ML092330231

Rev. 0 to 0900530.306, Pilgrim, ASME Code,Section III Evaluation of N9A Jet Pump Instrument Nozzle with Weld Overlay Repair.

ML092330231
Person / Time
Site:	Pilgrim
Issue date:	08/10/2009
From:	Structural Integrity Associates
To:	Office of Nuclear Reactor Regulation
References
0900530.306, Rev 0
Download: ML092330231 (159)

Text

StructuralIntegrity Associates, Inc. File No.: 0900530.306 CALCULATION PACKAGE Project No.: 0900530 Quality Program: Z Nuclear 0 Commercial PROJECT NAME:

Pilgrim Top Head Flaw and N9 Weld Overlay CONTRACT NO.:

10235773-01 CLIENT: PLANT:

Entergy Nuclear Pilgrim Nuclear Power Station CALCULATION TITLE:

ASME Code,Section III Evaluation of N9A Jet Pump Instrument Nozzle with Weld Overlay Repair Document Affected Project Manager Preparer(s) &

Revision Pages Revision Description Approval Checker(s)

Signature & Date Signatures & Date 0 1 - 25 Initial Issue A- - A-3 B-I - B-2 C-1 -C40 Minghao Qin Hal L. Gustin MQ 08/10/09 HLG 08/10/09 Karen K. Fujikawa KKF 08/10/09 Jennifer E. Smith JES 08/10/09 Page 1 of 25 F0306-01 RO

StructuralIntegrity Associates, Inc.

Table of Contents 1.0 O B JEC TIV E .................................................................................................................. 4 2.0 DESIGN CRITERIA .............................................. 4 3.0 BOUNDARY CONDITIONS, STRESS PATH DEFINITIONS, AND UNIT PRESSURE ................................ .................................................. 4 3.1 Boundary Conditions ................................................................................... 4 3.2 Stress Path D efinitions ................................................................................. 4 3.3 U nit Pressure L oad ............................................................................................. 5 4 .0 LO A D S .......................................................................................................................... 5 5.0 LOAD COM BINATION S ....................................................................................... 5 6.0 ASME CODE STRESS LIMITS EVALUATION ................................................ ý.6 6.1 Design Load Combination ..................................... 7 6.2 Service Level A/B Load Combination ............................... '-! ....................... 7 6.3 Pure Shear Stress Evaluation for Path 2 ........................... 8 7.0 FA TIG U E EV A LUA TION ............................................... I........................................... 8 7.1 V ESLFA T Program .................................................................................... 8 7.1.1 Cyclic Data (*.CYC) .......................................................................................... 9 7.1.2 Fatigue DataInput File (*.FDT)................................................................. 9 7.1.3. Stress Data Input File (*.STR) ...................................................................... 9 7.1.4 Fatigue Usage (*.FA T) .............................................................................. Il 8.0 C O N C LU SION S .................................................................................................... 11 9.0 REFER EN C E S ...................................................................................................... 12 Appendix A CALCULATION OF THE HEAT TRANSFER COEFFICIENTS ................ A-I Appendix B SUPPORTING FILES ................................................................................. B-1 Appendix C EXAMPLE VESLFAT FILES ...................................................................... C-1 File No.: 0900530.306 Page 2 of 25 Revision: 0 F0306-01.

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List of Tables Table 1: Bounding Transients to be Analyzed ................................................................... 13 Table 2: Load Com binations ............................................................................................ 14 Table 3: Allowable Stress Intensity Ranges ..................................................................... 14 Table 4: Materials at Each Path Inside and Outside Locations ........................................ 15 T able 5: M aterial Properties (1)............................................................................................... 16 Table 6: Design Load Combination, Stress Intensity Evaluation ....................................... 17 Table 7: Service Level A/B Load Combination, P+Q Stress Intensity Evaluation ............ 18 Table 8: Load Sets as Input to VESLFAT ....................................................................... 19 Table 9: Carbon/Low Alloy Steel and Stainless Steel Fatigue Curves ............................. 21 Table 10: Fatigue Usage Results .......................................... ............................................. 22 List of Figures, Figure 1: Boundary Conditions ......................................................................................... 23 Figure 2: Thermal Region Definitions .............................................................................. 23 Figure 3: Stress Path Definitions for ASME Code Evaluation ......................................... 24 Figure 4: Unit Internal Pressure ......................................................................................... 24 Figure 5: Stress Intensity under Unit Pressure ................................................................ 25 File No.: 0900530.306 Page 3 of 25 Revision: 0 F0306-01

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1.0 OBJECTIVE The objective of this calculation is to show that the ASME Code,Section III [1] design requirements are satisfied for a weld overlay repair of the jet pump instrument nozzle, N9A, at Pilgrim Nuclear Power Station (PNPS). An as-built weld overlay repair is provided in Reference [6].

A finite element model has been built [2] to support the ASME Code evaluations. These analyses, together with the design requirements of the ASME Code [1], will be used to determine the adequacy of the repairs.

2.0 DESIGN CRITERIA In accordance with the requirements of Code Case N-504-3, it is necessary to demonstrate that the primary stress requirements of the design Code continue to be met following repair. For the jet pump instrument nozzle, the requirements of the ASME Code,Section III for Class I components apply. As such, the rules of Article NB-3000 of Section III of the ASME Code, 2001 Edition with Addenda through 2003 [1], are used, and results will be reconciled with the original stress report.

The weld overlay repair region affects the instrument nozzle and safe end. As a result, the instrument nozzle and safe end of the repair will be evaluated using the rules of Subarticle NB-3200.

3.0 BOUNDARY CONDITIONS, STRESS PATH DEFINITIONS, AND UNIT PRESSURE 3.1 Boundary Conditions The jet pump instrument nozzle finite element model was built in Reference [2] with ANSYS program Release 8.1 [12] which is also used for this calculation. Two symmetric boundary conditions are applied at the two cross sections at the nozzle and penetration seal. To avoid rigid body movement, an axial direction restraint is applied at the inside corner of the nozzle cross section on the vessel side. Figure 1 shows the mechanical boundary condition.

The heat transfer coefficients (HTC) and temperatures are applied to four regions. The nozzle HTC and temperature are applied to Region I and the vessel HTC and temperature are applied to Region

3. The HTC and temperature of Region 2 (nozzle inner blend radius) is linearly transitioned from the HTC value used in Region I to the HTC value used in Region 3. The Region 4 HTC and temperature are assumed to be 0.2 BTU/hr-ft2-°F and I 00°F. Figure 2 shows the region definitions.

3.2 Stress Path Definitions Four stress paths are defined and shown in Figure 3. These paths are used for the ASME Code Section III analysis.

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3.3 Unit Pressure Load A uniform pressure of 1,000 psi was applied along the inside surface of the nozzle and the penetration seal. Figure 4 shows the applied pressure and Figure 5 shows the stress intensity distribution.

4.0 LOADS This evaluation only considers Design Loadings, Normal (Service Level A) and Upset (Service Level B) operating conditions in regards to meeting ASME Code,Section III Design and Service Level A/B allowables and fatigue. As such, thermal stresses resulting from Emergency (Service Level C) and Faulted (Service Level D) thermal transients are not considered [1, NB-3224.1, NB-3224.4 and Appendix F- 1310].

Primary stresses (such as mechanical loads due to deadweight, seismic effects and pressure) resulting from Design, Service Level A, B, C and D operating conditions are discussed in Section 5.0.

Pressure Per References [3] and [4], the design pressure is 1250 psig at 575 0 F and the operating pressure loads range from 0 psig to 1410 psig throughout the various thermal transients, whose temperatures range from 70'F to 556°F. The hydrostatic test (Transient 24) pressure ranges from 0 psig to 1565 psig. The pressure variations for the various transients are summarized in Table 1.

Thermal Transients Reference [5] defines eight thermal transients which are shown in Table 1. Details of the thermal transients are provided in References [3] and [4].

Mechanical Pipin2 Loads The jet pump instrument nozzle is not subjected to mechanical piping loads per Reference [5].

5.0 LOAD COMBINATIONS The load combinations used in the repair design are:

I. Design Load Combination

2. Level A Load Combination

3. Level B Load Combination

4. Level C Load Combination

5. Level D Load Combination

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The weld overlay sizing evaluation [6] considered general primary membrane, Pm, and primary membrane-plus-bending, Pm + Pb, stress intensities resulting from design/normal/upset (Design and Levels A & B) operating conditions and emergency/faulted (Levels C and D) conditions. Local primary membrane, PL, stress intensities were not specifically evaluated, because acceptability of the Pm and Pb stress intensities results in acceptable PL stress intensities.

The primary, Pm and primary membrane-plus-bending, Pm + Pb stress intensities (and as previously indicated, local primary membrane, PL, stress intensities) under design condition have to meet ASME Code Section II1, NB-3221. The specific load combinations are shown in Table 2. The allowable stress intensities for these load combinations are presented in Table 3 [1].

The sizing calculation did not specifically evaluate loads resulting from the Test Load Combination (Hydrostatic). However, the Test Load Combination considers only primary stresses, which result from pressure and mechanical loads. The added thickness of the weld overlay will only serve to reduce the general primary, Pm, and primary membrane-plus-bending, Pm + Pb stress intensities (and as previously indicated, local primary membrane, PL, stress intensities) when compared to the original configuration. Therefore, the only load combinations which will be considered herein are Service Levels A and B. The specific load combinations are shown in Table 2. The allowable stress intensities for these load combinations are presented in Table 3 [1]. Also, as indicated in Table 3, requirements for peak stresses and cyclic operation must also be met for Service Levels A and B.

Per ASME Code Section III NB-3227.2, the average primary shear stress (including Design, Service Levels A, B and C) shall be limited to 0.6 Sm and the maximum primary shear stress (including Design, Service Levels A, B and C) shall be limited to 0.8 Smn. This requirement is only applied to the limiting Path 2 in Figure 3.

It should be noted that in using the ASME Code, Section 1II, Class .1 rules in NB-3200, Service Levels A and B are combined together using bounding load combinations.

Thus, this calculation, together with Reference [6], contains the ASME Code qualification for the weld overlay repair for PNPS.

6.0 ASME CODE STRESS LIMITS EVALUATION Stress intensities are calculated for the various load combinations shown in Table 2 and stress intensity ranges are compared to the allowable limits shown in Table 3. Linearized stresses were evaluated through four paths (see Figure 3) throughout the transient time histories and the pressure analyses. These calculated stress intensities are then evaluated in accordance' with ASME Code,Section II, Subarticle NB-3200 [1].

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6.1 Design Load Combination The primary membrane (Pm) and membrane-plus-bending (PL+Qb) stress intensities due to pressure (1250 psig) are scaled from the 1000 psi unit pressure evaluation.

Table 4 lists the materials at the corresponding locations. Material properties are listed in Table 5.

Table 6 lists the evaluation of the primary stress intensities for the Design condition.

6.2 Service Level A/B Load Combination Examination of the membrane-plus-bending stresses does not provide an obvious pairing of stresses resulting from the various thermal transients for determination of operating stress intensity ranges. Thus, the VESLFAT program [8], developed by Structural Integrity, is used to calculate primary-plus-secondary membrane-plus-bending (P+Q) and total (P+Q+F) stress intensity ranges. The same program will be used to perform the fatigue usage analysis described in Section 7.0.

The primary-plus-secondary membrane-plus-bending (P+Q) and total (P+Q+F) component stress values are combined prior to use in the VESLFAT program [8]. The thermal component stresses resulting at each time increment from the various thermal transients are added to the component stresses resulting from corresponding pressure. The combination was performed in the Excel spreadsheets identified in Appendix B. Within the spreadsheets, the various component results are manipulated to produce the combined transient stress conditions, including:

The primary-plus-secondary membrane-plus-bending (P+Q) and total (P+Q+F) stress components due to pressure are scaled from the 1000 psi unit pressure evaluation. The actual pressure at any given time for a given transient is defined in Table I of this calculation. Pressure between any two specified time points is assumed to vary linearly throughout each of the thermal transients.

Cyclic information and material properties are also needed to complete the VESLFAT input, though they do not play a direct role in the determination of membrane-plus-bending stress intensity ranges. This input will be needed to support the fatigue evaluations, and is discussed in detail in Section 7.0.

Table 7 shows the evaluation of the primary-plus-secondary stress intensities for Service Level A and B. The stress ranges extracted from VESLFAT files, with the extension *.FAT, are the stress intensity ranges that produce the greatest ratio of stress intensity versus allowable stress.

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Examination of the maximum primary-plus-secondary (P+Q) range load pairs and fatigue causing load pairs (in the *.FAT files), identified the controlling thermal transients. The results are shown in Table 7.

6.3 Pure Shear Stress Evaluation for Path 2 The maximum primary stress occurs due to the test load (1565 psig), the shear stress can be scaled based on the 1000 psig results. Therefore, the maximum shear stress is 1.050 ksi which is below the allowable 0.6 Sm = 0.6

• 15.8 = 9.48 ksi, where Sm with 15.8 ksi is taken from Reference [5, page 17].

7.0 FATIGUE EVALUATION The fatigue evaluations are performed for Paths 1 through 4 of the weld overlay repair as shown in Figure 3. Both the inside and outside surfaces of the indicated paths will be evaluated. The evaluations are performed in accordance with ASME Code,Section III, Subparagraph NB-3222.4(e)

[1] for Paths I through 4, and use of the VESLFAT program [8].

7.1 VESLFAT Program The VESLFAT program requires three input files. The first is the *.CYC file, which includes the number of cycles for each load combination. The input used in the *.CYC file is discussed in detail in Section 7.1.1. The second file is the *.FDT file, which includes the fatigue curve data, appropriate temperature dependent material properties, and simplified elastic-plastic limits and factors. These values are discussed in Section 7.1.2. The final input file is the *.STR file, which contains the component membrane-plus-bending and membrane-plus-bending-plus-peak, e.g. total, stress components for the various load conditions to be evaluated. Additional details are provided in Section 7.1.3. As several load conditions occur within each load case, these load conditions will be identified by a number, which matches the load condition to the load case. This number is defined in the *.CYC file. Each of these three files must be identically named, with the exception of the file extension.

A number of intermediate files are generated which can be used to check the final results. The

• .STI file is an echo output of the *.STR file but includes transformations to output the results in terms of psi. The *.ALL file reflects all of the stress range pairs that are calculated. The *.PR file is a shortened version of the *.ALL file and lists only the significant (i.e., fatigue causing) pairs. The

• .ORD file re-sequences the *.PR file such that the ordered pairs are arrayed in order of reducing alternating stress.

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The final output file is labeled *.FAT. It echoes the input data, shows the significant cycle pairings, the cycle elimination, individual cycle pair fatigue contributions, and the final overall fatigue usage.

See Section 7.1.4 for fatigue results.

7.1.1 Cyclic Data (*.CYC)

Table I assigned a total number of cycles for each bounding event, which is listed in Table 8.

See Appendix C for an example of a *.CYC file.

7.1.2 FatigueData Input File (*.FDT)

The materials at the surfaces of the stress paths indicated in Figure 3 are tabulated in Table 4.

The fatigue curve for the austenitic and high nickel alloys is per Reference [1],Section III Appendices. The curve consists of two portions; the low cycle stress portion (<106 cycles) that is covered by Figure 1-9.2.1, and a high cycle portion for which Curve C, Figure 1-9.2.2, is conservatively used.

The fatigue curve for the SA-508 Class 2 material is also per Reference [5],Section III Appendices. Both curves presented in Figure 1.9.1 are used, with the conservatively lower alternating stress, Sa, used throughout. Table 9 listed the fatigue curves.

The modulus of elasticity correction factor from the fatigue curves will be based on Reference [9]

temperature dependent modulus of elasticity values with a fatigue curve elastic modulus of 28.3e6 psi for the austenitic and high nickel materialsand 30.0e6 psi for low alloy material. Sm and Sy temperature dependent values are also obtained from Reference [9].

Other material properties are input as follows:

m = 1.7, n = 0.3, parameters used to calculate Ke for the austenitic and high nickel materials [1, Table NB-3228.5(b)-l]

m = 2.0, n = 0.2, parameters used to calculate Ke for the low alloy material [1, Table NB-3228.5(b)-i]

See Appendix C for an example *.FDT file.

7.1.3 Stress Data Input File (*.STR)

Linearized membrane-plus-bending (P+Q) and membrane-plus-bending-plus-peak (P+Q+F) stress components from the finite element stress analyses were extracted for pressure and thermal transient loads. Stresses are scaled in cases (pressure) where the applied load magnitude is not the same as that analyzed.

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The resulting stress components are then added together to create the load combination for each thermal transient throughout the length of the event. Thus, thermal stresses are added to the scaled pressure stresses to create each membrane-plus-bending and membrane-plus-bending-plus-peak stress components entry.

Paths I and 4 terminate on the outside at geometric discontinuities. For these locations, fatigue strength reduction factors have to be calculated based on Reference [11, pages 91 through 94].

All of inside surfaces, as well as the outside surfaces of paths 2 and 3 do not have any geometric discontinuity and hence the fatigue strength reduction factor is unity.

The equation for calculating the fatigue strength reduction factor is based on Reference [11, pages 91 through 94]. The equation is as following:

where:

S

= angle of contour

= 36.50 for Path 1 outside [2]

450 for Path 4 outside [2]

r radius of curvature at contour interface

= 0.25 inches (assumed) h = height difference between contours

= 0.438 inches for Path I outside [2]

= 0.41 inches for Path 4 outside [2]

t = half thickness of thinner contour

= 0.608 inches for Path I outside [2]

= 0.880 inches for Path 4 outside (measured from inside node to outside node) r/t = 0.411 for Path I outside

= 0.284 for Path 4 outside Ko = 1.95 for Path I outside, per page 92 of Reference [11]

= 2.20 for Path 4 outside per page 92 of Reference [11]

Therefore K = 1.87 for Path I outside

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In addition, for those locations with fatigue strength reduction factors, the peak thermal stress components are added back into the total stress to capture the peak stress due to nonlinear radial temperature gradient, as follows:

P+Q+F = (ANSYS membrane plus bending)FSRF + ANSYS peak For those paths that do not occur at'a geometric discontinuity, no fatigue strength reduction factor is used. Instead, the membrane-plus-bending-plus-peak (P+Q+F) component stresses from the finite element stress analyses will be used directly.

The *.STR file includes the temperature of the location as it varies throughout the events and the pressure. The pressures vary as indicated in Section 3.0 and Table 1. The temperature at the location is the calculated metal temperature of the material rather than the fluid temperature.

These metal temperatures were extracted via the linearized stress results files, which include the temperature data in the last field under "Total" stress.

The load combinations and the development of the *.STR file entries were performed in the Excel spreadsheets identified in Appendix B. An example of the *.STR file is shown in Appendix C.

7.1.4 Fatigue Usage (*.FAT)

The fatigue evaluation automatically selects the load pairs that create the greatest alternating stress, performs a Ke calculation, corrects for the modulus of elasticity, and performs the fatigue evaluation. It repeats this process selecting the next highest stress range until the available cycles are used up or the remaining stress ranges fall below the endurance limit. An example *.FAT file is included in Appendix C. The intermediate solution files *.STI, *.ALL, *.PR, and *.ORD are included with computer files.

Table 10 tabulates the total fatigue usage for each location. In addition, the table includes information on the load pairing that produces the greatest alternating stress for each location, including the corresponding membrane-plus-bending stress intensity range, the calculated Ke elastic-plastic factor, and the alternating stress, Sa, for the specific load pair.

8.0 CONCLUSION

S An evaluation of the jet pump instrument nozzle weld overlay repair for PNPS has been performed in accordance with the requirements of the ASME Boiler and Pressure Vessel Code,Section III, for Class 1 components [ 1 ]. Stress intensities were conservatively determined for pressure and bounding thermal transients, and compared against ASME Code allowables for primary-plus-secondary stress effects. In all cases, the reported values of stress intensity range are less than their corresponding allowable Values.

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A detailed fatigue analysis was also performed. For the given number of expected cycles corresponding to a design period (see Table 1), the total usage at all locations evaluated is below the allowable value of I (see Table 10).

In conclusion, the jet pump instrument nozzle weld overlay repair for PNPS, provided in Reference [7],

satisfies the requirements of ASME Code Section 111.

9.0 REFERENCES

1. ASME Boiler and Pressure Vessel Code,Section III, Rules for Construction of Nuclear Facility Components, 2001 Edition with Addenda through 2003.

2. SI Calculation No. 0900530.305, "Weld Overlay Finite Element Model (FEM) and Material Properties for Nozzle N9A," (for revision refer to SI Project Revision Log, latest revision).

3. Boston Edison Company Drawing No. MIA12-2, Revision E0, (GE Drawing No. 730E491)

"Reactor Thermal Cycles," SI File No. PNPS-20Q-205.

4. Entergy Condition Report No. CR-PNP-2001-08015, 11/09/2001, SI File No. PNPS-IOQ-214.

5. Combustion Engineering, Inc., "Analytical Report for Pilgrim Reactor Vessel," Report No.

CENC- 1139, Approved 3/9/71, SI File No. PNPS-1OQ-21 I.

6. SI Calculation No. 0900530.301, Revision 1, "Weld Overlay Design for Jet Pump.

Instrumentation Nozzle N9A," April 30, 2009.

7. Welding Services, Inc. Drawing. "Construction Drawing Pilgrim, N9A." (2 sheets), Drawing No. 409506, May 1, 2009, SI File No. 0900530.202.

8. VESLFAT, Version 1.42, Structural Integrity Associates, Inc., February 6, 2007.

9. ASME Boiler and Pressure Vessel Code,Section II, Part D, 2001 Edition with Addenda through 2003.

10. J. P. Holman, "Heat Transfer," 5th Edition, McGraw-Hill, Inc., 1981.

11. Office of Technical Services, United States Department of Commerce, "Tentative Structural Design Basis for Reactor Pressure Vessels and Directly Associated Components (Pressurized Water Cooled Systems)," December 1, 1958 with Addendum No. 1, 27 February, 1959.

12. ANSYS/Mechanical, Release 8.1 (w/Service Pack 1), ANSYS Inc., June 2004.

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Table 1: Bounding Transients to be Analyzed 1

Trans.0) Cycles (1) t sec (3) Tves, IF (4) Tnoz, 'F ( P, psig(ý hv Btu/hr-ft'ZýF ( h., Btu/hr-ft-°F (8) 2 130 0 100 100 0 500 94 Design I 100 100 1250 500 94 Pressure 2 100 100 25 500 94

,3 120 0 100 100 0 500 94 Startup 16416 556 556 1035 500 438 11 30 0 532 532 1035 500 427, LFWP 3 532 532 1215 500 427 13 532 532 1160 500 427 233 310 310 1160 500 297 2213 510 510 1160 500 416 2393 310 310 910 500 297 67,73 510 510 1160 500 416 7193 310 310 700 500 297 7493 310 310 700 500 297 11093 410 410 240 500 363 16349 556 556 1035 500 438 26349 556 556 1035 500 438 26350 548 548 1035 500 434 36350 548 548 1035 500 434 36351 532 532 1035 500 427 46351 532 532 1035 .500 427 13 1 0 532 532 1035 500 427 Reactor 2 532 532 1410 500 427 Overpressure 32 532 532 965 500 427 452 556 556 1035 500 438 10452 556 556 1035 500 438 10453 548 548 1035 500 434 20453 548 548 1035 500 434.

20454 532 532 1035 500 427 30454 532 532 1035 500 427 14 2 0 532 532 1035 500 427 SRV 60 385 385 275 500 348 Blowdown 11400 70 70 25 500 0 17 5 0 532 532 1035 500 427 Improper 1 278 278 1035 500 272 Start 27 278 278 1035 500 272 28 532 532 1035 500 427 21-23 118 0 556 556 1035 500 438 Shutdown 6156 385 385 0 500 348 6756 330 330 0 500 311 15036 100 100 0 500 94 24 3 0 100 100 0 500 94 Hydro 1 100 100 1565 500 94 Pressure 2 100 100 0 500 94 Notes:

1. These eight transients are selected based on Reference [5].

2. The cycle numbers are based on design values [5].

3. Time is based on the thermal cycle diagram [3]. Using 10,000 sec to simulate the steady state.

4. The vessel temperature is taken from the thermal cycle diagram [3].

5. The nozzle temperature is assumed as the same as the vessel temperature.

6. Pressure is taken from thermal cycle diagram [3].

7. Heat transfer coefficient at the vessel is taken from Reference [5].

8. Heat transfer coefficient at the nozzle is calculated in Appendix A under natural convention condition.

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Table 2: Load Combinations LOADS Load Combinations Design Level A Level B Test Pressure (psig) (1) (2) (2) (4)

Temperature (OF) (1) (3) I (3) )) (4)

Thermal Transients N/A X X(5)X Notes:

1. 1250 psig and 575TF.

2. Varies between 0 and 1410 psig depending on transient conditions summarized in Table 1.

3. Varies between 70'F and 556'F depending on transient conditions summarized in Table 1.

4. 1565 psig and I 00°F.

5. See Table 1.

Table 3: Allowable Stress Intensity Ranges LoadL Combination Pm PL PL + Pb PL + Pb + Q Pure Shear (3) Note Design Condition Sm 1.5 Sm I 1.5 Sm - 0.6 Sm I Level A/B - - 3.O Sm 0.6 Sm 2 Note:

1. The requirements of ASME Code, Section Ill, Subparagraph NB-3221 [1] must be met.

2. The requirements of ASME Code, Section Il, Subparagraph NB-3222.4(e) [1] for peak stresses and cyclic operation must be met.

3. The requirements of ASME Code, Section 111, Subparagraph NB-3221 [1] must be met. Here, the maximum pure shear stress will be used.

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Table 4: Materials at Each Path Inside and Outside Locations Path"'I J Surface Material(2)

Inside SA-240 Type 304 1 OtA-508 C1.2 /

Alloy 52M A-508 C1. 2 /

A ll 2 Nozzle Side Alloy 52M 2 2 SA-182 F304 /

Seal Side Alloy 52M Inside SA-182 F304 3 s SA- 182 F304/

Alloy 52M Inside SA-182 F304 4

Outside SA- 182 F304 Notes: (

1. See Figure 3 for illustration of indicated locations.

2. Identified in Reference 2.

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Table 5: Material Properties(I)

Material T, -F E x 106, psi Sm, ksi SY, ksi SA-508 Class 2 70 27.8 26. 7 50.0 200 27.1 26.7 47.0 300 26.7 26.7 45.5 400 26.1 26.7 44.2 500 25.7 26.7 43.2 600 25.2 26.7 42.1 Alloy 52M 70 30.3 23.3 35.0 200 29.5 23.3 31.7 300 29.1 23.3 29.8 400 28.8 23.3 28.6 500 28.3 23.3 27.9 600 28.1 23.3 27.6 SA-204 304L 70 28.3 16.7 25.0 200 27.6 16.7 21.4 300 27.0 16.7 19.2 400 26.5 15.8 17.5 500 25.8 14.7 16.4 600 25.3 14.0 15.5 SA!-182 F304 70 28.3 20.0 30.0 200 27.6 20.0 25.0 300 27.0 20.0 22.4 400 26.5 18.6 20.7 500 25.8 17.5 19.4 600 25.3 16.6 18.4 Notes:

1. All values are obtained from Reference [9].

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Table 6: Design Load Combination, Stress Intensity Evaluation Path ( S Allowable P.L + Pb Allowable Number(S) Surface I ( Sm (ksi) (ksi) 1.5 Sm (ksi)

Inside (1) 14.0 5.350 21.0 Yes Outside (2) 4.203 26.7 40.1 Yes Outside (3) 23.3 35.0 Yes Noz. side (1) 14.0 21.0 Yes

'2 Noz.

Sasie()side (3) 2.159 23.3

2. _____

35.0 Yes Seal side (4) 16.6 24.9 Yes Seal side (3) 23.3 35.0 Yes Inside (4) 16.6 3.404 24.9 Yes 3 Outside (4) 1.579 16.6 24.9 Yes Outside (3) 23.3 0.355 35.0 Yes 16.6 2.908 24.9 Yes 4Inside (4)

Outsidet 4 ) 16.6 1.151 24.9 Yes Notes:

1. Material at location is SA-204 304L equivalent [2].

2. Material at location is A-508 CL. 2 [2].

3. Material at location is Alloy 52M [2].

4. Material at location is SA-182 F304 [2].

5. See Figure 3 for illustration of indicated locations.

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Table 7: Service Level A/B Load Combination, P+Q Stress Intensity Evaluation Path Maximum Stress Allowable Number(7) Nubr(S,,) Surface Intensity(ksi) (5)

Range 3Sin (ksi)(6) Accept Inside (1) 35.314 42.924 Yes I Outside (2) 34.612 80.100 Yes Outside (3) 34.612 69.900 Yes Noz. side (1) 11.141 80.100 Yes Noz. side (3) 11.141 69.900 Yes 2 Seal side (4) 11.937 51.285 Yes Seal side (3) 12.138 69.900 Yes Inside (4) 24.849 51.015 Yes 3 Outside (4) 30.901 51.258 Yes Outside (3) 31.087 69.900 Yes Inside (4) 23.264 51.015 Yes 4 Outside(4) 28.055 52.041 Yes Notes:

I. Material at location is SA-204 304L equivalent [2].

2. Material at location is A-508 CL. 2 [2].

3. Material at location is Alloy 52M [2].

4. Material at location is SA-182 F304 [2].

5. Sn values shown are based on the maximum S,/3Sm ratio from VESLFAT output files ending in *.FAT (see Appendix C for example).

6. All material stress allowable values shown [1, 9] are based on the maximum SnI3Sm ratio from VESLFAT output files ending in *.FAT (see Appendix C for example).

7. See Figure 3 for illustration of indicated locations.

File No.: 0900530.306 Page 18 of 25 Revision: 0 F0306-01.

