L-09-122, Calculation 0900354.301, Rev. 0, Flaw Evaluation for N6A and C Nozzle to Safe End Welds

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Calculation 0900354.301, Rev. 0, Flaw Evaluation for N6A and C Nozzle to Safe End Welds
ML092650791
Person / Time
Site: Perry FirstEnergy icon.png
Issue date: 04/25/2009
From: Gustin H, Herrmann T
Structural Integrity Associates
To:
FirstEnergy Nuclear Generation Corp, Office of Nuclear Reactor Regulation
References
L-09-122 0900354.301, Rev 0
Download: ML092650791 (22)
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Text

V Structural Integrity Associates, Inc.

File No.: 0900354.301 CALCULATION PACKAGE Project No.: 0900354 Quality Program: M Nuclear [] Commercial PROJECT NAME:

Perry Plant Flaw Evaluation CONTRACT NO.:

55107920, Revision 3 CLIENT:

PLANT:

rirstEuergy Nuclear Operating Co.'

Perry Nuclear Power Plant.

CALCULATION TITLE:

Flaw Evaluation for N6A and C Nozzle to Safe End Welds Document Affected Project Manager Preparer(s) &

Revision Pages Revision Description Approval Checker(s)

Signature & Date Signatures & Date 0

1 - 9 Initial Issue A-i -A-3 B-i - B-8 H. L. Gustin T. J. Herrmann HLG 4/25/09 TJH 4/25/09 H. L. Gustin HLG 4/25/09 Page 1 of 11 F0306-01RO

~

Structural Integrity Associates, Inc.

File No.: 0900354.301 CALCULATION PACKAGE Project No.: 0900354

.' Quality Program: IZl Nuclear D Commercial PROJECT NAME:

Perry Plant Flaw Evaluation CONTRACT NO.:

55107920, Revision 3 CLIENT:

PLANT:

FirstEnergy Nuclear Operating Co; Perry Nuclear Power Plant CALCULATION TITLE:

Flaw Evaluation for N6A and C Nozzle to Safe End Welds Document Affected Project Manager Revision Pages Revision Description Approval Signature & Date 0

1-9 Initial Issue A-I - A-3 "JI/~

B-I-B-8 H. L. Gustin HLG 4/25109 Preparer(s) &

Cbecker(s)

Signatures & Date I *.

T. J. Herrmann TJH 4/25109 JI/~

H. L. Gustin HLG 4/25109 Page 1 of 11 F0306-01RO

Structural Integrity Associates, Inc.

.Table of Contents

1.0 INTRODUCTION

/STATEMENT OF PROBLEM/ OBJECTIVE..........................

3 2.0 TECHNICAL APPROACH OR METHODOLOGY.............................................

3 3.0 ASSUMPTIONS / DESIGN INPUTS..................

3 4.0 FLAW CHARACTERIZATION...........................................................................

4 5.0 C A LC U LA TIO N S.........................................................................................................

5 6.0 STRUCTURAL EVALUATION.............................................................................

6

7.0 CONCLUSION

S AND DISCUSSIONS................................................................

7 8.0 REFEREN CES.........................................................

.............................................. 8 APPENDIX A INSPECTION

SUMMARY

SHEETS FROM [4]..................................

A-i APPENDIX B PC-CRACK OUTPUT..................................................................................

B-I List of Figures Figure 1. Path 1 Through-Wall Axial Stress (psi)..............................................................

9 Figure 2. Center-Cracked Plate Fracture Mechanics Model............................................

10 Figure 3. Crack Growth Through 200 Cycles 1..............................

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Table of Contents

1.0 INTRODUCTION

/STATEMENT OF PROBLEM! OBJECTIVE............................... 3 2.0 TECHNICAL APPROACH OR METHODOLOGY.................................................... 3 3.0 ASSUMPTIONS / DESIGN INPUTS................. :..................................................... :... 3 4.0 FLAW CHARACTERIZATION......................................... '.......................................... 4 5.0 CALCULATIONS......................................................................................................... 5

. 6.0 STRUCTURAL EVALUATION.................................................................................. 6

7.0 CONCLUSION

S AND DISCUSSIONS....................................................................... 7

8.0 REFERENCES

............................. :~............................................................................... 8 APPENDIX A INSPECTION

SUMMARY

SHEETS FROM [4]....................................... A-I APPENDIX B PC';'CRACK OUTPUT.................................................................................. B-l List of Figures Figure 1. Path 1 Through-Wall Axial Stress (psi).................................................................... 9 Figure 2. Center-Cracked Plate Fracture Mechanics Model.................................................. 10 Figure 3. Crack Growth Through 200 Cycles,....................................................................... 11 File No.: 0900354.301 Revision: 0 Page 2 of 11 F0306-01:

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1.0 INTRODUCTION

/STATEMENT OF PROBLEM/ OBJECTIVE The N6 A, and C nozzle to safe end welds at Perry are dissimilar metal welds connecting the low alloy steel nozzle forgings to the Alloy 600 safe ends. The welds are Alloy 82/182 weld metal [1, 2]. These welds were previously ultrasonically inspected in 2001, and all results were acceptable per IWB-3500 criteria, requiring no further evaluation. The welds were re-examined during the current refueling outage (RO12). This re-examination identified two flaw indications (on each in the N6-A weld and in the N6-C weld) in the Alloy 182 material which were determined to slightly exceed the flaw acceptance standards of IWB-3514-2 [3, 4]. Both of these flaw indications were determined to be subsurface indications with no connection to the inside surface of the welds. They were classified as fabrication-related defects which had not grown in the intervening period, but were re-sized due to enhancements in data acquisition and evaluation.

The purpose of this calculation is to evaluate the identified flaw indications per the requirements of IWB-3600, to demonstrate that these indications do not affect the structural adequacy of the nozzle to safe end welds.

2.0 TECHNICAL APPROACH OR METHODOLOGY A fracture mechanics-based evaluation of the flaws is performed per the requirements of IWB-3600 considering weld residual stresses present in the welds following the application of a mechanical stress improvement process (MSIP). The observed flaws are assumed to be growing due to a fatigue crack growth mechanism.

The resulting flaws after projected growth during the next 10 year inspection period are evaluated to demonstrate that all structural criteria are maintained.

3.0 ASSUMPTIONS / DESIGN INPUTS

1. A composite flaw was assumed, combining the greatest through-wall dimension and greatest eccentricity of the two reported flaws and assuming a full 360 degree circumferential crack length.

This hypothetical flaw conservatively bounds the evaluation of all of the reported flaws.

2. In a previous calculation performed by SI [1], finite element analysis of the nozzle-safe end welds was performed to determine the weld residual stresses present in the welds following the application of a mechanical stress improvement process (MSIP) in 1992. The bounding residual stress distribution is shown in Figure 1, taken from [1]. Note that in that distribution, which is shown from the inside surface towards the outside (from left to right), the residual stress following MSIP varies from compressive to tensile (perpendicular to the plane of the crack) through the thickness of the weld. In the present calculation, the weld residual stress is conservatively taken to be the maximum tensile from that distribution, and is considered to be a constant membrane stress across the weld File No.: 0900354.301 Page 3 of 11 Revision: 0 F0306-01 tJ Structurallntegr;ty Associates, Inc.

