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

From kanterella
Jump to navigation Jump to search
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)
v • d • e


Text

~

V Structural Integrity Structural Associates, Inc.

Integrity Associates, Inc. File No.: 0900354.301 File No.: 0900354.301 Project No.: 0900354 0900354 CALCULATION PACKAGE CALCULATION PACKAGE Project Quality Quality Program:

Program: MIZl Nuclear Nuclear [] D Commercial Commercial PROJECT NAME:

PROJECT NAME:

Perry Plant Flaw Evaluation Evaluation CONTRACT CONTRACT NO.:

55107920, Revision 55107920, Revision 3 CLIENT:

CLIENT: PLANT:

PLANT:

FirstEnergy Nuclear rirstEuergy Nuclear Operating Co.'

Operating Co; Perry Perry Nuclear Nuclear Power Power Plant.

Plant CALCULATION TITLE:

CALCULATION TITLE:

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

Preparer(s) &

Revision Document Pages Affected Revision Description Approval Checker(s)

Revision Description Approval Cbecker(s)

Revision Pages Signature & Date Signatures & Date Signature & Date Signatures & Date 0

A-i 1- 9 1-9 A-I - A-3 A-3 Initial Issue

-I *. -

B-I-B-i - B-8 B-8 "JI/~

H. L. Gustin T. J. Herrmann T. J. Herrmann 4/25109 HLG 4/25/09 TJH 4/25109 TJH 4/25/09 JI/~

H. L. Gustin HLG 4/25/09 HLG 4/25109 Page 1 of 11 11 F0306-01RO F0306-01RO

tJ Structurallntegri" StructuralIntegrityAssociates, Associates, Inc. Inc.

.Table Table of Contents

1.0 INTRODUCTION

/STATEMENT OF PROBLEM!

INTRODUCTION/STATEMENT PROBLEM/ OBJECTIVE ..........................

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

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

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

'.......................................... 4 5.0 C ALC ULA TIO N S .........................................................................................................

CALCULATIONS ......................................................................................................... 5

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

............................................................................. 6

7.0 CONCLUSION

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

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

REFERENCES ......................................................... .............................................. 8

~ ...............................................................................

APPENDIX A INSPECTION

SUMMARY

SUMMARY

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

.................................. A-i A-I PC-CRACK OUTPUT APPENDIX B PC';'CRACK ..................................................................................

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

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

Mechanics Model .................................................. 10 Figure 3.

3. Crack Growth Growth Through 200 Cycles ,....................................................................... 111..............................

File No.: 0900354.301 Page Page 2 of 11 11I Revision: 00 F0306-O0 F0306-01:

tJ Structurallntegr;ty Associates, Inc.

V StructuralIntegrity Associates, Inc.

1.0 INTRODUCTION

/STATEMENT OF PROBLEM!

INTRODUCTION/STATEMENT PROBLEM/ OBJECTIVE The N6 A, and C nozzle to safe end welds at Perry are dissimilar metal welds connecting connecting the low alloy alloy steel nozzle forgings to the Alloy 600 safe ends. The welds are Alloy 821182 [1, 2]. These 82/182 weld metal [1,2].

welds were previously ultrasonically inspected in 2001, acceptable per IWB-3500 2001, and all results were acceptable IWB-3500 criteria, requiring no further evaluation.

evaluation. The welds were re-examined during the current current refueling refueling re-examination identified two flaw indications (on each in the N6-A weld and in (RO12). This re-examination outage (ROI2).

the N6-C weld) in the Alloy 182 material which were detennined determined to slightly exceed exceed the flaw acceptance acceptance standards of standards IWB-3514-2 [3,4].

ofIWB-3514-2 of these flaw indications

[3, 4]. Both ofthese determined to be subsurface indications were detennined subsurface connection to the inside surface of the welds. They were classified as fabrication-indications with no connection indications related defects which had not grown in the intervening intervening period, but were were re-sized re-sized due to enhancements enhancements in evaluation.

data acquisition and evaluation.

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

2.0 TECHNICAL APPROACH APPROACH OR METHODOLOGYMETHODOLOGY mechanics-based evaluation of the flaws is perfonned A fracture mechanics-based performed per the requirements ofIWB-3600 of IWB-3600 considering weld residual stresses present in the welds following the application of a mechanical mechanical stress improvement process improvement process (MSIP).

(MSIP). The observed observed flaws are assumed to be growing growing due to a fatigue crack growth mechanism.