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Table 8: Load Sets as Input to VESLFAT Path 1 Inside Path 2 Nozzle Side Path 3 Inside Path 4 Inside Trans Name cycles Trans Name cycles Trans Name cycles Trans Name cycles 1 2_DHydT1 130 1 2_DHydT1 130 2_DHydTl 130 2_DHydT1 130 2 2_DHydT2 130 2 2_DHydT2 130 2_DHydT2 130 2_DHydT2 130 3 2_DHydT3 130 3 2_DHydT3 130 2_DHydT3 130 2_DHydT3 130 4 3_Staupl 120 4 3_Staupl 120 3_Staupl 120 3_Staupl 120 5 3_Staup2 120 5 3_Staup2 120 3_Staup2 120 3_Staup2 120 6 11_LFWP1 30 6 11_LFWP1 30 3_Staup3 120 3_Staup3 120 7 11_LFWP2 30 7 11_LFWP2 30 11_LFWP1 30 11_LFWP1 30 8 11_LFWP3 30 8 11_LFWP3 30 11_LFWP2 30 11_LFWP2 30 9 11_LFWP4 30 9 11_LFWP4 30 11_LFWP3 30 11_LFWP3 30 10 11_LFWP5 30 10 11_LFWP5 30 11_LFWP4 30 11_LFWP4 30 11 11_LFWP6 30 11 11_LFWP6 30 11_LFWP5 30 11_LFWP5 30 12 11_LFWP7 30 12 11_LFWP7 30 11_LFWP6 30 11_LFWP6 30 13 11_LFWP8 30 13 11_LFWP8 30 11_LFWP7 30 11_LFWP7 30 14 13_ROP1 1 14 11_LFWP9 30 11_LFWP8 30 11_LFWP8 30 15 13_ROP2 1 15 13_ROP1 1 11_LFWP9 30 11_LFWP9 30 16 13_ROP3 1 16 13_ROP2 1 11_LFWP1O 30 11_LFWP1O 30 17 14_SRVB1 2 17 13_ROP3 1 13_ROPI 1 13_ROP1 1 18 14_SRVB2 2 18 13_ROP4 1 13_ROP2 1 13_ROP2 1 19 14_SRVB3 2 19 13_ROPS 1 13_ROP3 1 13_ROP3 1 20 14_SRVB4 2 20 13_ROP6 1 13_ROP4 1 13_ROP4 1 21 17_lmpST1 5 21 13_ROP7 1 13_ROP5 1 13_ROP5 1 22 17_lmpST2 5 22 14_SRVB1 2 13_ROP6 1 14_SRVB1 2 23 17_lmpST3 5 23 14_SRVB2 2 14_SRVB1 2 14_SRVB2 2 24 21_ShDwl 118 24 14_SRVB3 2 14_SRVB2 2 14_SRVB3 2 25 21_ShDw2 118 25 14_SRVB4 2 14_SRVB3 2 17_lmpST1 5 26 21_ShDw3 118 26 17_lmpST1 5 17_lmpST1 5 17_lmpST2 5 27 21_ShDw4 118 27 17_lmpST2 5 17_lmpST2 5 17_lmpST3 5 28 24_Hydrol 3 28 17_lmpST3 5 17_lmpST3 5 17_lmpST4 S 29 24_Hydro2 3 29 17_lmpST4 5 17_lmpST4 5 21_ShDwl 118 30 24 Hydro3 3 30 21_ShDwl 118 21_ShDwl 118 21_ShDw2 118 31 21_ShDw2 118 21_ShDw2 118 21_ShDw3 118 32 21_ShDw3 118 21_ShDw3 118 21_ShDw4 118 33 24_Hydrol 3 21_ShDw4 118 21_ShDw5 118 34 24_Hydro2 3 21_ShDw5 118 21_ShDw6 118 35 24_Hydro3 3 24_Hydrol 3 24_Hydrol 3 24_Hydro2 3 24_Hydro2 3 24_Hydro3 3 24_Hydro3 3 File No.: 0900530.306 Page 19 of 25 Revision: 0 F0306-01I

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Table 8: Load Sets as Input to VESLFAT (continued)

Path 1 Outside Path 2 Seal Side Path 3 Outside Path 4 Outside Trans Name cycles Trans Name cycles Trans Name cycles Trans Name cycles 1 2_DHydT1 130 1 2_DHydT1 130 2_DHydT1 130 1 2_DHydT1 130 2 2_DHydT2 130 2 2_DHydT2 130 2_DHydT2 130 2 2_DHydT2 130 3 2_DHydT3 130 3 2_DHydT3 130 2_DHydT3 130 3 2_DHydT3 130 4 3_Staupl 120 4 3_Staupl 120 3_Staupl 120 4 3_Staupl 120 5 3_Staup2 120 5 3_Staup2 120 3_Staup2 120 5 3_Staup2 120 6 11 LFWP1 30 6 11_LFWP1 30 11_LFWP2 30 6 3 Staup3 120 7 11_LFWP2 30 7 11_LFWP2 30 11_LFWP2 30 7 11 LFWP1 30 8 11_LFWP3 30 8 11_LFWP3 30 11_LFWP3 30 8 11 LFWP2 30 9 11_LFWP4 30 9 11_LFWP4 30 11_LFWP4 30 9 11 LFWP3 30 10 11_LFWP5 30 10 11_LFWP5 30 11_LFWP5 30 10 11_LFWP4 30 11 11_LFWP6 30 11 11_LFWP6 30 11_LFWP6 30 11 11 LFWP5 30 12 11 LFWP7 30 12 11_LFWP7 30 11_LFWP7 30 12 11 LFWP6 30 13 11_LFWP8 30 13 11_LFWP8 30 11_LFWP8 30 13 11 LFWP7 30 14 11 LFWP9 30 14 13_ROP1 1 11_LFWP9 30 14 11 LFWP8 30 15 13_ROP1 1 15 13_ROP2 1 13_ROP1 1 15 11_LFWP9 30 16 13_ROP2 1 16 13_ROP3 1 13 ROP2 1 16 11 LFWP10 30 17 13_ROP3 1 17 13_ROP4 1 13_ROP3 1 17 13 ROP1 1 18 13_ROP4 1 18 13_ROPS 1 13_ROP4 1 18 13_ROP2 1 19 13_ROP5 1 19 14_SRVB1 2 13_ROP5 1 19 13 ROP3 1 20 13_ROP6 1 20 14_SRVB2 2 14_SRVB1 2 20 13_ROP4 1 21 14_SRVB1 2 21 14_SRVB3 2 14_SRVB2 2 21 13_ROP5 1 22 14_SRVB2 2 22 17_lmpST1 5 14_SRVB3 2 22 13_ROP6 1 23 14_SRVB3 2 23 17_lmpST2 5 14_SRVB4 2 23 13_ROP7 1 24 14_SRVB4 2 24 17_lmpST3 5 17_lmpST1 5 24 14_SRVB1 2 25 17_lmpST1 5 25 17_lmpST4 5 17_lmpST2 5 25 14 SRVB2 2 26 17_lmpST2 5 26 21_ShDwl 118 17_lmpST3 5 26 14_SRVB3 2 27 17_lmpST3 5 27 21_ShDw2 118 17_lmpST4 5 27 14 SRVB4 2 28 17_lmpST4 5 28 21_ShDw3 118 21_ShDwi 118 28 17_lmpST1 5 29 21_ShDwl 118 29 21_ShDw4 118 21_ShDw2 118 29 17_lmpST2 5 30 21_ShDw2 118 30 24_Hydrol 3 21_ShDw3 118 30 17_lmpST3 5 31 21_ShDw3 118 31 24_Hydro2 3 21_ShDw4 118 31 17_lmpST4 5 32 21_ShDw4 118 32 24_Hydro3 3 24_Hydrol 3 32 21 ShDwl 118 33 24_Hydrol 3 24_Hydro2 3 33 21_ShDw2 118 34 24_Hydro2 3 24_Hydro3 3 34 21 ShDw3 118

,118 35 24_Hydro3 3 35 21_ShDw4 118 36 21 ShDw5 37 24_Hydrol 3 3

38 24_Hydro2 3 39 24_Hydro3 File No.: 0900530.306 Page 20 of 25 Revision: 0 F0306-01.

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Table 9: Carbon/Low Alloy Steel and Stainless Steel Fatigue Curves S., ksi Sa, ksi Number of Cycles Carbon/Low Alloy ~ Austenitic 10 580 708 20 410 512 50 275 345 100 205 261 200 155 201 500 105 148 1000 83 119 2000 ,64 97 5000 48 76 10000 38 64 20000 31 55.5 50000 23 46.3 100000 20 40.8 200000 16.5 35.9 500000 13.5 31 1000000 12.5 28.2 2.E+06 N/A 22.8(2) 5.E+06 N/A 18.4(2)

L.E+07 N/A 16.4(2) 2.E+07 N/A 15.2(2) 5.E+07 N/A 14.3(2)

I.E+08 N/A 14.1(2) 1.E+09 N/A 13.9(2) 1.E+10 N/A 13.7(2)

I.E+lI1 N/A 13.6(2)

Note:

1. Using UTS < 80 ksi curve.

2. Using Curve C for austenitic steel.

File No.: 0900530.306 Page 21 of 25 Revision: 0 F0306-01

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Table 10: Fatigue Usage Results Path Maximum Alternating Stress Load Pair Total Surface Load Pair ( K" Alternating Fatigue L o a d_P ai rS . (p s i)_K_ St r e s s (p s i) U s a g e (2 )

N o .__

Inside 25 & 29 35314 1 18983 0.0000560 Outside 16 & 24 36503 1 29574 0.0211011 Noz. side 27 & 28 8606 1 13890 0.0000114 Seal side 5 & 21 9154 1 19005 0.0000913 Inside 27 & 31 27835 1 29106 0.0000541

_Outside 5 & 23 19927 1 19005 0.0000964 Inside 26 & 30 23250 1 28148 0.0000429 1 Outside 9 & 29 28043 1 28635 0.0002890 Notes:

1. See Figure 3 for illustration of indicated locations.

2. Cumulative fatigue usage from all contributing load pairs.

3. See Table 7 for transient.

File No.: 0900530.306 Page 22 of 25 Revision: 0 F0306-01I

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AREAS MAT NUM PILGRIM N9A Nozzle Figure 1: Boundary Conditions n1--

PEA rahr HUML~

[PILIM NgA N::oi.:

Figure 2: Thermal Region Definitions File No.: 0900530.306 Page 23 of 25 Revision: 0 F0306-01:

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Figure 3: Stress Path Definitions for ASME Code Evaluation AREAS MAT NUM P000 N PILGRIM N9A Nozzle Figure 4: Unit Internal Pressure File No.: 0900530.306 Page 24 of 25 Revision: 0 F0306-01I

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NODAL SOLUTION-STEP=1 SUB =1 TIME=1 SINT (AVG)

DMX =.745E-03 SMN =12.35 SMX =23053 12.35 10253 15373 20493 23053 I2.35 5133 10253 15373 20493 2572 2572 7693 12813 17933 23053 PILGRIM N9A Nozzle Figure 5: Stress Intensity under Unit Pressure File No.: 0900530.306 Page 25 of 25 Revision: 0 F0306-01:

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Appendix A CALCULATION OF THE HEAT TRANSFER COEFFICIENTS File No.: 0900530.306 Page A- I of A-3 Revision: 0 F0306-01 RO

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An expression for the natural convection heat transfer coefficient can be developed by combining Equations 5-42 and 7-56 of Reference [10], as follows:

Nufree C. (Gr. Pr)n (l) hfree = C. (Gr. Pr)" .k (2) x At 0.75 < x/D < 2.0 Where:

hfree = Natural-convection heat transfer coefficient, h = Nu

• k / x C = Linear coefficient representing the pipe geometry Gr = Grashof number for the flow n = Polynomial coefficient representing the pipe geometry x = Characteristic length (the pipe diameter for tube flow and difference of radius for annular flow), ft D = Pipe diameter, ft As shown in the accompanying text for Equation 7-56 of Reference [10], values of C = 0.55 and n 0.25 are reasonable for the pipe geometry under consideration. The Grashof number is a dimensionless quantity representing the free convection state of a system, and it is calculated with the following equation [ 10, Equation 7-21 ]:

Gr _ g'f.(6. - T.)x 3 (3)

Where: 2 g = Acceleration due to gravity, 32.173 ft/sec P3 = Volumetric rate of expansion of the fluid, ft'3/ft3'-F T, = Temperature of the pipe wall (surface), 'F T.o = Temperature of the fluid, 'F x = Characteristic length (the pipe diameter for tube flow and difference of radius for annular flow), ft File No.: 0900530.306 Page A-2 of A-3 Revision: 0 F0306-01 RO

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Calculation of Heat Transfer Coefficients for FeedwaterNozzle Flow Path I t

- -- - j____References" 1. P. Holman, "Heat Transfer '4th Edition, McGraw-Hill 19 76

_______________________. i2JPHolmnan, "HeatTransfer, "'5thEdition, 1981. ___I Vunus A. Cengel, John M. Cinrbala, "Fluid Mechanics Fundamentals and Applications",McGraw Hill-, 2006.

. . . ... __-43.

Pipe Inside Diameter, D = 3847 inches 0.321 ft -

Outer Pipe, Inside radius, r. 1.9233! inches = 0160 tit Flow, % of rated

,t i 0T..... ___0_/__

o0.049 'm, T_

I Fluid Velocity, V 0.000 ft/sec = 0.0 gpm =

- Characteristic Length, L = D 0.321 ft = 0.098 im Tfti - Tuf., AT = Tfid - 0.00 30.00 - 130.00 - 230.00 330.00 ' 430.00

• 530.00 *F The above assumption is based on 000 16.67 72.22 127.78 183.33 238.89 C experience wth past RP-V heat transfer ianalyses. T Value at Fluid Temperature, T [3] Units Conversion 70 100 T 200 1 300 1 400 500 600 'F Water Property Factor [1] 21.11 37.78 93.33 148.89 1204.44 260.00 315.56 'C k 1.7307 0.6006 0.6282 0.6767 0.6819 1 0.6611 06092 0.5175 W/m-*C (Thermal Conductivity) - 0.3470 0.3630 o0.3910 03940 0.3820 0.3520 0.2990 Btu/hr-ft-*F CP4.1869 4.183 4.183 4.208 4.308 4.513 4.974 6.318 kJ/kg-'C (Specific Heat) 0.999 0.999 1.005 1.029 1.078 1.188 1.509 Btu/-bm-*F 3

P (Dniy (Desit) 16.018 997.9 U.

6.3 993.1 23 2

963.0 60.11 915.1 57.1 859.4 53.7 fI 784.1 49.0 677.9 42.3 kg/in 3 Ib/f 3

1.8 2.07E-04 3.60E-04 i 7.11E-04 1.02E-03 1.39E-03 2.OOE-03 3.39E-03 m /m/-*C

_v , e,c Rate (Volumetric ro..........

.... E p.......! ..n .................

of Expansion) ...... ......

............ L 1..1S-0

.......... 0........

E.. ..........

I.. 22.OOE-04T OE* . _._..9...... -........

3.95E-04 ...... ...55.66E-04 6E  : .5 I7.71 E-04 _ ..I1.1IE-03

.2y_  : :..

.j 1.89E-03.................

..... 5.........

ft /ft'-*F .

2

.- g . 03048 9.806 9.806 9806 9806 98806 9806 9806 m/s t

(Gravitational Constant) 32.17 32.17 T 32.17 32.17 32.17 I 32.17 32.17 ft/s 1t.4881 .... E... 04, .... 303-0iz- 1.84E-04 4--04 I.3E-0G-4_1 1-02--E---0-4-- 0E-0 kgrs (Dynamic Viscosity) .. 6.56E-04 4.58E.04 2.04E-04 1

.24E- . 883E-05 6.83E-05.5.39E-05 Ibm/ft-s Pr 6.790 4.540 1.880 1.160 ) 0.893 0.830 0.979 -

(Prandtl Number) _ I Calculated Parameter Formula 70 100 200 300 400 500 [ 600 °F Reynold's Number, Re pVD/p 0.OOOOE+00 0.0000E+00 0.OOOOE+00 I 0.OOOOE+00 I.OOOOE+00I 0.OOOOE+00 0.OOOOE+00 -

3 2 Grashof Number, Gr gPAfl /TLl(p) 0.000E+00 1.1662E+08 4 7446E+09 2.9472E+10 9.9465E+ +11 6.5289E+11 -

Rayleigh Number, Ra GrPr 0.OOOOE+00 5.2944E+08; 8.9199E+09 3.4188E+10 EE11 7E.3918E11 -

From [2*) ... I ....... .. . . ............................

Inside urfacevtion Heat Transfer Coefficient:.,_ --

Case: Enclosed cylinder C = ....... n 02) .-I., . .

2 H,_ C(GrPr)rk/L 0.00 536.46 1,170.69', 1,650.59 2,031.74 2,336.94 2,604.66 W/m -*C 0.00 94.48 206.17 290.69 357.82 411.57 458.72 Btu/hr-ft2-*F 2

0.O00E+00 1.822E-04 3.977E-04 5.607E-04 6.902E-04 7.939E-04 8.849E-04 Btu/sec-in -°F File No.: 0900530.306 Page A-3 of A-3 Revision: 0 F0306-01 RO

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Appendix B SUPPORTING FILES File No.: 0900530.306 Page B- 1 of B-2 Revision: 0 F0306-01 RO

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File Name Description N9 Loads.xls Excel Spreadsheet to Create HTCs.

PNPS-N9.INP N9A Nozzle ANSYS Geometry Input File from Reference [2].

MPropLinear. PNPS.INP N9A Nozzle ANSYS Material Input File from Reference [2].

PNPS-N9-PRESS.INP N9A Nozzle ANSYS Pressure Load Input File.

PNPS-N9-PRESS S3 P*.OUT ANSYS Pressure Linearized Stress Output Files.

PNPS-N9-#-THM.INP N9A Nozzle ANSYS Thermal Load Input File.

PNPS-N9-#-THM mntr.inp N9A Nozzle ANSYS Thermal Load mntr File Created from ANSYS Thermal Run.

PNPS-N9-#-STR.inp N9A Nozzle ANSYS Thermal Load Stress Input File.

PNPS-N9-#-STR S3 P*.OUT ANSYS Thermal Analysis Linearized Stress Output Files.

StressResults.xis Excel Spreadsheet to Summary Linearized Stress. Each Path Has One File at corresponded Directory.

VFAT-*&.xls Excel Spreadsheet to Create .str File.

VFAT-*o III.xls Excel Spreadsheet to Create .str File for Maximum Intensity Range only.

p*-& @.CYC Cycle Input File for VESLFAT Program.

p*-o Ill @.CYC Cycle Input File for Maximum Intensity Range only at Outside Surface Locations for

-__ -_VESLFAT Program.

p*-& @.FDT Material Input File for VESLFAT Program.

p*-oiIII .FDT Material Input File for Maximum Intensity Range only at Outside Surface Locations for VESLFAT Program.

p*-& @aý.str Stress Input File for VESLFAT Program Created by the spreadsheets.

p**-oIllI@.str Stress Input File for Maximum Intensity Range only at Outside Surface Locations for VESLFAT Program Created by the spreadsheets.

p*-&J@.ALL, p*-&_ .PR, p*-& @ RD.ST p*-&_@.ORD, Intermediate Result File Created by VESLFAT Program where * = Paths I through 9.

p**- o_IlI @.ALL p** o III _@.ORD, Intermediate Result File for Maximum Intensity Range only at Outside Surface Locations o III@.PR, p**- o III @.ST Created by VESLFAT Program.

p*-& @.fat Fatigue Result File Created by VESLFAT Program p**- o_II_@.fat Fatigue Result File for Maximum Intensity Range only at Outside Surface Locations Created by VESLFAT Program.

Pressure Summary.xls Summary of Pressure Results for Design Load and Pure Shear Evaluation Where:

• = Paths I through 4,

• • = Paths 1 and 4,

1. = Thermal transients 2, 3, 11, 13, 14, 17, 21, 24 (transient 24 has the same time history as transient 2),

& = i or o for inside surface (Nozzle side for path 2) or outside surface (seal side for Path 2), respectively,

= 508, M52, F304, or 304L for material at locations, see Table 4 for corresponded materials.

File No.: 0900530.306 Page B-2 of B-2 Revision: 0 F0306-OI RO

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Appendix C EXAMPLE VESLFAT FILES VESLFAT INPUT FILE pl-i_304L.CYC File No.: 0900530.306 Page C-I of C-40 Revision: 0 F0306-01 RO

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Trans Name cycles 1 2_DHydT1 130 2 2_DHydT2 130 3 2_DHydT3 130 4 3_Staupl 120 5 3_Staup2 120 6 11 LFWP1 30 7 11 LFWP2 30 8 11LFWP3 30 9 11 LFWP4 30 10 I1 LFWP5 30 11 I--LFWP6 30 12 II-LFWP7 30 13 1I-LFWP8 30 14 13 ROPI 1 15 13ROP2 1 16 13_ROP3 1 17 14 SRVB1 2 18 14_SRVB2 2 19 14-SRVB3 2 20 14 SRVB4 2 21 17_ImpSTl 5 22 17.ImpST2 5 23 17_ImpST3 5 24 21lShDwl 118 25 21-ShDw2 118 26 21-ShDw3 118 27 21 ShDw4 118 28 24_Hydrol 3 29 24_Hydro2 3 30 24_Hydro3 3 File No.: 0900530.306 Page C-2 of C-40 Revision: 0 F0306-01 RO

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VESLFAT INPUT FILE pl-i_304L.FDT Fatigue Analysis Properties - Note: All text must remain in the file - ksi 1.7 .3 m and n for elastic plastic analysis 28300 E fatigue Curve,ksi 1 Multiplying factor to convert *.STR file data to psi 0.010 Max Membrane Stress (ksi) per psi applied pressure 40 NB-3222.5 (b) limit on Sy if large number of cycles 25 Number of Points on Fatigue Curve 6 Number of points on Material Property Curve Fatigue Curve with Cycles (ascending) and Salt, ksi 10 708 20 512 50 345 100 261 200 201 500 148 1000 119 2000 97 5000 76 10000 64 20000 55.5 50000 46.3 100000 40.8 200000 35.9 500000 31 1000000 28.2 2000000 22.8 5000000 18.4 10000000 16.4 20000000 15.2 50000000 14.3 100000000 14.1 1000000000 1J.9 10000000000 13.7 100000000000 13.6 Material Property Curve (SA-240 TP 304L equivalent ASME 2001)

Temp E,ksi Sm, ksi Sy, ksi 70 28300 16.7 25.0 200 27600 16.7 21.4 300 27000 16.7 19.2 400 26500 15.8 17.5 500 25800 14.7 16.4 600 25300 14.0 15.5 File No.: 0900530.306 Page C-3 of C-40 Revision: 0 F0306-01 RO

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VESLFAT INPUT FILE pl-i_304L.STR Name Sxx Syy Szz Sxy Sxz Syz Sxx Syy Szz Sxy Sxz Syz Tmax Pmax 2_DHydT10 -2 -1596 -1383 119 0 0 1632 -1440 -51 0 0 100 0 2_DHydT10 -2 -1596 -1383 119 0 0 1632 -1440 -51 0 0 100 0 2DHydTIO -2 -1596 -1383 119 0 0 1632 -1440 -51 0 0 100 0 2DHydT10 -2 -1596 -1383 119 0 0 1632 -1440 -51 0 0 100 0 2_DHydTI0 -2 -1596 -1383 119 0 0 1632 -1440 -51 0 0 100 0 2DHydT10 -2 -1596 -1383 119 0 0 1632 -1440 -51 0 0 1-00 0 2DHydTI0 -2 -1596 -1383 119 0 0 1632 -1440 -51 0 0 100 0 2DHydTII -2 -1596 -1383 119 0 0 1632 -1440 -51 0 0 100 0 2DHydTI1 -2 -1596 -1383 119 0 0 1632 -1440 -51 0 ~0' 100 0 2DHydT21 -1248 -623 2718 193 0 0 -1248 -456 2829 54 0 0 100 1250 2DHydT21 -1248 -623 2718 193 0 0 -1248 -456 2829 54 0 0 100 1250 2DHydT21 -1248 -623 2718 193 0 0 -1248 -456 2829 54 0 0 100 1250 2DHydT21 -1248 -623 2718 193 0 0 -1248 -456 2829 54 0 0 100 1250 2_DHydT21 -1248 -623 2718 193 0 0 -1248 -456 2829 54 0 0 100 1250 2DHydT21 -1248 -623 2718 193 0 0 -1248 -456 2829 54 0 0 100 1250 2_DHydT21 -1248 -623 2718 193 0 0 -1248 -456 2829 54 0 0 100 1250 2DHydT22 -1248 -623 2718 19.3 0 0 -1248 -456 2829 54 0 0 100 1250 2DHydT22 -1248 -623 2718 193 0 0 -1248 -456 2829 54 0 0 100 1250 2_DHydT32 -27 -1577 -1301 120 0 0 1608 -1355 -49 0 0 100 25 3_StauplO -2 -1596 -1383 119 0 0 1632 -144b -51 0 0 100 0 3_Staupl328 -23 -2092 -1731 133 0. 0 2178 -1857 -65 0 0 107 21 3_Staup2657 -44 -2631 -2126 157 0 0 2734 -2287 -81 0 0 115. 41 3_Staup2985 -66 -3183 -2533 186 0 0 3290 -2715 -96 0 0 124 62 3_Staup21313 -87 -3745 -2950 217 0 0 3850 -3145 -112 0 0 133 83 3_Staup21970 -129 -4902 -3801 281 0 0 -129 -4987 -4012 -143 0 0 151 124 3_Staup22627 -172 -5925 -4554 351 0 0 -172 -6009 -4787 -171 0 0 170 166 File No.: 0900530.306 Page C-4 of C-40 Revision: 0 F0306-O1 RO

CStructuralIntegrity Associates, Inc.

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-0 11_LFWP11 -1093 -31389 -21879 1407 0 -1093 -30036 -21856 -757 0 532 1067 0

11 LFWP11 -1129 -31361 -21761 1409 0 -1129 -30003 -21733 -754 0* 532 1103 File No.: 0900530.306 Page C-5 of C-40 Revision: 0 F0306-01 RO

C StructuralIntegrityAssociates, Inc.

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Structural Integrity Associates, Inc.

11_LFWP2709 -1175 -17737 -11044 1063 0 0 -1175 -17419 -11369 -422 355 1160 l1_LFWP2896 -1177 -19487 -12484 1041 0 0 -1177 -19119 -12859 -470 373 1160 llLFWP31029 -1178 -20737 -13484 1040 0 0 -1178 -20299 -13869 -502 386 1160 11_LFWP31108 -1178 -21487 -14084 1042 0 0 -1178 -20999 -14469 -521 394 1160 11_LFWP31188 -1179 -22217 -14664 1046 0 0 -1179 -21659 -15019 -539 402 1160 11 LFWP31267 -1180 -22777 -15094 1057 0 0 -1180 -22199 -15449 -553 410 1160 11_LFWP31346 -1180 -23277 -15514 1077 0 0 -1180 -22689 -15869 -567 418 1160 11_LFWP31465 -1181 -24027 -16124 1109 0 0 -1181 -23419 -16489 -588 4ý3 0 1160 11_LFWP31584 -1182 -24767 -16734 1143 0 0 -1182 -24139 -17109 -609 442 1160 llLFWP31702 -1182 -25507 -17324 1178 0 0 -1182 -24859 -17709 -629 454 1160 11_LFWP31821 -1183 -26387 -17974 1201 0 0 -1183 -25659 -18339 -648 466 1160 11 LFWP32019 -1184 -27917 -19054 1229 0 0 -1184 -27059 -19379 -682 486 1160 11_LFWP32213 -1185 -29477 -20154 1254 0 0 -1185 -28499 -20449 -716 506 1160 11_LFWP32217 -1180 -29251 -19980 1259 0 0 -1180 -28074 -20066 -704 505 1155 11_LFWP32220 -1174 -28915 -19717 1268 0 0 -1174 -27548 -19593 -688 503 1150 11_LFWP32224 -1168 -28519 -19423 1279 0 0 -1168 -26993 -19100 -672 502 1145 11_LFWP32227 -1163 -28103 -19110 1290 0 0 -1163 -26428 -18617 -656 500 1140 11 LFWP32235 -1151 -27240 -18472 1316 0 0 -1151 -25317 -17671 . 625 495 1130 11_LFWP42242 -1140 -26378 -17855 1339 0 0 -1140 -24277 -16805 -597 491 1120 11_LFWP42250 -1128 -25487 -17230 1362 0 0 -1128 -23217 -15952 -569 485 1109 11_LFWP42259 -1114 -24417 -16485 1385 0 0 -1114 -21979 -14958 -536 478 1096 11_LFWP42271 -1095 -23130 -15580 1407 0 0 -1095 -20525 -13805 -498 468 1079 11_LFWP42286 -1073 -21596 -14519 1426 0 0 -1073 -18855 -12497 -455 455 1058 11 LFWP42305 -1045 -19797 -13264 1442 0 0 -1045 -16939 -11005 -406 439 1032 11_LFWP42342 -991 -16546 -11050 1454 0 0 -991 -13587 -8479 -321 405 981 11_LFWP42383 -930 -13031 -8368 1399 0 0 -930 -9861 -5416 -219 365 924 11_LFWP42393 -915 -12132 -7674 1387 0 0 -915 -8971 -4681 -195 356 910 11_LFWP42481 -924 -12958 -8208 1242 0 0 -924 -11519 -7035 -271 334 915

-11 LFWP42568 -931 -14044 -8951 1144 0 0 -931 -13205 -8498 -316 327 920 File No.: 0900530.306 Page C-7 of C-40 Revision: 0 F0306-O1 RO

C StructuralIntegrity Associates, Inc.

9 11_LFWP42675 -938 -14969 -9561 1066 0 0 -938 -14409 -9467 -349 0 0 326 926 9 llLFWP42808 -947 -15683 -10077 1013 0 0 -947 -15242 -10172 -374 329 934 9 11_LFWP43072 -963 -16611 -10837 976 0 0 -963 -16258 -11060 -405 339 949 9 11_LFWP43337 -979 -17380 -11468 982 0 0 -979 -17023 -11728 -429 351 964 9 11_LFWP43602 -995 -18408 -12268 994 0 0 -995 -17999 -12537 -454 363 979 9 11 LFWP43777 -1006 -19120 -12805 1004 0 0 -1006 -18670 -13063 -471 371 989 9 11_LFWP43952 -1016 -19842 -13342 1016 0 0 -1016 -19340 -13588 -488 379 999 9 11_LFWP44127 -1027 -20575 -13880 1029 0 0 -1027 -20021 -14114 -505 387 1009 9 l1_LFWP44302 -1037 -21317 -14417 1043 0 0 -1037 -20712 -14640 -522 395 1019 9 11 LFWP44565 -1053 -22275 -15097 1069 0 0 -1053 -21588 -15299 -544 407 1034 10 11_LFWP54828 -1069 -23023 -15648 1107 0 0 -1069 -22313 -15858 -563 419 1049 10 11 LFWP55091 -1084 -23762 -16199 1146 0 0 -1084 -23029 -16406 -582 431 1064 10 11_LFWP55354 -1100 -24510 -16740 1186 0 0 -1100 -23755 -16955 -601 443 1079 10 11_LFWP55792 -1126 -25871 -17698 1236 0 0 -1126 -25032 -17890 -632 463 1104 10 11_LFWP56230 -1152 -27391 -18686 1268 0 0 -1152 -26418 -18835 -663 483 1129 10 11_LFWP56668 -1178 -28952 -19694 1296 0 0 -1178 -27845 -19819 -695 503 1154 10 11 LFWP56773 -1185 -29387 -20034 1310 0 0 -1185 -28249 -20149 -706 508 1160 10 11_LFWP56781 -1175 -29074 -19804 1318 0 0 -1175 -27758 -19720 -692 507 1151 10 11_LFWP56790 -1165 -28661 -19514 1328 0 0 -1165 -27206 -19251 -676 505 1142 10 11_LFWP56798 -1155 -28229 -19205 1339 0 0 -1155 -26655 -18803 -661 502 1132 10 11_LFWP56807 -1145 -27786 -18885 1348 0 0 -1145 -26124 -18364 -647 5oo 1123 10 11_LFWP56823 -1126 -26950 -18285 1361 0 0 -1126 -25151 -17577 -621 494 1105 11 11 LFWP66840 -1107 -26184 -17766 1373 0 0 -1107 -24308 -16920 -599 488 1086 11 11_LFWP66857 -1087 -25439 -17276 1382 0 0 -1087 -23516 -16323 -579 482 1068 11 11_LFWP66877 -1065 -24625 -16736 1390 0 0 -1065 -22666 -15696 -559 474 1047 11 11_LFWP66900 -1039 -23695 -16120 1395 0 0 -1039 -21730 -15013 -536 464 1021 11 11_LFWP66927 -1008 -22638 -15437 1398 0 0 -1008 -20688 -14265 -510 453 991 11 11_LFWP66959 -973 -21455 -14671 1398 0 0 -973 -19530 -13442 -483 439 957 11 11 LFWP67015 -909 -19583 -13443 1378 0 0 -909 -17688 -12153 -435 414 895 File No.: 0900530.306 Page C-8 of C-40 Revision: 0 F0306-OIRO

C StructuralIntegrityAssociates, Inc.

11 llLFWP67083 -832 -17332 -11769 1308 0 -832 -15399, -10350 -374 0 383 820 11 llLFWP67166 -739 -14022 -9395 1257 0 -739 -12364 -8057 -300 0 345 730 11 11 LFWP67193 -709 -13125 -8823 1241 0 -709 -11542 -7509 -281 0 333 700 11 llLFWP67199 -709 -13085 -8803 1233 0 -709 -11612 -7600 -284 0 331 700 11 11_LFWP67205 -709 -13105 -8823 1223 0 -709 -11732 -7720 -288 0 329 700 11 11 LFWP67223 -710 -13275 -8953 1195 0 -710 -12102 -8080 -298 0 326 700 11 11_LFWP67253 -711 -13585 -9143 1150 0 -711 -12632 -8540 -312 0 322 700 11 11_LFWP67313 -711 -14055 -9433 1083 0 -711 -13362 -9130 -331 0 317 700 11 l1_LFWP67373 -712 -14345 -9613 1035 0 -712 -13772 -9480 -343 0 314 700 11 llLFWP67433 -712 -14525 -9733 998 0 -712 -14022 -9700 -350 0 313 700 11 11iLFWP67493 -713 -14625 -9823 969 0 -713 -14162 -9830 -355 0 312 700 11 11 LFWP67565 -704 -14852 -10043 942 0 -704 -14450 -10131 -365 0 313 691 11 11_LFWP67637 -695 -15049 -10244 923 0 -695 -14679 -10372 -374 0 314 682 11 11_LFWP67787 -676 -15374 -10597 901 0 -676 -15037 -10778 -387 0 317 662 11 11_LFWP67902 -662 -15596 -10845 893 0 -662 -15271 -11048 -395 0 320 648 11 11_LFWP68065 -641 -15892 -11183 888 0 -641 -15580 -11399 -407 0 325 627 11 11_LFWP68227 -621 -16188 -11491 891 0 -621 -15870 -11730 -417 0 329 606 11 11 LFWP68390 -601 -16474 -11799 897 0 -601 -16159 -12051 -427 0 334 585 11 11_LFWP68553 -580 -16761 -12098 907 0 -580 -16449 -12352 -437 0 338 565 11 11_LFWP68716 -560 -17047 -12396 918 0 -560 -16739 -12663 -446 0 343 544 11 11_LFWP68879 -539 -17333 -12684 930 0 -539 -17028 -12954 -456 0 347 523 11 11_LFWP69032 -520 -17628 -12979 942 0 -520 -17317 .- 13261 -465 0 351 503 11 11_LFWP69248 -493 -18170 -13469 953 0 -493 -17833 -13755 -480 0 357 476 11 11 LFWP69464 -466 -18731 -13970 964 0 -466 -18359 -14250 -495 0 363 448 11 11_LFWP69680 -439 -19293 -14480 974 0 -439 -18894 -14754 -511 0 369 421 11 11_LFWP69896 -412 -19864 -14981 983 0 -412 -19430 -15258 -526 0 375 393 12 11_LFWP710256 -367 -20820 -15842 999 0 -367 -20334 -16105 -552 0 385 347 12 11_LFWP710616 -322 -21806 -16703 1014 0 -322 -21247 -16962 -578 0 395 301 12 11 LFWP710976 -276 -22652 -17464 1033 0 -276 .- 22050 -17709 -601 0 405 255 File No.: 0900530.306 Page C-9 of C-40 Revision: 0 F0306-O1 RO

C StructuralIntegrity Associates, Inc.