1.0 INTRODUCTION

/STATEMENT OF PROBLEM! OBJECTIVE The N6 A, and C nozzle to safe end welds at Perry are dissimilar metal welds connecting the low alloy steel nozzle forgings to the Alloy 600 safe ends. The welds are Alloy 821182 weld metal [1,2]. These welds were previously ultrasonically inspected in 2001, and all results were acceptable per IWB-3500 criteria, requiring no further evaluation. The welds were re-examined during the current refueling outage (ROI2). This re-examination identified two flaw indications (on each in the N6-A weld and in the N6-C weld) in the Alloy 182 material which were detennined to slightly exceed the flaw acceptance standards ofIWB-3514-2 [3,4]. Both ofthese flaw indications were detennined to be subsurface indications with no connection to the inside surface of the welds. They were classified as fabrication-related defects which had not grown in the intervening period, but were re-sized due to enhancements in data acquisition and evaluation.

The purpose of this calculation is to evaluate the identified flaw indications per the requirements of IWB-3600, to demonstrate that these indications do not affect the structural adequacy of the nozzle to safe end welds.

2.0 TECHNICAL APPROACH OR METHODOLOGY A fracture mechanics-based evaluation of the flaws is perfonned per the requirements ofIWB-3600 considering weld residual stresses present in the welds following the application of a mechanical stress improvement process (MSIP). The observed flaws are assumed to be growing due to a fatigue crack growth mechanism.

The resulting flaws after projected growth during the next 10 year inspection period are evaluated to demonstrate that all structural criteria are maintained.

3.0 ASSUMPTIONS / DESIGN INPUTS

1. A composite flaw was assumed, combining the greatest through-wall dimension and greatest eccentricity of the two reported flaws and assuming a full 360 degree circumferential crack length.

This hypothetical flaw conservatively bounds the evaluation of all of the reported flaws.

2. In a previous calculation perfonned by SI [1], finite element analysis ofthe nozzle-safe end welds was perfonned to detennine the weld residual stresses present in the welds following the application of a mechanical stress improvement process (MSIP) in 1992. The bounding residual stress distribution is shown in Figure 1, taken*from [1]. Note that in that distribution, which is shown from the inside surface towards the outside (from left to right), the residual stress following MSIP varies from compressive to tensile (perpendicular to the plane of the crack) through the thickness of the weld. In the present calculation, the weld residual stress is conservatively taken to be the maximum tensile from that distribution, and is considered to be a constant membrane stress across the weld File No.: 0900354.301 Revision: 0 Page 3 of 11 F0306-01

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thickness. Weld residual stress is a steady state secondary stress which is not limited by the ASME Code. In a fatigue crack growth calculation such as that which follows, residual stress acts only as a mean stress. Weld residual stresses have no effect on cumulative usage calculations. Therefore, no update to the calculated cumulative usage factor (CUF) is needed to demonstrate ASME Section III code compliance.

3. The N6 nozzles are assumed to experience stress cycles due to plant start-ups and shut downs, and due to system operation in the RHR mode. RHR cycles are assumed to occur twice as frequently as start-up/shut down cycles, and to have the same magnitude. Over the ten year period from the current refueling outage until the next scheduled inspection in 2019, the estimated number of such combined cycles is assumed to be less than 100 (49 cycles reported from 2001 through April 2008

[5]). For additional conservatism in the event that the number of cycles increases significantly from that assumed, calculations are carried out to 200 cycles.

4. Crack growth is calculated from the current refueling outage until the next time the N6 nozzles with reported flaw indications are scheduled to be re-examined (10 year inspection interval).
5. In the following, all applied stresses are modeled as membrane stresses (i.e., constant magnitude across the wall thickness). This is very conservative since the stress combination PL+PB+Q includes significant bending stresses in the PB and Q terms, and treating bending stresses as membrane is conservative.
6. Since all reported flaws are subsurface with no connection to the weld inside surface or to the coolant chemistry, the intergranular stress corrosion crack (IGSCC) growth mechanism is not active. This mechanism requires reactor water chemistry to be present in the crack.

7.., The fatigue crack growth law for Austenitic Material in Air was taken from ASME Section XI, Appendix C [3]. Since the flaws are subsurface and not wetted, the air law is appropriate.

8. The value of Sm used in the calculations is for the Alloy 182 material.

4.0 FLAW CHARACTERIZATION A total of 8 flaws were identified in the Reference [4] inspection reports.

N6A - Flaw Indication 1:

Length: 1.5", Through wall dimension: 0.35", Separation from outside surface: 0.3" N6A - Flaw Indication 2:

Length: 1.2", Through wall dimension: 0.2", Separation from outside surface: 0.3" N6A - Flaw Indication 3:

Length: 2.0", Through wall dimension: 0.15", Separation from outside surface: 0.4" File No.: 0900354.301 Page 4 of 11 Revision: 0 F0306-01' l) Struelurallntegrity Associates, Inc.

thickness. Weld residual stress is a steady state secondary stress which is not limited by the ASME Code. In a fatigue crack growth calculation such as that which follows, residual stress acts only as a mean stress. Weld residual stresses have no effect on cumulative usage calculations. Therefore, no update to the calculated cumulative usage factor (CUF) is needed to demonstrate ASME Section III code compliance.

3. The N6 nozzles are assumed to experience stress cycles due to plant start-ups and shut downs, and due to system operation in the RHR mode. RHR cycles are assumed to occur twice as frequently as start-up/shut down cycles, and to have the same magnitude. Over the ten year period from the current refueling outage until the next scheduled inspection in 2019, the estimated number of such combined cycles is assumed to be less than 100 (49 cycles reported from 2001 through April 2008

[5]). For additional conservatism in the event that the number of cycles increases significantly from that assumed, calculations are carried out to 200 cycles.

4. Crack growth is calculated from the current refueling outage until the next time the N6 nozzles with

, reported flaw indications are scheduled to be re-examined (10 year inspection interval).

5. In the following, all applied stresses are modeled as membrane stresses (i.e., constant magnitude across the wall thickness). This is very conservative since the stress combination PL+PB+Q includes significant bending stresses in the PB and Q terms, and treating bending stresses as membrane is conservative.
6. Since all reported flaws are subsurface with no connection to the weld inside surface or to the coolant chemistry, the intergranular stress corrosion crack (IGSCC) growth mechanism is not active. This mechanism requires reactor water chemistry to be present in the crack.
7. "The fatigue crack growth law for Austenitic,Material in Air was taken from ASME Section XI, Appendix C [3]. Since the flaws are subsurface and not wetted, the air law is appropriate.
8. The value of Sm used in the calculations is for the Alloy 182 material.