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

maintained.

3.0 ASSUMPTIONS ASSUMPTIONS / DESIGN INPUTS

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

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

2. In a previous calculation performed by SI [1],

calculation perfonned [1], finite element analysis oftheof the nozzle-safe nozzle-safe end welds was perfonned performed to determine detennine the weld residual stresses present in the welds following the application of a mechanical improvement process (MSIP) in 1992. The bounding residual mechanical stress improvement residual stress distribution is shown in Figure 1, taken from 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 compressive to tensile (perpendicular (perpendicular to the plane of the crack) through the thickness of the weld. In the present calculation, calculation, the weld residual stress is conservatively conservatively taken to be the maximum tensile from that distribution, and is considered considered to be a constant membrane membrane stress across the weld weld File No.: 0900354.301 0900354.301 Page 33 of 11 11 Revision: 0 F0306-01 F0306-01

l) Struelurallntegrity StructuralIntegrityAssociates,Associates, Inc. Inc.

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

3. The N6 nozzles are assumed to experience
3. 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 inspection in 2019, the estimated number of such current refueling outage until the next scheduled inspection combined combined cycles is assumed to be less than 100 (49 cycles cycles reported from 2001 through April 2008

[5]). For additional additional conservatism conservatism in the event that the number of cycles increases significantly 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 flaw indications indications are scheduled scheduled to be re-examined re-examined (10(10 year inspection 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 combination PL+PB+Q PL+PB+Q includes significant includes significant bending stresses in the PB and Q terms, and treating bending stresses as membrane membrane is is conservative.

conservative.

6. Since all reported reported flaws are subsurface subsurface with no connection to the weld inside surface or to the coolant chemistry, the intergranular intergranular stress corrosion corrosion crack (IGSCC) growth mechanism is not active. This mechanism requires reactorreactor water chemistry to be present in the crack.

7.., The fatigue

7. "The crack growth fatigue crack growth law law for for Austenitic Material in Air was taken from ASME Section Austenitic,Material Section XI, Appendix C [3]. Since the flaws are subsurface

, Appendix subsurface and not wetted, the air law is appropriate.

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

4.0 FLAW CHARACTERIZATION CHARACTERIZATION A total A total of of 88 flaws flaws were identified in were identified in the the Reference Reference [4]

[4] inspection reports.

inspection reports.

N6A - Flaw Indication Indication 1:1:

Length: 1.5",

Length: 1.5", Through wall dimension:

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

Length: 1.2",

Length: Through wall 1.2", Through wall dimension:

dimension: 0.2", Separation from outside Separation from outside surface: 0.3" surface: 0.3" N6A - Flaw Indication 3:

Length: 2.0",

Length: Through wall 2.0", Through wall dimension:

dimension: 0.15", Separation from 0.15", Separation outside surface:

from outside surface: 0.4" 0.4"

, File No.: 0900354.301 0900354.301 Page 4 of 1111 Revision: 0 F0306-01' F0306-0J:

( ; Structural V Structurallntegr;ty Associates, Inc.

IntegrityAssociates, Inc.

N6A N6A -- Flaw Indication 4:

Flaw Indication 4:

Length: 0.85",

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

Flaw Indication 1:

Length: Through wall Length: 1.9",Through 1.9", dimension: 0.1",

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

Flaw Indication 2:

Length: 3.7",

Length: Through wall 3.7", Through dimension: 0.25",

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

Flaw Indication 3:

16.6", Through Length: 16.6",

Length: Through wall dimension: 0.3",

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

Flaw Indication 4:

Length: 1.9", Through wall dimension:

Length: 1.9", Through wall dimension: 0.2", Separation from 0.2", Separation outside surface:

from outside surface: 0.35" 0.35" From the review From the review of ofall all of the above ofthe above indications, there are indications, there are two subsurface flaws two subsurface requiring further flaws requiring further evaluation [4],

evaluation [4], which which will be identified will be furthermore as identified furthermore as Flaw Flaw I1 and Flaw 2.

and Flaw 2. One One ofofthese located in these isis located in the the N6A weld, and one is located in the N6C weld. These flaws are N6A weld, and one is located in the N6C weld. These flaws are characterized as follows: characterized as follows:

Flaw 1 (N6A):

Flaw (N6A):

1.5", Through Length: 1.5",

Length: Through wall dimension: 0.35",

wall dimension: Separation from 0.35", Separation outside surface:

from outside surface: 0.3" 0.3" Flaw 22 (N6C):