12 l1_LFWP711093 -262 -22873 -17683 1042 0 -262 -22264 -17930 -608 409 240 12 llLFWP711198 -278 -23041 -17770 1052 0 -278 -22429 -18026 -611 412 256 12 l1_LFWP711303 -294 -23218 -17868 1063 0 -294 -22594 -18112 -615 415 272 12 11_LFWP711408 -310 -23386 -17956 1073 0 -310 -22759 -18208 -619 417 288 412 11_LFWP711513 -326 -23564 -18054 1084 0 -326 -22925 -18303 -622 420 304 12 11 LFWP711724 -358 -23909 -18239 1104 0 -358 -23255 -18484 -629 426 335 12 11_LFWP711934 -390 -24244 -18425 1125 0 -390 -23585 -18676 -636 432 367 12 11_LFWP712144 -422 -24589 -18611 1146 0 -422 -23905 -18858 -644 438 399 12 11_LFWP712354 -454 -24935 -18797 1166 0 -454 -24235 -19039 -651 444 431 12 11_LFWP712565 -486 -25270 -18982 1187 0 -486 -24565 -19220 -658 450 463 12 11_LFWP712775 -518 -25655 -19178 1203 0 -518 -24915 -19412 -665 455 494 12 11 LFWP712985 -550 -26080 -19384 1214 0 -550 -25295 -19603 -672 461 526 12 11_LFWP713300 -598 -26713 -19697 1230 0 -598 -25860 -19900 -682 470 574 12 11_LFWP713616 -646 -27356 -20010 1246 0 -646 -26435 -20187 -693 479 622 12 11 LFWP713931 -694 -27999 -20324 1261 0 -694 -27011 -20474 -704 488 669 12 11_LFWP714247 -742 -28642 -20627 1276 0 -742 -27596 -20761 -714 496 717 12 11 LFWP714772 -822 -29850 -21347 1314 0 -822 -28711 -21460 -738 511 796 12 l1_LFWP715298 -903 -31098 -22176 1357 0 -903 -29876 -22258 -766 526 876 12 l1_LFWP715823 -983 -32366 -23015 1399 0 -983 -31071 -23087 -794 540 955 12 11_LFWP716349 -1063 -33424 -23654 1443 0 -1063 -32047 -23705 -815 555 io35 12 11_LFWP716549 -1063 -33304 -23564 1457 0 -1063 -31887 -23555 -810 556 1035 12 11_LFWP716749 -1063 -33264 -23534 1464 0 -1063 -31837 -23515 -809 556 1035 12 11 LFWP716973 -1063 -33264 -23524 1468 0 -1063 -31827 -23495 -808 556 1035 12 11_LFWP717242 -1063 -33264 -23514 1470 0 -1063 -31837 -23485 -808 556 1035 12 11_LFWP717934 -1063 -33274 -23514 1472 0 -1063 -31837 -23485 -808 556 1035 12 11_LFWP718783 -1063 -33274 -23514 1473 0 -1063 -31837 -23485 -808 556 1035 12 11_LFWP719688 -1063 -33274 -23514 1473 0 -1063 -31837 -23485 -808 556 1035 12 11_LFWP721688 -1063 -33274 -23514 1473 0 -1063 -31837 -23485 -808 556 1035 12 11 LFWP723688 -1063 -33274 -23514 1473 0 -1063 -31837 -23485 -808 556 1035 File No.: 0900530.306 Page C-10 of C-40 Revision: 0 F0306-01 RO

StructuralIntegrity Associates, Inc.

12 11 LFWP725688 -1063 -33274 -23514 1473 0 0 -1063 -31837 -23485 -808 0 0 556 1035 12 11_LFWP726349 -1063 -33274 -23514 1473 0 -1063 -31837 -23485 -808 556 1035 12 11_LFWP726349 -1063 -33274 -23514 1473 0 -1063 -31837 -23485 -808 556 1035 12 11_LFWP726349 -1063 -33274 -23514 1473 0 -1063 -31837 -23476 -808 556 1035 12 11_LFWP726349 -1063 -33274 -23514 1473 0 -1063 -31827 -23476 -808 556 1035 12 11_LFWP726349 -1063 -33274 -23504 P473 0 -1063 -31807 -23446 -807 556 1035 12 l1 LFWP726349 -1063 -33254 -23494 1473 0 -1063 -31727 -23366 -804 555 1035 12 l1_LFWP726350 -1063 -33224 -23464 1473 0 -1063 -31627 -23275 -801 555 1035 12 11_LFWP726350 -1063 -33194 -23434 1474 0 -1063 -31517 -23165 -798 555 1035 12 11_LFWP726350 -1062 -33154 -23404 1474 0 -1062 -31427 -23075 -795 555 1035 12 11_LFWP726350 -1062 -33144 -23394 1474 0 -1062 -31387 -23035 -794 554 1035 12 11_LFWP726550 -1063 -32804 -23154 1467 0 -1063 -31297 -23035 -793 549 1035 12 11 LFWP726750 -1063 -32844 -23174 1457 0O -1063 -31407 -23125 -796 548 1035 12 11_LFWP726950 -1063 -32864 -23184 1453 0 -1063 -31437 -23155 -797 548 1035 12 11_LFWP727150 -1063 -32864 -23194 1451 0 -1063 -31447 -23155 -797 548 1035 12 l1_LFWP727564 -1063 -32864 -23194 1449 0 -1063 -31447 -23165 -798 548 1035 12 11_LFWP728094 -1063 -32864 -23194 1448 0 -1063 -31447 -23165 -798 548 1035 12 11_LFWP729429 -1063 -32864 -23194 1448 0 -1063 -31447 -23165 -798 548 1035 12 11 LFWP731429 -1063 -32864 -23194 1448 0 -1063 -31447 -23165 -798 548 1035 12 11_LFWP733429 -1063 -32864 10 63

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C StructuralIntegrity Associates, Inc.

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C Structural Integrity Associates, Inc.

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23 17_ImpST33638 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 532 1035 24 21_ShDwlO -1063 -33294 -23514 1471 0 0 -1063 -31867 -23495 -809 0 556 1035 24 21_ShDwl123 -1042 -33300 -23582 1471 0 0 -1042 -31866 -23556 -810 0 556 1014 24 21_ShDw1246 -1022 -33307 -23650 1471 0 0 -1022 -31886 -23627 -812 0 556 994 24 21_ShDw1544 -972 -33346 -23814 1468 0 0 -972 -31923 -23798 -816 0 556 944 25 21 ShDw2960 -902 -33400 -24044 1463 0 0 -902 -31988 -24037 -822 0 556 874 25 21_ShDw21865 -751 -33518 -24543 1454 0 0 -751 -32131 -24556 -834 0 556 722 25 21_ShDw22782 -597 -33638 -25049 1445 0 0 -597 -32276 -25083 -847 0 556 567 25 21_ShDw23700 -443 -33759 -25555 1436 0 0 -443 -32422 -25610 -860 0 556 413 25 21_ShDw24931 -237 -33920 -26234 1423 0 0 -237 -32616 -26317 -878 0 556 206 25 21_ShDw26156 -32 -34080 -26910 1411 0 0 32810 -27020 -895 0 556 0 25 21_ShDw26168 -31 -33730 -26640 1419 0 0 32310 -26570 -880 0 554 0 25 21 ShDw26180 -30 -33340 -26340 1429 0 0 31800 -26130 -866 0 551 0 25 21_ShDw26192 -30 -32930 -26040 -1438 0 0 31260 -25670 -851 0 548 0 25 21_ShDw26204 -29 -32470 -25700 1445 0 0 30710 -25210 -836 0 545 0 25 21_ShDw26228 -28 -31520 -24930 1447 0 0 29670 -24290 -806 0 537 0 25 21_ShDw26252 -27 -30580 -24170 1447 0 0 28670 -23430 -779 0 530 0 25 21 ShDw26277 -26 -29660 -23420 1444 0 0 27730 -22610 -752 0 522 0 25 21_ShDw26304 -25 -28640 -22590 1436 0 0 26710 -21710 -724 0 512 0 25 21_ShDw26337 -24 -27520 -21650 1425 0 0 25590 -20730 -692 0 501 0 26 21_ShDw36373 -22 -26350 -20680 1406 0 0 24480 -19740 -660 0 488 0 26 21_ShDw36414 -21 -25160. -19800 1400 0 0 23360 -18860 -633 0 473 0 26 21 ShDw36485 -20 -23150 -18340 1393 0 0 21480 -17400 -586 0 447 0 26 21_ShDw36567 -18 -21000 -16750 1361 0 0 19410 -15790 -530 0 417 0 26 21_ShDw36661 -16 -18530 -14710 1272 0 0 16950 -13650 -460 0 382 0 26 21_ShDw36756 -13 -15380 -12280 1215 0 0 14030 -11280 -386 0 348 0 26 21_ShDw36922 -15 -15620 -12510 1081 0 0 14980 -12280 -417 0 332 0 26 21_ShDw37087 -15 -15690 -12550 989 0 0 15230 -12540 -426 0 324 0 26 21 ShDw37253 -15 -15530 -12450 929 0 0 15130 -12520 -425 0 319 0 File No.: 0900530.306 Page C-19 of C-40 Revision: 0 F0306-01 RO

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26 21_ShDw37418 -15 -15280 -12300 886 0 0 14920 -12390 -421 314 26 '21_ShDw37750 -15 -14720 -11910 827 0 0 14390 -12020 -408 304 26 21_ShDw38081 -14 -14120 -11480 787 0 0 13810 -11590 -394 295 26 21_ShDw38412 -14 -13480 -11010 757 0 0 13200 -11130 -378 286 26 21_ShDw38743 -13 -12840 -10530 730 0 0 12600 -10650 -363 276 26 21 ShDw39074 -13 -12220 -10050 704 0 0 12000 -10170 -347 267 26 21_ShDw39406 -12 -11590 -9572 678 0 0 11400 -9694 -331 258 26 21_ShDw39737 -11 -10960 -9083 652 0 0 10790 -9201 -315 249 26 21_ShDw310234 -10 -9893 -8239 614 0 0 -10 -9770 -8356 -287 235 26 21_ShDw310730 -9 -8860 -7417 575 0 0 -9 -8775 -7531 -260 222 26 21 ShDw311227 -9 -7861 -6617 534 0 0 -9 -7809 -6725 -233 208 208 194 26 21_ShDw311724 -8 -6962 -5890 490 0 0 -8 -6929 -5988 -

26 21_ShDw312552 -6 -5663 -4806 406 0 0 -6 -5623 -4868 -169 172 26 21_ShDw313380 -5 -4355 -3711 324 0 0 -5 -4306 -3736 -130 149 26 21_ShDw314208 -3 -2911 -2519 247 0 0 -3 -2877 -2518 -88 127 27 21_ShDw415036 -2 -1575 -1404 168 0 0 -2 -1541 -1371 -48 105 27 21 ShDw415072 -2 -1559 -1388 164 0 0 -2 -1537 -1368 -48 104 27 21_ShDw415108 -2 -1552 -1379 160 0 0 -2 -1539 -1370 -48 103 27 21_ShDw415216 -2 -1549 -1369 153 0 0 -2 -1553 -1380 -48 102 27 21_ShDw415467 -2 -1559 -1369 141 0 0 -2 -1579 -1402 -49 101 27 21_ShDw416132 -2 -1581 -1380 127 0 0 -2 -1614 -1430 -50 100 27 21_ShDw416852 -2 -1590 -1384 122 0 0 -2 -1626 -1439 -50 100 27 21 ShDw417572 -2 .1593 -1385 120 0 0 -2 -1629 -1441 -51 100 27 21_ShDw418292 -2 -1595 -1384 119 0 0 -2 -1631 -1441 -51 100 27 21_ShDw418636 -2 -1595 -1384 119 0 0 -2 -1631 -1441 -51 100 27 21_ShDw418646 -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 100 28 24 HydrolO -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 100 28 24 HydrolO -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 100 28 24_Hydrol0 -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 100 File No.: 0900530.306 Page C-20 of C-40 Revision: 0 F0306-O1RO

StructuralIntegrity Associates, Inc.

28 24_HydrolO -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 28 24 -HydrolO -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 28 24-HydrolO -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 28 24_HydrolO -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 28 24_Hydroll -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 .0 28 24 Hydroll -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 29 24 _Hydro2l -1562 -378 3752 212 0 0 -1562 -160 3904 81 0 0 I00 1565 29 24 Hydro2l -1562 -378 3752 212 0 0 -1562 -160 3904 81 0 0 100 1565 29 24 Hydro2l -1562 -378 3752 212 0 0 -1562 -160 3904 81 0 0 100 1565 29 24_Hydro2l -1562 -378 3752 212 0 0 -1562 -160 3904 81 0 0 100 1565 29 24_Hydro2l -1562 -378 3752 212 0 0 -1562 -160 3904 81 0 0 100 1565 29 24_Hydro2l -1562 -378 3752 212 0 0 -1562 -160 3904 81 0 0 100 1565 29 24 Hydro2l -1562 -378 3752 212 0 0 -1562 -160 3904 81 0 0 100 1565 29 24_Hydro22 -1562 -378 3752 212 0 0 -1562 -160 3904 81 0 0 100 1565 29 24_Hydro22 -1562 -378 3752 212 0 0 -1562 -160 3904 81 0 0 100 1565 30 24_Hydro32 -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 File No.: 0900530.306 Page C-21 of C-40 Revision: 0 F0306-O1 RO

StructuralIntegrity Associates, Inc.

VESLFAT OUTPUT FILE pl-i_304L.FAT VESLFAT Version 1.42 12/29/2006 (VeslFatlp42) 06-23-2009 23:04:07 Page 1 VESLFAT Load Set Pair Module Version 1.42 - 01/03/2007 (&VeslFatPairlp42)

Stress Pairing Analysis Elastic Plastic Properties m= 1.7 n= 0.3 Stresses Multiplied by 1 to convert to psi Max General Membrane Stress(ksi) per unit Pressure (psi) = 0.01 Upper Limit on Sy for large number of cycles NB-5222.5(b) (ksi) 40 Material Properties vs Temperature T,F E, ksi 3Sm, ksi Sy, ksi 70 28300 16.7 25.0 200 27600 16.7 21.4 300 27000 16.7 19.2 400 26500 15.8 17.5 500 25800 14.7 16.4 600 25300 14.0 15.5 Stress ranges < 13328 psi neglected Files:

Input Stress File = pl-i 304L.STR Converted Stress File = pl-i 304L.STI All Stress Ranges File pl-i 304L.ALL Significant Ranges File = pl-i_304L.PR Thermal Ratchet Case File = pl-i 304L.TRC Max Ratio of Sn/3Sm = 0.822699 for Trans Pair 25 and 29 Max P+Q Stress, psi = 35313.51 <= 3Sm, psi = 42924 VESLPAT Load Pair Sort Module Version 1.42 - 12/29/2006 (&VeslFatSortlp42)

Sorting Stress Ranges from File = pl-i_304L.PR Storing Output Ordered Ranges in File = pl-i 304L.ORD Fatigue Analysis using VESLFAT Fatigue Module Version 1.42 - 12/29/2006 (&VeslFatFatlp42)

Page 2 06-23-2009 23:04:20 Input Echo:

Fatigue Properties:

m= 1.7 n= 0.3 E (Fatigue Curve), ksi = 28300 E (Analysis) chosen at the highest of transient pair temperatures Sm chosen at the highest of transient pair temperatures Fatigue Curve: Cycles Salt, ksi File No.: 0900530.306 Page C-22 of C-40 Revision: 0 F0306-01 RO

StructuralIntegrity Associates, Inc.

1.0E+01 708.00

2. OE+01 512.00

5. 0E+01 345.00

1. OE+02 261.00

2. 0E+02 201.00

5. OE+02 148.00

1. OE+03 119.00

2. OE+03 97.00

5. 0E+03 76.00

1. OE+04 64 . 00

2. OE+04 55.50

5. 0E+04 46.30

1. 0E+05 40.80

2. OE+05 35.90

.5.0E+05 31.00

1. 0E+06 28.20

2. 0E+06 22.80

5. 0E+06 18.40

1. 0E+07 16.40

2. 0E+07 15.20

5. OE+07 14.30

1. OE+08 14.10

1. OE+09 13.90 I

1. 0E+10 13.70

1. OE-+ 13.60 Events: Index Name Num. Cycles 1 2 DHydTl 130 2 2 _DHydT2 130 3 2 _DHydT3 130 4 3 Staupl 120 5 3 Staup2 120 1

6 i11LFWP1 30 I

7 1 1I--LFWP2 30 8 1 1 LFWP3 30 I

9 1 1 LFWP4 30 1

10 1 1I LFWP5 30 11 I1 1 LFWP6 30 1

12 1 1_LFWP7 30 1

13 1I1_LFWP8 30 3 1 14 1:3 ROPI File No.: 0900530.306 Page C-23 of C-40 Revision: 0 F0306-OIRO

Structural Integrity Associates, Inc.

Fatigue Analysis using VESLFAT Fatigue Module Version 1.42 - 12/29/2006 (&VeslFatFatlp42)

Page 3 06-23-2009 23:04:20 15 13_ROP2 1 16 13_ROP3 1 17 14 _SRVB 2 18 14 _SRVB2 2 19 14-SRVB3 2 20 140SRVB4 2 21 17_lImpSTl 5 22 17_ImpST2 5 23 17ImpST3 5 24 21_ShDwl 108 2521 ShDw2 118 26 21_ShDw3 118 27 21_ShDw4 118 28 24NHydrol 3 29 24 Hydro2 3 30 24Hydro3 3 Stress input file:

N Name Sxx Syy Szz Sxy Sxz Syz Sxx Syy Szz Sxy Sxz Syz Tmax Pmax 1 2_DHydTlO -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 1 2_DHydT1O -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 1 2DHydTlO -2 -1596 .- 1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 1 2_DHydTlO -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 1 2DHydTIO -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 1 2_DHydTlO -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 1 2_DHydTlO -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 1 2_DHydTll -2 -1596 -1383 119 0 0. -2 -1632 -1440 -51 0 0 100 0 1 2_DHydTIl -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 2 2_DHydT21 -1248 -623 2718 193 0 0 -1248 -456 2829 54 0 0 100 1250 2 2_DHydT21 -1248 -623 2718 193 0 0 -1248 -456 2829 54 0 0 100 1250 2 2_DHydT21 -1248 -623 2718 193 0 0 -1248 -456 2829 54 0 0 100 1250 2 2DHydT21 -1248 -623 2718 193 0 0 -1248 -456 2829 54 0 0 100 1250 2 2 DHydT21 -1248 -623 2718 193 0 0 -1248 -456 2829 54 0 0 100 1250 2 2 DHydT21 -1248 -623 2718 193 0 0 -1248 -456 2829 54 0 0 100 1250 2 2DHydT21 -1248 -623 2718 193 0 0 -1248 -456 2829 54 0 0 100 1250 2 2DHydT22 -1248 -623 2718 193 0 0 -1248 -456 2829 54 0 0 100 1250 2 2DHydT22 -1248 -623 2718 193 0 0 -1248 -456 2829 54 0 0 100 1250 3 2 DHydT32 -27 -1577 -1301 120 0 0 -27 -1608 -1355 -49 0 0 100 25 4 3StauplO -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 4 3_Staup1328 -23 -2092 -1731 133 0 0 -23 -2178 -1857 -65 0 0 107 21 5 35Staup2657 -44 -2631 -2126 157 0 0 -44 -2734 ,-2287 -81 0 0 115 41 5 35Staup2985 -66 -3183 -2533 186 0 0 -66 -3290 -2715 -96 0 0 124 62 5 3Staup21313 -87 -3745 -2950 217 0 0 -87 -3850 -3145 -112 0 0 133 83 5 39Staup21970 -129 -4902 -3801 281 0 0 -129 -4987 -4012 -143 0 0 151 124 5 3_Staup22627 -172 -5925 -4554 351 0 0 -- 172 -6009 -4787 -171 0 0 170 166 5 3_Staup23283 -214 -6937 -5297 423 0 0 -214 -7020 -5552 -199 0 0 188 207 5 3_Staup23940 -257 -8026 -6094 491 0 0 -257 -8097 -6369 -228 0 0 207 248 5 3_Staup24597 -299 -9325 -7031 550 0 0 -299 -9347 -7308 -261 0 0 225 290 5 3_Staup25253 -342 -10682 -8007 605 0 0 -342 -10649 -8281 -294 0 0 244 331 5 3_Staup25910 -384 -11960 -8897 660 0 0 -384 -11850 -9158 -324 0 0 262 373 5 3Staup26895 -448 -13782 -10134 740 0 0 -448 -13581 -10386 -366 0 0 290 435 File No.: 0900530.306 Page C-24 of C-40 Revision: 0 F0306-O1RO

Structural Integrity Associates, Inc.

5 3Staup27880 -511 -15523 -11320 826 0 0 -511 -15253 -11573 -408 0 0 317 497 5 3_Staup28865 -575 -17155 -12456 922 0 0 -575 -16844 -12731 -449 0 0 345 559 5 3Staup29850 -639 -19377 -14012 991 0 0 -639 -18926 -14259 -500 0 0 372 621 File No.: 0900530.306 Page C-25 of C-40

-Revision: 0 F0306-01 RO

StructuralIntegrity Associates, Inc.

Fatigue Analysis using VESLFAT Fatigue Module Version 1.42 - 12/29/2006 (&VeslFatFatlp42)

Page 4 06-23-2009 23:04:20 5 3_Staup211491 -745 -23076 -16543 1100 0 0 -745 -22369 -16736 -582 0 0 418 724 5 3_Staup213133 -851 -26015 -18513 0236 0 0 -851 -25161 -18692 -650 0 0 463 828 5 3_Staup214774 -957 -29575 -20774 1316 0 0 -957 -28424 -20859 -723 0 0 509 931 5 3_Staup216416 -1063 -33424 -23654 1443 0 0 -1063 -32047 -23705 -815 0 0 555 1035 5 3Staup216452 -1063 -33374 -23624 1448 0 0 -1063 -31977 -23645 -813 0 0 555 1035 5 3Staup216488 -1063 -33334 -23594 1452 0 0 -1063 -31927 -23595 -812 0 0 555 1035 5 38taup216596 -1063 -33284 -23554 1458 0 0 -1063 -31857 -23535 -810 0 0 556 1035 5 3_Staup216784 -1063 -33264 -23534 1464 0 0 -1063 -31837 -23505 -809 0 0 556 1035 5 3Staup217289 -1063 -33264 -23514 1470 0 0 -1063 -31837 -23485 -808 0 0 556 1035 5 3Staup217973 -1063 -33274 -23514 1472 0 0 -1063 -31837 -23485 -808 0 0 556 1035 5 3_Staup218693 -1063 -33274 -23514 1473 0 0 -1063 -31837 -23485 -808 0 0 556 1035 5 3_Staup219413 -1063 -33274 -23514 1473 0 0 -1063 -31837 -23485 -808 0 0 556 1035 5 3Staup220016 -1063 -33274 -23514 1473 0 0 -1063 -31837 -23485 -808 0 0 556 1035 5 3_Staup220026 -1063 -33274 -23514 1473 0 0 -1063 -31837 -23485 -808 0 0 556 1035 6 I LFWPIO -1061 -31414 -21984 1405 0 0 -1061 -30067 -21965 -760 0 0 532 1035 6 11 LFWPIO -1065 -31412 -21972 1405 0 0 -1065* -30063 -21953 -760 0 0 532 1039 6 11 LFWP10 -1069 -31409 -21961 1405 0 0 -1069 -30060 -21941 -759 0 0 532 1042

-21935 1406 0 0 -1076 -30052 -21914 -759 0 0 532 1050 6 11 LFWPIO -1076 -31403 6 11 LFWP1I -1093 -31389 -21879 1407 0 0 -1093 -30036 -21856 -757 0 0 532 1067 6 11 LFWPlI -1129 -31361 -21761 1409 0 0 -1129 -30003 -21733 -754 0 0 532 1103 6 11-LFWP12 -1165 -31333 -21643 1411 0 0 -1165 -29969 -21610 -751 0 0 532 1139 6 11 LFWP12 -1201 -31305 -21525 1413 0 0 -1201 -29935 -21487 -748 0 0 532 1175 6 11 LFWP1I3 -1230 -31283 -21430 1415 0 0 -1230 -29908 -21388 -746 0 0 532 1204 6 1i LFWPI3 -1241 -31264 -21394 1416 0 0 -1241 -29887 -21351 -745 0 0 532 1215 6 11 LFWP13 -1240 -31265 -21397 1416 0 0 -1240 -29888 -21355 -745 0 0 532 1214 6 11 LFWPI3 -1239 -31266 -21401 1416 0 0 -1239 -29889 -21358 -745 0 0 532 1213 6 11 LFWP14 -1235 -31269 -21412 1416 0 0 -1235 -29892 -21370 -745 0 0 532 1210 6 T1-LFWP15 -1230 -31273 -21430 1415 0 0 -1230 -29898 -21388 -746 0 0 532 1204 6 11 LFWPO7 -1219 -31281 -21466 1415 0 0 -1219 -29908 -21426 -746 0 0 532 1193 6 11 LFWPl9 -1208 -31290 -21502 1415 0 0 -1208 -29918 -21463 -747 0 0 532 1182 6 11 LFWP111 -1197 -31298 -21538 1414 0 0 -1197 -29929 -21501 -748 0 0 532 1171 6 T1-LFWP1I3 -1186 -31307 -21574 1414 0 0 -1186 -29939 -21539 -749 0 0 532 1160 6 11LFWP117 -1185 -31017 -21334 1420 0 0 -1185 -29449 -21069 -734. 0 0 530 1160 6 11 LFWP122 -1185 -30607 -21004 1429 0 0 -1185 -28849 -20539 -717 '0 0 528 1160 6 11-LFWP126 -1184 -30147 -20644 1440 0 0 -1184 -28239 -19989 -699 0 0 526 1160 6 11 LFWP131 -1183 -29657 -20264 1451 0 0 -1183 -27619 -19449 -682 0 0 523 1160 6 11 LFWPI39 -1182 -28677 -19504 . 1472 0 0 -1182 -26409 -18399 -648 0 0 518 1160 6 11 LFWP149 -1180 -27657 -18724 1490 0 0 -1180 -25199 -17359 -614 0 0 512 1160 7 11-LFWP260 -1179 -26387 -17744 1506 0 0 -1179 -23749 -16119 -574 O0 0 504 1160 7 11 LFWP275 -1177 -24847 -16534 1517 0 0 -1177 -22069 -14669 -527 0 0 492 1160 7 11 LFWP294 -1175 -23097 -15134 1518 0 0 -1175 -20209 -13059 -475 0 0 477 1160 7 11 LFWP2117 -1173 -21117 -13684 1529 0 0 -1173 -18169 -11399 -423 0 0 458 1160 7 11 LFWP2145 -1171 -18817 -12004 1539 0 0 -1171 -15839 -9539 -363 0 0 434 1160 7 11 LFWP2198 -1167 -14797 -9024 1517 0 0 -1167 -11629 -6169 -249 0 0 386 1160 7 11L-LFWP2233 -1164 -11977 -6694 1464 0 0 -1164 -8890 -3774 -172 0 0 354 1160 7 11 LFWP2273 -1166 -12417 -6974 1371 0 0 -1166 -10519 -5294 -222 0 0 341 1160.

7 11 LFWP2312 -1168 -13217 -7574 1302 0 0 -1168 -11929 -6589 -263 0 0 335 1160 7 11 LFWP2406 -1171 -14737 -8684 1197 0 0 -1171 -13999 -8369 -320 0 0 333 1160 7 11 LFWP2522 -1173 -16097 -9694 1117 0 0 -1173 -15629 -9779 -367 0 0 339 1160 7 11LLFWP2709 -1175 -17737 -11044 1063 0 0 -1175 -17419 -11369 -422 0 0 355 1160 7 11 LFWP2896 -1177 -19487 -12484 1041 0 0 -1177 -19119 -12859 -470 0 0 373 1160 8 1lOLFWP31029 -1178 -20737 -13484 1040 0 0 -1178 -20299 -13869 -502 0 0 386 1160 File No.: 0900530.306 Page C-26 of C-40 Revision: 0 F0306-OIRO

StructuralIntegrity Associates, Inc.

Fatigue Analysis using VESLFAT Fatigue Module Version 1.42 - 12/29/2006 (&VeslFatFatlp42)

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StructuralIntegrity Associates, Inc.

Fatigue Analysis using VESLFAT Fatigue Module Version 1.42.- 12/29/2006 (&VeslFatFatlp42)

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Structural Integrity Associates, Inc.

Fatigue Analysis using VESLFAT Fatigue Module Version 1.42 - 12/29/2006 (&VeslFatFatlp42)

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.11 LFWP736751 -1061 -31364 -21934 1424 0 0 -1061 -29977 -21865 -756 0 0 532 1035 11 LFWP736951 -1061 -31394 -21964 1416 0 0 -1061 -30037 -21925 -758 0 0 532 1035 I1 LFWP737151 -1061 -31404 -23974 1412 0 0 -1061 -30057 -21945 1759 0 0 532 1035 11 LFWP737565 -1061 -31404 -21974 1408 0 0 -1061 -30057 -21955 -759 0 0 532 1035 31 LFWP738096 -1061 -31404 -21974 1407 0 0 -1061 -30057 -21955 -760 0 0 532 1035 11 LFWP738820 -1061 -31404 -21984 1406 0 0 -1061 -30057 -21955 -760 0 0 532 1035 11 LFWP740244 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 11-LFWP742244 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 11 LFWP744244 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 11 LFWP845798 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 11 LFWP846351 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 File No.: 0900530.306 Page C-29 of C-40 Revision: 0 F0306-01 R0

StructuralIntegrity Associates, Inc.