4.0 FLAW CHARACTERIZATION A total of 8 flaws were identified in the Reference [4] inspection reports.

N6A - Flaw Indication 1:

Length: 1.5", Through wall dimension: 0.35", Separation from outside surface: 0.3" N6A - Flaw Indication 2:

Length: 1.2", Through wall dimension: 0.2", Separation from outside surface: 0.3" N6A - Flaw Indication 3:

Length: 2.0", Through wall dimension: 0.15", Separation from outside surface: 0.4"

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N6A - Flaw Indication 4:

Length: 0.85", Through wall dimension: 0.15", Separation from outside surface: 0.35" N6C - Flaw Indication 1:

Length: 1.9", Through wall dimension: 0.1", Separation from outside surface: 0.5" N6C - Flaw Indication 2:

Length: 3.7", Through wall dimension: 0.25", Separation from outside surface: 0.3" N6C - Flaw Indication 3:

Length: 16.6", Through wall dimension: 0.3", Separation from outside surface: 0.35" N6C - Flaw Indication 4:

Length: 1.9", Through wall dimension: 0.2", Separation from outside surface: 0.35" From the review of all of the above indications, there are two subsurface flaws requiring further evaluation [4], which will be identified furthermore as Flaw I and Flaw 2. One of these is located in the N6A weld, and one is located in the N6C weld. These flaws are characterized as follows:

Flaw 1 (N6A):

Length: 1.5", Through wall dimension: 0.35", Separation from outside surface: 0.3" Flaw 2 (N6C):

Length: 16.6", Through wall dimension: 0.3", Separation from outside surface: 0.35" From the 8 identified indications, a single worst case flaw was determined that bounds all of the flaw indications for future inspections. This was done in consideration of future UT technology improvements which could result in identifying additional connected flaws (such as occurred from the 2001 data to current dimensions).

The inspection summary sheets for these flaws [4] are attached as Appendix A.

5.0 CALCULATIONS The SI fracture mechanics program pc-CRACK [6] was used to perform the crack growth calculations.

The bounding flaw from the flaw characterizations above (see assumption 1) was taken as: Length:

16.6", through wall dimension: 0.35", Separation from outside surface: 0.3".

This flaw was used as the starting point for the fatigue crack growth calculation. The center-cracked plate model was used to represent the flaw geometry for the crack growth calculation. This is illustrated in Figure 2. This model treats the modeled flaw as infinitely long in the depth direction (into the page in Figure 2). This model effectively represents the assumed full circumferential flaw.

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N6A - Flaw Indication 4:

Length: 0.85", Through wall dimension: 0.15", Separation from outside surface: 0.35" N6C - Flaw Indication 1:

Length: 1.9", Through walldimension: 0.1", Separation from outside surface: 0.5" N6C - Flaw Indication 2:

Length: 3.7", Through wall dimension: 0.25", Separation from outside surface: 0.3" N6C - Flaw Indication 3:

Length: 16.6", Through wall dimension: 0.3", Separation from outside surface: 0.35" N6C - Flaw Indication 4:

Length: 1.9", Through wall dimension: 0.2", Separation from outside surface: 0.35" From the review of all of the above indications, there are two subsurface flaws requiring further evaluation [4], which will be identified furthermore as Flaw 1 and Flaw 2. One of these is located in the N6A weld, and one is located in the N6C weld. These flaws are characterized as follows:

Flaw 1 (N6A):

Length: 1.5", Through wall dimension: 0.35", Separation from outside surface: 0.3" Flaw 2 (N6C):

Length: 16.6", Through wall dimension: 0.3", Separation from outside surface: 0.35" From the 8 identified indications, a single worst case flaw was determined that bounds all of the flaw indications for future inspections. This was done in consideration of future UT technology improvements which could result in identifying additional connected flaws (such as occurred from the 2001 data to currerit dimensions).

The inspection summary sheets for these flaws [4] are attached as Appendix A.

5.0 CALCULATIONS The SI fracture mechanics program pc-CRACK [6] was used to perform the crack growth calculations.

The bounding flaw from the flaw characterizations above (see assumption 1) was taken as: Length:

16.6", through wall dimension: 0.35", Separation from outside surface: 0.3".

This flaw was used as the starting point for the fatigue crack growth calculation. The center-cracked plate model was used to represent the flaw geometry for the crack growth calculation. This is illustrated in Figure 2. This model treats the modeled flaw as infinitely long in the depth direction (into the page in Figure 2). This model effectively represents the assumed full circumferential flaw.

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Reference [2 page 2] gives the maximum stresses experienced at the weld as PL+PB+Q=55.03 ksi for the Inconel material. This is conservatively used to bound the stress magnitude associated with the startup-shutdown and RHR cycles.

For the purposes of the fatigue crack growth calculation, the Kmax is taken as {PL+PB+Q+RESIDUAL}

and the Kmin is taken as RESIDUAL. The value of residual stress chosen is consistent with assumption 5; all stresses are conservatively treated as membrane stresses. Referring to Figure 1, the applicable residual stress used was for the post MSIP normal operating cases(MSIP OFF, NOP2), where the assumed valued in this analysis is tensile, and axially oriented, i. e., normal to the crack face.

The pc-CRACK crack growth results are shown in Figure 3, and the output is included in Appendix B.

For the anticipated number of bounding cycles expected to occur from 2009 to 2019, only a minimal amount of growth is predicted to occur, even under the very conservative set of assumptions contained herein. The resulting throughwall dimension of the bounding flaw after 100 cycles is 0.366",

corresponding to less than 0.02" growth. This meets the acceptance criteria ofIWB-3641 [3].

6.0 STRUCTURAL EVALUATION The presence of flaws will reduce the amount of wall thickness in the weld that is available to carry load.

The existing flaw in nozzle N6A has an area of: [Flaw 1]: Length (1.5) x Throughwall dimension (0.35)

= 0.53 in2. The existing flaw in nozzle N6C has an area of [Flaw 2]: Length (16.6) x Throughwall dimension (0.3) = 4.98 in2.

The cross sectional area of the weld without flaws is A= t(OR2-IR 2)=T(49.87-33.78)=50.55 in2 [7]. So the reported flaws in N6A represent approximately 1% of the total area of the weld. The flaw in N6C represents 9.9% of the total area. Removing that amount of material in either weld would increase the stress in the remaining material by the same %. All ASME Allowable stress limits as reported in [2]

continue to be met after projected flaw growth up to an increase of more than 25%. Even if the conservatively evaluated full circumferential flaw of 0.366 x 27E(5.8125 + 0.55) = 14.63 in2 were used, this would be 29 % of the area section, with a projected growth of less than 0.02", significant margin is provided to primary stress limits.

The primary membrane stress intensities at the Alloy 82/182 safe end to nozzle weld are reported in [8],

sheet 13 of 18 to be 11158 psi for normal and upset conditions. The same page notes that any bending stress intensities are very small. The allowable stress intensity for the Inconel material is reported on the same page as 23300 psi. The primary stress intensity ratio (Pm+Pb)/Sm is then equal to 0.48. The largest observed flaw has a length of approximately 16 inches, and the circumference of the component at the flaw location is approximately 44 inches, so the ratio of flaw length to circumference is 0.36, which will be rounded to 0.4. Referring to ASME Section XI, 1989 Edition, Table IWB-3641-5, it may be seen that for a stress ratio of 0.48 (i.e., less than 0.6) and a flaw length/circumference of 0.4, the allowable end of interval flaw depth (2a for a subsurface flaw) is 0.6 a/t. This value is much greater than File No.: 0900354.301 Page 6 of 11 Revision: 0 F0306-01O tJ Structural Integrity Associates, Inc.

Reference [2 page 2] gives the maximum stresses experienced at the weld as PL+PB+Q=55.03 ksi for the Inconel material. This is conservatively used to bound the stress magnitude associated with the startup-shutdown and RHR cycles.

