.3560 0. 2 622 26.9470 60.5750 0.2841 24 .1130 62.7870 0.3059 21.0440 64.7910 0.3278 17.7900 66.5960 0.3496 14.4030 68.2120 ale = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 12.4750 10.3660 0.0437 31.6430 31.3180 0.0656 34.3630 37.3400 0.0874 35.1450 41.9310 0.1093 35.1080 46.2880 0.1311 34.1530 50.0600 File No.: 1501350.301 Page C-26 of C-173 Revision:

0 F0306-0J R2 e Structural Integrity Associates, Inc. 0.1530 32.4990 0.1748 30.3000 0.1967 27.9290 0.2185 25.2670 0.2404 22.3890 0. 2 622 19.3590 0.2841 16.1060 0.3059 12.7240 0.3278 9.2694 0.3496 6.5215 a/c = 0.7500 Crack Depth Kdeepest 4.370E-03 10.7370 0.0437 26.8200 0.0656 28.8510 0.0874 29.1970 0.1093 29.0250 0.1311 28.0920 0.1530 26.5870 0.1748 24.6430 0.1967 22.1720 0.2185 19.4430 0.2404 16.5270 0.2622 13.4840 0.2841 10.3160 0.3059 7.0906 0.3278 5.2080 0.3496 5.7058 a/c = 1.0000 Crack Depth Kdeepest 4.370E-03 9.2864 0.0437 22.8270 0.0656 24.3070 0.0874 24.3160 0.1093 24.0430 0.1311 23.1390 0.1530 21.7 670 0.1748 20.0390 0.1967 17.5230 0.2185 14.7790 0.2404 11.8760 0. 2622 8.8788 0.2841 5.8584 0.3059 4.1909 0.3278 4.6159 0.3496 5.0381 Load Case 8:IAS Min 2-d SIF Input by User 53.3760 56.3200 59.4770 62.3540 64.9740 67.3600 68.9130 70.2350 71.3440 72.2570 Ksurface 10.7310 32.2340 38.3010 42.8570 47.1710 50.8820 54.1300 57.0050 59.8050 62.3310 64.6140 66.6820 68.3900 69.9020 71.2350 72.4030 Ksurface 10.9030 32.6100 38.6490 43.1320 47.3690 50.9970 54.1600 56.9520 59.4490 61. 6800 63.6820 65.4850 67.2970 68.9440 70.4380 71.7940 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\INAUX.MNN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-0 3 -0.2444 0.0437 -0.3412 0.0656 -0.1435 0.0874 0.1357 0.1093 0.4708 0.1311 0.8610 0.1530 1. 2979 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface -0.0943 -0.2715 -0.3108 -0.3311 -0.3513 -0.3623 -0.3653 Page C-27 of C-173 F030 6-0 IR2 e Structural Integrity Associates, Inc. 0.1748 1.7747 -0.3610 0.1967 2.3066 -0.3554 0.2185 2.8784 -0.3436 0.2404 3.4863 -0.3260 0.2622 4.1265 -0.3027 0.2841 5.0222 -0.2796 0.3059 5.9880 -0.2497 0.3278 7.0173 -0.2128 0.3496 8.1021 -0.1688 ale = 0.1667 Crack Depth Kdeepest Ksurface 4.370E-03

-0.2399 -0.1088 0.0437 -0.3307 -0.3091 0.0656 -0.1347 -0.3513 0.0874 0.1399 -0.3715 0.1093 0.4748 -0.3916 0.1311 0.8647 -0.4015 0.1530 1.3010 -0.4023 0.1748 1. 7771 -0.3949 0.1967 2. 2972 -0.3780 0.2185 2.8530 -0.3520 0.2404 3.4408 -0.3171 0. 2 622 4.0564 -0.2734 0.2841 4.8701 -0.2217 0.3059 5.7392 -0.1592 0.3278 6.6578 -0.0856 0.3496 7.6179 -1.203E-03 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03

-0.2360 -0.1200 0.0437 -0.3221 -0.3380 0.0656 -0.1277 -0.3823 0.0874 0.1430 -0.4024 0.1093 0.4772 -0.4225 0.1311 0.8662 -0.4314 0.1530 1.3015 -0.4305 0.1748 1.7761 -0.4208 0.1967 2.2862 -0.3953 0.2185 2.8287 -0.3583 0.2404 3.3998 -0.3100 0.2622 3.9950 -0.2506 0.2841 4.7436 -0.1770 0.3059 5.5359 -0.0894 0.3278 6.3666 0.0123 0. 3496 7.22 77 0.1278 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03

-0.2298 -0.1359 0.0437 -0.3087 -0.3792 0.0656 -0.1173 -0.4266 0.0874 0.1471 -0.4463 0.1093 0.4795 -0.4664 0.1311 0.8664 -0.4739 0.1530 1.2991 -0.4706 0.1748 1. 77 07 -0.4575 0.1967 2.2649 -0.4196 0.2185 2.7870 -0.3669 0.2404 3.3323 -0.2994 0. 2622 3.8966 -0.2175 0.2841 4.5486 -0.1123 0.3059 5.2276 0. 0115 0.3278 5.9282 0.1536 File No.: 1501350.301 Page C-28 of C-173 Revision:

0 F0306-0 I R2 e Structural Integrity Associates, Inc. 0.3496 6.6431 0.3138 a/c = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03

-0.2197 -0.1492 0.0437 -0.2888 -0.4129 0.0656 -0.1003 -0.4622 0.0874 0.1588 -0.4808 0.1093 0.4824 -0.4953 0.1311 0.8569 -0.4948 0.1530 1.2735 -0.4813 0.1748 1.7254 -0.4562 0.1967 2.1962 -0.4078 0.2185 2.6904 -0.3435 0.2404 3.2034 -0.2636 0.2622 3.7307 -0.1684 0.2841 4.3305 -0.0493 0.3059 4.9496 0. 0872 0.3278 5.5815 0.2410 0.3496 6.2177 0. 4116 a/c = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03

-0.1991 -0.1712 0.0437 -0.2498 -0.4678 0. 0656 -0.0687 -0.5197 0.0874 0.1775 -0.5363 0.1093 0.4813 -0.5406 0.1311 0.8288 -0.5258 0.1530 1.2114 -0.4945 0.1748 1. 6224 -0.4485 0.1967 2.0454 -0.3820 0.2185 2.4835 -0.2980 0.2404 2.9318 -0.1970 0. 2 622 3.3861 -0.0795 0.2841 3.8838 0.0626 0.3059 4.3843 0.2202 0.3278 4.8756 0.3926 0.3496 4.4750 0.5791 ale = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03

-0.1710 -0.1771 0.0437 -0.1969 -0.4787 0.0656 -0.0275 -0.5273 0.0874 0.1987 -0.5384 0.1093 0.4713 -0.5383 0.1311 0.7805 -0.5194 0.1530 1.1187 -0.4844 0.1748 1.4800 -0.4353 0.1967 1.8591 -0.3682 0.2185 2.2502 -0.2867 0.2404 2.6485 -0.1916 0.2622 3.0497 -0.0835 0.2841 3.4761 0.0432 0.3059 3.2815 0.1827 0.3278 1.8430 0.3344 0.3496 -0.3031 0.4977 a/c = 1.0000 Crack Depth Kdeepest Ksurface 4.370E-03

-0.1476 -0.1799 0.0437 -0.1541 -0.4821 0.0656 4.512E-03

-0.5278 File No.: 1501350.301 Page C-29 of C-173 Revision:

0 F03 0 6-01R2 e Structural Integrity Associates, Inc. 0.0874 0.2129 0.1093 0.4585 0.1311 0.7349 0.1530 1. 0354 0.1748 1.3545 0.1967 1.6957 0.2185 2.0460 0.2404 2.4010 0. 2 622 2.5997 0.2841 1.5904 0.3059 0.1449 0.3278 -1.7967 0.3496 -4.3229 Load Case 9:Residual Type: Stress Coefficient Coefficient Coefficient Coefficient Coefficients Input co C1 C2 C3 30.0000 0.0000 0.0000 0.0000 Load Case 10:0BE -0.5345 -0.5311 -0.5091 -0.4717 -0.4209 -0.3540 -0.2754 -0.1858 -0.0863 0. 0271 0 .1511 0.2852 0.4289 by User Type: Stress Coefficients Input by User Coefficient CO Coefficient C1 Coefficient C2 Coefficient C3 Load Case 11:DW 3.3100 0.0000 0.0000 0.0000 Type: Stress Coefficients Input by User Coefficient CO Coefficient C1 Coefficient C2 Coefficient C3 Load Case 12:SLID Max 2-d SIF Input by User 0.7290 0.0000 0.0000 0.0000 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\SLID.MXN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-03 4.6760 0.0437 12.2520 0.0656 13.6730 0.0874 14.4430 0.1093 15.2790 0.1311 15.8610 0.1530 16.2510 0.1748 16.4900 0.1967 16.7970 0.2185 1 6.9950 0.2404 17.1020 0.2622 17.1310 0.2841 17.1790 0.3059 17.0690 0.3278 16.8160 0.3496 16.4370 a/c = 0.1667 Crack Depth Kdeepest File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 1. 7434 5.2852 6.3022 7.0711 7.8616 8.5606 9.1883 9.7581 10.3480 10.9030 11.4250 11.9190 12.6350 13.3360 14.0220 14.6940 Ksurface Page C-30 of C-173 F0306-01R2 e Structural Integrity Associates, Inc. 4.370E-03 4.5904 2. 0135 0.0437 11.9740 6.0889 0.0656 13.3330 7.2553 0.0874 14.0530 8.1380 0.1093 14.7720 9.0653 0.1311 15.2290 9.8931 0.1530 15.4870 10.6440 0.1748 15.5870 11.3340 0.1967 15.7530 12.0250 0.2185 15.8150 12.6700 0.2404 15.7900 13.2740 0.2622 15.6930 13.8410 0.2841 15.6380 14.6100 0.3059 15.4570 15.3530 0.3278 15.1640 16.0710 0.3496 14.7760 16.7660 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 4.5166 2.2210 0.0437 11.7390 6.7060 0.0656 13.0470 7.9874 0.0874 13.7270 8.9577 0.1093 14.3540 9.9902 0.1311 14.7130 10.9170 0.1530 14.8670 11.7640 0.1748 14.8590 12.5460 0.1967 14.9160 13.3150 0.2185 14.8720 14.0300 0.2404 14.7450 14.6980 0.2622 14.5510 15.3220 0.2841 14.4160 16.1310 0.3059 14.1790 16.9070 0.3278 13.8550 17.6500 0.3496 13.4590 18.3620 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 4.3994 2.5173 0.0437 11.3720 7.5875 0.0656 12.6030 9.0331 0.0874 13.2230 10.1290 0.1093 13.7150 11.3120 0.1311 13.9320 12.3810 0.1530 13.9370 13.3650 0.1748 13.7730 14.2790 0.1967 13.6710 15.1600 0.2185 13.4740 15.9770 0.2404 13.2000 16.7360 0.2622 12.8650 17.4430 0.2841 12.6130 18.3100 0.3059 12.2960 19.1320 0.3278 11.9270 19.9100 0.3496 11.5210 20.6450 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 4.2095 2. 7 672 0.0437 10.8320 8.3390 0.0656 11. 9710 9.9322 0.0874 12.5210 11.1450 0.1093 12.9170 12.3920 0.1311 13.0480 13.5030 0.1530 12.9750 14.5120 0.1748 12.7420 15.4400 File No.: 1501350.301 Page C-31 of C-173 Revision:

0 F0306-01R2 e Structuralfnlegrity Associates, Inc. 0.1967 12.5360 16.3760 0.2185 12.2410 17.2450 0.2404 11.8760 18.0540 0. 2 622 11.4580 18.8080 0.2841 11.0820 19.5780 0.3059 10.6520 20.2990 0.3278 10.1820 20.9720 0.3496 9.6836 21.6010 ale = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 3.8181 3.1771 0.0437 9.7328 9.5724 0.0656 10.6940 11.4090 0.0874 11.1150 12.8180 0.1093 11.3350 14.1610 0.1311 11.3110 15.3350 0.1530 11.1030 16.3790 0.1748 10.7520 17.3190 0.1967 10.3640 18.3430 0.2185 9.9006 19.2950 0.2404 9.3812 20.1810 0.2622 8.8225 21.0090 0.2841 8.2344 21.5980 0.3059 7.6156 22.1290 0.3278 6.9812 22.6080 0.3496 6.5215 23.0390 ale = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 3.2861 3.2889 0.0437 8.2576 9.8521 0.0656 8.9998 11.7040 0.0874 9.2731 13.1030 0.1093 9.4290 14.4360 0.1311 9.3833 15.5940 0.1530 9.1875 16.6200 0.1748 8.8769 17.5410 0.1967 8.4222 18.4560 0.2185 7.9000 19.2980 0.2404 7.3284 20.0760 0.2 622 6. 7235 20.7990 0.2841 6.1071 21.4250 0.3059 5.4784 22.0010 0.3278 5.1800 22.5320 0.3496 5.4938 23.0230 ale = 1.0000 Crack Depth Kdeepest Ksurface 4.370E-03 2.8420 3.3414 0.0437 7.0357 9. 9669 0.0656 7.6020 11.8110 0.0874 7.7596 13.1900 0.1093 7.8652 14.5010 0.1311 7.8040 15.6350 0.1530 7.6199 16.6360 0.1748 7.3434 17.5330 0.1967 6.8439 18.3550 0.2185 6.2842 19.1040 0.2404 5.6820 19.7920 0. 2 622 5.0543 20.4260 0.2841 4.4367 21.0750 0.3059 4.1481 21.6810 0.3278 4.3995 2 2.2480 0.3496 4.6493 2 2.7820 FileNo.: 1501350.301 Page C-32 of C-173 Revision:

0 F 0306-01 R2 S} Structural Integrity Associates, Inc."' Load Case 13:SLID Min 2-d SIF Input by User The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\SLID.MNN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-03 0.5070 0.0437 1. 7294 0.0656 2.1993 0.0874 2. 62 97 0.1093 3.1175 0.1311 3.6085 0.1530 4.1054 0.1748 4.6096 0.1967 5.1754 0.2185 5.7569 0.2404 6.3539 0. 2 622 6.9657 0.2841 7.8217 0.3059 8.7150 0.3278 9.6436 0.3496 10.6050 ale = 0.1667 Crack Depth Kdeepest 4.370E-03 0.4979 0.0437 1. 6935 0.0656 2.1503 0.0874 2. 5671 0.1093 3.0337 0.1311 3.5016 0.1530 3.9737 0.1 7 48 4.4513 0.1967 4.9802 0.2185 5.5217 0.2404 6.0756 0.2622 6.6415 0.2841 7.4017 0.3059 8.19 1 5 0.3278 9.0091 0.3496 9.8522 a/c = 0.2 000 Crack Depth Kdeepest 4.370E-03 0.4900 0.0437 1.6629 0.0656 2.1088 0.0874 2.5142 0.1093 2.9637 0.1311 3.4129 0.1530 3.8648 0.1748 4.3210 0.1967 4.8203 0.2185 5. 32 98 0.2404 5.8493 0.26 2 2 6.3784 0.2841 7.0628 0.3059 7.7706 0.3278 8.5004 0.3496 9.2501 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 0.1836 0.5793 0.7095 0.8199 0.9304 1.034 7 1.1348 1.2318 1.3295 1.4260 1. 5218 1. 6173 1.7489 1.8839 2.0222 2.1639 Ksurface 0.2122 0.6737 0.8277 0.9593 1.0951 1.224 7 1. 3503 1.4733 1. 6035 1.7340 1. 8654 1.9980 2.1709 2.3490 2.5323 2. 7208 Ksurface 0.2343 0.7463 0.9185 1. 0664 1. 2217 1.3709 1. 5162 1. 6592 1.8145 1.9714 2.1302 2.2914 2.4963 2.7077 2.9257 3.1502 Page C-33 of C-173 F030 6-0l R2 lJ Structural Integrity Associates, Inc. ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 0.4774 0.2657 0.0437 1.6148 0.8499 0.0656 2.0438 1.0483 0.0874 2.4320 1.2197 0.1093 2.8554 1.4029 0.1311 3.2764 1.5800 0.1530 3.6982 1.7 537 0.1748 4.1223 1. 9254 0.1967 4.5774 2.1169 0.2185 5.0392 2. 3116 0.2404 5.5075 2.5100 0. 2 622 5.9821 2.7123 0.2841 6.5548 2.9630 0.3059 7.1420 3.2224 0.3278 7.7426 3.4902 0.3496 8.3548 3.7665 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 0.4570 0.2923 0.0437 1.5443 0.9401 0.0656 1. 9536 1.1629 0.08 7 4 2.3234 1.3566 0.1093 2. 7204 1.558 1 0.1311 3.1133 1. 7524 0.1530 3.5052 1. 9424 0.1748 3.8976 2.1299 0.1967 4. 3114 2.3434 0.2185 4.7291 2.5605 0.2404 5.1506 2.7816 0.2622 5.5 7 57 3.0070 0.2841 6. 0772 3.2576 0.3059 6.5888 3.5150 0.3278 7.1091 3.7792 0.3496 7. 6362 4.0501 ale = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 0.4148 0.3359 0.0437 i. 3992 1.0887 0.0656 1.7682 1.3521 0.0874 2.1008 1. 5834 0.1093 2.4458 1. 8148 0.1311 2.7836 2. 0371 0.1530 3.1172 2.2538 0.1748 3.4482 2.4670 0.1967 3.7831 2.7171 0.2185 4 .1170 2. 9712 0.2404 4.4497 3.2300 0.2622 4.7811 3.4937 0.2841 5.1492 3.7408 0.3059 5.5187 3.9914 0.3278 5.8872 4.2457 0.3496 5. 9572 4.5037 ale = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 0.3576 0.3479 0.0437 1.2047 1.1249 0.0656 1.5210 1. 3954 0.0874 1.8051 1. 6322 0.1093 2.1056 1. 8 667 FileNo.: 1501350.301 Page C-34 of C-173 Revision:

0 F0306-0JR2 e Structural Integrity Associates, Inc."' 0.1311 2.4004 2.0909 0.1530 2.6918 2.3083 0.1748 2.9811 2. 5211 0.1967 3.2612 2.7531 0.2185 3.5389 2.9861 0.2404 3.8141 3.2206 0.2622 4. 08 67 3.4570 0.2841 4.3843 3.6939 0.3059 4.4445 3.9333 0.3278 4.2545 4.1755 0.3496 3.9093 4.4204 a/c = 1.0000 Crack Depth Kdeepest Ksurface 4.370E-03 0.3098 0.3535 0.0437 1.0423 1.1413 0.0656 1.3147 1.4144 0.0874 1. 5585 1. 6531 0.1093 1.8216 1.8877 0.1311-----*2 0801 2*.1109 0.1530 2.3359 2.3266 0.1748 2.5901 2.5369 0.1967 2.8249 2.7526 0.2185 3.0563 2.9668 0.2404 3.2842 3.1801 0. 2622 3.3935 3.3932 0.2841 3.2636 3.6197 0.3059 3.0308 3.8480 0.3278 2.6884 4.0782 0.3496 2.2199 4.3106 Total Load Sub-Blocks:

6 Load Sub-Block

1. 1 Load Sub-block Name: Heatup/Cooldown Maximum Load Case Multiplier 1.0000 1.0000 1.0000 Minimum Load Case Multiplier 1.0000 1.0000 1.0000 Load Case ID HU/CD Max Residual ow Load Case ID HU/CD Min Residual DW Growth Law: ASMEAusteniticAir Cycles/Time:

140 Temperature:

650 Load Sub-Block

1. 2 Load Sub-block Name: Cooldown II Maximum Load Case Multiplier Load Case 1.0000 CD II Max 1.0000 Residual 1.0000 DW Minimum Load Case Multiplier Load Case 1.0000 CD II Min 1.0000 Residual 1.0000 ow Growth Law: ASMEAusteniticAir Cycles/Time:

8 Temperature:

650 File No.: 1501350.301 Revision:

0 ID ID Page C-35 of C-173 F0306-01 R2

(;Structural Integrity Associates, Inc.'" Load Sub-Block

1. 3 Load Sub-block Name: Inadvertent Aux Spray Maximum Load Case Multiplier 1.0000 1.0000 1.0000 Minimum Load Case Multiplier 1.0000 1.0000 1.0000 Load Case ID IAS Max Residual ow Load Case ID IAS Min Residual ow Growth Law: ASMEAusteniticAir Cycles/Time:

2 Temperature:

650 Load Sub-Block

1. 4 Load Sub-block Name: Unload Maximum L oad Case Multiplier 1.0000 1.0000 1.0000 Minimum Load Case Multiplier 1.0000 1.0000 1.0000 Load Case ID Unload Max Residual ow Load Case ID Unload Min Residual ow Growth Law: ASMEAusteniticAir Cycles/Time:

2744 Temperature:

650 Load Sub-Block

1. 5 Load Sub-block Name: OBE Maximum Load Case Multiplier 2.0000 1.0000 1.0000 Minimum Load Case Multiplier 0.0000 1.0000 1.0000 Load Case ID OBE Unload Max ow Load Case ID OBE Unload Max ow Growth Law: ASMEAusteniticAir Cycles/Time:

1 6 Temperature:

650 Load Sub-Block

1. 6 Load Sub-block Name: Step Load Inc/Dec Maximum Load Case Multiplier

1. 0000 1.0000 1.0000 Minimum Load Case Multiplier

1. 0000 1.0000 1.0000 Load Case ID SLID Max ow Residual Load Case ID SLID Min ow Residual Growth Law: ASMEAusteniticAir Cycles/Time:

210 Temperature:

650 File No.: 1501350.301 Revision:

0 Page C-36 of C-173 F0306-0JR2 lJ Structural Integrity Associates, Inc."' Material:

1 Sample Material 1: Only a sample *************

Austenitic Stainless Steel in Air environment (U.S. Customary Units) The Fatigue Crack Growth Rate (in/cycle) is g i ven by: da/dN = Co*(Delta K)An where Delta K = Kmax -Kmin n =the slope of the l og (da/dN) versus log (Delta K) 3.3 Co = a scaling constant Co C*S C is given by: T is the metal temperature in deg F S is a scaling parameter to account for R ratio and is given by: s 1.0 1.0 + 1.8

• R -43.35 + 57.97

• R where R = Kmin I Kmax for R <= 0 for 0 < R <= 0.7 9 for 0.79 < R < 1 No. of Data in the KIC Tab l e = 3 Crack Depth 0.0000 0.1000 2.0000 messages/Warnings:

KIC 500.0000 500.0000 500.0000 Number of Warnings in Inputs: 0 ----------ANALYSIS RESULTS ---------STRESS INTENSITY FACTORS Load Case # 1: HU/CD ------------

Crack a c 0.0800 0.3125 0.0900 0.3516 0.1000 0.3906 0.1100 0.4297 0.1200 0.4688 0.1300 0. 5078 File No.: 1501350.301 Revision:

0 Max Dimensions a/t 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 ------------c/a 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 K at tip a 27.7227 28.0975 28.3497 28.5794 28.5318 28.4842 Page C-3 7 of C-173 F0306-0 !R2 e Structural Integrity Associates, Inc.'" 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.23 00 0.24 00 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1. 0156 1.0547 1. 0938 1.132 8 1.1719 1.2109 1.2500 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0. 6865 0.7094 0.7323 Load Case # 2: HU/CD Min a 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 Crack Dimensions c a/t 0.3125 0.1831 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0. 6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1.0156 1. 054 7 1. 0938 1.1328 1.1719 1.2109 1.2500 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 Load Case # 3: CD II Max a 0.0800 0.0900 0.1000 0 .1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.17 00 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 Crack Dimensions c a/t 0.3125 0.1831 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.742 2 0.7813 0.8203 0.8594 0.8984 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4 577 0.4805 0.5034 0.5263 File No.: 1501350.301 Revision:

0 3.9063 3.9063 3.9063 3. 9063 3.9063 3.90 63 3.9063 3.9063 3.9063 3.9063 3.90 63 3.9063 3.9063 3.9063 3.9063 3.9063 3.906 3 3.9063 3.9063 c/a 3.9063 3.9063 3.90 63 3.9063 3.9063 3.9063 3.9063 3.9063. 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.90 63 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 c/a 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.90 63 3.9063 3.90 63 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 28.2300 27.9503 27.5397 27.0745 26.63 25 26.2120 25.7553 25.2265 24.6845 24.0677 23.4509 22.7663 22.079 2 21.4100 20.7459 20.0343 19.2903 18.5195 17.7102 K at tip a 1.2952 1.4530 1. 6275 1.8029 1.9879 2.1730 2.3665 2. 5611 2.7 616 2.9647 3.1741 3.3894 3. 6071 3.8296 4.0530 4.2817 4.5105 4.7444 4.9785 5.2455 5.5218 5.8035 6.0887 6.3770 6.6698 K at tip a 33.7249 34.1561 34.4303 34.6765 34.5774 34.4784 34.1 212 33.7321 33.1795 32.55 84 31.9639 31.3939 30.7782 30.0718 29.3488 28.5321 Page C-38 ofC-173 F0306-0 lR2 e Structural Integrity Associates, Inc. 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.9375 0.9766 1. 0156 1. 054 7 1. 0938 1.1328 1.1719 1.2109 1.2500 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 Load Case # 4: CD II Min a 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 Crack Dimensions c a/t 0.3125 0.1831 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1. 0156 1.0547 1.0938 1.1328 1.1719 1. 2109 1.2500 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 Load Case # 5: Unload Max a 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 Crack Dimensions c a/t 0.3125 0.1831 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1.0156 1.0547 1.0938 1.1328 1.1719 1.2109 1.2500 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0.4119 0.4348 0.4577 0.4805 0.5034 0. 52 63 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 File No.: 1501350.301 Revision:

0 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3: 9063 c/a 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 c/a 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 27.7153 26.8133 25.9082 25.0162 24.1277 23.1792 22.1897 21.1664 20.0945 K at tip a 0.8522 0.9997 1.1662 1.3339 1.5160 1. 6981 1. 8923 2.0880 2.2920 2.4995 2. 7130 2.9320 3.1540 3.3821 3. 6113 3.8472 4.0832 4.3254 4.5678 4.8425 5.1263 5.4160 5.7098 6.0070 6.3090 K at tip a 12.7283 12.9928 13.2144 13.4268 13.5256 13.6244 13.6391 13.6434 13.5944 13.5230 13.4658 13.4217 13.3634 13.2769 13.1853 13.0647 12.9441 12.7977 12.6503 12.5312 12.4200 12.2922 12.1530 12.0044 11.8423 Page C-39 of C-173 F030 6-0 I R2 e Structural Integrity Associates, Inc. Load Case # 6: Unload Min a 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 Crack Dimensions c a/t 0.3125 0.1831 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0. 7813 0.8203 0.8594 0.8984 0.9375 0.9766 1.0156 1. 054 7 1.0938 1.132 8 1.1719 1.2109 1.2500 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 Load Case # 7: IAS Max a 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 Crack Dimensions c a/t 0.3125 0.1831 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1.0156 1.0547 1.0938 1.132 8 1.1719 1.2109 1.2500 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 52 63 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 Load Case # 8: IAS Min c/a 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 c/a 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 ------------

Crack Dimensions

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a c a/t c/a 0.0800 0.3125 0.1831 3.9063 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 File No.: 1501350.301 Revision:

0 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 K at tip a 2.3087 2.4902 2.6834 2. 87 65 3.0683 3.2602 3.4522 3.6442 3.8368 4.0297 4.2298 4.4366 4.6444 4.8541 5.0643 5. 27 68 5.4893 5.7045 5.9198 6.1695 6.4290 6.6924 6.9583 7.2267 7.4986 K at tip a 41.3345 41.8895 42.2350 42.5446 42.4110 42.2774 41.8113 41.3041 40.5853 39.7778 38.9973 38.2416 37.4266 36.4937 35.5393 34.4632 33.3871 32.2001 31.0089 29.8227 28.6377 27.3749 26.0591 24.6993 23.2763 K at tip a 0.0586 0.1875 0.3393 0.4930 0.6696 0.8463 1.0415 Page C-40 of C-173 F0306-0l R2 e Structural Integrity Associates, Inc. 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.5859 0. 6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1.0156 1. 054 7 1. 0938 1.132 8 1.1719 1.2109 1. 2500 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 Load Case # 9: Residual ------------

Crack Dimensions a c a/t 0.0800 0.3125 0.1831 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0. 7813 0.8203 0.8594 0.8984 0.9375 0.9766 1.0156 1. 054 7 1.0938 1.1328 1.1719 1.2109 1.2500 Load Case # 10: OBE 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 c/a 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 ------------

Crack Dimensions

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a c a/t c/a 0.0800 0.3125 0.1831 3.9063 0.0900 0.3516 0.2059 3.9063 0.1000 0.3906 0.2288 3.9063 0.1100 0.4297 0.2517 3.9063 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0. 7813 0.8203 0.8594 0.8984 0.9375 File No.: 1501350.301 Revision:

0 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3. 9063 3.9063 1. 23 90 1.4490 1.6641 1.8846 2.1100 2.3397 2.5777 2.8173 3.0658 3.3143 3. 5710 3.8281 4.1160 4.4127 4. 7166 5.0253 5.3380 5.6564 K at tip a 15.4155 16.4062 17.4799 18.5285 19.5564 20.5674 21.5642 22.5492 23.5243 24.4912 25.4905 26.5237 27.5562 28.5885 29.6214 30.6554 31.6909 32.7283 33.7680 34.9827 36.2562 37.5407 38.8362 40.1427 41.4602 K at tip a 1.7008 1.8102 1.9286 2.0443 2.1577 2.2693 2. 37 92 2.4879 2.5955 2.7022 2.8125 2. 92 65 3.0404 3.1543 3.2682 3.3823 3.4966 Page C-41 of C-1 73 F0306-0 IR2 e Structural Integrity Associates, Inc."' 0.2500 0. 2 600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.9766 1. 0156 1.0547 1.0938 1.1328 1.1719 1.2109 1. 2500 Load Case # 11: OW 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 ------------

Crack Dimensions

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a c a/t c/a 0.0800 0.3125 0.1831 3.9063 0.0900 0.3516 0.2059 3.9063 0.1000 0.3906 0.2288 3.9063 0.1100 0.4297 0.2517 3.9063 0.1200 0.4688 0.2746 3.9063 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1. 0156 1.0547 1. 0938 1.1328 1.1719 1. 2109 1.2500 Load Case# 12: SLID Max 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 . 0. 5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 ------------

Crack Dimensions

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a c a/t c/a 0.0800 0.3125 0.1831 3.9063 0.0900 0.3516 0.2059 3.9063 0.1000 0.3906 0.2288 3.9063 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1. 0156 1.0547 1.0938 1.132 8 1.1719 1.2109 1.2500 Load Case # 13: SLID Min File No.: 1501350.301 Revision:

0 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3. 9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3. 6110 3.7257 3.8598 4.0003 4.1420 4.2849 4.4291 4.5744 K at tip a 0.3746 0.3987 0.4248 0.4502 0.4752 0.4998 0.5240 0.5479 0.5716 0.5951 0.6194 0.6445 0. 6696 0.6947 0. 7198 0.7449 0.7701 0.7953 0.8206 0.8501 0.8810 0.9122 0.9437 0.9755 1.0075 K at tip a 12.9640 13.2300 13.4520 13.6645 13.7610 13.8575 13.8678 13.8675 13.8129 13.7356 13. 6724 13. 6223 13.5577 13.4643 13.3656 13.2372 13.1088 12.9537 12.7976 12.6701 12.5507 12.4138 12.2650 12.1065 11.9343 Page C-42 of C-173 F0306-0IR2 e Structural Integrity Associates, Inc. ------------

Crack Dimensions

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a 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c 0.3125 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0.7 813 0. 8203 0.8594 0.8984 0.9375 0.9766 1.0156 1. 054 7 1. 0938 1.1328 1.1719 1. 2109 1.2500 a/t c/a 0.1831 3.9063 0.2059 3.9063 0.2288 3.9063 0. 2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 52 63 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7 323 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 CRACK GROWTH ANALYSIS RESULTS Blocks da/dn da/dt Subblock Cycles/ Time 0.0000 1.764E-05 140.0000 3.408E-05 8.0000 6.749E-05 2.0000 1.026E-06 2744.0000 3.1 84E-08 16.0000 1.105E-06 210.0000 0.5490 1.791E-05 140.0000 3.463E-05 8.0000 6.870E-05 2.0000 1.041E-06 2744.0000 3.250E-08 16.0000 1.121E-06 210.0000 1.0900 1.819E-05 140.0000 3.518E-05 8.0000 6.991E-05 2.0000 1.055E-06 2744.0000 3.291E-08 16.0000 1.136E-06 210.0000 1.6245 1.838E-05 140.0000 3.557E-05 8.0000 7.078E-05 2.0000 1.065E-06 2744.0000 3.524E-08 16.0000 1.146E-06 210.0000 2.1543 1.854E-05 140.0000 3.589E-05 8.0000 7.153E-05 2.0000 1.072E-06 2744.0000

• 3. 77 SE-08 16.0000 1.154E-06 210.0000 2.6801 1.870E-05 140.0000 3.621E-05 8.0000 7.228E-05 2.0000 1.079E-06 2744.0000 File No.: 1501350.301 Revision:

0 Crack Dim. a 0.0800 0.0833 0.0866 0.0898 0.0931 0.0964 a/t 0.1831 0.1 906 0.1981 0.2056 0. 2131 0.2206 K at tip a 2.2931 2.4743 2. 6672 2.8600 3.0518 3.2435 3.4355 3.6276 3.8203 4. 0134 4. 2137 4.4206 4.6285 4.8384 5.0487 5.2615 5.4743 5.6897 5.9053 6.1553 6.4151 6.6787 6.9449 7.2136 7.4858 Kmax 43.5128 49.5150 57.1246 28.5184 16.5045 28.7541 43.9742 49.9988 57.6550 28.9344 16.6738 29.1707 44.4295 50.4766 58.1794 29.3444 16.8416 29.5813 44.8795 50.9377 58.6700 29.7753 17.0036 30.0125 45.3259 51.3914 59.1 470 30.2118 17.1632 30.4490 45.7692 51.8419 59.6209 30.6450 Kmin 17.0853 16.6423 15.8486 18.0988 13.1 029 18.0832 17.4595 17.0129 16.2127 18.4814 13.2022 18.4657 17.8277 17.3774 16.5706 18.8579 13.3014 18.8421 18.2363 17.7832 16. 9711 19.2732 13.3873 19.2573 18.6573 18.2015 17.3847 19.7003 13.4686 19.6843 19.0752 18.6167 17.7951 20.1243 Sub Delta Block K No 26.4275 32.8727 41.2759 10.4196 3.4017 10.6709 26.5147 32.9860 41.4424 10.4531 3.4716 10.7051 26.6018 33.0992 41.6088 10.4866 3.540 2 10.7393 26.6432 33.1546 41.6988 10.5021 3.6163 10.7 552 26.6686 33.1899 41.7623 10.5114 3.6947 10.7647 26.6941 33.2252 41.8258 10.5208 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 Page C:-43 of C-173 F0306-01 R2 e S/ructurallnlegrily Associates, Inc. 4.036E-08 16.0000 1.162E-06 210.0000 3.2019 1.885E-05 140.0000 3.653E-05 7.302E-05 8.0000 2.0000 1.086E-06 2744.0000 4.307E-08 16.0000 1.170E-06 210.0000 3.7198 1.900E-05 140.0000 3.685E-05 8.0000 7.375E-05 2.0000 1.093E-06 2744.0000 4.587E-08 16.0000 1.177E-06 210.0000 4.2340 1.916E-05 140.0000 3. 716E-05 8.0000 7.449E-05 2.0000 1.100E-06 2744.0000 4.878E-08 16.0000 1.185E-06 210.0000 4.7448 1.929E-05 140.0000 3.744E-05 8.0000 7.515E-05 2.0000 1.106E-06 2744.0000 5.179E-08 16.0000 1.191E-06 210.0000 5.2552 1.922E-05 140.0000 3. 731E-05 8.0000 7.498E-05 2.0000 1.100E-06 2744.0000 5.489E-08 16.0000 1.185E-06 210.0000 5.7680 1.914E-05 140.0000 3.718E-05 8.0000 7.480E-05 2.0000 1.093E-06 2744.0000 5.808E-08 16.0000 1.178E-06 210.0000 6.2834 1.906E-05 140.0000. 3.704E-05 8.0000 7.462E-05 2.0000 1.087E-06 2744.0000 6.139E-08 16.0000 1.171E-06 210.0000 6.8015 1.898E-05 140.0000 3.690E-05 8.0000 7.442E-05 2.0000 1.080E-06 2744.0000 6.480E-08 16.0000 1.164E-06 210.0000 7.3222 1.889E-05 140.0000 3.675E-05 8.0000 7.421E-05 2.0000 1.073E-06 2744.0000 6.831E-08 16.0000 1.156E-06 210.0000 7.8458 1.881E-05 140.0000 3.660E-05 8.0000 7.400E-05 2.0000 1.067E-06 2744.0000 7.194E-08 16.0000 1.149E-06 210.0000 8.3733 1.865E-05 140.0000 3.631E-05 8.0000 7.349E-05 2.0000 1.056E-06 2744.0000 7.567E-08 16.0000 1.137E-06 210.0000 File No.: 1501350.301 Revision:

0 0.0997 0.1029 0.1062 0.1095 0.1128 0.1161 0.1193 0.1226 0.1259 0.1292 0.1324 0.2281 0.2356 0.2431 0.2506 0.2581 0.2656 0.2731 0.2806 0.2881 0.2956 0.3031 17.3221 30.8824 46.2095 52.2894 60.0918 31.0753 17.4803 31.3128 46.6471 52.7342 60.5599 31.5028 17.6378 31.7 405 47.0820 53.1763 61.0254 31.9277 17.7947 32.1655 47.5071 53.6068 61.4766 32.3471 17.9479 32.5850 47.8390 53.9219 61.7804 32.7271 18.0634 32.9642 48.1688 54.2348 62.0820 33.1049 18.1784 33.3412 48.4967 54.5457 62.3816 33.4807 18.2929 33.7162 48.8226 54.8548 62.6793 33.8546 18.4070 34.0894 49.1467 55.1621 62.9753 34.2267 18.5206 34.4607 49.4692 55.4677 63.2696 34.5971 18.6338 34.8304 49.7590 55.7328 63.5122 34.9533 18.7340 35.1856 13.5498 20.1082 19.4900 19.0290 18.2025 20.5452 13.6309 20.5291 19.9021 19.4384 18.6072 20.9634 13.7119 20.9472 20.3116 19.8453 19.0092 21.3790 13.7929 21.3627 20.7189 20.2501 19.4094 21.7921 13.8708 21.77 57 21.1271 20.6573 19.8149 22.2026 13.9114 22.1861 21.5332 21.0624 20.2182 22.6109 13.9520 22.5944 21.9372 21.4655 20.6195 23.0172 13.9925 23.0006 22.3394 21.8667 21.0189 23.4216 14.0330 23.4050 22.7398 22.2661 21.4165 23.8242 14.0735 23.8076 23 .1385 22.6639 21.8125 24.2252 14.1139 24.2085 23.5369 23.0619 22.2097 24.6246 14.1416 24.6079 3.7724 10.7743 26.7195 33.2605 41.8893 10.5301 3.8494 10.7838 26.7450 33.2957 41.9527 10.5394 3.9259 10.7933 26.7704 33.3310 42.0162 10.5487 4.0017 10.8029 26.7882 33.3567 42.0672 10.5550 4.0771 10.8093 26.7119 33.2645 41.9655 10.5245 4.1520 10.7781 26.6357 33.1724 41.8638 10.4940 4.2264 10.7469 26.5594 33.0802 41.7621 10.4635 4.3004 10.7156 26.4832 32.9881 41.6604 10.4330 4.3740 10.6844 26.4069 32.8959 41.5587 10.4025 4.4471 10.6532 26.3307 32.8038 41.4570 10.3720 4.5200 10.6219 26.2220 32.6709 41.3025 10.3288 4.5925 10.5777 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 Page C-44 of C-173 F0306-0 I R2 lJ Structural Integrity Associates, Inc.'" 8.9072 1.839E-05 140.0000 3.581E-05 7.257E-05 8.0000 2.0000 1.039E-06 2744.0000 7.950E-08 16.0000 1.119E-06 210.0000 9.4493 1.812E-05 140.0000 3.532E-05 8.0000 7.165E-05 2.0000 1.022E-06 2744.0000 8.344E-08 16.0000 l.lOlE-06 210.0000 9.9998 1.786E-05 140.0000 3.483E-05 7.073E-05 8.0000 2.0000 1.005E-06 2744.0000 8.749E-08 16.0000 1.083E-06 210.0000 10.5589 1.760E-05 140.0000 3.433E-05 6.980E-05 8.0000 2.0000 9.886E-07 2744.0000 9.166E-08 16.0000 1.065E-06 210.0000 11.1269 1.734E-05 140.0000 3.384E-05 8.0000 6.888E-05 2.0000 9.720E-07 2744.0000 9.594E-08 16.0000 1.047E-06 210.0000 11.7041 1.708E-05 140.0000 3.335E-05 8.0000 6.795E-05 2.0000 9.555E-07 2744.0000 1.003E-07 16.0000 1.030E-06 210.0000 12.2924 1.672E-05 140.0000 3.267E-05 6.663E-05 8.0000 2.0000 9.335E-07 2744.0000 1.048E-07 16.0000 1.006E-06 210.0000 12.8945 1.633E-05 140.0000 3.193E-05 6.519E-05 8.0000 2.0000 9.099E-07 2744.0000 1.095E-07 16.0000 9.807E-07 210.0000 13.5116 1.595E-05 140.0000 3 .119E-05 6.375E-05 8.0000 2.0000 8.866E-07 2744.0000 1.142E-07 16.0000 9.556E-07 210.0000 14.1444 1.557E-05 140.0000 3.047E-05 8.0000 6.233E-05 2.0000 8.636E-07 2744.0000 1.190E-07 16.0000 9.309E-07 210.0000 14.7933 1.519E-05 140.0000 2.975E-05 8.0000 6.093E-05 2.0000 8.410E-07 2744.0000 1.240E-07 16.0000 9.065E-07 210.0000 15.4590 1.482E-05 140.0000 2.904E-05 8.0000 File No.: 1501350.301 Revision:

0 0.1357 0.1390 0.1423 0.1456 0.1488 0.1521 0.1554 0.1587 0.1619 0.1652 0.1685 0.1718 0.3106 0.3181 0.3256 0.3331 0.3406 0.3481 0.3556 0.3631 0.3706 0.3781 0.3856 0.3931 50.0023 55.9403 63.6810 35.2898 18.8156 35.5205 50.2442 56.1464 63.8484 35.6248 18.8968 35.8540 50.4849 56.3512 64.0145 35.9585 18.9776 36.1862 50.7242 56.5547 64.1793 36.2910 19.0582 36.5172 50.9624 56.7571 64.3430 36.6223 19.1385 36.8469 51.1995 56.9583 64.5055 36.9525 19.2186 37.1756 51.3905 57.1021 64.5940 37.2632 19.2800 37.4845 51.5647 57.2253 64.6561 37.5666 19.3347 37.7859 51.7380 57.3476 64.7172 37.8690 19.3893 38.0864 51.9105 57.4689 64.7775 38.1705 19.4436 38.3860 52.0821 57.5895 64.8370 38.4713 19.4977 38.6847 52.2529 57.7093 23.9357 23.4610 22.6094 25.0225 14.1509 25.0058 24.3331 23.8588 23.0078 25.4191 14.1603 25.4024 24.7292 24.2552 23.4048 25.8143 14.1695 25.7976 25.1240 24.6504 23.8006 26.2083 14.1788 26.1916 25.5176 25.0444 24.1952 26.6011 14.1881 26.5844 25.9102 25.4374 24.5887 26.9928 14.1973 26.9762 26.3037 25.8321 24.9855 27.3836 14.1881 27.3671 26.6970 26.2268 25.3827 27.7736 14.1724 27.7571 27.0894 26.6207 25.7791 28.1626 14.1568 28.1462 27.4809 27.0136 26.1745 28.5508 14.1411 28.5344 27.8715 27.4057 26.5692 28.9381 14.1254 28.9218 28.2614 27.7971 26.0666 32.4793 41.0716 10.2673 4.6646 10.5147 25.9111 32.2876 40.8406 10.2057 4.7365 10.4516 25.7557 32.0960 40.6097 10.1442 4.8081 10.3886 25.6003 31.9043 40.3787 10.0827 4.8794 10.3255 25.4448 31.7126 40.1478 10.0212 4.9505 10.2625 25.2894 31.5210 39.9168 9.9597 5. 0213 10.1995 25.0867 31_.2700 39.6085 9.8796 5.0919 10.1174 24.8677 30.9985 39.2733 9.7930 5.1623 10.0288 24.6486 30.7269 38.9382 9.7064 5.2325 9.9402 24.4296 30.4553 38.6030 9.6198 5.3025 9.8516 24.2106 30.1838 38.2678 9.5332 5. 3723 9.7630 23.9915 29.9122 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 Page C-45 of C-1 73 F0306-0l R2 e Structural Integrity Associates, Inc.'" 5.953E-05 2.0000 8.186E-07 2744.0000 1.291E-07 16.0000 8.825E-07 210.0000 16.1422 1.446E-05 140.0000 2.834E-05 5.816E-05 8.0000 2.0000 7.967E-07 2744.0000 1.344E-07 16.0000 8.589E-07 210.0000 16.8429 1.412E-05 140.0000 2.768E-05 5.687E-05 8.0000 2.0000 7.762E-07 2744.0000 1.402E-07 16.0000 8.369E-07 210.0000 17.5614 1.378E-05 140.0000 2.704E-05 8.0000 5.559E-05 2.0000 7.560E-07 2744.0000 1.462E-07 16.0000 8.152E-07 210.0000 18.2983 1.345E-05 140.0000 2.640E-05 8.0000 5.433E-05 2.0000 7.362E-07 2744.0000 1.523E-07 16.0000 7.938E-07 210.0000 19.0543 1.312E-05 140.0000 2.576E-05 8.0000 5.308E-05 2.0000 7.166E-07 2744.0000 1.586E-07 16.0000 7.727E-07 210.0000 19.8302 1.279E-05 140.0000 2.514E-05 8.0000 5.184E-05 2.0000 6.973E-07 2744.0000 1.651E-07 16.0000 7.519E-07 210.0000 20.6268 1.247E-05 140.0000 2.452E-05 8.0000 5.061E-05 2.0000 6.782E-07 2744.0000 1.717E-07 16.0000 7.315E-07 210.0000 21.4458 1.212E-05 140.0000 2.386E-05 8.0000 4.929E-05 2.0000 6.581E-07 2744.0000 1.785E-07 16.0000 7.097E-07 210.0000 22.2802 1.175E-05 140.0000 2.313E-05 8.0000 4.784E-05 2.0000 6.702E-07 2744.0000 1.855E-07 16.0000 6.862E-07 210.0000 23.1147 1.138E-05 140.0000 2.242E-05 4.640E-05 8.0000 2.0000 7.027E-07 2744.0000 1.926E-07 16.0000 6.972E-07 210.0000 23.9433 1.102E-05 140.0000 2.171E-05 4.499E-05 8.0000 2.0000 7.309E-07 2744.0000 File No.: 1501350.301 Revision:

0 0.1750 0.1783 0.1816 0.1849 0.1882 0.1914 0.1947 0.1980 0.2013 0.2045 0.2078 0.4006 0.4081 0.4156 0.4231 0.4306 0.4381 0.4456 0.4531 0.4606 0.4681 0.4756 64.8957 38.7712 19.5516 38.9827 52.4261 57.8315 64.9568 39.0730 19.6065 39.2825 52.6355 57.9919 65.0564 39.4058 19.6751 39.6134 52.8448 58.1522 65.1558 39.7384 19.7437 39.9440 53.0539 58.3123 65.2551 40.0708 19.8122 40.2745 53.2629 58.4723 65.3542 40.4032 19.8806 40.6049 53.4717 58.6321 65.4533 40.7354 19.9491 40.9351* 53.6806 58.7920 65.5522 41.0675 20.0175 41.2653 53.8748 58.9334 65.6274 41.3940 20.0802 41.5897 54.0481 59.0485 65.6682 41.7122 20.1348 41.9056 54.2213 59.1635 65.7089 42.0304 20.1893 42.2216 54.3946 59.2785 65.7498 42.3487 26.9630 29.3246 14.1097 29.3084 28.6528 28.1898 27.3583 29.7127 14.0947 29.6965 29.0706 28.6089 27.7794 30.1277 14.0884 30.1116 29.4882 29.0277 28.2004 30.5426 14.0822 30.5265 29.9057 29.4464 28.6212 30.9573 14.0760 30.9412 30.3231 29.8650 29.0419 31.3719 14.0697 31.3558 30.7403 30.2834 29.4624 31.7864 14.0635 31.7703 31.1575 30.7018 29.8829 32.2008 14.0572 32.1847 31.5756 31.1214 30.3051 32.6155 14.0453 32.5995 31.9951 31.5427 30.7296 33.0308 14.0252 33.0149 32.4145 31.9640 31.1542 33.4461 14.0051 33.4302 32.8340 32.3853 31.5788 33.8614 37.9326 9.4466 5.4420 9.6743 23.7733 29.6416 37.5985 9.3603 5. 5119 9.5861 23.5649 29.3830 37.2769 9.2780 5.5867 9.5018 23.3565 29.1245 36.9554 9.1958 5.6615 9.4176 23.1482 28.8659 36.6339 9.1135 5.7362 9.3333 22.9398 28.6073 36.3124 9. 0313 5.8109 9.2491 22.7314 28.3487 35.9908 8.9490 5.8856 9.1648 22.5231 28.0901 35.6693 8.8668 5.9603 9.0806 22.2992 27.8121 35.3223 8.7785 6.0349 8.9901 22.0530 27.5058 34.9385 8.6814 6.1096 8.8907 21.8068 27.1995 34.5547 8.5843 6.1843 8.7913 21.5605 26.8932 34.1710 8.4873 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 Page C-46 of C-1 73 F0306-0l R2 e Structural Integrity Associates, Inc."' 1.999E-07 16.0000 7.308E-07 210.0000 24.7679 1.066E-05 140.0000 2.102E-05 8.0000 4.360E-05 2.0000 7.549E-07 2744.0000 2.074E-07 16.0000 7.598E-07 210.0000 25.5907 1.031E-05 140.0000 2.034E-05 8.0000 4.224E-05 2.0000 7.750E-07 2744.0000 2.151E-07 16.0000 7.845E-07 210.0000 26.4138 9.964E-06 140.0000 1.968E-05 8.0000 4.090E-05 2.0000 7.915E-07 2744.0000 2.230E-07 16.0000 8.052E-07 210.0000 27.2400 9.593E-06 140.0000 1.896E-05 8.0000 3.944E-05 2.0000 8.037E-07 2744.0000 2.310E-07 16.0000 8.213E-07 210.0000 28.0724 9.220E-06 140.0000 1.823E-05 8.0000 3.796E-05 2.0000 8.121E-07 2744.0000 2.393E-07 16.0000 8.332E-07 210.0000 28.9133 8.854E-06 140.0000 1. 752E-05 3.652E-05 8.0000 2.0000 8.171E-07 2744.0000 2.477E-07 16.0000 8.413E-07 210.0000 29.7647 8.498E-06 140.0000 1.683E-05