Fatigue Analysis using VESLFAT Fatigue Module Version 1.42 - 12/29/2006 (&VeslFatFatlp42)

Page 8 06-23-2009 23:04:20 13 11 LFWP846387 -1061 -31394 -21984 1406. 0 0 -1061 -30047 -21955 -760 0 0 532 1035 13 11_LFWP846423 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 13 11 _LFWP846531 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 13 11LFWP846855 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 13 11 LFWP847575 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 13 11-LFWP848295 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 13 11 LFWP849015 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 13 11 LFWP849735 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 13 11 LFW2849951 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 13 11 LFWP849961 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 14 13 ROPl0 -1061 -31414 -21984 1405 0 0 -1061 -30067 -21965 -760 0 0 532 1035 14 13 ROPIO -1069 -31409 -21960 1406 0 0 -1069 -30060 -21940 -759 0 0 532 1043 14 13 ROPIO -1076 -31403 -21935 1406 0 0 -1076 -30052 -21914 -759 0 0 532 1050 14 13-ROPIO -1094 -31389 -21877 1407 0 0 -1094 -30036 -21854 -757 0 0 532 1068 14 13-ROPIO -1131 -31360 -21754 1409 0 0 -1131 -30001 -21726 -754 0 0 532 1105 15 13 ROP21 -1206 -31301 -21508 1414 0 0 -1206 -29930 -21470 -748 0 0 532 1180 15 13 ROP21 -1281 -31243 -21262 1418 0 0 -1281 -29860 -21214 -741 0 0 532 1255 15 13 ROP22 -1356 -31185 -21016 1423 0 0 -1356 -29789 -20958 -735 0 0 532 1330 15 13 ROP22 -1414 -31139 -20823 1426 0 0 -1414 -29734 -20757 -730 0 0 532 1389 15 13-ROP22 -1435 -31122 -20754 1428 0 0 -1435 -29714 -20685 -728 0 0 532 1410 15 13-ROP23 -1426 -31129 -20783 1427 0 0 -1426 -29722 -20715 -729 0 0 532 1401 15 13 ROP23 -1417 -31126 -20812 1426 0 0 -1417 -29721 -20746 -730 0 0 532 1392 15 13 ROP25 -1391 -31147 -20900 1425 0 0 -1391 -29746 -- -20837 -732 0 0 532 1366 15 13 ROP28 -1346 -31182 -21046 1423 0 0 -1346 -29788 -20989 -736 0 0 532 1321 15 13 ROP214 -1258 -31251 -21338 1418 0 0 -1258 -29871 -21293 -743 0 0 532 1232 15 13-ROP220 -1169 -31320 -21630 1413 0 0 -1169 -29955 -21597 -751 0 0 532 1143 15 13 ROP226 -1080 -31390 . -21922 1,407 0 0 -1080 -30039 -21891 -758 0 0 532 1054 15 13 ROP232 -992 -31459 -22214 1402 0 0 -992 -30122 -22195 -766 0 0 532 965 15 13 ROP240 -993 -31498 -22239 1401 0 0 -993 -30181 -22250 -767 0 0 532 966 15 13-ROP249 -995 -31547 -22275 1400 0 0 -995 -30240 -22305 -769 0 0 532 968 15 13 ROP257 -996 -31596 -22310 1399 0 0 -996 -30308 -22360 -771 0 0 533 969 15 13 ROP266 -998 -31644 -22345 1398 0 0 -998 -30367 -22405 -772 0 0 533 971 15 13-ROP282 -1000 -31752 -22426 1397 0 0 -1000 -30495 -22506 -776 0 0 534 973 15 13 ROP299 -1003 -31860 -22497 1397 0 0 -1003 -30602 -22596 -779 0 0 534 976 15 13 ROP2117 -1007 -31968 -22577 1397 0 0 -1007 -30719 -22686 -782 0 0 535 979 15 13 ROP2139 -1010 -32095 -22665 1397 0 0 -1010 -30846 -22784 -785 0 0 536 983 15 13 ROP2164 -1015 -32232 -22772 1398 0 0 -1015 -30992 -22899 -789 0 0 538 987 15 13 ROP2193 -1020 -32388 -22886 1399 0 0 -1020 -31147 -23023 -793 0 0 539 992 15 13 ROP2225 -1025 -32564 -23018 1402 0 0 -1025 -31312 -23165 -797 0 0 541 997 15 13 ROP2280 -1035 -32847 -23238 1406 0 0 -1035 -31594 -23383 -805 0 0 544 1006 15 13 ROP2343 -1045 -33169 -23484 1412 0 0 -1045 -31904 -23638 -813 0 0 548 1017 15 13 ROP2413 -1057 -33499 -23736 1420 0 0 -1057 -32193 -23858 -820 0 0 552 1028 15 13 ROP2452 -1064 -33604 -23784 1424 0 -1064 -32287 -23915 -822 0 0 554 1035 15 13 ROP2652 -1063 -33364 -23604 1448 0 0 -1063 -31957 -23615 -813 0 0 555 1035 15 13 ROP2852 -1063 -33284 -23544 1459 0 0 -1063 -31857 -23535 -810 0 0 .556 1035 15 13 ROP21052 -1063 -33264 -23524 1465 0 0 -1063 -31837 -23505 -809 0 0 556 1035 15 13 ROP21252 -1063 -33264 -23524 1468 0 0 -1063 -31837 -23495 -808 0 0 556 1035 15 13 ROP21739 -1063 -33274 -23514 1471 0 0 -1063 -31837 -23485 -808 0 0 556 1035 15 13 ROP22404 -1063 -33274 -23514 1472 0 0 -1063 -31837 -23485 -808 0 0 556 1035 15 13 ROP23237 -1063 -33274 -23514 1473 0 0 -1063 -31837 -23485 -808 0 0 556 1035 15 13 ROP24138 -1063 -33274 -23514 1473 0 0 -1063 -31837 -23485 -808 0 0 556 1035 15 13 ROP25053 -1063 -33274 -23514 1473 S 0 0 -1063 -31837 -23485 -808 0 0 556 1035 File No.: 0900530.306 Page C-30 of C-40 Revision: 0 F0306-OIRO

Structural lntegrity Associates, Inc.

Fatigue Analysis using VESLFAT Fatigue Module Version 1.42 - 12/29/2006 (&VeslFatFatlp42)

Page 9 06-23-2009 23:04:20 15 13 ROP25971 -1063 -33274 -23514 1473 0 0 -1063 -31837 -23485 -808 0 0 556 1035 15 139ROP27430 -1063 -33274 -23514 1473 0 0 -1063 -31837 -23485 -806 0 0 556 1035 15 13 ROP29941 -1063 -33274 -23514 1473 0 0 -1063 -31837 -23485 -608 0 0 556 1035 15 13 ROP210452 -1063 -33274 -23514 1473 0 0 -1063 -31837 -23485 -808 0 0 556 1035 15 13 ROP210452 -1063 -33274 -23514 1473 0 0 -1063 -31837 -23485 -808 0 0 556 1035 15 130RP210452 -1063 -33274 -23514 1473 0 0 -1063 -31837 -23475 -808 0 0 556 1035 15 13 ROP210452 -1063 -33274 -23514 1473 0 0 -1063 -31827 -23475 -808 0 0 556 1035 15 13 ROP210452 -1063 -33274 -23504 1473 0 0 -1063 -31807 -23445 -807 0 0 556 1035 15 13 ROP210452 -1063 -33254 -23494 1473 0 0 -1063 -31727 -23365 -804 0 0 555 1035 15 13 ROP210453 -1063 -33224 -23464 1473 0 0 -1063 -31627 -23275 -801 0 0 555 1035 15 13 ROP210453 -1063 -33194 -23434 1474 0 0 -1063 -31517 -23165 -798 0 0 555 1035 15 13 ROP210453 -1062 -33354 -23404 1474 0 0 -1062 -31427 -23075 -795 0 0 555 1035 15 13 ROP210453 -1062 -33144 -23394 1474 0 0 -1062 -31387 -23035 -794 0 0 554 1035 15 13 ROP210653 -1063 -32804 -23154 1467 0 0 -1063 -31297 -23035 -793 0 0 549 1035 15 13 ROP210853 -1063 -32844 -23174 1457 0 0 -1063 -31407 -23125 -796 0 0 548 1035 15 13 RO9211053 -1063 -32864 -23184 1453 0 0 -1063 -31437 -23155 -797 0 0 548 1035 15 13 ROP211253 -1063 -32864 -23194 1451 0 0 -1063 -31447 -23155 -797 0 0 548 1035 15 13 ROP211667 -1063 -32664 -23194 1449 0 0 -1063 -31447 -23165 -798 0 0 548 1035 15 13 ROP212197 -1063 -32864 -23194 1448 0 0 -1063 -31447 -23165 -798 0 0 548 1035 15 13 ROP212918 -1063 -32864 -23194 1448 0 0 -1063 -31447 -23165 -798 0 0 548 1035 15 13 ROP214339 -1063 -32864 -23194 1448 0 0 -1063 -31447 -23165 -798 0 0 548 1035 15 13 ROP216339 -1063 -32864 -23194 1448 0 0 -1063 -31447 -23165 -798 0 0 548 1035 15 13 ROP218339 -1063 -32864 -23194 1448 0 0 -1063 -31447 -23165 -798 0 0 548 1035 35 13-ROP219896 -1063 -32864 -23194 1448 0 0 -1063 -31447 -23165 -798 0 0 548 1035 15 13 ROP220453 -1063 -32864 -23194 1448 0 0 -1063 -31447 -23165 -798 0 0 548 1035 15 13 ROP220453 -1063 -32864 -23194 1448 0 0 -1063 -31437 -23165 -798 0 0 548 1035 15 13 ROP220453 -1063 -32864 -23194 1448 0 0 -1063 -31437 -23165 -797 0 0 548 1035 15 13 ROP220453 -1063 -32864 -23194 1448 0, 0 -1063 -31417 -23145 -797 0 0 548 1035 15 13 ROP220453 -1063 -32854 -23184 1448 - 0 0 -1063 -31357 -23085 -795 0 0 548 1035 15 13-ROP220453 -1062 -32814 -23144 1449 0 0 -1062 -31197 -22925 -790 0 0 547 1035 15 13 ROP220454 -1062 -32754 -23094 1449 0 0 -1062 -30987 -22715 -783 0 0 547 1035 15 13 ROP220454 -1061 -32674 -23024 1451 0 0 -1061 -30747 -22485 -776 0 0 546 1035 15 13 ROP220454 -1061 -32604 -22964 1452 0 0 -1061 -30547 -22285 -769 0 0 545 1035 15 13 ROP220454 -1061 -32564 -22934 1452 0 0 -1061 -30467 -22205 -767 0 0 545 1035 15 13 ROP220654 -1061 -31274 -21894 1443 0 0 -1061 -29757 -21685 -750 0 0 534 1035 15 13 R0P220854 -1061 -31364 -21934 1424 0 0 -1061 -29977 -21865 -756 0 0 532 1035 15 13 ROP221054 -1061 -31394 -21964 1416 0 0 -1061 -30037 -21925 -758 0 0 532 1035 15 13 ROP221254 -1061 -31404 -21974 1412 0 0 -1061 -30057 -21945 -759 0 0 532 1035 15 13 ROP221668 -1061 -31404 -21974 1408 0 0 -1061 -30057 -21955 -759 0 0 532 1035 15 13 ROP222199 -1061 -31404 -21974 1407 0 0 -1061 -30057 -21955 -760 0 0 532 1035 15 13 ROP222923 -1061 -31404 -21984 1406 0 0 -1061 -30057 -21955 -760 0 0 532 1035 15 13 ROP224347 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 15 13 ROP226347 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 16 13 ROP328347 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 16 13 ROP329901 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 16 13 ROP330454 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 16 13 ROP330490 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 16 13 ROP330526 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 16 13 ROP330634 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 16 13 ROP330958 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 16 13 ROP331678 -1061 -31394 -21984 1406 0 0 -1061 -30047 721955 -760 0 0 532 1035 16 13 ROP332398 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 File No.: 0900530.306 Page C-31 of C-40 Revision: 0 F0306-01RO

Structural Integrity Associates, Inc.

Fatigue Analysis using VESLFAT Fatigue Module Version 1.42 - 12/29/2006 (&VeslFatFatlp42)

Page 10 06-23-2009 23:04:20 16 13 ROP333118 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 16 13 ROP333838 -1061 -31394 -21984 1406 0 0 -1063 -30047 -21955 -760 0 0 532 1035 16 13 ROP334054 -1061 -31394 -21984 1406 0 0 -1063 -30047 -21955 -760 0 0 532 1035 16 13 ROP334064 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 17 14 SRVB10 -1061 -31414 -21984 3405 0 0 -1061 -30077 -21975 -760 0 0 532 1035 17 14 SRVB11 -1046 -31326 -21944 1406 0 0 -1046 -29831 -21777 -753 0 0 531 1020 17 14 -SRVB12 -1030 -31168 -21854 1408 0 0 -1030 -29515 -21509 -745 0 0 530 1005 17 14 SRVB14 -1015 -30960 -21714 1411 0 0 -1015 -29149 -21211 -735 0 0 529 989 17 14 SRV915 -999 -30712 -21554 1415 0 0 -999 -28764 -20893 -724 0 0 528 974 17 14 SRVB17 -967 -30166 -21194 1427 0 0 -967 -27953 -20228 -702 0 0 525 943 17 14--SRVB110 -927 -29396 -20681 1443 0 0 -927 -26899 -19380 -673 0 - 0 521 905 18 14 -SRVB214 -875 -28336 -19989 1468 0 0 -875 -25507 -18285 -637 0 0. 516 854 18 14 SRVB220 -805 -26918 -19092 1500 0 0 -805 -23731 -16917 -590 0 0 508 786 18 14 SRVB227 -713 -25078 -17927 1536 0 0 -713 -21516 -15264 -534 0 0 498 696 18 14-SRVB236 -591 -22771 -16478 1570 0 0 -591 -18848 -13290 -466 0 0 483 577 18 14 SRVB248 -439 -20148 -14859 1589 0 0 -439 -15938 -11191 -395 - 0 0 463 427 18 14 SRVB260 -284 -17806 -13548 1605 0 0 -284 -13381 -9491 -337 0 0 443 275 19 14-SRVB3287 -290 -19216 -14649 1287 0 0 -290 -17672 -13683 -468 0 0 393 275 19 14 SRVB3514 -291 -19307 -14611 1144 0 0 -291 -18482 -14414 -495 0 0 377 274 19 14-SRVB3740 -291 -18887 -14343 1079 0 0 -291 -18273 -14346 -494 0 0 369 274 19 14-SRVB3967 -290 -18347 . -13984 1037 0 0 -290 -17823 -14058 -485 0 0 362 273 19 14 -SRVB31421 -288 -17248 -13218 984 0 0 -288 -16824 -13341 -462 0 0 349 272 19 14 SRVB31874 -287 -16479 -12641 934 0 0 -287 "-16075 -12755 -441 0 0 336 271 19 14 SRVB32328 -285 -15700 -12034 889 0 0 -285 -15316 -12138 -420 0 0 323 270 19 14-SRVB32782 -283 -14931 -11427 846 0 0 -283 -14547 -11521 -399 0 0 311 269 19 14 SRVB33235 -281 -14151 -10811 804 0 0 -281 -13788 -10895 -378 0 0 298 268 19 14-SRVB33689 -280 -13282 -10154 771 0 0 -280 -12959 -10238 -357 0 0 286 267 19 14-SRVB34142 -278 -12423 -9497 737 0 0 -278 -12140 -9582 -335 0 0 273 266 19 14 SRVB34823 -275 -11144 -8519 685 0 0 -275 -10921 -8606 -303 0 0 255 265 19 14 SRVB35503 -273 -9733 -7415 633 0 0 -273 -9566 -7497 -266 0 0 236 263 19 14 SRVB36184 -270 -8332 -6305 580 0 0 -270 -8217 -6381 -229 0 0 217 262 19 14 SRVB36864 -267 -7005 -5246 524 0 0 -267 -6931 -5315 -193 0 0 199 260 19 14-SRVB37998 -263 -5250 -3796 414 0 0 -263 -5169 -3818 -141 0 0 169 258 19 14 SRVB39132 -258 -3450 -2314 311 0 0 -258 -3372 -2294 -88 0 0 139 255 19 14-SRVB310266 -254 -1797 -971 221 0 0 -254 -1739 -927 -40 0 0 113 253 19 14 SRVB311400 -251 -1401 -666 158 0 0 -251 -1413 -697 -30 0 0 102 250 19 14 SRVB311436 -251 -1419 -682 157 0 0 -251 -1430 -713 -30 0 0 102 250 19 14 SRVB311472 -251 -1435 -696 156 0 0 -251 -1444 -727 :31 0 0 102 250 19 14 SRVB311580 -251 -1469 -725 150 0 0 -251 -1476 -756 -32 0 0 102 250 19 14 SRVB311904 -251 -1503 -753 130 0 0 -251 -1507 -783 -35 0 0 102 250 20 14-SRV9412624 -251 -1448 -711 95 0 0 -251 -1449 -739 -36 0 0 100 250 20 14 SRVB413344 -251 -1330 -619 73 0 0 -251 -1329 -644 -34 0 0 98 250 20 14 SRVB414064 -251 -1202 -520 60 0 0 -251 -1200 -541 -30 0 0 96 250 20 14 SRVB414784 -27 -1262 -1165 39 0 0 -27 -1294 -1213 -46 0 0 94 25 20 14 SRVB415000 -27 -1230 -1138 37 0 0 -27 -1261 -1185 -45 0 0 93 25 20 14 SRVB415010 -25 -119 -55 5 0 0 -25 -119 -57 -3 0 0 73 25 21 17IImpSTlO -1061 -31414 -21984 1405 0 0 -1061 -30067 -21965 -760 0 0 532 1035 21 17ImpSTlO -1061 -31404 -21984 1405 0 0 -1061 -30037 -21935 -759 0 0 532 1035 21 17IImpSTlO -1061 -31404 -21974 1405 0 0 -1061 -29967 -21865 -756 0 0 532 1035 21 17 ImpSTlO -1061 -31354 -21934 1405 0 0 -1061 -29677 -21575 -747 0 0 531 1035 21 17 ImpSTlO -1059 -31254 -21844 1407 0 0 -1059 -29127 -21035 -730 0 0 529 1035 21 17OImpSTlO -1055 -30784 -21424 1413 0 0 -1055 -27057 -18985 -663 0 0 524 1035 File No.: 0900530.306 Page C-32 of C-40 Revision: 0 F0306-OIRO

StructuralIntegrity Associates, Inc.

Fatigue Analysis using VESLFAT Fatigue Module Version 1.42 - 12/29/2006 (&VeslFatFatlp42)

Page 11 06-23-2009 23:04:20 22 17_ImpST21 -1051 -30044 -20764 1423 0 0 -1051 -24507 -16495 - -583 0 0 516 1035 22 17_ImpST21 -1046 -29144 -19964 1436 0 0 -1046 -21877 -13925 -500 0 0 509 1035 22 17_1mpST26 -1043 -29134 -19074 1451 0 0 -1043 -19327 -11455 -420 0 0 502 1035 22 17ImpST2l -1041 -27824 -18814 1456 0 0 -1041 -18627 -10775 -398 0 0 500 1035' 22 17 ImpST22 -1037 -25504 -16824 1494 0 0 -1031 -15077 -7425 -291 0 0 489 1035 22 17_ImpST22 -1035 -23514 -15134 0530 0 0 -1035 -12607 -5138 -219 0 0 481 1035 22 17IImpST24 -1031 -19514 -11894 1621 0 0 -1031 -8570 -1593 -107 0 0 467 1035 22 171ImpST26 -1029 -15344 -8734 1745 0 0 -1029 -4980 1281 -15 0 0 451 1035 22 17ImpST211 -1027 -11074 -5836 1894 0 0 -1027 -1907 3302 54 0 0 431 1035 22 17_ImpST217 -1028 -9294 -4852 1951 0 0 -1028 -1128 3438 63 0 0 418 1035 22 17_ImpST222 -1028 -8550 -4572 1955 0 0 -1028 -1124 3052 52 0 0 407 1035 22 17 ImpST226 -1029 -8270 -4492 1935 0 0 -1029 -1330 2676 40 0 0 400 1035 22 171ImpST227 -1025 -8204 -4475 1926 0 0 -1025 -1411 2552 35 0 0 398 1035 22 17ImpST227 -1025 -8205 -4477 1925 0 0 -1025 -1431 2533 34 0 0 398 1035 22 17_ImpST227 -1025 -8209 -4480 1925 0 0 -1025 -1467 2496 33 0 0 398 1035 22 170ImpST227 -1030 -8239 -4510 1925 0 0 -1030 -1688 2274 27 0 0 398 1035 22 171ImpST227 -1031 -8346 -4609 1923 0 0 -1031 -2278 1690 8 0 0 400 1035 22 17ImpST227 -1035 -8742 -4968 1916 0 0 -1035 -4061 -69 -49 0 0 404 1035 23 17ImpST328 -1039 -9404 -5565 1906 0 0 -1039 -6594 -2560 -129 0 0 411 1035 23 17_ImpST328 -1045 -10364 -6421 1892 0 0 -1045 -9847 -5751 -232 0 0 420 1035 23 17_ImpST328 -1052 -11644 -7554 1872 0 0 -1052 -13807 -9615 -356 0 0 431 1035 23 17ImpST364 <-1065 -30494 -21424 1271 0 0 -1065 -31797 -24005 -826 0 0 502 1035 23 17ImpST3100 -1064 -32044 -22244 1257 0 -1064 -32017 -23635 -816 0 0 517 1035 23 17_ImpST3136 -1063 -32064 -22284 1308 0 -1063 -31447 -23075 -797 0 0 523 1035 23 17ImpST3172 -1063 -31914 -22224 1342 0 -1063 -30997 -22695 -784 0 0 526 1035 23 171ImpST3247 -1062 -31664 -22114 1372 0 0 -1062 -30477 -22285 -771 0 0 530 1035 23 17_ImpST3351 -1062 -31504 -22044 1386 0 -1062 -30207 -22085 -764 0 0 531 1035 23 17 ImpST3520 -1061 -31414 -22004 1396 0 0 -1061 -30077 -21995 -761 0 0 532 1035 23 17_ImpST31004 -1061 -31394 -21984 1403 0 0 -1061 -30047 -21965 -760 0 0 532 1035 23 17_ImpST31724 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 23 171ImpST32444 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 23 17ImpST33164 -1061 -31394 -21984 1406 0 0 -1061 -30047 -21955 -760 0 0 532 1035 23 17ImpST33628 -1061 -31394 -21984 1406 0 -1061 -30047 -21955 -760 0 0 532 1035 23 17 ImpST33638 -1061 -31394 -21984 1406 0 -1061 -30047 -21955 -760 0 0 532 1035 24 21 ShDwlO -1063 -33294 -23514 1471 0 0 -1063 -31867 -23495 -809 0 0 556 1035 24 21--ShDw123 -1042 -33300 -23582 1471 0 0 -1042 -31866 -23556 -810 0 0 556 1014 24 21 ShDw1246 -1022 -33307 -23650 1471 0 0 -1022 -31886 -23627 -812 0 0 556 994 24 21 ShDw1544 -972 -33346 -23814 1468 0 0 -972 -31923 -23798 -816 0 0 556 944 25 21 ShDw2960 -902 -33400 -24044 1463 0 0 -902 -31988 -24037 -822 0 0 556 874 25 21 ShDw21865 -751 -33518 -24543 1454 0 0 -751 -32131 -24556 -834 0 0 556 722 25 21-ShDw22782 -597 -33638 -25049 1445 0 0 -597 -32276 -25083 -847 0 0 556 567 25 21--hDw23700 -443 -33759 -25555 1436 0 0 -443 -32422 -25610 -860 0 0 556 413 25 21 ShDw24931 -237 -33920 -26234 1423 0 0 -237 -32616 -26317 -878 0 0 556 206 25 21-ShDw26156 -32 -34080 -26910 1411 0 0 -32 -32810 -27020 -895 0 0 556 0 25 21 ShDw26168 -31 -33730 -26640 1419 0 0 -31 -32310 -26570 -880 0 0 554 0 25 21 ShDw26180 -30 -33340 -26340 1429 0 0 -30 -31800 -26130 -866 0 0 551 0 25 21 ShDw26192 -30 -32930 -26040 1438 0 0 -30 -31260 -25670 -851 0 0 548 0 25 21 ShDw26204 -29 -32470 -25700 1445 0 0 -29 -30710 -25210 -836 0 0 545 0 25 21 ShDw26228 -28 -31520 -24930 1447 0 0 -28 -29670 -24290 -806 0 0 537 0 25 21 ShDw26252 -27 -30580 -24170 1447 0 0 -27 -28670 -23430 -779 0 0 530 0 25 21 ShDw26277 -26 -29660 -23420 1444 0 0 -26 -27730 -22610 -752 0 0 522 0 25 21 ShDw26304 -25 -28640 -22590 1436 0 0 -25 -26710 -21710 -724 0 0 512 0 File No.: 0900530.306 Page C-33 of C-40 Revision: 0 F0306-01 R0

StructuralIntegrity Associates, Inc.

Fatigue Analysis using VESLFAT Fatigue Module Version 1.42 - 12/29/2006 (&VeslFatFatlp42)

Page 12 06-23-2009 23:04:20 25 21_ShDw26337 -24 -27520 -21650 1425 0 0 -24 -25590 -20730 -692 0 0 501 0 26 21_ShDw36373 -22 -26350 -20680 1406 0 0 -22 -24480 -19740 -660 0 0 488 0 26 21 ShDw36414 -21 -25160 -19800 1400 0 0 -21 -23360 -18860 -633 0 0 473 0 26 21 ShDw36485 -20 -23150 -18340 1393 0 0 -20 -21480 -17400 -586 0 0 447 0 26 21-ShDw36567 -18 -21000 -16750 1361 0 0 -18 -19410 -15790 -530 0 0 417 0 26 21 ShDw36661 -16 -18530 -14710 1272 0 0 -16 -16950 -13650 -460 0 0 382 0 26 21 ShDw36756 -13 -15380 -12280 1215 0 0 -13 -14030 -11280 -386 0 0 348 0 26 21 ShDw36922- -15 -15620 -12510 1081 0 0 -15 -14980 -12280 -417 0 0 332 0 26 21 ShDw37087 -15 -15690 -12550 989 0 0 -15 -15230 -12540 -426 0 0 324 0 7

26 21 ShDw3 253 -15 -15530 -12450 929 0 -15 -15130 -12520 -425 0 0 319 0 26 21 ShDw37418 -15 -15280 -12300 886 0 0 -15 -14920 -12390 -421 0 0 314 0 26 21 ShDw37750 -15 -14720 -11910 827 0 0 -15 -14390 -12020 -408 0 0 304 0 26 21 ShDw38081 -14 -14120 -'11480 787 0 0 -14 -13810 -11590 -394 0 0 295 0 26 21-ShDw38412 -14 -13480 -11010 757 0 0 -14 -13200 -11130 -378 0 0 286 0 26 21 ShDw38743 -13 -12840 -10530 730 0 0 -13 -12600 -10650 -363 0 0 276 0 26 21 ShDw39074 -13 -12220 -10050 704 0 0 -13 -12000 -10170 -347 0 0 267 0 26 21 ShDw39406 -12 -11590 -9572 678 0 0 -12 -11400 -9694 -331 0 0 258 0 26 21 ShDw39737 -11 -10960 -9083 652 0 0 -11 -10790 -9201 -315 0 0 249 0 26 21 ShDw310234 -10 -9893 -8239 614 0 0 -10 -9770 -8356 -287 0 0 235 0 26 21 ShDw310730 -9 -8860 -7417 575 0 0 -9 -8775 -7531 -260 0 0 222 0 26 216ShDw31l227 -9 -7861 -6617 534 0 0 -9 -7809 -6725 -233 0 0 208 0 26 21 ShDw3l1724 -8 -6962 -5890 490 0 0 -8 -6929 -5988 -208 0 0 194 .0 26 21 ShDw312552 -6 -5663 -4806 406 0 0 -6 -5623 -4868 -169 0 0 172 0 26 21 ShDw313380 -5 -4355 -3711 324 0 0 -5 -4306 -3736 -130 0 0 149 0 26 21 ShDw314208 -3 -2911 -2519 247 0 0 -3 -2877 -2516 -88 0 0 -127 0 27 21 ShDw415036 -2 -1575 -1404 168 0 00 -2 -1541 -1371 -48 0 0 105 0 27 21-ShDw415072 -2 -1559 -1388 164 0 00 -2 -1537 -1368 -48 0 0 104 0

.27 21-ShDw4l5108 -2 -1552 -1379 160 0 0 -2 -1539 -1370 -48 0 0 103 0 27 21-ShDw415216 -2 -1549 -1369 153 0 0 -2 -1553 -1380 -48 0 - 0 102 0 27 21 ShDw415467 -2 -1559 -1369 141 0 0 -2 -1579 -1402 -49 0 0 101 0 27 21 ShDw416132 -2 -1581 -1380 127 0 0 -2 -1614 -1430 -50 0 0 100 0 27 21-ShDw416852 -2 -1590 -1384 122 0 0 -2 -1626 -1439 -50 0 0 100 0 27 21-ShDw417572 -2 -1593 -1385 120 0 0 -2 -1629 -1441 -51 0 0 100 0 27 21 ShDw418292 -2 -1595 -1384 119 0 0 -2 -1631 -1441 -51 0 0 100 0 27 21 ShDw418636 -2 -1595 -1384 119 0 -2 -1631 -1441 -51 0 0 100 0 27 21 ShDw418646 -2 -1596 -1383 119 0 -2 -1632 -1440 -51 0 0 100 0 28 24HydrolO -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 28 24_HydrolO -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 28 24HydrolO -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 28 24HydrolO -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 26 24_HydrolO -2 -1596 -1383 119 0 0 ý2 -1632 -1440 -51 0 0 100 0 28 24_HydrolO -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 28 24_Hydrol0 -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 - 0 100 0 28 24Hydroll -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 28 24 Hydroll -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 29 24_Hydro2l -1562 -378 3752 212 0 0 -1562 -160 3904 81 0 0 100 1565 29 24Hydro2l -1562 -378 3752 212 0 0 -1562 -160 3904 81 0 0 100 1565 29 24_Hydro2l -1562 -378 3752 212 0 0 -1562 -160 3904 81 0 0 100 1565 29 24Hydro2l -1562 -378 3752 212 0 0 -1562 -160 3904 61 0 0 100 1565 29 24 Hydro21 -1562 -378 3752 212 0 0 -1562 -160 3904 81 0 0 100 1565 29 24Hydro2l -1562 -378 3752 212 0 0 -1562 -160 3904 81 0 0 100 1565 29 24 Hydro2l -1562 -378 3752 212 0 0 -1562 -160 3904 81 0 0 100 1565 File No.: 0900530.306 Page C-34 of C-40 Revision: 0 F0306-OIRO

Structural Integrity Associates, Inc.

Fatigue Analysis using VESLFAT Fatigue Module Version 1.42 - 12/29/2006 (&VeslFatFatlp42)

Page 13 06-23-2009 23:04:20 2

29 4_Hydro22 -1562 -378 3752 212 0 0 -1562 -160 3904 81 0 0 100 1565 29 24Hydro22 -1562 -378 3752 212 0 0 -1562 -160 3904 81 0 0 100 1565 30 24Hydro32 -2 -1596 -1383 119 0 0 -2 -1632 -1440 -51 0 0 100 0 Ordered Input E-corrected Stress Intensities are from: pl-i_304L.ORD Stress Input (psi. - Salt w/E-modulus correction):

1. Eventl # Event 2 Sn Ke Salt 25 21 ShDw2 and 29 24Hydro2 35314 1.0000 18983 2 2DHydT2 and 25 21 _ShDw2 34759 1.0000 18643 22 17ImpST2 and 25 21 ShDw2 26548 1.0000 18152 20 14 _SRVB4 and 25 21 ShDw2 34070 1.0000 18149 15 13-ROP2 and 29 24lHydro2 33811 1.0000 18110 3

5 Staup2 and 29 2414ydro2 33635 1.0000 17981 12 11 LFWP7 and 29 241Hydro2 33635 1.0000 17981 24 21 -ShDwI and 29 24 Hydro2 33652 1.0000 17966 23 17ImpST3 and 29 24IHydro2 32232 1.0000 17831 2 201HydT2 and 15 13 ROP2 33256 1.0000 17771

2. 2DHydT2 and 5 3_Staup2 33081 1.0000 17642 2 2DHydT2 and 12 11_LFWP7 33081 1.0000 17642 2 2DHydT2 and 24 21_ShDwl 33097 1.0000 17627 19 14 SRVB3 and 25 21 ShDw2 32993 1.0000 17556 2 2DHydT2 and 23 17iImpST3 31677 1.0000 17494 25 21 ShDw2 and 27 21_ShDw4 32587 1.0000 17349 3 2-lDHydT3 and 25 21_ShDw2 32600 1.0000 17323 3

4 Staupl and 25 21_ShDw2 32557 1.0000 17296 1 2DHydTl and 25 21_ShDw2 32557 1.0000 17296 25 21 ShDw2 and 28 24Hydrol 32557 1.0000 17296 25 21_ShDw2 and 30 241Hydro3 32557 1.0000 17296 15 13 ROP2 and 22 17ImpST2 25041 1.0000 17279 15 135ROP2 and 20 14 _SRVB4 32570 1.0000 A 17277 5 3Staup2 and 22 17_ImpST2 24860 1.0000 17150 12 I LFWP7 and 22 17ImpST2 24860 1.0000 17150 3

5 Staup2 and 20 14_SRVB4 32395 1.0000 17148 12 1Y LFWP7 and 20 14 SRVB4 32395 1.0000 17148 22 17ImpST2 and 24 21_ShDwl 24871 1.0000 17135 20 14 SRV34 and 24 21_ShDwl 32412 1.0000 17133 22 17ImpST2 and 23 17_ImpST3 23500 1.0000 17006 20 14 _SRV4 and 23 17ImpST3 30987 1.0000 17004 17 14 SRVBI and 29 24 Hydro2 31627 1.0000 16813 6 11 -LFWP1 and 29 24lHydro2 31627 1.0000 16807 14 135ROP1 and 29 24lHydro2 31627 1.0000 16807 21 17iImpSTI and 29 24_Hydro2 31627 1.0000 16807 13 11 LFWP8 and 29 24 Hydro2 31607 1.0000 16796 16 13 ROP3 and 29 24_Hydro2 31607 1.0000 16796 5 3_Staup2 and 25 21_ShDw2 31561 1.0000 16707 15 13 ROP2 and 19 145SRVB3 31492 1.0000 16684 25 21 ShDw2 and 26 21 ShDw3 31227 1.0000 16605 File No.: 0900530.306 Page C-35 of C-40 Revision: 0 F0306-01 R0

StructuralIntegrity Associates, Inc.