For the purposes of the fatigue crack growth calculation, the Kmax is taken as {PL+PB+Q+RESIDUAL}

and the Kmin is taken as RESIDUAL. The value of residual stress chosen is consistent with assumption 5; ail stresses are conservatively treated as membrane stresses. Referring to Figure 1, the applicable residual stress used was for the post MSIP normal operating cases(MSIP OFF, NOP2), where the assumed valued in this analysis is tensile, and axially oriented, i. e., normal to the crack face.

The pc-CRACK crack growth results are shown in Figure 3, and the output is included in Appendix B.

For the anticipated number of bounding cycles expected to occur from 2009 to 2019, only a minimal amount of growth is predicted to occur, even under the very conservative set of assumptions contained herein. The resulting through wall dimension ofthe bounding flaw after 100 cycles is 0.366",

corresponding to less than 0.02" growth. This meets the acceptance criteria ofIWB-3641 [3].

6.0 STRUCTURAL EVALUATION The presence of flaws will reduce the amount of wall thickness in the weld that is available to carry load.

The existing flaw in nozzle N6A has an area of: [Flaw 1]: Length (1.5) x Throughwall dimension (0.35)

= 0.53 in2* The existing flaw in nozzle N6C has an area of [Flaw 2]: Length (16.6) x Throughwall dimension (0.3) = 4.98 in2*

The cross sectional area ofthe weld without flaws is A=1t(OR2-IR2):::::1t(49.87-33.78):::::50.55 in2 [7]. So the reported flaws in N6A represent approximately 1 % of the total area ofthe weld. The flaw in N6C represents 9.9% of the total area. Removing that amount of material in either weld would increase the stress in the remaining material by the same %. All ASME Allowable stress limits as reported in [2]

continue to be met after projected flaw growth up to an increase of more than 25%. Even ifthe conservatively evaluated full circumferential flaw of 0.366 x 21t(5.8125 + 0.55) = 14.63 in2 were used, this would be 29 % of the area section, with a projected growth ofless than 0.02", significant margin is provided to primary stress limits.

The primary membrane stress intensities at the Alloy 82/182 safe end to nozzle weld are reported in [8],..

sheet 13 of 18 to be 11158 psi for normal and upset conditions. The same page notes that any bending stress intensities are very small. The allowable stress intensity for the Inconel material is reported on the same page as 23300 psi. The primary stress intensity ratio (Pm+Pb)/Sm is then equal to 0.48. The largest observed flaw has a length of approximately 16 inches, and the circumference of the component at the flaw location is approximately 44 inches, so the ratio of flaw length to circumference is 0.36, which will be rounded to 0.4. Referring to ASME Section XI, 1989 Edition, Table IWB;.3641-5, it may be seen that for a stress ratio of 0.48 (i.e., less than 0.6) and a flaw length/circumference of 0.4, the allowable end of interval flaw depth (2a for a subsurface flaw) is 0.6 alt. This value is much greater than File No.: 0900354.301 Revision: 0 Page 6 of 11 F0306*01

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that of the limiting flaw of 6.366/1.2=0.305. Therefore, the limiting flaw is acceptable by the methods ofIWB-3641.

The evaluation methods contained in Sections 5.0 and 6.0 are consistent with the methods and requirements of ASME Section XI, IWB-3600 and Appendix C.

7.0 CONCLUSION

S AND DISCUSSIONS The presence of the two reported subsurface fabrication defects and their projected growth due to fatigue does not reduce the capacity of the welds in N6A and C below Code [3] allowable. The limiting flaw shows no significant growth in the through wall direction, as compared to the 2001 results as re-evaluated last October [5]. This supports the conclusion that the observed indications are in fact fabrication defects. The evaluation is projected out for more than 10 years, allowing the station to maintain the current 10 year inspection interval. All Code margins are maintained.

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that ofthe limiting flaw of 0.366/1.2=0.305. Therefore, the limiting flaw is acceptable by the methods QfIWB-3641.

The evaluation methods contained in Sections 5.0 and 6.0 are consistent with the methods and requirements of ASME Section XI, IWB-3600 and Appendix C.

7.0 CONCLUSION

S AND DISCUSSIONS The presence of the two reported subsurface fabrication defects and their projected growth due to fatigue does not reduce the capacity of the welds in N6A and C below Code [3] allowable. The limiting flaw shows no significant growth in the through wall direction, as compared to the 2001 results as re-evaluated last October [5]. This supports the conclusion that the observed indications are in fact fabrication defects. The evaluation is projected out for more than 10 years, allowing the station to maintain the current 10 year inspection interval. All Code margins are maintained.

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8.0 REFERENCES

1. SI Calculation 0800439.306R0, Residual Heat Removal/Low Pressure Core Injection (RHR/LPCI)

Nozzle, N6, ID Repair Weld Residual + MSIP Analysis.

2. CB&I Stress Report "238" BWR Vessel" Section S-13 sheet 2. SI File Number 0800439.216
3. ASME Section XI, 1989 Edition and 2001 Edition with Addenda through 2003
4. GE Flaw Inspection Reports APR-09-209-7 (weld 1B13-N6A-KB) and ARP-09-209-9 (weld 1B 13-N6C-KB). SI File 0900354.208
5. SI Calculation 0800439.307R1, Evaluation of fabrication defects in N6A and C Nozzle to Safe End Welds.
6. SI Program "pc-CRACK for Windows", version 3.1-98348
7. CB&I Drawing N6 Nozzle Forging (RHR-LPCI MODE),"CBI VPF No. 3521-257, Rev. 1, June 1973 SI File 0800439.208
8.

CB&I Stress Report "238" BWR Vessel" Section D-13 sheet 13.

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8.0 REFERENCES

1. SI Calculation 0800439.306RO, Residual Heat RemovallLow Pressure Core Injection (RHRfLPCI)

Nozzle, N6, ID Repair Weld Residual + MSIP Analysis.

2. CB&I Stress Report "238" BWR Vessel" Section S-13 sheet 2. SIFile Number 0800439216
3. ASME Section XI, 1989 Edition and 2001 Edition with Addenda through 2003
4. GE Flaw Inspection Reports APR-09-209-7 (weld IB13-N6A-KB) and ARP-09-209-9 (weld IB 13-N6C-KB). SI File 0900354208
5. SI Calculation 0800439.307Rl, Evaluation of fabrication defects in N6A and C Nozzle to Safe End Welds.
6. SI Program "pc-CRACK for Windows", version 3.1-98348
7. CB&I Drawing N6 Nozzle Forging (RHR-LPCI MODE),"*CBI VPF No. 3521-257, Rev. 1, June 1973 SI File 0800439.208
8.

CB&I Stress Report "238" BWR Vessel" Section D-13 sheet 13.

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Path 1 Axial Stresses (SY) 4* 0000

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Path 1 Axial Stresses (SY) 04 0.'

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Figure 1. Path 1 Through-Wall Axial Stress (PSi)

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a =C..

L. ra 1t REQUIRED INPUTS:

b: plate half width a: maxinm crack depth (a.

< 0.91b)

I F

Figure 2. Center-Cracked Plate Fracture Mechanics Model File No.: 0900354.301 Revision: 0 Page 10 of 11 F0306-01 lJ Structural/ntegrity Associates, Inc.

1 File No.: 0900354.301 Revision: 0 1

I..a~

~I b

1

~

REQUIRED INPUTS:

b: plate half vvidth a: maxim.un cmck depth (8max < O.9b)

Figure 2. Center-Cracked Plate Fracture Mechanics Model Page 10 of 11 F0306-0r

Structu'to';,r SSWer As oiates:Ic brack Gnrwt 5?