Flaw (N6C):

Length:

Length: 16.6", Through wall 16.6", Through dimension: 0.3",

wall dimension: 0.3", Separation Separation from outside surface:

from outside surface: 0.35" 0.35" From the From indications, aa single identified indications, the 88 identified worst case single worst flaw was case flaw determined that was determined bounds all that bounds all of ofthe the flaw flaw indications for future inspections. This was done in consideration indications for future inspections. This was done in consideration of future UT technology of future UT technology improvements which improvements which could result in could result identifying additional in identifying connected flaws additional connected (such as flaws (such as occurred occurred fromfrom thethe 2001 data 2001 data to currerit dimensions).

to current dimensions).

The inspection summary The inspection sheets for summary sheets for these flaws [4]

these flaws [4] are attached as are attached Appendix A.

as Appendix A.

5.0 5.0 CALCULATIONS CALCULATIONS The SI The SI fracture mechanics program fracture mechanics pc-CRACK [6]

program pc-CRACK [6] was was used used to perform the to perform the crack growth calculations.

crack growth calculations.

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

flaw characterizations above (see assumption 1) was taken as: Length:

Length:

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

This flaw was This flaw was used used as the starting as the point for starting point for the fatigue crack the fatigue crack growth calculation. The growth calculation. The center-cracked center-cracked plate model was used to represent the flaw geometry for the crack growth calculation. This plate model was used to represent the flaw geometry for the crack growth calculation. This is is illustrated illustrated in Figure in Figure 2. This model

2. This treats the model treats the modeled modeled flawflaw as infinitely long as infinitely long inin the depth direction (into the the depth direction (into the page page in in Figure 2). This model effectively represents the assumed full Figure 2). This model effectively represents the assumed full circumferential flaw. circumferential flaw.

File File No.:

No.: 0900354.301 0900354.301 Page 55 of Page of 11 11 Revision:

Revision: 00 F0306-01 F0306-0J

tJ Structural Associates, Inc.

IntegrityAssociates, StructuralIntegrity Inc.

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

{PL+PB+Q+RESIDUAL}

and the Kmin is taken as RESIDUAL.

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

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

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

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

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

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

The cross sectional of the weld without sectional area ofthe without flaws is A= t(OR2-IR A=1t(OR -IR22)=T(49.87-33.78)=50.55

):::::1t(49.87-33.78):::::50.55 in2 [7]. So So the reported reported flaws in N6A represent represent approximately 1% 1% of the total area ofthe of the weld. The flaw in N6C represents 9.9%

9.9% of the total area. Removing that amount of material in either either weld would increase the stress in the remaining material by the same %.  %. All ASME Allowable Allowable stress limits as reported in [2] [2]

continue to be met after projected projected flaw growth up to an increase of more than 25%. Even if the ifthe conservatively evaluated conservatively evaluated full circumferential 27E(5.8125 + 0.55) = 14.63 in2 were used, circumferential flaw of 0.366 x 21t(5.8125 this would be 29 % of the area section, section, with a projected of less than 0.02", significant margin is projected growth ofless provided provided to primary stress limits. .

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

membrane stress intensities [8], ..

sheet 13 of 18 to be 11158 psi for normal and upset conditions.

conditions. The same page notes that any bending bending stress intensities are very small. The allowable allowable stress intensity intensity for the Inconel material is reported on the same page as 23300 23300 psi. The primary stress intensity intensity ratio (Pm+Pb)/Sm is then equal equal to 0.48. The largest observed largest approximately 16 inches, and the circumference observed flaw has a length of approximately circumference of the component component at the flaw location is approximately approximately 44 inches, so the ratio of flaw length to circumference circumference is 0.36, which will be rounded to 0.4. Referring to ASME Section XI, 1989 1989 Edition, Table IWB-3641-5, IWB;.3641-5, it may be seen that for a stress ratio of 0.48 (i.e.,

(i.e., less than 0.6) and a flaw length/circumference length/circumference of 0.4, the allowable allowable end of interval flaw depth (2a for a subsurface subsurface flaw) is 0.6 alt.a/t. This value is much greater than File No.: 0900354.301 0900354.301 Page 6 of 11 11 Revision: 0 F0306-01O F0306*01

t} Struclural Associates, Inc.