Fatigue Analysis using VESLFAT Fatigue Module Version 1.42 - 12129/2006 (&VesIFatFatlp42I Page 14 06-23-2009 23:04:20 Stress Input (psi. - Salt w/E-modulus correction):

8 Eventl # Event 2 Sn Ke Salt 5 3Staup2 and 19 14 _SRVB3 3 1317 1.0000 16555 12 11_LFWP7 and 19 14 _SRVB3 3 1317 i.0ooo 16555 19 14 SRVB3 and 24 21_ShDwl 3 1334 1.0000 16540 15 13-ROP2 and 27 21 ShDw4 3 1085 1.0000 16477 2 2DHydT2 and 17 14 _SRVBI 3 1073 1. 0000 16475 2 2DHydT2 and 21 17 ImpSTl 3 1073 1.0000 16469 2 2DHydT2 and 6 11 LFWPI 3 1073 1.0000 16469 2 2DHydT2 and 14 13 POI 3 1073 1.0000 16469 2 2DHydT2 and 16 13 ROP3 3 1053 1.0000 16458 2 2DHydT2 and 13 11 LFWP8 3 1053 1.0000 16458 3 2_DHydT3 and 15 13 ROP2 31100 1.0000 16451 4 3Staupl and 15 13 ROP2 31056 1.0000 16424 15 13 ROP2 and 28 24Hydrol 31056 1.0000 16424 15 13ROP2 and 30 24Hydro3 31056 1.0000 16424 1 2DHydTl and 15 13 ROP2 31056 1.0000 16424 19 14 SRVB3 and 23 17IImpST3 2 9911 1.0000 16416 5 3Staup2 and 27 21 ShDw4 30910 1.0000 16347 12 11 LFWP7 and 27 21 ShDw4 30910 1.0000 16347 24 21 ShDwl and 27 21 ShDw4 30927 1.0000 16332 3 2DHydT3 and 12 11 LFWP7 30924 1.0000 16322 3 2DHydT3 and 5 3_Staup2 30924 1.0000 16322 3 2DHydT3 and 24 21 ShDwl 30942 1.0000 16307 4 3Staupl and 5 3_Staup2 30881 1.0000 16295 5 3Staup2 and 28 24lHydrol 3 0881 1.0000 16295 5 3Staup2 and 30 24_Hydro3 3 0881 1.0000 16295 12 11 LFWP7 and 28 24Hydrol 3 0881 1.0000 16295 12 11-LFWP7 and 30 24Hydro3 3 0881 1.0000 16295 1 2DHydTl and 12 ii1LFWP7 3 0881 1.0000 16295 4 3Staupl and 12 11_LFWP7 3 0881 1.0000 16295 I 2DHydTl and 5 3_Staup2 '3 0881 1.0000 16295 4 3_Staupl and 24 21 ShDwl 3 0898 1.0000 16280 1 2DHydTI and 24 21_ShDwi 3 0898 1.0000 16280 24 21 ShDwl and 28 24 Hydrol 3 0898 1.0000 16280 24 21-ShDwl and 30 24 Hydro3 3 0898 1.0000 16280 23 17 ImpST3 and 27 21 ShDw4 2 9504 1.0000 16210 3 2DHydT3 and 23 17IImpST3 2 9518 1.0000 16184 4 3Staupl and 23 17_ImpST3 2 9474 1.0000 16157 1 2DHydTl and 23 17ImpST3 2 9474 1.0000 16157 23 17 ImpST3 and 28 24IHydrol 2 9-474 1.0000 16157 23 17ImpST3 and 30 24Hydro3 2 9474 1.0000 16157 17 14 SRVB1 and 22 17ImpST2 2 2858 1.0000 15985 17 14 SRVBl and 20 14 _SRVB4 3 0388 1.0000 15983 6 11-LFWPI and 22 17_2mpST2 22858 1.0000 15980 14 13 ROPI and 22 17ImpST2 22858 1.0000 15980 21 17IImpSTl and 22 17ImpST2 22858 1.0000 15980 14 13 ROP1 and 20 14 SRV54 3 0388 1.0000 15978 6 11 LFWPI and 20 14 SRVB4 3 0388 1.0000 15978 20 14 SRVB4 and 21 17OmpSTl 3 0388 1.0000 15978 13 11 LFWP8 and 22 17_ImpST2 2 2837 1.0000 15969 File No.: 0900530.306 Page C-36 of C-40 Revision: 0 F0306-01 RO

StructuralIntegrity Associates, Inc.

Fatigue Analysis using VESLFAT Fatigue Module Version 1.42 - 12/29/2006 (&VeslFatFatlp42)

Page 15 06-23-2009 23:04:20 Stress Input (psi. - Salt w/E- modulus correction):

1. Eventl Event 2 Sn Ke Salt 16 13 ROP3 and 22 17ImpST2 22837 1.0000 15969 13 II-LFWP8 and 20 14_SRVB4 30369 1.0000 15967 16 13-ROP3 and 20 14 SRVB4 30369 1.0000 15967 5 3 Staup2 and 15 13-ROP2 30060 1.0000 15836 8 1i LFWP3 and 29 24_Hydro2 29550 1.0020 15792 15 13 ROP2 and 26 21 ShDw3 29725 1.0000 15734 5 3lStaup2 and 12 11LFWP7 29885 1.0000 15706 5 3Staup2 and 24 21ShDwl 29902 1.0000 15691 10 11 LFWP5 and 29 24Hydro2 29468 1.0000 15660 12 11 LFWP7 and 26 21 ShDw3 29550 1.0000 15604 5 3_Staup2 and 26 21-ShDw3 29550 1.0000 15604 24 21 ShDwl and 26 21_ShDw3 29567 1.0000 15589 5 3_Staup2 and 23 170ImpST3 28478 1.0000 15573 23 17_ImpST3 and 26 21 ShDw3 28145 1.0000 15472 2 2_HydT2 and 8 11 LFWP3 28995 1.0000 15456 17 14 SRVB1 and 19 14-SRVB3 29309 1.0000 15393 14 13-ROPI and 19- 14-SRVB3 29309 1.0000 15387 6 11 LFWPI and 19 14 SRVB3 29309 1.0000 15387 19 14 SRVB3 and 21 17ImpSTI 29309 1.0000 15387 13 T11LFWP8 and 19 14 SRVB3 29290 1.0000 15376 16 13-ROP3 and 19 14-SRVB3 29290 1.0000 15376 2 2DHydT2 and 10 11 LFWP5 28913 1.0000 15324 17 14 SRVBI and 27 21 ShDw4 28903 1.0000 15186 14 13 ROPI and 27 21_ShDw4 28903 1.0000 15181 6 11 LFWPI and 27 21_ShDw4 28903 1.0000 15181 21 17tImpSTl and 27 21 ShDw4 28903 1.0000 15181 13 11 LFWP8 and 27 21 ShDw4 28883 1.0000 15170 16 13_ROP3 and 27 21_ShDw4 28883 1.0000 15170 3 2DHydT3 and 17 14 SRVBI 28917 1.0000 15161 3 2DHydT3 and 6 11_LFWPI 28917 1.0000 15155 3 2DHydT3 and 21 17ImpSTl 28917 1.0000 15155 3 2DHydT3 and 14 13 ROPI 28917 1.0000 15155 3 2DHydT3 and 13 11 LFWPS 28988 1.0000 15144 3 2DHydT3 and 16 13 ROP3 28898 1.0000 15144 1 2DHydTl and 17 14 SRVBI 28874 1.0000 15134 17 14 SRVBI and 28 24Hydrol 28874 1.0000 15134 17 14 SRVB1 and 30 24Hydro3 28874 1.0000 15134 4 3Staupl and 17 14_SRVBI 28874 1.0000 15134 14 13 ROPI and 28 24Hydrol 28874 1.0000 15128 14 13_ROPI and 30 24Hydro3 28874 1.0000 15128 4 3Staupl and 14 13_ROPI 28874 1.0000 15128 6 31 LFWPI and 28 24Hydrol 28874 1.0000 15128 4 3Staupl and 21 17ImpSTl" 28874 1.0000 15128 6 11 LFWP1 and 30 24Hydro3 28874 1.0000 15128 1 2DHydT1 and 14 13_ROPI 28874 1.0000 15128 21 17_ImpSTl and 28 24jydrol 28874 1.0000 15128 21 17 ImpSTI and 30 24Hydro3 28874 1.0000 15128 1 2_DHydTl and 6 11 LFWP1 28874 1.0000 15128 1 2DHydTl and 21 17 ImpSTl 28874 i.0000 15128 File No.: 0900530.306 Page C-37 of C-40 Revision: 0 F0306-OIRO

StructuralIntegrity Associates, Inc.

Fatigue Analysis using VESLFAT Fatigue Module Version 1.42 - 12/29/2006 (&VeslFatFatlp42)

Page 16 06-23-2009 23:04:20 Stress Input (psi. - Salt w/E-modulus correction):

1. Eventi # Event 2 Sn Ke Salt 4 3Staupl and 6 11LFWP1 28874 1.0000 15128 23 17_ImpST3 and 25 21 ShDw2 25702 1.0000 15118 4 3_Staupl and 16 13_ROP3 28854 1.0000 15117 16 13ROP3 and 28 24Hydrol 28854 1.0000 15117 13 11 LFWP8 and 28 24 Hydrol 28854 1.0000 15117 16 13-ROP3 and 30 24Hydro3 28854 1.0000 15117 4 3Staupl and 13 11 LFWP8 28854 1.0000 15117 13 11 LFWP8 and 30 24fHydro3 28854 1.0000 15117 1 2DHydTl and 13 11 LFWP8 28854 1.0000 15117 1 2 DHydTI and 16 13_ROP3 28854 1.0000 15117 8 11 _LFWP3 and 22 17ImpST2 20817 1.0000 14969 8 11 LFWP3 and 20 14 SRVB4 28308 1.0000 14967 10 11-LFWP5 and 22 17 ImpST2 20720 1.0000 14837 10 11 LFWP5 and 20 14 SRVB4 28229 1.0000 14835 5 3Staup2 and 17 14 -SRVBI 27878 1.0000 14548 5 3 Staup2 and 21 170ImpSTl 27878 1.0000 14542 5 3 Staup2 and 14 13 ROPI 27878 1.0000 14542 5 3Staup2 and 6 11_LFWP1 27878 1.0000 14542 5 3Staup2 and 13 11 LFWP8 27858 1.0000 14531 5 3Staup2 and 16 13-ROP3 27858 1.0000 14531 17 14 SRVBI and 26 21-ShDw3 27543 1.0000 14446 21 17_ImpSTl and 26 21 ShDw3 27543 1.0000 14441 6 11 LFWPl and 26 21-ShDw3 27543 1.0000 14441 14 13 ROP1 and 26 21 ShDw3 27543 1.0000 14441 16 13 ROP3 and 26 21 ShDw3 27523 1.0000 14430 13 11-LFWP8 and 26 21 -ShDw3 27523 1.0000 14430 8 11-LFWP3 and 19 14 -SRVB3 27230 1.0000 14380 18 14 SRVB2 and 29 24 Hydro2 28755 1.0000 14345 10 11-LFWP5 and 19 14 SRVB3 27150 1.0000 14247 15 13 ROP2 and 23 17IImpST3 24194 1.0000 14247 8 11 LFWP3 and 27 21 ShDw4 26824 1.0000 14174 26 21 ShDw3 and 29 24_Hydro2 27615 1.0000 14160 3 2DHydT3 and 8 11_LFWP3 26838 1.0000 14149 8 I1 LFWP3 and 28 24EHydrol 26794 1.0000 14122 1 2DHydTl and 8 11_LFWP3 26794 1.0000 14122 8 I1 LFWP3 and 30 24_Hydro3 26794 1.0000 14122 4 3Staupl and 8 11_LFWP3 26794 1.0000 14122 12 I _LFWP7 and 23 17ImspST3 24014 1.0000 14117 23 17 ImpST3 and 24 21_ShDwl 24025 1.0000 14102 10 11 LFWP5 and 27 21 ShDw4 26743 1.0000 14042 3 20DHydT3 and 10 I1_LFWP5 26758 1.0000 14016 2 2DHydT2 and 18 14_SRVB2 28202 1.0000 14008 10 11 _LFWP5 and 28 24 Hydrol 26714 1.0000 13989 10 11 LFWP5 and 30 241Hydro3 26714 1.0000 13989 4 3Staupl and 10 11 LFWP5 26714 1.0000 13989 1 2ODHydTl and 10 11TLFWP5 26714 1.0000 13989 7 I1 LFWP2 and 25 21 ShDw2 23235 1.0000 13914 2 2_DHydT2 and 26 21 ShDw3 27062 1.0000 13826 9 11 LFWP4 and 25 215ShDw2 22831 1.0000 13730 File No.: 0900530.306 Page C-38 of C-40 Revision: 0 F0306-OIR0

C StructuralIntegrity Associates, Inc.

Fatigue Analysis using VESLFAT Fatigue Module Version 1.42 - 12/29/2006 (&VeslFatFatlp42)

Page 17 06-23-2009 23:04:20 Stress Input (psi. - Salt w/E-modulus correction):

.A Eventi # Event 2 Sn Ke Salt 22 17 ImpST2 and 29 .24_Hydro2 30274 1.0000 13695 5 3 Staup2 and 8 11_LFWP3 25799 1.0000 13539 18 14 _SRVB2 and 22 17_1mpST2 19963 1.0000 13520 18 14_SRVB2 and 20 14 _SRVB4 27523 1.0000 13518 11 11 LFWP6 and 29 24 Hydro2 26364 1.0000 13470 9 31 LFWP4 and 29 24_Hydro2 26518 1.0000 13446 8 11 LFWP3 and 26 21 ShDw3 25464 1.0000 13437 5 3_Staup2 and 10 11 LFWP5 25719 1.0000 13406 2 2_DHydT2 and 22 17 ImpST2 29720 1.0000 13359 22 17_ImpST2 and 26 21 ShDw3 18838 1.0000 13341 20 14 SRVB4 and 26 21 ShDw3 26383 1.0000 13338 File No.: 0900530.306 Page C-39 of C-40 Revision: 0 F0306-OIRO

C StructuralIntegrity Associates, Inc.

Fatigue Analysis using VESLFAT Fatigue Module Version 1.42 - 12/29/2006 (&VeslFatFatlp42)

Page 18 06-23-2009 23:04:20 I Load Sets Cycles Sn Ke Salt Nallowed Usage 1 25 21 ShDw2 118 35314 1.000 18983 4.3764E+06 .0000007 3

29 241Hydro2 2 2 2_DHydT2 130 34759 1.000 18643 4.7272E+06 .0000243 25 21 ShDw2 315 3 2 20DHydT2 15 33256 1.000 17771 6.1657E+06 .0000002 15 13 ROP2 1 4 2 2_OHydT2 14 33081 1.000 17642 6.4429E+06 .0000022 5 3lStaup2 120 5 5 3 Staup2 106 24860 1.000 17150 7.6387E+06 .0000007 22 17 ImpST2 5 6 5 3 Staup2 101 32395 1.000 17148 7.6446E+06 .0000003 20 14 SRV94 2 7 5 3 Staup2 99 31317 1.000 16555 9. 4491E+06 .0000002 19 14 SRVB3 2 8 5 3 Staup2 97 30910 1.000 16347 1.0297E+07 .0000094 27 21 ShDw4 118 9 12 31--LFWP7 30 30910 1.000 16347 1.0297E+07 .0000020 27 21 ShDw4 21 10 3 2_DHydT3 130 309 24 1.000 16322 1.0445E+07 .0000009 12 11 LFWP7 9 11 3 2DHydT3 121 30942 1.000 16307 1.0533E+07 .0000112 24 21 ShDwl 118 12 3 2 DHydT3 3 29518 1.000 16184 1. 1284E+07 .0000003 23 07ImpST3 5 13 4 3_Staupl 120' 29474 1.000 16157 1. 1457E+07 .0000002 23 07IImpST3 2 14 1 2 DHydT3 130 28874 1.000 15134 2.1354E+07 .0000001 17 14 SRVBI 2 15 14 13-OPI 1 28874 1.000 15128 2.1471E+07 .0000000 28 24Hydrol 3 16 6 11_LFWP1 30 28874 1.000 15128 2. 1471E+07 .0000001 28 241Hydrol 2 17 4 3Staupl 118 28874 1.000 15128 2.1471E+07 .0000002 21 17_ImpSTl 5 18 6 11iLFWP1 28 28874 1.000 15128 2. 1471E+07 .0000001 30 24Hydro3 3 19 1 2_DHydTl 128 28874 1.000 15128 2.1471E+07 .0000012 6 13 LFWPI 25 20 4 3_Staupl 113 28854 1.000 15117 2 1707E+07 .0000000 16 13 ROP3 1 21 4 3Staupl 112 28854 1.000 15117 2.1707E+07 .0000014 13 ii LFWP8 30 22 1 2_OHydTT 103 26794 1.000 14122 9.2711E+07 .00o0003 8 11 LFWP3 30 23 4 3_Staupl 82 26714 1.000 13989 3.5582E+08 .0000001 10 11 LFWP5 30 Total Usage = 0.0000560 File No.: 0900530.306 Page C-40 of C-40 Revision: 0 F0306-01 RO

ATTACHMENT 3 To Enterciy Letter No. 2.09.050 Structural Integrity Associates, Inc. File No. 0900530.307, "Residual Stress Analysis of Jet Pump Instrument Nozzle (N9A) with Weld Overlay Repair", dated August 10, 2009 (32 pages)

StructuralIntegrity Associates, Inc. File No.: 0900530.307 CALCULATION PACKAGE Project No.: 0900530 Quality Program: 0 Nuclear 0 Commercial PROJECT NAME:

Pilgrim Top Head Flaw and N9 Weld Overlay CONTRACT NO.:

10235773-01 CLIENT: PLANT:

Entergy Nuclear Pilgrim Nuclear Power Station CALCULATION TITLE:

Residual Stress Analysis of Jet Pump Instrumentation Nozzle (N9A) with Weld Overlay Repair Project Manager Preparer(s) &

Document Affected Revision Description Approval Checker(s)

Revision Pages Signature & Date Signatures & Date 0 1 - 32 Initial Issue.

Jennifer E. Smith Hal L. Gustin Preparer 08/10/2009 08/10/2009 Aparna Chintapalli Independent Verifier 08/10/2009 Page 1 of 32 F0306-OIRI

StructuralIntegrity Associates, Inc.

Table of Contents 1.0 O BJECTIV E ......................................................................................................... 4 2.0 D ESIGN IN PU TS .................................................................................................... 4 2.1 Finite Elem ent M odel .................................................................................. 4 2.2 M aterial Properties ........................................................................................ 5 3.0 ASSUM PTION S .................................................................................................. .6 4.0 M ETH O D O LO G Y .................................................................................................. 6 4.1 W eld Bead Sim ulation ................................................................................... 7 4.2 W elding Sim ulation .................................................................................... 8 4.2.1 InternalPressureLoading............................................................................ 8 5.0 WELDMENT TEMPERATURE GUIDELINE ...................................................... 8 6.0 RESULTS O F ANA LY SIS .................................................................................... 9 7.0 REFEREN CES ............................................................................................................ 10 I

File No.: 0900530.307 Page 2 of 32 Revision: 0 F0306-0l

StructuralIntegrity Associates, Inc.

List of Figures Figure 1: Applied Boundary Conditions to the Finite Element Model ............................. 12 Figure 2: As-M odeled Components ................................................................................... 13 Figure 3: As-Modeled Nuggets for ID Weld Repair 1 (2), ID Weld Repair 2 (2), Old WOL (24),

and New WO L (66) ......................................................................................... 14 Figure 4: Internal Pressure Loading ........................................ 15 Figure 5: Predicted Fusion Boundary for ID Weld Repair 1 ....................... 16 Figure 6: Predicted Fusion Boundary for ID Weld Repair 2 ............................................. 17 Figure 7: Predicted Fusion Boundary for Weld Overlay 1 ........................ 18 Figure 8: Predicted Fusion Boundary for Weld Overlay 2 ........................ 19 Figure 9: Post-ID Weld Repair 1 Axial Stress at 70'F ...................................................... 20 Figure 10: Post-ID Weld Repair 1 Hoop Stress at 70'F .................................................... 21 Figure 11: Post-ID Weld Repair 2 Axial Stress at 70'F .................................................... 22 Figure 12: Post-ID Weld Repair 2 Hoop Stress at 70'F .................................................... 23 Figure 13: Post Weld Overlay 1 Axial Stress at 70'F ..................................................... 24 Figure 14: Post Weld Overlay 1 Hoop Stress at 70'F ...................................................... 25 Figure 15: Post Weld Overlay 2 Axial Stress at 70'F ..................................................... 26 Figure 16: Post Weld Overlay 2 Hoop Stress at 70'F ..................................................... 27 Figure 17: Post Weld Overlay Axial Stress at 550'F and 1035 psia ...................................... 28 Figure 18: Post Weld Overlay Hoop Stress at 550'F and 1035 psia ................................ 29 Figure 19: ID Surface Axial Residual Stress ..................................................................... 30 Figure 20: ID Surface Hoop Residual Stress ..................................................................... 31 Figure 21: Path D efinitions ................................................................................................. 32 List of Tables Table 1: AN SY S Input and Output Files ............................................................................ 11 File No.: 0900530.307 Page 3 of 32 Revision: 0 F0306-01E

StructuralIntegrity Associates, Inc.

1.0 OBJECTIVE The Pilgrim jel pump instrument nozzle N9A had a previous weld overlay repair applied in 1984. It was determined that the previous repair did not sufficiently cover all potentially IGSCC-susceptible weld locations at the nozzle to safe end joint. In addition, the overlay was too short to allow a qualified ultrasonic examination of the underlying material. The Reference [1] calculation designed an upgrade and extension to the repair to bring the entire repair up to current standards, and to allow ultrasonic examination of the weld overlay and underlying welds. This updated repair has been installed on the N9A nozzle.

The objective Of this evaluation is to perform a weld residual stress analysis using ANSYS finite element software [2] on the jet pump instrumentation nozzle due to the new weld overlay (WOL) repair. The new WOL was applied in order to enlarge the original WOL in order for it to cover both the nozzle-to-safe end weld and the safe end-to-penetration seal welds and allow for inspection. This analysis includes performing two weld repairs from the inner diameter (ID) surface for postulated flaws within the original nozzle-to-safe end weld and the safe end-to-penetration seal weld. The two ID weld repairs are simulated to provide an unfavorable stress condition (prior to applying the weld overlay) due to the original fabrication of these welds. The nozzle-to-safe end and safe end-to-penetration seal welds are not considered in this analysis. The original WOL from 1984 is modeled and is performed in this analysis followed by the new WOL.

The results will be evaluated to demonstrate that the weld overlay repair has indeed generated a favorable stress condition for the jet pump instrumentation nozzle, safe end, and penetration seal by inducing a compressive stress condition on the ID surface. The favorable stress condition minimizes and/or arrests crack initiation/propagation caused by Inter Granular Stress Corrosion Cracking (IGSCC) in the susceptible DMW material.

2.0 DESIGN INPUTS 2.1 Finite Element Model The finite element model of the jet pump instrumentation nozzle, including material properties, is obtained from Reference [3]. The ID weld -epairs on the nozzle-to-safe end weld and the safe end-to-penetration seal weld are included in this analysis to show that the significant tensile stresses generated by these weld repairs are mitigated by the weld overlay repair.

Section 4.2 of MRP-169 states that, to adequately demonstrate the favorable residual stress effects of a weld overlay, one must start with a highly unfavorable, pre overlay residual stress condition such as that which would result from an ID surface weld repair during construction. If the nozzle specific weld overlay design is shown to produce favorable residual stresses in this severe case, one can be assured that it will effectively mitigate against future Intergranular Stress Corrosion Cracking (IGSCC) in the File No.: 0900530.307 Page 4 of 32 Revision: 0 F0306-011

StructuralIntegrity Associates, Inc.

DMW. While MRP-169 applies to PWR's, the same methodology is used here in order to insure the WOL will produce favorable residual stresses.

Figure 1 shows the applied structural boundary conditions on the axisymmetric finite element model, while Figure 2 shows the different components in the finite element model. The weld overlay nugget layout used for the residual stress evaluation is shown in Figure 3. The progression of the overlay welding is from the nozzle end to the piping end. The welding direction was chosen based on communications with the client.

Axisynmmetric PLANE55 elements are used in the thermal analysis, while axisymmetric PLANE182 elements are used in the stress analysis. The weld bead depositions are simulated using the element "birth and death" feature in ANSYS. A node on the vessel ID was fixed in all directions for the stress run in order to constrain the model against infinite motion in the y-direction.

The element "birth and death" feature in ANSYS allows for the deactivation (death) and reactivation (birth) of the elements' stiffness contribution when necessary. It is used such that elements that have no contribution to a particular phase of the weld simulation process are deactivated (via EKILL command) because they have not been deposited. The deactivated elements have near-zero conductivity and stiffness contribution to the structure. When those elements are required in a later phase, they are then reactivated (via EALIVE command).

The analyses consist of a thermal pass to determine the temperature distribution due to the welding process, and an elastic-plastic stress pass to calculate the residual stresses through the thermal history.

Appropriate weld heat efficiency along with sufficient cooling time are utilized in the thermal pass to ensure that the temperature between weld layer nuggets meets the required interpass temperature as well as obtain acceptable overall temperature distribution within the FEM (i.e., peak temperature, sufficient resolution of results, etc.). In the stress pass, symmetric boundary conditions are applied on the end of the penetration seal as well; as the vessel. A node on the vessel ID was also fixed in the y direction to prevent the entire model from moving due to the loading.

2.2 Material Properties The materials of the various components of the model are listed below per Reference [3].

• Nozzle Body: A-508 Cl. 2

• Old Safe End SA-182-F304

• Penetration Seal SA-182-F304

• Nozzle to Old Safe-End Weld Inc. 182

• Old Safe-End to Penetration Seal Weld Inc. 182

• Weld Butters Inc. 182

• Old Weld Overlay Inc. 182

• Cladding SA-240 Type 304 File No.: 0900530.307 Page 5 of 32 Revision: 0 F0306-01f

Structural Integrity Associates, Inc.

• New Weld Overlay Alloy 52M

• Vertical Pipe 304 Stainless Steel

• ID Weld Repairs Inc. 182 The temperature dependent nonlinear material property values are obtained from Reference [3] (input file MPropMISO_NLinearPNPS.INP).This analysis applies the multi-linear isotropic hardening material behavior available within the ANSYS finite element program.

3.0 ASSUMPTIONS The following assumptions are used in the residual stress evaluation:

1. Assumptions from Reference [3] are applicable in this calculation.

2. A convection heat transfer coefficient boundary condition of 5.0 Btuihr-ft2 -°F at 70'F bulk ambient temperature is applied to simulate the air condition at the inside surface of the nozzle during the application of the ID weld repair I and ID weld repair 2.

3. The outside surface of the nozzle has a heat transfer coefficient of 5.0 Btu/hr-ftZ-°F at 70'F bulk temperature during the application of the ID weld repair 1 and ID weld repair 2.

4. During both weld overlay processes, the nozzle is assumed to be filled with water. Therefore, the applied heat transfer boundary condition of 20.0 Btu/hr-ft2 -°F at 70'F bulk temperature was used on the inside surface of the nozzle to simulate water.

5. The outside surface of the nozzle had a heat transfer coefficient of 5.0 Btu/hr-fte-°F at 70'F bulk temperature during both WOL processes. This represents, an air environment.

6. A maximum interpass temperature of 350'F between the depositions of weld nuggets is assumed for all welding processes [4]. This is confirmed by the welding procedure in Reference [12].

7. Additional assumptions including details on the heat source and heat efficiency values can be obtained from Reference [5].

4.0 METHODOLOGY The residual stresses due to welding are controlled by various welding parameters, thermal transients due to application of the welding process, temperature dependent material properties, and elastic-plastic stress reversals. The analytical technique uses finite element analysis to simulate the multi-pass weld repair and weld overlay processes.

A residual stress evaluation process was previously developed in an internal SI project. Details of the process and its comparison to actual test data are provided in Reference [5]. The same process will be used herein. The finite element model of the jet pump instrumentation nozzle was developed in File No.: 0900530.307 Page 6 of 32 Revision- 0 F0306-01:

V StructuralIntegrity Associates, Inc.

Reference [3]. The model includes the instrumentation nozzle, the original nozzle to safe end dissimilar metal weld (DMW), the left over piece of the original safe end, the DMW that attaches the old safe end to the penetration seal, a portion of the penetration seal, the original weld overlay repair (WOL), the new WOL, a postulated weld repair at each of the DMWs, and a portion of the attached piping.

4.1 Weld Bead Simulation In order to reduce computational time, individual weld beads or passes are lumped together into weld nuggets. This methodology is based on the approach presented in References 6, 7, 8, and 9.

The number of equivalent bead passes is estimated by dividing each nugget area by the area of an individual bead. The resulting number of equivalent bead passes per nugget is used as a multiplier to the heat generation rate. The progression of the overlay welding is from the nozzle end to the piping end.

The welding direction was chosen based on communications with the client. A summary of nuggets for the welds is summarized as follows (see Figure 3):

" The ID weld repair 1 (nozzle-to-safe end weld) is performed in two layers, with one nugget for each layer. A total of 2 nuggets are defined for the ID weld repair 1.

• The ID weld repair 2 (safe end-to-penetration seal) is performed in 2 layers, with one nugget for each layer. A total of 2 nuggets are defined for ID weld repair 2.

• The old weld overlay is performed in three layers. A total of twenty four nuggets are defined for this weld overlay.

o Layer one is comprised of nine nuggets o Layer two is comprised of eight nuggets o Layer three is comprised of seven nuggets

• The new weld overlay is performed in four layers, which are applied in 3 pieces. The first piece has three layers and is on the nozzle side of the old WOL. The second piece consists of three layers and is on the piping side of the old WOL. The third and final piece is one layer and covers the previous two pieces as well as the old WOL. The necessity of a three piece weld overlay can be seen in Reference [11]. A total of sixty six nuggets are defined for the new weld overlay:

o Piece 1, Layer one is comprised of ten nuggets o Piece 1, Layer two is comprised of ten nuggets o Piece 1, Layer three is comprised of ten nuggets o Piece 2, Layer one is comprised of five nuggets o Piece 2, Layer two is comprised of five nuggets o Piece 2, Layer three is comprised of five nuggets o Piece 3, Layer one is comprised of twenty one nuggets File No.: 0900530.307 Page 7 of 32 Revision: 0 F0306-01O

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4.2 Welding Simulation ID weld repair 1, on the nozzle-to-safe end weld, is applied first. After ID weld repair 1 is completed, the model is cooled down to a uniform ambient temperature of 70'F. Next, ID weld repair 2, on the safe end-to-penetration seal weld, is applied. After ID repair 2 is completed, the model is again cooled to a uniform ambient temperature of 70'F. This is followed by the application of the old WOL, cooling it to an ambient temperature of 70'F and finally followed by the new weld overlay simulation.

After the weld overlay is completed, the model is cooled to a uniform ambient temperature of 70'F to obtain the combined residual thermal stresses at room temperature. Then it is heated to a uniform operating temperature of 550'F [10] and operating pressure of 1035 psia [10] in order to obtain the combined residual thermal stresses at operating temperature and pressure.

4.2.1 InternalPressureLoading The internal operating pressure of 1035 psia[10] is applied to the model. Due to the closed piping end of the model, this pressure is applied on the inside surfaces of the Nozzle, DMW welds, Old Safe End, ID Repairs, and Penetration Seal. See Figure 4 for applied pressure loadings. The same boundary conditions are used for the pressure loading as were applied for the stress runs and described in section 2.1.

The ANSYS input and output files for the analysis are listed in Table 1.

5.0 WELDMENT TEMPERATURE GUIDELINE The analytical procedure described in Section 4.0 has provided reasonable results as seen in previous "similaranalyses when compared to results from test data. This can be demonstrated by observing the fusion boundary prediction of the welds. Figures 5 through 8 show the predicted fusion boundaries for all the welding processes as generated by ANSYS for this specific overlay. The fusion boundaries represent the predicted maximum temperature contour mapping that the weld nugget elements will reach during each welding process. Note that the figures are composites showing the maximum temperature among all nuggets of each weld. This is made possible by an ANSYS macro (MapTemp.MAC) that reads in the maximum predicted temperatures across the different weld nugget elements during the welding process and displays it as a temperature contour plot.

The figures show that all weld elements have reached temperatures between 2,024°F and 3,000 0 F. It also shows that the heat penetration depth, where temperatures are above 1,300'F, is similar in size to the heat affected zone (HAZ) of roughly between 1/8" and 1/4".

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6.0 RESULTS OF ANALYSIS Figures 9 and 10 depict the axial and hoop residual stress distributions for the post-ID weld repair 1 condition, on the nozzle-to-safe end weld, at 70'F, respectively. The axial direction and the hoop direction are with respect to the global coordinate system, the axial stress is SY and the hoop stress is SZ. Once again, it is shown that extensive tensile axial and hoop residual stresses occur along the inside surface of the nozzle in the vicinity of the ID weld repair 1.