4, 0,1V92 092881 01866' A2-0 i~~;~;~.'1:1/2 i~L2~A~

I

  • j-:

4

-A

-~: __

V.-.,>

20 40 60 80 l~oo"

.120

'140 160

ý18 Figure 3-Crack Gr,owth Through 200 Cycles 200 Page 11 of 11

~F0306-01 File No.: 0900354.301 Revision, 0

Structural Integrity Associates, Inc.

APPENDIX A INSPECTION

SUMMARY

SHEETS FROM [41 File No.: 0900354.301 File No.: 0900354.301 Revision: 0 F0306-01 RO Page A-I of A-3 e Structural Integrity Associates, Inc.

File No.: 0900354.301 Revision: 0 F0306-01RO APPENDIX A INSPECTION

SUMMARY

SHEETS FROM [4]

Page A-I of A-3

V Structural Integrity Associates, Inc.

HrrACHI I Austenitic Piping Flow Evaluation Sheet k*ct: Pe"y l

~uidID: 1813-N6A-KB BurnDatagbemt: Af'-09-209O7 Inidkcag

I S1ug Data Anet: N/A Felw l/mwh Wall.

0.346 0.35 "rTrmbtd-1.12 1.1 FEA.L&Wt T.

1.53

.5 T'10mmu,,.

1.20 1.2 Swfab pSmWe n"'r =

0333 03 AS#E SectUion. 2001 rm*M 200A Mdua TAMKE RIB-3514-2 AMWMf USMIo6 1.$0 hkid NW*W ThkbWU - IngevIc oA SuSum %

SitMm %

Surbe S.ljdam %

0.00 10.48 10.48 0.05 10.60 10.60 0.10 10.88 10,88 10.91 10.91Y 0.15 10-96 10.9e 0,20 1126 11.26

~

0.25 11.38 11.38

~

0.30 11.58 11.58 0.35 11.76 1176 0.40 11.96 11.96

~

0.45 12.46 12 0.50 1234 1234 Alk9d A10w.d 10.91 1091 a0 0.175 oil value-0.117 Y-1.000 Flow is Subsurface Alowed afts 10.9%

a/t=

14.6%

Flaw Is W=Cmcpzb.b a*y T"

S-35,4-L.

mw"W7 1"~

COMM~ft ASME Secio run

-tpe rformed In xd wfth WA-3200 w4 M E29.

Indicatin is circumferential in orientation.

Subsurface Planar faw per IWA-3320, WW,.3320-1 LevdQW By:

Dote ROC9064 9* JReviewed By.

Earnest Caon Levet 11 Date 3/29/2009 ILevek III Date 3/29/2009 vwo w3Nr0i Poge 22 of 25 File No.: 0900354.301 File No.: 0900354.301 Revision: 0 F0306-01 RO Page A-2 of A-3 l) Siructuralinlegr;ty Associates, Inc.

In I HITACHI Austenitic Piping Flaw Evaluation Sheet 1'nI#Kt: I'eny Unit 1 MIWcIID: 18ll-N6A-1<8 Indication: 1 tfIII8a:d B!IImIfIIt o.J46 0.35 1.53 L5 0.333 0.3 EllamOalo.... : APR-09-Z09-07 SIIIng 0aI0.... : N/A

.,. nominal.

.,.-.1.

tfIIIIIlIIf LlZ LZO ASHE SedIan II, 2001 fdIIIon, 20IB AddIi.da TABLE IWB-351WAuanIIIc,..., UOInch NomhII ~-I-w:.

all

~" sut.urfDce "

SUrfDcII" SUbIIII1'ucI "

0.00 10.118 10.118 o.os lQ.60 10.60 0.10 10.B8 lOBS 10.91 10.91 V 0.15 10.98 10.98 020 11.26 1LZ6 0.25.

11.J8 11.J8 o.JO 1LS8 1LS8 o.J5.

1L76 1L76 0.110 11.96 11.96 0.45

,-12.08 l2.D8 0.50 12.34 1Z.34 Allowed AIIclwed 10.91 10.91

  • 0-0.175 011 value -

0.117 v-LOOO Row is Subsurface AIowed oft =

10.996 oft-11&.6'16 ASME Xlroun E29.

is circurnfenIntia in orientation bsu ce Planar flow IYIA-33ZO

~An:.:::d~re"-!* ROChoI=~~_-=.:::;..--...:._

B!IIKIIfIIt Ll L2 LeveI:..::.II __

Dote: 31Z912OO9 LeYeI:.:::III __

Dote: 3/2912009 File No.: 0900354.301 Revision: 0 F0306-0IRO 5

Page A-2 of A-3

V Structural Integrity Associates, Inc.

HMCH Austenitic Piping Flaw Evaluation Sheet WedO. 1813-N6C-KB S amDataght: APR-09-209-09 dkxcatmw: 3 Sh Data,set:

W/A flow Throup. VAN 0.31 0.3 Trwnab 1.12 1.1 FlwLmVO 1-1655 15.6 "Trnmansd.

.20 12 S

rk "SdPwa 0.34 0.35 A.SME e

an 16.

260 Mm.. 263 Dddmda TABLE IW-3S1*2 AudimVk Sbwk 1.0 LOh Muh Mo lnd Thdma - kmnvko oA sufam' %

sthusagtm Srk"e %

SuLmtxfos S 0.00 10.48 10.48 10.50 10.50 V 0.0 10.0 10.0 0.10 10.88 10.8 0.15 10.88 10.98 0.20 1126 1126 025 11.38 11.38 0.30 1258 11.58 0.35 1176 1.76 0.40 11.96 11.96 0.45 12.06 12.08 0,50 12.34 12.34 Aflavd Alwed 10.0 10.50 a=

0L150 011vake:

009 V.

1.000 Flow is Subsurface Allowed alt-10.5%

aft -

12.5%

law b-wuMhCtm by TOM@

MW'-3m1-F.*dvm om itASI4E ecn ru ngifoedm-acodn t WA-U andA n

SubSwdoC Pona flaw W !#A-3320, rWA-3320-1

ýMouated By AandrW Rodid tl Ch' Revee Bly.______

Levek 11 Date: 3/28/2009 ILevek III Daft 3/28/2009 P,6=OC

-3fERIO Pogo Z3 Of Z4 File No.: 0900354.301 File No.: 0900354.301 Revision: 0 F0306-01RO0 Page A-3 of A-3 tJ Structural Integrity Associates, Inc.

I 8' HITACHI Aust.. nitic Piping Flow Evaluation Sheet Pn¥Kt: Perry Unit 1 WiIId /0: l81J-N6C-KB flIIm 00fa st.t: APR.()9.2Q9-09 1ndIcaIIon: 3 5IIInf 00fa st.t: NiA lMm4t I1JmIr1I.

"r'--"-

ffIIIIIrCIIf

~

"'-T1nugIt !MIl-0.31 0.3 1.12 U

"., un,tII T-16.55 16.6

'T'-.d.

L20 U

swa.s.pauCfIMT-0.34 0.35 ASHE 5K1Ion ICI, 2G01 EIIIIan. ZOD3 MdIndo TABU! 1W8-:J514.2 AuDIItIc SbIIIt. UO IndI NoIIIInai 'YIIIcIIr.a -"-"Ice all s..tac."