3. 511E-05 8.0000 2.0000 8.190E-07 2744.0000 2.563E-07 16.0000 8.460E-07 210.0000 8.150E-06 140.0000 1.615E-05 3.373E-05 8.0000 2.0000 8.180E-07 2744.0000 2.651E-07 16.0000 8.474E-07 210.0000 31.5069 7.811E-06 140.0000 1.549E-05 8.0000 3.239E-05 2.0000 8.144E-07 2744.0000 2.742E-07 16.0000 8.458E-07 210.0000 32.4018 7.478E-06 140.0000 1.484E-05 8.0000 3.106E-05 2.0000 8.082E-07 2744.0000 2.834E-07 16.0000 8.414E-07 210.0000 33.3165 7.126E-06 140.0000 1.415E-05 8.0000 2.966E-05 2.0000 7.981E-07 2744.0000 2.928E-07 16.0000 8.327E-07 210.0000 File No.: 1501350.301 Revision:

0 0.2111 0.2144 0.2177 0.2209 0.2242 0.2275 0.2308 0.2340 0.2373 0.2406 0.2439 0.4831 0.4906 0.4981 0.5056 0. 5131 0.5206 0.5281 0.5356 0.5431 0.5506 0.5581 20.2439 42.5375 54.5679 59.3936 65.7906 42.6669 20.2984 42.8536 54.7413 59.5088 65.8315 42.9853 20.3530 43.1696 54.9148 59.6241 65.8725 43.3037 20.4076 43.4858 55.0670 59.7126 65.8788 43.6140 20.4539 43.7936 55.2118 59.7919 65.8732 43.9215 20.4974 44.0985 55.3568 59.8714 65.8677 13.9850 33.8456 33.2536 32.8067 32.0034 34.2768 13.9648 34.2610 33.6732 33.2282 32.4282 34.6922 13.9447 34.6765 34.0929 33.6497 32.8530 35.1077 13.9246 35.0921 34.5142 34.0733 33.2804 35.5240 13.8962 35.5085 34.9362 34.4976 33.7089 35.9407 13.8649 35.9252 35.3583 34.9221 34.1375 44.2291 36.3575 20.5409 13.8336 44.4036 36.3421 55.5019' 35.7806 59.9510 65.8623 44.5369 20.5844 44.7088 55.6472 60.0308 65.8571 44.8448 20.6280 45.0142 55.7927 60.1108 65.8521 45.1530 20.6716 45.3197 55.9367 60.1888 65.8444 45.4606 20.7146 45.6248 56.0596 60.2402 65.8021 45.7604 20.7496 45.9218 35.3467 34.5662 36.7745 13.8023 36.7592 36.2031 35.7715 34.9951 37.1916 13.7710 37.1764 36.6257 36.1965 35.4242 37.6089 13.7398 37.5938 37.0487 36.6218 35.8538 38.0265 13.7078 38.0114 37.4735 37.0494 36.2861 38.4451 13.6678 38.4302 6.2589 8.6919 21.3143 26.5869 33.7872 8.3902 6.3336 8.5925 21.0681 26.2806 33.4034 8.2931 6.4083 8.4931 20.8219 25.9744 33.0196 8.1960 6.4830 8.3937 20.5527 25.6393 32.5984 8.0900 6.5577 8.2851 20.2756 25.2943 32.1643 7.9808 6.6325 8.1733 19.9984 24.9493 31.7302 7.8716 6.7073 8.0614 19.7213 24.6043 31.2961 7. 7 62 4 6.7821 7.9496 19.4442 24.2593 30.8620 7.6532 6.8569 7.8378 19.1670 23.9143 30.4278 7.5440 6.9318 7. 7260 18.8880 23.5669 29.9907 7.4341 7.0068 7.6134 18.5861 23.1908 29.5160 7.3153 7.0818 7.4916 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 Page C-4 7 of C-173 F0306-0 !R2 e Structural Integrity Associates, Inc."' 34.2547 6.785E-06 140.0000 1.348E-05 8.0000 2.829E-05 2.0000 7.857E-07 2744.0000 3.024E-07 16.0000 8.215E-07 210.0000 35.2189 6.454E-06 140.0000 1.283E-05 8.0000 2.696E-05 2.0000 7.714E-07 2744.0000 3.122E-07 16.0000 8.080E-07 210.0000 36.2117 6.133E-06 140.0000 1.220E-05 8.0000 2.566E-05 2.0000 7.554E-07 2744.0000 3.222E-07 16.0000 7.925E-07 210.0000 37.2358 5.822E-06 140.0000 8.0000 2.441E-05 2.0000 7.378E-07 2744.0000 3.325E-07 16.0000 7.753E-07 210.0000 38.2944 5.522E-06 140.0000 1.100E-05 8.0000 2.320E-05 2.0000 7.188E-07 2744.0000 3.429E-07 16.0000 7.564E-07 210.0000 39.3903 5.229E-06 140.0000 1.043E-05 8.0000 2.201E-05 2.0000 6.990E-07 2744.0000 3.546E-01 16.0000 7.367E-07 210.0000 40.5267 4.944E-06 140.0000 9.867E-06 2.085E-05 8.0000 2.0000 6.786E-07 2744.0000 3.680E-07 16.0000 7.162E-07 210.0000 41.7072 4.669E-06 140.0000 9.324E-06 8.0000 1.973E-05 2.0000 6.571E-07 2744.0000 3.817E-07 16.0000 6.944E-07 210.0000 42.9360 4.403E-06 140.0000 8.801E-06 8.0000 1.865E-05 2.0000 6.346E-07 2744.0000 3.958E-07 16.0000 6.715E-07 210.0000 44.2177 4.147E-06 140.0000 8.296E-06 8.0000 1.760E-05 2.0000 6.114E-07 2744.0000 4.103E-07 16.0000 6.477E-07 210.0000 45.5572 3.901E-06 140.0000 7.810E-06 1.659E-05 8.0000 2.0000 5.877E-07 2744.0000 4.252E-07 16.0000 6.232E-07 210.0000 46.9602 3.664E-06 140.0000 7.342E-06 8.0000 File No.: 1501350.301 Revision:

0 0.2472 0.2504 0.2537 0.2570 0.2603 0.2635 0.2668 0.2701 0.2734 0.2767 0.2799 0.2832 0.5656 0.5731 0.5806 0.5881 0.5956 0.6031 0.6106 0.6181 0.6256 0.6331 0.6406 0.6481 56.1827 60.2918 65.7600 46.0604 20.7846 46.2189 56.3061 60.3437 65.7182 46.3607 20.8196 46.5163 56.4297 60.3959 65.6766 46.6612 20.8547 46.8140 56.5535 60.4483 65.6352 46.9619 20.8899 47.1119 56.6777 60.5010 65.5942 4 7. 2629 20.9251 47.4100 56.8352 60.5862 65.5842 47.5991 20.9725 47.7434 57.0414 60.7189 65.6198 47.9866 2 1.037 4 48.1282 57.2489 60.8529 65.6565 48.3753 21.1027 48.5141 57.4575 60.9880 65.6945 48.7652 2 1.168 2 48.9013 57.6674 6 1.1244 65.7337 49.1563 21.2340 49.2897 57.8785 61.2619 65.7741 49.5486 21.3001 49.6793 58.0908 61.4007 37.8985 37.4771 36.7186 38.8640 13. 6277 38.8491 38.3238 37.9051 37.1514 39.2831 13.5877 39.2683 38.7493 38.3334 37.5844 39.7024 13.5477 39.6878 39.1751 38.7619 38.0177 40.1220 13.5077 40.1075 39.6011 39.1907 38.4513 40.5419 13.4677 40.5275 40.0631 39.6553 38.9205 40.9980 13.4332 40.9836 40.5776 40.1722 39.4416 41.5070 13.4068 41.4927 41.0933 40.6903 39.9640 42.0171 13.3805 42.0029 41.6102 41.2097 40.4875 42.5285 13.3542 42.5144 42.1283 41.7302 41.0123 43.0411 13.3279 43.0271 42.6476 42.2520 41.5383 43.5549 1 3.3016 43.5409 43.1681 42.7750 1 8.2842 22.8147 29.0414 7.19 64 7.15 68 7.3 698 17.9823 22.4386 28.5668 7.0776 7.2 319 7.2480 17.6804 22.0625 28.0921 6.9587 7.3070 7.1262 17.3784 21.6864 27.6175 6.8399 7.3822 7.0044 17.0765 21.3103 27.1429 6. 7210 7.4575 6.8826 16.7720 20.9309 26.6638 6. 6011 7.5393 6. 7598 16.4638 20.5467 26.1782 6.4796 7.6306 6.6355 16.1556 20.1625 25.6926 6.3581 7. 7222 6. 5112 15.8473 19.7783 25.2070 6.2366 7.8140 6.3869 15.5 39 1 19.3941 24.7214 6.1151 7.9061 6. 2 626 15.2309 19.0099 24.2 358 5.9937 7.9985 6.1384 14.9227 18.6257 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 Page C-48 of C-173 F0306-0 I R2 e Structural Integrity Associates, Inc.'" 1.562E-05 2.0000 5.634E-07 2744.0000 4.405E-07 16.0000 5.982E-07 210.0000 48.4354 3.421E-06 140.0000 6.860E-06 8.0000 1.462E-05 2.0000 5.369E-07 2744.0000 4.561E-07 16.0000 -5. 705E-07 210. oooo 49.9942 3.182E-06 140.0000 6.388E-06 1.363E-05 8.0000 2.0000 5.096E-07 2744.0000 4.721E-07 16.0000 5.420E-07 210.0000 51.6464 2.955E-06 140.0000 5.937E-06 8.0000 1.269E-05 2.0000 4.823E-07 2744.0000 4.886E-07 16.0000 5.134E-07 210.0000 53.4021 2.739E-06 140.0000 5.507E-06 8.0000 1.179E-05 2.0000 4.551E-07 2744.0000 5.054E-07 16.0000 4.849E-07 210.0000 55.2724 2.533E-06 140.0000 5.098E-06 8.0000 1.093E-05 2.0000 4.283E-07 2744.0000 5.227E-07 16.0000 4.566E-07 210.0000 57.2700 2.338E-06 140.0000 4.709E-06 8.0000 1. 011E-05 2.0000 4.019E-07 2744.0000 5.404E-07 16.0000 4.288E-07 210.0000 59.4097 2.151E-06 140.0000 4.337E-06 9.329E-06 8.0000 2.0000 3.758E-07 2744.0000 5.585E-07 16.0000 4.012E-07 210.0000 61.6848 2.220E-06 140.0000 3.963E-06 8.538E-06 8.0000 2.0000 3.485E-07 2744.0000 5.770E-07 16.0000 3.724E-07 210.0000 64.0829 2.292E-06 140.0000 3.610E-06 8.0000 7.792E-06 2.0000 3.221E-07 2744.0000 5.960E-07 16.0000 3.443E-07 210.0000 66.6180 2.323E-06 140.0000 3.279E-06 7.089E-06 8.0000 2.0000 2.965E-07 2744.0000 6.154E-07 16.0000 3.172E-07 210.0000 69.3123 2.317E-06 140.0000 2.968E-06 6.429E-06 8.0000 2.0000 2.719E-07 2744.0000 File No.: 1501350.301 Revision:

0 0.2865 0.2898 0.2930 0.2963 0.2996 0.3029 0.3061 0.3094 0.3127 0.3160 0.3193 0.6556 0.6631 0.6706 0.6781 0.6856 0.6931 0.7006 0.7081 0. 7156 0.7231 0.7306 65.8156 49.9421 21.3665 50.0701 58.2848 61.5161 65.8266 50.3300 21.4264 50.4550 58.4734 61.6242 65.8277 50.7168 21.4842 50.8386 58.6631 61.7334 65.8300 51.104 7 21.5422 51.2234 58.8540 61.8439 65.8336 51.4939 21.6006 51.6094 59.0462 61.9556 65.8383 51.8843 21.6593 51.9967 59.2396 62.0685 65.8443 52.2759 21.7182 52.3851 59.4325 62.1806 65.8488 52.6682 21.7769 52.7742 59.6069 62.2689 65.8220 53.0546 21.8289 53.1574 59.7826 62.3584 65.7965 53.4423 21.8812 53.5418 59.9594 62.4492 65.7721 53.8313 21.9337 53.9274 60.1374 62.5411 65.7490 54.2214 42.0655 44.0699 13.2754 44.0560 43.6920 43.3016 42.5968 44.5877 13.2424 44.5739 44.2179 43.8302 43.1304 45.1072 13.2070 45.0935 44.7449 44.3601 43.6652 45.6280 13.1717 45.6144 45.2732 44.8912 44.2012 46.1500 13.1364 46.1364 45.8027 45.4235 44.7384 46.6731 13 .1011 46.6597 46.3334 45.9570 45.2768 47.1975 13.0659 47.1842 46.8655 46.4919 45.8167 47.7233 13.0301 47.7100 47.4011 47.0305 46.3606 48.2520 12.9874 48.2389 47.9379 47.5703 46.9058 48.7819 12.9447 48.7689 48.4759 48 .1114 47.4522 49.3131 12.9020 49.3002 49.0151 48.6536 47.9998 49.8455 23.7502 5. 8722 8. 0911 6.0141 14.5928 18.2145 23.2298 5.7423 8.1840 5.8811 14.2555 17.7939 22.6973 5.6095 8. 2772 5.7451 13.9182 17.3733 22.1649 5.4767 8.3706 5.6090 13.5808 16.9527 21. 6324 5.3439 8.4642 5.4730 13.2435 16.5321 21.0999 5. 2112 8.5582 5.3369 12.9062 16.1116 20.5675 5.0784 8.6523 5.2009 12.5671 15.6887 20.0321 4.9449 8.7468 5.0641 12.2059 15.2384 19.4614 4.8026 8.8415 4.9185 11.8447 14.7881 18.8906 4.6604 8.9365 4.7728 11.4835 14.3378 18.3199 4.5182 9.0317 4. 6272 11.1223 13.8875 17.7492 4.3759 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 Page C-49 of C-173 F0306-0l R2 SJ Structural Integrity Associates, Inc. 6.353E-07 16.0000 2. 911E-07 210.0000 72.1910 2.279E-06 140.0000 2.677E-06 8.0000 5.810E-06 2.0000 2.484E-07 2744.0000 6.556E-07 16.0000 2.660E-07 210.0000 75.2808 2.216E-06 140.0000 2.595E-06 8.0000 5.232E-06 2.0000 2.259E-07 2744.0000 6.764E-07 16.0000 2.421E-07 210.0000 Crack Depth, a= 0.3291 exceeds Number of Runtime Warnings:

0 *** End of pc-CRACK output File No.: 1501350.301 Revision:

0 21.9866 54.3142 0.3 2 25 0.7381 60.3166 62.6343 65.7271 54.6127 22.0398 54.7022 0.3258 0.7456 60.4971 62.7286 65.7064 55.0052 22.0932 55.0915 user-specified maximum= 0.3278 *** 12.8594 9.1272 5 49.8327 4.4815 6 49.5555 10.7611 1 49.1971 13.4372 2 48.5487 17.1784 3 50.3790 4.2337 4 12.8168 9.2230 5 50.3664 4.3358 6 50.0972 10.3999 1 49.7418 12.9869 2 49.0987 16.6077 3 50.9138 4.0914 4 12.7742 9.3190 5 50.9013 4.1902 6 Page C-50 of C-173 F0306-0 IR2 e Structural Integrity Associates, Inc. Fatigue Crack Growth-Variable Aspect Ratio pc-CRACK 4.1 CS Version Control No. 4.1.0.0 Structural Integrity Associates, Inc. www.structint.com pccrack@structint.com Date: 10/29/2015 10:57 Input Data read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\pcCRACK\FCG-Fixed.pcf Analysis Title: DCPP Spray Line Units Selected:

US Customary Linear Dimensions

-inches Stress -ksi Load -kips Temperature

-deg F Time -hours Analysis Type: Crack Growth (LEFM) Crack Growth Calculation Method -Crack Stepping Crack Model: 306-Semi-Elliptical Circumferential Crack in Cy l inder on the I nside Surface (API 579) Crack Depth, a = 0.0800 Ha l f Crack Length, c 0.3125 Wall T hickness, t = 0.4370 Ins i de Radius, Ri = 1.8130 Aspect ratio allowed to vary Maximum a/t = 0.75 Crack Depth Print Increment for SIF Tabulation=

0.01 Maximum Aspect Ratio (c/a) for SIF Tabulation = 5 Aspect Ratio Increment for SIF Tabulation

= 0.25 Total Load Cases: 13 Load Case 1:HU/CD Max 2-d SIF Input by User The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\HUCD.MXN No. of aspect ratios (a/c) in the tables = 8 a/c = 0.1250 Crack Depth Kdeepest Ksurface 4.370E-03 10.4510 3.9032 0.0437 26.8310 11.8060 0.0656 29.5570 14.0540 0.0874 30.7780 15.7380 0.1093 32. 0710 17.4750 0.1311 32.7520 19.0020 0.1530 32.9650 20.3650 0.1748 32,8050 21.5940 0.1967 32.7170 22.8730 0.2185 32.3480 24.0670 0.2404 31.7350 25.1860 0.2622 30.9160 26.2380 0.2841 29.7890 27.7710 0.3059 28.2260 29.2630 0.3278 26.2690 30.7150 0.3496 23.9630 32.1260 a/c = 0.1667 File No.: 1501350.301 Revision:

0 Page C-51 of C-173 F0306-01 R2 e Structural Integrity Associates, Inc."' Crack Depth Kdeepest Ksurface 4.370E-03 10.2590 4.5078 0.0437 26.2190 13.5920 0.0656 28 0 8130 16.1640 0.0874 29.9340 18.0900 0.1093 30.9780 20.1180 0.1311 31.3940 21.9160 0.1530 31.3250 23.5370 0.1748 30.8710 25.0150 0.1967 30.5010 26.4860 0.2185 29.8620 27.8470 0.2404 28.9970 29.1100 0.2622 27.9440 30.2830 0.2841 26.7090 31.8800 0.3059 25.1260 33.4090 0.3278 23.2340 34.8710 0.3496 21.0750 36.2690 a/c = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 10.0940 4. 9720 0.0437 25.7010 14.9640 0.0656 28.1890 17.7850 0.0874 29.2300 19.8970 0.1 093 30.0790 22.1480 0.1311 30.2870 24.1550 0.1530 30.0010 25.9760 0.1748 29.3190 27.6450 0.1967 28.7290 29.2660 0.2185 27.8830 30.7570 0.2404 26.8240 32.1310 0. 2 622 25.5900 33.3990 0.2841 24.2720 35.0450 0.3059 22.6760 36.6020 0.3278 20.8370 38.0720 0.3496 18.7960 39.4580 a/c = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 9.8321 5.6352 0.0437 24.8910 16.9230 0.0656 27.2190 20.1 000 0.0874 28.1420 22.4770 0.1093 28.7070 25.0490 0.1311 28.6150 27.3560 0.1530 28.0140 29.4610 0.1748 27.0060 31.4060 0.1967 26.1010 33.2410 0.2185 24.9580 34.9190 0.2404 23.6210 36.4540 0.2622 22.1290 37.8580 0.2841 20.6920 39.5750 0.3059 19.0780 41.1720 0.3278 17.3190 42.6510 0.3496 15.4500 44.0180 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 9.4074 6.1941 0.0437 23.6990 18.5910 0.0656 25.8360 22.0860 0.0874 26.6190 24.7140 0.1093 26.9910 27.4090 0.1311 26.7330 29.7930 File No.: 1501350.301 Page C-52 of C-173 Revision:

0 F0306-0 IR2 e Structural Integrity Associates, Inc.'" 0.1530 25.9910 31.9370 0.1748 24.8640 33.8890 0.1967 23.7690 35.8250 0.2 185 2 2.4550 37.5950 0.2404 2 0.9690 39.2140 0.2622 19.3490 40.6950 0. 284 , 1 17.7170 42.1800 0.3059 15.9420 43.5360 0.3278 14. 0550 44.7680 0.3496 12.0880 45.8850 ale = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 8.5324 7.1113 0.0437 21.2790 21.3290 0.0656 23.0480 25.3480 0.0874 23.5740 28.3890 0.1093 23.6000 31.2740 0.1311 2 3.0510 33.7670 0.1530 22.0680 35.9560 0.1748 20.7490 37.9000 0.1967 19.3320 39.9930 0.2185 17.7370 41.9050 0.2404 16.0090 43.6540 0.2622 14.1880 45.2550 0.2841 12.2420 46.3080 0.3059 10.2180 47.2180 0.3278 8.1538 47.9960 0.3496 6.5215 48.6530 ale = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 7.3428 7.3615 0.0437 18.0280 21.9460 0.0656 19.3480 25.9910 0.0874 19.5900 29.0030 0.1093 19.5280 31.8580 0.1311 18.9900 34.3100 0.1530 18.0990 36.4540 0.1748 16.9350 38.3530 0.1967 15.4390 40.2090 0.2185 13.7840 41.8890 0.2404 12.0140 43.4150 0.2622 10.1680 44.8030 0.2841 8.2553 45.9590 0.3059 6.3129 46.9930 0.3278 5.1927 47.9160 0.3496 5. 58 96 48.7370 ale = 1.0000 Crack Depth Kdeepest Ksurface 4.370E-03 6.3496 7.4789 0.0437 15.3380 22.1970 0.0656 16.3000 26.2 200 0.0874 16.3230 29.1800 0.1093 16.1940 31.9830 0.1311 15.6720 34.3790 0.1530 14.8600 36.4670 0.1748 13.8290 38.3130 0.1967 12.2920 39.9680 0.2185 10.6140 41.45 2 0 0.2404 8.8402 42.7910 0.262 2 7.0094 44.0030 0.2841 5.1774 45.2280 0.3059 4.1674 46.3 490 File No.: 1501350.301 Page C-53 of C-173 Revision:

0 F030 6-0 1R2 e Structural Integrity Associates, Inc.'" 0.3278 0.3496 4.4973 4.8250 Load Case 2:HU/CD Min 2-d SIF Input by User The SIF originally read No. of aspect ratios (a/c) ale = 0.1250 Crack Depth Kdeepest 4.370E-03 0.1714 0.0437 0.8047 0.0656 1.1531 0.0874 1.5159 0.1093 1.9355 0.1311 2.3815 0.1530 2.8518 0.1748 3.3440 0.1967 3.8949 0.2185 4.4723 0.2404 5.0743 0.2622 5.6988 0.2841 6.5727 0.3059 7.4985 0.3278 8. 4722 0.3496 9.4884 ale = 0.1667 Crack Depth Kdeepest 4.370E-03 0.1684 0.0437 0.7895 0.0656 1.1299 0.0874 1.4831 0.1093 1.8909 0.1311 2.3240 0.1530 2.7803 0.1748 3.2575 0.1967 3.7827 0.2185 4.3308 0.2404 4.8999 0.2622 5.4880 0.2841 6. 2723 0.3059 7.0977 0.3278 7.9603 0.3496 8.8555 ale = 0.2000 Crack Depth Kdeepest 4.370E-03 0.1657 0.0437 0.7765 0.0656 1.1100 0.0874 1.4553 0.1093 1.8532 0.1311 2.2756 0.1530 2.7203 0.1748 3.1850 0.1967 3.6893 0.2185 4.2137 0.2404 4.7563 0.2622 5.3150 0.2841 6.0281 0.3059 6.7738 0.3278 7.5485 File No.: 1501350.301 Revision:

0 47.3760 48.3170 from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\HUCD.MNN in the tables = 8 Ksurface 0.0594 0.1993 0.2538 0.3058 0.3579 0.4106 0.4646 0.5202 0.5767 0.6353 0.6961 0.7593 0.8424 0.9303 1. 0233 1.1213 Ksurface 0.0688 0.2347 0.3011 0.3649 0.4310 0.4983 0.5675 0.6388 0. 7183 0.8022 0.8904 0.9833 1.1020 1.2285 1. 3627 1. 504 7 Ksurface 0.0760 0. 2620 0.3375 0.4104 0.4873 0.5659 0.6467 0.7302 0.8275 0.9308 1.0403 1.1560 L 3022 1.4584 1. 6244 Page C-54 of C-173 F0306-0IR2 S} Structural Integrity Associates, Inc."' 0.3496 8.3479 1.8003 a/c = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 0.1615 0.0863 0.0437 0.7558 0.3009 0.0656 1. 07 87 0.3896 0.0874 1.4116 0.4756 0.1093 1. 7943 0.5680 0.1311 2.2002 0. 6627 0.1530 2.6270 0.7603 0.1748 3.0726 0.8612 0.1967 3.5454 0.9841 0.2185 4.0342 1.1154 0.2404 4.5369 1.2553 0.2622 5.0516 1. 4039 0.2841 5.6599 1.5897 0.3059 6.2881 1.7885 0.3278 6.9332 2.0002 0.3496 7. 5913 2.2247 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 0.1547 0.0951 0.0437 0. 7257 0.3358 0.0656 1.0364 0. 4371 0.0874 1. 3567 0.5360 0.1093 1.7209 0.6410 0.1311 2.1057 0.7488 0.1530 2.5088 0.8600 0.1748 2.9280 0.9749 0.1967 3.3674 1.114 7 0.2185 3.8194 1. 2636 0.2404 4.2818 1. 4217 0. 2 622 4.7526 1. 5890 0.2841 5.2981 1. 7808 0.3059 5.8575 1.9843 0.3278 6.4277 2.1992 0.3496 7.0035 2.4253 a/c = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 0.1406 0.1094 0.0437 0.6628 0.3935 0.0656 0.9479 0.5161 0.0874 1.2419 0.6367 0.1093 1.5684 0. 7629 0.1311 1.9107 0.8926 0.1530 2.2664 1. 0265 0.1748 2.6333 1.1650 0.1967 3.0077 1.3331 0.2185 3.3881 1. 5113 0.2404 3. 7725 1.6996 0.2622 4.1589 1.8981 0.2841 4.5847 2.0983 0.3059 5.0127 2.3073 0.3278 5.4362 2.5249 0.3496 5.1316 2.7510 a/c = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 0.1215 0.1134 0.0437 0.5788 0.4087 0.0656 0.8295 0.5366 File No.: 1501350.301 Page C-55 of C-173 Revision:

0 F0306-01 R2 e Structural Integrity Associates, Inc. 0.0874 1.0877 0.1093 1. 37 5 7 0.1311 1. 6771 0.1530 1.9896 0.1748 2. 3112 0.1967 2.6356 0.2185 2 .. 9639 0.2404 3.2941 0. 2 622 3.6241 0.2841 3.9792 0.3059 3.7631 0.3278 2.9125 0.3496 1. 6720 a/c = 1.0000 Crack Depth Kdeepest 4.370E-03 0.1055 0.0437 0.5080 0.0656 0.7296 0.0874 0.9576 0.1093 1. 2129 0.1311 1. 4795 0.1530 1.7554 0.1748 2.0387 0.1967 2. 3211 0.2185 2.6056 0.2404 2.8902 0.2622 2.9045 0.2841 2.2874 0.3059 1.4158 0.3278 0.2709 0.3496 -1.1900 Load Case 3:CD II Max 2-d SIF Input by User 0.6628 0.792 7 0.9252 1. 0611 1.2008 1.3592 1.5246 1.6968 1.8760 2.0636 2.2584 2.4601 2.6686 Ksurface 0.1153 0.4162 0.5470 0.6761 0.8075 0.9408 1.0769 1. 2160 1.3653 1. 5190 1.6770 1.8394 2.0154 2.1971 2.3843 2. 5771 The SIF originally read from C:\Users\c l ohse\Documents\ANSYS\PGE\1501350\TIFFANY\CDII

.MXN No. of aspect ratios (a/c) ale= 0.1250 Crack Depth Kdeepest 4.370E-03 12.7140 0.0437 32.6970 0.0656 35.9930 0.0874 37.4290 0.1093 38.9310 0.1311 39.6700 0.1530 39.8220 0.1 7 48 39.5090 0.1967 39.2 660 0.2185 38.6680 0.2404 37.7630 0. 2 622 36.5970 0.2841 34.9880 0.3059 32.8280 0.3278 30.1680 0.3496 27.0670 ale= 0.1667 Crack Depth Kdeepest 4.370E-03 12.4810 0.0437 31.9510 0.0656 35.0860 0.0874 36.4010 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 4.7459 14.3690 17.1130 19.1700 21.2930 23.1600 24.8260 26.3270 27.8900 29.3490 30.7150 31.9990 33.8670 35.6840 37.4520 39.1690 Ksurface 5. 4811 16.5440 19.6840 22.0360 Page C-56 of C-173 F0306-0 I R2 e Structural Integrity Associates, Inc. 0.1093 37.6000 24.5130 0.1311 38.0150 26.7100 0.1530 37.8260 28.6890 0.1748 37.1530 30.4930 0.1967 36.5690 32.2880 0.2185 35.6470 33.9480 0.2404 34.4400 35.4850 0.2622 32.9940 36.9110 0.2841 31.2740 38.8510 0.3059 29.1150 40.7050 0.3278 26.5640 42.4760 0.3496 23.6740 44.1650 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 12.2810 6.0457 0.0437 31.3190 18.2150 0.0656 34.3250 21.6580 0.0874 35.5430 24.2380 0.1093 36.5050 26.9860 0.1311 36.6680 29.4380 0.1530 36.2130 31.6590 0.1748 35.2640 33.6950 0.1967 34.4150 35.6710 0.2185 33.2430 37.4860 0.2404 31.8030 39.1560 0.2622 30.1430 40.6930 0.2841 28.3380 42.6880 0.3059 26.1820 44.5700 0.3278 23.7190 46.3430 0.3496 20.9970 48.0100 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03

11. 9620 6.8520 0.0437 30.3330 20.6000 0. 0656 33.1440 24.4770 0.0874 34.2190 27.3820 0.1093 34.8350 30.5200 0.1311 34.6330 33.3360 0.1530 33.7950 35.9040 0.1748 32.4480 38.2750 0.1967 31.2190 40.5090 0.2185 29.6900 42.5480 0.2404 27.9180 44.4090 0.2622 25.9510 46.1060 0.2841 24.0260 48.1790 0.3059 21.8770 50.1010 0.3278 19.5450 51.8740 0.3496 17.0720 53.5060 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03

11. 4450 7.5318 0.0437 28.8800 22.6330 0.0656 31.4580 26.8990 0.0874 32.3630 30.1080 0.1093 32.7450 33.3980 0.1311 32.3430 36.3060 0.1530 31.3370 38.9200 0.1748 29.8510 41.2980 0.1967 28.3950 43.6520 0.2185 26.6650 45.8000 0.2404 24.7190 47.7600 0.2622 22.6050 49.5470 File No.: 1501350.301 Page C-57 of C-173 Revision:

0 F0306-0 lR 2 e Structural Integrity Associates, Inc. 0.2841 20.4560 51.3330 0.3059 18.1260 52.9570 0.3278 15.6540 54.4260 0.3496 13.0810 55.7480 ale = 0.5000 Crack Depth Kdeepest Ksurface 4.3 7 0E-03 10.3810 8. 64 72 0.0437 25.9290 25.9670 0.0656 28.0600 30.8750 0.0874 28.6530 34.5880 0.1093 28.6170 38.1090 0.1311 27.8660 41.1480 0.1530 26.5750 43.8150 0.1748 24.8640 46.1800 0.1967 23.0280 48.7200 0.2185 20.9680 51.0350 0.2404 18.7430 53.1470 0.2622 16.4020 55.0740 0.2841 13.8960 56.3270 0.3059 11.2920 57.4000 0.3278 8.6359 58.3090 0.3496 6.5215 59.0650 a/c = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 8.9337 8.9515 0.0437 21.96 7 0 26.7200 0.0656 23.5500 31.6580 0.0874 23.8000 35.3370 0.1093 23.6620 38.8210 0.1311 22.9330 41.8100 0.1530 21.7 630 44.4210 0.1748 20.2530 46.7300 0.1967 18.3310 48.9810 0.2185 16.2110 51.0130 0.2404 13.9480 52.8540 0. 2 622 11.5890 54.5230 0.2841 9.1408 55.9050 0.3059 6.6539 57.1330 0.3278 5.1983 58.2230 0.3496 5.6320 59.1840 a/c = 1.0000 Crack Depth Kdeepest Ksurface 4.370E-03 7.7256 9.0943 0.0437 18.6870 27.0270 0.0656 19.8350 31.9390 0.0874 19.8200 35.5540 0.1093 19.6060 38.9730 0.1311 18.9030 41.8940 0.1530 17.8380 44.4360 0.1748 16.5010 46.6790 0.1967 14.5380 48.6850 0.2185 12.4010 50.4790 0.2404 10.1430 52.0920 0. 2622 7.8145 53.5480 0.2841 5.4789 55.0170 0.3059 4.1760 56.3550 0.3278 4.5406 57.5750 0.3496 4.9028 58.6880 Load Case 4:CD II Min 2-d SIF Input by User File No.: 1501350.301 Page C-5 8 of C-173 Revision:

0 F0306-01 R2 SJ Structural Integrity Associates, Inc."' The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\CDII.MNN No. of aspect ratios (a/c) in the tables = 8 ale = 0.1250 Crack Depth Kdeepest Ksurface 4.370E-03 0.0222 4.244E-03 0.0437 0.3938 0.0303 0.0656 0.6885 0.0512 0.0874 1.0215 0. 0772 0.1093 1.4110 0.1033 0.1311 1.8373 0.1331 0.1530 2.2957 0.1666 0.1748 2.7826 0.2038 0.1967 3.32 7 0 0.2419 0.2185 3.9025 0.2836 0.2404 4.5067 0.3288 0.2622 5.1370 0.3775 0.2841 6.0192 0.4389 0.3059 6.9599 0.5059 0.3278 7.9539 0.5786 0.3496 8.9950 0. 6571 ale = 0.1667 Crack Depth Kdeepest Ksurface 4.370E-03 0.0218 5.058E-03 0.0437 0.3879 0.0395 0.0656 0. 6767 0.0670 0.0874 1. 0020 0.100 7 0.1093 1.3839 0.1358 0.1311 1.8017 0.1754 0.1530 2.2510 0.2194 0.1748 2.7280 0.2678 0.1967 3.2515 0.3248 0.2185 3.8026 0.3878 0.2404 4.3785 0.4569 0. 2 622 4.9766 0.5320 0.2841 5. 7719 0.6266 0.3059 6.6134 0.7301 0.3278 7.4964 0.8425 0.3496 8.4152 0.9638 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 0.0216 5.686E-03 0.0437 0.3826 0.0467 0.0656 0.6665 0.079 2 0.0874 0.9852 0.1188 0.1093 1.3605 0.1609 0.1 311 1.7711 0.2080 0.1530 2.2126 0.2602 0.1748 2. 6811 0. 3172 0.1967 3.1876 0.3887 0.2185 3. 7187 0.4682 0.2404 4. 2715 0.5557 0. 2 622 4.8436 0.6512 0.2841 5.5699 0. 7714 0.3059 6.3327 0.9030 0.3278 7.1277 1.0460 0.3496 7.9495 1.2002 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03

0. 0211 6.584E-03 File No.: 1501350.301 Page C-59 of C-173 Revision: 0 F030 6-0 IR2 e Structural Integrity Associates, Inc." 0.0437 0.3741 0.0569 0.0656 0.6501 0.0967 0.0874 0.9587 0.1449 0.1093 1. 3236 0.1969 0.1311 1. 7228 0.2550 0.1530 2.1519 0.3188 0.1748 2.6070 0.3882 0.1967 3.0876 0.4806 0.2185 3.5884 0.5838 0.2404 4.1066 0.6978 0.2622 4.6393 0.8224 0.2841 5.2637 0.9794 0.3059 5.9103 1.1513 0.3278 6.5755 1.3382 0.3496 7.2543 1.5397 a/c = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 0.0203 7.392E-03 0.0437 0.3619 0.0671 0.0656 0. 62 91 0.1144 0.0874 0.9277 0.1712 0.1093 1.2775 0.2334 0.1311 1.6587 0.3027 0.1530 2.0668 0.3789 0.1748 2.4979 0.4616 0.1967 2.9488 0.5687 0.2185 3.4159 0.6873 0.2404 3.8966 0.8174 0. 2622 4.3880 0.9589 0.2841 4.9533 1.1248 0.3059 5.5343 1.3044 0.3278 6.1268 1. 497 4 0.3496 6.7245 1.7038 a/c = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 0.0187 8.739E-03 0.0437 0.3357 0.0844 0.0656 0.5836 0.1445 0.0874 0.8607 0.2159 0.1093 1.17 93 0.2954 0.1311 1. 5235 0.3839 0.1530 1.8890 0.4810 0.1748 2. 2719 0.5865 0.1967 2.6638 0. 7182 0.2185 3.0649 0.8627 0.2404 3. 4725 1.0198 0.2622 3.8834 1.1894 0.2841 4.3352 1. 368 9 0.3059 4.7894 1.5596 0.3278 5.2374 1. 7611 0.3496 4.8097 1.9731 ale = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 0.0165 9 .139E-03 0.0437 0.3007 0.0903 0.0656 0.5224 0.1549 0.0874 0.7693 0.2319 0.1093 1.0520 0.3153 0.1311 1. 3562 0. 4071 0.1530 1. 67 81 0.5069 0.1748 2.0141 0.6142 0.1967 2.3581 0.7399 FileNo.: 1501350.301 Page C-60 of C-173 Revision:

0 F0306-01 R 2 e Structural Integrity Associates, Inc. 0.2185 2.7091 0.2404 3.0639 0.2622 3.4195 0.2841 3.8004 0.3059 3.5065 0.3278 2.3892 0.3496 0.7737 ale = 1.0000 Crack Depth Kdeepest 4.370E-03 0.0147 0.0437 0.2706 0.0656 0.4698 0.0874 0.6909 0.1093 0.9429 0.1311 1.2131 0.1530 1. 4979 0.1748 1.7942 0.1967 2.0976 0.2185 2.4060 0.2404 2. 7160 0. 2 622 2.7269 0.2841 1.9188 0.3059 0.7885 0.3278 -0.6909 0. 3496 -2.5753 Load Case 5:Unload Max 2-d SIF Input by User 0.8753 1. 0200 1.1738 1. 3397 1.5147 1.6986 1. 8911 Ksurface 9.353E-03 0.0939 0.1614 0.2419 0.3274 0.4208 0.5216 0.6291 0.7489 0.8758 1.0094 1.1493 1. 3030 1. 4641 1. 6324 1. 8077 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\UNLD.MXN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-03 4.5828 0.0437 12.0180 0.0656 13.4190 0.0874 14.1820 0.1093 15.0110 0.1311 15.5920 0.1530 15.9850 0.1748 16.2300 0.1967 16.5440 0.2185 16.7510 0.2404 16.8690 0.2622 16.9120 0.2841 16.9790 0.3059 16.8920 0.3278 16.6650 0. 3496 16.3180 a/c = 0.1667 Crack Depth Kdeepest 4.370E-03 4.4990 0.0437 11.7 460 0.0656 13.0850 0.08 7 4 13.7990 0.1093 14.5130 0.1311 14.9710 0.1530 15.2340 0.1748 15.34 30 0.1967 15.5180 0.2185 15.5910 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 1.7085 5.1801 6.1774 6.9317 7. 7071 8.3929 9.0089 9.5682 10.1480 10.6920 11.2040 11. 6900 12.3930 13.0810 13.7550 14.4150 Ksurface 1.9733 5.9679 7.1119 7.9780 8.8877 9.7001 10.4380 11.1150 11.7930 1 2.42 70 Page C-61 of C-173 F0306-0l R2 S} Structural Integrity Associates, Inc. 0.2404 15.5790 13.0200 0.2622 15.4980 13.5780 0.2841 15.4620 14.3340 0.3059 15.3030 15.0640 0.3278 15.0360 15.7710 0.3496 14.6760 16.4540 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 4.4266 2.1766 0.0437 11.5160 6.5730 0.0656 12.8050 7.8297 0.0874 13.4790 8.7818 0.1093 14.1030 9.7950 0.1311 14.4650 10.7050 0.1530 14.6260 11.5360 0.1748 14.6290 12.3040 0.1967 14.6960 13.0590 0.2185 14.6650 13.7620 0.2404 14.5530 14.4190 0. 2622 14.3750 15.0330 0.2841 14.2590 15.8290 0.3059 14.0440 16.5920 0.3278 13.7440 17.3230 0.3496 13.3740 18.0240 a/c = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03

4. 3118 2.4670 0.0437 11.1560 7. 4371 0.0656 12.3690 8.8550 0.0874 12.9850 9.9301 0.1093 13.4760 11.0910 0.1311 13.6980 12.1410 0.1530 13.7130 13.1060 0.1748 13.5620 14.0050 0.1967 13.4730 14.8700 0.2185 13.2910 15.6740 0.2404 13.0340 16.4210 0.2622 12.7180 17.1170 0.2841 12.4840 17.9700 0.3059 12.1880 18.7790 0.3278 11.8410 19.5460 0.3496 11.4580 20.2720 a/c = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 4.1257 2.7118 0.0437 10.6260 8.1738 0.0656 11.7490 9.7367 0.0874 12.2960 10.9270 0.1093 12.6930 12.1510 0.1311 12.8300 13.2420 0.1530 12.7680 14.2330 0.1748 12.5490 15.1440 0.1967 12.3570 16.0650 0.2185 12.0790 16.9200 0.2404 11.7320 17.7150 0. 2622 11.3330 18.4580 0.2841 10.9760 19.2170 0.3059 10.5680 19.9270 0.3278 10.1200 20.5920 0.3496 9.6 453 21.2130 a/c = 0.5000 File No.: 1501350.301 Page C-62 of C-1 73 Revision:

0 F030 6-01 R2 e Structural Integrity Associates, Inc.'" Crack Depth Kdeepest 4.370E-03 3.7421 0.0437 9.5479 0.0656 10.4970 0.0874 10.9160 0.1093 11.1390 0.1311 11.1240 0.1530 10.9280 0.1748 10.5930 0.1967 10.2210 0.2185 9.7759 0.2404 9.2758 0.2622 8.7372 0.2841 8.1707 0.3059 7.5742 0.3278 6. 9626 0.3496 6.5215 a/c = 0.7500 Crack Depth *Kdeepest 4.370E-03 3.2207 0.0437 8.1012 0.0656 8.8345 0.0874 9.1085 0.1093 9.2680 0.1311 9.2303 0.1530 9.0456 0.1748 8.7486 0.1967 8.3106 0.2185 7.8064 0.2404 7.2539 0.2622 6.6687 0.2841 6.0729 0.3059 5.4651 0.3278 5.1798 0.3496 5.4923 a/c = 1.0000 Crack Depth Kdeepest 4.370E-03 2.7854 0.0437 6.9029 0.0656 7.4631 0.0874 7.6230 0.1093 7.7325 0.1311 7.6786 0.1530 7.5046 0.1748 7.2401 0.1967 6.7572 0.2185 6.2153 0.2404 5.6318 0. 2 622 5.0232 0.2841 4.4249 0.3059 4.1478 0.3278 4.3980 0.3496 4.6465 Load Case 6:Unload Min 2-d SIF Input by User Ksurface 3.1136 9.3831 11.1850 12.5680 13.8860 15.0390 16.0650 16.9890 17.9970 18.9330 19.8060 20.6210 21.2030 21.7290 22.2030 22.6290 Ksurface 3.2232 9.6574 11.4740 12.8480 14.1570 15.2940 16.3020 17.2070 18.1070 18.9360 19.7030 20.4150 21.0320 21.6020 22.1270 22.6130 Ksurface 3.2746 9.7700 11.5790 12.9330 14.2200 15.3350 16.3190 17.2010 18.0090 18.7460 19.4240 20.0500 20.6890 21.2860 21.8470 22.3740 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\UNLD.MNN No. of aspect ratios (a/c) in the tables = 8 a/c = 0.1250 Crack Depth Kdeepest Ksurface File No.: 1501350.301 Revision:

0 Page C-63 of C-1 73 F0306-01 R2 e Structural Integrity Associates, Inc. 4.370E-03 0.5123 0.1855 0.0437 1. 7438 0.5852 0.0656 2.2156 0. 7166 0.0874 2. 64 71 0.8279 0.1093 3.1360 0.9394 0.1311 3.6276 1.0445 0.1530 4.1249 1.1452 0.1748 4.6293 1.2429 0.1967 5.1954 1. 3412 0.2185 5.7770 1.4383 0.2404 6.3738 1.5347 0. 2 622 6.9854 1. 6307 0.2841 7.8412 1.7631 0.3059 8.7341 1.8987 0.3278 9.6619 2.0377 0.3496 10.6220 2.1801 ale = 0.1667 Crack Depth Kdeepest Ksurface 4.370E-03 0.5030 0.2145 0.0437 1.7076 0.6806 0.0656 2.1662 0.8359 0.0874 2.5840 0.9685 0.1093 3.0515 1.1054 0.1311 3.5200 1. 2360 0.1530 3.9923 1. 3625 0.1748 4.4699 1.4863 0.1967 4.9989 1. 617 3 0.2185 5.5403 1.7486 0.2404 6.0940 1.8806 0. 2 622 6.6595 2.0138 0.2841 7.4193 2.1876 0.3059 8.2086 2.3665 0.3278 9.0255 2.5505 0.3496 9.8678 2.7397 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 0.4950 0.2367 0.0437 1.6767 0.7538 0.0656 2.1243 0.9276 0.0874 2.5308 1.0767 0.1093 2.9810 1.2332 0.1311 3.4306 1.3834 0.1530 3.8827 1. 52 98 0.1748 4.3388 1.6737 0.1967 4.8379 1.8299 0.2185 5.3472 1.9876 0.2404 5.8663 2.1472 0. 2 622 6.3950 2.3091 0.2841 7.0789 2.5149 0.3059 7.7862 2. 7272 0.3278 8.5153 2.9460 0.3496 9.2642 3.1713 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 0.4823 0.2685 0.0437 1.6282 0.8585 0.0656 2.0589 1.0586 0.0874 2.4479 1. 2313 0.1093 2.8719 1.4159 0.1311 3.2932 1.5943 0.1530 3.7149 1. 7 692 File No.: 1501350.301 Page C-64 of C-173 Revision:

0 F0306-0I R2 e Structural Integrity Associates, Inc." 0.1748 4.1386 1.9420 0.1967 4.5935 2.1346 0.2185 5.0549 2.3303 0.2404 5.5227 2.5295 0. 2622 5.9966 2.7327 0.2841 6.5688 2.9845 0.3059 7.1554 3.2447 0.3278 7.7552 3. 5135 0.3496 8.3668 3.7906 a/c = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 0.4617 0.2954 0.0437 1. 5571 0.9495 0.0656 1.9679 1.1742 0.0874 2.3385 1. 3694 0.1093 2.7360 1.5724 0.1311 3.1291 1.7680 0.1530 3.5207 1.9593 0.1748 3.9127 2.1479 0.1967 4.3261 2. 3626 0.2185 4.7433 2.5807 0.2404 5.1642 2.8028 0.2622 5.5886 3.0291 0.2841 6.0894 3.2807 0.3059 6.6002 3.5389 0.3278 7 .1197 3.8038 0.3496 7.6461 4.0755 a/c = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 0.4191 0.3395 0.0437 1.4107 1.0996 0.0656 1. 7810 1.3651 0.0874 2 .1142 1.5982 0.1093 2.4594 1. 8312 0.1311 2.7972 2.0550 0.1530 3.1305 2.2730 0.1748 3.4609 2.4873 0.1967 3.7952 2.7387 0.2185 4.1283 2.9940 0.2404 4.4603 3.2539 0.2622 4.7909 3.5186 0.2841 5.1581 3.7664 0.3059 5.5267 4.0177 0.3278 5.8943 4.2725 0.3496 5.9705 4.5310 ale = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03

0. 3613 0.3516 0.0437 1.2145 1.1361 0.0656 1.5318 1.4088 0.0874 1. 8163 1. 6473 0.1093 2.1170 1.8835 0.1311 2. 4117 2.1091 0.1530 2.7028 2.3278 0.1748 2.9916 2.5417 0.1967 3. 2710 2.7749 0.2185 3.5478 3.0089 0.2404 3.8222 3.2443 0. 2 622 4.0939 3.4817 0.2841 4.3907 3. 7193 0.3059 4.4556 3.9595 0.3278 4.2761 4.2022 File No.: 1501350.301 Page C-65 of C-173 Revision:

0 F0306-0l R2 SJ Structural Integrity Associates, Inc. 0.3496 3.9452 ale = 1.0000 Crack Depth Kdeepest 4.370E-03 0.3130 0.0437 1.0506 0.0656 1. 3238 0.0874 1.5679 0.1093 1. 8311 0.1311 2.0894 0.1530 2.3450 0.1748 2.5987 0.1967 2.8328 0.2185 3.0634 0.2404 3.2904 0.2622 3.4015 0.2841 3.2795 0.3059 3.0569 0.3278 2. 7272 0.3496 2.2743 Load Case 7:IAS Max 2-d SIF Input by User 4.4478 Ksurface 0.3573 1.152 6 1.4280 1. 668 4 1.9045 2.1292 2.3461 2.5575 2.7743 2.9894 3.2036 3.4174 3.6447 3.8737 4.1047 4.3377 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\INAUX.MXN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-03 15.2760 0.0437 39.8790 0.0656 44.0560 0.0874 45.8970 0.1093 47.7650 0.1311 48.6540 0.1530 48.7860 0.1748 48.3150 0.1967 47.9010 0.2185 47.0250 0.2404 45.7510 0.2622 44.1360 0.2841 41.8980 0.3059 38.9510 0.3278 35.3580 0.3496 31.1950 a/c = 0.1667 Crack Depth Kdeepest 4.370E-03 14.9970 0.0437 38.9710 0. 0656 42.9480 0.0874 44.6370 0.1093 46.1330 0.1311 46.6220 0.1530 46.3300 0.1748 45.4150 0.1967 44.5790 0.2185 43.3060 0.2404 41.6610 0.2622 39.7050 0.2841 37.3500 0.3059 34.4270 0.3278 30.9990 0.3496 27.1320 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 5.6875 17.2900 20.6390 23.1720 25.7840 28.0900 30.1530 32.0170 33.9550 35.7660 37.4630 39.0570 41.3660 43. 6110 45.7950 47.9150 Ksurface 6.5691 19.9180 23.7560 26.6550 29.7040 32.4170 34.8670 37.1030 39.3340 41.3980 43.3100 45.0830 47.4830 49.7740 51.9600 54.0420 Page C-66 of C-173 F0306-0I R2 e Structural Integrity Associates, Inc. ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 14.7560 7.2461 0.0437 38.2030 21.9370 0.0656 42.0180 26.1480 0.0874 43.5860 29.3300 0.1093 44.7890 32.7150 0.1311 44.9670 35.7410 0.1530 44.3470 38.4900 0.1748 43.0880 41.0120 0.1967 41.9260 43.4690 0.2185 40.3460 45.7290 0.2404 38.4160 47.8070 0.2622 36.1990 49.7180 0.2841 33.7540 52.1880 0.3059 30.8550 54.5140 0.3278 27.5590 56.7000 0.3496 23.9280 58.7500 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 14.3730 8. 2130 0.0437 37.0030 24.8190 0.0656 40.5750 29.5660 0.0874 41.9640 33.1510 0.1093 42.7400 37.0150 0.1311 42.4660 40.4910 0.1530 41.3730 43.6660 0.1748 39.6210 46.6010 0.1967 37.9900 49.3820 0.2185 35.9690 51.9210 0.2404 33.6330 54.2380 0. 2 622 3 1.0430 56.3490 0.2841 28.4 7 30 58.9170 0.3059 25.6130 61.2900 0.3278 22.5150 63.4740 0.3496 19.2330 65.4740 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 13.7530 9.0284 0.0437 35.2350 27.2800 0.0656 38.5150 32.5080 0.0874 39.6910 36.4720 0.1093 40.1760 40.5320 0.1311 39.6530 44.1290 0.1530 38.3510 47.3680 0.1748 36.4280 50.3180 0.1967 34.5200 53.2470 0.2185 32.2570 55.9190 0.2404 29.7110 58.3560 0. 2622 26.9470 60.5750 0.2841 24.1130 62.7870 0.3059 21.0440 64.7910 0.3278 17.7900 66.5960 0.3496 14.4030 68.2120 ale = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 12.4750 10.3660 0.0437 31.6430 31.3180 0.0656 34.3630 37.3400 0.0874 35.1450 41.9310 F il e No.: 1501350.301 Page C-67 of C-1 7 3 Revision: 0 F0306-01R2 e Structural Integrity Associates, Inc. 0.1093 35.1080 0.1311 34.1530 0.1530 32.4990 0.1748 30.3000 0.1967 27.9290 0.2185 25.2670 0.2404 22.3890 0. 2 622 19.3590 0.2841 16.1060 0.3059 12.7240 0.3278 9.2694 0.3496 6.5215 a/c = 0.7500 Crack Depth Kdeepest 4.370E-03 10.7370 0.0437 26.8200 0.0656 28.8510 0.0874 29.1970 0.1093 29.0250 0.1311 28.0920 0.1530 26.5870 0.1748 24.6430 0.1967 22.1720 0.2185 19.4430 0.2404 16.5270 0. 2622 13.4840 0.2841 10.3160 0.3059 7.0906 0.3278 5.2080 0.3496 5.7058 ale = 1.0000 Crack Depth Kdeepest 4.370E-03 9.2864 0.0437 22.8270 0.0656 24.3070 0.0874 24.3160 0.1093 24.0430 0.1311 23.1390 0.1530 21.7670 0.1748 20.0390 0.1967 17.5230 0.2185 14.7790 0.2404 11.8760 0.2622 8.8788 0.2841 5.8584 0.3059 4.1909 0.3278 4.6159 0.3496 5.0381 Load Case 8:IAS Min 2-d SIF Input by User 46.2880 50.0600 53.3760 56.3200 59.4770 62.3540 64.9740 67.3600 68.9130 70.2350 71.3440 72.2570 Ksurface 10.7310 32.2340 38.3010 42.8570 47.1710 50.8820 54.1300 57.0050 59.8050 62.3310 64.6140 66.6820 68.3900 69.9020 71.2350 72.4030 Ksurface 10.9030 32.6100 38.6490 43.1320 47.3690 50.9970 54.1600 56.9520 59.4490 61.6800 63.6820 65.4850 67.2970 68.9440 70.4380 71.7940 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\INAUX.MNN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-03

-0.2444 0.0437 -0.3412 0.0656 -0.1435 0.0874 0 .1357 0.1093 0.4708 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface -0.0943 -0.2715 -0.3108 -0.3311 -0.3513 Page C-68 of C-173 F0306-01 R2

Integrity Associates, Inc."' 0.1311 0.8610 -0.3623 0.1530 1.2979 -0.3653 0.1748 1.7747 -0.3610 0.1967 2.3066 -0.3554 0.2185 2.8784 -0.3436 0.2404 3.4863 -0.3260 0.2622 4.1265 -0.3027 0.2841 5.0222 -0.2796 0.3059 5.9880 -0.2497 0.3278 7. 0173 -0.2128 0.3496 8.1021 -0.1688 ale = 0.1667 Crack Depth Kdeepest Ksurface 4.370E-03

-0.2399 -0.1088 0.0437 -0.3307 -0.3091 0.0656 -0.1347 -0.3513 0.0874 0.1399 -0.3715 0.1093 0.4748 -0.3916 0.1311 0.8647 -0.4015 0.1530 1.3010 -0.4023 0.1748 1. 7771 -0.3949 0.1967 2. 2972 -0.3780 0.2185 2.8530 -0.3520 0.2404 3.4408 -0.3171 0. 2 622 4.0564 -0.2734 0.2841 4.8701 -0.2217 0.3059 5.7392 -0.1592 0.3278 6.6578 -0.0856 0.3496 7.6179 -1.203E-03 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03* -0.2360 -0.1200 0.0437 -0.3221 -0.3380 0.0656 -0.1277 -0.3823 0.0874 0.1430 -0.4024 0.1093 0.4772 -0.4225 0.1311 0.8662 -0.4314 0.1530 1. 3015 -0.4305 0.1748 1. 77 61 -0.4208 0.1967 2.2862 -0.3953 0.2185 2.8287 -0.3583 0.2404 3.3998 -0.3100 0.2622 3.9950 -0.2506 0.2841 4.7436 -0.1770 0.3059 5.5359 -0.0894 0.3278 6.3666 0.0123 0.3496 7.2 2 77 0.1278 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03

-0.2298 -0.1359 0.0437 -0.3087 -0.3792 0.0656 -0.1173 -0.4266 0.0874 0.1471 -0.4463 0.1093 0.4795 -0.4664 0.1311 0.8664 -0.4739 0.1530 1.2991 -0.4706 0.1748 1.7707 -0.4575 0.1967 2.2649 -0:_4196 0.2185 2.7870 -0.3669 0.2404 3.3323 -0.2994 0. 2622 3.8966 -0.2175 0.2841 4.5486 -0.1123 File No.: 1501350.301 Page C-69 of C-173 Revision:

0 F0306-0IR2 e Structural Integrity Associates, Inc."' 0.3059 5.2276 0. 0115 0.3278 5.9282 0.1536 0.3496 6.6431 0. 3138 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03

-0.2197 -0.1492 0.0437 -0.2888 -0.4129 0.0656 -0.1003 -0.4622 0.0874 0.1588 -0.4808 0.1093 0.4824 -0.4953 0.1311 0.8569 -0.4948 0.1530 1.2735 -0.4813 0.1748 1. 7254 -0.4562 0.1967 2.1962 -0.4078 0.2185 2.6904 -0.3435 0.2404 3.2034 -0.2636 0. 2 622 3.7307 -0.1684 0.2841 4.3305 -0.0493 0.3059 4.9496 0. 0872 0.3278 5.5815 0.2410 0.3496 6.2177 0. 4116 a/c = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03

-0.1991 -0.1712 0.0437 -0.2498 -0.4678 0.0656 -0.0687 -0.5197 0.0874 0.1775 -0.5363 0.1093 0.4813 -0.5406 0.1311 0.8288 -0.5258 0.1530 1. 2114 -0.4945 0.1748 1.6224 -0.4485 0.1967 2.0454 -0.3820 0.2185 2.4835 -0.2980 0.2404 2.9318 -0.1970 0.2622 3.3861 -0.0795 0.2841 3.8838 0. 0626 0.3059 4.3843 0.2202 0.3278 4.8756 0.3926 0.3496 4.4750 0.5791 a/c = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03

-0.1710 -0.1771 0.0437 -0.1969 -0.4787 0.0656 -0.0275 -0.5273 0.0874 0.1987 -0.5384 0.1093 0.4713 -0.5383 0.1311 0.7805 -0.5194 0.1530 1.1187 -0.4844 0.1748 1.4800 -0.4353 0.1967 1.8591 -0.3682 0.2185 2.2502 -0.2867 0.2404 2.6485 -0.1916 0.2622 3.0497 -0.0835 0.2841 3.4761 0.0432 0.3059 3.2815 0.1827 0.3278 1.8430 0.3344 0.3496 -0.3031 0.4977 a/c = 1.0000 Crack Depth Kdeepest Ksurface 4.370E-03

-0.1476 -0.1799 FileNo.: 1501350.301 Page C-70 of C-173 Revision:

0 F0306-0IR2 e Structural Integrity Associates, Inc. 0.0437 -0.1541 0.0656 4.512E-03 0.0874 0.2129 0.1093 0.4585 0.1311 0.7349 0.1530 1.0354 0.1748 1.3545 0.1967 1.6957 0.2185 2.04 60 0.2404 2.4010 0.2622 2.5997 0.2841 1.5904 0.3059 0.1449 0.3278 -1.79 67 0.3496 -4.3 229 Load Case 9:Residual Type: Stress Coefficient Coefficient Coefficient Coefficient Coefficients Input co C1 C2 C3 30.0000 0.0000 0.0000 0.0000 Load Case 10:0BE -0.4821 -0.5278 -0.5345 -0.5311 -0.5091 -0.4717 -0.4209 -0.3540 -0.2754 -0.1858 -0.086 3 0. 0271 0.1511 0.2852 0.4289 by User Type: Stress Coefficients Input by User Coefficient CO Coefficient C1 Coefficient C2 Coefficient C3 Load Case 11:DW 3.3100 0.0000 0.0000 0.0000 Type: Stress Coefficients Input by User Coefficient CO Coefficient C1 Coefficient C2 Coefficient C3 Load Case 12:SLID Max 2-d SIF Input by User 0. 7290 0.0000 0.0000 0.0000 The SIF originally read from C:\Users\clohse\Docurnents\ANSYS\PGE\1501350\TIFFANY\SLID.MXN No. of aspect ratios (a/c) ale= 0.1250 Crack Depth Kdeepest 4.370E-03

4. 6 7 60 0.0437 12.2520 0.0656 13.6730 0.0874 14.4430 0.1093 15.2790 0.1311 15.8610 0.1530 16.2510 0.1748 16.4900 0.1967 16.7970 0.2185 16.9950 0.2404 17.1020 0.2622 17.1310 0.2841 17.1790 0.3059 17.0690 0.3278 16.8160 0.3496 16.4 370 ale = 0.1667 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 1. 7434 5.2852 6.30 22 7.0711 7.8616 8.560 6 9.1883 9.7581 10.3480 10.9030 11.4250 11. 9190 1 2.6350 1 3.3360 14.02 20 14.6940 Page C-71 of C-173 F0306-0 I R2 e Structural Integrity Associates, Inc. Crack Depth Kdeepest Ksurface 4.370E-03 4.5904 2. 0135 0.0437 11.9740 6.0889 0.0656 13.3330 7.2553 0.0874 14.0530 8.1380 0.1093 14;7720 9.0653 0.1311 15.2290 9.8931 0.1530 15.4870 10.6440 0.1748 15.5870 11.3340 0.1967 15.7530 12.0250 0.2185 15.8150 12.6700 0.2404 15.7900 13.2740 0.2622 15.6930 13.8410 0.2841 15.6380 14.6100 0.3059 15.4570 15.3530 0.3278 15.1640 16.0710 0.3496 14.7760 16.7660 a/c = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 4.5166 2.2210 0.0437 11.7390 6.7060 0.0656 13.0470 7.9874 0.0874 13.7270 8.9577 0.1093 14.3540 9.9902 0.1311 14.7130 10.9170 0.1530 14.8670 11.7640 0.1748 14.8590 12.5460 0.1967 14.9160 13.3150 0.2185 14.8720 14.0300 0.2404 14.7450 14.6980 0.2622 14.5510 15.3220 0.2841 14.4160 16.1310 0.3059 14.1790 16.9070 0.3278 13.8550 17.6500 0.3496 13.4590 18.3620 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 4.3994 2.5173 0.0437 11.3720 7.5875 0.0656 12.6030 9.0331 0.0874 13.2230 10.1290 0.1093 13.7150 11.3120 0.1311 13. 9320 12.3810 0.1530 13.9370 13.3650 0.1748 13.7730 14.2790 0.1967 13.6710 15.1600 0.2185 13.-4740 15.9770 0.2404 13.2000 16.7360 0.2622 12.8650 17.4430 0.2841 12.6130 18.3100 0.3059 12.2960 19.1320 0.3278 11.9270 19.9100 0.3496 11.5210 20.6450 a/c = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 4.2095 2. 7 672 0.0437 10.8320 8.3390 0.0656 11.9710 9.9322 0.0874 12.5210 11.1450 0.1093 12.9170 12.3920 0.1311 13.0480 13.5030 File No.: 1501350.301 Page C-72 of C-1 73 Revision:

0 F0306-01R2 e Structural Integrity Associates, Inc."' 0.1530 12.9750 14.5120 0.1748 12.7420 15.4400 0.1967 12.5360 16.3760 0.2185 12.2410 17.2450 0.2404 11.8760 18.0540 0.2622 11.4580 18.8080 0.2841 11.0820 19.5780 0.3059 10.6520 20.2990 0.3278 10.1820 20.9720 0.3496 9.6836 21.6010 a/c = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 3.8181 3.1771 0.0437 9.7328 9.5724 0.0656 10.6940 11.4090 0.0874 11.1150 12.8180 0.1093 11.3350 14.1610 0.1311 11.3110 15.3350 0.1530 11.1030 16.3790 0.1748 10.7520 17.3190 0.196 7 10.3640 18.3430 0.2185 9.9006 19.2950 0.2404 9.3812 20.1810 0. 2 622 8.8225 21.0090 0.2841 8.2344 21.5980 0.3059 7.6156 22.1290 0.3278 6.9812 22.6080 0.3496 6.5215 23.0390 a/c = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 3.2861 3.2889 0.0437 8.2576 9.8521 0.0656 8.9998 11.7040 0.0874 9.2731 13.1030 0.1093 9.4290 14.4360 0.1311 9.3833 15.5940 0.1530 9.1875 16. 6200 0.1748 8.8769 17.5410 0.1967 8.4222 18.4560 0.2185 7.9000 19.2980 0.2404 7.3284 20.0760 0.2622 6. 7235 20.7990 0.2841 6.1071 21.4250 0.3059 5.4784 22.0010 0.3278 5.1800 22.5320 0.3496 5.4938 23.0230 ale = 1.0000 Crack Depth Kdeepest Ksurface 4.370E-03 2.8420 3.3414 0.0437 7.0357 9.9669 0.0656 7.6020 11.8110 0.0874 7.7 596 13.1900 0.1093 7.8652 14.5010 0.1311 7.8040 15.6350 0.1530 7.6199 16.6360 0.1748 7.3434 17.5330 0.1967 6.8439 18.3550 0.2185 6.2842 19.1040 0.2404 5.6820 19.7920 0.2622 5.0543 20.4260 0.2841 4.4367 21.0750 0.3059 4.1481 21. 6810 File No.: 1501350.301 Page C-73 of C-173 Revision:

0 F0306-0 I R2 e Structural Integrity Associates, Inc. 0.3278 0.3496 4.3995 4.6493 Load Case 13:SLID Min 2-d SIF Input by User 22.2480 22.7820 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\SLID.MNN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-03 0.5070 0.0437 1.7294 0.0656 2.1993 0.0874 2. 6297 0.1093 3.1175 0.1311 3.6085 0.1530 4.1054 0.1748 4.6096 0.1967 5.1754 0.2185 5.7569 0.2404 6.3539 0. 2 622 6.9657 0.2841 7.8217 0.3059 8. 7150 0.3278 9.6436 0.3496 10.6050 ale= 0.1667 Crack Depth Kdeepest 4.370E-03 0.4979 0.0437 1.6935 0.0656 2.1503 0.0874 2.5671 0.1093 3.0337 0.1311 3.5016 0.1530 3.9737 0.1748 4. 4513 0.1967 4.9802 0.2185 5. 5217 0.2404 6.0756 0. 2 622 6.6415 0.2841 7.4017 0.3059 8.1915 0.3278 9.0091 0.3496 9.8522 a/c = 0.2000 Crack Depth Kdeepest 4.370E-03 0.4900 0.0437 1. 6629 0.0656 2.1088 0.0874 2.5142 0.1093 2.9637 0.1311 3.4129 0.1530 3.8648 0.1748 4.3210 0.1967 4.8203 0.2185 5. 32 98 0.2404 5.8493 0.2622 6.3784 0.2841 7.0628 0.3059 7.7706 0.3278 8.5004 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 0.1836 0.5793 0.7095 0.8199 0.9304 1.0347 1.1348 1.2318 1.3295 1. 4260 1. 5218 1. 6173 1. 7489 1.8839 2.0222 2.1639 Ksurface 0.2122 0.6737 0.8277 0.9593 1. 0951 1.2247 1. 3503 1.4733 1. 6035 1.7340 1. 8 654 1.9980 2.1709 2.3490 2.5323 2. 7208 Ksurface 0.2343 0.7463 0.9185 1. 0664 1. 2217 1.3709 1.5162 1. 6592 1.8145 1. 9714 2 .1302 2.2914 2.4963 2.7077 2.9257 Page C-74 of C-173 F0306-0IR2 e Structural/nlegrily Associates, Inc. 0.3496 9.2501 3.1502 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 0.4774 0.2657 0.0437 1. 6148 0.8499 0.0656 2.0438 1.0483 0.0874 2.4320 1.2197 0.1093 2.8554 1.4029 0.1311 3.2764 1.5800 0.1530 3.6982 1. 7537 0.1748 4.1223 1. 9254 0.1967 4.5774 2.1169 0.2185 5.0392 2. 3116 0.2404 5.5075 2.5100 0. 2622 5.9821 2. 712 3 0.2841 6.5548 2.9630 0.3059 7 .1420 3.2224 0.3278 7.7426 3.4902 0.3496 8.3548 3.7665 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 0.4570 0.2923 0.0437 1.5443 0.9401 0.0656 1.9536 1.1629 0.0874 2.3234 1.3566 0.1093 2.7204 1.5581 0.1311 3.1133 1. 7524 0.1530 3.5052 1.9424 0.1748 3.8976 2.1299 0.1967 4.3114 2.3434 0.2185 4.7291 2.5605 0.2404 5.1506 2.7816 0. 2 622 5.5757 3.0070 0.2841 6. 0772 3.2576 0.3059 6.5888 3.5150 0.3278 7.1091 3.7792 0.3496 7. 6362 4.0501 ale = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 0.4148 0.3359 0.0437 1. 3992 1.0887 0.0656 1.7682 1.3521 0.0874 2.1008 1.5834 0.1093 2.4458 1.8148 0.1311 2.7836 2. 0371 0.1530 3 .1172 2.2538 0.1748 3.4482 2.4670 0.1967 3.7831 2. 7171 0.2185 4 .1170 2. 9712 0.2404 4.4497 3.2300 0. 2 622 4.7811 3.4937 0.2841 5.1492 3.7408 0.3059 5.5187 3.9914 0.3278 5. 8872 4.2457 0.3496 5. 9572 4.5037 ale = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 0.3576 0.3479. 0.0437 1.2047 1.1249 0.0656 1.5210 1.3954 File No.: 1501350.301 Page C-75 of C-173 Revision:

0 F030 6-0lR2 e Structural Integrity Associates, Inc. 0.0874 1.8051 1. 6322 0.1093 2.1056 1.8667 0.1311 2.4004 2.0909 0.1530 2.6918 2.3083 0.1748 2.9811 2. 5211 0.1967 3.2612 2.7531 0.2185 3.5389 2.9861 0.2404 3.8141 3.2206 0.2622 4.0867 3.4570 0.2841 4.3843 3.6939 0.3059 4.4445 3.9333 0.3278 4.2545 4.1755 0.3496 3.9093 4.4204 a/c = 1.0000 Crack Depth Kdeepest Ksurface 4.370E-03 0.3098 0.3535 0.0437 1.0423 1.1413 0.0656 1.3147 1.4144 0.0874 1. 5585 1. 6531 0.1093 1.8216 1.8877 0.1311 2.0801 2.1109 0.1530 2.3359 2.3266 0.1748 2.5901 2.5369 0.1967 2.8 2 49 2.7526 0.2185 3.0563 2.9668 0.2404 3.2842 3.1801 0.2622 3.3935 3.3932 0.2841 3.2636 3.6197 0.3059 3.0308 3.8480 0.3278 2.6884 4.0782 0.3496 2.2199 4.3106 Total Load Sub-Blocks:

6 Load Sub-Block

1. 1 Load Sub-block Name: Heatup/Cooldown Maximum Load Case Multiplier Load Case 1.0000 HU/CD Max 1.0000 Residual 1.0000 DW Minimum Load Case Multiplier Load Case 1.0000 HU/CD Min 1.0000 Residual 1.0000 DW Growth Law: ASMEAusteniticAir Cycles/Time:

140 Temperature:

650 Load Sub-Block

1. 2 Load Sub-block Name: Cooldown II Maximum ID ID Load Case Multiplier Load Case ID 1.0000 CD II Max 1.0000 Residual 1.0000 DW Minimum Load Case Multiplier Load Case ID 1.0000

• CD II Min 1.0000 Residual 1.0000 DW Growth Law: ASMEAusteniticAir File No.: 1501350.301 Revision:

0 Page C-76 of C-173 F03 06-0 IR2 e Structural Integrity Associates, Inc. Cycles/Time:

8 Temperature:

650 Load

1. 3 Load Sub-block Name: Inadvertent Aux Spray Maximum Load Case Multiplier 1.0000 1.0000 1.0000 Minimum Load Case Multiplier 1.0000 1.0000 1.0000 Load Case ID IAS Max Residual DW Load Case ID IAS Min Residual DW Growth Law: ASMEAusteniticAir Cycles/Time:

2 Temperature:

650 Load Sub-Block

1. 4 Load Sub-block Name: Unload Maximum Load Case Multiplier 1.0000 1.0000 1.0000 Minimum Load Case Multiplier 1.0000 1.0000 1.0000 Load Case ID Unload Max Residual DW Load Case ID Unload Min Residual DW Growth Law: ASMEAusteniticAir Cycles/Time:

2744 Temperature:

650 Load Sub-Block

1. 5 Load Sub-block Name: OBE Maximum Load Case Multiplier 2.0000 1.0000 1.0000 Minimum Load Case Multiplier 0.0000 1.0000 1.0000 Load Case ID OBE Unload Max DW Load Case ID OBE Unload Max DW Growth Law: ASMEAusteniticAir Cycles/Time:

16 Temperature:

650 Load Sub-Block

1. 6 Load Sub-block Name: Step Load Inc/Dec Maximum Load Case Multiplier 1.0000 1.0000 1.0000 Minimum Load Case Multiplier 1.0000 1.0000 1.0000 Load Case ID SLID Max DW Residual Load Case ID SLID Min DW Residual Growth Law: ASMEAusteniticAir File No.: 1501350.301 Revision:

0 Page C-77 of C-173 F0306-0IR2 e Structural Integrity Associates, Inc."' Cycles/Time:

210 Temperature:

650 Material:

1 Sample Material 1: Only a sample *****************************************************************************

Austenitic Stai nless Steel in Air environment (U.S. Customary Units) The Fatigue Crack Growth Rate (in/cycle) is given by:

• da/dN = Co*(Delta K)An where Delta K = Kmax -Kmin n =the slope of the l og (da/dN) vers us log (Delta K) 3.3 Co = a scaling constant Co C*S C is given by: T is the metal temperature in deg F S is a scaling parameter to account for R ratio and is given by: s 1.0 1.0 + 1.8

• R -4 3.35 + 57.97

• R where R = Kmin I Kmax for R <= 0 for 0 < R <= 0.79 for 0.79 < R < 1 **************************************************************

No. of Data in the KIC Table = 3 Crack D epth 0.0000 0.1000 2.0000 messages/Warnings:

KIC 500.0000 500.0000 500.0000 Number o f Warnings in Inputs: 0 ----------ANALYS IS RESULTS ---------STR E SS INTENSITY FACTORS Load Case # 1: HU/CD ------------

Crack a c c/a = 0.0800 0.0900 3.9063 0.3125 0.3516 File No.: 1501350.301 Revision:

0 Max Dimensions a/t 0.1831 0.2059 ------------

K c/a a 3.9063 27.7 22 7 3.9063 28.0 975 at tips c 21.82 75 22.9458 Page C-78 of C-173 F0306-0 I R2 S) Structural Integrity Associates, Inc."' 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0. 7813 0.8203 0.8594 0.8984 0.9375 0.9766 1. 0156 1.0547 1.0938 1.1328 1.1719 1.2109 1.2500 4.1563 0.3325 0.3741 0.4156 0. 4572 0.4988 0.5403 0.5819 0. 6234 0.6650 0.7066 0.7481 0.7897 0.8313 0.8728 0.9144 0.9559 0.9975 1.0391 1.0806 1.1222 1.1638 1.2053 1.2469 1.2884 1.3300 4.4063 0.3525 0.3966 0.4406 0.4847 0.5288 0.5728 0.6169 0.6609 0.7050 0.7491 0.7931 0. 8372 0.8813 0.9253 File No.: 1501350.301 Revision:

0 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 28.3497 28.5794 28.5318 28.4842 28.2300 27.9503 27.5397 27.0745 26.6325 26.2120 25.7553 25.2265 24.6845 24.0677 23.4509 22.7663 22.0792 21.4100 20.7459 20.0343 19.2903 18.5195 17.7102 28.0264 28.4201 28.7031 28.9637 28.9474 28.9311 28.7086 28.4606 28.0820 27.6487 27.2395 26.8524 26.4283 25.9307 25.4196 24.8316 24.2436 23.5855 22.9249 2 2.2746 21.6271 20.9263 20.1892 19.4214 18.6095 28.3125 28.7264 29.0449 29.3411 29.3623 29.3834 29.2001 28.9915 28.6532 28.2607 27.8915 27.5437 27.1582 26.6978 24.1270 25.2990 26.3574 27.4157 28.3907 29.3554 30.2677 31.1581 32.0239 32.8671 33.6861 34.4571 35.2182 35.9235 36.6288 37.2760 37.9212 38.6700 39.4482 40.1935 40.9164 41.6171 42.2858 21.2039 22.2909 23.4404 24.5810 25. 6110 26.6410 27.5900 28.5289 29.4167 30.2832 31.1262 31.9476 32.7457 33.4976 34.2400 34.9286 35.6173 36.2502 36.8811 37.6280 38.4077 39.1563 39.8838 40.5902 41.2663 20.5240 21.5761 22.6855 23.7861 24.7786 25.7712 26.6844 27.5879 28.4410 29.2729 30.0854 30.8801 31.6526 32.3811 Page C-79 of C-173 F0306-0J R2 SJ Structural Integrity Associates, Inc. 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.9694 1.0134 1.0575 1.1016 1.1456 1.1897 1.2338 1.2778 1. 3219 1. 3659 1.4100 4.6563 0.3725 0.4191 0.4656 0.5122 0.5588 0.6053 0.6519 0.6984 0.7450 0.7916 0.8381 0.8847 0.9313 0.9778 1. 0244 1. 0709 1.1175 1.1641 1.2106 1. 2572 1.3038 1.3503 1. 3969 1.4434 1. 4900 4.9063 0.3925 0.4416 0.4906 0.5397 0.5888 0.6378 0.6869 0.7359 0.7850 0.8341 0.8831 0.9322 0.9813 1.0303 1.0794 1.1284 1.1775 1.2266 1. 2756 1.3247 1.3738 1. 4228 1.4719 1. 5209 1.5700 File No.: 1501350.301 Revision:

0 0.5034 0.5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 26.2234 25.6702 25.1169 24.4911 23.8627 23.2311 22.5985 21.9051 21.1702 20.3997 19.5778 28.5680 28.9998 29.3499 29.6779 29.7326 29.7872 29.6389 29.4654 29.1631 28.8069 28.4734 28.1608 27.8098 27.3825 26.9409 26.4187 25.8964 25.2995 24.6999 24.0849 23.4656 22.7788 22.0459 21.2729 20.4420 28.7973 29.2453 29.6239 29.9805 30.0652 30.1499 30.0329 29.8910 29.6210 29.2975 28.9961 28.7150 28.3949 27.9974 27.5853 27.0909 26.5965 26.0255 25.4517 24.8517 24.2444 23.5634 22.8323 22.0571 21.2182 33.1006 33.7692 34.4377 35.0535 35.6674 36.4037 37.1745 37.9166 38.6390 39.3420 40.0170 19.9171 20.9380 22.0116 23.0766 24.0357 24.9948 25.8762 26.7479 27.5699 28.3711 29.1564 29. 9272 30.6769 31.3845 32.0836 32.7342 33.3848 33.9853 34.5840 35.3108 36.0737 36.8099 37.5279 38.2279 38.9018 19.3721 20.3650 21.4064 22.4394 23.3684 24.2975 25.1502 25.9936 26.7877 27.5612 28.3221 29.0715 29.8006 30.4895 31.1703 31.8047 32.4392 33.0260 33. 6111 34.3293 35.0851 35.8161 36.5300 37.2273 37.9003 Page C-80 of C-173 F0306-0I R2 l) Structural Integrity Associates, Inc. Load Case # 2: HU/CD Min ------------

Crack Dimensions

---

a c a/t c/a c/a = 3.9063 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.3125 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0. 7813 0.8203 0.8594 0.8984 0.9375 0.9766 1. 0156 1. 054 7 1. 0938 1.1328 1.1719 1.2109 1. 2500 4.1563 0.3325 0.3741 0.4156 0.4572 0.4988 0.5403 0.5819 0.6234 0.6650 0.7066 0.7481 0.7897 0. 8313 0.8728 0.9144 0.9559 0.9975 1.0391 1.0806 1.1222 1.1638 1.2053 1.2469 1. 2884 1.3300 4.4063 0.3525 0.3966 0.4406 0.4847 0.5288 0.5728 File No.: 1501350.301 Revision:

0 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 K at tips a c 1. 2952 1.4530 1. 6275 1.8029 1.9879 2.1730 2.3665 2. 5611 2.7616 2.9647 3.1741 3.3894 3. 6071 3.8296 4.0530 4.2817 4.5105 4.7444 4.9785 5.2455 5.5218 5.8035 6.0887 6.3770 6.6698 1.3063 1.4657 1. 6421 1.8194 2.0066 2.1938 2.3896 2.5865 2.7895 2.9950 3.2077 3. 42 68 3.6484 3.8752 4.1030 4.3365 4.5700 4.8091 5.0485 5.3253 5.6127 5. 9062 6.2038 6.5050 6.8114 1. 3171 1.4781 1.6565 1.8356 2.0249 2.2141 0.4505 0. 4911 0.5338 0.5766 0.6203 0.6641 0.7091 0.7542 0.8004 0.8470 0.8989 0.9557 1.0139 1. 07 45 1.1358 1.2004 1.2651 1.3336 1.4022 1.4838 1.5690 1.6577 1.7489 1.8424 1.9394 0.4351 0.4740 0.5150 0.5560 0.5979 0.6399 0.6830 0. 7262 0.7704 0.8151 0.8647 0.9187 0.9740 1. 0317 1.0899 1.1513 1. 2127 1.2778 1.3430 1. 4210 1.5026 1.5876 1.6749 1.7646 1. 8575 0.4185 0.4557 0.4947 0.5338 0.5737 0.6137 Page C-81 of C-173 F0306-0J R2 SJ Structurallnlegrily Associates, Inc."' 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.6169 0.6609 0.7050 0.7491 0.7931 0. 8372 0. 8813 0.9253 0.9694 1.0134 1.0575 1.1016 1.1456 1.1897 1.2338 1.2778 1. 3219 1. 3659 1. 4100 4.6563 0. 3725 0.4191 0.4656 0.5122 0.5588 0.6053 0.6519 0.6984 0.7450 0.7916 0.8381 0.8847 0. 9313 0.9778 1. 0244 1.0709 1.1175 1.1 64 1 1.2106 1. 2572 1.3038 1.3503 1.3969 1.4434 1. 4900 4.9063 0.3925 0.4416 0.4906 0.5397 0.5888 0.6378 0.6869 0.7359 0.7850 0.8341 0.8831 0.9322 0.9813 1.0 303 1.07 94 1.1284 1.1775 1.2266 File No.: 1501350.301 Revision:

0 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 52 63 0.5492 0. 5721 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4. 6563 4.6563 4.6563 4.6563 4. 6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 2.4122 2. 6113 2.8166 3.0246 3.2404 3.4634 3.6892 3.9204 4.1527 4.3912 4.6297 4.8743 5.1192 5.4074 5.7079 6.0155 6.3277 6.6443 6.9668 1. 32 67 1. 48 92 1. 6693 1. 8501 2.0412 2. 23.2"3 2.4323 2.6334 2.8409 3.0510 3.2696 3. 4962 3. 7256 3.9608 4.1971 4.4401 4.6830 4.9325 5.1823 5.4807 5.7929 6.1130 6.4384 6.7686 7.1056 1. 3353 1.4992 1.6807 1.8632 2.0559 2.2486 2.4504 2.6533 2. 8626 3.0746 3.2959 3.5256 3.7583 3.9970 4.2370 4.4840 4.7309 4.9848 0.6547 0.6958 0.7379 0.7804 0. 8272 0.8781 0.9301 0.9842 1.0390 1.0966 1.1542 1.2151 1.2762 1. 3494 1.4261 1. 5060 1.5879 1.6721 1.7593 0.4037 0.4394 0.4767 0.5140 0.5521 0.5903 0.6294 0.6687 0.7088 0.7494 0.7938 0.8418 0.8908 0.9419 0.9935 1. 0477 1.1019 1.1592 1.2 166 1.2856 1.3578 1.4331 1.5103 1.5896 1.6717 0.3904 0.4247 0.4604 0.4962 0.5327 0.5693 0.6067 0.6443 0.6827 0.7216 0.7638 0.8093 0.8556 0.9039 0.9526 1.0038 1.0549 1.1089 Page C-82 of C-173 F0306-0 I R2 e Structural Integrity Associates, Inc. 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 1.2756 1. 324 7 1. 3738 1. 4228 1.4719 1.5209 1.5700 Load Case # 3: CD II Max 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 ------------

Crack Dimensions

---

a c a/t c/a c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 3.9063 0.3125 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0. 7813 0.8203 0.8594 0.8984 0.9375 0.9766 1.0156 1. 054 7 1.0938 1.1328 1.1719 1.2109 1.2500 4.1563 0.3325 0.3741 0.4156 0. 4572 0.4988 0.5403 0.5819 0.6234 0.6650 0.7066 0.7481 0.7897 0.8313 0.8728 0.9144 0.9559 0.9975 1.0391 1.0806 1.1222 1.1638 1.2053 1.2469 1.2884 1.3300 File No.: 1501350.301 Revision:

0 0.1831 0.2059 0.2288 0. 2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 52 63 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3. 9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 5.2390 5.5466 5.8693 6.2006 6.5377 6.8802 7.2302 1.1630 1.2282 1. 2 965 1. 3676 1.4406 1. 5154 1. 5930 K at tips a c 33.7249 34.1561 34.4303 34.6765 34.5774 34.4784 34.1212 33.7321 33.1795 32.5584 31.9639 31.3939 30.7782 30.0718 29.3488 28.5321 27.7153 26.8133 25.9082 25.0162 24.1277 23.1792 22.1897 21.1664 20.0945 34.0947 34.5489 34.8606 35.1443 35.0833 35.0222 34.7035 34.3529 33.8390 33.2568 32.7018 32.1721 31.5956 30.9266 30.2405 29.4581 28.6756 27.8050 26.9312 2 6.0598 25.1892 24.2510 23.2668 22.2440 21.1655 26.5878 27.9538 29.3950 30.8249 32 .1168 33.4086 34.5981 35.7749 36.8872 37.9726 39.0273 40.0537 41.0500 41.9868 42. 9113 43.7663 44.6213 45.4036 46.1832 47.0874 48.0266 48.9245 49.7943 50.6360 51.4374 25.8279 27.1557 28.5583 29.9500 31.2075 32.4650 33.6227 34.7682 35.8508 36.9071 37.9342 38.9344 39.9058 40.8197 41.7218 42.5571 43.3924 44.1578 44.9207 45.8233 46.7653 47.6682 48.5444 49.3940 50.2055 Page C-83 of C-173 F 0 30 6-01 R2 e Structural Integrity Associates, Inc. c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 4.4063 0.3525 0.3966 0.4406 0.4847 0.5288 0.5728 0.6169 0.6609 0.7050 0.7491 0.7931 0. 8372 0.8813 0.9253 0.9694 1. 0134 1.0575 1.1016 1.1456 1.1897 1. 2338 1.2778 1. 3219 1. 3659 1.4100 4.6563 0.3725 0.4191 0.4656 0.5122 0.5588 0.6053 0.6519 0.6984 0.7450 0.7916 0.8381 0.8847 0.9313 0.9778 1. 0244 1.0709 1.1175 1.1641 1.2106 1.2572 1. 3038 1.3503 1.3969 1.4434 1.4900 4.9063 0.3925 0.4416 0.4906 0.5397 0.5888 0.6378 0.6869 0.7359 0.7850 0.8341 File No.: 1501350.301 Revision:

0 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 52 63 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0. 2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 34.4430 34.9216 35.2766 35.6037 35.5883 35.5728 35.3017 34.9990 34.5343 34.0018 33.4954 33.0131 32.4831 31.8587 31.2168 30.4758 29.7349 28.9027 28.0673 27.2160 26.3604 25.4277 24.4427 23.4127 22.3177 34.7538 35.2543 35.6478 36.0137 36.0390 36.0643 35.8357 35.5757 35.1548 34.6667 34.2037 33.7638 33.2754 32.6907 32.0882 31.3843 30.6804 29.8826 29.0814 28.2481 27.4058 26.4781 25.4923 24.4558 23.3463 35.0330 35.5531 35.9813 36.3820 36.4438 36.5057 36.3152 36.0936 35.7122 35.2639 24.9995 26.2846 27.6385 28.9818 30.1937 31.4057 32.5199 33.6220 34.6623 35.6767 36.6670 37.6350 38.5755 39.4614 40.3362 41.1476 41.9590 42.7043 43.4472 44.3378 45.2701 46.1660 47.0372 47.8839 48.6954 24.2602 25.5071 26.8175 28.1175 29.2888 30.4602 31.5355 32.5989 33.6014 34.5785 35.5359 36.4751 37.3881 38.2490 39.0993 39.8895 40.6796 41.4069 42.1320 43.0119 43.9355 44.8252 45.6919 46.5360 47.3474 23.5961 24.8088 26.0802 27.3412 28.4762 29.6111 30.6514 31.6800 32.6486 33.5922 Page C-84 of C-173 F0306-0l R2

(;Structural Integrity Associates, Inc. 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.8831 0.9322 0.9813 1.0303 1.0794 1.1284 1.1775 1.2266 1.2756 1.3247 1.3738 1.4228 1.4719 1. 5209 1.5700 Load Case # 4: CD II Min 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 ------------

Crack Dimensions

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a c a/t c/a c/a = 3.9063 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.3125 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1. 0156 1. 054 7 1.0938 1.132 8 1.1719 1.2109 1.2500 4.1563 0.3325 0.3741 0.4156 0. 4572 0.4988 0.5403 0.5819 0.6234 0.6650 0.7066 0.7481 0.7897 0. 8313 0.8728 0.9144 0.9559 0.9975 1.0391 File No.: 1501350.301 Revision:

0 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0. 68 65 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0.5721 3.9063 3.9063 3.9063 3. 9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 34.8398 34.4380 33.9868 33.4380 32.8708 32.2002 31.5295 30.7626 29.9921 29.1750 28.3447 27.4215 26.4350 25.3927 24.2700 34.5200 35.4334 36.3217 37.1602 37.9886 38.7595 39.5305 40.2417 40.9507 41.8210 42.7368 43.6210 44.4837 45.3254 46.1369 K at tips a c 0.8522 0.9997 1.1662 1.3339 1. 5160 1.6981 1. 8923 2.0880 2.2920 2.4995 2. 7130 2.9320 3.1540 3.3821 3. 6113 3. 84 72 4.0832 4.3254 4.5678 4.8425 5.1263 5.4160 5.7098 6.0070 6.3090 0.8585 1.0073 1.1752 1.3443 1. 5280 1.7117 1.9076 2.1051 2.3110 2.5204 2.7365 2.9586 3.1841 3.4159 3.6489 3.8891 4.1292 4.3761 0.1303 0.1530 0 .1 772 0.2016 0.2285 0.2554 0.2848 0.3144 0.3458 0.3780 0.4157 0.4585 0.5030 0.5507 0.5992 0.6519 0.7046 0.7620 0.8196 0.8886 0.9607 1.0369 1.1158 1.1975 1.2833 0.1242 0.1459 0.1689 0.1921 0.2177 0.2433 0.2712 0.2994 0.3294 0.3601 0.3959 0.4364 0.4785 0.5237 0.5696 0.6194 0.6693 0.7237 Page C-85 of C-173 F0306-0 lR2 SJ Structural Integrity Associates, Inc.'" 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 1.0806 1.1222 1.1638 1. 2053 1.2469 1.2884 1.3300 4.4063 0.3525 0.3966 0.4406 0.4847 0.5288 0.5728 0.6169 0.6609 0.7050 0.7491 0.7931 0. 8372 0. 8813 0.9253 0.9694 1.0134 1.0575 1.1016 1.1456 1.1897 1.2338 1.2778 1. 3219 1. 3659 1.4100 4.6563 0. 3725 0.4191 0.4656 0.5122 0.5588 0.6053 0.6519 0.6984 0.7450 0.7916 0.8381 0.8847 0. 9313 0.9778 1.0244 1.0709 1.1175 1.1641 1.2106 1. 2572 1.3038 1. 3503 1.3969 1.4434 1.4900 4.9063 0.3925 0.4416 File No.: 1501350.301 Revision:

0 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0. 2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0.4119 0.4348 0.4577 0.4805 0.5034 0. 52 63 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.6563 4.6563 4. 6563 4.6563 4. 6563 4.6563 4. 6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4. 6563 4.6563 4. 6563 4. 6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.9063 4.9063 4.6233 4.9074 5.2020 5.5033 5.8092 6.1191 6.4347 0.8648 1.0149 1.1841 1.3545 1. 5396 1.7247 1.9222 2.1212 2.3287 2.5398 2.7584 2.9838 3.2126 3.4482 3.6851 3.9296 4.1741 4.4259 4.6780 4.9731 5.2804 5.5955 5.9160 6. 2411 6.5729 0.8704 1. 0217 1.1920 1. 3636 1. 5500 1. 7363 1. 9352 2 .1356 2.3446 2.5572 2.7779 3.0062 3.2381 3.4771 3.7175 3.9658 4.2141 4.4703 4. 72 68 5.0318 5.3504 5.6779 6. 0113 6.3499 6. 6963 0.8755 1. 0278 0.7783 0.8438 0.9125 0.9851 1. 0603 1.1381 1.2199 0.1179 0.1385 0.1602 0.1821 0.2064 0.2307 0. 2571 0.2839 0.3123 0.3415 0.3752 0.4130 0.4524 0.4946 0.5375 0.5841 0.6306 0.6814 0.7323 0. 7 935 0.8576 0.9253 0.9954 1. 0681 1.1444 0.1122 0 .1318 0.1525 0.1732 0.1963 0.2194 0.2445 0.2700 0. 2971 0.3248 0.3566 0.3922 0.4291 0.4687 0.5089 0.5525 0.5961 0.6436 0. 6913 0.7486 0.8085 0. 8719 0.9376 1. 0056 1. 0770 0 .1072 0.1259 Page C-86 of C-173 F0306-0I R2 e Structural Integrity Associates, Inc. 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.4906 0.5397 0.5888 0.6378 0.6869 0.7359 0.7850 0.8341 0.8831 0.9322 0.9813 1.0303 1.0794 1.1284 1.1775 1.2266 1.2756 1.3247 1.3738 1. 422 8 1.4719 1. 5209 1.5700 Load Case # 5: Unload Max 0.2288 0. 2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0.4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 ------------

Crack Dimensions

---

a c a/t c/a c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 3.9063 0.3125 0.3516 0.3906 0.4297 0.4688 0.5078 0.546 9 0.5859 0.6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1. 0156 1. 054 7 1. 0938 1.1328 1.1719 1.2109 1.2500 4.1563 0.3325 0.3741 0.4156 0.4572 0.4988 0.5403 0.5819 0. 6234 0.6650 0.7066 File No.: 1501350.301 Revision:

0 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0. 2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 1.1991 1.3717 1. 5593 1.7468 1.9469 2.1485 2.3588 2. 5727 2.7955 3.0264 3.2610 3.5030 3.7465 3.9983 4.2501 4.5102 4.7707 5.0845 5. 4133 5.7518 6.0968 6.4477 6.8070 0.1455 0.1653 0.1872 0.2092 0.2332 0.2575 0.2834 0.3099 0.3400 0.3735 0.4082 0.4454 0.4832 0 .'6 2 42 0.5652 0.6097 0.6545 0.7082 0.7645 0.8240 0.8856 0.9494 1. 0164 K at tips a c 12.7283 12.9928 13.2144 13.4268 13.5256 13.6244 13.6391 13.6434 13.5944 13.5230 13.4658 13.4217 13.3634 13.2769 13.1853 13.0647 12.9441 12.7977 12.6503 12.5312 12.4200 12.2922 12.1530 12.0044 11.8423 12.8655 13.1393 13.3754 13.6024 13.7160 13.8297 13.8595 13.8789 13.8452 13.7894 9.6352 10.1408 10.6742 11.2038 11. 6857 12.1676 12.6144 13. 0569 13.4778 13.8897 14.2942 14.6919 15.0802 15.4499 15.8156 16.1591 16.5025 16.8234 17.1435 17.5160 17.9033 18.2785 18.6455 19.0045 19.3522 9.3580 9.8491 10.3677 10.8825 11.3510 11.8195 12.2539 12.6840 13.0930 13.4932 Page C-87 of C-173 F0306-0IR2 e Structural Integrity Associates, Inc." 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2 300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2 000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2 600 0.2 700 0.2800 0.2 900 0.7481 0.7897 0.8313 0.8728 0.9144 0.9559 0.9975 1.0391 1.0806 1.1222 1.1638 1. 2053 1.2469 1.2884 1.3300 4.4063 0.3525 0.3966 0.4406 0.4847 0.5288 0.5728 0.6169 0.6609 0.7050 0.7491 0.7931 0. 8372 0.8813 0.9253 0.9694 1.0134 1.0575 1.1016 1.1456 1.1897 1.2338 1.2778 1. 3219 1. 3659 1. 4100 4.6563 0. 3725 0.4191 0.4656 0.5122 0.5588 0.6053 0.6519 0.6984 0.7450 0.7916 0.8381 0.8847 0. 9313 0.9778 1. 0244 1.0709 1.1175 1.1641 1.2 106 1.2 572 1.3038 1. 3503 File No.: 1501350.301 Revision:

0 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 52 63 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0. 2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4. 6563 4.6563 4.6563 4.6563 4.6563 4. 6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4. 6563"' 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 13.7484 13.7210 13.6793 13.6090 13.5335 13.4284 13.3232 13.1914 13.0587 12.9539 12.8569 12.7412 12.6127 12.4734 12.3187 12.9951 13.2785 13.5312 13.7749 13.9060 14.0372 14.0851 14.1228 14.1081 14.0715 14.0498 14.0420 14.0196 13.9681 13. 9114 13.8243 13.7373 13.6228 13.5073 13.4178 13.3356 13.2318 13.1134 12.9826 12.8337 13.1107 13.4027 13.6703 13.9289 14.0756 14.2224 14.2865 14.3405 14.3427 14.3232 14.3189 14.3285 14.3233 14.2887 14.2486 14.1778 14.1069 14.0078 13.9077 13.8318 13.7628 13.6698 13.8862 14.2726 14.6499 15.0092 15.3647 15.6989 16.0330 16.3453 16.6567 17.0259 17.4114 17.7855 18.1518 18.5106 18.8585 9.0558 9.5308 10.0309 10.5274 10.9784 11.4294 11.8469 12.2603 12.6528 13.0366 13.4146 13.7873 14 .1513 14.4979 14.8410 15.1639 15.4868 15.7888 16.0900 16.4514 16.8298 17.1975 17.5581 17.9116 18.2551 8.7861 9.2466 9.7303 10.2104 10.6458 11.0812 11.4837 11.8821 12.2599 12.6291 12.9937 13.3541 13.7061 14.0415 14.3735 14.6864 14.9992 15.2921 15.5841 15.9386 16.3106 16.6727 Page C-88 of C-173 F 0 306-01 R2 e Structural Integrity Associates, Inc."' 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 1. 3969 1.4434 1. 4900 4.9063 0.3925 0.4416 0.4906 0.5397 0.5888 0.6378 0.6869 0.7359 0.7850 0.8341 0.8831 0.9322 0.9813 1.0303 1.0794 1.1284 1.177 5 1.2266 1.2756 1.3247 1.3738 1. 4228 1.4719 1. 5209 1.5700 Load Case # 6: Unload Min 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 4.6563 4.6563 4.6563 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 ------------

Crack Dimensions

---

a c a/t c/a c/a = 3.9063 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.3125 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0. 62 50 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1.0156 1. 054 7 1.0938 1.1328 1.1719 1.2109 1.2500 4.1563 0.3325 0.3741 File No.: 1501350.301 Revision:

0 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 '3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 4.1563 4.1563 13.5604 13.4370 13.2934 13.2145 13.5143 13.7952 14.0671 14.2279 14.3887 14.4674 14.5360 14.5534 14.5494 14.5606 14.5858 14.5960 14.5765 14.5515 14.4952 14.4389 14.3536 14.2673 14.2037 14.1465 14.0631 13.9619 13.8452 13.7062 17.0281 17.3770 17.7164 8.5439 8.9915 9.4603 9.9257 10.3470 10.7684 11.1574 11.5424 11.9070 12.2631 12.6157 12.9651 13.3064 13.6317 13.9537 14.2576 14.5614 14.8460 15.1298 15.4780 15.8443 16.2014 16.5522 16.8968 17.2327 K at tips a c 2.3087 2.4902 2.6834 2.8765 3.0683 3.2602 3.4522 3.6442 3.8368 4.0297 4.2298 4.4366 4.6444 4.8541 5.0643 5.2768 5.4893 5.7045 5.9198 6.1695 6. 4290 6.6924 6.9583 7.2267 7.4986 2.3306 2.5145 1.1822 1.2634 1.3485 1.4334 1. 5156 1. 5978 1.6786 1. 7592 1.8391 1.9187 2.0031 2.0920 2.1813 2.2716 2.3622 2.4541 2.5460 2.6397 2.7335 2.8440 2.9592 3.0767 3.1957 3.3164 3.4392 1.1453 1.2236 Page C-89 of C-173 F0306-0JR2 Pacific Gas and Electric Company November 3, 2015 PG&E Letter DCL-15-131 U.S. Nuclear Regulatory Commission ATIN: Document Control Desk Washington, DC 20555-0001 Docket No. 50-275, OL-DPR-80 Diablo Canyon Power Plant (DCPP) Unit 1 Pressurizer Spray Line Pipe Weld Flaw Evaluation Dear Commissioners and Staff: B arry S. Allen Vice President, Nuclear Services Diablo Canyon Power Plant Mail Code 104/6 P. 0. Box 56 Avila Beach, CA 93424 805.545.4888 Internal: 691.4888 Fax: 805.545.6445 In accordance with the requirements of the American Society of Mechanical Engineers (ASME) Boiler and Pressure Vessel Code Section XI, 2001 Edition through 2003 Addenda, Paragraphs IWB-3132.3, IWB-3134(b), and IWB-3640, Pacific Gas &.Electric Company is submitting to the NRC the attached structural flaw evaluation of a flaw found in Diablo Canyon Unit 1, ASME Code Class 1 pressurizer spray line pipe weld. IWB-3134(b) states, "Analytical evaluation of examination results as required by IWB-3132.3 shall be submitted to the regulatory authority having jurisdiction at the plant site." Ultrasonic exam-inations performed during the Unit 1 nineteenth refueling outage (1R19) identified a flaw in the pressurizer spray line pipe weld WIB-378, a 4-inch nominal pipe size, 0.437 -inch nominal thickness, pipe-to-elbow weld in the pressurizer spray line. The flaw was characterized per Section XI, Paragraph IWA-3310 and Figure IWA-3310-1 of the ASME Code as a planar flaw. Flaw characteristic calculations were performed to determine acceptability on the basis of IWB-3500, Paragraph IWB-3514.3.