Figures 11 and 12 depict the axial and hoop residual stress distributions for post-ID weld repair 2 condition, on the safe end-to-penetration seal weld, at 70'F, respectively. Figures 13 and 14 depict the axial and hoop residual stress distributions for the post-WOL 1 condition at 70'F, respectively. Figures 15 and 16 depict the axial and hoop residual stress distributions for the post-WOL 1 condition at 70°F, respectively. Figures 17 and 18 depict the resultant residual and operating stress distributions for the post-WOL 2 configuration at the maximum operating temperature of 550'F and operating pressure of 1035 psia in the axial and hoop directions, respectively.

Figures 19 and 20 are ID surface stress plots for the axial and hoop directions as a function of distance from the ID weld repair 1 centerline, respectively. The results are plotted for post-ID weld repair 1, post ID weld repair 2, post-WOL 1 at 70'F, and post-WOL 2 at 70'F, and post-WOL 2 at 550'F and 1035 psia.

Furthermore, Figures 19 and 20 show that post-overlay compressive stresses for both the 70'F and operating conditions (550'F/1035 psia) are present on most of the ID surface of the susceptible material.

This would indicate that at any intermediate steady-state operating condition (i.e., temperature and pressure) that the residual stresses would remain compressive. Any additive loads (i.e., thermal transients) are short term in nature and are not relevant to IGSCC concerns. The results suggest that the weld overlay has indeed mitigated the susceptible material against inter granular stress corrosion cracking (IGSCC).

In addition, through-wall axial and hoop stress results are extracted for various paths defined in Figure

21. Six paths were extracted, three paths for each dissimilar metal weld. One path was extracted on each weld through the center of the ID repair. Also, a path was extracted on each side of each dissimilar metal weld. On the nozzle end, the path was taken through the weld material since the nozzle material is not susceptible to cracking. In the three other cases, the path is taken through the stainless steel material, since this is the material more likely to crack. The objective is to get stress estimates in the materials which are susceptible to IGSCC. The results obtained will be used for a subsequent crack growth analysis in a separate calculation package. Two sets of data are obtained, which are for post-WOL at 70'F and for post-WOL at 550'F/1035 psia.

The post-processing outputs are listed in Table 1. They are further processed in Excel spreadsheet PNPS_0900530_307_RES.xls.

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7.0 REFERENCES

1. SI Calculation, Revision 1, "Weld Overlay Design for Jet Pump Instrumentation Nozzle N9A." April 30, 2009, SI File No. 0900530.301.

2. ANSYS/Mechanical, Release 8.1 (w/Service Pack 1), ANSYS Inc., June 2004.

3. SI Calculation, Revision A DRAFT, "Weld Overlay Finite Element Model (FEM) and Material Properties for Nozzle N9A." June, 2009, SI File No. 0900530.305.

4. ASME Boiler and Pressure Vessel Code Case N-740-2, "Full Structural Dissimilar Metal Weld Overlay for Repair or Mitigation of Class 1, 2, and 3 items,Section XI, Division 1."

5. SI Calculation No. 0800777.304, Revision 0, "Residual Stress Methodology Development and Benchmarking of a Small Diameter Pipe Weld Overlay Using MISO Properties."

6. P. Dong, "Residual Stress Analysis of a Multi-Pass Girth Weld: 3-D Special Shell Versus Axisymmetric Models," Journal of Pressure-Vessel Technology, Vol. 123, May 2001.

7. Rybicki, E. F., et al., "Residual Stresses at Girth-Butt Welds in Pipes and Pressure Vessels,"

U.S. Nuclear Regulatory Commission Report NUREG-0376, R5, November 1977.

8. Rybicki, E. F., and Stonesifer, R. B., "Computation of Residual Stresses Due to Multipass Welds in Piping Systems," Journal of Pressure Vessel Technology, Vol. 101, May 1979.

9. MaterialsReliability Program: Technical Basisfor Preemptive Weld Overlays for Alloy 82/182 Butt Welds in PWRs (MRP-169), EPRI, Palo Alto, CA, and Structural Integrity Associates, Inc., San Jose, CA: 2005. 1012843.

10. Nuclear Energy, Document No. 26A5821, "Reactor Vessel- Thermal Power Optimization,"

Rev. 0, March 5, 2002. SI File No. 0900530.205.

11. Welding Services, Inc. Drawing. "Construction Drawing Pilgrim, N9A." (2 sheets),

Drawing No. 409506, May 1, 2009, SI File No. 0900530.202.

12. Pilgrim Nuclear Power Station. Temporary Procedure No. TP09-029. Welding Procedure Specification No. WPS 03-43-T-80410759. Revision 0. April 2009. SI File No.

0900530.206.

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Table 1: ANSYS Input and Output Files

- IputFie -. >y*>'~.<- De'scrip'fioifCornmente',"

PNPS-N9.INP Structural geometry for 2D axisymmetric geometry [3]

MProp MISO NLinear PNPS.INP Material Property data of E, alpha, conductivity, specific heat, and stress strain curves [3]

BCNUGGET2D.INP Weld nuggets definition and boundary conditions file PICK2D.[NP Writes boundary conditions and nugget definitions into BCNUGGET2D.INP file THERMAL2D.INP Thermal pass for simulating weld processes STRESS2D.INP Stress pass for simulating weld processes WELD1 mntr.INP Contains LDREAD commands for ID weld repair 1 portion of the stress pass WELD2 mntr.INP Contains LDREAD commands for ID weld repair 2 portion of the stress pass WELD3 mntr.INP Contains LDREAD commands for WOL 1 portion of the stress pass WELD4 mntr.INP Contains LDREAD commands for'WOL 2 portion of the stress pass POST2D PATH.INP Post-processing file to extract path stresses POST2D ID.INP Post-processing file to extract ID surface stresses File -, . Descrlptloii/omment PATH T70.OUT Path stress outputs for post-WOL 2 at 70TF PATH T550 P1035.OUT Path stress outputs for post-WOL 2 at 550TF and 1035 psia ID NLIST.OUT ID surface nodal coordinate outputs ID WELD1.OUT ID surface stress outputs for post-ID weld repair 1 at 70TF ID WELD2.OUT ID surface stress outputs for post-ID weld repair 2 at 70TF ID WELD3.OUT ID surface stress outputs for post-WOL 1 at 70TF ID T70.OUT ID surface stress outputs for post-WOL 2 at 70°F ID T550 P1035.OUT ID surface stress outputs for post-WOL 2 at 550TF and 1035 psia PNPS 0900530 307 RES.xls Excel spreadsheet containing all output data File No.: 0900530.307 Page 11 of 32 Revision: 0 F0306-01E

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Figure 1: Applied Boundary Conditions to the Finite Element Model File No.: 0900530.307 Page 12 of 32 Revision: 0 F0306-01f

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AREAS' jW --

AREAS MAT NUM MAT NUM 14 :13 b New WOL Old WOL ID Weld Repair 1/

Safe End-to-Penetration Seal Jet Pump Instrumentation ID Weld Repair 2 Weld Weld Nozzle \

Piping Nozzle-to-Old Old ýafe End Nozzle Cladding Safe End Weld Seal PILGRIM NYA Nozzle Figure 2: As-Modeled Components File No.: 0900530.307 Page 13 of 32 Revision: 0 F0306-01

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ELEMENTS

.... .<--i

.......- .% .L."... ...........-....* ,.....

• PILGRIM N9A Nozzle Figure 3: As-Modeled Nuggets for ID Weld Repair 1 (2), ID Weld Repair 2 (2), Old WOL (24),

and New WOL (66)

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ELEMENTS

_____ A-0 230 460 690 920 115 345 575 805 1035 PILGRIM N9A Nozzle Figure 4: Internal Pressure Loading File No.: 0900530.307 Page 15 of 32 Revision: 0 F0306-01

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NODAL SOLUTION STEP=137 SUB =1 TIME=41 TEMP SMN =72.32 SMX =3000

. .. . . i"h ... ......r -,,,1 72 32 722.915 1374 2024 2675 397 618 1048 1699 2349 3000 Predicted fusion boundary plot Figure 5: Predicted Fusion Boundary for ID Weld Repair 1 File No.: 0900530.307 Page 16 of 32 Revision: 0 F0306-01:

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NODAL SOLUTION STEP=146 SUB =1 TIME=83 TEMP SMN =70.985 SMX =3000 70.985 721.877 1373 2024 2675 396.431 1047 1698 2349 3000 Predicted fusion boundary plot Figure 6: Predicted Fusion Boundary for ID Weld Repair 2 File No.: 0900530.307 Page 17 of 32 Revision: 0 F0306-01

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NODAL SOLUTION STE2=1204 SUB =1 TIME=178 TEMP SMN =74.312 SMX =3000

-HEH E I4r~

I;iI ,11611 ,1, -,1 1'1 ;11E F FH9 Fi F F 1'i 74.312 724.465 1375 2025 2675 399.389 1050 1700 2350 3000 Predicted fusion boundary plot Figure 7: Predicted Fusion Boundary for Weld Overlay 1 File No.: 0900530.307 Page 18 of 32 Revision: 0 F0306-01

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Figure 8: Predicted Fusion Boundary for Weld Overlay 2 File No.: 0900530.307 Page 19 of 32 Revision: 0 F0306-01.

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Figure 9: Post-ID Weld Repair 1 Axial Stress at 70'F File No.: 0900530.307 Page 20 of 32 Revision: 0 F0306-01I

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NODAL SOLUTION STEP=62 SUB =1 TIME=41 Sz (AVG)

RSYS=0 DMX =.01928 SMN =-45220 SMX =136800 Figure 10: Post-ID Weld Repair 1 Hoop Stress at 70°F File No.: 0900530.307 Page 21 of 32 Revision: 0 F0306-01

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Figure 11: Post-ID Weld Repair 2 Axial Stress at 70°F File No.: 0900530.307 Page 22 of 32 Revision: 0 F0306-011

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Figure 12: Post-ID Weld Repair 2 Hoop Stress at 70'F File No.: 0900530.307 Page 23 of 32 Revision: 0 F0306-01I

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Figure 13: Post Weld Overlay 1 Axial Stress at 70°F File No.: 0900530.307 Page 24 of 32 Revision: 0 F0306-01.

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Figure 14: Post Weld Overlay 1 Hoop Stress at 70'F File No.: 0900530.307 Page 25 of 32 Revision: 0 F0306-01:

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Figure 15: Post Weld Overlay 2 Axial Stress at 70'F File No.: 0900530.307 Page 26 of 32 Revision: 0 F0306-01

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Figure 16: Post Weld Overlay 2 Hoop Stress at 70°F File No.: 0900530.307 Page 27 of 32 Revision: 0 F0306-0L

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Figure 17: Post Weld Overlay Axial Stress at 5501F and 1035 psia File No.: 0900530.307 Page 28 of 32 Revision: 0 F0306-O1

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Figure 18: Post Weld Overlay Hoop Stress at 550'F and 1035 psia File No.: 0900530.307 Page 29 of 32 Revision: 0 F0306-01:

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ID Surface Axial Residual Stress e Post ID weld repair 1 70OF --3-Post. ID w eld repair 2 70°F

-A*- Post weld ov erl ay 2 70°F Post weld overlay 550'F/1035 psia

• Postweld overlay 1 70°F Hea tA ff e*cted Zo nes H--

140

-- Nozzle - :afe End 120.

100 80 g ,,

260 W8 . ..

44A (0 0 /ýt'R 1/2.~

-20 -1_ __ _ __ _ _

-60

-80 Distance from ID Weld Repair Centerline (in)

Figure 19: ID Surface Axial Residual Stress File No.: 0900530.307 Page 30 of 32 Revision: 0 F0306-01l

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Figure 20: ID Surface Hoop Residual Stress File No.: 0900530.307 Page 31 of 32 Revision: 0 F0306-01.

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Figure 21: Path Definitions File No.: 0900530.307 Page 32 of 32 Revision: 0 F0306-OIRI

ATTACHMENT 4 To Entergy Letter No. 2.09.050 Structural Intelrity Associates, Inc. File No. 0900530.308, "Crack Growth Analysis for Jet Pump Instrument Nozzle (N9A)". dated August 10, 2009 (55 pages)

V StructuralIntegrity Associates, Inc. File No.: 0900530.308 CALCULATION PACKAGE Project No.: 0900530 Quality Program: Z Nuclear 0 Commercial PROJECT NAME:

Pilgrim Top Head Flaw and N9 Weld Overlay CONTRACT NO.:

10235773-01 CLIENT: PLANT:

Entergy Nuclear Operations, Inc. Pilgrim Nuclear Power Station CALCULATION TITLE:

Crack Growth Analysis for Jet Pump Instrumentation Nozzle (N9A)

Document Affected Project Manager Preparer(s) &

Revision Pages Revision Description Approval Checker(s)

Signature & Date Signatures & Date 0 1 - 4' Initial Issue A- I- A-20 B1- - B-21 H. L. Gustin Charlotte J. Herhold 08/10/09 Preparer 08/10/09 H. L. Gustin Preparer 08/10/09 Terry J. Herrmann Independent Verifier 08/10/09 Page 1 of 14 F0306-01 RO

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Table of Contents

1.0 INTRODUCTION

/OBJECTIVE ............................................................................... 3 2.0 M ETH O D O LO G Y .................................................................................................. 3 3.0 DESIGN INPUTS ................................................ 4 3.1 M aterials and G eom etry .............................................................................. 4 3.2 Loading ....................................................................................................... 4 4.0 A SSU M PTION S ................................................................................................... 7 5.0 CRACK GROWTH CALCULATIONS .................. ................................................. 8 5.1 Fatigue Crack Growth (FCG) ....................................................................... 8 5.2 Intergranular Stress Corrosion Cracking (IGSCC) .................... 8 6.0 RESULTS AND CONCLUSIONS ....................................................................... 10 7.0 REFEREN C ES .................................................................................................... II APPENDIX A IGSCC CASE PC-CRACK OUTPUT FILES ........................................ A-1 APPENDIX B FCG CASE PC-CRACK OUTPUT FILES ............................................. B-1 List of Tables Table 1: Results Sum m ary ................................................................................................ 12 List of Figures Figure 1. Path D efinitions [4] ........................................................................................... 13 Figure 2. Fracture Mechanics Results, K-vs-a Curve (from pc-CRACK) ......................... 14 File No.: 0900530.308 Page 2 of 14 Revision: 0 F0306-01O

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1.0 INTRODUCTION

/OBJECTIVE A weld overlay was applied to the N9A Jet Pump Instrumentation nozzle at Pilgrim Nuclear Power Station during the Spring 2009 refueling outage [6]. This weld overlay was applied over a preexisting 1984 weld overlay that was applied to mitigate a flaw found in the original Type 304 safe end between the nozzle and penetration seal [1]. The original 1984 weld overlay did not sufficiently cover all potentially IGSCC-susceptible weld locations at the nozzle to safe end joint, thus necessitating the application of the 2009 weld overlay. The station has made commitments to perform analyses, including finite element stress analyses, of the 2009 weld overlay following startup.

The purpose of this calculation package is to apply linear elastic fracture mechanics (LEFM) to calculate crack growth in the nozzle-to-safe end dissimilar metal weld (DMW) for the reactor pressure Vessel (RPV) jet pump instrumentation nozzle N9A at Pilgrim Nuclear Power Station.

Loads considered are internal pressure and weld overlay (WOL) repair residual stresses. Both fatigue crack growth (FCG) and Intergranular Stress Corrosion Cracking (IGSCC) are considered.

2.0 METHODOLOGY The allowable end-of-evaluation period flaw depth to thickness ratio (a/t) was taken from Table IWB-3641-3, which is derived by the methodology of Appendix C of ASME Code,Section XI [2].

The geometry and design pressure for the N9A nozzle is documented in a separate design input calculation [3]. The post-weld overlay (WOL) repair residual stresses are documented in a separate stress analysis calculation [4].

Crack growth is computed using linear elastic fracture mechanics (LEFM) techniques. IGSCC growth is determined by computing the stress intensity factor versus flaw depth curve (K-vs.-a) at steady state normal operating conditions. Crack growth laws for Alloy 600 weld metals (Alloy 82/Alloy 182) are used at the susceptible DMW material region [2, 10]. The time for the observed flaw to grow to 75% of the weld thickness is determined, with and without the benefit of WOL residual stresses.

• The crack growth analysis was performed using the LEFM analysis option in pc-CRACK for WindowsTM software [5]. This software includes options for the evaluation of FCG and IGSCC, and allows for defining load cases, material properties, crack models, and the selection of the applicable crack growth law. Appendix A contains pc-CRACK output of the IGSCC growth analysis and Appendix B contains pc-CRACK output of the FCG growth analysis.

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3.0 DESIGN INPUTS 3.1 Materials and Geometry The section of the jet pump instrumentation nozzle evaluated for crack growth, and considered representative for the susceptible material region, is described below.

Details of the jet pump instrumentation nozzle materials are provided in References [3], [6], [7], and

[8].

Material (Safe End): SA-182 Type F304 Material (Nozzle): SA-508 Class 2 Material (Weld): Alloy 82/182 Material (Weld Overlay): Alloy 52M Design Pressure (P): 1250 psig Normal Operating Pressure: 1035 psig (increased for Power Optimization, [9, sheet 8])

Details of the nozzle geometry are provided in Reference [7, sheet 8 of A-476 (PDF page 576)], with the as-built final dimensions of the 2009 weld overlay provided in Reference [I I].

Before 2009 weld overlay:

Outside radius OR = 2.53125 inches Inside radius IR= 1.89125 inches Thickness' t = 0.608 inch Note 1: The nominal thickness prior to the 2009 weld overlay is assumed as 0.64 inch in this analysis, in order to be consistent with previous pc-CRACK analyses in PNPS-19Q-311 [12] and the weld overlay design basis in 0900530.301 [6].

As-built including the 2009 weld overlay (with a thickness of 0.4 inch) [11]:

Outside radius OR= 2.93125 inches

.Inside radius IR=I1.89125 inches Thickness t= 1.04 inch 2 2 2

Pipe Cross-Sectional Area A= 7r(OR -IR ) = 15.76 in 2 Section Modulus Z= 7t/4(OR 4 -IR 4)/OR= 16.35 in 3.2 Loading Loads considered in this evaluation are internal pressure and WOL residual stresses, as obtained from the finite element analysis [4]. Bending stresses are identified as negligible in the original stress report [7, sheets 5 of A-474 (PDF page 524), sheet 18 of A-485 (PDF page 535), and sheet 21 File No.: 0900530.308 Page 4 of 14 Revision: 0 F0306-01O

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of A-488 (PDF page 538)], and are therefore not included in this analysis. The flaw is assumed to be a circumferential flaw, and thus is unaffected by hoop stresses. Therefore, axial stresses due to internal pressure are the only stresses that could contribute to crack growth of a circumferential flaw. The axial pressure stresses will be treated as a membrane stress, which is constant across the entire thickness of the pipe.

The through-wall residual stress distributions are curve fit with a third order polynomial in form shown below:

2

+C 3x 3

(1)

C(X) C 0 + ClX + C 2x where:

cy = axial stress x = distance from inside surface Residual stress results were obtained for through-wall paths in the susceptible material regions. The paths used are as defined in Figure 1. Six paths were extracted, three paths for each dissimilar metal weld. One path was extracted on each weld through the center of the repair. Also, a path was extracted on each side of each dissimilar metal weld. On the nozzle end, the path (Path 1) was taken through the weld material since the nozzle material is not susceptible to cracking. In the three other cases, the path is taken through the stainless steel material, since this is the material more likely to crack. Two sets of data are obtained, which are for post-WOL at 707F and for post-WOL at 550'F/1 035 psig. The intent for this approach is to characterize the residual stresses for each of the different loading conditions for six different locations associated with the DMW. Residual stresses have a strong effect on IGSCC growth. They have a much less significant effect on fatigue

• crack growth, since they are steady state secondary stresses, and contribute to FCG only through a mean stress effect.

Internal Pressure The pressure stress is evaluated at the normal operating pressure, 1035 psig, and as-built dimensions of the nozzle, which is appropriate for crack growth calculations. The primary axial stress (PAxial) is a combination of the stress of the end cap (Gendcap) and the pressure stress (Gpressure).

P(Q

• IR 2 )

endcap= r(OR2 -I R 2 )

1035(Qr

• 1.891252) aendcap= Zr(2.93125 2 - 1.891252)

Gendcap- 738 psi P*OR apressure= 2 2t File No.: 0900530.308 Page 5 of 14 Revision: 0 F0306-01,

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1035

• 2.93125 G7pressure 2

• 0.64 Cypressure= 2370 psi PAxial = Gendcap + apressure= 738 psi + 2370 psi = 3108 psi Using the outside radius of the pipe to calculate the pressure stress is conservative, and accounts for effects due to pressure on the crack face. This pressure is treated as a membrane stress and is assumed to be constant through the thickness of the pipe.

Note that the original design report reported a design primary membrane stress intensity of 9.6 ksi [7, sheet 18 of A-485], which was based on a hoop stress direction (as opposed to the present axial stress used for crack growth). The design report was also based on design pressure (1250 psi) design thickness. The present calculation is based on operating pressure and as-measured wall thickness.

WOL Residual Stresses The residual stresses which result from implementing a weld repair are developed from the ANSYS model described in Reference [4]. The values of the stresses are given for 70'F and 550'F in [4].

These stresses vary across the thickness and are represented by the curve fit Equation 1. These stresses are obtained using the ANSYS output files "PATHT70.OUT" and "PATHT550_PI035.OUT", and they are digitized using pc-CRACK to perform the curve fit. Six paths were investigated and these residual stresses are used for the crack growth analysis.

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4.0 ASSUMPTIONS Basic assumptions for the analysis are listed below:

• A circumferential flaw is assumed for the purpose of analyzing crack growth over time due to fatigue and stress corrosion cracking.

• The nominal pipe thickness prior to the 2009 weld overlay is assumed as 0.64 inch in this analysis, in order to be consistent with previous pc-CRACK analyses in PNPS-19Q-311 [12]

and the weld overlay design basis in 0900530.301 [6].

• The nozzle itself is not attached to a piping system, and therefore there are no piping-induced loads that need to be considered. Also, bending stresses are identified as negligible in the original stress report [7, sheets 5 of A-474, sheet 18 of A-485, and sheet 21 of A-488].

Hloop stresses are oriented parallel to the assumed flaw, and therefore do not affect the circumferential assumed flaw or flaw growth.

• Residual stress is considered in addition to the axial stress that was calculated above. The through-wall residual stress distribution is sufficiently represented with a third order polynomial curve fit.

• Residual stresses are steady state secondary stresses and therefore only act as a mean stress in regards to fatigue crack growth.

• The axial stresses due to pressure are assumed to be membrane stresses and are constant throughout the thickness of the pipe.

" The primary membrane stress intensity is assumed to be 3.1 ksi, based on the operating pressure and the as-measured wall thickness.

• The nozzle has no internal flow, and therefore it does not experience thermal transients other than startup and shutdown. The total number of startup and shutdown cycles that the plant will likely experience is estimated to be about 400 cycles, per [13, page 4.3-5 (PDF page 819)].

" Also, because the nozzle does not experience flow, credit cannot be taken for Hydrogen Water Chemistry. The Normal Water Chemistry case will be evaluated instead.

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5.0 CRACK GROWTH CALCULATIONS 5.1 Fatigue Crack Growth (FCG)

FCG is calculated using the loading described in Section 3.2 of this calculation. The minimum stress intensity Kmin is taken as the weld repair residual axial stress distribution at 70'F, which is present when the plant is shutdown. The maximum stress intensity Kmax is the combination of the pressure axial stress and the residual axial stress at 550'F. This stress intensity range represents the range seen from shutdown to startup. The FCG after 800 applied cycles is calculated using pc-CRACK software using the crack growth law for austenitic material in air, as described by Figure C-3210-1 in Section XI Appendix C of the ASME Code [2]. 800 cycles was chosen as a conservative estimate that nearly doubles the total number of startup and shutdown cycles the plant will likely experience over its lifetime [13, page 4.3-5 (PDF page 819)]. Appendix B contains output files for FCG with and without WOL residual stresses.

The stress intensity components of Kmax and Kmin for the weld overlay case are shown below.

Kmax Kmin Kresidual 550 Kresidual 70 Kpressure 5.2 Intergranular Stress Corrosion Cracking (IGSCC)

For IGSCC, the applied K (Kmax above) is the crack driving force. The growth of the crack after 100,000 hours0 days <br />0 hours <br />0 weeks <br />0 months <br /> of service, or 11.4 years, is calculated. PVP2008-61299 [10] provides stress corrosion crack growth laws for nickel-base austenitic alloys. The N9A nozzle-to-safe end weld location does not experience any internal flow, so Hydrogen Water Chemistry cannot be assured.

Therefore, the normal water chemistry (NWC) case is evaluated. Specifically, the NWC below EPRI Guidelines Action Level I case is used.

The SCC growth law is, taken from Reference [II], equations 2 and 3:

daC f in dt - CoK, in/hr for KI < 25 ks1iin (2) dt da =C in/hr for K, > 25 ksiin (3) dt File No.: 0900530.308 Page 8 of 14 Revision: 0 F0306-01

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where, I

Water Chemistry Co C1 n Normal 1.6E-08 5.OE-05 2.5 K,= stress intensity factor at flaw tip (ksiVin)

The K-dependent crack growth rates are calculated with pc-CRACK using the coefficients shown above and the K values developed within the software. For this evaluation the'K-independent crack growth rates were not used since the combined stress intensity factor was never greater than +25 ksWin, as seen in Figure 2.

Appendix A contains pc-CRACK output files for the following cases:

" IGSCC case without residual stresses.

• IGSCC case with WOL residual stresses.

Appendix B contains pc-CRACK output files for the following cases:

• FCG case without residual stresses.

• FCG case with WOL residual stresses.

File No.: 0900530.308 Page 9 of 14 Revision: 0 F0306-011

StructuralIntegrity Associates, Inc.

The pc-CRACK and ANSYS computer files used in this evaluation are listed below.

File Name, Description PATH T70.OUT ANSYS Residual Stress Output at 70'F PATH T550 P1035.OUT ANSYS Residual Stress Output at 550'F JPINSCC.OUT pc-CRACK Output File for IGSCC with Weld Overlay, Normal Water Chemistry, and without Residual Stresses JPINSCCR.OUT pc-CRACK Output File for IGSCC with Weld Overlay, Normal Water Chemistry, and considering Residual Stresses JPINFCG.OUT pc-CRACK Output File for Fatigue Crack Growth with Weld Overlay and without Residual Stresses JPINFCGR.OUT pc-CRACK Output File for Fatigue Crack Growth with Weld Overlay and considering Residual Stresses 6.0 RESULTS AND CONCLUSIONS Although no known indication is present in the N9-A nozzle at Pilgrim Nuclear Power Station, for the purpose of this analysis, a starting flaw was assumed to extend entirely through the original wall, and completely around the circumference. Results show that such an indication would not grow by a Fatigue Crack Growth mechanism even without the beneficial effects of residual stress. The maximum allowed crack size is exceeded due to lntergranular Stress Corrosion Cracking at approximately 33,000 hours0 days <br />0 hours <br />0 weeks <br />0 months <br /> (3.8 years) when the beneficial effects of residual stresses are ignored; this is overly conservative. However, there is also no crack growth due to an Intergranular Stress Corrosion Cracking mechanism into the 2009 Inconel weld overlay when residual stresses are considered. Therefore, the structural integrity of the 2009 weld overlay repair will not degrade with time due to ongoing crack growth. Results are presented in Table 1.

File No.: 0900530.308 Page 10 of 14 Revision: 0 F0306-01I

StructuralIntegrity Associates, Inc.

7.0 REFERENCES

1. General Electric Document No. HKI-336, "Field Deviation Disposition Request and Repair Plan", Revision 1, October 11, 1984, SI File No. 0900530.203.

2. ASME Boiler & Pressure Vessel Code,Section XI, 1998 Edition, with Addenda through 2000.

3. Structural Integrity Associates, Inc., "Design Input for Jet Pump Instrumentation Nozzle Finite Element Analyses", Revision A, July 23, 2009, SI File No. 0900530.304.

4. Structural Integrity Associates, Inc., "Residual Stress Analysis of Jet Pump Instrumentation Nozzle (N9A) with Weld Overlay Repair", Revision A, July 23, 2009, SI File No.

0900530.307.

5. pc-CRACK for Windows, Version 3.1-98348, Structural Integrity Associates, 1998.

6. Structural Integrity Associates, Inc., "Weld Overlay Design for Jet Pump Instrumentation Nozzle N9A", Revision 1, April 30, 2009, SI File No. 0900530.301.

7. Combustion Engineering Inc., Pilgrim Document 1979-308-1, Stress Report 1139, "Analytical Report for Pilgrim Reactor Vessel", March 9, 1971, SI File No. PNPS-1OQ-21 1.

8. General Electric Document No. 488 925-1687, "Pilgrim Jet Pump Instrumentation Nozzle Weld Overlay Design", Revision 1, October 3, 1984, Received from George Mileris, SI File No. 0900530.203.

9. GE Nuclear Energy, Document No. 26A582 1, "Reactor Vessel- Thermal Power Optimization", Revision 0, March 5, 2002, SI File No. 0900530.205.

10. ASME Paper PVP2008-61299, "Nickel Alloy Crack Growth Correlations in BWR Environment and Application to Core Support Structure Welds Evaluation", July 2008, SI File No. BWRVIP-01-259P.

11. Entergy Nuclear Operations, Inc., Document No. ECO000014631, "SKM-N9A-I N9A Weld Overlay Design", Received from George Mileris, SI File No. 0900530.207.

12. Structural Integrity Associates, Inc,, "Weld Overlay Design for Jet Pump Instrumentation Nozzles N9A, B", January 31, 2005, SI File No. PNPS-19Q-311.

13. Entergy Nuclear Operations, Inc., "License Renewal Application: Pilgrim Nuclear Power Station", taken from the Nuclear Regulatory Commission's website, <www.nrc.gov>.

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Table 1: Results Summary IGSCC Water Time Crack Chemistry Hours Years Growth Without Residual Normal 33000 3.8 0.1443 in1 Stresses With Residual Normal 100000 11.4 No Growth Stresses FCG2 Without Residual Stresses 0.0002 in With Residual Stresses No Growth Note 1: The maximum allowed crack size of 0.78 inches (a/t = 0.75, per ASME Code [2]) is exceeded at approximately 33000 hours. Please see Section 6.0: Results and Conclusions.

Note 2: Fatigue crack growth calculations are for 800 transient cycles.

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Figure 1. Path Definitions [41 File No.: 0900530.308 Page 13 of 14 Revision: 0 F0306-01:

StructuralIntegrity Associates, Inc.

Stress Intensity Factor

- Primary Axial Stress

-20000

- P l_rsdi_70FAxial

- P2_rsdl_70F_Axial

- P3_rsdl_70F_Axial

- P4_rsdl7SF AMia S-4mm0 - P5_rsdl_70FAxial

- PB_rsdl_70F_Axial

-500m P1_rsdl_550FAxial

- P2_rsdl_50F Axial

- P3_rsdl50F Axial

- P4_rsdl.5SOFAxial

-P5rsdl_55OF Axial

-70000

- P6-rsdl_550FAxial

-80000 Crack Size Figure 2./ Fracture Mechanics Results, K-vs-a Curve (from pc-CRACK)

File No.: 0900530.308 Page 14 of 14 Revision: 0 F0306-01

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APPENDIX A IGSCC CASE PC-CRACK OUTPUT FILES File No.: 0900530.308 Page A-I of A-20 Revision: 0 F0306-01 RO

StructuralIntegrityAssociates, Inc.

IGSCC Case without Residual Stresses Considered tm pc-CRACK for Windows Version 3.1-98348 (C) Copyright '84 -'98 Structural Integrity Associates, Inc.

3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice: 408-978-8200 Fax: 408-978-8964 E-mail: pccrack@structint.com Linear Elastic Fracture Mechanics Date: Thu Jul 23 09:31:12 2009 Input Data and Results File: JPINSCC.LFM

Title:

Pilgrim N9A JPIN IGSCC Analysis without Residual Stresses Load Cases:

Stress Coefficients Case ID CO C1 C2 C3 Type Primary Axial S 3108 0 0 0 Coeff Through Wall Stresses for Load Cases With Stress Coeff.

Wall Case Depth Primary Ax 0.0000 3108 0.0780 3108 0.1560 3108 0.2340 3108 0.3120 3108 0.3900 3108 0.4680 3108 0.5460 -3108 0.6240 3108 File No.: 0900530.308 Page A-2 of A-20 Revision: 0 F0306-01 RO

StructuralIntegrity Associates, Inc.

0.7020 3108 0.7800 3108 Crack Model: Circumferential Crack in Cylinder (t/R=0.2)

Crack Parameters:

Wall thickness: 1.0400 Max. crack size: 0.7800

---

Stress Intensity Factor ........