IntegrityAssociates, Structurallntsgrity that of that limiting flaw the limiting ofthe flaw of Therefore, the 0.366/1.2=0.305. Therefore, of 6.366/1.2=0.305. flaw is limiting flaw the limiting acceptable by is acceptable by the the methods methods ofIWB-3641.

QfIWB-3641.

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

7.0

7.0 CONCLUSION

S AND CONCLUSIONS AND DISCUSSIONS DISCUSSIONS presence of The presence The ofthe two reported the two subsurface fabrication reported subsurface defects and fabrication defects their projected and their growth due projected growth to fatigue due to fatigue does reduce the not reduce does not capacity of the capacity welds in the welds ofthe in N6A N6A and Code [3]

below Code and CC below allowable. The

[3] allowable. limiting flaw The limiting flaw shows no shows growth in significant growth no significant through wall the through in the direction, as wall direction, compared to as compared to the the 2001 results as 2001 results as re-re-evaluated last October [5]. This supports the conclusion that the observed indications are in fact evaluated last October [5]. This supports the conclusion that the observed indications are in fact defects. The fabrication defects.

fabrication projected out evaluation isis projected The evaluation out for more than for more 10 years, than 10 allowing the years, allowing station to the station to maintain the maintain current 10 the current 10 year year inspection interval. All inspection interval. All Code margins are Code margins are maintained.

maintained.

No.: 0900354.301 File No.:

File 0900354.301 Page Page 77 ofof 11 11 Revision: 00 Revision:

F0306-01:

F0306-0r

l) Structural V IntegrityAssociates, StructuralIntegrity Associates, Inc.

Inc.

8.0

8.0 REFERENCES

REFERENCES

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

Heat RemovallLow (RHR/LPCI)

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

2. CB&I Stress Report "238" "238" BWR Vessel" Vessel" Section S-13 sheet 2. SI File Number 0800439.216 SIFile 0800439216
3. ASME Section XI, 1989 Edition and 2001 Edition with Addenda Addenda through 2003
4. GE Flaw Inspection Reports APR-09-209-7 APR-09-209-7 (weld IB13-N6A-KB) 1B13-N6A-KB) and ARP-09-209-9 ARP-09-209-9 (weld IB1B 13-13-N6C-KB). SI File 0900354208 0900354.208
5. SI Calculation Calculation 0800439.307R1, 0800439.307Rl, Evaluation Evaluation of fabrication defects in N6A and C Nozzle to Safe Safe End Welds.
6. SI Program "pc-CRACK for Windows", version 3.1-98348 Program "pc-CRACK 3.1-98348
7. CB&I Drawing N6 Nozzle Nozzle Forging Forging (RHR-LPCI MODE),"*CBI MODE),"CBI VPF No. 3521-257, 3521-257, Rev. 1, June 1973 1973 SI File 0800439.208 0800439.208
8. CB&I Stress Report "238" "238" BWR Vessel" Vessel" Section Section D-13 sheet 13.

13.

File No.: 0900354.301 0900354.301 Page Page 8 of 1111I Revision: 0 F0306-01:

F0306-01

~---

lJSStubtraml Associats, Inc.

IntegrityAssociates, Structural/nleurily Inc.

Path 1 Axial StressesStresses (SY) (SY) 4*0000 60000

,GOOW 40000 2 0000

-+-Ilon-"",air

_ NCPl 0 _CO Cod Ca ldl I I

I --MSgPO#4 M IP O"

-!t"- 1IiI ' POf'

-20000

- - NCP2

-..,- (;.0 Id I

-o00

-. 0 000

-8"000 0 0,2 04 04 I

0.4 00.3 1I L2 14 DMtIll from W.Jd 044mw kms VAN 111 M ' 5I.IIrbee Isaw Surw* On.) ft .)

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

(PSi)

No.:.. : 0900354.301 File No Page 9 of 11 11 Revision:

Revision: 0 F0306 ..01 :

F0306-01

lJ Structural IntegrityAssociates, Structural/ntegrity Associates, Inc.

a =C. .

1 1 1 L. ra b ..

~

1t I..a~

- ~I REQUIRED REQUIRED INPUTS:

INPUTS:

b: plate half width b: plate vvidth maxim.un crack a:a: maxinm (8max << 0.91b) depth (a.

cmck depth O.9b)

I , ,F Figure 2.