The flaw was initially dispositioned as unacceptable.

Further analytical evaluation, performed in accordance with the methods prescribed in IWB-3600, demonstrate that the weld containing the flaw is acceptable for continued service. The pressurizer spray line pipe weld WIB-378 flaw evaluation report prepared by Structural Integrity Associates is enclosed.

PG&E makes no new or revised regulatory commitments (as defined by NEI 99-04) in this letter. If you have any questions or require additional information, please contact Mr. Hossein Hamzehee at (805) 545-4720.

A member of the STARS (Strategic Teaming and Resource Sharing) Alliance Callaway

• Diablo Canyon

• Palo Verde

• Wolf Creek Document Control Desk November 3, 2015 Page 2-Sincerely, 5 4£L--Barry S. Allen rntt/4231/SAPN 50033145 Enclosure cc: Diablo Distribution cc/enc: Marc L. Dapas, NRC Region IV Administrator PG&E Letter DCL-15-131 Thomas R. Hipschman, NRC Senior Resident Inspector Siva P. Lingam, NRR Project Manager Gonzalo L. Perez, Branch Chief, California Department of Public Health State of California, Pressure Vessel Unit A member of the STARS (Strategic Teaming and Resource Sharing) Alliance Callaway

• Diablo Canyon

• Palo Verde

• Wolf Creek Enclosure PG&E Letter DCL-15-131 Structural Integrity Associates Report No. 1501350.301 Diablo Canyon Power Plant Spray Line Flaw Evaluation Diablo Canyon Power Plant, Unit 1 Evaluation of the Flaw in the 4-inch Spray Line Weld WIB-378 Structural Integrity Associates, Inc. File No.: 1501350.301 Project No.: 1501350 CALCULATION PACKAGE Quality Program Type: Nuclear D Commercial PROJECT NAME: Diablo Canyon Power Plant Spray Line Flaw Evaluation CONTRACT NO.: 3501065975 CLIENT: PLANT: Pacific Gas & Electric Diablo Canyon Power Plant, Unit 1 CALCULATION TITLE: Evaluation of the Flaw in the 4-inch Spray Line Weld WIB-378 Document Revision 0 Affected Pages 1-24 A-1-A-3 B-1 -B-3 C-1 -C-173 Revision Description Initial Issue Project Manager Approval ature & Date N.G.Cofie NGC 1112/15 Pre parer( s) & Checker(s) tures & Date Preparers: C. S. Lohse CSL 1112/15 W. Wong ww 1112/15 Checkers: S. S. Tang SST 1112115 M.Fong MF 1112/15 Page 1 of24 F030 6-01R2 e Structural Integrity Associates, Inc."' Table of Contents

1.0 INTRODUCTION

.........................................................................................................

4 2.0 TECIINICAL APPROACH ..........................................................................................

4 3.0 DESIGN INPUTS ..........................................................................................................

5 3.1 Geo1netry

...........................................................................................................

5 3.2 Loads ..................................................................................................................

5 3.3 Operating Conditions

.........................................................................................

6 3.4 Material ..............................................................................................................

6 3.5 I11dication Size ...................................................................................................

6 3.6 Cause of Cracking ..............................................................................................

6 3.7 Thermal Transients

............................................................................................

7 3.8 Residual Stress ...................................................................................................

8 4.0 CALCULATIONS

.........................................................................................................

8 4.1 Flaw Characterization

........................................................................................

8 4.2 Determination of Stresses and Load Combinations

...........................................

9 4.3 Thermal Transient Stress Analyses and Stress Intensity Factors Determination

.............

.....................................................................................

1 0 4.4 Crack Growth Evaluation

................................................................................

11 4.4.1 Stress Intensity Factors ..........................

..............................................

............

11 4.4.2 Austenitic Stainless Steel Fatigue Crack Growth Law ......................

..............

12 4. 4. 3 Loading Combinations and Stresses ................................................................

13 4. 4. 4 Allowable Flaw Size Determination

...............................

................

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13 5.0 RESULTS ....................................................................................................................

13

6.0 CONCLUSION

S

.........................................................................................................

14

7.0 REFERENCES

.* ...........................................................................................................

15 APPENDIX A NDE lSI EXAMINATION DATA ..............................................................

A-1 APPENDIX B COMPUTER FILE LISTING .......................................................................

B-1 APPENDIX C PC-CRACK OUTPUT FILES ..........................................

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C-1 File No.: 1501350.301 Revision:

0 Page 2 of24 F0 3 06-0 I R 2 e Structural integrity Associates, Inc. List of Tables Table 1: Piping Loads at Node 165 ...............

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16 Table 2: Piping Loads for Calculation of Stresses (Node 165) ..............................................

17 Table 3: Load Combinations for Stress Calculations

.............................................................

18 Table 4: Primary Stresses .......................................................................................................

19 Table 5: Secondary Stresses ...................................................................................................

19 Table 6: Transient Cycles and Groupings

..............................................................................

20 Table 7: Transients Analyzed in SI-TIFFANY

......................................................................

21 Table 8: Material Propetiies for A-376 TP 316 ......................................................................

22 Table 9: Fatigue Crack Growth Loadings ..............................................................................

22 Table 10: Initial, Final, and Allowable Flaw Sizes ................................................................

22 List of Figures Figure 1. Is01netric Drawing of the Spray Line ......................................................................

23 Figure 2. Setni-Elliptic Flaw on Inside Surface of a Cylinder ..................................... .........

24 File No.: 1501350.301 Revision:

0 Page 3 of24 F0306-0 I R2 e Structural Integrity Associates, Inc.

1.0 INTRODUCTION

During routine in service inspection of pressurizer spray line welds at Diablo Canyon Power Plant (DCPP), Unit 1 in the Fall2015 1R19 outage, a circwnferential flaw was identified at Weld WIB-378 [1]. The location of this weld is shown in Figure 1 (isometric drawing of the spray line). As can be seen frmn this figure, this weld is located two elbows away frmn the pressurizer.

There is a short vertical line that goes upwards from the pressurizer, followed by a horizontal section and then another vertical pmiion that goes downwards.

The flawed elbow is on the upstream side of the second elbow on the down vet1ical pmiion of the spray line. The possible cause of cracking is discussed in Section 3 .6. This calculation documents an evaluation to determine the acceptability of the circumferential flaw identified in the spray line S6-15, weld WIB-378 at DCPP Unit 1 for continued operation.

Included in the calculation is documentation of loadings, calculation of stresses and stress intensity factors, determination of fatigue crack growth, and the allowable flaw size. Based on the evaluation contained herein, the flawed component is acceptable for continued operation.

The crack will not exceed the ASME Code,Section XI allowable flaw size for the life of the plant (asswning a 60-year operating life). 2.0 TECHNICAL APPROACH The technical approach used for the flaw evaluation consists of using the ASME Code,Section XI, IWB-3600 and Appendix C requiretnents sumtnarized in the following steps: 1. Characterize the flaw and use the Acceptance Standards ofiWB-3500 (specifically Table IWB-3514-2) of the ASME Code,Section XI [3] to determine if a detailed flaw evaluation is required per IWB-3600.

If required, perfonn a detailed flaw evaluation.

As will be explained later, the rules of IWB-3600 are used in this evaluation.

2. Determine the stresses at the flaw location.

Since the flaw is in the circmnferential direction, the stresses required are the axial stresses.

The loadings considered in this evaluation include pressure, deadweight, thermal expansion, seismic (inetiial and anchor movements), residual, and thermal transient stresses.

3. Determine the ASME Code,Section XI allowable flaw size for austenitic stainless steel piping in IWB-3640 and Appendix C [3]. 4. Determine thennal transients applicable to this piping location.

5. Calculate stress intensity factors for the thermal transients and other loadings.

6. Perform a crack growth evaluation to determine how long it will take the as-found flaw to reach the ASME Code,Section XI allowable flaw size determined in Step 3. 7. Cmnpare the end of the evaluation period flaw (after fatigue crack growth) to the ASME Code,Section XI allowable flaw size to determine acceptability for operation tlu*ough the evaluation period. The current version of ASME Code,Section XI used at DCPP is the 2001 Edition with Addenda tlu*ough 2003 [3]. File No.: 1501350.301 Revision:

0 Page 4 of24 F0306-0 I R2 e Structural Integrity Associates, Inc. Two computer 'programs verified under Structural Integrity Associates (SI) Quality Assurance (QA) program are used to facilitate the calculations in this evaluation.

These cmnputer programs are TIFFANY [8] and pc-CRACK [9]. The software SI-TIFFANY

[8] perfonns thermal stress and stress intensity factor analysis of a pipe with a specified temperature/flow history of the fluid inside the pipe. The end result of the software output is tables of the 1naxin1um and 1ninimum stress intensity factor for ID part-through circumferential or axial flaws for selected crack sizes. In this calculation, SI-TIFFANY is used to calculate the thermal transient stress and tninimuin and maximum stress intensity factor distributions for the bounding thermal transient(s).

These 1naximwn and 1ninimum stress intensity factors are used for the fatigue crack growth evaluation.

The fatigue crack growth evaluation is performed using pc-CRACK [9]. pc-CRACK [9] is a Windows-based software for the fracture 1nechanics analysis of cracks in materials.

Analysis procedures are based on linear elastic fracture tnechanics (LEFM) or elastic-plastic fracture tnechanics (EPFM). The code can be used for a very wide range of crack geometries subjected to a variety of stress states. Smne 35 LEFM and 15 EPFM crack configurations are included, several with influence functions that allow consideration of arbitrary stress distributions.

pc-CRACK can compute critical crack size, allowable flaw size based on the ASME Code, and the life of a cmnponent subjected to sub-critical crack growth such as fatigue, stress corrosion cracking (SCC) or primary water stress corrosion cracking (PWSCC). In this calculation, pc-CRACK is used to calculate the fatigue crack growth and to detennine the flaw acceptability (stability) using the rules of ASME Code,Section XI, Appendix C [3]. 3.0 DESIGN INPUTS 3.1 Geounetry Nmninal pipe size (NPS) = 4 inch [5] Pipe outside diameter (OD) = 4.5 inches [5] Nominal pipe thickness=

0.437 inches [5] Actualtneasured pipe thickness are all thicker than 0.452 inches [1] In this evaluation, the nmninal thickness will be conservatively used as it results in a larger a/t and larger stre&B;J s. -3.2 Loads All piping loads for this analysis are taken from Reference

7. The location of the flaw is shown in Figure 1. The node in the piping analysis [7] is node 165. Multiple load cases are provided in Reference

7. All the load cases in Reference 7 are contained in Table 1. To account for any future updates of the piping loads due to changes in the piping analysis, the loads are conservatively increased by a 50% factor. Table 2 presents the loads in different units and includes the 50% increase.

The loads are fwiher explained in the calculation of stresses.

File No.: 1501350.301 . Revision:

0 Page 5 of24 F0306-0IR2 e Structural Integrity Associates, Inc.'" 3.3 Operating Conditions Reference 6 defines the operating conditions for the spray line. The spray line is line 15 in Reference

6. Four operating conditions are defined [6, pg. 11]. Page 46 of Reference 6 defines the temperatures and pressures for the four conditions.

In order to bound all the operating conditions, the enveloped condition listed in Reference 6 is used and the pressure and tetnperature are shown below. Discussion of the thermal transients applicable to this location is contained in Section 3.7. Internal Pressure=

2510 psig [6, pg. 46, enveloped condition used] Tetnperature

= 650°F [6, pg. 46, enveloped condition used] 3.4 Material The tnaterial of the piping is A-376 TP 316 austenitic stainless steel and the elbow is A-403 Type 316 [5]. Reference 2 identifies the weld as being stainless steel (Type 308) and using both GTA Wand SMA W welding processes.

As a flux type weld is used, the elastic plastic fracture tnechanics method of the ASME Code,Section XI, Appendix C will be required for the allowable flaw size detennination.

For the flaw evaluation, the flow stress of the material is required.

At a temperature of 650°F, the stainless steel material properties are as follows (SA-376 TP 316 properties used): Sy = 18.5 ksi [4] Su = 71.8 ksi [ 4] ay= 45.15 ksi (average of Sy and Su) 3.5 Indication Size One circumferential indication was identified in the weld [1]. A page frmn the NDE report and the indication sketch is contained in Appendix A of this calculation.

Length= 0.625 inch [1] Maxitnmn flaw depth= 0.08 inch [1] Flaw depth-to-thickness ratio (a/t) = 0.183 (based on nominal thickness) 3.6 Cause of Cracking A thorough root cause of the cracking cmmot be undetiaken since the flawed component was not retnoved from service. Possible causes of the cracking include:

• Thennal fatigue from thennal transients and thermal stratification

• Stress corrosion cracking

• Fabrication defect File No.: 1501350.301 Revision:

0 Page 6 of24 F0306-0 I R2 e Structural Integrity Associates, Inc. Although not very conclusive, the crack like indication identified in Reference 1 is noted as being ID connected for conservatism.

The indication plot [1] (Appendix A) shows the indication located 90 degrees frmn the intrados and extrados of the elbow. One of the concerns is that stratification may occur in the spray line. Stratification would occur if there was low flow in the spray line that did not fill up the horizontal portion of the piping. If the flow did not fill the pipe, hot steam from the pressurizer could fill up the top portion of the spray line and create a stratified condition with hot steam on the top and colder water on the bottom. If stratification were to occur, it would cause a bending moment in the upper portion of the spray line. This would cause high stresses in the intrados or extrados of the elbow. As the indication is located 90 degrees frmn the intrados and extrados, it does not appear that stratification would be the cause as the location is at the neutral axis for the bending moment. As noted in Reference 10, the plant is operated with a constant spray flow for normal operations with main spray always available.

Having a constant spray flow reduces the risk of stratifying the upper spray line. One other possible apparent cause could be stress corrosion cracking.

However as the system is in constant operation and there is very little oxygen in the system, the risk of stress corrosion cracking is small. DCPP has also perfonned other evaluations that has eliminated stress corrosion cracking as a plausible degradation mechanism in the reactor coolant systetn. During the NDE of this weld, PGE examiners observed that the flaw produced a very sharp signal with limited reflection at any skew angle indicating that it is likely planar and "smooth surfaced" like a lack of fusion, and not like a multi-faceted stress corrosion flaw or thermal fatigue striations.

The flaw was not seen on the original construction radiograph mostly ruling out a volumetric inclusion type defect. As thennal stratification and SCC are not likely causes and the defect appears to be associated with a lack of fusion, the only mechanistn that will lead to flaw growth is due to thermal transients and thermal cycling. As such, the fatigue crack growth evaluation is appropriate as the thermal transient cycles are considered.

3. 7 Thermal Transients The spray line is used for pulling water off of the cold legs and injecting it into the top of the pressurizer through the spray nozzle. The pressurizer runs at a higher temperature than the cold leg of the reactor coolant systetn. As shown in Figure 1, this location is two elbows retnoved fron1 the spray nozzle ofthe pressurizer.

Therefore, it is conservatively assumed that this location will see transients sitnilar to the pressurizer spray nozzle. The pressurizer spray nozzle is located in the steam space of the pressurizer.

As such, it is subject to a steatn condition at the pressurizer temperature.

As the flaw is located on the lower half of the 2nd elbow, it would be expected to be full of water as some constant flow of water is present in the spray line. Therefore, this location would not be subjected to a cold shock (due to the cold fluid from the cold leg) and then a hot shock (due to reflood of the steam in the pressurizer space) which is typical for a pressurizer spray nozzle. However, it is still subjected to a cold shock of water as this potiion of the spray line will be closer to the pressurizer tetnperature and will see colder water frmn the cold leg side of File No.: 1501350.301 Revision:

0 Page 7 of24 F 0 30 6-0 I R 2 e Structural integrity Associates, Inc.'" the plant. Since it will retnain filled with water, after flow stops, it would slowly transition back to near the pressurizer temperature.

For this evaluation a few bounding thermal transients for the pressurizer spray nozzle are considered at the flaw location.

Reference 1 0 lists the pressurizer spray nozzle transients, nmnber of cycles, and temperature changes for the DCPP life of 50 years. The transients sta11 at a constant temperature and then a shock of cold water occurs for some time duration until the flow of water stops. As all transients are sitnilar, a group of five transients is developed based on the temperature change value. Table 6 lists the group of transients and number of cycles. The maxilnmn flow rate for the spray nozzle is used for all transients which is 800 gpm [10]. Each event is assumed to stat1 at 650°F. The actual operating pressurizer te1nperature is 653°F, but since this location is slightly removed frmn the pressurizer, a value of 650°F is reasonable and chosen for shnplicity.

Note that all transients do not occur at full temperature.

Some of the heatup and cooldown transients occur at a lower tetnperature, however, using the higher temperature is conservative. The five transient definitions to be analyzed are listed in Table 7. The tilnes, te1nperatures, pressures, and flow rates are defined in this table. As shown in the table, the full pressure is assmned for all conditions.

This will be conservative as the spray nozzle does not see pressure variations during the transients, so using the higher pressure will give a higher tnean stress (higher constant stress intensity factor) which is conservative.

The ramp back to full te1nperature is assumed to occur over 300 seconds. 3.8 Residual Stress The residual stresses in the weld are required for the crack growth evaluation.

For this evaluation, a constant tensile residual stress will be assumed. The value assumed is the room temperature yield strength of the tnaterial, which is 30 ksi [4] for Type 316 stainless steel. Using this value is conservative as the axial residual stresses in piping are required to balance through the wall thickness to retnain in equilibrium which is represented by a linear through-wall bending stress that is compressive on the ID and tensile on the OD. Assuming a constant tensile stress is not realistic, but is conservative as it gives a higher mean stress for the evaluation which leads to higher crack growth rates. 4.0 CALCULATIONS 4.1 Flaw Characterization .... *.Since oniy one circumferential flaw was identified

,.the flaw cmnbination rules of ASME Code,Section XI, IW A-3300 do not apply. The characterized flaw length is 0.625 inch and the flaw depth is 0.08 inch [1] (see Appendix A). The actualtneasured thickness at the flaw location varies, but is greater than 0.452 inches, therefore, the nmninal pipe wall thickness of 0.437 inches is conservatively used for a flaw-depth to-thickness ratio of0.183 and an aspect ratio of0.128. Using Table IWB-3514-2 of ASME Code Section XI, this flaw does not meet the Acceptance Standards and, therefore, will need to be evaluated per the flaw evaluation procedures of IWB-3600.

File No.: 1501350.301 Revision:

0 Page 8 of24 F 0 30 6-0 I R2 lJ Structural Integrity Associates, Inc. 4.2 Determination of Stresses and Load Combinations The stresses are calculated based on the piping loads frmn Reference 7 and contained in Tables 1 and 2. A description of the loads is given below. After the description, the load cmnbinations for all service levels are described.

Deadweight (DW)-Deadweight of piping syste1n Thermal I through 4-Four thennal expansion conditions described in Reference

6. The bounding condition is used. The bounding thennalload is labeled at TH. SAM DE-Seismic anchor tnovements from DE condition (Shnilar to OBE) SAM DD-Seismic anchor movements from DD condition (Siinilar to SSE) SAM HS-Seismic anchor movetnents frmn HS condition (Faulted seistnic condition specific to DCPP) Seismic DX/DZ-Inet1ia seismic loads for DE conditions.

Only the bounding loads frmn DX or DZ are used. This is labeled as DE in the text. Seismic XD/ZD-Inertia seismic loads from DD condition.

Only the bounding loads from XD or ZD are used. This is labeled as DD in the text. Seismic HX/HZ -Inertia seistnic loads frmn HS condition.

Only the bounding loads from HX or HZ are used. This is labeled as HS in the text. With the definition of the piping loadings, the load combinations for each service level are defined as: Primary Loads Service Level A -D W + Pressure (P) Service Level B-DW + P +DE Service Level C-DW + P + DD Service Level D-DW + P + HS Secondary Loads Service Level A-TH Service Level B-TH + SAM DE Service Level C-TH + SAM DD Service Level D -TH + SAM HS The load cotnbinations are shown in Table 3. The piping stresses are calculated based on pressure and external bending tnoments using equations frmn Appendix C, Section C-2500 [3] as described as follows. Primary tnetnbrane stress ( Oin) is given by: Oin = PD/(4t) + F/A, where: P operating pressure for the service level being considered D outside diatneter of the component t thickness, consistent with the location at which the outside diameter is taken File No.: 1501350.301 Page 9 of24 Revision:

0 F0306-0 I R2

!\SJ Structural Integrity Associates, Inc. F resultant force for the appropriate primary load cmnbination for each Service Level A cross sectional area of the pipe Primary bending stress ( m) is given by: m = DMb/(21), where: D outside dimneter of the component d inside diameter, consistent with the point at which the outside diameter is taken Mb resultant tnmnent for the appropriate primary load co'mbination for each Service Level I moment of inertia, (n:/64) (D 4-cf) Secondary bending stress (a-e) is given by: O"e = DMe/(21), where: D outside dimneter of the component d inside diameter, consistent with the point at which the outside diameter is taken Me resultant moment for the appropriate secondary load combination for each Service Level (includes seis1nic anchor loads and thermal expansion)

I tnmnent of inertia, (n:/64) (D 4-cf) For this evaluation, the forces are conservatively considered a tnembrane stress and added to the pressure cmnponent.

Secondary forces are also added to the secondary bending stress tenn for conservatism.

The stress for the secondary forces are calculated as F I A, where F is the resultant force and A is the area of the piping. The calculation of stresses is shown in Tables 4 and 5. 4.3 Thermal Transient Stress Analyses and Stress Intensity Factors Determination Tables 6 and 7 list the transients that are evaluated for the flawed location.

The transients in Table 7 are *evaluated with SI-TIFFANY to detennine the transient stresses and stress intensity factors. A total of five SI-TIFFANY runs are made. Construction of the input files for each transient involves inserting each transient titne history into an input file. A ti1ne step ofO.Ol seconds is used in all SI-TIFFANY runs. Alltnaterial properties used for the SI-TIFFANY runs are contained in Table 8. Each SI-TIFF ANY run with the corresponding filenmne has the following relevant files, which are included as supporting files to this calculation:

• .dat SI-TIFFANY input file * .rpt SI-TIFFANY output file, which echoes the inputs. File No.: 1501350.301 Page 10 of 24 Revision:

0 F0306-0l R2 e Structural Integrity Associates, Inc. *.mnn SI-TIFFANY output file with tabulated Kmin values. *.Inxn SI-TIFFANY output file with tabulated Kmm( values. The tabulated values of the Ininitnum and maximum stress intensity factors, Kmin and Kmax, for specific crack sizes are used for fatigue crack growth analysis.

All SI-TIFFANY files are listed in Appendix B. SI-TIFFANY uses tetnperature history of the transient to compute the thermal stress due to the radial gradient of the temperature in the pipe wall. At the beginning of the transient, the piping location is taken to be at a uniform temperature equal to the first line in the transient history. The radial gradient thermal stress is then cmnbined with the pressure stress and thermal expansion stresses due to tensile and bending loads (restraint of thermal expansion) to provide stresses that are used to calculate stress intensity factors. The thermal expansion tension and bending stress at the beginning of the transient is taken to be the stress due to the resultant force and mmnent of the restraint of thetmal expansion, which are obtained from the loads in Table 2, scaled up or down from the normal operating tetnperature using the following relation: (T ) Ta ve -70 (J ave = (Jno T,IO -70 This relation is applied to tension and bending thermal expansion stresses to scale the values during the transient.

Tno is 650.0oF (normal operation tetnperature).

Tave is the average wall temperature, which is evaluated in SI-TIFFANY.

The values of (Jno(nominal stress) for tension and bending were calculated using the equations from Section 4.2 and the loads from Table 2. The values of (Jno t e nsion and (Jno b e ndin g frmn thermal expansion input to SI-TIFFANY are 0.077 ksi and 1.241 ksi, respectively.

Stresses due to deadweight and OBE are input separately in the subsequent crack growth calculation.

Pressure stresses do not need to be input to SI-TIFFANY separately.

Only the pressure term is included as SI-TIFFANY calculates the stresses due to pressure.

SI-TIFFANY treats the piping as insulated and the insulation is considered perfect which tneans that no heat transfer is considered to the surrounding enviromnent.

The piping is insulated as noted in the ison1etric drawing shown in Figure 1. 4.4 Crack Growth Evaluation 4.4.1 Stress Intensity Factors SI-TIFF ANY calculated stress intensity factors (K) and determined tnaxiinuin applied K (Kmax) and 1ninhnmn applied l( (Kmin) for a semi-elliptical inside-surface flaw in a cylinder for various flaw depths and aspect ratios. The Kmax and Kmin values include the effects of internal pressure, thermal expansion piping loads, and thermal transient stresses.

Kmax and Kmin represent the range of applied K for each transient whose difference, = Kmax-Kmin, are used by pc-CRACK for the fatigue crack growth (FCG) calculations.

File No.: 1501350.301 Revision:

0 Page 11 of24 F0306-0 I R2 e Structural Integrity Associates, Inc ... The constant stress intensity values for deadweight and residual stress were not included in SI-TIFFANY.

As such, they are input as constant stress values for each load cycle. The semi-elliptical flaw model is used in pc-CRACK to determine the fatigue crack growth. The flaw model is shown in Figure 2. 4.4.2 Austenitic Stainless Steel Fatigue Crack Growth Law The ASME Code has developed new fatigue crack growth laws for austenitic stainless steels in PWR water environments.

However, these new laws have not been published and as such, they have not been endorsed by the US NRC. As such, the fatigue crack growth law for austenitic steels in air currently approved in ASME Section XI, Appendix C is used in the FCG calculation with an appropriate environmental factor to account for the PWR environment (see below). This crack growth law is built into pc-CRACK and is based on the crack growth law for austenitic steels published in Appendix C of Section XI of the ASME Code [3]. Since the built-in crack growth law is for stainless steel in air, a tnultiplication factor of2 for the PWR environment

[11] is employed.

This factor of2 is accounted for in the crack growth evaluation by multiplying the number of cycles for each transient by 2. This factor of 2 is included in the number of cycles used for evaluation in Table 6. Crack growth is computed on a yearly basis to determine how long it will take the initial flaw size to reach the allowable flaw size. The nutnber of cycles is given in Table 6. da =C (M)n dN a where: Co =CS log 10 C = -10.009 + 8.12x1 0-4 T -1.13x1 0-6 T 2 + 1.02x1 0-9 T 3 l l R 0 S = 1 + 1.8R 0 < R 0.79 -43.35 + 57.97 R 0.79 < R < 1.0 n = 3.3 Tis temperature in °F, which is taken to be the maximmn temperature during the transient.

For this evaluation the temperature value is 650°F. The above constants provide crack growth rates in inches per File No.: 1501350.301 Revision:

0 Page 12 of24 F0306-0 1 R 2 S} Structural Integrity Associates, Inc."' cycle when K is in ksi-in 112* The evaluation is performed with a constant aspect ratio and also a variable aspect ratio. The limiting result from both evaluations is used. 4. 4. 3 Loading Combinations and Stresses SI-TIFFANY was used to obtain tables oftnaxiinum applied K (Kmax) and miniinum applied K (Kmin) for various flaw depths and aspect ratios due to system transients.

The Kmax values are contained in the filenames with MXN file extension and the Kmin values are contained in the filenames with MNN file extension.

The maximmn and minimum K for crack growth cycles are sitnply the Kmax and Kmin tables output frmn SI-TIFFANY, with deadweight and weld residual stress added to both the max and min of the cycle. Deadweight stresses are calculated from the loads given in Table 2. Deadweight and residual stress loads do not cycle, but are present in both the maximum and minimum of the cycle. The fatigue crack growth also needs to include OBE(DE). OBE(DE) is assumed to occur at the steady state plant condition, but steady state results were not calculated in any SI-TIFFANY runs. Therefore, OBE(DE) was considered to occur with the loading/unloading bounding transient.

Four hundred ( 400) OBE(DE) cycles are considered over the 50 year plant life [1 0]. Therefore, eight (8) cycles are considered each year. This number is doubled to account for a PWR environment, so sixteen (16) cycles are considered in the evaluation for each year. Table 9 defines the loading combinations used for each event evaluated in pc-CRACK. 4. 4. 4 Allowable Flaw Size Determination After the fatigue crack growth is performed, the final flaw size has to be checked against th.e allowable flaw sizes in the ASME Code,Section XI, Appendix C. pc-CRACK is used to determine the allowable flaw sizes. As stated earlier, the weld was manufactured partly with a SMA W process and, therefore, requires the use of elastic plastic fracture tnechanics (EPFM). The EPFM rules are contained in Article C-6000 of Section XI [3]. Each service level is checked by inputting pipe gemnetry, crack paratneters, and stresses appropriate for the service level. For this calculation, the initial flaw size is input into the progratn.

Based on the stress ratios, it gives the allowable flaw size tables (a/t (flaw depth/pipe thickness) and 1/c (flaw length/pipe circmnference) values), which can be used to determine the maximmn length and depth of the flaw. The pc-CRACK output files for the allowable flaw sizes are contained in Appendix C. 5.0 RESULTS The results of the evaluation are contained in Table 10. Table 10 contains the initial flaw size and the final flaw sizes using the two aspect ratio assmnptions.

It also contains a single bounding limiting allowable flaw size from all service levels. For the loadings, the limiting flaw size is from the tnembrane only check for Service Level A (see Appendix C) and this is the value reported in Table 10. As can be seen from this table, the allowable flaw depth is relatively large (75% of pipe wall thickness which is the tnaximum allowed by the ASME Code,Section XI). File No.: 1501350.301 Revision:

0 Page 13 of24 F0306-0 I R2 SJ Structural Integrity Associates, Inc."' For the fatigue crack growth evaluation, the flaw was grown under two conditions.

The first approach used a fixed-aspect ratio where the flaw aspect ratio remains constant as the flaw grows. The second approach used a variable aspect ratio where the length and depth of the flaws are allowed to grow independently from one another. As shown in Table 10, both the variable and fixed aspect ratios yield about the smne results. Looking at the output files in Appendix C, using a fixed aspect ratio is slightly n1ore conservative.

Nevertheless, the results show that using the grouped loadings, the flaw does not exceed the ASME Code,Section XI allowable flaw size for the remainder of the plant life (assuming a 60-year operating period). All files used in the analysis are listed in Appendix B. The results in Table 10 include the end of evaluation period flaw sizes for both growth conditions.

In order to show flaw acceptability, both the flaw depth and length must be acceptable as the ASME Code,Section XI has depth li1nits for defined flaw lengths. The flaw depth ratio (a/t) is compared to the ASME Code,Section XI allowable depth. If that depth is acceptable, then the flaw length ratio (1/circ) is compared to the ASME Code,Section XI allowable length. As shown in Table 10, both of these values are acceptable.

6.0 CONCLUSION

S The evaluation presented in this report has shown that the flawed weld in the spray line at DCPP, Unit 1 is acceptable for continued operation.

Using the bounding loads assumption, the flaw is acceptable for the remainder of the plant life (assuming a 60-year operating period). File No.: 1501350.301 Revision:

0 ... :.;, ,: Page 14 of24 F0 3 06-0 1 R 2 e Structural Integrity Associates, Inc.

7.0 REFERENCES

1. DCPP Design Input Transtnittal No. DIT-50809162-001-00, "Diablo Canyon Unit 1 Pressurizer Spray Line Flaw Evaluation," Attachment 7, Exam Data Sheet and Indication Sketch for Weld No. WIB-378, SI File No. 1501350.206.

2. DCPP Design Input Transmittal No. DIT-50809162-001-00, "Diablo Canyon Unit 1 Pressurizer Spray Line Flaw Evaluation," Attachment 6, Spray Line Welding Records, SI File No. 1501350.206.

3. ASME Boiler and Pressure Vessel Code,Section XI, 2001 Edition, with Addenda through 2003. 4. ASME Boiler and Pressure Vessel Code,Section II, Part D, 2001 Edition, with Addenda tluough 2003. 5. DCPP Design Input Transmittal No. DIT-50809162-001-00, "Diablo Canyon Unit 1 Pressurizer Spray Line Flaw Evaluation," Attachment 5, Engineering Calculation No. 3-104 and attached specification and isometric, SI File No. 1501350.206.

6. DCPP Design Input Transmittal No. DIT-50809162-001-00, "Diablo Canyon Unit 1 Pressurizer Spray Line Flaw Evaluation," Attachment 4, PG&E DCM No. M-46, Rev. 44, "Design Criteria!

Memorandmn M-46, Piping Pressure, Tetnperatures and Operation Modes," SI File No. 1501350.206.

7. DCPP Design Input Transmittal No. DIT-50809162-001-00, "Diablo Canyon Unit 1 Pressurizer Spray Line Flaw Evaluation," ME101 File, Problem No. 3-104, Rev. 5, SI File Nos. 1501350.203 and 1501350.206.

8. SI-TIFFANY 3.0, Structural Integrity Associates, Septetnber 15,2015. 9. pc-CRACK 4.1 CS, Version Control No. 4.1.0.0, Structural Integrity Associates , Decen1ber 31, 2013. 10. DCPP Design Input Transtnittal No. DIT-50809162-001-00, "Diablo Canyon Unit 1 Pressurizer Spray Line Flaw Evaluation," Attachments 1 through 3, FSAR and Transient Definitions, SI File No. 1501350.206.

11.Section XI Task Group for Piping Flaw Evaluation, ASME Code, "Evaluation of Flaws in Austenitic Steel Piping," Journal ofPressure Vessel Technology, Vol. 108, August 1986. File No.: 1501350.301 Revision:

0 Page 15 of24 F0306-0 1 R2 e Structural Integrity Associates, Inc.'" Table 1: Piping Loads at Node 165 Load Case FA (lb) FB (lb) Deadweight 211 18 Thermal! 316 52 Thermal2 12 113 Therma13 276 69 Therma14 9 15 SAM DE 57 43 SAMDD 115 86 SAMHS 41 25 Seismic DX 83 177 Seismic DZ 31 152 Seismic XD 139 301 Seismic ZD 53 271 Seismic HX 146 598 Seismic HZ 100 680 Note: Absolute values are used for all loads. File No.: 1501350.301 Revision:

0 FC (lb) MA (ft-lb) MB (ft-lb) 9 3 73 8 6 117 37 15 120 '* 14 5 125 4 0 16 12 20 53 24 40 105 8 12 35 682 738 229 227 235 87 1136 1230 381 384 396 148 864 906 407 443 362 264 MC (ft-lb) Page Number from ME101 File [7] 179 A-536 312 A-578 307 A-618 334 A-658 44 A-698 96 A-740 192 A-782 56 A-824 104 A-1073 69 A-1125 179 A-1177 122 A-1229 278 A-1281 296 A-1333 Page 16 of24 F0 306-0 I R 2

(}Structural Integrity Associates, Inc. Table 2: Piping Loads for Calculation of Stresses (Node 165) Load Case FA (lb) FB (lb) FC (lb) MA (in-lb) MB (in-lb) MC (in-lb) Fsrss {lb) Msrss (in-lb) Deadweight 317 27 14 54 1314 3222 318 3480 Thermal1 474 78 12 108 2106 5616 481 5999 Thermal2 18 170 56 270 2160 5526 179 5939 Thermal3 414 104 21 90 2250 6012 427 6420 Thermal4 14 23 6 0 288 792 27 843 SAM DE 86 65 18 360 954 1728 109 2006 SAMDD 173 129 36 720 1890 3456 218 4004 SAMHS 62 38 12 216 630 1008 73 1208 Seismic DX 125 266 1023 13284 4122 1872 1064 14034 Seismic DZ 47 228 341 4230 1566 1242 412 4678 Seismic XD 209 452 1704 22140 6858 3222 1775 23401 Seismic ZD 80 407 576 7128 2664 2196 709 7920 Seismic HX 219 897 1296 16308 7326 5004 1591 18565 Seismic HZ 150 1020 665 6516 4752 5328 1227 9666 Notes: 1. The bounding thermal case is determined fi*om the largest square root of the sum of the squares of the moments and is shown in bold. 2. Only the bounding seismic direction is required to be evaluated.

For the DE, DD, and HS seismic loadings, the bounding loads from either the X or Z direction are used. These are shown in bold. 3. These piping loads are given in the local coordinate system. A is the axial direction, so FA is the axial force and MB and MC are the bending moments. 4. All loads are increased by a factor of 1.5 to account for any potential changes in the piping analyses.

File No.: 1501350.301 Revision:

0 Page 17 of24 F 0306-0 I R 2 SJ Structural Integrity Associates, Inc.'" Table 3: Load Combinations for Stress Calculations Load Combinations FA (lb) Service Level A Service Level B Service Level C Service Level D Service Level A Service Level B Service Level C Service Level D File No.: 1501350.301 Revision:

0 317 441 525 536 414 500 587 476 Load Combinations for Primary Loads FB (lb) FC (lb) MA (in-lb) MB (in-lb) MC (in-lb) 27 14 54 1314 3222 293 1037 13338 5436 5094 479 1718 22194 8172 6444 924 1310 16362 8640 8226 Load Combinations for Secondary Loads 104 21 90 2250 6012 168 39 450 3204 7740 233 57 810 4140 9468 141 33 306 2880 7020 Fms (lb) Mms (in-lb) 318 3480 1164 15277 1859 24513 1690 20249 427 6420 528 8389 633 10365 497 7594 Page 18 of24 F0306-0 I R2 e Structural Integrity Associates, Inc. Table 4: Primary Stresses Load Combinations Pressure (psi) Force (psi) Moment (psi) Service Level A 6462 57 672 Service Level B 6462 209 2952 S ervice Level C 6462 333 4737 Service Level D 6462 303 3913 Table 5: Secondary Stresses File No.: 15 013 5 0.301 Revision:

0 Load Combinations Service Level A Service Level B Service Level C Service Level D Force (psi) Moment (psi) 77 1241 95 1621 114 2003 89 1467 Gm (psi) Gb (psi) 6519 672 6670 2952 6795 4737 6765 3913 Ge (psi) 1317 1716 2117 1557 Page 19 of24 F0306-0 I R2

{J Structural Integrity Associates, Inc. Table 6: Transient Cycles and Groupings Transients Cycles for 50 years Spray Nozzle COF) Normal Heatup 1200 320 Cooldown (Case I) 1200 320 Cooldown (Case II) 200 405 Cooldown (Case II) 1000 320 Unit Loading 18300 125 Unit Unloading 18300 125 Large Step Decrease 250 128 Step Load Increase 2500 128 Step Load Decrease 2500 126 Boron Concentration Equalization 32000 125 Upset Loss ofLoad 7 100 143 Inadvertent Aux Spray 12 553 Bounding Event Cycles Total Events with 125°F 68600 Total Events with 320°F T 4 3500 Total Events with 128°F 5250 Inadvertent Aux Spray 12 Cooldown Case II 200 Number of Cycles for 1 Year (=Total cycles/50)

Total Events with 125°F 1372 Total Events with 320°F T 4 70 Total Events with l28°F 105 Inadvetient Aux Spray 2 0.24 Cooldown Case II 4 Number of Cycles for 1 Year (used in analysis)1 Total Events with l25°F T 5 2744 Total Events with 320°F T 4 140 Total Events with l28°F T 6 210 Inadvetient Aux Spray 2 Cooldown Case II 8 .. Notes: 1. The number of cycles used m the analysts IS doubled to account for a PWR water environment.

This is required as the stainless steel fatigue crack growth law is given in air. 2. The inadvetient auxiliary spray event has less than one cycle per year. Therefore, it is conservatively assumed that one cycle per year occurs. 3. All infonnation is obtained from Reference

10. 4. This event is referred to as heatup/cooldown (HU/CD) in the analysis files. 5. This event is referred to as unload or load in the analysis files. 6. This event is referred to as step load inc or dec in the analysis files. 7. The loss of load transient is included with the 320°F T events. File No.: 1501350.301 Revision:

0 Page 20 of24 F 0 3 06-0 1 R 2 e Structural Integrity Associates, Inc. Table 7: Transients Analyzed in SI-TIFFANY Transient Time (sec) Temperature eF) Pressure (psig) Flow Rate (gpm) Heatup/Cooldown 0 650 2510 800 L).T (°F) = 320 0.1 330 2510 800 60.1 330 2510 800 360.1 650 2510 800 960.1 650 2510 800 Cooldown II 0 650 2510 800 L).T (°F) = 405 0.1 245 2510 800 60.1 245 2510 800 360.1 650 2510 800 960.1 650 2510 800 Loading/Unloading 0 650 2510 800 L).T (°F) = 125 0.1 525 2510 800 60.1 525 2510 800 360.1 650 2510 800 960.1 650 2510 800 Step Load Inc/Dec 0 650 2510 800 L).T (°F) = 128 0.1 522 2510 800 60.1 522 2510 800 360.1 650 2510 800 960.1 650 2510 800 Inadvertent Aux 0 650 2510 800 1 Spray L).T (°F) = 553 0.1 97 2510 800 1 300.1 97 2510 800 1 600.1 650 2510 800 1 1200.1 650 2510 800 1 Notes: 1. The inadvetient aux spray transient actually occurs at 200 gpm [1 0]. 800 gpm is used here for conservatism.

2. For information on transient development, see Section 3.7. File No.: 1501350.301 Revision:

0 Page 21 of24 F030 6-0 IR 2 e Structural Integrity Associates, Inc. Table 8: Material Properties for A-376 TP 316 Material Prope1iy Units Spray Line Normal Operating Temperature op 650 Young's Modulus ksi 25050 Poisson's Ratio --0.3 Density lb/in 3 0.283 Specific Heat BTU/lb-°F 0.133 Coefficient of Thermal Expansion op-1 9.9 x w-6 Thermal Conductivity BTU/sec-in-°F 2.52 x Io-4 Note: 1. Material prope1iies are taken at a temperature of 650 op from Reference

[ 4]. Table 9: Fatigue Crack Growth Loadings Event Kmax Kmin Heatup/Cooldown HUCDmax, DW, Residual HUCDmin, DW, Residual Cooldown II CDIImax, DW, Residual CDIImin, DW, Residual Loading/Unloading Unloadm ax , DW, Residual Unloadmin, DW, Residual Step Load Inc/Dec SLIDma x , DW, Residual SLIDmin, DW, Residual Inadve1ient Aux IASma x , DW, Residual IASmin, DW, Residual Spray OBE Unloadmax, DW, Residual, 2*0BE Unloadmax, DW, Residual Table 10: Initial, Final, and Allowable Flaw Sizes Flaw Depth (in) Length (in) Initial 0.08 0.625 Final-Fixed 0.3258 2.545 Final-Variable 0.3276 1.553 Allowable 0.3278 4.241 Notes: 1. aft is the ratio of the flaw depth to the pipe wall thickness.

2. )/eire is the ratio of the flaw length to the pipe circumference.

File No.: 1501350.301 Revision:

0 a/t<I) l/circ<2) Years 0.18 0.044 N/A 0.75 0.180 75 0.75 0.110 81 0.75 0.300 N/A Page 22 of24 F0306-01 R2 SJ S tructural Integrity Associates, Inc.'" Figure 1. Isometric Drawing of the Spray Line L(!E , END. _____.£_

.. Pt'.>_, ,....------t

jl(E D ;

;,,; Note: Location of the flaw is circles in the picture. The node of interest is # 165. Dr a wing is from Reference

5. File No.: 1501350.301 Revision:

0 Page 23 of24 F0306-0 I R2 e Structural Integrity Associates, Inc. cr Figure 2. Semi-Elliptic Flaw on Inside Surface of a Cylinder File No.: 1501350.301 Revision:

0 Page 24 of24 F0306-0 I R2 e Structural Integrity Associates, Inc."' APPENDIX A NDE lSI EXAMINATION DATA File No.: 1501350.301 Revision:

0 Page A-I of A-3 F0306-0IR2 S} Structural Integrity Associates, Inc."' 69-21802 10/01/14 DlirnLOCANYONPOWERPLANT NDEPDI-UT-2 ATTACHMENTll.3 TITLE: Exam Data Sheet DCPPUnit:

1 Procedtu"e Revision 111 Outage: j1RI9 I *Line#: I ISO#: I WeldlD: S6-15-4 1.4-29 WIB-378 Component Configuration Diameter.