Crack Case Size Primary.Ax 0.0156 759.948 0.0312 1079.11 0.0468 1326.99 0.0624 1538.47 0.0780 1726.99 0.0936 1899.41 0.1092 2063.43 0.1248 2226.33 0.1404 2383.05 0.1560 2534.8 0.1716 2682.48 0.1872 2826.79 0.2028 2968.26 0.2184 3120.22 0.2340 3277.7 0.2496 3434.73 0.2652 3591.5 0.2808 3748.17 0.2964 3904.87 0.3120 4061.69 0.3276 4232.94 0.3432 4405.17 0.3588 4578.42 0.3744 4752.73 0.3900 4928.14 0.4056 5104.67 0.4212 5285.93 0.4368 5475.77 0.4524 5667.18 0.4680 5860.16 File No.:'0900530.308 Page A-3 of A-20 Revision: 0 F0306-01 RO

V StructuralIntegrity Associates, Inc.

0.4836 6054.71 0.4992 6250.85 0.5148 6448.55 0.5304 6663.88 0.5460 6889.39 0.5616 7117.16 0.5772 7347.17 0.5928 7579.4 0.6084 7813.83 0.6240 8050.45 0.6396 8309.06 0.6552 8570.31 0.6708 8834.16 0.6864 9100.59 0.7020 9369.59 0.7176 9641.12 0.7332 9924.6 0.7488 10229.8 0.7644 10538.1 0.7800 10849.5 Crack Growth Laws:

Law ID: Overlay Type: Corrosion Model: Paris da/dN = c * (dK)^n where dK = Kmax - Kmin dK > Kthres Kmax < KIc Material parameters:

c = 1.6000e-008 n = 2.5000 Kthres = 0.0000 Material Fracture Toughness KIc:

Material ID: Weld Overlay Depth KIc File No.: 0900530.308 Page A-4 of A-20 Revision: 0 F0306-01 RO

StructuralIntegrity Associates, Inc.

0.2500 200.0000 1.0000 200.0000 2.0000 200.0000 Initial crack size= 0.6400 Max. crack size= 0.7800 Number of blocks= 1 Print increment of block= I Cycles CaIc. Print Crk. Grw. Mat.

Subblock /Time incre. incre. Law KIc Overlay 100000 1000 1000 Overlay Weld Overlay Kmax Kmin Subblock Case ID Scale Factor Case ID Scale Factor Overlay Primary Axial Stress 0.0010 Crack growth results:

Total Subblock Cycles Cycles DaDn

/Time /Time Kmax Kmin DeltaK R /DaDt Da a a/thk Block: I 1000 1000 8.32e+000 0.00e+000 8.32e+000 0.00 3.19e-006 3.19e-003 0.6432 0.62 2000 2000 8.37e+000 0.00e+000 8.37e+000 0.00 3.24e-006 3.24e-003 0.6464 0.62 3000 3000 8.42e+000 0.00e+000 8.42e+000 0.00 3.29e-006 3.29e-003 0.6497 0.62 4000 4000 8.48e+000 0.00e+000 8.48e+000 0.00 3.35e-006 3.35e-003 0.6531 0.63 5000 5000 8.53e+000 0.00e+000 8.53e+000 0.00 3.40e-006 3.40e-003 0.6565 0.63 6000 6000 8.59e+000 0.00e+000 8.59e+000 0.00 3.46e-006 3.46e-003 0.6599 0.63 7000 7000 8.65e+000 0.00e+000 8.65e+000 0.00 3.52e-006 3.52e-003 0.6635 0.64 8000 8000 8.71e+000 0.00e+000 8.71e+000 0.00 3.58e-006 3.58e-003 0.667 0.64 9000 9000 8.77e+000 0.00e+000 8.77e+000 0.00 3.65e-006 3.65e-003 0.6707 0.64 10000 10000 8.83e+000 0.00e+000 8.83e+000 0.00 3.7le-006 3.7le-003 0.6744 0.65 11000 11000 8.90e+000 0.00e+000 8.90e+000 0.00 3.78e-006 3.78e-003 0.6782 0.65 12000 12000 8.96e+000 0.00e+000 8.96e+000 0.00 3.85e-006 3.85e-003 0.682 0.66 13000 13000 9.03e+000 0.00e+000 9.03e+000 0.00 3.92e-006 3.92e-003 0.6859 0.66 File No.: 0900530.308 Page A-5 of A-20 Revision: 0 F0306-01 RO

C StructuralIntegrityAssociates, Inc.

14000 14000 9.09e+000 0.00e+000 9.09e+000 0.00 3.99e-006 3.99e-003 0.6899 0.66 15000 15000 9.16e+000 0.00e+000 9.16e+000 0.00 4.06e-006 4.06e-003 0.694 0.67 16000 16000 9.23e+000 0.00e+000 9.23e+000 0.00 4.14e-006 4.14e-003 0.6981 0.67 17000 17000 9.30e+000 0.00e+000 9.30e+000 0.00 4.22e-006 4.22e-003 0.7024 0.68 18000 18000 9.38e+000 0.00e+000 9.38e+000 0.00 4.3 le-006 4.3 le-003 0.7067 0.68 19000 19000 9.45e+000 0.00e+000 9.45e+000 0.00 4.39e-006 4.39e-003 0.7111 0.68 20000 20000 9.53e+000 0.0Oe+000 9.53e+000 0.00 4.48e-006 4.48e-003 0.7155 0.69 21000 21000 9.61e+000 0.00e+000 9.61e+000 0.00 4.58e-006 4.58e-003 0.7201 0.69 22000 22000 9.69e+000 0.00e+000 9.69e+000 0.00 4.67e-006 4.67e-003 0.7248 0.70 23000 23000 9.77e+000 0.00e+000 9.77e+000 0.00 4.78e-006 4.78e-003 0.7296 0.70 24000 24000 9.86e+000 0.00e+000 9.86e+000 0.00 4.88e-006 4.88e-003 0.7344 0.71 25000 25000 9.95e+000 0.00e+000 9.95e+000 0.00 5.00e-006 5.00e-003 0.7394 0.71 26000 26000 1.00e+001 0.00e+000 1.00e+001 0.00 5.12e-006 5.12e-003 0.7446 0.72 27000 27000 1.01e+001 0.00e+000 1.01e+001 0.00 5.25e-006 5.25e-003 0.7498 0.72 28000 28000 1.02e+001 0.00e+000 1.02e+001 0.00 5.38e-006 5.38e-003 0.7552 0.73 29000 29000 1.04e+001 0.00e+000 1.04e+001 0.00 5.52e-006 5.52e-003 0.7607 0.73 30000 30000 1.05e+001 0.00e+000 1.05e+001 0.00 5.67e-006 5.67e-003 0.7664 0.74 31000 31000 1.06e+001 0.00e+000 1.06e+001 0.00 5.82e-006 5.82e-003 0.7722 0.74 32000 32000 1.07e+001 0.00e+000 1.07e+001 0.00 5.98e-006 5.98e-003 0.7782 0.75 33000 33000 1.08e+001 0.00e+000 1.08e+001 0.00 6.15e-006 6.15e-003 0.7843 0.75 Crack size exceeded 0.7800 at cycle/time 33000 End of pc-CRACK Output File No.: 0900530.308 Page A-6 of A-20 Revision: 0 F0306-01 RO

StructuralIntegrity Associates, Inc.

]GSCC Case with Residual Stresses Considered tm pc-CRACK for Windows Version 3.1-98348 (C) Copyright '84 -'98 Structural Integrity Associates, Inc.

3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice: 408-978-8200 Fax: 408-978-8964 E-mail: pccrack@structint.com Linear Elastic Fracture Mechanics Date: Tue Jul 21 11:16:05 2009 Input Data and Results File: JPINSCCR.LFM

Title:

Pilgrim N9A JPIN IGSCC Analysis with Residual Stresses Load Cases:

Case ID: P1_rsdl_70FAxial --- Stress Distribution Depth Stress 0.0000 -2706.0000 0.0563 -13254.0000 0.1127 -19160.0000 0.1690 -23077.0000 0.2254 -31868.0000 0.2817 -51968.0000 0.3380 -63785.0000 0.3944 -54357.0000 0.4507 -44784.0000 0.5070 -39731.0000 0.5634 -19705.0000 0.6197 -4105.7002 0.6761 8184.1001 0.7324 19524.0000 0.7887 17780.0000 0.8451 17251.0000 0.9014 22486.0000 File No.: 0900530.308 Page A-7 of A-20 Revision: 0 F0306-O1 RO

StructuralIntegrity Associates, Inc.

0.9577 36904.0000 1.0141 47132.0000 1.0704 66681.0000 1.1268 76587.0000 Case ID: P2_rsdl_70FAxial --- Stress Distribution Depth Stress 0.0000 -15358.0000 0.0523 -19223.0000 0.1046 -25101.0000 0.1569 -29725.0000 0.2092 -32260.0000 0.2615 -36466.0000 0.3138 -42170.0000 0.3661 -43463.0000 0.4184 -38617.0000 0.4707 -25977.0000 0.5230 -10235.0000 0.5753 10778.0000 0.6276 8643.0996 0.6799 2881.7000 0.7322 -1006.4000 0.7845 20303.0000 0.8368 24785.0000 0.8891 32769.0000 0.9414 44502.0000 0.9938 63483.0000 1.0460 76944.0000 Case ID: P3_rsdl_70FAxial --- Stress Distribution Depth Stress 0.0000 -28088.0000 0.0547 -25470.0000 0.1093 -24553.0000 0.1640 -23860.0000 0.2187 -23108.0000 0.2733 -23068.0000 0.3280 -25974.0000 0.3826 -30169.0000 0.4373 -31442.0000 0.4920 -26786.0000 File No.: 0900530.308 Page A-8 of A-20 Revision: 0 F0306-01 RO

StructuralIntegrity Associates, Inc.

0.5466 -16923.0000 0.6013 876.7800 0.6559 -7463.1001 0.7106 10757.0000 0.7653 4197.2998 0.8199 9730.2002 0.8746 8700.4004 0.9292 26349.0000 0.9839 42410.0000 1.0386 59758.0000 1.0932 69767.0000 Case ID: P4_rsdl_70FAxial --- Stress Distribution Depth Stress 0.0000 -3281.0000 0.0579 -5048.2002 0.1158 -8148.1001 0.1737 -11551.0000 0.2316 -14631.0000 0.2895 -17622.0000 0.3474 -21975.0000 0.4053 -26882.0000 0.4632 -31775.0000 0.5211 -33323.0000 0.5790 -22262.0000 0.6370 1515.5000 0.6949 -9935.4004 0.7528 1211.8000 0.8107 1405.7000 0.8686 13106.0000 0.9265 16245.0000 0.9844 25417.0000 1.0423 41034.0000 1.1002 58041.0000 1.1581 69767.0000 Case ID: P5 rsdl_70FAxial --- Stress Distribution Depth Stress 0.0000 5531.2998 0.0523 3583.8999 0.1046 -1635.9000 File No.: 0900530.308 Page A-9 of A-20 Revision: 0 F0306-01 RO

StructuralIntegrityAssociates, Inc.

0.1569 -5833.7002 0.2092 -13755.0000 0.2615 -21502.0000 0.3138 -31547.0000 0.3661 -35499.0000 0.4184 -43808.0000 0.4707 -43321.0000 0.5230 -29471.0000 0.5753 -12445.0000 0.6276 -7875.0000 0.6799 14412.0000 0.7322 14364.0000 0.7845 7326.5000 0.8368 15584.0000 0.8891 26384.0000 0.9414 36435.0000 0.9937 53063.0000 1.0460 66263.0000 Case ID: P6_rsdl_70FAxial --- Stress Distribution Depth Stress 0.0000 15237.0000 0.0578 13824.0000 0.1156 9049.5996 0.1734 3724.6001 0.2311 -1101.8000 0.2889 -6785.2002 0.3467 -14316.0000 0.4045 -20867.0000 0.4623 -22738.0000 0.5201 -17319.0000 0.5778 -16816.0000 0.6356 -15223.0000 0.6934 -24384.0000 0.7512 -18228.0000 0.8090 7268.0000 0.8668 -291.4900 0.9245 6025.0000 0.9823 9106.2998 1.0401 3584.8000 1.0979 8781.2998 1.1557 21056.0000 File No.: 0900530.308 Page A-10 of A'20 Revision: 0 F0306-01 RO

StructuralIntegrityAssociates, Inc.

Case ID: P1 rsdl_550FAxial --- Stress Distribution Depth Stress 0.0000 -37423.0000 0.0563 -30666.0000 0.1127 -30371.0000 0.1690 -29966.0000 0.2254 -30253.0000 0.2817 -39782.0000 0.3380 -49528.0000 0.3944 -40497.0000 0.4507 -31440.0000 0.5070 -26593.0000 0.5634 -7998.7002 0.6197 5466.5000 0.6761 8603.5996 0.7324 17911.0000 0.7887 16327.0000 0.8451 15865.0000 0.9014 20738.0000 0.9577 34114.0000 1.0141 43571.0000 1.0704 61619.0000 1.1268 70638.0000 Case ID: P2_rsdl_550FAxial --- Stress Distribution Depth Stress 0.0000 -28342.0000 0.0523 -33121.0000 0.1046 -35067.0000 0.1569 -34809.0000 0.2092 -33286.0000 0.2615 -34479.0000 0.3138 -37713.0000 0.3661 -37277.0000 0.4184 -31583.0000 0.4707 -18984.0000 0.5230 -3771.5000 0.5753 16109.0000 0.6276 14282.0000 0.6799 8925.0996 0.7322 5161.7998 File No.: 0900530.308 Page A-1I1 of A-20 Revision: 0 F0306-01 RO

Structural IntegrityAssociates, Inc.

0.7845 24625.0000 0.8368 28148.0000 0.8891 30056.0000 0.9414 40041.0000 0.9938 57475.0000 1.0460 69873.0000 Case ID: P3_rsdl_550FAxial -- Stress Distribution Depth Stress 0.0000 -34046.0000 0.0547 -34208.0000 0.1093 -33623.0000 0.1640 -32502.0000 0.2187 -31245.0000 0.2733 -30681.0000 0.3280 -32849.0000 0.3826 -36206.0000 0.4373 -36877.0000 0.4920 -32049.0000 0.5466 -22250.0000 0.6013 -3054.5000 0.6559 10338.0000 0.7106 26693.0000 0.7653 18601.0000 0.8199 22315.0000 0.8746 20287.0000 0.9292 34714.0000 0.9839 41014.0000 1.0386 56687.0000 1.0932 66000.0000 Case ID: P4_rsdl_550FAxial --- Stress Distribution Depth Stress 0.0000 -17246.0000 0.0579 -18986.0000 0.1158 -20712.0000 0.1737 -22641.0000 0.2316 -24508.0000 0.2895 -26478.0000 0.3474 -29810.0000 0.4053 -33677.0000 File No.: 0900530.308 Page A-12 of A-20 Revision: 0 F0306-01 RO

StructuralIntegrity Associates, Inc.

0.4632 -37487.0000 0.5211 -38129.0000 0.5790 -27106.0000 0.6370 -2506.3999 0.6949 8712.0000 0.7528 18573.0000 0.8107 16621.0000 0.8686 25919.0000 0.9265 27604.0000 0.9844 34020.0000 1.0423 39826.0000 1.1002 55151.0000 1.1581 66000.0000 Case ID: P5_rsdl_550FAxial --- Stress Distribution Depth Stress 0.0000 -9860.5996 0.0523 -12023.0000 0.1046 -13281.0000 0.1569 -12536.0000 0.2092 -15937.0000 0.2615 -20404.0000 0.3138 -27645.0000 0.3661 -29658.0000 0.4184 -36181.0000 0.4707 -34869.0000 0.5230 -21384.0000 0.5753 -5155.2998 0.6276 -680.5100 0.6799 20099.0000 0.7322 19979.0000 0.7845 13215.0000 0.8368 20522.0000 0.8891 28901.0000 0.9414 29654.0000 0.9937 44123.0000 1.0460 55627.0000 Case ID: P6_rsdl_550FAxial --- Stress Distribution Depth Stress 0,0000 -4153.3999 File No.: 0900530.308 Page A-13 of A-20 Revision: 0 F0306-O1 RO

StructuralIntegrity Associates, Inc.

0.0578 -3844.7000 0.1156 -5437.7002 0.1734 -7985.3999 0.2311 -10562.0000 0.2889 -14188.0000 0.3467 -19675.0000 0.4045 -24334.0000 0.4623 -24692.0000 0.5201 -18159.0000 0.5778 -15576.0000 0.6356 -7235.2998 0.6934 -8139.7998 0.7512 -4439.8999 0.8090 17203.0000 0.8668 8686.5996 0.9245 13425.0000 0.9823 15405.0000 1.0401 9661.2002 1.0979 14122.0000 1.1557 25381.0000 Stress Coefficients Case ID CO Cl C2 C3 Type Primary Axial S 3108 0 0 0 Coeff P1 rsdl 70F Axi 3885.37 -340174 671398 -282654 StressDist P2 rsdl 70F Axi -13893.9 -170320 375369 -129810 StressDist P3 rsdl 70F Axi -25590 -6482.04 -2191.35 80004.7 StressDist P4 rsdl 70F Axi 899.913 -114302 127279 19565.5 StressDist P5 rsdl 70F Axi 15914.8 -269042 441695 -134813 StressDist P6 rsdl 70F Axi 22229.9 -168601 206743 -54358.7 StressDist PI rsdl 550F Ax -30101.6 -84939.3 247674 -86072.5 StressDist P2 rsdl 550F Ax -29975.6 -79766.8 278772 -113600 StressDist P3 rsdl 550F Ax -29271.3 -93075.8 280055 -108485 StressDist P4 rsdl 550F Ax -9900.14 -166413 342253 -124837 StressDist P5 rsdl 550F Ax -2123.08 -180397 374942 -146624 StressDist P6_rsdl_550FAx 3166.73 -139838 258349 -106937 StressDist Through Wall Stresses for Load Cases With Stress Coeff-------

Wall Case Depth Primary Ax File No.: 0900530.308 Page A-14 of A-20 Revision: 0 F0306-01 RO

U StructuralIntegrity Associates, Inc.

0.0000 3108 0.0780 3108 0.1560 3108 0.2340 3108 0.3120 3108 0.3900 3108 0.4680 3108 0.5460 3108 0.6240 3108 0.7020 3108 0.7800 3108 Crack Model: Circumferential Crack in Cylinder (t/R=0.2)

Crack Parameters:

Wall thickness: 1.0400 Max. crack size: 0.7800 Intensity Factor --------------------

-Stress Crack Case Case Case Case Case Size Primary Ax P1_rsdl_70 P2_rsdl_70 P3_rsdl_70 P4_rsdl_70 0.0156 759.948 209.446 -3766.98 -6271.6 -31.4349 0.0312 1079.11 -704.379 -5846.04 -8926.02 -392.173 1326.99 -2038.64 -7766.64 -11001.3 -897.952 0.0468 0.0624 1538.47 -3655.95 -9636.32 -12782.6 -1509.53 0.0780 1726.99 -5481.91 -11485.1 -14379.1 -2205.36 0.0936 1899.41 -7467.14 -13322.3 -15846.1 -2970.97 0.1092 2063.43 -9588.18 -15174.2 -17246.3 -3800.85 0.1248 2226.33 -11841.3 -17074.4 -18639 -4696.58 0.1404 2383.05 -14184.5 -18975.5 -19980.7 -5643.35 0.1560 2534.8 -16598.8 -20873.1 -21280.3 -6635.49 0.1716 2682.48 -19067.9 -22762.6 -22543.8 -7667.98 0.1872 2826.79 -21577.6 -24639.5 -23775.7 -8736.28 0.2028 2968.26 -24115 -26499.1 -24979.2 -9836.24 0.2184 3120.22 -26705.5 -28419.3 -26263.6 -10981.5 0.2340 3277.7 -29328.5 -30363.8 -27586.3 -12164.1 0.2496 3434.73 -31957.1 -32288 -28896.1 -13372.8 0.2652 3591.5 -34581.7 -34187.2 -30192.8 -14604.1 0.2808 3748.17 -37193.4 -36056.3 -31476.2 -15854.9 0.2964 3904.87 -39783.7 -37890.8 -32745.4 -17122 0.3120 4061.69 -42344.3 -39685.9 -33999.7 -18402.1 0.3276 4232.94 -44920.7 -41525.5 -35354 -19728.2 File No.: 0900530.308 Page A-15 of A-20 Revision: 0 F0306-01 RO

C Structural Integrity Associates, Inc.

0.3432 4405.17 -47449.1 -43315.8 -36695.4 -21063.4 0.3588 4578.42 -49920.4 -45051.1 -38021.9 -22404.

0.3744 4752.73 -52326.1 -46725.7 -39331.4 -23746.5 0.3900 4928.14 -54657.4 -48334 -40621.8 -25087.2 0.4056 5104.67 -56906.2 -49870.3 -41890.8 -26422.4 0.4212 5285.93 -59180.2 -51404.8 -43162.9 -27781.5 0.4368 5475.77 -61619.1 -53024.5 -44462.8 -29201.2 0.4524 5667.18 -64001.3 -54582.1 -45733.4 -30615.1 0.4680 5860.16 -66322.2 -56073.6 -46971.3 -32019.4 0.4836 6054.71 -68577.3 -57494.9 -48172.8 -33410.5 0.4992 6250.85 -70762.6 -58842.5 -49334.2 -34784.5 0.5148 6448.55 -72874.3 -60112.3 -50451.7 -36137.5 0.5304 6663.88 -74819.8 -61316.8 -51660.1 -37491.2 0.5460 6889.39 -76604 -62425.2 -52891.6 -38826.7 0.5616 7117.16 -78257.4 -63420.1 -54073.4 -40125.8 0.5772 7347.17 -79773 -64295.6 -55200.8 -41383.6 0.5928 7579.4 -81143.7 -65045.8 -56269.3 -42595.1 0.6084 7813.83 -82362.8 -65664.9 -57273.9 -43755.2 0.6240 8050.45 -83424 -66147.2 -58209.7 -44858.7 0.6396 8309.06 -84434.6 -66605.4 -59210.2 -45972.3 0.6552 8570.31 -85268.6 -66909.8 -60129.8 -47017.6 0.6708 8834.16 -85919.4 -67054 -60962.4 -47988.4 0.6864 9100.59 -86380.4 -67031.8 -61701.7 -48878.3 0.7020 9369.59 -86645.4 -66837.1 -62341.5 -49681.1 0.7176 9641.12 -86708.5 -66463.8 -62874.9 -50390.1 0.7332 9924.6 -86848.7 -66085.6 -63359.9 -51086.5 0.7488 10229.8 -87383.4 -65894.9 -63852.4 -51859.8 0.7644 10538.1 -87759.2 -65536.5 -64214 -52531.5 0.7800 10849.5 -87973.1 -65005.5 -64436.6 -53094.3 Intensity Factor --------------------

-Stress Crack Case Case Case Case Case Size P5 rsdl_70 P6_rsdl_70 P1_rsdl_55 P2 rsdl_55 P3_rsdl_55 0.0156 3303.26 5065.06 -7543 -7499.82 -7357.26 0.0312 3888.26 6681.52 -10951.8 -10870.6 -10710.2 0.0468 3834.23 7606.67 -13741.8 -13614.8 -13469.1 0.0624 3391.63 8132.88 -16224.6 -16042.9 -15933.5 0.0780 2673.18 8382.15 -18513.9 -18268.1 -18212.1 0.0936 1745.01 8421.62 -20664.5 -20344.8 -20356.3 0.1092 656.096 8310.76 -22745.3 -22341.1 -22432.5 0.1248 -562.451 8095.83 -24825.7 -24325.1 -24508.1 0.1404 -1898.45 7763.81 -26843.6 -26235.3 -26520.9 0.1560 -3332.65 7330.44 -28804.9 -28077.3 -28476 File No.: 0900530.308 Page A-16 of A-20 Revision: 0 F0306-01 RO

V StructuralIntegrityAssociates, Inc.

0.1716 -4848.98 6808.33 -30713 -29854.6 -30376.1 0.1872 -6433.68 6207.88 -32569.9 -31568.8 -32222.7 0.2028 -8074.7 5537.9 -34376.6 -33220.7 -34016.1 0.2184 -9740.51 4867.13 -36268 -34942.5 -35888.1 0.2340 -11435.2 4172.78 -38188.3 -36678.7 -37783.7 0.2496 -13161.1 3429.94 -40070.8 -38363.8 -39637.1 0.2652 -14910.1 2643.51 -41913.6 -39995.6 -41446.1 0.2808 -16674.4 1817.96 -43714.5 -41571.9 -43208.1 0.2964 -18447 957.448 -45471.3 -43090.4 -44920.6 0.3120 -20220.8 65.8688 -47181.5 -44548.5 -46581.1 0.3276 -21988.4 -811.731 -48979.3 -46070.7 -48318.5 0.3432 -23742.1 -1712.82 -50727 -47527.3 -49999.1 0.3588 -25474.6 -2633.71 -52421.1 -48914.6 -51619.1 0.3744 -27178.7 -3570.85 -54058 -50228.7 -53174.7 0.3900 -28847.2 -4520.73 -55633.8 -51466 -54661.9 0.4056 -30473.2 -5479.93 -57145.1 -52622.8 -56077 0.4212 -32121.9 -6474.51 -58653.6 -53760.8 -57484.5 0.4368 -33879.6 -7541.95 -60232.3 -54952.9 -58961 0.4524 -35607.6 -8626.6 -61752.5 -56071.5 -60373.1 0.4680 -37300.9 -9726.13 -63211.3 -57113.8 -61717.7 0.4836 -38954.7 -10838.3 -64605.8 -58077.4 -62992.4 0.4992 -40564.2 -11960.8 -65933.4 -58959.6 -64194.3 0.5148 -42124.9 -13091.5 -67191.3 -59758.3 -65321.1 0.5304 -43544 -14147.8 -68471.4 -60543.7 -66450.1 0.5460 -44839.1 -15158.9 -69712.6 -61262.2 -67524.9 0.5616 -46043.3 -16160 -70861 -61870.7 -68498.8 0.5772 -47149.4 -17148.1 -71912.4 -62365 -69367.5 0.5928 -48150.6 -18119.8 -72862.5 -62741.3 -70126.8 0.6084 -49039.9 -19072.1 -73706.9 -62995.5 -70772.6 0.6240 -49810.4 -20001.7 -74441.6 -63123.9 -71300.8 0.6396 -50499.2 -20901.4 -75226.8 -63263.2 -71863.1 0.6552 -51051 -21772.4 -75889.9 -63263.5 -72295.2 0.6708 -51458.2 -22611 -76426.2 -63120.6 -72592.7 0.6864 -51713.2 -23413.7 -76831.3 -62830.4 -72751.3 0.7020 -51808.6 -24177.1 -77100.4 -62389 -72766.6 0.7176 -51736.9 -24897.6 -77229.3 -61792.5 -72634.7 0.7332 -51672.6 -25655 -77366.4 -61185.1 -72509.6 0.7488 -51815.7 -26544.4 -77671.7 -60722.2 -72558.2 0.7644 -51809.1 -27403.7 -77840.9 -60110.8 -72467 0.7800 -51646.4 -28229.7 -77870 -59348.2 -72232.7

---

Stress Intensity Factor --------------------

Crack Case Case Case Size P4 rsdl_55 P5 rsdl_55 P6_rsdl_55 File No.: 0900530.308 Page A-17 of A-20 Revision: 0 F0306-01 RO

V StructuralIntegrity Associates, Inc.

0.0156 -2782.63 -911.342 469.397 0.0312 .- 4439.7 -1823.15 252.718 0.0468 -6029.73 -2859.24 -175.233 0.0624 -7617.33 -3993.04 -740.887 0.0780 -9216.66 -5202.64 -1407.27 0.0936 -10829.2 -6470.62 -2150.95 0.1092 -12472.1 -7794.35 -2958.77 0.1248 -14170.6 -9180.99 -3826.01

0. 1404 -15884.5 -10601.1 -4738.06 0.1560 -17608.7 -12045.7 -5686.81 0.1716 -19338.1 -13507.1 -6665.33 0.1872 -21067.9 -14978.1 -7667.6 0.2028 -22793.3 -16452.3 -8688.31 0.2184 -24576.3 -17959.8 -9731.99 0.2340 -26387.4 -19482.6 -10792.8 0.2496 -28190.5 -20998.3 -11862.7 0.2652 -29981 -22501.5 -12937.8 0.2808 -31754.4 -23987.2 -14014.6 0.2964 -33506.6 -25450.6 -15089.6 0.3120 -35233.4 -26886.9 -16159.7 0.3276 -37006.1 -28334.2 -17240.2 0.3432 -38745.2 -29743.5 -18308.9 0.3588 -40445.5 -31109.7 -19362.4 0.3744 -42102.2 -32427.4 -20397.3 0.3900 -43710.3 -33691.4 -21410.2 0.4056 -45265 -34896.9 -22398 0.4212 -46831.2 -36104.9 -23402.9 0.4368 -48489.7 -37393.7 -24479.8 0.4524 -50105.9 -38635.9 -25542.1 0.4680 -51676.3 -39828.4 -26588 0.4836 -53197.9 -40968.2 -27615.8 0.4992 -54667.6 -42052.2 -28624.1 0.5148 -56082.4 -43077.8 -29611.2 0.5304 -57449.2 -44006.3 -30540.8 0.5460 -58743.5 -44832.8 -31415.7 0.5616 -59952.3 -45566.7 -32248.2 0.5772 -61070.6 -46203.2 -33035.4 0.5928 -62093.6 -46737.6 -33774.9 0.6084 -63016.7 -47165.3 -34463.9 0.6240 -63835.1 -47481.9 -35100.1 0.6396 -64656.8 -47752.1 -35728.7 0.6552 -65361 -47897.6 -36297.9 0.6708 -65942.5 -47913.6 -36805.2 0.6864 -66396.4 -47795.6 -37248.1 File No.: 0900530.308 Page A-18 of A-20 Revision: 0 F0306-01 RD

Structural IntegrityAssociates, Inc.

0.7020 -66717.8 -47538.8 -37624.2 0.7176 -66901.8 -47139.1 -37931.2

'0.7332 -67112.6 -46750.9 -38280.3 0.7488 -67533 -46549 -38798.6 0.7644 -67830.9 -46222 -39265.5 0.7800 -68002.4 -45767 -39679.8 Crack Growth Laws:

Law ID: Overlay Type: Corrosion Model: Paris da/dN - c * (dK)An where dK = Kmax - Kmin dK > Kthres Kmax < KIc Material parameters:

c = 1.6000e-008 n = 2.5000 Kthres 0.0000 Material Fracture Toughness KIc:

Material ID: Weld Overlay Depth Kic 0.2500 200.0000 1.0000 200.0000 2.0000 200.0000 Initial crack size= 0.6400 Max. crack size= 0.7800 Number of blocks= I Print increment of block= I Cycles Calc. Print Crk. Grw. Mat.

Subblock /Time incre. incre. Law KIc File No.: 0900530.308 Page A-19 of A-20 Revision: 0 F0306-01 RO

V StructuralIntegrity Associates, Inc.

Overlay 100000 10000 10000 Overlay Weld Overlay Kmax Kmin Subblock Case ID Scale Factor Case ID Scale Factor Overlay Primary Axial Stress 0.0010 Plrsdl_550FAxial 0.0010 P2_rsdl_550FAxial 0.0010 P3_rsdl_5501FAxial 0.0010 P4_rsdl_550FAxial 0.0010 P5 rsdl_550FAxial 0.0010 P6_rsdl_550FAxial 0.0010 Crack growth results:

Total Subblock Cycles Cycles DaDn

/Time /Time Kmax Kmin DeltaK R /DaDt Da a a/thk Block: 1 10000 10000 -3.50e+002 0.00e+000 -3.50e+002 0.00 0.00e+000 0.00e+000 0.64 0.62 20000 20000 -3.50e+002 0.00e+000 -3.50e+002 0.00 0.00e+000 0.00e+000 0.64 0.62 30000 30000 -3.50e+002 0.00e+000 -3.50e+002 0.00 0.00e+000 0.00e+000 0.64 0.62 40000 40000 -3.50e+002 0.00e+000 -3.50e+002 0.00 0.00e+000 0.00e+000 0.64 0.62 50000 50000 -3.50e+002 0.00e+000 -3.50e+002 0.00 0.00e+000 0.00e+000 0.64 0.62 60000 60000 -3.50e+002 0.00e+000 -3.50e+002 0.00 0.00e+000 0.00e+000 0.64 0.62 70000 70000 -3.50e+002 0.00e+000 -3.50e+002 0.00 0.00e+000 0.00e+000 0.64 0.62 80000 80000 -3.50e+002 0.00e+000 -3.50e+002 0.00 0.00e+000 0.00e+000 0.64 0.62 90000 90000 -3.50e+002 0.00e+000 -3.50e+002 0.00 0.00e+000 0.00e+000 0.64 0.62 100000 100000 -3.50e+002 0.00e+000 -3.50e+002 0.00 0.00e+000 0.00e+000 0.64 0.62 End of pc-CRACK Output File No.: 0900530.308 Page A-20 of A-20 Revision: 0 F0306-01RO

StructuralIntegrity Associates, Inc.