SUIsurfaa "

s..tac." -"

0.00 10AS l0A8 10.s0 10.s0V 0.05 10.60 lQ.60 0.10 10.88 10.88 0.15 10.98 10.98 0.20 1126 1126 025 1llS IUS 0.30 11.58 11.58 0.35 11.76 11.76 0.40 11.96 11.96 0.45 12.oa 12.08 o.so 12.34 l2.34 AIbwd AIkMecI 10.s0 10.s0 0=

0.150 a/lvuIue-0.009 V_

LOOO Flaw is Subsurface AlawedaJt-10.5" aIt-125" FlalrIsUl'

....... by Tallie 1W8-351W.

_>mIOl ASHE 1110 11W""3200 andASTliirm.

IndIaItian is In Planar Haw Del' 1W""3320 1W""332G-l jEvaluated By. Andre' RadIal

().A..,' /.....77 ReIIiewed By:

~~

level: II File No.: 0900354.301 Revision: 0 F0306-01RO Data: 3/28/2009 I l8ve/; III Date: 3/28/2009 i23Of24 Page A-3 of A-3

C Structural Integrity Associates, Inc.

APPENDIX B PC-CRACK OUTPUT File No.: 0900354.301 File No.: 0900354.301 Revision: 0 F0306-OIRO Page B-1 of B-8 l) Structural Integrity Associates, Inc.

File No.: 0900354.301 Revision: 0 F0306-01RO APPENDIXB PC-CRACK OUTPUT Page B-1 of B-8

V Structural Integrity Associates, Inc.

t=

pc-cv=

fazt Windows Version 3.1-90345 (C)

Copyright

'54 "ge structural Integrity Amsociates. Inc.

2215 A*laden Expressway, Suite 24 San Jose, CA 95115-1537 Voice:

405-970-0200 Fam:

408-978-5944 E-uail:

pccrack szuctint.cc=

Linear Elastic Fractuxe Mechanics Date: Mon Apr 0 17:22:12 2009 Input Data and Results rile:

F._PLP=.LrK

Title:

0900354: Przzy )IEA and NGC Flaw Evaluation Load Cases:

Case ID Unit membrane Residual Conzat Stress Coefficient*s CO Cl 10 0

20 0

C2 0

0 C2 Type 0

Coeff 0

Coeff

Through Wall Wall Case Depth Unit M*uabr Stresses for Load Cases Case Residual C With Stress Coeff -------

0.0000 10 20 0.0200 10 20 0.0600 10 20 0.0900 10 20 0.1200 10 20 0.1500 10 20 0.1300 10 20 0.2100 I0 20 0.2400 10 20 0.2700 10 20 0.3000 10 20 Crack Model: Ceaner Cracked Plate Under Renowe Tension Stress Crack Parameters:

Plate Halt Width:

0.6000 Crack depth:

0.2000 Co = RmAote Tension Stress All other stress coefficients are neglected.

-- Stress Intensity Factor-Crack Case Case size Unit MeHmbr Residual C 0.0060 1.27302 2.74604 Page: 1 File No.: 0900354.301 Revision: 0 Page B-2 of B-8 F0306-OIRO lJ Structurallntegfity Associates, Inc.

pc-CRACK fo%" Windows VersioD 3.1-98348 (C) Copyri9ht 'et -

'S8 Structura~ IDteg:ity ~soci... s, IDc.

3315 ~deD EXpressway.

S~ite 24 Saa Jose, CA 98118-1557 Voice:

408-878-8200 Fax:

40B-978-8ge4 E~i~: pccrackistructiAt.CaD nate: Hon Apr oe 17:22:13 2009 Input Data ;md lI.esul"s f"ile: PY_PLPlIQ.LlM Titl.: 0800354: Pe%ry NeA and NeC rlaw Evaluation Load Cases:

ODit lfembr......

lI.e.. idual Co.... "

Stress CoefficieDts CO C1 10 20 o o C2 o o C3 o o Type Coeff Caeff

ThEough Wall Stre.... es for Load CaDeD With Stre... Coef£-------

.al~

c......

Ca **

Depth UDi t Heoabr lI.eaidual C 0;0000 10 20 0.0301) 10 20 o.oeoo 10

21) 0.1)900 10 20 0.1200 10 20 0.1500 10 20 0.1800 10 20 0:2100 10 20 0.2"1)0 10 20 0.2700 10 20 0.3000 10 20 Crack HDde~: Center Cracked P~ate UDder ~e T..... ion Stres..

Crack Para.e~e%D:

Plate Bal£ Width:

Crack depth:

o.eooo 0.3000 CD = Re.ote Tenaion St~eD5

~l a~hez B~zeDS coe£ficieutD are Deg1ccted~

~-----StreBs IDte.... ity Factor--------------------

Crack Case C:ase Siae UDit Hembr Re.. idua~ c:

0.0060 1.37302 2.74604 File No.: 0900354.301 Revision: 0 F0306*0IRO Paqe: 1 Page B-2 ofB-8

C Structural Integrity Associates, Inc.

0.0120 0.0150 0.0240 0.0200 0.0260 0.0420 0.0480 0.0540 0.0600 0.0660 0.0720 0.0750 0.0540 0.0900 0.0960 0.1020 0.1050 0.1140 0.1200 0.1260 0.1220 0.1250 0.1440 0.1500 0.1560 0.1620 0.1650 0-1740 0.1500 0.1560 0.1920 0.1950 0.2040 0.2100 0.2160 0.2220 0.2250 0.2340 0.2400 0.2460 0.2520

0. 2550 0.2640 0.2700 0.2760 0.2520 0.2550 0.2940 0.2000 1.94209 2.27926 Z.74548 2.01745 2.23015
2. 64202 2.59804 4.12869 4.28752 4.5845 4.79701 5.00041 5.19763
5. 2951 5.57675 5.75995 5.92964 8.11628 6-29028 6.462 8.6217a 6.79992 6.96671 7.1324 7.29724 7-48146 7.62527 7_75889 7.95251 5.11622

.m20052

. 44521

8. 81084 0.77722 8.9449 9.11379 9.28416 9.4562 9.62009 9.80602 9.9842 10.1648 10.2481 10.5242 10.7225 10.916 11.1121 11.2121 11.5161 3.18417 4.7 853
5. 49695
6. 14906 e.74026
7. 25605 7.7960B 8.27725 B.72502 9.17291 9.59403 10.0005 10.3952 10.779 11.1525 11.5199 11.5792 12.2326 12.5806 12.924 12.2626 13.5995 13.9334 14.2645 14.8945 14.9229 15.2505 15.5779 15.905 16.2326 16.5611 16.5906 17.2217 17.5546 17.5898 18.2276 16.5692 18.9124 19.2602 19.612 19.96584 20.3296 20.6962 21.06B4 21.4469 21.822 22.2242 22.6241 23.0222 Crack Growth Lawn:

Law ID:

Sect XI hus Air Model:

ASHE Section XI anstenitic stainless steel in air environment da/dX = C - 10^F

  • 5 k dKI3.2 where

= 1.0 for R < 0

= 1.0 + 1.6

  • R for 0 < 3 < 0.79

= -42.5 + 57.97

  • 3 for 0.79 <

3 < 1 r = code specified func*ion of t14umeratuxe P~age:

2 File No.: 0900354.301 Revision: 0 Page B-3 of B-8 F0306-OIRO tJ Structural/ntegr;1y Associates, Inc.

0.0120 1.942011 3.88417 0.01110 2.37926 4.7&IIS3 0.0240 2.74848 5~49US 0.0300 3.07453 6.14906 0.0360 3.37018 15.740315 0.0420 3.64303 7.2860S 0.04110 3.B9804

'1.7960B 0.OS40 4.U8n 8.2'1'73B 0.0600 4.36752 8.73503 0.0660 4.SBf45 9.1'1291 0.0720 4.79701 9.59403 0.07!\\)

5.00041 10.0008 0.OB4\\)

5.111763 10.3953 0.0900 5.311951 10.779 0.0960 5.57675

'11.1535 0.1020 5.75n5 11.5199 0.1080 5.9311414 11.!793 0.1140 6.11E211 12.2326 0.1200 6.2902e 12.SII06 0.12150 8.462 12.924 0.1320 6.631711 13.2U6 0.13BO 6.79992 13.59911 0.1440 li.!l6671 13.9334 0.1600 7.U24 14.2648 0.lS60 7.29724 14.5945 0.1620 7.4U46 14.9229 0.1680 7.e2527 15.2505 0.1740 7.788ell 15.S778 0.1800 7.1152S1 IS. 905 0.1860 1I.11ea2 111.2326 0.1920 B.2B053 16.sell 0.1980 B.44531 16.81106 0.2040 B.U084 17.2217 0.2100 B.77732 17.SS46 0.21150 8.114U 17.81!98 0.2220 9.11379 18.2276 0.2280 1I.2B4115 18.5683 0.2340 9.45152 18.91%4 0.2400 9.630011 19.2602 0.%4150 9.B0602 19.612 0.2520 9.9B42 19.11684 0.2580 10.164B 20.32S15 0.21540 10.3481 20.6962 0.2700 10.5342 21.0684 0.27110 10.7235 21.44159 0.2B20 10.lIle 21.822 0.2880 11.1121 22.2242 0.2940 11.3121 22.11241 0.3000 11.5161 23.0322 Crack Gr~h Lawa:

, L.... ID:

Sect XI Aus Air, Hadel:

ASHE Section XI - agstenibic abainleas steel in air enyiro~t where S = 1.0 for R < 0 1.0 + 1.8

  • II fDr 0 < II < 0.79

-43.5 + 57.97

  • a fDr 0.'19 < a < 1 F = code specified function of temperature File No.: 0900354.301 Revision: 0 F0306-OIRO P'"'I": 2 Page B-3 ofB-8

V Structural Integrity Associates, Inc.

dR = FmaR

lad, A = rain

/ Kmax where:

C l OF

=

,.840ae-010 is for the currently Selected units of:

farce: kip length; inch temperature:

550.0000 Fahrenheit material Fracture Toughness Ric:

Material MD: Alloy 182 Depth RIC 0.0000 Z00.0000 0.8000 Z00.0000 1.0000 Z00.0000 1.5000 200.0000 Inltial crack siuze 0.

Man. crack sire=

Number of blockse PrzLn incrtement of block-

  • 1780

[.3000 1

1 Cycles Calc.

Print Crk. Gzw.

/Time incre. incre. Law Mat.

KIc Subblock Per:ryl 200 1

1 Sect Xr,us Air Alloy 182 lma lain Subblock Case ID Scale Factor Case ID Scale Factor Pe*ryl Residual Const 1.5000 Residual Const 1.5000 Unit. Membrane 5.5000 Crack gronh results:

Total Subblock Cycles Cycles

/Tie

/Tlime DaDn

/DaDt mos lRain DeltaK R

Da a

a/thk Block:

1 22 4

5 "7

8 9

10 11 1

2 a

4 5

6 7

9 10 11

6. 64e+001
6. GSe+O01
6. 68e+001
6. 65e+001 a -5es+001 E.ESe+001 6.65e+001 G.E6e+001 6.66e+001
6. 66e+001 6.96e+001 2.34e+001
2. a5e+001
2. 28e+001
2. 35e+001 2.25e+001 2.25e+001 2.35e+001 2.25e+001
2. 25e+001
2. 35e+001 2.35e+001 4.20e+001
4. 20e+001 4.30e*001
4. 30e.001 4.20e+001 4.20e+001 4.21e+001 4.21e+001
4. 81e+001 4.21e+001
4. 21e+001 0.25 7.39e-005 7.29e-005 0.28 7.39e-005 7.29e-005 0.25 7.40e-006 7.40c-005 0.25 7.41e-008 7.41e-005 0.28 7.41e-005 7.4le-005 0.28 7.42e-005 7.42e-005 0.25 7.42e-005 7.4te-005 0.25 7.42e-005 7.43e-005 0.25 7.44e-005 7.44e-005 0.25 ?4e--005 7.45e-005 0.25 7.48e-005 7.45e-005 0.1751 0.1751 0.1752 0.17532 0.1784 0-1754 0.1755 0.1756 0-1757 0.1757 0.1758 0.29 0.29 0.29 0.29 0.29 0.29 0.29 0.29 0.29 0.29 0.29 Page: 2 File No.: 0900354.301 Revision: 0 Page B-4 of B-8 F0306-01RO t> Structurallntsgrity Associates, Inc.

wbe~e:

dK = J:.aa -

l.'tm:i1l a = ltIaill ! ~

C

  • 10~r = 1.Bt03e-010

~. fo~ ~

CUE~eA~ly 8elec~ed uni~. of:

fa~ce: Up length: ;Lach

~empera~w:e:

550. 0000 F.. hr.. ah...i~

Ka~e~~a1 ID: Alloy l8Z 0.0000 O.SOOO 1.0000 1.5000 lac 200.0000 eOO.OOClO eoo.OOOO eoo.OOOO Ini~~al crack.i.e:

Max. crack a~.e=

!lumber of blocl..,=

Cl.1750 0.3000 1

P:d.,,~.iz>=_nu of blocit='

1 SubbJ.ock p.,rryl Cycl....

!Ti_

200 C.. l.c.

incZ'e~

1 baa Pr.iD~

il1c:re.

1 CEIl.. <Ont.

Kat..

!.a" ttIc Sec~ XI Au.. hE Al.l.oy 182 ltIain SubbJ.ock C..... ID Seal.. ract.or C.. oe ID Scal.. ract.or Perry!

llesidu.a1 Conat tJD:L Co ltc.brAfte 1.6000 6.5000 lleaidua1 Conet er.. cIL 9Z~b r...,ul.tts:

TDt... l Cycl...

/TDIr!.

Bl.DCIL:

1 2

3..

5 6

7 II 9

10 11 File No.: 0900354.301 Revision: 0 F0306*01RO Subblock Cycle..

/TDIr!.

1 1

~.64e+OCl1 2 6.1!.5e+ClCll 3 6.6S.. +001

.. G.e5e+001 5 E.I!S.. +OOl 6 E.E5e+001

'1 E.65e+00l B 6.E6e+OO1 9 6. 66e+00l 10 6.E6e+001 11 6.e6e+001 D.. Dn bin Del~

R ID.. Dt.