4" nominal Thickness Upsb*e am: T.,Nom.: 0.437" Thickness Centerline:

Config.: Pipe to Elbow Thiclmess Downstream:

Crown 0.8" Coun te rbore Width: Upstream:

Covemge: >99% (Note 3) Counterbore Downstream:

Scan Information SearcltUnit Upstream. Weld Downstream Scan Angle Mode Ax Circ. Ax Clrc. Ax Ciro. dB Nole 45° sw X X X X X X 35.5 I 60° sw X X X X X X 41.0 1&2 70° sw X X X 48.5 I Notes l Sketcll: I. Linear flaw, see attached indication sheet and plot. 2. Very low amplitude root geometry noted witlt the 60° D IT-50809162-001-00 Page 27 of28 Attachment 7, Page 1 of 2 Page 1 of! Page: I 6 I of I 10 0.413" 0.487" 0.470" None None Exam Indications Flaw flaw None Oeom Ace. Reject X X X 3. 70"limited on intrados of elbow for 4" circumferential dist11nce. 60" angle at the intrados did not cover a triangular area of 0.1" x 0.05" (0.0025 sqlin). Exam box area 3.1" x 0.15" = 0.465 sq/in. Exam Strut Time: 2340 Personnel Name Examiner:

Michael Leger Exnminer:

J amie I(l!pela Reviewer:

I r ANU: Cv'!)Y Gv!I\>A!:.1JDLI NDE_PDI-UT-2uJrll.DOC 18 0930.1259 File No.: 1501350.301 Revision:

0 I Exam Completion Time: 01 09 "Signature Level lu -.'-1:: ,_ III Tr. I/C//2SZ-.

iZ]:

1/ I Dale /o/stt/ L!i

_lo/ti.J/1>

\ Page A-2 of A-3 F0306-0 I R2 e Structural Integrity Associates, Inc. Weld # WIB-378 UneS6-15-4 4" Nominal Pipe Size 0.437" nominal thickness Indication Sizing Sketch 7ll*lipsgtJ

ll _ _ . I #1.o..ro* IDS!cit> '"* w '"'\§ r ODsutf

: 0:nded iu'" ;, mdkatloo a<ea fo<S;,;0 g 'I' Row '--... Pipe Indication Sound Distance to Iden tifi cation Path W!l!d r.s:o-n!er 1A 0.94" 0.85" 18 1.40" 1.35" 1C 1.09 1.10 Note: Indication ID 1A, 18, & 1C are different ultrasonic sound plots to the same Indication o.4&J o.4 S4 o.45'2 o.4M o.4o9 o.45 9 o.454 k!uli'Thld;mss 0.08" lrxfiCalion throu;,twJa!l "0" at eioow extrados Indication Length= 0.62S' (3-1/8" to 3-3/4") 10/0D ratio = 0.8 Length on 10 = O.S' Indication height= 0.08" Looking Downstream Indication

---*-------------------NDE exam report and indication sketch are from Reference 1 File No.: 1501350.301 Revision:

0 Page A-3 of A-3 F 0306-0 1R 2 e Structural Integrity Associates, Inc. APPENDIXB COMPUTER FILE LISTING File No.: 1501350.301 Revision:

0 Page B-1 ofB-3 F0306-0 I R2 SJ Structural Integrity Associates, Inc."' SI-TIFFANY Files **.dat SI-TIFF ANY input file ** .rpt SI-TIFF ANY output file, which echoes the inputs **.tnnn SI-TIFF ANY output file with tabulated Kmin values **.mxn SI-TIFF ANY output file with tabulated Kmax values **-HUCD-Heatup and Cooldown, CDII-Cooldown II, INAUX-Inadvertent Aux Spray, Loading/Unloading, SLID -Step Load Inc/Dec File No.: 1501350.301 Revision:

0 Page B-2 ofB-3 F0306-0 I R 2 e Structural Integrity Associates, Inc. pc-CRACK Files SLA.pcf SLB.pcf SLC.pcf SLD.pcf SLA.rpt SLB.rpt SLC.rpt SLD.rpt FCG-Fixed.pcf FCG-Fixed.rpt FCG-Fixed.kva FCG-Fixed.avn FCG-Variable.pcf FCG-Variable.rpt FCG-Variable.kva FCG-Variable.avn File No.: 1501350.301 Revision:

0 pc-CRACK input file for Service Level A EPFM evaluation pc-CRACI( input file for Service Level B EPFM evaluation pc-CRACK input file for Service Level C EPFM evaluation pc-CRACK input file for Service Level D EPFM evaluation pc-CRACK output file for Service Level A EPFM evaluation pc-CRACK output file for Service Level B EPFM evaluation pc-CRACK output file for Service Level C EPFM evaluation pc-CRACK output file for Service Level D EPFM evaluation pc-CRACK input file for fatigue crack growth for fixed aspect ratio pc-CRACK output file for fatigue crack growth for fixed aspect ratio pc-CRACK file including K vs A for fatigue crack growth with fixed aspect ratio pc-CRACK file including crack depth vs time for fatigue crack growth with fixed aspect ratio pc-CRACK input file for fatigue crack growth for variable aspect ratio pc-CRACK output file for fatigue crack growth for variable aspect ratio pc-CRACK file including K vs A for fatigue crack growth with variable aspect ratio pc-CRACK file including crack depth vs time for fatigue crack growth with variable aspect ratio Page B-3 of B-3 F0306-0 I R2 e Structural Integrity Associates, Inc. A PPENDIXC PC-CRACK OUTPUT FILES File No.: 1501350.301 Revision:

0 Page C-1 of C-1 73 F0.306-0 I R2 e Structural Integrity Associates, Inc. pc-CRACK 4.1 CS Version Control No. 4.1.0.0 Structural Integrity Associates, Inc. www.structint.com pccrack@structint.com Date: 10/09/2015 15:31 Service Level A Input Data read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\pcCRACK\SLA.pcf Analysis Title: DCPP Spray Units Selected:

US Customary Linear Dimensions

-inches Stress -ksi Load -kips Temperature

-deg F Time -hours Jic -in-lbs/inA2 Analysis Type: ASME Section XI IWB-3640 (2004) Crack Geometry Orientation:

Circumferential Crack Depth= 0.0800 Crack Length 0.6250 Pipe Geometry Nominal Pipe Size Outer Diameter Wall Thickness Service Level: A 4.0000 4.5000 0.4370 The allowable flaw size is determined using Formulae Stresses Pm Pb Pe 6.5190 (safety factor 0.6720 (safety factor 1.3170 K (Residual Stress) = 0.0000 Material:

Stainless Steel Flux weld Flow Stress 45.1500 Number of Warnings in Inputs: 0 Analysis Results File No.: 1501350.301 Revision:

0 2.7000) 2.3000) Page C-2 of C-173 F0306-0 I R2

{J Structural Integrity Associates, Inc. Failure Mode per Screening Criteria:EPFM (Class l screening rules used) Stress Ratio Z factor 1/circumference a/t allowable 1/Circumference Allowable 0.0000 0.7500 0.1000 0.7 500 0.2000 0.7500 0.3000 0.7500 0.4000 0.7500 0.5000 0.7500 0.6000 0.6934 0.7000 0.6642 0.8000 0.6535 Stress Ratio Z factor 1/circumference a/t a l lowable 1/Circumference Allowable 0.0000 0.7500 0.1000 0.7500 0.2000 0.7500 0.3000 0.7500 0.4000 0.6961 0.5000 0.5991 0.6000 0.5442 0.7000 0.5141 0.8000 0.4993 0.2235 1.3000 0.0442 0.7500(Combined Loading) a/t 0.5068 1.3000 0.0442 0.7500(Membrane Loading) a/t Note: Allowable crack size is calculated based on the failure mode indicated by the screening criteria which is based on the input crack size Number of Runtime Warn i ngs: 0 *** End of pc-CRACK output *** File No.: 1501350.301 Revision:

0 Page C-3 of C-173 F 0306-0 IR 2 e Structural Integrity Associates, Inc.* pc-CRACK 4.1 CS Version Control No. 4.1.0.0 Structural Integrity Associates, Inc. www.structint.com pccrack@structint.com Date: 10/09/2015 15:32 Service Level B Input Data read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\pcCRACK\SLB.pcf Analysis Title: DCPP Spray Units Selected:

US Customary Linear Dimensions

-inches Stress -ksi Load -kips Temperature

-deg F Time -hours Jic -in-lbs/inA2 Analysis Type: ASME Section XI IWB-3640 (2004) Crack Geometry Orientation:

Circumferential Crack Depth = 0.0800 Crack Length Pipe Geometry Nominal Pipe Size Outer Diameter Wall Thickness Service Level: B 0.6250 4.0000 4.5000 0.4370 The allowable flaw size is determined using Formulae Stresses Pm Pb 6.6700 (safety factor 2.9520 (safety factor Pe 1.7160 K (Residual Stress) = Material:

Stainless Steel Flux weld 0.0000 Flow Stress 45.1500 Number of Warnings in Inputs: 0 Analysis Results File No.: 1501350.301 Revision:

0 2.4000) 2.0000) Page C-4 of C-1 73 F0306-0I R2 e Structural Integrity Associates, Inc."' Failure Mode per Screening Criteria:EPFM (Class 1 screening rules used) Stress Ratio Z factor 1/circumference a/t allowable 1/Circumference Allowable 0.0000 0.7500 0.1000 0.7500 0.2000 0.7500 0.3000 0.7500 0.4000 0.7500 0.5000 0.6832 0.6000 0.6309 0.7000 0.6063 0.8000 0.5988 Stress Ratio Z factor 1/circumference a/t allowable 1/Circumference Allowable 0.0000 0.7500 0.1000 0.7500 0.2000 0.7500 0.3000 0.7500 0.4000 0.7500 0.5000 0.6540 0.6000 0.5944 0.7000 0.5617 0.8000 0.5457 0.3017 1.3000 0.0442 0.7500(Cornbined Loading) a/t 0.4609 1.3000 0.0442 0.7500(Mernbrane Loading) a/t Note: Allowable crack size is calculated based on the failure mode indicated by the screening criteria which is based on the input crack size Number of Runtime Warnings:

0 *** End of pc-CRACK output *** File No.: 1501350.301 Revision:

0 Page C-5 of C-173 F030 6-0\Rl e Structural Integrity Associates, Inc. pc-CRACK 4.1 CS Version Control No. 4.1.0.0 Structural Integrity Associates, Inc. www.structint.com pccrack@structint.com Date: 10/09/2015 15:33 Service Level C Input Data read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\pcCRACK\SLC.pcf Analysis Title: DCPP Spray Units Selected:

US Customary Linear Dimensions

-inches Stress -ksi Load -kips Temperature

-deg F Time -hours Jic -in-lbs/inA2 Analysis Type: ASME Section XI IWB-3640 (2004) Crack Geometry Orientation:

Circumferential Crack Depth= 0.0800 Crack Length 0.6250 Pipe Geometry Nominal Pip e Size Outer Diameter Wall Thickness Service Level: C 4.0000 4.5000 0.4 3 70 The allowable flaw size is determined using Formulae Stresses Pm 6.7950 (safety factor Pb 4.7370 (saf e ty factor Pe 2.1170 K (Residual Stress) = 0.0000 Material:

Stainless Steel Flu x weld Flow Stress 45.1500 Number of Warnings in Inputs: 0 Analysis Results File No.: 1501350.301 Revision:

0 1.8000) 1.6000) Page C-6 of C-1 73 F0 306-0 I R2 e Structural Integrity Associates, Inc. Failure Mode per Screening Criteria:EPFM (Class 1 screening rules used) Stress Ratio Z factor 1/circumference a/t allowable 1/Circumference Allowable 0.0000 0.7500 0.1000 0.7500 0.2000 0.7500 0.3000 0.7500 0.4000 0.7500 0.5000 0.6967 0.6000 0.6429 0.7000 0.6172 0.8000 0.6089 Stress Ratio Z factor 1/circumference a/t allowable 1/Circumference Allowable 0.0000 0.7500 0.1000 0.7500 0.2000 0.7500 0.3000 0.7500 0.4000 0.7500 0.5000 0.7500 0.6000 0.7128 0.7000 0.6742 0.8000 0.6555 0.3701 1.3000 0.0442 0.7500(Cornbined Loading) a/t 0.3522 1.3000 0.0442 0.7500(Mernbrane Loading) a/t Note: Allowable crack size is calculated based on the failure mode indicated by the screening criteria which is based on the input crack size Number of Runtime Warnings:

0 *** End of pc-CRACK output *** File No.: 1501350.301 Revision:

0 Page C-7 ofC-173 F0306-0I R2 e Structural Integrity Associates, Inc. pc-CRACK 4.1 CS Version Control No. 4.1.0.0 Structural Integrity Associates, Inc. www.structint.com pccrack@structint.com Date: 10/09/2015 15:34 Service Level D Input Data read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\pcCRACK\SLD.pcf Analysis Title: DCPP Spray Units Selected:

US Customary Linear Dimensions

-inches Stress -ksi Load -kips Temperature

-deg F Time -hours Jic -in-lbs/inA2 Analysis Type: ASME Section XI IWB-3640 (2004) Crack Geometry Orientation:

Circumferential Crack Depth = 0.0800 Crack Length 0.6250 Pipe Geometry Nominal Pipe Size Outer Diameter Wall Thickness Service Level: D 4.0000 4.5000 0.4370 The allowable flaw size is determined using Formulae Stresses Pm 6.7650 (safety factor Pb 3.91 30 (safety factor Pe 1.5570 K (Residual Stress) = 0.0000 Material:

Stainless Steel Flux weld Flow Stress 45.1500 Number of Warnings in Inputs: 0 Analysis Results File No.: 1501350.301 Revision:

0 1.3000) 1.4000) Page C-8 of C-1 73 F0306-0 I R2 e Structural Integrity Associates, Inc."' Failure Mode per Screening Criteria:EPFM (Class 1 screening rules used) Stress Ratio Z factor 1/circumference a/t allowable 1/Circumference Allowable 0.0000 0.7500 0.1000 0.7500 0.2000 0.7500 0.3000 0.7500 0.4000 0.7500 0.5000 0.7500 0.6000 0.7377 0.7000 0.7048 0.8000 0.6915 Stress Ratio Z factor 1/circumference a/t allowable 1/Circumference Allowable 0.0000 0.7500 0.1000 0.7500 0.2000 0.7500 0.3000 0.7500 0.4000 0.7500 0.5000 0.7500 0.6000 0.7500 0.7000 0.7500 0.8000 0.7500 .0.3395 1.3000 0.0442 0.7500(Cornbined Loading) a/t 0.2532 1.3000 0.0442 0.7500(Mernbrane Loading) a/t Note: Allowable crack size is calculated based on the failure mode indicated by the screening criteria which is based on the input crack size Number of Runtime Warnings:

0 *** End of pc-CRACK output *** File No.: 1501350.301 Revision:

0 Page C-9 of C-173 F030 6-01R2 e Structural Integrity Associates, Inc.'" Fatigue Crack Growth-Fixed Aspect Ratio pc-CRACK 4.1 CS Version Control No. 4.1.0.0 Structural Integrity Associates, Inc. www.structint.com pccrack@structint.com Date: 10/29/2015 10:55 Input Data read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\pcCRACK\FCG-Fixed.pcf Analysis Title: DCPP Spray Line Units Selected:

US Customary Linear Dimensions

-inches Stress -ksi Load -kips Temperature

-deg F Time -hours Analysis Type: Crack Growth (LEFM) Crack Growth Calculation Method -Crack Stepping Crack Model: 306-Semi-Elliptical Circumferential Crack in Cylinder on the Inside Surface (API 579) Crack Depth, a= 0.0800 Half Crack Length, c 0.3125 Wall Thickness, t = 0.4370 Inside Radius, Ri = 1.8130 Aspect ratio fixed Maximum a/t = 0.75 Crack Depth Print Increment for SIF Tabulation 0.01 Total Load Cases: 13 Load Case 1:HU/CD Max 2-d SIF Input by User The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\HUCD.MXN No. of aspect ratios (a/c) in the tables = 8 a/c = 0.1250 Crack Depth Kdeepest Ksurface 4.370E-03 10.4510 3.9032 0.0437 26.8310 11.8060 0.0656 29.5570 14.0540 0.0874 30.7780 15.7380 0.1093 32. 0710 17.4750 0.1311 32.75 2 0 19.0020 0.1530 32. 9650 2 0.3650 0.1748 32.8050 21.5940 0.1967 32.7170 22.8730 0.2185 32.3480 24.0670 0.2404 31.7350 25.1860 0.2622 30.9160 26.2380 0.2841 29.7890 27.7710 0.3059 28.2260 29.2630 0.3278 2 6.2690 30.7150 0.3496 23.9630 32.1260 a/c = 0.1667 Crack Depth Kdeepest Ksurface File No.: 1501350.301 Revision:

0 Page C-1 0 of C-173 F03 0 6-0 I R2 e Structural Integrity Associates, Inc. 4.370E-03 10.2590 4.5078 0.0437 26.2190 13.5920 0.0656 28.8130 16.1640 0.0874 29.9340 18.0900 0.1093 30.9780 20.1180 0.1311 31.3940 21.9160 0.1530 31.3250 23.5370 0.174 8 30.8710 25.0150 0.1967 30.5010 26.4860 0.2185 29.8620 2 7.84 70 0.2404 28.9970 29.1100 0.2622 27.9440 30.2830 0.284 1 26.7090 31.8800 0.3059 25.126 0 33.4090 0.32 78 23.2340 34.8710 0.3496 21.07 50 36.2690 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 10.0940 4. 9720 0.0437 25.7010 14.9640 0.0656 28.1890 17.7850 0.0874 29.2300 19.8970 0.1093 30.0790 22.1480 0.1311 30.2870 24.1550 0.1530 30.0010 25.9760 0.1748 29.3190 27.6450 0.1967 28.7290 29.2660 0.2185 27.8830 30.7570 0.2404 26.8240 32 .1310 0. 2 622 25.5900 33.3990 0.2841 24.2720 3 5.0450 0.3059 22.6760 36.6020 0.3278 20.8370 38.0720 0.3496 18.7960 39.4580 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 9.8321 5.6352 0.0437 24.8910 16.9230 0.0656 2 7.2 190 20.1000 0.0874 28.1420 22.4770 0.1093 28.7070 25.0490 0.1311 28.6150 2 7.3560 0.1530 28.0140 29.4610 0.1748 2 7.0060 3 1.4060 0.1967 26.1010 33.2410 0.2185 24.9580 34.9190 0.2404 23.6 2 10 36.4540 0. 2622 22.1 290 3 7.8580 0.2841 20.6920 39.5 750 0.3059 19.0780 41.1720 0.3278 17.3 190 42.6510 0.3496 15.4500 44.0180 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 9.4074 6.1941 0.0437 23.6990 18.5910 0.0656 25.8360 22.0860 0.0874 26.6190 24.7140 0.1093 26.9910 2 7.4090 0.1311 26.7330 2 9.7930 0.1530 25.9910 31.9370 0.1748 24.8 640 33.8890 FileNo.: 1501350.301 Page C-11 ofC-173 Revision:

0 F0306-0I R2 e Structural Integrity Associates, Inc."' 0.1967 23.7690 35.8250 0.2185 22.4550 37.5950 0.2404 20.9690 39.2140 0.2622 19.3490 40.6950 0.2841 17.7170 42.1800 0.3059 15.9420 43.5360 0.3278 14.0550 44.7680 0.3496 12.0880 45.8850 ale = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 8.5324 7.1113 0.0437 21.2790 21.3290 0.0656 23.0480 25.3480 0.0874 23.5740 28.3890 0.1093 23.6000 31.2740 0.1311 23.0510 33.7670 0.1530 22.0680 35.9560 0.1748 20.7490 37.9000 0.1967 19.3320 39.9930 0.2185 17.7370 41.9050 0.2404 16.0090 43.6540 0.2622 14.1880 45.2550 0.2841 12.2420 46.3080 0.3059 10.2180 47.2180 0.3278 8.1538 47.9960 0.3496 6.5215 48.6530 .. ale = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 7.3428 7.3615 0.0437 18.0280 21.9460 0.0656 19.3480 25.9910 0.0874 19.5900 29.0030 0.1093 19.5280 31.8580 0.1311 18.9900 34.3100 0.1530 18.0990 36.4540 0.1748 16.9350 38.3530 0.1967 15.4390 40.2090 0.2185 13.7840 41.8890 0.2404 12.0140 43.4150 0. 2 622 10.1680 44.8030 0.2841 8.2553 45.9590 0.3059 6.3129 46.9930 0.3278 5.1927 47.9160 0.3496 5.5896 48.7370 ale = 1.0000 Crack Depth Kdeepest Ksurface 4.370E-03 6.3496 7.4789 0.0437 15.3380 22.1970 0.0656 16.3000 26.2200 0.0874 16.3230 29.1800 0.1093 16.1940 31.9830 0.1311 15.6720 34.3790 0.1530 14.8600 36.4670 0.1748 13.8290 38.3130 0.1967 12.2920 39.9680 0.2185 10.6140 41.4520 0.2404 8.8402 42.7910 0.2622 7.0094 44.0030 0.2841 5.1774 45.2280 0.3059 4.1674 46.3490 0.3278 4.4973 47.3760 0.3496 4.8250 48.3170 File No.: 1501350.301 Page C-12 of C-173 Revision:

0 F0306-0 I R2 e Structural Integrity Associates, Inc. Load Case 2:HU/CD Min 2-d SIF Input by User The SIF originally read from C:\Users\clohse\Docurnents\ANSYS\PGE\1501350\TIFFANY\HUCD.MNN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-03 0 .1714 0.0437 0.8047 0.0656 1.1531 0.0874 1. 5159 0.1093 1.9355 0.1311 2.3815 0.1530 2.8518 0.1748 3.3440 0.1967 3.8949 0.2185 4. 4723 0.2404 5.0743 0.2622 5.6988 0.2841 6. 5727 0.3059 7.4985 0.3278 8. 4 722 0.3496 9.4884 ale= 0.1667 Crack Depth Kdeepest 4.370E-03 0.1684 0.0437 0.7895 0.0656 1.1299 0.0874 1.4831 0.1093 1.8909 0.1311 2.3240 0.1530 2.7803 0.1748 3.2575 0.1967 3.7827 0.2185 4.3308 0.2404 4.8999 0. 2 622 5.4880 0.2841 6.2723 0.3059 7.0977 0.3278 7.9603 0.3496 8.8555 a/c = 0.2000 Crack Depth Kdeepest 4.370E-03 0.1657 0.0437 0.7765 0.0656 1.1100 0.0874 1. 4553 0.1093 1. 8532 0.1311 2.2756 0.1530 2.7203 0.1748 3.1850 0.1967 3.6893 0.2185 4. 2137 0.2404 4.7563 0.2622 5.3150 0.2841 6.0281 0.3059 6.7738 0.3278 7.5485 0.3496 8.3479 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 0.0594 0.1993 0.2538 0.3058 0.3579 0.4106 0.4646 0.5202 0.5767 0.6353 0.6961 0.7593 0.8424 0.9303 1. 0233 1.1213 Ksurface 0.0688 0.2347 0.3011 0.3649 0.4310 0.4983 0.5675 0.6388 0. 7183 0.8022 0.8904 0.9833 1.1020 1.2285 1. 3627 1. 504 7 Ksurface 0.0760 0. 2620 0.3375 0.4104 0.4873 0.5659 0.6467 0.7302 0.8275 0.9308 1.0403 1.1560 1. 3022 1.4584 1. 6244 1.8003 Page C-13 ofC-173 F030 6-0J R2 lJ Struc/ural/nlegrity Associates, Inc. ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 0.1615 0.0863 0.0437 0.7558 0.3009 0.0656 1.07 8 7 0.3896 0.0874 1. 4116 0.4756 0.1093 1. 7 943 0.5680 0.1311 2.2002 0.6627 0.1530 2. 6270 0.7603 0.1748 3. 0726 0.8612 0.1967 3.5454 0.9841 0.2185 4.0342 1.1154 0.2404 4.5369 1.2553 0.2622 5.0516 1.4039 0.2841 5.6599 1.5897 0.3059 6.2881 1. 7885 0.3278 6.9332 2.0002 0.3496 7. 5913 2.2247 a/c = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 0.1547 0.0951 0.0437 0. 7257 0.3358 0.0656 1.0364 0. 4371 0.0874 1. 3567 0.5360 0.1093 1.7209 0.6410 0.1311 2.1057 0.7488 0.1530 2.5088 0.8600 0.1748 2.9280 0.9749 0.1967 3.3674 1.1147 0.2185 3.8194 1.2636 0.2404 4.2818 1. 4217 0. 2 622 4.7526 1.5890 0.2841 5.2981 1.7808 0.3059 5.8575 1.9843 0.3278 6.4277 2.1992 0.3496 7.0035 2.4253 a/c = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 0.1406 0.1094 0.0437 0.6628 0.3935 0.0656 0.9479 0.5161 0.0874 1.2419 0.6367 0.1093 1.5684 0. 7629 0.1311 1.9107 0. 8926 0.1530 2.2664 1.0 265 0.1748 2.6333 1.1650 0.1967 3.0077 1.333 1 0.2185 3.3881 1. 5113 0.2404 3. 7725 1. 6996 0.2622 4.1589 1. 8981 0.2841 4.5847 2.0983 0.3059 5.0127 2.3073 0.3278 5.4362 2.5 249 0.3496 5.1316 2.7510 a/c = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 0.1215 0.1134 0.0437 0.5788 0.4087 0.0656 0.8295 0.5366 0.0874 1.0877 0.6628 0.1093 1.3757 0.7927 File No.: 1501350.301 Page C-14 ofC-173 Revision:

0 F0306-01R2 e Structural Integrity Associates, Inc. 0.1311 1. 6771 0.1530 1.9896 0.1748 2. 3112 0.1967 2.6356 0.2185 2.9639 0.2404 3.2941 0. 2 622 3.6241 0.2841 3.9792 0.3059 3.7631 0.3278 2.9125 0.3496 1.6720 a/c = 1.0000 Crack Depth Kdeepest 4.3 7 0E-03 0.1055 0.0437 0.5080 0.0656 0.7296 0.0874 0.9576 0.1093 1.2129 0.1311 1. 4795 0.1530 1. 7554 0.1748 2.0387 0.1967 2. 3211 0.2185 2.6056 0.2404 2.8902 0. 2622 2.9045 0.2841 2.2874 0.3059 1. 4158 0.3278 0.2709 0.3496 -1.1900 Load Case 3:CD II Max 2-d SIF Input by User 0.9252 1. 0611 1.2008 1. 3592 1. 5246 1. 6968 1.8760 2.0636 2.2584 2.4601 2.6686 Ksurface 0.1153 0.4162 0.5470 0.6 7 61 0.8075 0.9408 1.0769 1.2160 1.3653 1. 5190 1.67 7 0 1.8394 2.0154 2.1971 2.3843 2. 5771 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\CDII.MXN No. of aspect ratios (a/c) ale= 0.1250 Crack Depth Kdeepest 4.370E-03 12.7140 0.0437 32.6970 0.0656 35.9930 0.0874 37.4290 0.1093 38.9310 0.1311 39.6700 0.1530 39.8220 0.1748 39.5090 0.1967 39.2660 0.2185 38.6680 0.2404 37.7630 0.2622 36.5970 0.2841 34.9880 0.3059 32.8280 0.3278 30.1680 0.3496 27.0670 ale = 0.1667 Crack Depth Kdeepest 4.370E-03 12.4810 0.0437 31.9510 0.0656 35.0860 0.0874 36.4010 0.1093 37.6000 0.1311 38.0150 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 4.7459 14.3690 17.1130 19.1700 21.2930 23.1600 24.8260 26.3270 27.8900 29.3490 30.7150 31.9990 33.8670 35.6840 37.4520 39.1690 Ksurface 5.4811 16.5440 19.6840 22.0360 24.5130 26.7100 Page C-15 of C-173 F0 3 0 6-0l R2 l} Structural integrity Associates, Inc. 0 .1530* 37.8260 28.6890 0.1748 37.1530 30.4930 0.1967 36.5690 32.2880 0.2185 35.6470 33.9480 0.2404 34.4400 35.4850 0.2622 32.9940 36.9110 0.2841 31.27 40 38.8510 0.3059 29.1150 40.7050 0.3278 26.5640 42.4760 0.3496 23.6740 44.1650 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 12.2810 6.0457 0.0437 31.3190 18.2150 0.0656. 34.3250 21.6580 0.0874 35.5430 24.2380 0.1093 36.5050 26.9860 0.1311 36.6680 29.4380 0.1530 36.2130 31.6590 0.1748 35.2640 33.6950 0.1967 34.4150 35. 6710 0.2185 33.2430 37.4860 0.2404 31.8030 39.1560 0.2622 30.1430 40.6930 0.2841 28.3380 42.6880 0.3059 26.1820 44.5700 0.3278 23.7190 46.3430 0.3496 20.9970 48.0100 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 11.9620 6.8520 0.0437 30.3330 20.6000 0. 0656 33.1440 24.4770 0.0874 34.2190 27.3820 0.1093 34.8350 30.5200 0.1311 34.6330 33.3360 0.1530 33.7950 35.9040 0.1748 32.4480 38.2750 0.1967 31.2190 40.5090 0.2185 29.6900 42.5480 0.2404 27.9180 44.4090 0.2622 25.9510 46.1060 0.2841 24.0260 48.1790 0.3059 21.8770 50.1010 0.3278 19.5450 51.8740 0.3496 17.0720 53.5060 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 11.4450 7.5318 0.0437 28.8800 22.6330 0.0656 31.4580 26.8990 0.0874 32.3630 30.1080 0.1093 32.7450 33.3980 0.1311 32.3430 36.3060 0.1530 31.3370 38.9200 0.1748 29.8510 41.2980 0.1967 28.3950 43.6520 0.2185 26.6650 45.8000 0.2404 24.7190 47.7600 0. 2 622 22.6050 49.5470 0.2841 20.4560 51.3330 0.3059 18.1260 52.9570 File No.: 1501350.301 Page C-16 of C-173 Revision:

0 F0306-0IR2 lJ Structural Integrity Associates, Inc. 0.3278 15.6540 0.3496 13.0810 a/c = 0.5000 Crack Depth Kdeepest 4.370E-03 10.3810 0.0437 25.9290 0.0656 28.0600 0.0874 28.6530 0.1093 28.6170 0.1311 27.8660 0.1530 26.5750 0.1748 24.8640 0.1967 23.0280 0.2185 20.9680 0.2404 18.7430 0. 2 622 16.4020 0.2841 13.8960 0.3059 11.2920 0.3278 8.6359 0.3496 6.5215 a/c = 0.7500 Crack Depth Kdeepest 4.370E-03 8.9337 0.0437 21.9670 0.0656 23.5500 0.0874 23.8000 0.1093 23.6620 0.1311 22.9330 0.1530 21.7630 0.1748 20.2530 0.1967 18.3310 0.2185 16.2110 0.2404 13.9480 0.2622 11.5890 0.2841 9.1408 0.3059 6.6539 0.3278 5.1983 0.3496 5.6320 ale = 1.0000 Crack Depth Kdeepest 4.370E-03 7. 7256 0.0437 18.6870 0.0656 19.8350 0.0874 19.8200 0.1093 19.6060 0.1311 18.9030 0.1530 17.8380 0.1748 16.5010 0.1967 14.5380 0.2185 12.4010 0.2404 10.1430 0. 2 622 7.8145 0.2841 5.4789 0.3059 4.1760 0.3278 4.5406 0.3496 4.9028 Load Case 4:CD II Min 2-d SIF Input by User The SIF originally read File No.: 1501350.301 Revision:

0 from 54.4260 55.7480 Ksurface 8. 64 72 25.9670 30.8750 34.5880 38.1090 41.1480 43.8150 46.1800 48.7200 51.0350 53.1470 55.0740 56.3270 57.4000 58.3090 59.0650 Ksurface 8.9515 26.7200 31.6580 35.3370 38.8210 41.8100 44.4210 46.7 300 48.9810 51.0130 52.8540 54.5230 55.9050 5 7.1330 58.223 0 59.1840 Ksurface 9.0943 27.0270 31.9390 35.5540 38.9 7 30 41.8940 44.4360 46.6790 48.6850 50.4790 52.0920 53.5480 55.0170 56.3550 57.5750 58.6880 C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\CDII.MNN Page C-17 of C-173 F0306-0 I R2 e Slruclurallnlegrily Associates, Inc. No. of aspect ratios (a/c) in the tables 8 ale = 0.1250 Crack Depth Kdeepest Ksurface 4.370E-03 0.0222 4.244E-03 0.0437 0.3938 0.0303 0.0656 0.6885 0.0512 0.0874 1.0215 0. 0772 0.1093 1. 4110 0.1033 0.1311 1.8373 0.1331 0.1530 2.2957 0.1666 0.1748 2.7826 0.2038 0.1967 3.3270 0.2419 0.2185 3.9025 0.2836 0.2404 4.5067 0.3288 0. 2 622 5.1370 0.3775 0.2841 6.0192 0.4389 0.3059 6.9599 0.5059 0.3278 7.9539 0.5786 0.3496 8.9950 0.6571 ale = 0.1667 Crack Depth Kdeepest Ksurface 4.370E-03 0.0218 5.058E-03 0.0437 0.3879 0.0395 0.0656 0.6767 0. 0 67 0 0.0874 1.0020 0.1007 0.1093 1.3839 0.1358 0.1311 1. 8017 0.1754 0.1530 2.2510 0.2194 0.1748 2.7280 0.2678 0.1967 3.2515 0.3248 0.2185 3.8026 0.3878 0.2404 4.3785 0.4569 0.2622 4.9766 0.5320 0.2841 5.7719 0. 6266 0.3059 6. 6134 0.7301 0.3278 7.4964 0.8425 0.3496 8.4152 0.9638 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 0.0216 5.686E-03 0.0437 0.3826 0.0467 0.0656 0.6665 0.0792 0.0874 0.9852 0.1188 0.1093 1.3605 0.1609 0.1311 1.7711 0.2080 0.1530 2.2126 0.2602 0.1748 2. 6811 0.3172 0.1967 3.1876 0.3887 0.2 185 3.7187 0.4682 0.2404 4. 2715 0.5557 0. 2 622 4.8436 0.6512 0.2841 5.5699 0. 7714 0.3059 6.3327 0.9030 0.3278 7.1277 1.0460 0.3496 7.9495 1.2002 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03

0. 0211 6.584E-03 0.0437 0.3741 0.0569 0.0656 0.6501 0. 0967 File No.: 1501350.301 Page C-18 ofC-173 Revision:

0 F0306-0IR2 e Struc/urallnlegrily Associates, Inc.'" 0.0874 0.9587 0.1449 0.1093 1.3236 0.1969 0.1311 1. 7228 0.2550 0.1530 2.1519 0.3188 0.1748 2.6070 0.3882 0.1967 3.0876 0.4806 0.2185 3.5884 0.5838 0.2404 4.1066 0.6978 0.2622 4.6393 0.8224 0.2841 5.2637 0.9794 0.3059 5.9103 1.1513 0.3278 6.5755 1.3382 0.3496 7.2543 1. 5397 a/c = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 0.0203 7.392E-03 0.0437 0.3619 0.0671 0.0656 0.6291 0.1144 0.0874 0.9277 0.1712 0.1093 1.2775 0.2334 0.1311 1. 6587 0.3027 0.1530 2.0668 0.3789 0.1748 2.4979 0.4616 0.1967 2.9488 0.5687 0.2185 3.4159 0.6873 0.2404 3.8966 0.8174 0.2622 4.3880 0.9589 0.2841 4.9533 1.1248 0.3059 5.5343 1.3044 0.3278 6.1268 1.4974 0.3496 6.7245 1. 7038 a/c = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 0.0187 8.739E-03 0.0437 0.3357 0.0844 0.0656 0.5836 0.1445 0.0874 0.8607 0.2159 0.1093 1.1793 0.2954 0.1311 1. 5235 0.3839 0.1530 1. 8890 0.4810 0.1748 2.2719 0.5865 0.1967 2.6638 0. 7182 0.2185 3.0649 0. 8 62 7 0.2404 3.4725 1.0198 0.2622 3.8834 1.1894 0.2841 4.3352 1. 368 9 0.3059 4.7894 1.5596 0.3278 5.2374 1. 7 611 0.3496 4.8097 1.9731 a/c = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 0.0165 9.139E-03 0.0437 0.3007 0.0903 0.0656 0.5224 0.1549 0.0874 0.7693 0.2319 0.1093 1. 0520 0.3153 0.1311 1. 3562 0. 4071 0.1530 1.6781 0.5069 0.1748 2.0141 0.6142 0.1967 2.3581 0.7399 0.2185 2.7091 0.8753 0.2404 3.0639 1. 0200 File No.: 1501350.301 Page C-19 ofC-173 Revision:

0 F030 6-0I R2 Structural Integrity Associates, Inc. 0. 2622 0.2841 0.3059 0.3278 0.3496 a/c = Crack Depth 4.370E-03 0.0437 0.0656 0.0874 0.1093 0.1311 0.1530 0.1748 0.1967 0.2185 0.2404 0.2622 0.2841 0.3059 0.3278 0.3496 3.4195 3.8004 3.5065 2.3892 0.7737 1.0000 Kdeepest 0.0147 0.2706 0.4698 0.6909 0.9429 1. 2131 1.4979 1. 7942 2.0976 2.4060 2. 7160 2. 7269 1. 9188 0.7885 -0.6909 -2.5753 Load Case 5:Unload Max 2-d SIF Input by User 1.1738 1.3397 1. 514 7 1.6986 1. 8911 Ksurface 9.353E-03 0.0939 0.1614 0.2419 0.3274 0.4208 0.5216 0.6291 0.7489 0.8758 1.0094 1.1493 1.3030 1. 4641 1.6324 1. 8077 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\UNLD.MXN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-03 4.5828 0.0437 12.0180 0.0656 13.4190 0.0874 14.1820 0.1093 15. 0110 0.1311 15.5920 0.1530 15.9850 0.1748 16.2300 0.1967 16.5440 0.2185 16.7510 0.2404 16.8690 0. 2622 16.9120 0.2841 16.9790 0.3059 16.8920 0.3278 16.6650 0.3496 16.3180 a/c = 0.1667 Crack Depth Kdeepest 4.370E-03 4.4990 0.0437 11.7460 0.0656 13.0850 0.0874 13.7990 0.1093 14.5130 0.1311 14.9710 0.1530 15.2340 0.1748 15.3430 0.1967 15.5180 0.2185 15.5910 0.2404 15.5790 0.2622 15.4980 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 1.7085 5.1801 6.1774 6.9317 7.7071 8.3929 9.0089 9.5682 10.1480 10.6920 11.2040 11. 6900 12.3930 13.0810 13.7550 14.4150 Ksurface 1.9733 5.9679 7.1119 7.9780 8.8877 9.7001 10.4380 11.1150 11.7930 12.4270 13.0200 13.5780 Page C-20 of C-173 F030 6-01 R2 SJ Structural Integrity Associates, Inc."' 0.2841 15.4620 14.3340 0.3059 15.3030 15.0640 0.3278 15.0360 15.7710 0.3496 14.6760 16.4540 a/c = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 4.4266 2.1766 0.0437 11.5160 6.5730 0.0656 12.8050 7.8297 0.0874 13.4790 8.7818 0.1093 14.1030 9.7950 0.1311 14.4650 10.7050 0.1530 14.6260 11.5360 0.1748 14.6290 12.3040 0.1967 14.6960 13.0590 0.2 185 14.6650 13.7620 0.2404 14.5530 14.4190

0. 2622 14.3750 15.0330 0.2841 14.2590 15.8290 0.3059 14.0440 16.5920 0.3278 13.7440 17.3230 0.3496 13.3740 18.0240 a/c = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03

4. 3118 2. 4 67 0 0.0437 11.1560 7.4371 0.0656 12.3690 8.8550 0.0874 12.9850 9.9301 0.1093 13.4760 11.0910 0.1311 13. 6980 12.1410 0.1530 13.7130 13.1060 0.1748 13.5620 14.0050 0.1967 13.4730 14.8700 0.2185 13.2910 15.6740 0.2404 13.0340 16.4210 0.2622 12.7180 17.1170 0.2841 12.4840 17.9700 0.3059 12.1880 18.7790 0.3278 11.8410 19.5460 0.3496 11.4580 20.2720 a/c = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-:-03 4.1257 2.7118 0.0437 10.6260 8.1738 0.0656 11.7490 9.7367 0.0874 12.2960 10.9270 0.1093 12.6930 12.1510 0.1311 12.8300 13.2420 0.1530 12.7680 14.2 330 0.1748 12.5490 15.1440 0.1967 12.3570 16.0650 0.2 185 12.0790 16.9200 0.2 404 11.7320 17.7150 0.2 622 11.3330 18.4580 0.2841 10.9760 19.2170 0.3059 10.5680 19.9270 0.3278 10.1200 20.5920 0.3496 9.6453 21.2130 ale = 0.5000 Crack Depth Kdeepest Ksurface File No.: 1501350.301 Page C-21 of C-173 Revision:

0 F0 3 0 6-0l R2 e Structural Integrity Associates, Inc. 4.370E-03 3.7421 0.0437 9.5479 0.0656 10.4970 0.0874 10.9160 0.1093 11.1390 0.1311 11.1240 0.1530 10.9280 0.1748 10.5930 0.1967 10.2210 0.2185 9.7759 0.2404 9.2758 0. 2622 8. 7372 0.2841 8.1707 0.3059 7.5742 0.3278 6.9626 0.3496 6.5215 a/c = 0.7500 Crack Depth Kdeepest 4.370E-03 3.2207 0.0437 8.1012 0.0656 8.8345 0.0874 9.1085 0.1093 9.2680 0.1311 9.2303 0.1530 9.0456 0.1748 8.7486 0.1967 8.3106 0.2185 7.8064 0.2404 7.2539 0.2622 6.6687 0.2841 6.0729 0.3059 5.4651 0.3278 5.1798 0.3496 5.4923 ale = 1.0000 Crack Depth Kdeepest 4.370E-03 2.7854 0.0437 6.9029 0.0656 7.4631 0.0874 7.6230 0.1093 7.7325 0.1311 7.6786 0.1530 7.5046 0.1748 7.2401 0.1967 6.7572 0.2185 6.2153 0.2404 5.6318 0. 2 622 5.0232 0.2841 4.4249 0.3059 4.1478 0.3278 4.3980 0.3496 4.6465 Load Case 6:Unload Min 2-d SIF Input by User 3.1136 9.3831 11.1850 12.5680 13.8860 15.0390 16.0650 16.9890 17.9970 18.9330 19.8060 20.6210 21.2030 21.7290 22.2030 22.6290 Ksurface 3.2232 9.6574 11.4740 12.8480 14.1570 15.2940 16.3020 17.2070 18.1070 18.9360 19.7030 20.4150 21.0320 21.6020 22.1270 22.6130 Ksurface 3.2746 9.7700 11.57 90 12.9330 14.2200 15.3350 16.3190 17.2010 18.0090 18.7460 19.4240 20.0500 20.6890 21.2860 2 1.8470 22.3740 L The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\UNLD.MNN No. of aspect ratios (a/c) in the tables = 8 ale= 0.1250 Crack Depth Kdeepest 4.370E-03 0.5123 File No.: 1501350.301 Revision:

0 Ksurface 0.1855 Page C-22 of C-173 F0306-0 I R2 e Structural Integrity Associates, Inc. 0.0437 1. 7438 0.5852 0.0656 2.2156 0. 7166 0.0874 2. 6471 0.8279 0.1093 3 .13 60 0.9394 0.1311 3.6276 1.0445 0.1530 4.1249 1.1452 0.1748 4.6293 1.2429 0.1967 5.1954 1.3412 0.2185 5.7770 1.4383 0.2404 6.3738 1.5347 0.2622 6.9854 1. 6307 0.2841 7.8412 1.7631 0.3059 8.7341 1.8987 0.3278 9.6619 2.0377 0.3496 10.6220 2.1801 ale = 0.1667 Crack Depth Kdeepest Ksurface 4.370E-03 0.5030 0.2145 0.0437 1.7076 0.6806 0.0656 2.1662 0.8359 0.0874 2.5840 0.9685 0.1093 3.0515 1.1054 0.1311 3.5200 1. 2360 0.1530 3.9923 1. 3625 0.1748 4.4699 1. 4863 0.1967 4.9989 1. 6173 0.2185 5.5403 1.7486 0.2404 6.0940 1.8806 0.2622 6.6595 2.0138 0.2841 7.4193 2.1876 0.3059 8.2086 2.3665 0.3278 9.0255 2.5505 0.3496 9. 8 67 8 2.7397 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 0.4950 0.2367 0.0437 1. 67 67 0.7538 0.0656 2.1243 0.9276 0.0874 2.5308 1.0767 0.1093 2.9810 1.2332 0.1311 3.4306 1.3834 0.1530 3.8827 1.5298 0.1748 4.3388 1.6737 0.1967 4.8379 1.8299 0.2185 5.3472 1.9876 0.2404 5.8663 2.1472 0.2622 6.3950 2.3091 0.2841 7.0789 2.5149 0.3059 7.7862 2. 7272 0.3278 8.5153 2.9460 0.3496 9.2642 3.1713 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 0.4823 0.2685 0.0437 1.6282 0.8585 0.0656 2.0589 1. 058 6 0.0874 2.4479 1.2313 0.1093 2. 8719 1.4159 0.1311 3.2932 1.5943 0.1530 3.7149 1.7692 0.1748 4.1386 1.9420 0.1967 4.5935 2.1346 File No.: 1501350.301 Page C-23 of C-1 73 Revision:

0 F030 6-0 I R2 e Structural Integrity Associates, Inc. 0.2185 5.0549 2.3303 0.2404 5.5227 2.5295 0.2622 5.9966 2.7327 0.2841 6.5688 2.9845 0.3059 7.1554 3.2447 0.3278 7.7552 3.5135 0.3496 8.3668 3.7906 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 0.4617 0.2954 0.0437 1. 5571 0.9495 0.0656 1.9679 1.1742 0.0874 2.3385 1.3694 0.1093 2.7360 1.5724 0.1311 3.1291 1. 7 680 0.1530 3.5207 1. 9593 0.1748 3.9127 2.1479 0.1967 4.3261 2. 362 6 0.2185 4.7433 2.5807 0.2404 5.1642 2.8028 0.2622 5.5886 3.0291 0.2841 6.0894 3.2807 0.3059 6.6002 3.5389 0.3278 7 .1197 3.8038 0.3496 7.6461 4.0755 ale = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 0.4191 0.3395 0.0437 1. 4107 1.0996 0.0656 1. 7810 1.3651 0.0874 2 .1142 1.5982 0.1093 2.4594 1. 8312 0.1311 2.7972 2.0550 0.1530 3.1305 2.2730 0.1748 3.4609 2.4873 0.1967 3.7952 2.7387 0.2185 4.1283 2.9940 0.2404 4.4603 3.2539 0. 2 622 4.7909 3.5186 0.2841 5.1581 3.7664 0.3059 5. 52 67 4.0177 0.3278 5.8943 4. 2725 0.3496 5.9705 4.5310 ale = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 0.3613 0.3516 0.0437 1.2145 1.1361 0.0656 1.5318 1.4088 0.0874 1. 8163 1.6473 0.1093 2.1170 1.8835 0.1311 2.4117 2.1091 0.1530 2.7028 2.3278 0.1748 2.9916 2.5417 0.1967 3. 2710 2.7749 0.2185 3.5478 3.0089 0.2404 3.8222 3.2443 0.2622 4.0939 3.4817 0.2841 4.3907 3.7193 0.3059 4.4556 3.9595 0.3278 4.2761 4.2022 0.3496 3.9452 4.4478 File No.: 1501350.301 Page C-24 of C-173 Revision:

0 F0306-0 I R2 .

Structural Integrity Associates, Inc. ale = 1.0000 Crack Depth Kdeepest 4.370E-03 0.3130 0.0437 1.0506 0.0656 1. 3238 0.0874 1.5679 0.1093 1. 8311 0.1311 2.0894 0.1530 2.3450 0.1748 2.5987 0.1967 2.8328 0.2185 3.0634 0.2404 3.2904 0.2622 3.4015 0.2841 3.2795 0 .. 3059 3.0569 0.3278 2. 7272 0.3496 2.2743 Load Case 7:IAS Max 2-d SIF Input by User Ksurface 0.3573 1.152 6 1.4280 1. 668 4 1.9045 2.1292 2.3461 2.5575 2.7743 2.9894 3.2036 3.4174 3.6447 3.8737 4.1047 4.3377 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\INAUX.MXN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-03 15.2760 0.0437 39.8790 0.0656 44.0560 0.0874 45.8970 0.1093 47.7650 0.1311 48.6540 0.1530 48.7860 0.1748 48.3150 0.1967 47.9010 0.2185 47.0250 0.2404 45.7510 0.2622 44.1360 0.2841 41.8980 0.3059 38.9510 0.3278 35.3580 0.3496 31.1950 a/c = 0.1667 Crack Depth Kdeepest 4.370E-03 14.9970 0.0437 38.9710 0.0656 42.9480 0.0874 44.6370 0.1093 46.1330 0.1311 46.6220 0.1530 46.3300 0.1748 45.4150 0.1967 44.5790 0.2185 43.3060 0.2404 41. 6610 0.2622 39.7050 0.2841 37.3500 0.3059 34.4270 0.3278 30.9990 0.3496 27 .1320 a/c = 0.2000 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 5.68 7 5 17.2900 20.6390 23.1720 25.7840 28.0900 30.1530 32.0170 33.9550 35.7660 37.4630 39.05 7 0 41.3660 43. 6110 45.7950 47.9150 Ksurface 6.5691 19.9180 23.7560 26.6550 29.7040 32.4170 34.86 7 0 37.1030 39.3340 41.3980 43.3100 45.0830 47.4830 49.7740 51.9600 54.0420 Page C-25 of C-173 F0306-01 R2

(;Structural Integrity Associates, Inc. Crack Depth Kdeepest Ksurface 4.370E-03 14.7560 7.2461 0.0437 38.2030 21.9370 0.0656 42.0180 26.1480 0.0874 43.5860 29.3300 0.1093 44.7890 32.7150 0.1311 44.9670 35.7410 0.1530 44.3470 38.4900 0.1748 43.0880 41.0120 0.1967 41.9260 43.4690 0.2185 40.3460 45.7290 0.2404 38.4160 47.8070 0.2622 36.1990 49.7180 0.2841 33.7540 52.1880 0.3059 30.8550 54.5140 0.3278 27.5590 56.7000 0.3496 23.9280 58.7500 a/c = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 14.3730 8. 2130 0.0437 37.0030 24.8190 0.0656 40.5750 29.5660 0.0874 41.9640 33.1510 0.1093 42.7400 37.0150 0.1311 42.4660 40.4910 0.1530 41.3730 43.6660 0.1748 39.6210 46.6010 0.1967 37.9900 49.3820 0.2185 35.9690 51.9210 0.2404 33.6330 54.2380 0. 2 622 31.0430 56.3490 0.2841 28.4730 58.9170 0.3059 25.6130 61.2900 0.3278 22.5150 63.4740 0.3496 19.2330 65.4740 a/c = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 13.7530 9.0284 0.0437 35.2350 27.2800 0.0656 38.5150 32.5080 0.0874 39.6910 36.4720 0.1093 40.1760 40.5320 0.1311 39.6530 44.1290 0.1530 38.3510 47.3680 0.1748 36.4280 50.3180 0.1967 34.5200 53.2 470 0.2185 32.2570 55.9190 0.2404 29.7110 58.3560 0. 2 622 26.9470 60.5750 0.2841 24 .1130 62.7870 0.3059 21.0440 64.7910 0.3278 17.7900 66.5960 0.3496 14.4030 68.2120 ale = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 12.4750 10.3660 0.0437 31.6430 31.3180 0.0656 34.3630 37.3400 0.0874 35.1450 41.9310 0.1093 35.1080 46.2880 0.1311 34.1530 50.0600 File No.: 1501350.301 Page C-26 of C-173 Revision:

0 F0306-0J R2 e Structural Integrity Associates, Inc. 0.1530 32.4990 0.1748 30.3000 0.1967 27.9290 0.2185 25.2670 0.2404 22.3890 0. 2 622 19.3590 0.2841 16.1060 0.3059 12.7240 0.3278 9.2694 0.3496 6.5215 a/c = 0.7500 Crack Depth Kdeepest 4.370E-03 10.7370 0.0437 26.8200 0.0656 28.8510 0.0874 29.1970 0.1093 29.0250 0.1311 28.0920 0.1530 26.5870 0.1748 24.6430 0.1967 22.1720 0.2185 19.4430 0.2404 16.5270 0.2622 13.4840 0.2841 10.3160 0.3059 7.0906 0.3278 5.2080 0.3496 5.7058 a/c = 1.0000 Crack Depth Kdeepest 4.370E-03 9.2864 0.0437 22.8270 0.0656 24.3070 0.0874 24.3160 0.1093 24.0430 0.1311 23.1390 0.1530 21.7 670 0.1748 20.0390 0.1967 17.5230 0.2185 14.7790 0.2404 11.8760 0. 2622 8.8788 0.2841 5.8584 0.3059 4.1909 0.3278 4.6159 0.3496 5.0381 Load Case 8:IAS Min 2-d SIF Input by User 53.3760 56.3200 59.4770 62.3540 64.9740 67.3600 68.9130 70.2350 71.3440 72.2570 Ksurface 10.7310 32.2340 38.3010 42.8570 47.1710 50.8820 54.1300 57.0050 59.8050 62.3310 64.6140 66.6820 68.3900 69.9020 71.2350 72.4030 Ksurface 10.9030 32.6100 38.6490 43.1320 47.3690 50.9970 54.1600 56.9520 59.4490 61. 6800 63.6820 65.4850 67.2970 68.9440 70.4380 71.7940 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\INAUX.MNN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-0 3 -0.2444 0.0437 -0.3412 0.0656 -0.1435 0.0874 0.1357 0.1093 0.4708 0.1311 0.8610 0.1530 1. 2979 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface -0.0943 -0.2715 -0.3108 -0.3311 -0.3513 -0.3623 -0.3653 Page C-27 of C-173 F030 6-0 IR2 e Structural Integrity Associates, Inc. 0.1748 1.7747 -0.3610 0.1967 2.3066 -0.3554 0.2185 2.8784 -0.3436 0.2404 3.4863 -0.3260 0.2622 4.1265 -0.3027 0.2841 5.0222 -0.2796 0.3059 5.9880 -0.2497 0.3278 7.0173 -0.2128 0.3496 8.1021 -0.1688 ale = 0.1667 Crack Depth Kdeepest Ksurface 4.370E-03