APPENDIX B FCG CASE PC-CRACK OUTPUT FILES File No.: 0900530.308 Page B- I of B-21 Revision: 0 F0306-01 RO

Structural IntegrityAssociates, Inc.

FCG Case without Residual Stresses Considered tm pc-CRACK for Windows Version 3.1-98348 (C) Copyright '84 -'98 Structural Integrity Associates, Inc.

3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice: 408-978-8200 Fax: 408-978-8964 E-mail: pccrack@structint.com Linear Elastic Fracture Mechanics Date: Thu Jul 23 09:32:54 2009 InputData and Results File: JPINFCG.LFM

Title:

Pilgrim N9A JPIN FCG Analysis without Residual Stresses Load Cases:

Stress Coefficients Case ID CO CI C2 C3 Type Primary Axial S 3108 0 0 0 Coeff Through

---

Wall Stresses for Load Cases With Stress Coeff-------

Wall Case Depth Primary Ax 0.0000 3108 0.0780 3108 0.1560 3108 0.2340 3108 0.3120 3108 0.3900 3108 0.4680 3108 0.5460 3108 0.6240 3108 File No.: 0900530.308 Page B-2 of B-21 Revision: 0 F0306-01 RO

V StructuralIntegrity Associates, Inc.

0.7020 3108 0.7800 3108 Crack Model: Circumferential Crack in Cylinder (t/R=0.2)

Crack Parameters:

Wall thickness: 1.0400 Max. crack size: 0.7800

- Stress Intensity Factor--------------------

Crack Case Size Primary Ax 0.0156 759.948 0.0312 1079.11 0.0468 1326.99 0.0624 1538.47 0.0780 1726.99 0.0936 1899.41 0.1092 2063.43 0.1248 2226.33 0.1404 2383.05 0.1560 2534.8 0.1716 2682.48 0.1872 2826.79 0.2028 2968.26 0.2184 3120.22 0.2340 3277.7 0.2496 3434.73 0.2652 3591.5 0.2808 3748.17 0.2964 3904.87 0.3120 4061.69 0.3276 4232.94 0.3432 4405.17 0.3588 4578.42 0.3744 4752.73 0.3900 4928.14 0.4056 5104.67 0.4212 5285.93 0.4368 5475.77 0.4524 5667.18 0.4680 5860.16 File No.: 0900530.308 Page B-3 ofB-21 Revision: 0 F0306-01 RO

V StructuralIntegrity Associates, Inc.

0.4836 6054.71 0.4992 6250.85 0.5148 6448.55 0.5304 6663.88 0.5460 6889.39 0.5616 7117.16 0.5772 7347.17 0.5928 7579.4 0.6084 7813.83 0.6240 8050.45 0.6396 8309.06 0.6552 8570.31 0.6708 8834.16 0.6864 9100.59 0.7020 9369.59 0.7176 9641.12 0.7332 9924.6 0.7488 10229.8 0.7644 10538.1 0.7800 10849.5 Crack Growth Laws:

Law ID: Overlay Model: ASME Section XI - austenitic stainless steel in air environment da/dN - C

• 10/F

• S

• dKA3.3 where S= 1.0 for R < 0

=1.0+1.8*R for 0 < R < 0.79

-43.5 + 57.97

• R for 0.79 < R < I F.= code specified function of temperature dK Kmax -Kmin R = Kmin / Kmax where:

C

• 10AF= 1.8403e-010 is for the currently selected units of:

force: kip length: inch temperature: 550.0000 Fahrenheit File No.: 0900530.308 Page B-4 of B-21 Revision: 0 F0306-01 RO

StructuralIntegrity Associates, Inc.

Material Fracture Toughness KIc:

Material ID: Overlay Depth KIc 0.2500 200.0000 1.0000 200.0000 2.0000 200.0000 Initial crack size= 0.6400 Max. crack size= 0.7800 Number of blocks= I Print increment of block= I Cycles Caic. Print Crk. Grw. Mat.

Subblock /Time incre. incre. Law Klc Overlay 800 20 20 Overlay Overlay Kmax. Kmin Subblock Case ID Scale Factor Case ID Scale Factor Overlay Primary Axial Stress 0.0010 Crack growth results:

Total Subblock Cycles Cycles DaDn

/Time /Time Kmax Kmin DeltaK R /DaDt Da a a/thk Block:

20 I 20 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.64 0.62 40 10 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.64 0.62 60 50 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.64 0.62 80 80 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.64 0.62 100 100 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.64 0.62 120 120 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.64 0.62 140 140 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.64 0.62 160 160 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.64 0.62 File No.: 0900530.308 Page B-5 of B-21 Revision: 0 F0306-01 RO

StructuralIntegrity Associates, Inc.

180 180 8.32e+000 0.00e+000 8.32e+000 0.00-2.00e-007 4.00e-006 0.64 0.62 200 200 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.64 0.62 220 220 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.64 0.62 240 240 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.64 0.62 260 260 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 280 280 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 300 300 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 320 320 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 340 340 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 360 360 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 380 380 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 400 400 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 420 420 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 440 440 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 460 460 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 480 480 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 500 500 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 520 520 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 540 540 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 560 560 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 580 580 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 600 600 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 620 620 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 640 640 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 660 660 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 680 680 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 700 700 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 720 720 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 740 740 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6401 0.62 760 760 8.32e+000 0.00e+000 8.32e-+000 0.00 2.00e-007 4.00e-006 0.6402 0.62 780 780 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6402 0.62 800 800 8.32e+000 0.00e+000 8.32e+000 0.00 2.00e-007 4.00e-006 0.6402 0.62 End of pc-CRACK File No.: 0900530.308 Page B-6 of B-21 Revision: 0 F0306-OiRO

StructuralIntegrity Associates, Inc.

FCG Case with Residual Stresses Considered tm pc-CRACK for Windows Version 3.1-98348 (C) Copyright '84 -'98 Structural Integrity Associates, Inc.

3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice: 408-978-8200 Fax: 408-978-8964 E-mail: pccrack@structint.com Linear Elastic Fracture Mechanics Date: Thu Jul 23 09:40:18 2009 Input Data and Results File: JP1NFCGR.LFM

Title:

Pilgrim N9A JPIN FCG Analysis with Residual Stresses Load Cases:

Case ID: P1_rsdl_70FAxial --- Stress Distribution Depth Stress 0.0000 -2706.0000 0.0563 -13254.0000 0.1127 -19160.0000 0.1690 -23077.0000 0.2254 -31868.0000 0.28 17 -51968.0000 0.3380 -63785.0000 0.3944 -54357.0000 0.4507 -44784.0000 0.5070 -39731.0000 0.5634 -19705.0000 0.6197 -4105.7002 0.6761 8184.1001 0.7324 19524.0000 0.7887 17780.0000 0.8451 17251.0000 0.9014 22486.0000 File No.: 0900530.308 Page B-7 of B-21 Revision: 0 F0306-01 RO

StructuralIntegrity Associates, Inc.

0.9577 36904.0000 1.0141 47132.0000 1.0704 66681.0000 1.1268 76587.0000 Case ID: P2_rsdl_70FAxial --- Stress Distribution Depth Stress 0.0000 -15358.0000 0.0523 -19223.0000 0.1046 -25101.0000 0.1569 -29725.0000 0.2092 -32260.0000 0.2615 -36466.0000 0.3138 -42170.0000 0.3661 -43463.0000 0.4184 -38617.0000 0.4707 -25977.0000 0.5230 -10235.0000 0.5753 10778.0000 0.62ý76 8643.0996 0.6799 2881.7000 0.7322 -1006.4000 0.7845 20303.0000 0.8368 24785.0000 0.8891 32769.0000 0.9414 44502.0000 0.9938 63483.0000 1.0460 76944.0000 Case ID: P3_rsdl_70FAxial --- Stress Distribution Depth Stress 0.0000 -28088.0000 0.0547 -25470.0000 0.1093 -24553.0000 0.1640 -23860.0000 0.2187 -23108.0000 0.2733 -23068.0000 0.3280 -25974.0000 0.3826 -30169.0000 0.4373 -31442.0000 0.4920 -26786.0000 File No.: 0900530.308 Page B-8 of B-21 Revision: 0 F0306-01 RO

V StructuralIntegrity Associates, Inc.

0.5466 -16923.0000 0.6013 876.7800 0.6559 -7463.1001 0.7106 10757.0000 0.7653 4197.2998 0.8199 9730.2002 0.8746 8700.4004 0.9292 26349.0000 0.9839 42410.0000 1.0386 59758.0000 1.0932 69767.0000 Case ID: P4_rsdl_70FAxial --- Stress Distribution Depth Stress 0.0000 -3281.0000 0U0579 -5048.2002 0,1158 -8148.1001 0.1737 -11551.0000 0,2316 -14631.0000 0U2895 -17622.0000 0,3474 -21975.0000 0,4053 -26882.0000 0,4632 -31775.0000 0.5211 -33323.0000 0.5790 -22262.0000 0.6370 1515.5000 0,6949 -9935.4004 0.7528 1211.8000 0.8107 1405.7000 0.8686 13106.0000 0.9265 16245.0000 0.9844 25417.0000 1.0423 41034.0000 1.1002 58041.0000 1.1581 69767.0000 Case ID: P5 rsdl_70FAxial --- Stress Distribution Depth Stress 0.0000 5531.2998 0.0523 3583.8999 0.1046 -1635.9000 File No.: 0900530.308 Page B-9 of B-21 Revision: 0 F0306-01 RO

StructuralIntegrity Associates, Inc.

0.1569 -5833.7002 0.2092 -13755.0000 0.2615 -21502.0000 0.3138 -31547.0000 0.3661 -35499.0000 0.4184 -43808.0000 0.4707 -43321.0000 0.5230 -29471.0000 0.5753 -12445.0000 0.6276 -7875.0000 0.6799 14412.0000 0.7322 14364.0000 0.7845 7326.5000 0.8368 15584.0000 0.8891 26384.0000 0.9414 36435.0000 0.9937 53063.0000 1.0460 66263.0000 Case ID: P6_rsdl_70FAxial --- Stress Distribution Depth Stress 0.0000 15237.0000 0.0578 13824.0000 0.1156 9049.5996 0.1734 3724.6001 0.2311 -1101.8000 0.2889 -6785.2002 0.3467 -14316.0000 0.4045 -20867.0000 0.4623 -22738.0000 0.5201 -17319.0000 0.5778 -16816.0000 0.6356 -15223.0000 0.6934 -24384.0000 0.7512 -18228.0000 0.8090 7268.0000 0.8668 -291.4900 0.9245 6025.0000 0.9823 9106.2998 1.0401 3584.8000 1.0979 8781.2998 1.1557 21056.0000 File No.: 0900530.308 Page B-10 of B-21 Revision: 0 F0306-01 RO

StructuralIntegrity Associates, Inc.

Case ID: Plrsdl_550FAxial --- Stress Distribution Depth Stress 0.0000 -37423.0000 0.0563 -30666.0000 0.1127 -30371.0000 0.1690 -29966.0000 0.2254 -30253.0000 0.2817 -39782.0000 0.3380 -49528.0000 0.3944 -40497.0000 0.4507 -31440.0000 0.5070 -26593.0000 0.5634 -7998.7002 0.6197 5466.5000 0.6761 8603.5996 0.7324 17911.0000 0.7887 16327.0000 0.8451 15865.0000 0.9014 20738.0000 0.9577 34114.0000 1.0141 43571.0000 1.0704 61619.0000 1.1268 70638.0000 Case ID: P2_rsdl_550FAxial --- Stress Distribution Depth Stress 0.0000 -28342.0000 0.0523 -33121.0000 0.1046 -35067.0000 0.1569 -34809.0000 0.2092 -33286.0000 0.2615 -34479.0000 0.3138 -37713.0000 0.3661 -37277.0000 0.4184 -31583.0000 0.4707 -18984.0000 0.5230 -3771.5000 0.5753 16109.0000 0.6276 14282.0000 0.6799 8925.0996 0.7322 5161.7998 File No.: 0900530.308 Page B-11 of B-21 Revision: 0 F0306-01 RO

StructuralIntegrity Associates, Inc.

0.7845 24625.0000 0.8368 28148.0000 0.8891 30056.0000 0.9414 40041.0000 0.9938 57475.0000 1.0460 69873.0000 Case ID: P3_rsdl_550FAxial --- Stress Distribution Depth Stress 0.0000 -34046.0000 0.0547 -34208.0000 0.1093 -33623.0000 0.1640 -32502.0000 0.2187 -31245.0000 0.2733 -30681.0000 0.3280 -32849.0000 0.3826 -36206.0000 0.4373 -36877.0000 0.4920 -32049.0000 0.5466 -22250.0000 0.6013 -3054.5000 0.6559 10338.0000 0.7106 26693.0000 0.7653 18601.0000 0.8199 22315.0000 0.8746 20287.0000 0.9292 34714.0000 0.9839 41014.0000 1.0386 56687.0000 1.0932 66000.0000 Case ID: P4_rsdl_550FAxial --- Stress Distribution Depth Stress 0.0000 -17246.0000 0.0579 -18986.0000 0.1158 -20712.0000 0.1737 -22641.0000 0.2316 -24508.0000 0.2895 -26478.0000 0.3474 -29810.0000 0.4053 -33677.0000 File No.: 0900530.308 Page B-12 of B-21 Revision: 0 F0306-01 RO

Structural Integrity Associates, Inc.

0.4632 -37487.0000 0.5211 -38129.0000 0.5790 -27106.0000 0.6370 -2506.3999 0.6949 8712.0000 0.7528 18573.0000 0.8107 16621.0000 0.8686 25919.0000 0.9265 27604.0000 0.9844 34020.0000 1.0423 39826.0000 1.1002 55151.0000 1.1581 66000.0000 Case ID: P5_rsdi550FAxial --- Stress Distribution Depth Stress 0.0000 -9860.5996 0.0523 -12023.0000 0.1046 -13281.0000 0.1569 -12536.0000 0.2092 -15937.0000 0.2615 -20404.0000 0.3138 -27645.0000 0.3661 -29658.0000 0.4184 -36181.0000 0.4707 -34869.0000 0.5230 -21384.0000 0.5753 -5155.2998 0.6276 -680.5100 0.6799 20099.0000 0.7322 19979.0000 0.7845 13215.0000 0.8368 20522.0000 0.8891 28901.0000 0.9414 29654.0000 0.9937 44123.0000 1.0460 55627.0000 Case ID: P6_rsdl_55OFAxial --- Stress Distribution Depth Stress 0.0000 -4153.3999 File No.: 0900530.308 Page B-13 of B-21 Revision: 0 F0306-01 RO

V StructuralIntegrity Associates, Inc.

0.0578 -3844.7000 0.1156 -5437.7002 0.1734 -7985.3999 0.2311 -10562.0000 0.2889 -14188.0000 0.3467 -19675.0000 0.4045 -24334.0000 0.4623 -24692.0000 0.5201 -18159.0000 0.5778 -15576.0000 0.6356 -7235.2998 0.6934 -8139.7998 0.7512 -4439.8999 0.8090 17203.0000 0.8668 8686.5996 0.9245 13425.0000 0.9823 15405.0000 1.0401 9661.2002 1.0979 14122.0000 1.1557 25381.0000 Stress Coefficients Case ID CO Cl C2 C3 Type Primary Axial S 3108 0 0 0 Coeff PI rsdl 70F Axi 3885.37 -340174 671398 -282654 StressDist P2 rsdl 70F Axi -13893.9 -170320 375369 -129810 StressDist P3 rsdl 70F Axi -25590 -6482.04 -2191.35 80004.7 StressDist P4 rsdl 70F Axi 899.913 -114302 127279 19565.5 StressDist P5 rsdl 70F Axi 15914.8 -269042 441695 -134813 StressDist P6 rsdl 70F Axi 22229.9 -168601 206743 -54358.7 StressDist P1 rsdl 550F Ax -30101.6 -84939.3 247674 -86072.5 StressDist P2 rsdl 550F Ax -29975.6 -79766.8 278772 -113600 StressDist P3 rsdl 550F Ax -29271.3 -93075.8 280055 -108485 StressDist P4 rsdl 550F Ax -9900.14 -166413 342253 -124837 StressDist P5 rsdl 550F Ax -2123.08 -180397 374942 -146624 StressDist P6_rsdl_550FAx 3166.73 -139838 258349 -106937 StressDist Through Wall Stresses for Load Cases With Stress Coeff-------

Wall Case Depth Primary Ax File No.: 0900530.308 Page B-14 of B-21 Revision: 0 F0306-01 RO

StructuralIntegrity Associates, Inc.

0.0000 3108 0.0780 3108 0.1560 3108 0.2340 3108 0.3120 3108 0.3900 3108 0.4680 3108 0.5460 3108 0.6240 3108 0.7020 3108 0.7800 3108 Crack Model: Circumferential Crack in Cylinder (t/R=0.2)

Crack Parameters:

Wall thickness: 1.0400 Max. crack size: 0.7800

-Stress Intensity Factor --------------------

Crack Case Case Case Case Case Size Primary Ax Plrsdl_70 P2_rsdl_70 P3_rsdl_70 P4_rsdl_70 0.0156 759.948 209.446 -3766.98 -6271.6 -31.4349 0.0312 1079.11 -704.379 -5846.04 -8926.02 -392.173 0.0468 1326.99 -2038.64 -7766.64 -11001.3 -897.952 0.0624 1538.47 -3655.95 -9636.32 -12782.6 -1509.53 0.0780 1726.99 -5481.91 -11485.1 -14379.1 -2205.36 0.0936 1899.41 -7467.14 -13322.3 -15846.1 -2970.97 0.1092 2063.43 -9588.18 -15174.2 -17246.3 -3800.85 0.1248 2226.33 -11841.3 -17074.4 -18639 -4696.58 0.1404 2383.05 -14184.5 -18975.5 -19980.7 -5643.35 0.1560 2534.8 -16598.8 -20873.1 -21280.3 -6635.49 0.1716 2682.48 -19067.9 -22762.6 -22543.8 -7667.98 0.1872 2826.79 -21577.6 -24639.5 -23775.7 -8736.28 0.2028 2968.26 -24115 -26499.1 -24979.2 -9836.24 0.2184 3120.22 -26705.5 -28419.3 -26263.6 -10981.5 0.2340 3277.7 -29328.5 -30363.8 -27586.3 -12164.1 0.2496 3434.73 -31957.1 -32288 -28896.1 -13372.8 0.2652 3591.5 -34581.7 -34187.2 -30192.8 -14604.1 0.2808 3748 17 -37193.4 -36056.3 -31476.2 -15854.9 0.2964 3904.87 -39783.7 -37890.8 -32745.4 -17122 0.3120 4061.69 -42344.3 -39685.9 .33999.7 -18402.1 0.3276 4232.94 -44920.7 -41525.5 -35354 -19728.2 File No.: 0900530.308 Page B- 15 of B-21 Revision: 0 F0306-01 RO

V StructuralIntegrity Associates, Inc.

0.3432 4405.17 -47449.1 -43315.8 -36695.4 -21063.4 0.3588 4578.42 -49920.4 -45051.1 -38021.9 -22404 0.3744 4752.73 -52326.1. -46725.7 -39331.4 -23746.5 0.3900 4928.14 -54657.4 -48334 -40621.8 -25087.2 0.4056 5104.67 -56906.2 -49870.3 -41890.8 -26422.4 0.4212 5285.93 -59180.2 -51404.8 -43162.9 -27781.5 0.4368 5475.77 -61619.1 -53024.5 -44462.8 -29201.2 0.4524 5667.18 -64001.3 -54582.1 -45733.4 -30615.1 0.4680 5860.16 -66322.2 -56073.6 -46971.3 -32019.4 0.4836 6054.71 -68577.3 -57494.9 -48172.8 -33410.5 0.4992 6250.85 -70762.6 -58842.5 -49334.2 -34784.5 0.5148 6448.55 -72874.3 -60112.3 -50451.7 -36137.5 0.5304 6663.88 -74819.8 -61316.8 -51660.1 -37491.2 0.5460 6889.39 -76604 -62425.2 -52891.6 -38826.7 0.5616 7117.16 -78257.4 -63420.1 -54073.4 -40125.8 0.5772 7347.17 -79773 -64295.6 -55200.8 -41383.6 0.5928 7579.4 -81143.7 -65045.8 -56269.3 -42595.1 0.6084 7813.83 -82362.8 -65664.9 -57273.9 -43755.2 0.6240 8050.45 -83424 -66147.2 -58209.7 -44858.7 0.6396 8309.06 -84434.6 -66605.4 -59210.2 -45972.3 0.6552 8570.31 -85268.6 -66909.8 -60129.8 -47017.6 0.6708 8834.16 -85919.4 -67054 -60962.4 -47988.4 0.6864 9100.59 -86380.4 -67031.8 -61701.7 -48878.3 0.7020 9369.59 -86645.4 -66837.1 -62341.5 -49681.1 0.7176 9641.12 -86708.5 -66463.8 -62874.9 -50390.1 0.7332 9924.6 -86848.7 -66085.6 -63359.9 -51086.5 0.7488 10229.8 -87383.4 -65894.9 -63852.4 -51859.8 0.7644 10538.1 -87759.2 -65536.5 -64214 -52531.5 0.7800 10849.5 -87973.1 -65005.5 -64436.6 -53094.3

---

Stress Intensity Factor ------------

Crack Case Case Case Case Case Size P5 rsdl_70 P6_rsdl_70 P1_rsdl_55 P2_rsdl_55 P3_rsdl_55 0.0156 3303.26 5065.06 -7543 -7499.82 -7357.26 0.0312 3888.26 6681.52 -10951.8 -10870.6 -10710.2 0.0468 3834.23 7606.67 -13741.8 -13614.8 -13469.1 0.0624 3391.63 8132.88 -16224.6 -16042.9 -15933.5 0.0780 2673.18 8382.15 -18513.9 -18268.1 -18212.1 0.0936 1745.01 8421.62 -20664.5 -20344.8 -20356.3 0.1092 656.096 8310.76 -22745.3 -22341.1 -22432.5 0.1248 -562.451 8095.83 -24825.7 -24325.1 -24508.1 0.1404 -1898.45 7763.81 -26843.6 -26235.3 -26520.9 0.1560 -3332.65 7330.44 -28804.9 -28077.3 -28476 File No.: 0900530.308 Page B-16 of B-21 Revision: 0 F0306-01 R0

r StructuralIntegrity Associates, Inc.

0.1716 -4848.98 6808.33 -30713 -29854.6 -30376.1 0.1872 -6433.68 6207.88 -32569.9 -31568.8 -32222.7 0.2028 -8074.7 5537.9 -34376.6 -33220.7 -34016.1 0.2184 -9740.51 4867.13 -36268 -34942.5 -35888.1 0.2340 -11435.2 4172.78 -38188.3 -36678.7 -37783.7 0.2496 -13161.1 3429.94 -40070.8 -38363.8 -39637.1 0.2652 -14910.1 2643.51 -41913.6 -39995.6 -41446.1 0.2808 -16674.4 1817.96 .- 43714.5 -41571.9 -43208.1 0.2964 -18447 957.448 -45471.3 -43090.4 -44920.6 0.3120 -20220.8 65.8688 -47181.5 -44548.5 -46581.1 0.3276 -21988.4 -811.731 -48979.3 -46070.7 -48318.5 0.3432 -23742.1 -1712.82 -50727 -47527.3 -49999.1 0.3588 -25474.6 -2633.71 -52421.1 -48914.6 -51619.1 0.3744 -27178.7 -3570.85 -54058 -50228.7 -53174.7 0.3900 -28847.2 -4520.73 -55633.8 -51466 -54661.9 0.4056 -30473.2 -5479.93 -57145.1 -52622.8 -56077 0.4212 -32121.9, -6474.51 -58653.6 -53760.8 -57484.5 0.4368 -33879.6 -7541.95 -60232.3 -54952.9 -58961 0.4524 -35607.6 -8626.6 -61752.5 -56071.5 -60373.1 0.4680 -37300.9 -9726.13 -63211.3 -57113.8 -61717.7 0.4836 -38954.7 -10838.3 -64605.8 -58077.4 -62992.4 0.4992 -40564.2 -11960.8 -65933.4 -58959.6 -64194.3 0.5148 -42124.9 -13091.5 -67191.3 -59758.3 -65321.1 0.5304 -43544 -14147.8 -68471.4 -60543.7 -66450.1 0.5460 -44839.1 -15158.9 -69712.6 -61262.2 -67524.9 0.5616 -46043.3 -16i60 -70861 -61870.7 -68498.8 0.5772 -47149.4 -17148.1 -71912.4 -62365 -69367.5 0.5928 -48150.6 -18119.8 -72862.5 -62741.3 -70126.8 0.6084 -49039.9 -19072.1 -73706.9 -62995.5 -70772.6 0.6240 -49810.4 -20001.7 -74441.6 -63123.9 -71300.8 0.6396 -50499.2 -20901.4 -75226.8 -63263.2 -71863.1 0.6552 -51051 -21772.4 -75889.9 -63263.5 -72295.2 0.6708 -51458.2 -22611 -76426.2 -63120.6 -72592.7 0.6864 -51713.2 -23413.7 -76831.3 -62830.4 -72751.3 0.7020 -51808.6 -24177.1 -77100.4 -62389 -72766.6 0.7176 -51736.9 -24897.6 -77229.3 -61792.5 -72634.7 0.7332 -51672.6 -25655 -77366.4 -61185.1 -72509.6 0.7488 -51815.7 -26544.4 -77671.7 -60722.2 -72558.2 0.7644 -51809.1 -27403.7 -77840.9 -60110.8 -72467 0.7800 -51646.4 -28229.7 -77870 -59348.2 -72232.7

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Stress Intensity Factor ....

Crack Case Case Case Size P4_rsdl_55 P5_rsdl_55 P6_rsdl_55 File No.: 0900530.308 Page B-17 of B-21 Revision: 0 F0306-01 RO

V StructuralIntegrity Associates, Inc.

0.0156 -2782.63 -911.342 469.397 0.0312 -4439.7 -1823.15 252.718 0.0468 -6029.73 -2859.24 -175.233 0.0624 -7617.33 -3993.04 -740.887 0.0780 -9216.66 -5202.64 -1407.27 0.0936 -10829.2 -6470.62 -2150.95 0.1092 -12472.1 -7794.35 -2958.77 0.1248 -14170.6 -9180.99 -3826.01 0.1404 -15884.5 -10601.1 -4738.06 0.1560 -17608.7 -12045.7 -5686.81 0.1716 -19338.1 -13507.1 -6665.33 0.1872 -21067.9 -14978.1 -7667.6 0.2028 -22793.3 -16452.3 -8688.31 0.2184 -24576.3 -17959.8 -9731.99 0.2340 -26387.4 -19482.6 -10792.8 0.2496 -28190.5 -20998.3 -11862.7 0.2652 -29981 -22501.5 -12937.8 0.2808 -31754.4 -23987.2 -14014.6 0.2964 -33506.6 -25450.6 -15089.6 0.3120 -35233.4 -26886.9 -16159.7 0.3276 -37006.1 -28334.2 -17240.2 0.3432 -38745.2 -29743.5 -18308.9 0.3588 -40445.5 -31109.7 -19362.4 0.3744 -42102.2 -32427.4 -20397.3 0.3900 -43710.3 -33691.4 -21410.2 0.4056 -45265 -34896.9 -22398 0.4212 -46831.2 -36104.9 -23402.9 0.4368 -48489.7 -37393.7 -24479.8 0.4524 -50105.9 -38635.9 -25542.1 0.4680 -51676.3 -39828.4 -26588 0.4836 -53197.9 -40968.2 -27615.8 0.4992 -54667.6 -42052.2 -28624.1 0.5148 -56082.4 -43077.8 -29611.2 0.5304 -57449.2 -44006.3 -30540.8 0.5460 -58743.5 -44832.8 *31415.7 0.5616 -59952.3 -45566.7 -32248.2 0.5772 -61070.6 -46203.2 -33035.4 0.5928 -62093.6 -46737.6 -33774.9 0.6084 -63016.7 -47165.3 -34463.9 0.6240 -63835.1 -47481.9 -35100.1 0.6396 -64656.8 -47752.1 -35728.7 0.6552 -65361 -47897.6 -36297.9 0.6708 -65942.5 -47913.6 -36805.2 0.6864 -66396.4 -47795.6 -37248.1 File No.: 0900530.308 Page B-18 of B-21 Revision: 0 F0306-01 R0

V StructuralIntegrity Associates, Inc.

0.7020 -66717.8 -47538.8 -37624.2 0.7176 -66901.8 -47139.1 -37931.2 0.7332 -67112.6 -46750.9 -38280.3 0.7488 -67533 -46549 -38798.6 0.7644 -67830.9 -46222 -39265.5 0.7800 -68002.4 -45767 -39679.8 Crack Growth Laws:

Law ID: Overlay Model: ASME Section XI - austenitic stainless steel in air environment da/dN r C

• 10AF

• S

• dKA3.3 where S= 1.0 for R< 0

=1.0+l.8*R for 0 < R < 0.79

=-43.5+57.97* R for 0.79<R<I F code specified function of temperature dK = Kmax - Kmin R = Kmin / Kmax where:

C

• 10AF= 1.8403e-010 is for the currently selected units of:

force: kip length: inch temperature: 550.0000 Fahrenheit Material Fracture Toughness Kic:

Material ID: Overlay Depth Kic 0.2500 200.0000 1.0000 200.0000 2.0000 200.0000 Initial crack size= 0.6400 Max. crack size= 0.7800 File No.: 0900530.308 Page 13-19 of B-21 Revision: 0 F0306-01 RO

Structural Integrity Associates, Inc.

Number of blocks=

Print increment of block= 1 Cycles Calc. Print Crk. Grw. Mat.

Subblock /Time incre. incre. Law KIc Overlay 800 20 20 Overlay Overlay Kmax Kmin Subblock Case ID Scale Factor Case ID Scale Factor Overlay Primary Axial Stress 0.0010 PI rsdi 550F Axial 0.0010 P1_rsdl_70FAxial 0.0010 P2 rsdl 550F Axial 0.0010 P2 rsdl 70F Axial 0.0010 P3 rsdl 550F Axial 0.0010 P3 rsdl 70F Axial 0.0010 P4 rsdl 550F Axial 0.0010 P4_rsdl_70FAxial 0.0010 P5 rsdl 550F Axial 0.0010 P5 rsdl 70F Axial 0.0010 P6_rsdl_550FAxial 0.0010 P6_rsdl_70FAxial 0.0010 Crack growth results:

Total Subblock Cycles Cycles DaDn

/Time /Time Kmax Kmin DeltaK R /DaDt Da a a/thk Block: 1 20 20 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 40 40 -3.28e+002 -3.50e+002 2.25e+001 [.07 0.00e+000 0.00e+000 0.64 0.62 60 60 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 80 80 -3.28e+002 -3.50e+002 2.25e+001 [.07 0.00e+000 0.00e+000 0.64 0.62 100 100 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 120 120 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 140 140 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 160 160 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 180 180 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 200 200 -3.28e+002 -3.50e+002 2.25e+001 1.07.0.00e+000 0.00e+000 0.64 0.62 220 220 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 240 240 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 260 260 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 280 280 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 300 300 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 320 320 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 File No.: 0900530.308 Page B-20 of B-21 Revision: 0 F0306-01 RO

V StructuralIntegrity Associates, Inc.

340 340 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 360 360 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 380 380 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 400 400 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 420 420 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 440 440 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 460 460 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 480 480 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 500 500 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 520 520 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 540 540 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 560 560 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 580 580 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 600 600 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 620 620 -3.28e+002 -3.50e+002 2.25e+00l 1.07 0.00e+000 0.00e+000 0.64 0.62 640 640 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.00e+000 0.00e+000 0.64 0.62 660 660 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.OOe+000 0.OOe+000 0.64 0.62 680 680 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.OOe+000 0.OOe+000 0.64 0.62 700 700 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.OOe+000 0.OOe+000 0.64 0.62 720 720 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.OOe+000 0.OOe+000 0.64 0.62 740 740 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.OOe+000 0.OOe+000 0.64 0.62 760 760 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.OOe+000 0.OOe+000 0.64 0.62 780 780 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.OOe+000 0.OOe+000 0.64 0.62 800 800 -3.28e+002 -3.50e+002 2.25e+001 1.07 0.OOe+000 0.OOe+000 0.64 0.62 End of pc-CRACK Output File No.: 0900530.308 Page B-21 of B-21 Revision: 0 F0306-01 RO