2.34e+001 4.30.. +001 0.3S 7.39.. -00&

2.3S.. +001 4.30.. +001 0.35 7. 3ge-00S 2.3&.. +001 4.20.. +001 0.3S 7.40.. -00&

2.35.. +001 4.30.. +001 0.35 '1.41.,-005 2.35.. +001 4.30.. +001 0.25 7.41.. -005 2.25.,+001 4.30.. +001 0.25 7. 42e-005 2.35.,+001 4.ale+001 0.35 7. 43.,-00S 2.35.,+001 4.31.,+001 0.3S 7. 43e-005 2.35.. +001 ".31.. +001 0.35 7.4'1.,-005

2. 35e+001 4.21.. +001 0.3S.7.4Se-005 2.35.. +001 4.31"+001 0.35 7. 45e-005 1.&000 0..

7.39.. -005 7.29.,-00S 7.40.. -005 7.41.. -005 7.41.. -005 7.42.. -005 7.43.. -00S 7.43.. -005 7.44.. -005 7.45.. -005 7.45.. -005

.. /t-hIL 0.17S1 0.29 o.17S1 0*.29 0.1752 0.29 0.1'1113 0.29 0.1'54 0.29 0.1754 0.29 0.17S5 0.29 0.1756 0.29 0.1'15'1 0.29 0.1'57 0.29 0.1758 0.29 Pa.ge: 3 Page B-4 ofB-8

V Structural Integrity Associates, Inc.

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'1.01.. +001 2.47.. +001. 4.54.. +001 0.35 8.33~-005 8.33e-005 0.1115'1 0.31 0.35 8.34,.-005 B.34,.-005 0.185'1 0.31 0.35 8.34,.-005 8.8... -005 0.11158 C.31 0.35 8.aSe-00s 8.~5e-005 0.18S~ C.31 0.35 11.36.. -005 8.36.,-005 0.18E 0.31 0.35 11.37.. -005 II. 37e-00S O.leel 0.31 0.35 8.37.. -005 8.37.. -005 0.1862 0.31 0.35 1I.3e.. -001i 15.alle-005 0.1863 0.31 0.35 1I.3h-005 11.31.,-005 0.11U13 0.3i 0.35 8.40.. -005 !l.40.,-005 0.le64 0.31 0.35 lI.n.. -OOIi 8.41.. -005 0.1865 0.31 0.35 8.41.. -005 !l.n.. -005 0.186e 0.31 0.35 8.U.. -001i B.42.,-005 0.186'1 0.31 0.3S lI.n.. -005 15.n.,-005 0.186B 0.31 0.35 11.44.. -005 B.n.. -005 0.1116a 0.31 0.35 1I.4l1e-001i 8.t5.. -005 0.le61 0,31 0.35 1I.4Se-00S 8.45.. -005 0.18'1 0.31 0.35 B.U.. -OOS B.46.. -005 0.18'11 C.31 0.35 8.47.. -005 8.t7.-005 0.11172 0.31 0.35 11.48.. -005 8.t15.. -005 0.18'13 0.31 0.35 8.49.. -005 8.U.,-00S 0.11173 C.31 0.35 B.4h-005 8.49.. -005 0.1874 0.31 0.35 8.50.. -005 B.50.-005 0.18'15 0.21 0.3S 8.51.,-005 B.51.. -005 0.18'1£ 0.31 0.35 8.52.,-005 8.5Z.. -005 0.18'17 0.31 0.25 8.53.. -005 B.53.. -00S 0.111711 0.31 0.35 8.5a.,-005 II.Sa.. -005 0.18'19 0.31 0.35 11.54.,-005 B.5.... -005 0.18'19 0.31 0.311 S.5l1e-005 8.55e-00S O.lSe 0.31 0.35 8.56.. -005 B.S6.. -005 0.1881 0.31 0.35 8.57.,-005 B.57.-005 0.1882 0.31 0.35 8.57.,-005 B.57.. -005 0.18S3 0.31 0.35 a.58.. -005 8.SB.. -005 0.11184 0.31 0.35 8.5h-00S 8.59.. -005 0.1885 0.31 0.35 8.60.,-005 8.6il.. -005 0.1885 0.31 0.35 8.61.. -005 8.61.. -005 o.18se 0.31 0.35 8.61.. -005 11.61.. -0011 0.11187 0.31 0.35 S.62.. -005 8.62.. -005 0.1888 0.31 0.35 8.63.-005 lI.n.. -005 0.1889 0.31 0.:15 8. 64e-005 B.64e-005 0.189 0.31 0.311 lI.fiSe-OOIi 8.65e-005 0.18111 0.32 0.35 8. 66.. -001l 8.66.. -005 o.lUl 0.32 0.35 S.66e-OOli 15.tifi.. -OOS 0.18t2 0.32 0.25 8.67.-005 8.6'1.. -005 0.18n 0.32 0.35 II. 68.,-001i 8.68.,-005 O.lUt 0.32 0.35 1I.61e-001i 11.119.. -0011 0.lS9S 0.32 o.as 8.70.. -005 8.70.,-005 0.1896 0.32 0.35 8.71.. -005 B.'11.. -005 0.18117 0.32 0.35 8.71.. -005 11.71.. -005 0.1898 0.32 0.:15 8.n.. -005 8.72.,-0011 O.lUe 0.22 0.3S 8.73.. -005 8.73.. -005 0.18U 0.22 0.35 8.. 74.....,005 11.74.,-005 O.H 0.32 0.25 8.75..-005 8.75.. -005 0.1901 0.32 0.3S 1I.'16e-005 8.76.,-005 0.11102 0.32 0.35 8.7.6.. -005 8.'16.. -005 0.1903 0.32 0.35 8.77.. -005 8.'1'1.. -005 0.lB04 0.32 0.35 8.78.. -005 8.78.. -005 0.1905 0.32 0.35 8.7h-005 8.79.. -005 0.1905 0.32 0.35 8.80.. -005 e.'80.. -0oS 0.19015 0.32 0.35 8.111.. -005 8.81.. -005 0.1907 0.32 0.35 8.81.. -005 B.81.. -005 0.190e 0.32 0.35 11.112.. -00:1 11.112.. -005 0.190' 0.32 Paq.. : t Page B-7 of B-8

V Structural Integrity Associates, Inc.

199 200 190 1.61,+002 2.43e+00I. *.54u+001 0.238 8.92e-003 B.82e-O00 0.291 0.22 199 7.01*+001 2.4$e+00I. 4.54e+001 0.88 8.84e-005 B-64e-005 0.1912 0.32 200 I.OZe+0O1 2.48e4001. 4.54e+001 0.23 e.85e-008 0.55c-005 0.91i2 0.22 End of PC-CRAM Output.

Paqe: I7 Hle No.: U0U0354.3U1 Revision: 0 Page B-8 of B-8 F0306-OIRO e Structurallntegr;ty Associates, Inc.

1ge UII '7.010+001 2.45e+llOl *. U.,+llOl 0.3& 8.S3e-005 8.83e-OD5 0.191 0.32 199 199 '7.01e+00l 2.4!1e+lllll 4.Ste+00l 0.35 8.8te-005 8.84e-005 0.1911 0.32 200 ZOO '7.0Z.. +001 2.4!1e+Olll 4.5t.,+001 0.3S e.8Se-005 8.88e-OD5 0.191Z 0.32 File No.: 0900354.301 Revision: 0 F0306-OIRO Page: '7 Page B-8 of B-8

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