-0.2399 -0.1088 0.0437 -0.3307 -0.3091 0.0656 -0.1347 -0.3513 0.0874 0.1399 -0.3715 0.1093 0.4748 -0.3916 0.1311 0.8647 -0.4015 0.1530 1.3010 -0.4023 0.1748 1. 7771 -0.3949 0.1967 2. 2972 -0.3780 0.2185 2.8530 -0.3520 0.2404 3.4408 -0.3171 0. 2 622 4.0564 -0.2734 0.2841 4.8701 -0.2217 0.3059 5.7392 -0.1592 0.3278 6.6578 -0.0856 0.3496 7.6179 -1.203E-03 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03

-0.2360 -0.1200 0.0437 -0.3221 -0.3380 0.0656 -0.1277 -0.3823 0.0874 0.1430 -0.4024 0.1093 0.4772 -0.4225 0.1311 0.8662 -0.4314 0.1530 1.3015 -0.4305 0.1748 1.7761 -0.4208 0.1967 2.2862 -0.3953 0.2185 2.8287 -0.3583 0.2404 3.3998 -0.3100 0.2622 3.9950 -0.2506 0.2841 4.7436 -0.1770 0.3059 5.5359 -0.0894 0.3278 6.3666 0.0123 0. 3496 7.22 77 0.1278 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03

-0.2298 -0.1359 0.0437 -0.3087 -0.3792 0.0656 -0.1173 -0.4266 0.0874 0.1471 -0.4463 0.1093 0.4795 -0.4664 0.1311 0.8664 -0.4739 0.1530 1.2991 -0.4706 0.1748 1. 77 07 -0.4575 0.1967 2.2649 -0.4196 0.2185 2.7870 -0.3669 0.2404 3.3323 -0.2994 0. 2622 3.8966 -0.2175 0.2841 4.5486 -0.1123 0.3059 5.2276 0. 0115 0.3278 5.9282 0.1536 File No.: 1501350.301 Page C-28 of C-173 Revision:

0 F0306-0 I R2 e Structural Integrity Associates, Inc. 0.3496 6.6431 0.3138 a/c = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03

-0.2197 -0.1492 0.0437 -0.2888 -0.4129 0.0656 -0.1003 -0.4622 0.0874 0.1588 -0.4808 0.1093 0.4824 -0.4953 0.1311 0.8569 -0.4948 0.1530 1.2735 -0.4813 0.1748 1.7254 -0.4562 0.1967 2.1962 -0.4078 0.2185 2.6904 -0.3435 0.2404 3.2034 -0.2636 0.2622 3.7307 -0.1684 0.2841 4.3305 -0.0493 0.3059 4.9496 0. 0872 0.3278 5.5815 0.2410 0.3496 6.2177 0. 4116 a/c = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03

-0.1991 -0.1712 0.0437 -0.2498 -0.4678 0. 0656 -0.0687 -0.5197 0.0874 0.1775 -0.5363 0.1093 0.4813 -0.5406 0.1311 0.8288 -0.5258 0.1530 1.2114 -0.4945 0.1748 1. 6224 -0.4485 0.1967 2.0454 -0.3820 0.2185 2.4835 -0.2980 0.2404 2.9318 -0.1970 0. 2 622 3.3861 -0.0795 0.2841 3.8838 0.0626 0.3059 4.3843 0.2202 0.3278 4.8756 0.3926 0.3496 4.4750 0.5791 ale = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03

-0.1710 -0.1771 0.0437 -0.1969 -0.4787 0.0656 -0.0275 -0.5273 0.0874 0.1987 -0.5384 0.1093 0.4713 -0.5383 0.1311 0.7805 -0.5194 0.1530 1.1187 -0.4844 0.1748 1.4800 -0.4353 0.1967 1.8591 -0.3682 0.2185 2.2502 -0.2867 0.2404 2.6485 -0.1916 0.2622 3.0497 -0.0835 0.2841 3.4761 0.0432 0.3059 3.2815 0.1827 0.3278 1.8430 0.3344 0.3496 -0.3031 0.4977 a/c = 1.0000 Crack Depth Kdeepest Ksurface 4.370E-03

-0.1476 -0.1799 0.0437 -0.1541 -0.4821 0.0656 4.512E-03

-0.5278 File No.: 1501350.301 Page C-29 of C-173 Revision:

0 F03 0 6-01R2 e Structural Integrity Associates, Inc. 0.0874 0.2129 0.1093 0.4585 0.1311 0.7349 0.1530 1. 0354 0.1748 1.3545 0.1967 1.6957 0.2185 2.0460 0.2404 2.4010 0. 2 622 2.5997 0.2841 1.5904 0.3059 0.1449 0.3278 -1.7967 0.3496 -4.3229 Load Case 9:Residual Type: Stress Coefficient Coefficient Coefficient Coefficient Coefficients Input co C1 C2 C3 30.0000 0.0000 0.0000 0.0000 Load Case 10:0BE -0.5345 -0.5311 -0.5091 -0.4717 -0.4209 -0.3540 -0.2754 -0.1858 -0.0863 0. 0271 0 .1511 0.2852 0.4289 by User Type: Stress Coefficients Input by User Coefficient CO Coefficient C1 Coefficient C2 Coefficient C3 Load Case 11:DW 3.3100 0.0000 0.0000 0.0000 Type: Stress Coefficients Input by User Coefficient CO Coefficient C1 Coefficient C2 Coefficient C3 Load Case 12:SLID Max 2-d SIF Input by User 0.7290 0.0000 0.0000 0.0000 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\SLID.MXN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-03 4.6760 0.0437 12.2520 0.0656 13.6730 0.0874 14.4430 0.1093 15.2790 0.1311 15.8610 0.1530 16.2510 0.1748 16.4900 0.1967 16.7970 0.2185 1 6.9950 0.2404 17.1020 0.2622 17.1310 0.2841 17.1790 0.3059 17.0690 0.3278 16.8160 0.3496 16.4370 a/c = 0.1667 Crack Depth Kdeepest File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 1. 7434 5.2852 6.3022 7.0711 7.8616 8.5606 9.1883 9.7581 10.3480 10.9030 11.4250 11.9190 12.6350 13.3360 14.0220 14.6940 Ksurface Page C-30 of C-173 F0306-01R2 e Structural Integrity Associates, Inc. 4.370E-03 4.5904 2. 0135 0.0437 11.9740 6.0889 0.0656 13.3330 7.2553 0.0874 14.0530 8.1380 0.1093 14.7720 9.0653 0.1311 15.2290 9.8931 0.1530 15.4870 10.6440 0.1748 15.5870 11.3340 0.1967 15.7530 12.0250 0.2185 15.8150 12.6700 0.2404 15.7900 13.2740 0.2622 15.6930 13.8410 0.2841 15.6380 14.6100 0.3059 15.4570 15.3530 0.3278 15.1640 16.0710 0.3496 14.7760 16.7660 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 4.5166 2.2210 0.0437 11.7390 6.7060 0.0656 13.0470 7.9874 0.0874 13.7270 8.9577 0.1093 14.3540 9.9902 0.1311 14.7130 10.9170 0.1530 14.8670 11.7640 0.1748 14.8590 12.5460 0.1967 14.9160 13.3150 0.2185 14.8720 14.0300 0.2404 14.7450 14.6980 0.2622 14.5510 15.3220 0.2841 14.4160 16.1310 0.3059 14.1790 16.9070 0.3278 13.8550 17.6500 0.3496 13.4590 18.3620 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 4.3994 2.5173 0.0437 11.3720 7.5875 0.0656 12.6030 9.0331 0.0874 13.2230 10.1290 0.1093 13.7150 11.3120 0.1311 13.9320 12.3810 0.1530 13.9370 13.3650 0.1748 13.7730 14.2790 0.1967 13.6710 15.1600 0.2185 13.4740 15.9770 0.2404 13.2000 16.7360 0.2622 12.8650 17.4430 0.2841 12.6130 18.3100 0.3059 12.2960 19.1320 0.3278 11.9270 19.9100 0.3496 11.5210 20.6450 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 4.2095 2. 7 672 0.0437 10.8320 8.3390 0.0656 11. 9710 9.9322 0.0874 12.5210 11.1450 0.1093 12.9170 12.3920 0.1311 13.0480 13.5030 0.1530 12.9750 14.5120 0.1748 12.7420 15.4400 File No.: 1501350.301 Page C-31 of C-173 Revision:

0 F0306-01R2 e Structuralfnlegrity Associates, Inc. 0.1967 12.5360 16.3760 0.2185 12.2410 17.2450 0.2404 11.8760 18.0540 0. 2 622 11.4580 18.8080 0.2841 11.0820 19.5780 0.3059 10.6520 20.2990 0.3278 10.1820 20.9720 0.3496 9.6836 21.6010 ale = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 3.8181 3.1771 0.0437 9.7328 9.5724 0.0656 10.6940 11.4090 0.0874 11.1150 12.8180 0.1093 11.3350 14.1610 0.1311 11.3110 15.3350 0.1530 11.1030 16.3790 0.1748 10.7520 17.3190 0.1967 10.3640 18.3430 0.2185 9.9006 19.2950 0.2404 9.3812 20.1810 0.2622 8.8225 21.0090 0.2841 8.2344 21.5980 0.3059 7.6156 22.1290 0.3278 6.9812 22.6080 0.3496 6.5215 23.0390 ale = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 3.2861 3.2889 0.0437 8.2576 9.8521 0.0656 8.9998 11.7040 0.0874 9.2731 13.1030 0.1093 9.4290 14.4360 0.1311 9.3833 15.5940 0.1530 9.1875 16.6200 0.1748 8.8769 17.5410 0.1967 8.4222 18.4560 0.2185 7.9000 19.2980 0.2404 7.3284 20.0760 0.2 622 6. 7235 20.7990 0.2841 6.1071 21.4250 0.3059 5.4784 22.0010 0.3278 5.1800 22.5320 0.3496 5.4938 23.0230 ale = 1.0000 Crack Depth Kdeepest Ksurface 4.370E-03 2.8420 3.3414 0.0437 7.0357 9. 9669 0.0656 7.6020 11.8110 0.0874 7.7596 13.1900 0.1093 7.8652 14.5010 0.1311 7.8040 15.6350 0.1530 7.6199 16.6360 0.1748 7.3434 17.5330 0.1967 6.8439 18.3550 0.2185 6.2842 19.1040 0.2404 5.6820 19.7920 0. 2 622 5.0543 20.4260 0.2841 4.4367 21.0750 0.3059 4.1481 21.6810 0.3278 4.3995 2 2.2480 0.3496 4.6493 2 2.7820 FileNo.: 1501350.301 Page C-32 of C-173 Revision:

0 F 0306-01 R2 S} Structural Integrity Associates, Inc."' Load Case 13:SLID Min 2-d SIF Input by User The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\SLID.MNN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-03 0.5070 0.0437 1. 7294 0.0656 2.1993 0.0874 2. 62 97 0.1093 3.1175 0.1311 3.6085 0.1530 4.1054 0.1748 4.6096 0.1967 5.1754 0.2185 5.7569 0.2404 6.3539 0. 2 622 6.9657 0.2841 7.8217 0.3059 8.7150 0.3278 9.6436 0.3496 10.6050 ale = 0.1667 Crack Depth Kdeepest 4.370E-03 0.4979 0.0437 1. 6935 0.0656 2.1503 0.0874 2. 5671 0.1093 3.0337 0.1311 3.5016 0.1530 3.9737 0.1 7 48 4.4513 0.1967 4.9802 0.2185 5.5217 0.2404 6.0756 0.2622 6.6415 0.2841 7.4017 0.3059 8.19 1 5 0.3278 9.0091 0.3496 9.8522 a/c = 0.2 000 Crack Depth Kdeepest 4.370E-03 0.4900 0.0437 1.6629 0.0656 2.1088 0.0874 2.5142 0.1093 2.9637 0.1311 3.4129 0.1530 3.8648 0.1748 4.3210 0.1967 4.8203 0.2185 5. 32 98 0.2404 5.8493 0.26 2 2 6.3784 0.2841 7.0628 0.3059 7.7706 0.3278 8.5004 0.3496 9.2501 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 0.1836 0.5793 0.7095 0.8199 0.9304 1.034 7 1.1348 1.2318 1.3295 1.4260 1. 5218 1. 6173 1.7489 1.8839 2.0222 2.1639 Ksurface 0.2122 0.6737 0.8277 0.9593 1.0951 1.224 7 1. 3503 1.4733 1. 6035 1.7340 1. 8654 1.9980 2.1709 2.3490 2.5323 2. 7208 Ksurface 0.2343 0.7463 0.9185 1. 0664 1. 2217 1.3709 1. 5162 1. 6592 1.8145 1.9714 2.1302 2.2914 2.4963 2.7077 2.9257 3.1502 Page C-33 of C-173 F030 6-0l R2 lJ Structural Integrity Associates, Inc. ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 0.4774 0.2657 0.0437 1.6148 0.8499 0.0656 2.0438 1.0483 0.0874 2.4320 1.2197 0.1093 2.8554 1.4029 0.1311 3.2764 1.5800 0.1530 3.6982 1.7 537 0.1748 4.1223 1. 9254 0.1967 4.5774 2.1169 0.2185 5.0392 2. 3116 0.2404 5.5075 2.5100 0. 2 622 5.9821 2.7123 0.2841 6.5548 2.9630 0.3059 7.1420 3.2224 0.3278 7.7426 3.4902 0.3496 8.3548 3.7665 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 0.4570 0.2923 0.0437 1.5443 0.9401 0.0656 1. 9536 1.1629 0.08 7 4 2.3234 1.3566 0.1093 2. 7204 1.558 1 0.1311 3.1133 1. 7524 0.1530 3.5052 1. 9424 0.1748 3.8976 2.1299 0.1967 4. 3114 2.3434 0.2185 4.7291 2.5605 0.2404 5.1506 2.7816 0.2622 5.5 7 57 3.0070 0.2841 6. 0772 3.2576 0.3059 6.5888 3.5150 0.3278 7.1091 3.7792 0.3496 7. 6362 4.0501 ale = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 0.4148 0.3359 0.0437 i. 3992 1.0887 0.0656 1.7682 1.3521 0.0874 2.1008 1. 5834 0.1093 2.4458 1. 8148 0.1311 2.7836 2. 0371 0.1530 3.1172 2.2538 0.1748 3.4482 2.4670 0.1967 3.7831 2.7171 0.2185 4 .1170 2. 9712 0.2404 4.4497 3.2300 0.2622 4.7811 3.4937 0.2841 5.1492 3.7408 0.3059 5.5187 3.9914 0.3278 5.8872 4.2457 0.3496 5. 9572 4.5037 ale = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 0.3576 0.3479 0.0437 1.2047 1.1249 0.0656 1.5210 1. 3954 0.0874 1.8051 1. 6322 0.1093 2.1056 1. 8 667 FileNo.: 1501350.301 Page C-34 of C-173 Revision:

0 F0306-0JR2 e Structural Integrity Associates, Inc."' 0.1311 2.4004 2.0909 0.1530 2.6918 2.3083 0.1748 2.9811 2. 5211 0.1967 3.2612 2.7531 0.2185 3.5389 2.9861 0.2404 3.8141 3.2206 0.2622 4. 08 67 3.4570 0.2841 4.3843 3.6939 0.3059 4.4445 3.9333 0.3278 4.2545 4.1755 0.3496 3.9093 4.4204 a/c = 1.0000 Crack Depth Kdeepest Ksurface 4.370E-03 0.3098 0.3535 0.0437 1.0423 1.1413 0.0656 1.3147 1.4144 0.0874 1. 5585 1. 6531 0.1093 1.8216 1.8877 0.1311-----*2 0801 2*.1109 0.1530 2.3359 2.3266 0.1748 2.5901 2.5369 0.1967 2.8249 2.7526 0.2185 3.0563 2.9668 0.2404 3.2842 3.1801 0. 2622 3.3935 3.3932 0.2841 3.2636 3.6197 0.3059 3.0308 3.8480 0.3278 2.6884 4.0782 0.3496 2.2199 4.3106 Total Load Sub-Blocks:

6 Load Sub-Block

1. 1 Load Sub-block Name: Heatup/Cooldown Maximum Load Case Multiplier 1.0000 1.0000 1.0000 Minimum Load Case Multiplier 1.0000 1.0000 1.0000 Load Case ID HU/CD Max Residual ow Load Case ID HU/CD Min Residual DW Growth Law: ASMEAusteniticAir Cycles/Time:

140 Temperature:

650 Load Sub-Block

1. 2 Load Sub-block Name: Cooldown II Maximum Load Case Multiplier Load Case 1.0000 CD II Max 1.0000 Residual 1.0000 DW Minimum Load Case Multiplier Load Case 1.0000 CD II Min 1.0000 Residual 1.0000 ow Growth Law: ASMEAusteniticAir Cycles/Time:

8 Temperature:

650 File No.: 1501350.301 Revision:

0 ID ID Page C-35 of C-173 F0306-01 R2

(;Structural Integrity Associates, Inc.'" Load Sub-Block

1. 3 Load Sub-block Name: Inadvertent Aux Spray Maximum Load Case Multiplier 1.0000 1.0000 1.0000 Minimum Load Case Multiplier 1.0000 1.0000 1.0000 Load Case ID IAS Max Residual ow Load Case ID IAS Min Residual ow Growth Law: ASMEAusteniticAir Cycles/Time:

2 Temperature:

650 Load Sub-Block

1. 4 Load Sub-block Name: Unload Maximum L oad Case Multiplier 1.0000 1.0000 1.0000 Minimum Load Case Multiplier 1.0000 1.0000 1.0000 Load Case ID Unload Max Residual ow Load Case ID Unload Min Residual ow Growth Law: ASMEAusteniticAir Cycles/Time:

2744 Temperature:

650 Load Sub-Block

1. 5 Load Sub-block Name: OBE Maximum Load Case Multiplier 2.0000 1.0000 1.0000 Minimum Load Case Multiplier 0.0000 1.0000 1.0000 Load Case ID OBE Unload Max ow Load Case ID OBE Unload Max ow Growth Law: ASMEAusteniticAir Cycles/Time:

1 6 Temperature:

650 Load Sub-Block

1. 6 Load Sub-block Name: Step Load Inc/Dec Maximum Load Case Multiplier

1. 0000 1.0000 1.0000 Minimum Load Case Multiplier

1. 0000 1.0000 1.0000 Load Case ID SLID Max ow Residual Load Case ID SLID Min ow Residual Growth Law: ASMEAusteniticAir Cycles/Time:

210 Temperature:

650 File No.: 1501350.301 Revision:

0 Page C-36 of C-173 F0306-0JR2 lJ Structural Integrity Associates, Inc."' Material:

1 Sample Material 1: Only a sample *************

Austenitic Stainless Steel in Air environment (U.S. Customary Units) The Fatigue Crack Growth Rate (in/cycle) is g i ven by: da/dN = Co*(Delta K)An where Delta K = Kmax -Kmin n =the slope of the l og (da/dN) versus log (Delta K) 3.3 Co = a scaling constant Co C*S C is given by: T is the metal temperature in deg F S is a scaling parameter to account for R ratio and is given by: s 1.0 1.0 + 1.8

• R -43.35 + 57.97

• R where R = Kmin I Kmax for R <= 0 for 0 < R <= 0.7 9 for 0.79 < R < 1 No. of Data in the KIC Tab l e = 3 Crack Depth 0.0000 0.1000 2.0000 messages/Warnings:

KIC 500.0000 500.0000 500.0000 Number of Warnings in Inputs: 0 ----------ANALYSIS RESULTS ---------STRESS INTENSITY FACTORS Load Case # 1: HU/CD ------------

Crack a c 0.0800 0.3125 0.0900 0.3516 0.1000 0.3906 0.1100 0.4297 0.1200 0.4688 0.1300 0. 5078 File No.: 1501350.301 Revision:

0 Max Dimensions a/t 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 ------------c/a 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 K at tip a 27.7227 28.0975 28.3497 28.5794 28.5318 28.4842 Page C-3 7 of C-173 F0306-0 !R2 e Structural Integrity Associates, Inc.'" 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.23 00 0.24 00 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1. 0156 1.0547 1. 0938 1.132 8 1.1719 1.2109 1.2500 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0. 6865 0.7094 0.7323 Load Case # 2: HU/CD Min a 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 Crack Dimensions c a/t 0.3125 0.1831 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0. 6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1.0156 1. 054 7 1. 0938 1.1328 1.1719 1.2109 1.2500 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 Load Case # 3: CD II Max a 0.0800 0.0900 0.1000 0 .1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.17 00 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 Crack Dimensions c a/t 0.3125 0.1831 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.742 2 0.7813 0.8203 0.8594 0.8984 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4 577 0.4805 0.5034 0.5263 File No.: 1501350.301 Revision:

0 3.9063 3.9063 3.9063 3. 9063 3.9063 3.90 63 3.9063 3.9063 3.9063 3.9063 3.90 63 3.9063 3.9063 3.9063 3.9063 3.9063 3.906 3 3.9063 3.9063 c/a 3.9063 3.9063 3.90 63 3.9063 3.9063 3.9063 3.9063 3.9063. 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.90 63 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 c/a 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.90 63 3.9063 3.90 63 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 28.2300 27.9503 27.5397 27.0745 26.63 25 26.2120 25.7553 25.2265 24.6845 24.0677 23.4509 22.7663 22.079 2 21.4100 20.7459 20.0343 19.2903 18.5195 17.7102 K at tip a 1.2952 1.4530 1. 6275 1.8029 1.9879 2.1730 2.3665 2. 5611 2.7 616 2.9647 3.1741 3.3894 3. 6071 3.8296 4.0530 4.2817 4.5105 4.7444 4.9785 5.2455 5.5218 5.8035 6.0887 6.3770 6.6698 K at tip a 33.7249 34.1561 34.4303 34.6765 34.5774 34.4784 34.1 212 33.7321 33.1795 32.55 84 31.9639 31.3939 30.7782 30.0718 29.3488 28.5321 Page C-38 ofC-173 F0306-0 lR2 e Structural Integrity Associates, Inc. 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.9375 0.9766 1. 0156 1. 054 7 1. 0938 1.1328 1.1719 1.2109 1.2500 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 Load Case # 4: CD II Min a 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 Crack Dimensions c a/t 0.3125 0.1831 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1. 0156 1.0547 1.0938 1.1328 1.1719 1. 2109 1.2500 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 Load Case # 5: Unload Max a 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 Crack Dimensions c a/t 0.3125 0.1831 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1.0156 1.0547 1.0938 1.1328 1.1719 1.2109 1.2500 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0.4119 0.4348 0.4577 0.4805 0.5034 0. 52 63 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 File No.: 1501350.301 Revision:

0 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3: 9063 c/a 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 c/a 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 27.7153 26.8133 25.9082 25.0162 24.1277 23.1792 22.1897 21.1664 20.0945 K at tip a 0.8522 0.9997 1.1662 1.3339 1.5160 1. 6981 1. 8923 2.0880 2.2920 2.4995 2. 7130 2.9320 3.1540 3.3821 3. 6113 3.8472 4.0832 4.3254 4.5678 4.8425 5.1263 5.4160 5.7098 6.0070 6.3090 K at tip a 12.7283 12.9928 13.2144 13.4268 13.5256 13.6244 13.6391 13.6434 13.5944 13.5230 13.4658 13.4217 13.3634 13.2769 13.1853 13.0647 12.9441 12.7977 12.6503 12.5312 12.4200 12.2922 12.1530 12.0044 11.8423 Page C-39 of C-173 F030 6-0 I R2 e Structural Integrity Associates, Inc. Load Case # 6: Unload Min a 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 Crack Dimensions c a/t 0.3125 0.1831 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0. 7813 0.8203 0.8594 0.8984 0.9375 0.9766 1.0156 1. 054 7 1.0938 1.132 8 1.1719 1.2109 1.2500 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 Load Case # 7: IAS Max a 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 Crack Dimensions c a/t 0.3125 0.1831 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1.0156 1.0547 1.0938 1.132 8 1.1719 1.2109 1.2500 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 52 63 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 Load Case # 8: IAS Min c/a 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 c/a 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 ------------

Crack Dimensions

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a c a/t c/a 0.0800 0.3125 0.1831 3.9063 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 File No.: 1501350.301 Revision:

0 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 K at tip a 2.3087 2.4902 2.6834 2. 87 65 3.0683 3.2602 3.4522 3.6442 3.8368 4.0297 4.2298 4.4366 4.6444 4.8541 5.0643 5. 27 68 5.4893 5.7045 5.9198 6.1695 6.4290 6.6924 6.9583 7.2267 7.4986 K at tip a 41.3345 41.8895 42.2350 42.5446 42.4110 42.2774 41.8113 41.3041 40.5853 39.7778 38.9973 38.2416 37.4266 36.4937 35.5393 34.4632 33.3871 32.2001 31.0089 29.8227 28.6377 27.3749 26.0591 24.6993 23.2763 K at tip a 0.0586 0.1875 0.3393 0.4930 0.6696 0.8463 1.0415 Page C-40 of C-173 F0306-0l R2 e Structural Integrity Associates, Inc. 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.5859 0. 6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1.0156 1. 054 7 1. 0938 1.132 8 1.1719 1.2109 1. 2500 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 Load Case # 9: Residual ------------

Crack Dimensions a c a/t 0.0800 0.3125 0.1831 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0. 7813 0.8203 0.8594 0.8984 0.9375 0.9766 1.0156 1. 054 7 1.0938 1.1328 1.1719 1.2109 1.2500 Load Case # 10: OBE 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 c/a 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 ------------

Crack Dimensions

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a c a/t c/a 0.0800 0.3125 0.1831 3.9063 0.0900 0.3516 0.2059 3.9063 0.1000 0.3906 0.2288 3.9063 0.1100 0.4297 0.2517 3.9063 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0. 7813 0.8203 0.8594 0.8984 0.9375 File No.: 1501350.301 Revision:

0 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3. 9063 3.9063 1. 23 90 1.4490 1.6641 1.8846 2.1100 2.3397 2.5777 2.8173 3.0658 3.3143 3. 5710 3.8281 4.1160 4.4127 4. 7166 5.0253 5.3380 5.6564 K at tip a 15.4155 16.4062 17.4799 18.5285 19.5564 20.5674 21.5642 22.5492 23.5243 24.4912 25.4905 26.5237 27.5562 28.5885 29.6214 30.6554 31.6909 32.7283 33.7680 34.9827 36.2562 37.5407 38.8362 40.1427 41.4602 K at tip a 1.7008 1.8102 1.9286 2.0443 2.1577 2.2693 2. 37 92 2.4879 2.5955 2.7022 2.8125 2. 92 65 3.0404 3.1543 3.2682 3.3823 3.4966 Page C-41 of C-1 73 F0306-0 IR2 e Structural Integrity Associates, Inc."' 0.2500 0. 2 600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.9766 1. 0156 1.0547 1.0938 1.1328 1.1719 1.2109 1. 2500 Load Case # 11: OW 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 ------------

Crack Dimensions

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a c a/t c/a 0.0800 0.3125 0.1831 3.9063 0.0900 0.3516 0.2059 3.9063 0.1000 0.3906 0.2288 3.9063 0.1100 0.4297 0.2517 3.9063 0.1200 0.4688 0.2746 3.9063 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1. 0156 1.0547 1. 0938 1.1328 1.1719 1. 2109 1.2500 Load Case# 12: SLID Max 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 . 0. 5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 ------------

Crack Dimensions

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a c a/t c/a 0.0800 0.3125 0.1831 3.9063 0.0900 0.3516 0.2059 3.9063 0.1000 0.3906 0.2288 3.9063 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1. 0156 1.0547 1.0938 1.132 8 1.1719 1.2109 1.2500 Load Case # 13: SLID Min File No.: 1501350.301 Revision:

0 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3. 9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3. 6110 3.7257 3.8598 4.0003 4.1420 4.2849 4.4291 4.5744 K at tip a 0.3746 0.3987 0.4248 0.4502 0.4752 0.4998 0.5240 0.5479 0.5716 0.5951 0.6194 0.6445 0. 6696 0.6947 0. 7198 0.7449 0.7701 0.7953 0.8206 0.8501 0.8810 0.9122 0.9437 0.9755 1.0075 K at tip a 12.9640 13.2300 13.4520 13.6645 13.7610 13.8575 13.8678 13.8675 13.8129 13.7356 13. 6724 13. 6223 13.5577 13.4643 13.3656 13.2372 13.1088 12.9537 12.7976 12.6701 12.5507 12.4138 12.2650 12.1065 11.9343 Page C-42 of C-173 F0306-0IR2 e Structural Integrity Associates, Inc. ------------

Crack Dimensions

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a 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c 0.3125 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0.7 813 0. 8203 0.8594 0.8984 0.9375 0.9766 1.0156 1. 054 7 1. 0938 1.1328 1.1719 1. 2109 1.2500 a/t c/a 0.1831 3.9063 0.2059 3.9063 0.2288 3.9063 0. 2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 52 63 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7 323 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 CRACK GROWTH ANALYSIS RESULTS Blocks da/dn da/dt Subblock Cycles/ Time 0.0000 1.764E-05 140.0000 3.408E-05 8.0000 6.749E-05 2.0000 1.026E-06 2744.0000 3.1 84E-08 16.0000 1.105E-06 210.0000 0.5490 1.791E-05 140.0000 3.463E-05 8.0000 6.870E-05 2.0000 1.041E-06 2744.0000 3.250E-08 16.0000 1.121E-06 210.0000 1.0900 1.819E-05 140.0000 3.518E-05 8.0000 6.991E-05 2.0000 1.055E-06 2744.0000 3.291E-08 16.0000 1.136E-06 210.0000 1.6245 1.838E-05 140.0000 3.557E-05 8.0000 7.078E-05 2.0000 1.065E-06 2744.0000 3.524E-08 16.0000 1.146E-06 210.0000 2.1543 1.854E-05 140.0000 3.589E-05 8.0000 7.153E-05 2.0000 1.072E-06 2744.0000

• 3. 77 SE-08 16.0000 1.154E-06 210.0000 2.6801 1.870E-05 140.0000 3.621E-05 8.0000 7.228E-05 2.0000 1.079E-06 2744.0000 File No.: 1501350.301 Revision:

0 Crack Dim. a 0.0800 0.0833 0.0866 0.0898 0.0931 0.0964 a/t 0.1831 0.1 906 0.1981 0.2056 0. 2131 0.2206 K at tip a 2.2931 2.4743 2. 6672 2.8600 3.0518 3.2435 3.4355 3.6276 3.8203 4. 0134 4. 2137 4.4206 4.6285 4.8384 5.0487 5.2615 5.4743 5.6897 5.9053 6.1553 6.4151 6.6787 6.9449 7.2136 7.4858 Kmax 43.5128 49.5150 57.1246 28.5184 16.5045 28.7541 43.9742 49.9988 57.6550 28.9344 16.6738 29.1707 44.4295 50.4766 58.1794 29.3444 16.8416 29.5813 44.8795 50.9377 58.6700 29.7753 17.0036 30.0125 45.3259 51.3914 59.1 470 30.2118 17.1632 30.4490 45.7692 51.8419 59.6209 30.6450 Kmin 17.0853 16.6423 15.8486 18.0988 13.1 029 18.0832 17.4595 17.0129 16.2127 18.4814 13.2022 18.4657 17.8277 17.3774 16.5706 18.8579 13.3014 18.8421 18.2363 17.7832 16. 9711 19.2732 13.3873 19.2573 18.6573 18.2015 17.3847 19.7003 13.4686 19.6843 19.0752 18.6167 17.7951 20.1243 Sub Delta Block K No 26.4275 32.8727 41.2759 10.4196 3.4017 10.6709 26.5147 32.9860 41.4424 10.4531 3.4716 10.7051 26.6018 33.0992 41.6088 10.4866 3.540 2 10.7393 26.6432 33.1546 41.6988 10.5021 3.6163 10.7 552 26.6686 33.1899 41.7623 10.5114 3.6947 10.7647 26.6941 33.2252 41.8258 10.5208 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 Page C:-43 of C-173 F0306-01 R2 e S/ructurallnlegrily Associates, Inc. 4.036E-08 16.0000 1.162E-06 210.0000 3.2019 1.885E-05 140.0000 3.653E-05 7.302E-05 8.0000 2.0000 1.086E-06 2744.0000 4.307E-08 16.0000 1.170E-06 210.0000 3.7198 1.900E-05 140.0000 3.685E-05 8.0000 7.375E-05 2.0000 1.093E-06 2744.0000 4.587E-08 16.0000 1.177E-06 210.0000 4.2340 1.916E-05 140.0000 3. 716E-05 8.0000 7.449E-05 2.0000 1.100E-06 2744.0000 4.878E-08 16.0000 1.185E-06 210.0000 4.7448 1.929E-05 140.0000 3.744E-05 8.0000 7.515E-05 2.0000 1.106E-06 2744.0000 5.179E-08 16.0000 1.191E-06 210.0000 5.2552 1.922E-05 140.0000 3. 731E-05 8.0000 7.498E-05 2.0000 1.100E-06 2744.0000 5.489E-08 16.0000 1.185E-06 210.0000 5.7680 1.914E-05 140.0000 3.718E-05 8.0000 7.480E-05 2.0000 1.093E-06 2744.0000 5.808E-08 16.0000 1.178E-06 210.0000 6.2834 1.906E-05 140.0000. 3.704E-05 8.0000 7.462E-05 2.0000 1.087E-06 2744.0000 6.139E-08 16.0000 1.171E-06 210.0000 6.8015 1.898E-05 140.0000 3.690E-05 8.0000 7.442E-05 2.0000 1.080E-06 2744.0000 6.480E-08 16.0000 1.164E-06 210.0000 7.3222 1.889E-05 140.0000 3.675E-05 8.0000 7.421E-05 2.0000 1.073E-06 2744.0000 6.831E-08 16.0000 1.156E-06 210.0000 7.8458 1.881E-05 140.0000 3.660E-05 8.0000 7.400E-05 2.0000 1.067E-06 2744.0000 7.194E-08 16.0000 1.149E-06 210.0000 8.3733 1.865E-05 140.0000 3.631E-05 8.0000 7.349E-05 2.0000 1.056E-06 2744.0000 7.567E-08 16.0000 1.137E-06 210.0000 File No.: 1501350.301 Revision:

0 0.0997 0.1029 0.1062 0.1095 0.1128 0.1161 0.1193 0.1226 0.1259 0.1292 0.1324 0.2281 0.2356 0.2431 0.2506 0.2581 0.2656 0.2731 0.2806 0.2881 0.2956 0.3031 17.3221 30.8824 46.2095 52.2894 60.0918 31.0753 17.4803 31.3128 46.6471 52.7342 60.5599 31.5028 17.6378 31.7 405 47.0820 53.1763 61.0254 31.9277 17.7947 32.1655 47.5071 53.6068 61.4766 32.3471 17.9479 32.5850 47.8390 53.9219 61.7804 32.7271 18.0634 32.9642 48.1688 54.2348 62.0820 33.1049 18.1784 33.3412 48.4967 54.5457 62.3816 33.4807 18.2929 33.7162 48.8226 54.8548 62.6793 33.8546 18.4070 34.0894 49.1467 55.1621 62.9753 34.2267 18.5206 34.4607 49.4692 55.4677 63.2696 34.5971 18.6338 34.8304 49.7590 55.7328 63.5122 34.9533 18.7340 35.1856 13.5498 20.1082 19.4900 19.0290 18.2025 20.5452 13.6309 20.5291 19.9021 19.4384 18.6072 20.9634 13.7119 20.9472 20.3116 19.8453 19.0092 21.3790 13.7929 21.3627 20.7189 20.2501 19.4094 21.7921 13.8708 21.77 57 21.1271 20.6573 19.8149 22.2026 13.9114 22.1861 21.5332 21.0624 20.2182 22.6109 13.9520 22.5944 21.9372 21.4655 20.6195 23.0172 13.9925 23.0006 22.3394 21.8667 21.0189 23.4216 14.0330 23.4050 22.7398 22.2661 21.4165 23.8242 14.0735 23.8076 23 .1385 22.6639 21.8125 24.2252 14.1139 24.2085 23.5369 23.0619 22.2097 24.6246 14.1416 24.6079 3.7724 10.7743 26.7195 33.2605 41.8893 10.5301 3.8494 10.7838 26.7450 33.2957 41.9527 10.5394 3.9259 10.7933 26.7704 33.3310 42.0162 10.5487 4.0017 10.8029 26.7882 33.3567 42.0672 10.5550 4.0771 10.8093 26.7119 33.2645 41.9655 10.5245 4.1520 10.7781 26.6357 33.1724 41.8638 10.4940 4.2264 10.7469 26.5594 33.0802 41.7621 10.4635 4.3004 10.7156 26.4832 32.9881 41.6604 10.4330 4.3740 10.6844 26.4069 32.8959 41.5587 10.4025 4.4471 10.6532 26.3307 32.8038 41.4570 10.3720 4.5200 10.6219 26.2220 32.6709 41.3025 10.3288 4.5925 10.5777 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 Page C-44 of C-173 F0306-0 I R2 lJ Structural Integrity Associates, Inc.'" 8.9072 1.839E-05 140.0000 3.581E-05 7.257E-05 8.0000 2.0000 1.039E-06 2744.0000 7.950E-08 16.0000 1.119E-06 210.0000 9.4493 1.812E-05 140.0000 3.532E-05 8.0000 7.165E-05 2.0000 1.022E-06 2744.0000 8.344E-08 16.0000 l.lOlE-06 210.0000 9.9998 1.786E-05 140.0000 3.483E-05 7.073E-05 8.0000 2.0000 1.005E-06 2744.0000 8.749E-08 16.0000 1.083E-06 210.0000 10.5589 1.760E-05 140.0000 3.433E-05 6.980E-05 8.0000 2.0000 9.886E-07 2744.0000 9.166E-08 16.0000 1.065E-06 210.0000 11.1269 1.734E-05 140.0000 3.384E-05 8.0000 6.888E-05 2.0000 9.720E-07 2744.0000 9.594E-08 16.0000 1.047E-06 210.0000 11.7041 1.708E-05 140.0000 3.335E-05 8.0000 6.795E-05 2.0000 9.555E-07 2744.0000 1.003E-07 16.0000 1.030E-06 210.0000 12.2924 1.672E-05 140.0000 3.267E-05 6.663E-05 8.0000 2.0000 9.335E-07 2744.0000 1.048E-07 16.0000 1.006E-06 210.0000 12.8945 1.633E-05 140.0000 3.193E-05 6.519E-05 8.0000 2.0000 9.099E-07 2744.0000 1.095E-07 16.0000 9.807E-07 210.0000 13.5116 1.595E-05 140.0000 3 .119E-05 6.375E-05 8.0000 2.0000 8.866E-07 2744.0000 1.142E-07 16.0000 9.556E-07 210.0000 14.1444 1.557E-05 140.0000 3.047E-05 8.0000 6.233E-05 2.0000 8.636E-07 2744.0000 1.190E-07 16.0000 9.309E-07 210.0000 14.7933 1.519E-05 140.0000 2.975E-05 8.0000 6.093E-05 2.0000 8.410E-07 2744.0000 1.240E-07 16.0000 9.065E-07 210.0000 15.4590 1.482E-05 140.0000 2.904E-05 8.0000 File No.: 1501350.301 Revision:

0 0.1357 0.1390 0.1423 0.1456 0.1488 0.1521 0.1554 0.1587 0.1619 0.1652 0.1685 0.1718 0.3106 0.3181 0.3256 0.3331 0.3406 0.3481 0.3556 0.3631 0.3706 0.3781 0.3856 0.3931 50.0023 55.9403 63.6810 35.2898 18.8156 35.5205 50.2442 56.1464 63.8484 35.6248 18.8968 35.8540 50.4849 56.3512 64.0145 35.9585 18.9776 36.1862 50.7242 56.5547 64.1793 36.2910 19.0582 36.5172 50.9624 56.7571 64.3430 36.6223 19.1385 36.8469 51.1995 56.9583 64.5055 36.9525 19.2186 37.1756 51.3905 57.1021 64.5940 37.2632 19.2800 37.4845 51.5647 57.2253 64.6561 37.5666 19.3347 37.7859 51.7380 57.3476 64.7172 37.8690 19.3893 38.0864 51.9105 57.4689 64.7775 38.1705 19.4436 38.3860 52.0821 57.5895 64.8370 38.4713 19.4977 38.6847 52.2529 57.7093 23.9357 23.4610 22.6094 25.0225 14.1509 25.0058 24.3331 23.8588 23.0078 25.4191 14.1603 25.4024 24.7292 24.2552 23.4048 25.8143 14.1695 25.7976 25.1240 24.6504 23.8006 26.2083 14.1788 26.1916 25.5176 25.0444 24.1952 26.6011 14.1881 26.5844 25.9102 25.4374 24.5887 26.9928 14.1973 26.9762 26.3037 25.8321 24.9855 27.3836 14.1881 27.3671 26.6970 26.2268 25.3827 27.7736 14.1724 27.7571 27.0894 26.6207 25.7791 28.1626 14.1568 28.1462 27.4809 27.0136 26.1745 28.5508 14.1411 28.5344 27.8715 27.4057 26.5692 28.9381 14.1254 28.9218 28.2614 27.7971 26.0666 32.4793 41.0716 10.2673 4.6646 10.5147 25.9111 32.2876 40.8406 10.2057 4.7365 10.4516 25.7557 32.0960 40.6097 10.1442 4.8081 10.3886 25.6003 31.9043 40.3787 10.0827 4.8794 10.3255 25.4448 31.7126 40.1478 10.0212 4.9505 10.2625 25.2894 31.5210 39.9168 9.9597 5. 0213 10.1995 25.0867 31_.2700 39.6085 9.8796 5.0919 10.1174 24.8677 30.9985 39.2733 9.7930 5.1623 10.0288 24.6486 30.7269 38.9382 9.7064 5.2325 9.9402 24.4296 30.4553 38.6030 9.6198 5.3025 9.8516 24.2106 30.1838 38.2678 9.5332 5. 3723 9.7630 23.9915 29.9122 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 Page C-45 of C-1 73 F0306-0l R2 e Structural Integrity Associates, Inc.'" 5.953E-05 2.0000 8.186E-07 2744.0000 1.291E-07 16.0000 8.825E-07 210.0000 16.1422 1.446E-05 140.0000 2.834E-05 5.816E-05 8.0000 2.0000 7.967E-07 2744.0000 1.344E-07 16.0000 8.589E-07 210.0000 16.8429 1.412E-05 140.0000 2.768E-05 5.687E-05 8.0000 2.0000 7.762E-07 2744.0000 1.402E-07 16.0000 8.369E-07 210.0000 17.5614 1.378E-05 140.0000 2.704E-05 8.0000 5.559E-05 2.0000 7.560E-07 2744.0000 1.462E-07 16.0000 8.152E-07 210.0000 18.2983 1.345E-05 140.0000 2.640E-05 8.0000 5.433E-05 2.0000 7.362E-07 2744.0000 1.523E-07 16.0000 7.938E-07 210.0000 19.0543 1.312E-05 140.0000 2.576E-05 8.0000 5.308E-05 2.0000 7.166E-07 2744.0000 1.586E-07 16.0000 7.727E-07 210.0000 19.8302 1.279E-05 140.0000 2.514E-05 8.0000 5.184E-05 2.0000 6.973E-07 2744.0000 1.651E-07 16.0000 7.519E-07 210.0000 20.6268 1.247E-05 140.0000 2.452E-05 8.0000 5.061E-05 2.0000 6.782E-07 2744.0000 1.717E-07 16.0000 7.315E-07 210.0000 21.4458 1.212E-05 140.0000 2.386E-05 8.0000 4.929E-05 2.0000 6.581E-07 2744.0000 1.785E-07 16.0000 7.097E-07 210.0000 22.2802 1.175E-05 140.0000 2.313E-05 8.0000 4.784E-05 2.0000 6.702E-07 2744.0000 1.855E-07 16.0000 6.862E-07 210.0000 23.1147 1.138E-05 140.0000 2.242E-05 4.640E-05 8.0000 2.0000 7.027E-07 2744.0000 1.926E-07 16.0000 6.972E-07 210.0000 23.9433 1.102E-05 140.0000 2.171E-05 4.499E-05 8.0000 2.0000 7.309E-07 2744.0000 File No.: 1501350.301 Revision:

0 0.1750 0.1783 0.1816 0.1849 0.1882 0.1914 0.1947 0.1980 0.2013 0.2045 0.2078 0.4006 0.4081 0.4156 0.4231 0.4306 0.4381 0.4456 0.4531 0.4606 0.4681 0.4756 64.8957 38.7712 19.5516 38.9827 52.4261 57.8315 64.9568 39.0730 19.6065 39.2825 52.6355 57.9919 65.0564 39.4058 19.6751 39.6134 52.8448 58.1522 65.1558 39.7384 19.7437 39.9440 53.0539 58.3123 65.2551 40.0708 19.8122 40.2745 53.2629 58.4723 65.3542 40.4032 19.8806 40.6049 53.4717 58.6321 65.4533 40.7354 19.9491 40.9351* 53.6806 58.7920 65.5522 41.0675 20.0175 41.2653 53.8748 58.9334 65.6274 41.3940 20.0802 41.5897 54.0481 59.0485 65.6682 41.7122 20.1348 41.9056 54.2213 59.1635 65.7089 42.0304 20.1893 42.2216 54.3946 59.2785 65.7498 42.3487 26.9630 29.3246 14.1097 29.3084 28.6528 28.1898 27.3583 29.7127 14.0947 29.6965 29.0706 28.6089 27.7794 30.1277 14.0884 30.1116 29.4882 29.0277 28.2004 30.5426 14.0822 30.5265 29.9057 29.4464 28.6212 30.9573 14.0760 30.9412 30.3231 29.8650 29.0419 31.3719 14.0697 31.3558 30.7403 30.2834 29.4624 31.7864 14.0635 31.7703 31.1575 30.7018 29.8829 32.2008 14.0572 32.1847 31.5756 31.1214 30.3051 32.6155 14.0453 32.5995 31.9951 31.5427 30.7296 33.0308 14.0252 33.0149 32.4145 31.9640 31.1542 33.4461 14.0051 33.4302 32.8340 32.3853 31.5788 33.8614 37.9326 9.4466 5.4420 9.6743 23.7733 29.6416 37.5985 9.3603 5. 5119 9.5861 23.5649 29.3830 37.2769 9.2780 5.5867 9.5018 23.3565 29.1245 36.9554 9.1958 5.6615 9.4176 23.1482 28.8659 36.6339 9.1135 5.7362 9.3333 22.9398 28.6073 36.3124 9. 0313 5.8109 9.2491 22.7314 28.3487 35.9908 8.9490 5.8856 9.1648 22.5231 28.0901 35.6693 8.8668 5.9603 9.0806 22.2992 27.8121 35.3223 8.7785 6.0349 8.9901 22.0530 27.5058 34.9385 8.6814 6.1096 8.8907 21.8068 27.1995 34.5547 8.5843 6.1843 8.7913 21.5605 26.8932 34.1710 8.4873 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 Page C-46 of C-1 73 F0306-0l R2 e Structural Integrity Associates, Inc."' 1.999E-07 16.0000 7.308E-07 210.0000 24.7679 1.066E-05 140.0000 2.102E-05 8.0000 4.360E-05 2.0000 7.549E-07 2744.0000 2.074E-07 16.0000 7.598E-07 210.0000 25.5907 1.031E-05 140.0000 2.034E-05 8.0000 4.224E-05 2.0000 7.750E-07 2744.0000 2.151E-07 16.0000 7.845E-07 210.0000 26.4138 9.964E-06 140.0000 1.968E-05 8.0000 4.090E-05 2.0000 7.915E-07 2744.0000 2.230E-07 16.0000 8.052E-07 210.0000 27.2400 9.593E-06 140.0000 1.896E-05 8.0000 3.944E-05 2.0000 8.037E-07 2744.0000 2.310E-07 16.0000 8.213E-07 210.0000 28.0724 9.220E-06 140.0000 1.823E-05 8.0000 3.796E-05 2.0000 8.121E-07 2744.0000 2.393E-07 16.0000 8.332E-07 210.0000 28.9133 8.854E-06 140.0000 1. 752E-05 3.652E-05 8.0000 2.0000 8.171E-07 2744.0000 2.477E-07 16.0000 8.413E-07 210.0000 29.7647 8.498E-06 140.0000 1.683E-05

3. 511E-05 8.0000 2.0000 8.190E-07 2744.0000 2.563E-07 16.0000 8.460E-07 210.0000 8.150E-06 140.0000 1.615E-05 3.373E-05 8.0000 2.0000 8.180E-07 2744.0000 2.651E-07 16.0000 8.474E-07 210.0000 31.5069 7.811E-06 140.0000 1.549E-05 8.0000 3.239E-05 2.0000 8.144E-07 2744.0000 2.742E-07 16.0000 8.458E-07 210.0000 32.4018 7.478E-06 140.0000 1.484E-05 8.0000 3.106E-05 2.0000 8.082E-07 2744.0000 2.834E-07 16.0000 8.414E-07 210.0000 33.3165 7.126E-06 140.0000 1.415E-05 8.0000 2.966E-05 2.0000 7.981E-07 2744.0000 2.928E-07 16.0000 8.327E-07 210.0000 File No.: 1501350.301 Revision:

0 0.2111 0.2144 0.2177 0.2209 0.2242 0.2275 0.2308 0.2340 0.2373 0.2406 0.2439 0.4831 0.4906 0.4981 0.5056 0. 5131 0.5206 0.5281 0.5356 0.5431 0.5506 0.5581 20.2439 42.5375 54.5679 59.3936 65.7906 42.6669 20.2984 42.8536 54.7413 59.5088 65.8315 42.9853 20.3530 43.1696 54.9148 59.6241 65.8725 43.3037 20.4076 43.4858 55.0670 59.7126 65.8788 43.6140 20.4539 43.7936 55.2118 59.7919 65.8732 43.9215 20.4974 44.0985 55.3568 59.8714 65.8677 13.9850 33.8456 33.2536 32.8067 32.0034 34.2768 13.9648 34.2610 33.6732 33.2282 32.4282 34.6922 13.9447 34.6765 34.0929 33.6497 32.8530 35.1077 13.9246 35.0921 34.5142 34.0733 33.2804 35.5240 13.8962 35.5085 34.9362 34.4976 33.7089 35.9407 13.8649 35.9252 35.3583 34.9221 34.1375 44.2291 36.3575 20.5409 13.8336 44.4036 36.3421 55.5019' 35.7806 59.9510 65.8623 44.5369 20.5844 44.7088 55.6472 60.0308 65.8571 44.8448 20.6280 45.0142 55.7927 60.1108 65.8521 45.1530 20.6716 45.3197 55.9367 60.1888 65.8444 45.4606 20.7146 45.6248 56.0596 60.2402 65.8021 45.7604 20.7496 45.9218 35.3467 34.5662 36.7745 13.8023 36.7592 36.2031 35.7715 34.9951 37.1916 13.7710 37.1764 36.6257 36.1965 35.4242 37.6089 13.7398 37.5938 37.0487 36.6218 35.8538 38.0265 13.7078 38.0114 37.4735 37.0494 36.2861 38.4451 13.6678 38.4302 6.2589 8.6919 21.3143 26.5869 33.7872 8.3902 6.3336 8.5925 21.0681 26.2806 33.4034 8.2931 6.4083 8.4931 20.8219 25.9744 33.0196 8.1960 6.4830 8.3937 20.5527 25.6393 32.5984 8.0900 6.5577 8.2851 20.2756 25.2943 32.1643 7.9808 6.6325 8.1733 19.9984 24.9493 31.7302 7.8716 6.7073 8.0614 19.7213 24.6043 31.2961 7. 7 62 4 6.7821 7.9496 19.4442 24.2593 30.8620 7.6532 6.8569 7.8378 19.1670 23.9143 30.4278 7.5440 6.9318 7. 7260 18.8880 23.5669 29.9907 7.4341 7.0068 7.6134 18.5861 23.1908 29.5160 7.3153 7.0818 7.4916 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 Page C-4 7 of C-173 F0306-0 !R2 e Structural Integrity Associates, Inc."' 34.2547 6.785E-06 140.0000 1.348E-05 8.0000 2.829E-05 2.0000 7.857E-07 2744.0000 3.024E-07 16.0000 8.215E-07 210.0000 35.2189 6.454E-06 140.0000 1.283E-05 8.0000 2.696E-05 2.0000 7.714E-07 2744.0000 3.122E-07 16.0000 8.080E-07 210.0000 36.2117 6.133E-06 140.0000 1.220E-05 8.0000 2.566E-05 2.0000 7.554E-07 2744.0000 3.222E-07 16.0000 7.925E-07 210.0000 37.2358 5.822E-06 140.0000 8.0000 2.441E-05 2.0000 7.378E-07 2744.0000 3.325E-07 16.0000 7.753E-07 210.0000 38.2944 5.522E-06 140.0000 1.100E-05 8.0000 2.320E-05 2.0000 7.188E-07 2744.0000 3.429E-07 16.0000 7.564E-07 210.0000 39.3903 5.229E-06 140.0000 1.043E-05 8.0000 2.201E-05 2.0000 6.990E-07 2744.0000 3.546E-01 16.0000 7.367E-07 210.0000 40.5267 4.944E-06 140.0000 9.867E-06 2.085E-05 8.0000 2.0000 6.786E-07 2744.0000 3.680E-07 16.0000 7.162E-07 210.0000 41.7072 4.669E-06 140.0000 9.324E-06 8.0000 1.973E-05 2.0000 6.571E-07 2744.0000 3.817E-07 16.0000 6.944E-07 210.0000 42.9360 4.403E-06 140.0000 8.801E-06 8.0000 1.865E-05 2.0000 6.346E-07 2744.0000 3.958E-07 16.0000 6.715E-07 210.0000 44.2177 4.147E-06 140.0000 8.296E-06 8.0000 1.760E-05 2.0000 6.114E-07 2744.0000 4.103E-07 16.0000 6.477E-07 210.0000 45.5572 3.901E-06 140.0000 7.810E-06 1.659E-05 8.0000 2.0000 5.877E-07 2744.0000 4.252E-07 16.0000 6.232E-07 210.0000 46.9602 3.664E-06 140.0000 7.342E-06 8.0000 File No.: 1501350.301 Revision:

0 0.2472 0.2504 0.2537 0.2570 0.2603 0.2635 0.2668 0.2701 0.2734 0.2767 0.2799 0.2832 0.5656 0.5731 0.5806 0.5881 0.5956 0.6031 0.6106 0.6181 0.6256 0.6331 0.6406 0.6481 56.1827 60.2918 65.7600 46.0604 20.7846 46.2189 56.3061 60.3437 65.7182 46.3607 20.8196 46.5163 56.4297 60.3959 65.6766 46.6612 20.8547 46.8140 56.5535 60.4483 65.6352 46.9619 20.8899 47.1119 56.6777 60.5010 65.5942 4 7. 2629 20.9251 47.4100 56.8352 60.5862 65.5842 47.5991 20.9725 47.7434 57.0414 60.7189 65.6198 47.9866 2 1.037 4 48.1282 57.2489 60.8529 65.6565 48.3753 21.1027 48.5141 57.4575 60.9880 65.6945 48.7652 2 1.168 2 48.9013 57.6674 6 1.1244 65.7337 49.1563 21.2340 49.2897 57.8785 61.2619 65.7741 49.5486 21.3001 49.6793 58.0908 61.4007 37.8985 37.4771 36.7186 38.8640 13. 6277 38.8491 38.3238 37.9051 37.1514 39.2831 13.5877 39.2683 38.7493 38.3334 37.5844 39.7024 13.5477 39.6878 39.1751 38.7619 38.0177 40.1220 13.5077 40.1075 39.6011 39.1907 38.4513 40.5419 13.4677 40.5275 40.0631 39.6553 38.9205 40.9980 13.4332 40.9836 40.5776 40.1722 39.4416 41.5070 13.4068 41.4927 41.0933 40.6903 39.9640 42.0171 13.3805 42.0029 41.6102 41.2097 40.4875 42.5285 13.3542 42.5144 42.1283 41.7302 41.0123 43.0411 13.3279 43.0271 42.6476 42.2520 41.5383 43.5549 1 3.3016 43.5409 43.1681 42.7750 1 8.2842 22.8147 29.0414 7.19 64 7.15 68 7.3 698 17.9823 22.4386 28.5668 7.0776 7.2 319 7.2480 17.6804 22.0625 28.0921 6.9587 7.3070 7.1262 17.3784 21.6864 27.6175 6.8399 7.3822 7.0044 17.0765 21.3103 27.1429 6. 7210 7.4575 6.8826 16.7720 20.9309 26.6638 6. 6011 7.5393 6. 7598 16.4638 20.5467 26.1782 6.4796 7.6306 6.6355 16.1556 20.1625 25.6926 6.3581 7. 7222 6. 5112 15.8473 19.7783 25.2070 6.2366 7.8140 6.3869 15.5 39 1 19.3941 24.7214 6.1151 7.9061 6. 2 626 15.2309 19.0099 24.2 358 5.9937 7.9985 6.1384 14.9227 18.6257 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 Page C-48 of C-173 F0306-0 I R2 e Structural Integrity Associates, Inc.'" 1.562E-05 2.0000 5.634E-07 2744.0000 4.405E-07 16.0000 5.982E-07 210.0000 48.4354 3.421E-06 140.0000 6.860E-06 8.0000 1.462E-05 2.0000 5.369E-07 2744.0000 4.561E-07 16.0000 -5. 705E-07 210. oooo 49.9942 3.182E-06 140.0000 6.388E-06 1.363E-05 8.0000 2.0000 5.096E-07 2744.0000 4.721E-07 16.0000 5.420E-07 210.0000 51.6464 2.955E-06 140.0000 5.937E-06 8.0000 1.269E-05 2.0000 4.823E-07 2744.0000 4.886E-07 16.0000 5.134E-07 210.0000 53.4021 2.739E-06 140.0000 5.507E-06 8.0000 1.179E-05 2.0000 4.551E-07 2744.0000 5.054E-07 16.0000 4.849E-07 210.0000 55.2724 2.533E-06 140.0000 5.098E-06 8.0000 1.093E-05 2.0000 4.283E-07 2744.0000 5.227E-07 16.0000 4.566E-07 210.0000 57.2700 2.338E-06 140.0000 4.709E-06 8.0000 1. 011E-05 2.0000 4.019E-07 2744.0000 5.404E-07 16.0000 4.288E-07 210.0000 59.4097 2.151E-06 140.0000 4.337E-06 9.329E-06 8.0000 2.0000 3.758E-07 2744.0000 5.585E-07 16.0000 4.012E-07 210.0000 61.6848 2.220E-06 140.0000 3.963E-06 8.538E-06 8.0000 2.0000 3.485E-07 2744.0000 5.770E-07 16.0000 3.724E-07 210.0000 64.0829 2.292E-06 140.0000 3.610E-06 8.0000 7.792E-06 2.0000 3.221E-07 2744.0000 5.960E-07 16.0000 3.443E-07 210.0000 66.6180 2.323E-06 140.0000 3.279E-06 7.089E-06 8.0000 2.0000 2.965E-07 2744.0000 6.154E-07 16.0000 3.172E-07 210.0000 69.3123 2.317E-06 140.0000 2.968E-06 6.429E-06 8.0000 2.0000 2.719E-07 2744.0000 File No.: 1501350.301 Revision:

0 0.2865 0.2898 0.2930 0.2963 0.2996 0.3029 0.3061 0.3094 0.3127 0.3160 0.3193 0.6556 0.6631 0.6706 0.6781 0.6856 0.6931 0.7006 0.7081 0. 7156 0.7231 0.7306 65.8156 49.9421 21.3665 50.0701 58.2848 61.5161 65.8266 50.3300 21.4264 50.4550 58.4734 61.6242 65.8277 50.7168 21.4842 50.8386 58.6631 61.7334 65.8300 51.104 7 21.5422 51.2234 58.8540 61.8439 65.8336 51.4939 21.6006 51.6094 59.0462 61.9556 65.8383 51.8843 21.6593 51.9967 59.2396 62.0685 65.8443 52.2759 21.7182 52.3851 59.4325 62.1806 65.8488 52.6682 21.7769 52.7742 59.6069 62.2689 65.8220 53.0546 21.8289 53.1574 59.7826 62.3584 65.7965 53.4423 21.8812 53.5418 59.9594 62.4492 65.7721 53.8313 21.9337 53.9274 60.1374 62.5411 65.7490 54.2214 42.0655 44.0699 13.2754 44.0560 43.6920 43.3016 42.5968 44.5877 13.2424 44.5739 44.2179 43.8302 43.1304 45.1072 13.2070 45.0935 44.7449 44.3601 43.6652 45.6280 13.1717 45.6144 45.2732 44.8912 44.2012 46.1500 13.1364 46.1364 45.8027 45.4235 44.7384 46.6731 13 .1011 46.6597 46.3334 45.9570 45.2768 47.1975 13.0659 47.1842 46.8655 46.4919 45.8167 47.7233 13.0301 47.7100 47.4011 47.0305 46.3606 48.2520 12.9874 48.2389 47.9379 47.5703 46.9058 48.7819 12.9447 48.7689 48.4759 48 .1114 47.4522 49.3131 12.9020 49.3002 49.0151 48.6536 47.9998 49.8455 23.7502 5. 8722 8. 0911 6.0141 14.5928 18.2145 23.2298 5.7423 8.1840 5.8811 14.2555 17.7939 22.6973 5.6095 8. 2772 5.7451 13.9182 17.3733 22.1649 5.4767 8.3706 5.6090 13.5808 16.9527 21. 6324 5.3439 8.4642 5.4730 13.2435 16.5321 21.0999 5. 2112 8.5582 5.3369 12.9062 16.1116 20.5675 5.0784 8.6523 5.2009 12.5671 15.6887 20.0321 4.9449 8.7468 5.0641 12.2059 15.2384 19.4614 4.8026 8.8415 4.9185 11.8447 14.7881 18.8906 4.6604 8.9365 4.7728 11.4835 14.3378 18.3199 4.5182 9.0317 4. 6272 11.1223 13.8875 17.7492 4.3759 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 5 6 1 2 3 4 Page C-49 of C-173 F0306-0l R2 SJ Structural Integrity Associates, Inc. 6.353E-07 16.0000 2. 911E-07 210.0000 72.1910 2.279E-06 140.0000 2.677E-06 8.0000 5.810E-06 2.0000 2.484E-07 2744.0000 6.556E-07 16.0000 2.660E-07 210.0000 75.2808 2.216E-06 140.0000 2.595E-06 8.0000 5.232E-06 2.0000 2.259E-07 2744.0000 6.764E-07 16.0000 2.421E-07 210.0000 Crack Depth, a= 0.3291 exceeds Number of Runtime Warnings:

0 *** End of pc-CRACK output File No.: 1501350.301 Revision:

0 21.9866 54.3142 0.3 2 25 0.7381 60.3166 62.6343 65.7271 54.6127 22.0398 54.7022 0.3258 0.7456 60.4971 62.7286 65.7064 55.0052 22.0932 55.0915 user-specified maximum= 0.3278 *** 12.8594 9.1272 5 49.8327 4.4815 6 49.5555 10.7611 1 49.1971 13.4372 2 48.5487 17.1784 3 50.3790 4.2337 4 12.8168 9.2230 5 50.3664 4.3358 6 50.0972 10.3999 1 49.7418 12.9869 2 49.0987 16.6077 3 50.9138 4.0914 4 12.7742 9.3190 5 50.9013 4.1902 6 Page C-50 of C-173 F0306-0 IR2 e Structural Integrity Associates, Inc. Fatigue Crack Growth-Variable Aspect Ratio pc-CRACK 4.1 CS Version Control No. 4.1.0.0 Structural Integrity Associates, Inc. www.structint.com pccrack@structint.com Date: 10/29/2015 10:57 Input Data read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\pcCRACK\FCG-Fixed.pcf Analysis Title: DCPP Spray Line Units Selected:

US Customary Linear Dimensions

-inches Stress -ksi Load -kips Temperature

-deg F Time -hours Analysis Type: Crack Growth (LEFM) Crack Growth Calculation Method -Crack Stepping Crack Model: 306-Semi-Elliptical Circumferential Crack in Cy l inder on the I nside Surface (API 579) Crack Depth, a = 0.0800 Ha l f Crack Length, c 0.3125 Wall T hickness, t = 0.4370 Ins i de Radius, Ri = 1.8130 Aspect ratio allowed to vary Maximum a/t = 0.75 Crack Depth Print Increment for SIF Tabulation=

0.01 Maximum Aspect Ratio (c/a) for SIF Tabulation = 5 Aspect Ratio Increment for SIF Tabulation

= 0.25 Total Load Cases: 13 Load Case 1:HU/CD Max 2-d SIF Input by User The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\HUCD.MXN No. of aspect ratios (a/c) in the tables = 8 a/c = 0.1250 Crack Depth Kdeepest Ksurface 4.370E-03 10.4510 3.9032 0.0437 26.8310 11.8060 0.0656 29.5570 14.0540 0.0874 30.7780 15.7380 0.1093 32. 0710 17.4750 0.1311 32.7520 19.0020 0.1530 32.9650 20.3650 0.1748 32,8050 21.5940 0.1967 32.7170 22.8730 0.2185 32.3480 24.0670 0.2404 31.7350 25.1860 0.2622 30.9160 26.2380 0.2841 29.7890 27.7710 0.3059 28.2260 29.2630 0.3278 26.2690 30.7150 0.3496 23.9630 32.1260 a/c = 0.1667 File No.: 1501350.301 Revision:

0 Page C-51 of C-173 F0306-01 R2 e Structural Integrity Associates, Inc."' Crack Depth Kdeepest Ksurface 4.370E-03 10.2590 4.5078 0.0437 26.2190 13.5920 0.0656 28 0 8130 16.1640 0.0874 29.9340 18.0900 0.1093 30.9780 20.1180 0.1311 31.3940 21.9160 0.1530 31.3250 23.5370 0.1748 30.8710 25.0150 0.1967 30.5010 26.4860 0.2185 29.8620 27.8470 0.2404 28.9970 29.1100 0.2622 27.9440 30.2830 0.2841 26.7090 31.8800 0.3059 25.1260 33.4090 0.3278 23.2340 34.8710 0.3496 21.0750 36.2690 a/c = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 10.0940 4. 9720 0.0437 25.7010 14.9640 0.0656 28.1890 17.7850 0.0874 29.2300 19.8970 0.1 093 30.0790 22.1480 0.1311 30.2870 24.1550 0.1530 30.0010 25.9760 0.1748 29.3190 27.6450 0.1967 28.7290 29.2660 0.2185 27.8830 30.7570 0.2404 26.8240 32.1310 0. 2 622 25.5900 33.3990 0.2841 24.2720 35.0450 0.3059 22.6760 36.6020 0.3278 20.8370 38.0720 0.3496 18.7960 39.4580 a/c = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 9.8321 5.6352 0.0437 24.8910 16.9230 0.0656 27.2190 20.1 000 0.0874 28.1420 22.4770 0.1093 28.7070 25.0490 0.1311 28.6150 27.3560 0.1530 28.0140 29.4610 0.1748 27.0060 31.4060 0.1967 26.1010 33.2410 0.2185 24.9580 34.9190 0.2404 23.6210 36.4540 0.2622 22.1290 37.8580 0.2841 20.6920 39.5750 0.3059 19.0780 41.1720 0.3278 17.3190 42.6510 0.3496 15.4500 44.0180 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 9.4074 6.1941 0.0437 23.6990 18.5910 0.0656 25.8360 22.0860 0.0874 26.6190 24.7140 0.1093 26.9910 27.4090 0.1311 26.7330 29.7930 File No.: 1501350.301 Page C-52 of C-173 Revision:

0 F0306-0 IR2 e Structural Integrity Associates, Inc.'" 0.1530 25.9910 31.9370 0.1748 24.8640 33.8890 0.1967 23.7690 35.8250 0.2 185 2 2.4550 37.5950 0.2404 2 0.9690 39.2140 0.2622 19.3490 40.6950 0. 284 , 1 17.7170 42.1800 0.3059 15.9420 43.5360 0.3278 14. 0550 44.7680 0.3496 12.0880 45.8850 ale = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 8.5324 7.1113 0.0437 21.2790 21.3290 0.0656 23.0480 25.3480 0.0874 23.5740 28.3890 0.1093 23.6000 31.2740 0.1311 2 3.0510 33.7670 0.1530 22.0680 35.9560 0.1748 20.7490 37.9000 0.1967 19.3320 39.9930 0.2185 17.7370 41.9050 0.2404 16.0090 43.6540 0.2622 14.1880 45.2550 0.2841 12.2420 46.3080 0.3059 10.2180 47.2180 0.3278 8.1538 47.9960 0.3496 6.5215 48.6530 ale = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 7.3428 7.3615 0.0437 18.0280 21.9460 0.0656 19.3480 25.9910 0.0874 19.5900 29.0030 0.1093 19.5280 31.8580 0.1311 18.9900 34.3100 0.1530 18.0990 36.4540 0.1748 16.9350 38.3530 0.1967 15.4390 40.2090 0.2185 13.7840 41.8890 0.2404 12.0140 43.4150 0.2622 10.1680 44.8030 0.2841 8.2553 45.9590 0.3059 6.3129 46.9930 0.3278 5.1927 47.9160 0.3496 5. 58 96 48.7370 ale = 1.0000 Crack Depth Kdeepest Ksurface 4.370E-03 6.3496 7.4789 0.0437 15.3380 22.1970 0.0656 16.3000 26.2 200 0.0874 16.3230 29.1800 0.1093 16.1940 31.9830 0.1311 15.6720 34.3790 0.1530 14.8600 36.4670 0.1748 13.8290 38.3130 0.1967 12.2920 39.9680 0.2185 10.6140 41.45 2 0 0.2404 8.8402 42.7910 0.262 2 7.0094 44.0030 0.2841 5.1774 45.2280 0.3059 4.1674 46.3 490 File No.: 1501350.301 Page C-53 of C-173 Revision:

0 F030 6-0 1R2 e Structural Integrity Associates, Inc.'" 0.3278 0.3496 4.4973 4.8250 Load Case 2:HU/CD Min 2-d SIF Input by User The SIF originally read No. of aspect ratios (a/c) ale = 0.1250 Crack Depth Kdeepest 4.370E-03 0.1714 0.0437 0.8047 0.0656 1.1531 0.0874 1.5159 0.1093 1.9355 0.1311 2.3815 0.1530 2.8518 0.1748 3.3440 0.1967 3.8949 0.2185 4.4723 0.2404 5.0743 0.2622 5.6988 0.2841 6.5727 0.3059 7.4985 0.3278 8. 4722 0.3496 9.4884 ale = 0.1667 Crack Depth Kdeepest 4.370E-03 0.1684 0.0437 0.7895 0.0656 1.1299 0.0874 1.4831 0.1093 1.8909 0.1311 2.3240 0.1530 2.7803 0.1748 3.2575 0.1967 3.7827 0.2185 4.3308 0.2404 4.8999 0.2622 5.4880 0.2841 6. 2723 0.3059 7.0977 0.3278 7.9603 0.3496 8.8555 ale = 0.2000 Crack Depth Kdeepest 4.370E-03 0.1657 0.0437 0.7765 0.0656 1.1100 0.0874 1.4553 0.1093 1.8532 0.1311 2.2756 0.1530 2.7203 0.1748 3.1850 0.1967 3.6893 0.2185 4.2137 0.2404 4.7563 0.2622 5.3150 0.2841 6.0281 0.3059 6.7738 0.3278 7.5485 File No.: 1501350.301 Revision:

0 47.3760 48.3170 from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\HUCD.MNN in the tables = 8 Ksurface 0.0594 0.1993 0.2538 0.3058 0.3579 0.4106 0.4646 0.5202 0.5767 0.6353 0.6961 0.7593 0.8424 0.9303 1. 0233 1.1213 Ksurface 0.0688 0.2347 0.3011 0.3649 0.4310 0.4983 0.5675 0.6388 0. 7183 0.8022 0.8904 0.9833 1.1020 1.2285 1. 3627 1. 504 7 Ksurface 0.0760 0. 2620 0.3375 0.4104 0.4873 0.5659 0.6467 0.7302 0.8275 0.9308 1.0403 1.1560 L 3022 1.4584 1. 6244 Page C-54 of C-173 F0306-0IR2 S} Structural Integrity Associates, Inc."' 0.3496 8.3479 1.8003 a/c = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 0.1615 0.0863 0.0437 0.7558 0.3009 0.0656 1. 07 87 0.3896 0.0874 1.4116 0.4756 0.1093 1. 7943 0.5680 0.1311 2.2002 0. 6627 0.1530 2.6270 0.7603 0.1748 3.0726 0.8612 0.1967 3.5454 0.9841 0.2185 4.0342 1.1154 0.2404 4.5369 1.2553 0.2622 5.0516 1. 4039 0.2841 5.6599 1.5897 0.3059 6.2881 1.7885 0.3278 6.9332 2.0002 0.3496 7. 5913 2.2247 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 0.1547 0.0951 0.0437 0. 7257 0.3358 0.0656 1.0364 0. 4371 0.0874 1. 3567 0.5360 0.1093 1.7209 0.6410 0.1311 2.1057 0.7488 0.1530 2.5088 0.8600 0.1748 2.9280 0.9749 0.1967 3.3674 1.114 7 0.2185 3.8194 1. 2636 0.2404 4.2818 1. 4217 0. 2 622 4.7526 1. 5890 0.2841 5.2981 1. 7808 0.3059 5.8575 1.9843 0.3278 6.4277 2.1992 0.3496 7.0035 2.4253 a/c = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 0.1406 0.1094 0.0437 0.6628 0.3935 0.0656 0.9479 0.5161 0.0874 1.2419 0.6367 0.1093 1.5684 0. 7629 0.1311 1.9107 0.8926 0.1530 2.2664 1. 0265 0.1748 2.6333 1.1650 0.1967 3.0077 1.3331 0.2185 3.3881 1. 5113 0.2404 3. 7725 1.6996 0.2622 4.1589 1.8981 0.2841 4.5847 2.0983 0.3059 5.0127 2.3073 0.3278 5.4362 2.5249 0.3496 5.1316 2.7510 a/c = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 0.1215 0.1134 0.0437 0.5788 0.4087 0.0656 0.8295 0.5366 File No.: 1501350.301 Page C-55 of C-173 Revision:

0 F0306-01 R2 e Structural Integrity Associates, Inc. 0.0874 1.0877 0.1093 1. 37 5 7 0.1311 1. 6771 0.1530 1.9896 0.1748 2. 3112 0.1967 2.6356 0.2185 2 .. 9639 0.2404 3.2941 0. 2 622 3.6241 0.2841 3.9792 0.3059 3.7631 0.3278 2.9125 0.3496 1. 6720 a/c = 1.0000 Crack Depth Kdeepest 4.370E-03 0.1055 0.0437 0.5080 0.0656 0.7296 0.0874 0.9576 0.1093 1. 2129 0.1311 1. 4795 0.1530 1.7554 0.1748 2.0387 0.1967 2. 3211 0.2185 2.6056 0.2404 2.8902 0.2622 2.9045 0.2841 2.2874 0.3059 1.4158 0.3278 0.2709 0.3496 -1.1900 Load Case 3:CD II Max 2-d SIF Input by User 0.6628 0.792 7 0.9252 1. 0611 1.2008 1.3592 1.5246 1.6968 1.8760 2.0636 2.2584 2.4601 2.6686 Ksurface 0.1153 0.4162 0.5470 0.6761 0.8075 0.9408 1.0769 1. 2160 1.3653 1. 5190 1.6770 1.8394 2.0154 2.1971 2.3843 2. 5771 The SIF originally read from C:\Users\c l ohse\Documents\ANSYS\PGE\1501350\TIFFANY\CDII

.MXN No. of aspect ratios (a/c) ale= 0.1250 Crack Depth Kdeepest 4.370E-03 12.7140 0.0437 32.6970 0.0656 35.9930 0.0874 37.4290 0.1093 38.9310 0.1311 39.6700 0.1530 39.8220 0.1 7 48 39.5090 0.1967 39.2 660 0.2185 38.6680 0.2404 37.7630 0. 2 622 36.5970 0.2841 34.9880 0.3059 32.8280 0.3278 30.1680 0.3496 27.0670 ale= 0.1667 Crack Depth Kdeepest 4.370E-03 12.4810 0.0437 31.9510 0.0656 35.0860 0.0874 36.4010 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 4.7459 14.3690 17.1130 19.1700 21.2930 23.1600 24.8260 26.3270 27.8900 29.3490 30.7150 31.9990 33.8670 35.6840 37.4520 39.1690 Ksurface 5. 4811 16.5440 19.6840 22.0360 Page C-56 of C-173 F0306-0 I R2 e Structural Integrity Associates, Inc. 0.1093 37.6000 24.5130 0.1311 38.0150 26.7100 0.1530 37.8260 28.6890 0.1748 37.1530 30.4930 0.1967 36.5690 32.2880 0.2185 35.6470 33.9480 0.2404 34.4400 35.4850 0.2622 32.9940 36.9110 0.2841 31.2740 38.8510 0.3059 29.1150 40.7050 0.3278 26.5640 42.4760 0.3496 23.6740 44.1650 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 12.2810 6.0457 0.0437 31.3190 18.2150 0.0656 34.3250 21.6580 0.0874 35.5430 24.2380 0.1093 36.5050 26.9860 0.1311 36.6680 29.4380 0.1530 36.2130 31.6590 0.1748 35.2640 33.6950 0.1967 34.4150 35.6710 0.2185 33.2430 37.4860 0.2404 31.8030 39.1560 0.2622 30.1430 40.6930 0.2841 28.3380 42.6880 0.3059 26.1820 44.5700 0.3278 23.7190 46.3430 0.3496 20.9970 48.0100 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03

11. 9620 6.8520 0.0437 30.3330 20.6000 0. 0656 33.1440 24.4770 0.0874 34.2190 27.3820 0.1093 34.8350 30.5200 0.1311 34.6330 33.3360 0.1530 33.7950 35.9040 0.1748 32.4480 38.2750 0.1967 31.2190 40.5090 0.2185 29.6900 42.5480 0.2404 27.9180 44.4090 0.2622 25.9510 46.1060 0.2841 24.0260 48.1790 0.3059 21.8770 50.1010 0.3278 19.5450 51.8740 0.3496 17.0720 53.5060 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03

11. 4450 7.5318 0.0437 28.8800 22.6330 0.0656 31.4580 26.8990 0.0874 32.3630 30.1080 0.1093 32.7450 33.3980 0.1311 32.3430 36.3060 0.1530 31.3370 38.9200 0.1748 29.8510 41.2980 0.1967 28.3950 43.6520 0.2185 26.6650 45.8000 0.2404 24.7190 47.7600 0.2622 22.6050 49.5470 File No.: 1501350.301 Page C-57 of C-173 Revision:

0 F0306-0 lR 2 e Structural Integrity Associates, Inc. 0.2841 20.4560 51.3330 0.3059 18.1260 52.9570 0.3278 15.6540 54.4260 0.3496 13.0810 55.7480 ale = 0.5000 Crack Depth Kdeepest Ksurface 4.3 7 0E-03 10.3810 8. 64 72 0.0437 25.9290 25.9670 0.0656 28.0600 30.8750 0.0874 28.6530 34.5880 0.1093 28.6170 38.1090 0.1311 27.8660 41.1480 0.1530 26.5750 43.8150 0.1748 24.8640 46.1800 0.1967 23.0280 48.7200 0.2185 20.9680 51.0350 0.2404 18.7430 53.1470 0.2622 16.4020 55.0740 0.2841 13.8960 56.3270 0.3059 11.2920 57.4000 0.3278 8.6359 58.3090 0.3496 6.5215 59.0650 a/c = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 8.9337 8.9515 0.0437 21.96 7 0 26.7200 0.0656 23.5500 31.6580 0.0874 23.8000 35.3370 0.1093 23.6620 38.8210 0.1311 22.9330 41.8100 0.1530 21.7 630 44.4210 0.1748 20.2530 46.7300 0.1967 18.3310 48.9810 0.2185 16.2110 51.0130 0.2404 13.9480 52.8540 0. 2 622 11.5890 54.5230 0.2841 9.1408 55.9050 0.3059 6.6539 57.1330 0.3278 5.1983 58.2230 0.3496 5.6320 59.1840 a/c = 1.0000 Crack Depth Kdeepest Ksurface 4.370E-03 7.7256 9.0943 0.0437 18.6870 27.0270 0.0656 19.8350 31.9390 0.0874 19.8200 35.5540 0.1093 19.6060 38.9730 0.1311 18.9030 41.8940 0.1530 17.8380 44.4360 0.1748 16.5010 46.6790 0.1967 14.5380 48.6850 0.2185 12.4010 50.4790 0.2404 10.1430 52.0920 0. 2622 7.8145 53.5480 0.2841 5.4789 55.0170 0.3059 4.1760 56.3550 0.3278 4.5406 57.5750 0.3496 4.9028 58.6880 Load Case 4:CD II Min 2-d SIF Input by User File No.: 1501350.301 Page C-5 8 of C-173 Revision:

0 F0306-01 R2 SJ Structural Integrity Associates, Inc."' The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\CDII.MNN No. of aspect ratios (a/c) in the tables = 8 ale = 0.1250 Crack Depth Kdeepest Ksurface 4.370E-03 0.0222 4.244E-03 0.0437 0.3938 0.0303 0.0656 0.6885 0.0512 0.0874 1.0215 0. 0772 0.1093 1.4110 0.1033 0.1311 1.8373 0.1331 0.1530 2.2957 0.1666 0.1748 2.7826 0.2038 0.1967 3.32 7 0 0.2419 0.2185 3.9025 0.2836 0.2404 4.5067 0.3288 0.2622 5.1370 0.3775 0.2841 6.0192 0.4389 0.3059 6.9599 0.5059 0.3278 7.9539 0.5786 0.3496 8.9950 0. 6571 ale = 0.1667 Crack Depth Kdeepest Ksurface 4.370E-03 0.0218 5.058E-03 0.0437 0.3879 0.0395 0.0656 0. 6767 0.0670 0.0874 1. 0020 0.100 7 0.1093 1.3839 0.1358 0.1311 1.8017 0.1754 0.1530 2.2510 0.2194 0.1748 2.7280 0.2678 0.1967 3.2515 0.3248 0.2185 3.8026 0.3878 0.2404 4.3785 0.4569 0. 2 622 4.9766 0.5320 0.2841 5. 7719 0.6266 0.3059 6.6134 0.7301 0.3278 7.4964 0.8425 0.3496 8.4152 0.9638 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 0.0216 5.686E-03 0.0437 0.3826 0.0467 0.0656 0.6665 0.079 2 0.0874 0.9852 0.1188 0.1093 1.3605 0.1609 0.1 311 1.7711 0.2080 0.1530 2.2126 0.2602 0.1748 2. 6811 0. 3172 0.1967 3.1876 0.3887 0.2185 3. 7187 0.4682 0.2404 4. 2715 0.5557 0. 2 622 4.8436 0.6512 0.2841 5.5699 0. 7714 0.3059 6.3327 0.9030 0.3278 7.1277 1.0460 0.3496 7.9495 1.2002 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03

0. 0211 6.584E-03 File No.: 1501350.301 Page C-59 of C-173 Revision: 0 F030 6-0 IR2 e Structural Integrity Associates, Inc." 0.0437 0.3741 0.0569 0.0656 0.6501 0.0967 0.0874 0.9587 0.1449 0.1093 1. 3236 0.1969 0.1311 1. 7228 0.2550 0.1530 2.1519 0.3188 0.1748 2.6070 0.3882 0.1967 3.0876 0.4806 0.2185 3.5884 0.5838 0.2404 4.1066 0.6978 0.2622 4.6393 0.8224 0.2841 5.2637 0.9794 0.3059 5.9103 1.1513 0.3278 6.5755 1.3382 0.3496 7.2543 1.5397 a/c = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 0.0203 7.392E-03 0.0437 0.3619 0.0671 0.0656 0. 62 91 0.1144 0.0874 0.9277 0.1712 0.1093 1.2775 0.2334 0.1311 1.6587 0.3027 0.1530 2.0668 0.3789 0.1748 2.4979 0.4616 0.1967 2.9488 0.5687 0.2185 3.4159 0.6873 0.2404 3.8966 0.8174 0. 2622 4.3880 0.9589 0.2841 4.9533 1.1248 0.3059 5.5343 1.3044 0.3278 6.1268 1. 497 4 0.3496 6.7245 1.7038 a/c = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 0.0187 8.739E-03 0.0437 0.3357 0.0844 0.0656 0.5836 0.1445 0.0874 0.8607 0.2159 0.1093 1.17 93 0.2954 0.1311 1. 5235 0.3839 0.1530 1.8890 0.4810 0.1748 2. 2719 0.5865 0.1967 2.6638 0. 7182 0.2185 3.0649 0.8627 0.2404 3. 4725 1.0198 0.2622 3.8834 1.1894 0.2841 4.3352 1. 368 9 0.3059 4.7894 1.5596 0.3278 5.2374 1. 7611 0.3496 4.8097 1.9731 ale = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 0.0165 9 .139E-03 0.0437 0.3007 0.0903 0.0656 0.5224 0.1549 0.0874 0.7693 0.2319 0.1093 1.0520 0.3153 0.1311 1. 3562 0. 4071 0.1530 1. 67 81 0.5069 0.1748 2.0141 0.6142 0.1967 2.3581 0.7399 FileNo.: 1501350.301 Page C-60 of C-173 Revision:

0 F0306-01 R 2 e Structural Integrity Associates, Inc. 0.2185 2.7091 0.2404 3.0639 0.2622 3.4195 0.2841 3.8004 0.3059 3.5065 0.3278 2.3892 0.3496 0.7737 ale = 1.0000 Crack Depth Kdeepest 4.370E-03 0.0147 0.0437 0.2706 0.0656 0.4698 0.0874 0.6909 0.1093 0.9429 0.1311 1.2131 0.1530 1. 4979 0.1748 1.7942 0.1967 2.0976 0.2185 2.4060 0.2404 2. 7160 0. 2 622 2.7269 0.2841 1.9188 0.3059 0.7885 0.3278 -0.6909 0. 3496 -2.5753 Load Case 5:Unload Max 2-d SIF Input by User 0.8753 1. 0200 1.1738 1. 3397 1.5147 1.6986 1. 8911 Ksurface 9.353E-03 0.0939 0.1614 0.2419 0.3274 0.4208 0.5216 0.6291 0.7489 0.8758 1.0094 1.1493 1. 3030 1. 4641 1. 6324 1. 8077 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\UNLD.MXN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-03 4.5828 0.0437 12.0180 0.0656 13.4190 0.0874 14.1820 0.1093 15.0110 0.1311 15.5920 0.1530 15.9850 0.1748 16.2300 0.1967 16.5440 0.2185 16.7510 0.2404 16.8690 0.2622 16.9120 0.2841 16.9790 0.3059 16.8920 0.3278 16.6650 0. 3496 16.3180 a/c = 0.1667 Crack Depth Kdeepest 4.370E-03 4.4990 0.0437 11.7 460 0.0656 13.0850 0.08 7 4 13.7990 0.1093 14.5130 0.1311 14.9710 0.1530 15.2340 0.1748 15.34 30 0.1967 15.5180 0.2185 15.5910 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 1.7085 5.1801 6.1774 6.9317 7. 7071 8.3929 9.0089 9.5682 10.1480 10.6920 11.2040 11. 6900 12.3930 13.0810 13.7550 14.4150 Ksurface 1.9733 5.9679 7.1119 7.9780 8.8877 9.7001 10.4380 11.1150 11.7930 1 2.42 70 Page C-61 of C-173 F0306-0l R2 S} Structural Integrity Associates, Inc. 0.2404 15.5790 13.0200 0.2622 15.4980 13.5780 0.2841 15.4620 14.3340 0.3059 15.3030 15.0640 0.3278 15.0360 15.7710 0.3496 14.6760 16.4540 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 4.4266 2.1766 0.0437 11.5160 6.5730 0.0656 12.8050 7.8297 0.0874 13.4790 8.7818 0.1093 14.1030 9.7950 0.1311 14.4650 10.7050 0.1530 14.6260 11.5360 0.1748 14.6290 12.3040 0.1967 14.6960 13.0590 0.2185 14.6650 13.7620 0.2404 14.5530 14.4190 0. 2622 14.3750 15.0330 0.2841 14.2590 15.8290 0.3059 14.0440 16.5920 0.3278 13.7440 17.3230 0.3496 13.3740 18.0240 a/c = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03

4. 3118 2.4670 0.0437 11.1560 7. 4371 0.0656 12.3690 8.8550 0.0874 12.9850 9.9301 0.1093 13.4760 11.0910 0.1311 13.6980 12.1410 0.1530 13.7130 13.1060 0.1748 13.5620 14.0050 0.1967 13.4730 14.8700 0.2185 13.2910 15.6740 0.2404 13.0340 16.4210 0.2622 12.7180 17.1170 0.2841 12.4840 17.9700 0.3059 12.1880 18.7790 0.3278 11.8410 19.5460 0.3496 11.4580 20.2720 a/c = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 4.1257 2.7118 0.0437 10.6260 8.1738 0.0656 11.7490 9.7367 0.0874 12.2960 10.9270 0.1093 12.6930 12.1510 0.1311 12.8300 13.2420 0.1530 12.7680 14.2330 0.1748 12.5490 15.1440 0.1967 12.3570 16.0650 0.2185 12.0790 16.9200 0.2404 11.7320 17.7150 0. 2622 11.3330 18.4580 0.2841 10.9760 19.2170 0.3059 10.5680 19.9270 0.3278 10.1200 20.5920 0.3496 9.6 453 21.2130 a/c = 0.5000 File No.: 1501350.301 Page C-62 of C-1 73 Revision:

0 F030 6-01 R2 e Structural Integrity Associates, Inc.'" Crack Depth Kdeepest 4.370E-03 3.7421 0.0437 9.5479 0.0656 10.4970 0.0874 10.9160 0.1093 11.1390 0.1311 11.1240 0.1530 10.9280 0.1748 10.5930 0.1967 10.2210 0.2185 9.7759 0.2404 9.2758 0.2622 8.7372 0.2841 8.1707 0.3059 7.5742 0.3278 6. 9626 0.3496 6.5215 a/c = 0.7500 Crack Depth *Kdeepest 4.370E-03 3.2207 0.0437 8.1012 0.0656 8.8345 0.0874 9.1085 0.1093 9.2680 0.1311 9.2303 0.1530 9.0456 0.1748 8.7486 0.1967 8.3106 0.2185 7.8064 0.2404 7.2539 0.2622 6.6687 0.2841 6.0729 0.3059 5.4651 0.3278 5.1798 0.3496 5.4923 a/c = 1.0000 Crack Depth Kdeepest 4.370E-03 2.7854 0.0437 6.9029 0.0656 7.4631 0.0874 7.6230 0.1093 7.7325 0.1311 7.6786 0.1530 7.5046 0.1748 7.2401 0.1967 6.7572 0.2185 6.2153 0.2404 5.6318 0. 2 622 5.0232 0.2841 4.4249 0.3059 4.1478 0.3278 4.3980 0.3496 4.6465 Load Case 6:Unload Min 2-d SIF Input by User Ksurface 3.1136 9.3831 11.1850 12.5680 13.8860 15.0390 16.0650 16.9890 17.9970 18.9330 19.8060 20.6210 21.2030 21.7290 22.2030 22.6290 Ksurface 3.2232 9.6574 11.4740 12.8480 14.1570 15.2940 16.3020 17.2070 18.1070 18.9360 19.7030 20.4150 21.0320 21.6020 22.1270 22.6130 Ksurface 3.2746 9.7700 11.5790 12.9330 14.2200 15.3350 16.3190 17.2010 18.0090 18.7460 19.4240 20.0500 20.6890 21.2860 21.8470 22.3740 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\UNLD.MNN No. of aspect ratios (a/c) in the tables = 8 a/c = 0.1250 Crack Depth Kdeepest Ksurface File No.: 1501350.301 Revision:

0 Page C-63 of C-1 73 F0306-01 R2 e Structural Integrity Associates, Inc. 4.370E-03 0.5123 0.1855 0.0437 1. 7438 0.5852 0.0656 2.2156 0. 7166 0.0874 2. 64 71 0.8279 0.1093 3.1360 0.9394 0.1311 3.6276 1.0445 0.1530 4.1249 1.1452 0.1748 4.6293 1.2429 0.1967 5.1954 1. 3412 0.2185 5.7770 1.4383 0.2404 6.3738 1.5347 0. 2 622 6.9854 1. 6307 0.2841 7.8412 1.7631 0.3059 8.7341 1.8987 0.3278 9.6619 2.0377 0.3496 10.6220 2.1801 ale = 0.1667 Crack Depth Kdeepest Ksurface 4.370E-03 0.5030 0.2145 0.0437 1.7076 0.6806 0.0656 2.1662 0.8359 0.0874 2.5840 0.9685 0.1093 3.0515 1.1054 0.1311 3.5200 1. 2360 0.1530 3.9923 1. 3625 0.1748 4.4699 1.4863 0.1967 4.9989 1. 617 3 0.2185 5.5403 1.7486 0.2404 6.0940 1.8806 0. 2 622 6.6595 2.0138 0.2841 7.4193 2.1876 0.3059 8.2086 2.3665 0.3278 9.0255 2.5505 0.3496 9.8678 2.7397 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 0.4950 0.2367 0.0437 1.6767 0.7538 0.0656 2.1243 0.9276 0.0874 2.5308 1.0767 0.1093 2.9810 1.2332 0.1311 3.4306 1.3834 0.1530 3.8827 1. 52 98 0.1748 4.3388 1.6737 0.1967 4.8379 1.8299 0.2185 5.3472 1.9876 0.2404 5.8663 2.1472 0. 2 622 6.3950 2.3091 0.2841 7.0789 2.5149 0.3059 7.7862 2. 7272 0.3278 8.5153 2.9460 0.3496 9.2642 3.1713 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 0.4823 0.2685 0.0437 1.6282 0.8585 0.0656 2.0589 1.0586 0.0874 2.4479 1. 2313 0.1093 2.8719 1.4159 0.1311 3.2932 1.5943 0.1530 3.7149 1. 7 692 File No.: 1501350.301 Page C-64 of C-173 Revision:

0 F0306-0I R2 e Structural Integrity Associates, Inc." 0.1748 4.1386 1.9420 0.1967 4.5935 2.1346 0.2185 5.0549 2.3303 0.2404 5.5227 2.5295 0. 2622 5.9966 2.7327 0.2841 6.5688 2.9845 0.3059 7.1554 3.2447 0.3278 7.7552 3. 5135 0.3496 8.3668 3.7906 a/c = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 0.4617 0.2954 0.0437 1. 5571 0.9495 0.0656 1.9679 1.1742 0.0874 2.3385 1. 3694 0.1093 2.7360 1.5724 0.1311 3.1291 1.7680 0.1530 3.5207 1.9593 0.1748 3.9127 2.1479 0.1967 4.3261 2. 3626 0.2185 4.7433 2.5807 0.2404 5.1642 2.8028 0.2622 5.5886 3.0291 0.2841 6.0894 3.2807 0.3059 6.6002 3.5389 0.3278 7 .1197 3.8038 0.3496 7.6461 4.0755 a/c = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 0.4191 0.3395 0.0437 1.4107 1.0996 0.0656 1. 7810 1.3651 0.0874 2 .1142 1.5982 0.1093 2.4594 1. 8312 0.1311 2.7972 2.0550 0.1530 3.1305 2.2730 0.1748 3.4609 2.4873 0.1967 3.7952 2.7387 0.2185 4.1283 2.9940 0.2404 4.4603 3.2539 0.2622 4.7909 3.5186 0.2841 5.1581 3.7664 0.3059 5.5267 4.0177 0.3278 5.8943 4.2725 0.3496 5.9705 4.5310 ale = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03

0. 3613 0.3516 0.0437 1.2145 1.1361 0.0656 1.5318 1.4088 0.0874 1. 8163 1. 6473 0.1093 2.1170 1.8835 0.1311 2. 4117 2.1091 0.1530 2.7028 2.3278 0.1748 2.9916 2.5417 0.1967 3. 2710 2.7749 0.2185 3.5478 3.0089 0.2404 3.8222 3.2443 0. 2 622 4.0939 3.4817 0.2841 4.3907 3. 7193 0.3059 4.4556 3.9595 0.3278 4.2761 4.2022 File No.: 1501350.301 Page C-65 of C-173 Revision:

0 F0306-0l R2 SJ Structural Integrity Associates, Inc. 0.3496 3.9452 ale = 1.0000 Crack Depth Kdeepest 4.370E-03 0.3130 0.0437 1.0506 0.0656 1. 3238 0.0874 1.5679 0.1093 1. 8311 0.1311 2.0894 0.1530 2.3450 0.1748 2.5987 0.1967 2.8328 0.2185 3.0634 0.2404 3.2904 0.2622 3.4015 0.2841 3.2795 0.3059 3.0569 0.3278 2. 7272 0.3496 2.2743 Load Case 7:IAS Max 2-d SIF Input by User 4.4478 Ksurface 0.3573 1.152 6 1.4280 1. 668 4 1.9045 2.1292 2.3461 2.5575 2.7743 2.9894 3.2036 3.4174 3.6447 3.8737 4.1047 4.3377 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\INAUX.MXN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-03 15.2760 0.0437 39.8790 0.0656 44.0560 0.0874 45.8970 0.1093 47.7650 0.1311 48.6540 0.1530 48.7860 0.1748 48.3150 0.1967 47.9010 0.2185 47.0250 0.2404 45.7510 0.2622 44.1360 0.2841 41.8980 0.3059 38.9510 0.3278 35.3580 0.3496 31.1950 a/c = 0.1667 Crack Depth Kdeepest 4.370E-03 14.9970 0.0437 38.9710 0. 0656 42.9480 0.0874 44.6370 0.1093 46.1330 0.1311 46.6220 0.1530 46.3300 0.1748 45.4150 0.1967 44.5790 0.2185 43.3060 0.2404 41.6610 0.2622 39.7050 0.2841 37.3500 0.3059 34.4270 0.3278 30.9990 0.3496 27.1320 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 5.6875 17.2900 20.6390 23.1720 25.7840 28.0900 30.1530 32.0170 33.9550 35.7660 37.4630 39.0570 41.3660 43. 6110 45.7950 47.9150 Ksurface 6.5691 19.9180 23.7560 26.6550 29.7040 32.4170 34.8670 37.1030 39.3340 41.3980 43.3100 45.0830 47.4830 49.7740 51.9600 54.0420 Page C-66 of C-173 F0306-0I R2 e Structural Integrity Associates, Inc. ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 14.7560 7.2461 0.0437 38.2030 21.9370 0.0656 42.0180 26.1480 0.0874 43.5860 29.3300 0.1093 44.7890 32.7150 0.1311 44.9670 35.7410 0.1530 44.3470 38.4900 0.1748 43.0880 41.0120 0.1967 41.9260 43.4690 0.2185 40.3460 45.7290 0.2404 38.4160 47.8070 0.2622 36.1990 49.7180 0.2841 33.7540 52.1880 0.3059 30.8550 54.5140 0.3278 27.5590 56.7000 0.3496 23.9280 58.7500 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 14.3730 8. 2130 0.0437 37.0030 24.8190 0.0656 40.5750 29.5660 0.0874 41.9640 33.1510 0.1093 42.7400 37.0150 0.1311 42.4660 40.4910 0.1530 41.3730 43.6660 0.1748 39.6210 46.6010 0.1967 37.9900 49.3820 0.2185 35.9690 51.9210 0.2404 33.6330 54.2380 0. 2 622 3 1.0430 56.3490 0.2841 28.4 7 30 58.9170 0.3059 25.6130 61.2900 0.3278 22.5150 63.4740 0.3496 19.2330 65.4740 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 13.7530 9.0284 0.0437 35.2350 27.2800 0.0656 38.5150 32.5080 0.0874 39.6910 36.4720 0.1093 40.1760 40.5320 0.1311 39.6530 44.1290 0.1530 38.3510 47.3680 0.1748 36.4280 50.3180 0.1967 34.5200 53.2470 0.2185 32.2570 55.9190 0.2404 29.7110 58.3560 0. 2622 26.9470 60.5750 0.2841 24.1130 62.7870 0.3059 21.0440 64.7910 0.3278 17.7900 66.5960 0.3496 14.4030 68.2120 ale = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 12.4750 10.3660 0.0437 31.6430 31.3180 0.0656 34.3630 37.3400 0.0874 35.1450 41.9310 F il e No.: 1501350.301 Page C-67 of C-1 7 3 Revision: 0 F0306-01R2 e Structural Integrity Associates, Inc. 0.1093 35.1080 0.1311 34.1530 0.1530 32.4990 0.1748 30.3000 0.1967 27.9290 0.2185 25.2670 0.2404 22.3890 0. 2 622 19.3590 0.2841 16.1060 0.3059 12.7240 0.3278 9.2694 0.3496 6.5215 a/c = 0.7500 Crack Depth Kdeepest 4.370E-03 10.7370 0.0437 26.8200 0.0656 28.8510 0.0874 29.1970 0.1093 29.0250 0.1311 28.0920 0.1530 26.5870 0.1748 24.6430 0.1967 22.1720 0.2185 19.4430 0.2404 16.5270 0. 2622 13.4840 0.2841 10.3160 0.3059 7.0906 0.3278 5.2080 0.3496 5.7058 ale = 1.0000 Crack Depth Kdeepest 4.370E-03 9.2864 0.0437 22.8270 0.0656 24.3070 0.0874 24.3160 0.1093 24.0430 0.1311 23.1390 0.1530 21.7670 0.1748 20.0390 0.1967 17.5230 0.2185 14.7790 0.2404 11.8760 0.2622 8.8788 0.2841 5.8584 0.3059 4.1909 0.3278 4.6159 0.3496 5.0381 Load Case 8:IAS Min 2-d SIF Input by User 46.2880 50.0600 53.3760 56.3200 59.4770 62.3540 64.9740 67.3600 68.9130 70.2350 71.3440 72.2570 Ksurface 10.7310 32.2340 38.3010 42.8570 47.1710 50.8820 54.1300 57.0050 59.8050 62.3310 64.6140 66.6820 68.3900 69.9020 71.2350 72.4030 Ksurface 10.9030 32.6100 38.6490 43.1320 47.3690 50.9970 54.1600 56.9520 59.4490 61.6800 63.6820 65.4850 67.2970 68.9440 70.4380 71.7940 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\INAUX.MNN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-03

-0.2444 0.0437 -0.3412 0.0656 -0.1435 0.0874 0 .1357 0.1093 0.4708 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface -0.0943 -0.2715 -0.3108 -0.3311 -0.3513 Page C-68 of C-173 F0306-01 R2

Integrity Associates, Inc."' 0.1311 0.8610 -0.3623 0.1530 1.2979 -0.3653 0.1748 1.7747 -0.3610 0.1967 2.3066 -0.3554 0.2185 2.8784 -0.3436 0.2404 3.4863 -0.3260 0.2622 4.1265 -0.3027 0.2841 5.0222 -0.2796 0.3059 5.9880 -0.2497 0.3278 7. 0173 -0.2128 0.3496 8.1021 -0.1688 ale = 0.1667 Crack Depth Kdeepest Ksurface 4.370E-03

-0.2399 -0.1088 0.0437 -0.3307 -0.3091 0.0656 -0.1347 -0.3513 0.0874 0.1399 -0.3715 0.1093 0.4748 -0.3916 0.1311 0.8647 -0.4015 0.1530 1.3010 -0.4023 0.1748 1. 7771 -0.3949 0.1967 2. 2972 -0.3780 0.2185 2.8530 -0.3520 0.2404 3.4408 -0.3171 0. 2 622 4.0564 -0.2734 0.2841 4.8701 -0.2217 0.3059 5.7392 -0.1592 0.3278 6.6578 -0.0856 0.3496 7.6179 -1.203E-03 ale = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03* -0.2360 -0.1200 0.0437 -0.3221 -0.3380 0.0656 -0.1277 -0.3823 0.0874 0.1430 -0.4024 0.1093 0.4772 -0.4225 0.1311 0.8662 -0.4314 0.1530 1. 3015 -0.4305 0.1748 1. 77 61 -0.4208 0.1967 2.2862 -0.3953 0.2185 2.8287 -0.3583 0.2404 3.3998 -0.3100 0.2622 3.9950 -0.2506 0.2841 4.7436 -0.1770 0.3059 5.5359 -0.0894 0.3278 6.3666 0.0123 0.3496 7.2 2 77 0.1278 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03

-0.2298 -0.1359 0.0437 -0.3087 -0.3792 0.0656 -0.1173 -0.4266 0.0874 0.1471 -0.4463 0.1093 0.4795 -0.4664 0.1311 0.8664 -0.4739 0.1530 1.2991 -0.4706 0.1748 1.7707 -0.4575 0.1967 2.2649 -0:_4196 0.2185 2.7870 -0.3669 0.2404 3.3323 -0.2994 0. 2622 3.8966 -0.2175 0.2841 4.5486 -0.1123 File No.: 1501350.301 Page C-69 of C-173 Revision:

0 F0306-0IR2 e Structural Integrity Associates, Inc."' 0.3059 5.2276 0. 0115 0.3278 5.9282 0.1536 0.3496 6.6431 0. 3138 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03

-0.2197 -0.1492 0.0437 -0.2888 -0.4129 0.0656 -0.1003 -0.4622 0.0874 0.1588 -0.4808 0.1093 0.4824 -0.4953 0.1311 0.8569 -0.4948 0.1530 1.2735 -0.4813 0.1748 1. 7254 -0.4562 0.1967 2.1962 -0.4078 0.2185 2.6904 -0.3435 0.2404 3.2034 -0.2636 0. 2 622 3.7307 -0.1684 0.2841 4.3305 -0.0493 0.3059 4.9496 0. 0872 0.3278 5.5815 0.2410 0.3496 6.2177 0. 4116 a/c = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03

-0.1991 -0.1712 0.0437 -0.2498 -0.4678 0.0656 -0.0687 -0.5197 0.0874 0.1775 -0.5363 0.1093 0.4813 -0.5406 0.1311 0.8288 -0.5258 0.1530 1. 2114 -0.4945 0.1748 1.6224 -0.4485 0.1967 2.0454 -0.3820 0.2185 2.4835 -0.2980 0.2404 2.9318 -0.1970 0.2622 3.3861 -0.0795 0.2841 3.8838 0. 0626 0.3059 4.3843 0.2202 0.3278 4.8756 0.3926 0.3496 4.4750 0.5791 a/c = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03

-0.1710 -0.1771 0.0437 -0.1969 -0.4787 0.0656 -0.0275 -0.5273 0.0874 0.1987 -0.5384 0.1093 0.4713 -0.5383 0.1311 0.7805 -0.5194 0.1530 1.1187 -0.4844 0.1748 1.4800 -0.4353 0.1967 1.8591 -0.3682 0.2185 2.2502 -0.2867 0.2404 2.6485 -0.1916 0.2622 3.0497 -0.0835 0.2841 3.4761 0.0432 0.3059 3.2815 0.1827 0.3278 1.8430 0.3344 0.3496 -0.3031 0.4977 a/c = 1.0000 Crack Depth Kdeepest Ksurface 4.370E-03

-0.1476 -0.1799 FileNo.: 1501350.301 Page C-70 of C-173 Revision:

0 F0306-0IR2 e Structural Integrity Associates, Inc. 0.0437 -0.1541 0.0656 4.512E-03 0.0874 0.2129 0.1093 0.4585 0.1311 0.7349 0.1530 1.0354 0.1748 1.3545 0.1967 1.6957 0.2185 2.04 60 0.2404 2.4010 0.2622 2.5997 0.2841 1.5904 0.3059 0.1449 0.3278 -1.79 67 0.3496 -4.3 229 Load Case 9:Residual Type: Stress Coefficient Coefficient Coefficient Coefficient Coefficients Input co C1 C2 C3 30.0000 0.0000 0.0000 0.0000 Load Case 10:0BE -0.4821 -0.5278 -0.5345 -0.5311 -0.5091 -0.4717 -0.4209 -0.3540 -0.2754 -0.1858 -0.086 3 0. 0271 0.1511 0.2852 0.4289 by User Type: Stress Coefficients Input by User Coefficient CO Coefficient C1 Coefficient C2 Coefficient C3 Load Case 11:DW 3.3100 0.0000 0.0000 0.0000 Type: Stress Coefficients Input by User Coefficient CO Coefficient C1 Coefficient C2 Coefficient C3 Load Case 12:SLID Max 2-d SIF Input by User 0. 7290 0.0000 0.0000 0.0000 The SIF originally read from C:\Users\clohse\Docurnents\ANSYS\PGE\1501350\TIFFANY\SLID.MXN No. of aspect ratios (a/c) ale= 0.1250 Crack Depth Kdeepest 4.370E-03

4. 6 7 60 0.0437 12.2520 0.0656 13.6730 0.0874 14.4430 0.1093 15.2790 0.1311 15.8610 0.1530 16.2510 0.1748 16.4900 0.1967 16.7970 0.2185 16.9950 0.2404 17.1020 0.2622 17.1310 0.2841 17.1790 0.3059 17.0690 0.3278 16.8160 0.3496 16.4 370 ale = 0.1667 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 1. 7434 5.2852 6.30 22 7.0711 7.8616 8.560 6 9.1883 9.7581 10.3480 10.9030 11.4250 11. 9190 1 2.6350 1 3.3360 14.02 20 14.6940 Page C-71 of C-173 F0306-0 I R2 e Structural Integrity Associates, Inc. Crack Depth Kdeepest Ksurface 4.370E-03 4.5904 2. 0135 0.0437 11.9740 6.0889 0.0656 13.3330 7.2553 0.0874 14.0530 8.1380 0.1093 14;7720 9.0653 0.1311 15.2290 9.8931 0.1530 15.4870 10.6440 0.1748 15.5870 11.3340 0.1967 15.7530 12.0250 0.2185 15.8150 12.6700 0.2404 15.7900 13.2740 0.2622 15.6930 13.8410 0.2841 15.6380 14.6100 0.3059 15.4570 15.3530 0.3278 15.1640 16.0710 0.3496 14.7760 16.7660 a/c = 0.2000 Crack Depth Kdeepest Ksurface 4.370E-03 4.5166 2.2210 0.0437 11.7390 6.7060 0.0656 13.0470 7.9874 0.0874 13.7270 8.9577 0.1093 14.3540 9.9902 0.1311 14.7130 10.9170 0.1530 14.8670 11.7640 0.1748 14.8590 12.5460 0.1967 14.9160 13.3150 0.2185 14.8720 14.0300 0.2404 14.7450 14.6980 0.2622 14.5510 15.3220 0.2841 14.4160 16.1310 0.3059 14.1790 16.9070 0.3278 13.8550 17.6500 0.3496 13.4590 18.3620 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 4.3994 2.5173 0.0437 11.3720 7.5875 0.0656 12.6030 9.0331 0.0874 13.2230 10.1290 0.1093 13.7150 11.3120 0.1311 13. 9320 12.3810 0.1530 13.9370 13.3650 0.1748 13.7730 14.2790 0.1967 13.6710 15.1600 0.2185 13.-4740 15.9770 0.2404 13.2000 16.7360 0.2622 12.8650 17.4430 0.2841 12.6130 18.3100 0.3059 12.2960 19.1320 0.3278 11.9270 19.9100 0.3496 11.5210 20.6450 a/c = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 4.2095 2. 7 672 0.0437 10.8320 8.3390 0.0656 11.9710 9.9322 0.0874 12.5210 11.1450 0.1093 12.9170 12.3920 0.1311 13.0480 13.5030 File No.: 1501350.301 Page C-72 of C-1 73 Revision:

0 F0306-01R2 e Structural Integrity Associates, Inc."' 0.1530 12.9750 14.5120 0.1748 12.7420 15.4400 0.1967 12.5360 16.3760 0.2185 12.2410 17.2450 0.2404 11.8760 18.0540 0.2622 11.4580 18.8080 0.2841 11.0820 19.5780 0.3059 10.6520 20.2990 0.3278 10.1820 20.9720 0.3496 9.6836 21.6010 a/c = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 3.8181 3.1771 0.0437 9.7328 9.5724 0.0656 10.6940 11.4090 0.0874 11.1150 12.8180 0.1093 11.3350 14.1610 0.1311 11.3110 15.3350 0.1530 11.1030 16.3790 0.1748 10.7520 17.3190 0.196 7 10.3640 18.3430 0.2185 9.9006 19.2950 0.2404 9.3812 20.1810 0. 2 622 8.8225 21.0090 0.2841 8.2344 21.5980 0.3059 7.6156 22.1290 0.3278 6.9812 22.6080 0.3496 6.5215 23.0390 a/c = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 3.2861 3.2889 0.0437 8.2576 9.8521 0.0656 8.9998 11.7040 0.0874 9.2731 13.1030 0.1093 9.4290 14.4360 0.1311 9.3833 15.5940 0.1530 9.1875 16. 6200 0.1748 8.8769 17.5410 0.1967 8.4222 18.4560 0.2185 7.9000 19.2980 0.2404 7.3284 20.0760 0.2622 6. 7235 20.7990 0.2841 6.1071 21.4250 0.3059 5.4784 22.0010 0.3278 5.1800 22.5320 0.3496 5.4938 23.0230 ale = 1.0000 Crack Depth Kdeepest Ksurface 4.370E-03 2.8420 3.3414 0.0437 7.0357 9.9669 0.0656 7.6020 11.8110 0.0874 7.7 596 13.1900 0.1093 7.8652 14.5010 0.1311 7.8040 15.6350 0.1530 7.6199 16.6360 0.1748 7.3434 17.5330 0.1967 6.8439 18.3550 0.2185 6.2842 19.1040 0.2404 5.6820 19.7920 0.2622 5.0543 20.4260 0.2841 4.4367 21.0750 0.3059 4.1481 21. 6810 File No.: 1501350.301 Page C-73 of C-173 Revision:

0 F0306-0 I R2 e Structural Integrity Associates, Inc. 0.3278 0.3496 4.3995 4.6493 Load Case 13:SLID Min 2-d SIF Input by User 22.2480 22.7820 The SIF originally read from C:\Users\clohse\Documents\ANSYS\PGE\1501350\TIFFANY\SLID.MNN No. of aspect ratios (a/c) a/c = 0.1250 Crack Depth Kdeepest 4.370E-03 0.5070 0.0437 1.7294 0.0656 2.1993 0.0874 2. 6297 0.1093 3.1175 0.1311 3.6085 0.1530 4.1054 0.1748 4.6096 0.1967 5.1754 0.2185 5.7569 0.2404 6.3539 0. 2 622 6.9657 0.2841 7.8217 0.3059 8. 7150 0.3278 9.6436 0.3496 10.6050 ale= 0.1667 Crack Depth Kdeepest 4.370E-03 0.4979 0.0437 1.6935 0.0656 2.1503 0.0874 2.5671 0.1093 3.0337 0.1311 3.5016 0.1530 3.9737 0.1748 4. 4513 0.1967 4.9802 0.2185 5. 5217 0.2404 6.0756 0. 2 622 6.6415 0.2841 7.4017 0.3059 8.1915 0.3278 9.0091 0.3496 9.8522 a/c = 0.2000 Crack Depth Kdeepest 4.370E-03 0.4900 0.0437 1. 6629 0.0656 2.1088 0.0874 2.5142 0.1093 2.9637 0.1311 3.4129 0.1530 3.8648 0.1748 4.3210 0.1967 4.8203 0.2185 5. 32 98 0.2404 5.8493 0.2622 6.3784 0.2841 7.0628 0.3059 7.7706 0.3278 8.5004 File No.: 1501350.301 Revision:

0 in the tables = 8 Ksurface 0.1836 0.5793 0.7095 0.8199 0.9304 1.0347 1.1348 1.2318 1.3295 1. 4260 1. 5218 1. 6173 1. 7489 1.8839 2.0222 2.1639 Ksurface 0.2122 0.6737 0.8277 0.9593 1. 0951 1.2247 1. 3503 1.4733 1. 6035 1.7340 1. 8 654 1.9980 2.1709 2.3490 2.5323 2. 7208 Ksurface 0.2343 0.7463 0.9185 1. 0664 1. 2217 1.3709 1.5162 1. 6592 1.8145 1. 9714 2 .1302 2.2914 2.4963 2.7077 2.9257 Page C-74 of C-173 F0306-0IR2 e Structural/nlegrily Associates, Inc. 0.3496 9.2501 3.1502 ale = 0.2500 Crack Depth Kdeepest Ksurface 4.370E-03 0.4774 0.2657 0.0437 1. 6148 0.8499 0.0656 2.0438 1.0483 0.0874 2.4320 1.2197 0.1093 2.8554 1.4029 0.1311 3.2764 1.5800 0.1530 3.6982 1. 7537 0.1748 4.1223 1. 9254 0.1967 4.5774 2.1169 0.2185 5.0392 2. 3116 0.2404 5.5075 2.5100 0. 2622 5.9821 2. 712 3 0.2841 6.5548 2.9630 0.3059 7 .1420 3.2224 0.3278 7.7426 3.4902 0.3496 8.3548 3.7665 ale = 0.3330 Crack Depth Kdeepest Ksurface 4.370E-03 0.4570 0.2923 0.0437 1.5443 0.9401 0.0656 1.9536 1.1629 0.0874 2.3234 1.3566 0.1093 2.7204 1.5581 0.1311 3.1133 1. 7524 0.1530 3.5052 1.9424 0.1748 3.8976 2.1299 0.1967 4.3114 2.3434 0.2185 4.7291 2.5605 0.2404 5.1506 2.7816 0. 2 622 5.5757 3.0070 0.2841 6. 0772 3.2576 0.3059 6.5888 3.5150 0.3278 7.1091 3.7792 0.3496 7. 6362 4.0501 ale = 0.5000 Crack Depth Kdeepest Ksurface 4.370E-03 0.4148 0.3359 0.0437 1. 3992 1.0887 0.0656 1.7682 1.3521 0.0874 2.1008 1.5834 0.1093 2.4458 1.8148 0.1311 2.7836 2. 0371 0.1530 3 .1172 2.2538 0.1748 3.4482 2.4670 0.1967 3.7831 2. 7171 0.2185 4 .1170 2. 9712 0.2404 4.4497 3.2300 0. 2 622 4.7811 3.4937 0.2841 5.1492 3.7408 0.3059 5.5187 3.9914 0.3278 5. 8872 4.2457 0.3496 5. 9572 4.5037 ale = 0.7500 Crack Depth Kdeepest Ksurface 4.370E-03 0.3576 0.3479. 0.0437 1.2047 1.1249 0.0656 1.5210 1.3954 File No.: 1501350.301 Page C-75 of C-173 Revision:

0 F030 6-0lR2 e Structural Integrity Associates, Inc. 0.0874 1.8051 1. 6322 0.1093 2.1056 1.8667 0.1311 2.4004 2.0909 0.1530 2.6918 2.3083 0.1748 2.9811 2. 5211 0.1967 3.2612 2.7531 0.2185 3.5389 2.9861 0.2404 3.8141 3.2206 0.2622 4.0867 3.4570 0.2841 4.3843 3.6939 0.3059 4.4445 3.9333 0.3278 4.2545 4.1755 0.3496 3.9093 4.4204 a/c = 1.0000 Crack Depth Kdeepest Ksurface 4.370E-03 0.3098 0.3535 0.0437 1.0423 1.1413 0.0656 1.3147 1.4144 0.0874 1. 5585 1. 6531 0.1093 1.8216 1.8877 0.1311 2.0801 2.1109 0.1530 2.3359 2.3266 0.1748 2.5901 2.5369 0.1967 2.8 2 49 2.7526 0.2185 3.0563 2.9668 0.2404 3.2842 3.1801 0.2622 3.3935 3.3932 0.2841 3.2636 3.6197 0.3059 3.0308 3.8480 0.3278 2.6884 4.0782 0.3496 2.2199 4.3106 Total Load Sub-Blocks:

6 Load Sub-Block

1. 1 Load Sub-block Name: Heatup/Cooldown Maximum Load Case Multiplier Load Case 1.0000 HU/CD Max 1.0000 Residual 1.0000 DW Minimum Load Case Multiplier Load Case 1.0000 HU/CD Min 1.0000 Residual 1.0000 DW Growth Law: ASMEAusteniticAir Cycles/Time:

140 Temperature:

650 Load Sub-Block

1. 2 Load Sub-block Name: Cooldown II Maximum ID ID Load Case Multiplier Load Case ID 1.0000 CD II Max 1.0000 Residual 1.0000 DW Minimum Load Case Multiplier Load Case ID 1.0000

• CD II Min 1.0000 Residual 1.0000 DW Growth Law: ASMEAusteniticAir File No.: 1501350.301 Revision:

0 Page C-76 of C-173 F03 06-0 IR2 e Structural Integrity Associates, Inc. Cycles/Time:

8 Temperature:

650 Load

1. 3 Load Sub-block Name: Inadvertent Aux Spray Maximum Load Case Multiplier 1.0000 1.0000 1.0000 Minimum Load Case Multiplier 1.0000 1.0000 1.0000 Load Case ID IAS Max Residual DW Load Case ID IAS Min Residual DW Growth Law: ASMEAusteniticAir Cycles/Time:

2 Temperature:

650 Load Sub-Block

1. 4 Load Sub-block Name: Unload Maximum Load Case Multiplier 1.0000 1.0000 1.0000 Minimum Load Case Multiplier 1.0000 1.0000 1.0000 Load Case ID Unload Max Residual DW Load Case ID Unload Min Residual DW Growth Law: ASMEAusteniticAir Cycles/Time:

2744 Temperature:

650 Load Sub-Block

1. 5 Load Sub-block Name: OBE Maximum Load Case Multiplier 2.0000 1.0000 1.0000 Minimum Load Case Multiplier 0.0000 1.0000 1.0000 Load Case ID OBE Unload Max DW Load Case ID OBE Unload Max DW Growth Law: ASMEAusteniticAir Cycles/Time:

16 Temperature:

650 Load Sub-Block

1. 6 Load Sub-block Name: Step Load Inc/Dec Maximum Load Case Multiplier 1.0000 1.0000 1.0000 Minimum Load Case Multiplier 1.0000 1.0000 1.0000 Load Case ID SLID Max DW Residual Load Case ID SLID Min DW Residual Growth Law: ASMEAusteniticAir File No.: 1501350.301 Revision:

0 Page C-77 of C-173 F0306-0IR2 e Structural Integrity Associates, Inc."' Cycles/Time:

210 Temperature:

650 Material:

1 Sample Material 1: Only a sample *****************************************************************************

Austenitic Stai nless Steel in Air environment (U.S. Customary Units) The Fatigue Crack Growth Rate (in/cycle) is given by:

• da/dN = Co*(Delta K)An where Delta K = Kmax -Kmin n =the slope of the l og (da/dN) vers us log (Delta K) 3.3 Co = a scaling constant Co C*S C is given by: T is the metal temperature in deg F S is a scaling parameter to account for R ratio and is given by: s 1.0 1.0 + 1.8

• R -4 3.35 + 57.97

• R where R = Kmin I Kmax for R <= 0 for 0 < R <= 0.79 for 0.79 < R < 1 **************************************************************

No. of Data in the KIC Table = 3 Crack D epth 0.0000 0.1000 2.0000 messages/Warnings:

KIC 500.0000 500.0000 500.0000 Number o f Warnings in Inputs: 0 ----------ANALYS IS RESULTS ---------STR E SS INTENSITY FACTORS Load Case # 1: HU/CD ------------

Crack a c c/a = 0.0800 0.0900 3.9063 0.3125 0.3516 File No.: 1501350.301 Revision:

0 Max Dimensions a/t 0.1831 0.2059 ------------

K c/a a 3.9063 27.7 22 7 3.9063 28.0 975 at tips c 21.82 75 22.9458 Page C-78 of C-173 F0306-0 I R2 S) Structural Integrity Associates, Inc."' 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0. 7813 0.8203 0.8594 0.8984 0.9375 0.9766 1. 0156 1.0547 1.0938 1.1328 1.1719 1.2109 1.2500 4.1563 0.3325 0.3741 0.4156 0. 4572 0.4988 0.5403 0.5819 0. 6234 0.6650 0.7066 0.7481 0.7897 0.8313 0.8728 0.9144 0.9559 0.9975 1.0391 1.0806 1.1222 1.1638 1.2053 1.2469 1.2884 1.3300 4.4063 0.3525 0.3966 0.4406 0.4847 0.5288 0.5728 0.6169 0.6609 0.7050 0.7491 0.7931 0. 8372 0.8813 0.9253 File No.: 1501350.301 Revision:

0 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 28.3497 28.5794 28.5318 28.4842 28.2300 27.9503 27.5397 27.0745 26.6325 26.2120 25.7553 25.2265 24.6845 24.0677 23.4509 22.7663 22.0792 21.4100 20.7459 20.0343 19.2903 18.5195 17.7102 28.0264 28.4201 28.7031 28.9637 28.9474 28.9311 28.7086 28.4606 28.0820 27.6487 27.2395 26.8524 26.4283 25.9307 25.4196 24.8316 24.2436 23.5855 22.9249 2 2.2746 21.6271 20.9263 20.1892 19.4214 18.6095 28.3125 28.7264 29.0449 29.3411 29.3623 29.3834 29.2001 28.9915 28.6532 28.2607 27.8915 27.5437 27.1582 26.6978 24.1270 25.2990 26.3574 27.4157 28.3907 29.3554 30.2677 31.1581 32.0239 32.8671 33.6861 34.4571 35.2182 35.9235 36.6288 37.2760 37.9212 38.6700 39.4482 40.1935 40.9164 41.6171 42.2858 21.2039 22.2909 23.4404 24.5810 25. 6110 26.6410 27.5900 28.5289 29.4167 30.2832 31.1262 31.9476 32.7457 33.4976 34.2400 34.9286 35.6173 36.2502 36.8811 37.6280 38.4077 39.1563 39.8838 40.5902 41.2663 20.5240 21.5761 22.6855 23.7861 24.7786 25.7712 26.6844 27.5879 28.4410 29.2729 30.0854 30.8801 31.6526 32.3811 Page C-79 of C-173 F0306-0J R2 SJ Structural Integrity Associates, Inc. 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.9694 1.0134 1.0575 1.1016 1.1456 1.1897 1.2338 1.2778 1. 3219 1. 3659 1.4100 4.6563 0.3725 0.4191 0.4656 0.5122 0.5588 0.6053 0.6519 0.6984 0.7450 0.7916 0.8381 0.8847 0.9313 0.9778 1. 0244 1. 0709 1.1175 1.1641 1.2106 1. 2572 1.3038 1.3503 1. 3969 1.4434 1. 4900 4.9063 0.3925 0.4416 0.4906 0.5397 0.5888 0.6378 0.6869 0.7359 0.7850 0.8341 0.8831 0.9322 0.9813 1.0303 1.0794 1.1284 1.1775 1.2266 1. 2756 1.3247 1.3738 1. 4228 1.4719 1. 5209 1.5700 File No.: 1501350.301 Revision:

0 0.5034 0.5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 26.2234 25.6702 25.1169 24.4911 23.8627 23.2311 22.5985 21.9051 21.1702 20.3997 19.5778 28.5680 28.9998 29.3499 29.6779 29.7326 29.7872 29.6389 29.4654 29.1631 28.8069 28.4734 28.1608 27.8098 27.3825 26.9409 26.4187 25.8964 25.2995 24.6999 24.0849 23.4656 22.7788 22.0459 21.2729 20.4420 28.7973 29.2453 29.6239 29.9805 30.0652 30.1499 30.0329 29.8910 29.6210 29.2975 28.9961 28.7150 28.3949 27.9974 27.5853 27.0909 26.5965 26.0255 25.4517 24.8517 24.2444 23.5634 22.8323 22.0571 21.2182 33.1006 33.7692 34.4377 35.0535 35.6674 36.4037 37.1745 37.9166 38.6390 39.3420 40.0170 19.9171 20.9380 22.0116 23.0766 24.0357 24.9948 25.8762 26.7479 27.5699 28.3711 29.1564 29. 9272 30.6769 31.3845 32.0836 32.7342 33.3848 33.9853 34.5840 35.3108 36.0737 36.8099 37.5279 38.2279 38.9018 19.3721 20.3650 21.4064 22.4394 23.3684 24.2975 25.1502 25.9936 26.7877 27.5612 28.3221 29.0715 29.8006 30.4895 31.1703 31.8047 32.4392 33.0260 33. 6111 34.3293 35.0851 35.8161 36.5300 37.2273 37.9003 Page C-80 of C-173 F0306-0I R2 l) Structural Integrity Associates, Inc. Load Case # 2: HU/CD Min ------------

Crack Dimensions

---

a c a/t c/a c/a = 3.9063 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.3125 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0. 7813 0.8203 0.8594 0.8984 0.9375 0.9766 1. 0156 1. 054 7 1. 0938 1.1328 1.1719 1.2109 1. 2500 4.1563 0.3325 0.3741 0.4156 0.4572 0.4988 0.5403 0.5819 0.6234 0.6650 0.7066 0.7481 0.7897 0. 8313 0.8728 0.9144 0.9559 0.9975 1.0391 1.0806 1.1222 1.1638 1.2053 1.2469 1. 2884 1.3300 4.4063 0.3525 0.3966 0.4406 0.4847 0.5288 0.5728 File No.: 1501350.301 Revision:

0 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 K at tips a c 1. 2952 1.4530 1. 6275 1.8029 1.9879 2.1730 2.3665 2. 5611 2.7616 2.9647 3.1741 3.3894 3. 6071 3.8296 4.0530 4.2817 4.5105 4.7444 4.9785 5.2455 5.5218 5.8035 6.0887 6.3770 6.6698 1.3063 1.4657 1. 6421 1.8194 2.0066 2.1938 2.3896 2.5865 2.7895 2.9950 3.2077 3. 42 68 3.6484 3.8752 4.1030 4.3365 4.5700 4.8091 5.0485 5.3253 5.6127 5. 9062 6.2038 6.5050 6.8114 1. 3171 1.4781 1.6565 1.8356 2.0249 2.2141 0.4505 0. 4911 0.5338 0.5766 0.6203 0.6641 0.7091 0.7542 0.8004 0.8470 0.8989 0.9557 1.0139 1. 07 45 1.1358 1.2004 1.2651 1.3336 1.4022 1.4838 1.5690 1.6577 1.7489 1.8424 1.9394 0.4351 0.4740 0.5150 0.5560 0.5979 0.6399 0.6830 0. 7262 0.7704 0.8151 0.8647 0.9187 0.9740 1. 0317 1.0899 1.1513 1. 2127 1.2778 1.3430 1. 4210 1.5026 1.5876 1.6749 1.7646 1. 8575 0.4185 0.4557 0.4947 0.5338 0.5737 0.6137 Page C-81 of C-173 F0306-0J R2 SJ Structurallnlegrily Associates, Inc."' 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.6169 0.6609 0.7050 0.7491 0.7931 0. 8372 0. 8813 0.9253 0.9694 1.0134 1.0575 1.1016 1.1456 1.1897 1.2338 1.2778 1. 3219 1. 3659 1. 4100 4.6563 0. 3725 0.4191 0.4656 0.5122 0.5588 0.6053 0.6519 0.6984 0.7450 0.7916 0.8381 0.8847 0. 9313 0.9778 1. 0244 1.0709 1.1175 1.1 64 1 1.2106 1. 2572 1.3038 1.3503 1.3969 1.4434 1. 4900 4.9063 0.3925 0.4416 0.4906 0.5397 0.5888 0.6378 0.6869 0.7359 0.7850 0.8341 0.8831 0.9322 0.9813 1.0 303 1.07 94 1.1284 1.1775 1.2266 File No.: 1501350.301 Revision:

0 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 52 63 0.5492 0. 5721 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4. 6563 4.6563 4.6563 4.6563 4. 6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 2.4122 2. 6113 2.8166 3.0246 3.2404 3.4634 3.6892 3.9204 4.1527 4.3912 4.6297 4.8743 5.1192 5.4074 5.7079 6.0155 6.3277 6.6443 6.9668 1. 32 67 1. 48 92 1. 6693 1. 8501 2.0412 2. 23.2"3 2.4323 2.6334 2.8409 3.0510 3.2696 3. 4962 3. 7256 3.9608 4.1971 4.4401 4.6830 4.9325 5.1823 5.4807 5.7929 6.1130 6.4384 6.7686 7.1056 1. 3353 1.4992 1.6807 1.8632 2.0559 2.2486 2.4504 2.6533 2. 8626 3.0746 3.2959 3.5256 3.7583 3.9970 4.2370 4.4840 4.7309 4.9848 0.6547 0.6958 0.7379 0.7804 0. 8272 0.8781 0.9301 0.9842 1.0390 1.0966 1.1542 1.2151 1.2762 1. 3494 1.4261 1. 5060 1.5879 1.6721 1.7593 0.4037 0.4394 0.4767 0.5140 0.5521 0.5903 0.6294 0.6687 0.7088 0.7494 0.7938 0.8418 0.8908 0.9419 0.9935 1. 0477 1.1019 1.1592 1.2 166 1.2856 1.3578 1.4331 1.5103 1.5896 1.6717 0.3904 0.4247 0.4604 0.4962 0.5327 0.5693 0.6067 0.6443 0.6827 0.7216 0.7638 0.8093 0.8556 0.9039 0.9526 1.0038 1.0549 1.1089 Page C-82 of C-173 F0306-0 I R2 e Structural Integrity Associates, Inc. 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 1.2756 1. 324 7 1. 3738 1. 4228 1.4719 1.5209 1.5700 Load Case # 3: CD II Max 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 ------------

Crack Dimensions

---

a c a/t c/a c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 3.9063 0.3125 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0. 7813 0.8203 0.8594 0.8984 0.9375 0.9766 1.0156 1. 054 7 1.0938 1.1328 1.1719 1.2109 1.2500 4.1563 0.3325 0.3741 0.4156 0. 4572 0.4988 0.5403 0.5819 0.6234 0.6650 0.7066 0.7481 0.7897 0.8313 0.8728 0.9144 0.9559 0.9975 1.0391 1.0806 1.1222 1.1638 1.2053 1.2469 1.2884 1.3300 File No.: 1501350.301 Revision:

0 0.1831 0.2059 0.2288 0. 2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 52 63 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3. 9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 5.2390 5.5466 5.8693 6.2006 6.5377 6.8802 7.2302 1.1630 1.2282 1. 2 965 1. 3676 1.4406 1. 5154 1. 5930 K at tips a c 33.7249 34.1561 34.4303 34.6765 34.5774 34.4784 34.1212 33.7321 33.1795 32.5584 31.9639 31.3939 30.7782 30.0718 29.3488 28.5321 27.7153 26.8133 25.9082 25.0162 24.1277 23.1792 22.1897 21.1664 20.0945 34.0947 34.5489 34.8606 35.1443 35.0833 35.0222 34.7035 34.3529 33.8390 33.2568 32.7018 32.1721 31.5956 30.9266 30.2405 29.4581 28.6756 27.8050 26.9312 2 6.0598 25.1892 24.2510 23.2668 22.2440 21.1655 26.5878 27.9538 29.3950 30.8249 32 .1168 33.4086 34.5981 35.7749 36.8872 37.9726 39.0273 40.0537 41.0500 41.9868 42. 9113 43.7663 44.6213 45.4036 46.1832 47.0874 48.0266 48.9245 49.7943 50.6360 51.4374 25.8279 27.1557 28.5583 29.9500 31.2075 32.4650 33.6227 34.7682 35.8508 36.9071 37.9342 38.9344 39.9058 40.8197 41.7218 42.5571 43.3924 44.1578 44.9207 45.8233 46.7653 47.6682 48.5444 49.3940 50.2055 Page C-83 of C-173 F 0 30 6-01 R2 e Structural Integrity Associates, Inc. c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 4.4063 0.3525 0.3966 0.4406 0.4847 0.5288 0.5728 0.6169 0.6609 0.7050 0.7491 0.7931 0. 8372 0.8813 0.9253 0.9694 1. 0134 1.0575 1.1016 1.1456 1.1897 1. 2338 1.2778 1. 3219 1. 3659 1.4100 4.6563 0.3725 0.4191 0.4656 0.5122 0.5588 0.6053 0.6519 0.6984 0.7450 0.7916 0.8381 0.8847 0.9313 0.9778 1. 0244 1.0709 1.1175 1.1641 1.2106 1.2572 1. 3038 1.3503 1.3969 1.4434 1.4900 4.9063 0.3925 0.4416 0.4906 0.5397 0.5888 0.6378 0.6869 0.7359 0.7850 0.8341 File No.: 1501350.301 Revision:

0 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 52 63 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0. 2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 34.4430 34.9216 35.2766 35.6037 35.5883 35.5728 35.3017 34.9990 34.5343 34.0018 33.4954 33.0131 32.4831 31.8587 31.2168 30.4758 29.7349 28.9027 28.0673 27.2160 26.3604 25.4277 24.4427 23.4127 22.3177 34.7538 35.2543 35.6478 36.0137 36.0390 36.0643 35.8357 35.5757 35.1548 34.6667 34.2037 33.7638 33.2754 32.6907 32.0882 31.3843 30.6804 29.8826 29.0814 28.2481 27.4058 26.4781 25.4923 24.4558 23.3463 35.0330 35.5531 35.9813 36.3820 36.4438 36.5057 36.3152 36.0936 35.7122 35.2639 24.9995 26.2846 27.6385 28.9818 30.1937 31.4057 32.5199 33.6220 34.6623 35.6767 36.6670 37.6350 38.5755 39.4614 40.3362 41.1476 41.9590 42.7043 43.4472 44.3378 45.2701 46.1660 47.0372 47.8839 48.6954 24.2602 25.5071 26.8175 28.1175 29.2888 30.4602 31.5355 32.5989 33.6014 34.5785 35.5359 36.4751 37.3881 38.2490 39.0993 39.8895 40.6796 41.4069 42.1320 43.0119 43.9355 44.8252 45.6919 46.5360 47.3474 23.5961 24.8088 26.0802 27.3412 28.4762 29.6111 30.6514 31.6800 32.6486 33.5922 Page C-84 of C-173 F0306-0l R2

(;Structural Integrity Associates, Inc. 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.8831 0.9322 0.9813 1.0303 1.0794 1.1284 1.1775 1.2266 1.2756 1.3247 1.3738 1.4228 1.4719 1. 5209 1.5700 Load Case # 4: CD II Min 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 ------------

Crack Dimensions

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a c a/t c/a c/a = 3.9063 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.3125 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0.6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1. 0156 1. 054 7 1.0938 1.132 8 1.1719 1.2109 1.2500 4.1563 0.3325 0.3741 0.4156 0. 4572 0.4988 0.5403 0.5819 0.6234 0.6650 0.7066 0.7481 0.7897 0. 8313 0.8728 0.9144 0.9559 0.9975 1.0391 File No.: 1501350.301 Revision:

0 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0. 68 65 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0.5721 3.9063 3.9063 3.9063 3. 9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 34.8398 34.4380 33.9868 33.4380 32.8708 32.2002 31.5295 30.7626 29.9921 29.1750 28.3447 27.4215 26.4350 25.3927 24.2700 34.5200 35.4334 36.3217 37.1602 37.9886 38.7595 39.5305 40.2417 40.9507 41.8210 42.7368 43.6210 44.4837 45.3254 46.1369 K at tips a c 0.8522 0.9997 1.1662 1.3339 1. 5160 1.6981 1. 8923 2.0880 2.2920 2.4995 2. 7130 2.9320 3.1540 3.3821 3. 6113 3. 84 72 4.0832 4.3254 4.5678 4.8425 5.1263 5.4160 5.7098 6.0070 6.3090 0.8585 1.0073 1.1752 1.3443 1. 5280 1.7117 1.9076 2.1051 2.3110 2.5204 2.7365 2.9586 3.1841 3.4159 3.6489 3.8891 4.1292 4.3761 0.1303 0.1530 0 .1 772 0.2016 0.2285 0.2554 0.2848 0.3144 0.3458 0.3780 0.4157 0.4585 0.5030 0.5507 0.5992 0.6519 0.7046 0.7620 0.8196 0.8886 0.9607 1.0369 1.1158 1.1975 1.2833 0.1242 0.1459 0.1689 0.1921 0.2177 0.2433 0.2712 0.2994 0.3294 0.3601 0.3959 0.4364 0.4785 0.5237 0.5696 0.6194 0.6693 0.7237 Page C-85 of C-173 F0306-0 lR2 SJ Structural Integrity Associates, Inc.'" 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 1.0806 1.1222 1.1638 1. 2053 1.2469 1.2884 1.3300 4.4063 0.3525 0.3966 0.4406 0.4847 0.5288 0.5728 0.6169 0.6609 0.7050 0.7491 0.7931 0. 8372 0. 8813 0.9253 0.9694 1.0134 1.0575 1.1016 1.1456 1.1897 1.2338 1.2778 1. 3219 1. 3659 1.4100 4.6563 0. 3725 0.4191 0.4656 0.5122 0.5588 0.6053 0.6519 0.6984 0.7450 0.7916 0.8381 0.8847 0. 9313 0.9778 1.0244 1.0709 1.1175 1.1641 1.2106 1. 2572 1.3038 1. 3503 1.3969 1.4434 1.4900 4.9063 0.3925 0.4416 File No.: 1501350.301 Revision:

0 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0. 2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0.4119 0.4348 0.4577 0.4805 0.5034 0. 52 63 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.6563 4.6563 4. 6563 4.6563 4. 6563 4.6563 4. 6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4. 6563 4.6563 4. 6563 4. 6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.9063 4.9063 4.6233 4.9074 5.2020 5.5033 5.8092 6.1191 6.4347 0.8648 1.0149 1.1841 1.3545 1. 5396 1.7247 1.9222 2.1212 2.3287 2.5398 2.7584 2.9838 3.2126 3.4482 3.6851 3.9296 4.1741 4.4259 4.6780 4.9731 5.2804 5.5955 5.9160 6. 2411 6.5729 0.8704 1. 0217 1.1920 1. 3636 1. 5500 1. 7363 1. 9352 2 .1356 2.3446 2.5572 2.7779 3.0062 3.2381 3.4771 3.7175 3.9658 4.2141 4.4703 4. 72 68 5.0318 5.3504 5.6779 6. 0113 6.3499 6. 6963 0.8755 1. 0278 0.7783 0.8438 0.9125 0.9851 1. 0603 1.1381 1.2199 0.1179 0.1385 0.1602 0.1821 0.2064 0.2307 0. 2571 0.2839 0.3123 0.3415 0.3752 0.4130 0.4524 0.4946 0.5375 0.5841 0.6306 0.6814 0.7323 0. 7 935 0.8576 0.9253 0.9954 1. 0681 1.1444 0.1122 0 .1318 0.1525 0.1732 0.1963 0.2194 0.2445 0.2700 0. 2971 0.3248 0.3566 0.3922 0.4291 0.4687 0.5089 0.5525 0.5961 0.6436 0. 6913 0.7486 0.8085 0. 8719 0.9376 1. 0056 1. 0770 0 .1072 0.1259 Page C-86 of C-173 F0306-0I R2 e Structural Integrity Associates, Inc. 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 0.4906 0.5397 0.5888 0.6378 0.6869 0.7359 0.7850 0.8341 0.8831 0.9322 0.9813 1.0303 1.0794 1.1284 1.1775 1.2266 1.2756 1.3247 1.3738 1. 422 8 1.4719 1. 5209 1.5700 Load Case # 5: Unload Max 0.2288 0. 2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0.4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 ------------

Crack Dimensions

---

a c a/t c/a c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 3.9063 0.3125 0.3516 0.3906 0.4297 0.4688 0.5078 0.546 9 0.5859 0.6250 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1. 0156 1. 054 7 1. 0938 1.1328 1.1719 1.2109 1.2500 4.1563 0.3325 0.3741 0.4156 0.4572 0.4988 0.5403 0.5819 0. 6234 0.6650 0.7066 File No.: 1501350.301 Revision:

0 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0. 2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 1.1991 1.3717 1. 5593 1.7468 1.9469 2.1485 2.3588 2. 5727 2.7955 3.0264 3.2610 3.5030 3.7465 3.9983 4.2501 4.5102 4.7707 5.0845 5. 4133 5.7518 6.0968 6.4477 6.8070 0.1455 0.1653 0.1872 0.2092 0.2332 0.2575 0.2834 0.3099 0.3400 0.3735 0.4082 0.4454 0.4832 0 .'6 2 42 0.5652 0.6097 0.6545 0.7082 0.7645 0.8240 0.8856 0.9494 1. 0164 K at tips a c 12.7283 12.9928 13.2144 13.4268 13.5256 13.6244 13.6391 13.6434 13.5944 13.5230 13.4658 13.4217 13.3634 13.2769 13.1853 13.0647 12.9441 12.7977 12.6503 12.5312 12.4200 12.2922 12.1530 12.0044 11.8423 12.8655 13.1393 13.3754 13.6024 13.7160 13.8297 13.8595 13.8789 13.8452 13.7894 9.6352 10.1408 10.6742 11.2038 11. 6857 12.1676 12.6144 13. 0569 13.4778 13.8897 14.2942 14.6919 15.0802 15.4499 15.8156 16.1591 16.5025 16.8234 17.1435 17.5160 17.9033 18.2785 18.6455 19.0045 19.3522 9.3580 9.8491 10.3677 10.8825 11.3510 11.8195 12.2539 12.6840 13.0930 13.4932 Page C-87 of C-173 F0306-0IR2 e Structural Integrity Associates, Inc." 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2 300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2 000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2 600 0.2 700 0.2800 0.2 900 0.7481 0.7897 0.8313 0.8728 0.9144 0.9559 0.9975 1.0391 1.0806 1.1222 1.1638 1. 2053 1.2469 1.2884 1.3300 4.4063 0.3525 0.3966 0.4406 0.4847 0.5288 0.5728 0.6169 0.6609 0.7050 0.7491 0.7931 0. 8372 0.8813 0.9253 0.9694 1.0134 1.0575 1.1016 1.1456 1.1897 1.2338 1.2778 1. 3219 1. 3659 1. 4100 4.6563 0. 3725 0.4191 0.4656 0.5122 0.5588 0.6053 0.6519 0.6984 0.7450 0.7916 0.8381 0.8847 0. 9313 0.9778 1. 0244 1.0709 1.1175 1.1641 1.2 106 1.2 572 1.3038 1. 3503 File No.: 1501350.301 Revision:

0 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 52 63 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0. 2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0. 5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.1563 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4.4063 4. 6563 4.6563 4.6563 4.6563 4.6563 4. 6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4. 6563"' 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 4.6563 13.7484 13.7210 13.6793 13.6090 13.5335 13.4284 13.3232 13.1914 13.0587 12.9539 12.8569 12.7412 12.6127 12.4734 12.3187 12.9951 13.2785 13.5312 13.7749 13.9060 14.0372 14.0851 14.1228 14.1081 14.0715 14.0498 14.0420 14.0196 13.9681 13. 9114 13.8243 13.7373 13.6228 13.5073 13.4178 13.3356 13.2318 13.1134 12.9826 12.8337 13.1107 13.4027 13.6703 13.9289 14.0756 14.2224 14.2865 14.3405 14.3427 14.3232 14.3189 14.3285 14.3233 14.2887 14.2486 14.1778 14.1069 14.0078 13.9077 13.8318 13.7628 13.6698 13.8862 14.2726 14.6499 15.0092 15.3647 15.6989 16.0330 16.3453 16.6567 17.0259 17.4114 17.7855 18.1518 18.5106 18.8585 9.0558 9.5308 10.0309 10.5274 10.9784 11.4294 11.8469 12.2603 12.6528 13.0366 13.4146 13.7873 14 .1513 14.4979 14.8410 15.1639 15.4868 15.7888 16.0900 16.4514 16.8298 17.1975 17.5581 17.9116 18.2551 8.7861 9.2466 9.7303 10.2104 10.6458 11.0812 11.4837 11.8821 12.2599 12.6291 12.9937 13.3541 13.7061 14.0415 14.3735 14.6864 14.9992 15.2921 15.5841 15.9386 16.3106 16.6727 Page C-88 of C-173 F 0 306-01 R2 e Structural Integrity Associates, Inc."' 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 1. 3969 1.4434 1. 4900 4.9063 0.3925 0.4416 0.4906 0.5397 0.5888 0.6378 0.6869 0.7359 0.7850 0.8341 0.8831 0.9322 0.9813 1.0303 1.0794 1.1284 1.177 5 1.2266 1.2756 1.3247 1.3738 1. 4228 1.4719 1. 5209 1.5700 Load Case # 6: Unload Min 0.6865 0.7094 0.7323 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0. 5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 4.6563 4.6563 4.6563 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 4.9063 ------------

Crack Dimensions

---

a c a/t c/a c/a = 3.9063 0.0800 0.0900 0.1000 0.1100 0.1200 0.1300 0.1400 0.1500 0.1600 0.1700 0.1800 0.1900 0.2000 0.2100 0.2200 0.2300 0.2400 0.2500 0.2600 0.2700 0.2800 0.2900 0.3000 0.3100 0.3200 c/a = 0.0800 0.0900 0.3125 0.3516 0.3906 0.4297 0.4688 0.5078 0.5469 0.5859 0. 62 50 0.6641 0.7031 0.7422 0.7813 0.8203 0.8594 0.8984 0.9375 0.9766 1.0156 1. 054 7 1.0938 1.1328 1.1719 1.2109 1.2500 4.1563 0.3325 0.3741 File No.: 1501350.301 Revision:

0 0.1831 0.2059 0.2288 0.2517 0.2746 0.2975 0.3204 0.3432 0.3661 0.3890 0. 4119 0.4348 0.4577 0.4805 0.5034 0.5263 0.5492 0.5721 0.5950 0.6178 0.6407 0.6636 0.6865 0.7094 0.7323 0.1831 0.2059 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 '3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 3.9063 4.1563 4.1563 13.5604 13.4370 13.2934 13.2145 13.5143 13.7952 14.0671 14.2279 14.3887 14.4674 14.5360 14.5534 14.5494 14.5606 14.5858 14.5960 14.5765 14.5515 14.4952 14.4389 14.3536 14.2673 14.2037 14.1465 14.0631 13.9619 13.8452 13.7062 17.0281 17.3770 17.7164 8.5439 8.9915 9.4603 9.9257 10.3470 10.7684 11.1574 11.5424 11.9070 12.2631 12.6157 12.9651 13.3064 13.6317 13.9537 14.2576 14.5614 14.8460 15.1298 15.4780 15.8443 16.2014 16.5522 16.8968 17.2327 K at tips a c 2.3087 2.4902 2.6834 2.8765 3.0683 3.2602 3.4522 3.6442 3.8368 4.0297 4.2298 4.4366 4.6444 4.8541 5.0643 5.2768 5.4893 5.7045 5.9198 6.1695 6. 4290 6.6924 6.9583 7.2267 7.4986 2.3306 2.5145 1.1822 1.2634 1.3485 1.4334 1. 5156 1. 5978 1.6786 1. 7592 1.8391 1.9187 2.0031 2.0920 2.1813 2.2716 2.3622 2.4541 2.5460 2.6397 2.7335 2.8440 2.9592 3.0767 3.1957 3.3164 3.4392 1.1453 1.2236 Page C-89 of C-173 F0306-0JR2