Figure 2. Center-Cracked Fracture Mechanics Plate Fracture Center-Cracked Plate Mechanics Model Model No.: 0900354.301 File No.:

File 0900354.301 Page 10 of Page 10 of 11 11 Revision: 00 Revision:

F0306-01 F0306-0r

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

brack Gnrwt

,.: <!; 0,1V92 -

092881 01866'

____ i~~;~;~.'1:1/2 i~L2~A~ I *j-: 4 A2- -A

-~:__ _

V.-.,>

0 20 40 60 80 l~oo" .120 '140 160 ý18 200 Figure 3-Crack Gr,owth Through 200 Cycles File No.: 0900354.301 '- -' ..---

Page 11 of 11 Revision, 0

  • ~F0306-01

e Structural Structural IntegrityAssociates, Associates, Inc.

Inc.

APPENDIX APPENDIX A A

INSPECTION INSPECTION

SUMMARY

SUMMARY

SHEETS SHEETS FROM FROM [41

[4]

File No.: 0900354.301 File No.: 0900354.301 File No.: 0900354.301 Page Page A-A-II of ofA-3 A-3 '

Revision:

Revision: 00 F0306-01 RO F0306-01RO

l)

V Siructuralinlegr;ty StructuralIntegrityAssociates, Associates, Inc. Inc.

HITACHI I I HrrACHI Austenitic Piping Austenitic Piping Flaw Flow Evaluation Sheet Sheet 1'nI#Kt: I'eny k*ct: Pe"y Unit l 1 MIWcIID: 1813-N6A-KB

~uidID: 18ll-N6A-1<8 EllamOalo BurnDatagbemt: ....: Af'-09-209O7 APR-09-Z09-07 Inidkcag Indication:: 1 I S1ugData SIIIng 0aI0 .Anet: . . . : N/A N/A tfIII8a:d B!IImIfIIt tfIIIIIlIIf B!IIKIIfIIt Felw l/mwh Wall . 0.346 o.J46 0.35 .,. nominal.

"rTrmbtd- LlZ 1.12 Ll 1.1 FEA.L&Wt T. 1.53  :.5 L5 .,.-.1.

T'10mmu,,. LZO 1.20 1.2 L2 Swfab pSmWen"'r = 0333 0.333 03 0.3 rm*M 20IB SectUion II,. 2001 fdIIIon, AS#E SedIan ASHE 200A Mdua AddIi.da TABLE RIB-3514-2 TAMKE AMWMf USMIo6 UOInch IWB-351WAuanIIIc,..., 1.$0 hkid NomhII NW*W ~-I-w:. ThkbWU - IngevIc oA SuSum% SitMm % Surbe S.ljdam %

all

~" SUrfDcII" 0.00 10.48 10.118 sut.urfDce "

10.118 10.48 -

SUbIIII1'ucI "

o.os 0.05 0.10 0.10 10.60 lQ.60 10.88 10.B8 10.60 10,88 lOBS 10.91 10.91Y 10.91 V 0.15 0.15 10-96 10.98 10.9e 10.98 - -

0,20 020 1126 11.26 11.26 1LZ6 ~ .

0.25 . 11.38 11.J8 11.38 11.J8 ~

0.30 o.JO 0.35 o.J5.

11.58 1LS8 11.76 1L76 11.58 1LS8 1176 1L76 0.40 0.110 11.96 11.96 11.96 ~

0.45 0.50 12.46

,-12.08 1234 12.34 12 l2.D8 1234 1Z.34 - --

Allowed Alk9d AIIclwed A10w.d 10.91 1091

  • 10.91 a0 0- 0.175 0.175 value--

oil value 011 0.117 0.117 Y- 1.000 v- LOOO Row is Subsurface Flow Subsurface Alowed oft AIowed afts= 10.9%

10.996 a/t=

oft- 14.6%

11&.6'16 COMM~ft ASME Secio Xlroun run circumferential in orientation.

Indicatin is circurnfenIntia In Flaw Is W=Cmcpzb.b orientation rformed In xd T"

a*y S-35,4-L.

wfth WA-3200 -tpe w4 M E29. E29.

mw"W71"~

Subsurface bsu ce Planar Planar faw flow per IYIA-33ZO IWA-3320,* 1Y14-3320-1 WW,.3320-1 By: ~An:.:::d~re"-!*ROChoI=~~_-=.:::;..--...:._

EvoIuotedLevdQW By: ROC9064 Dote 9* JReviewed By. Earnest Caon LeveI:..::.II Levet 11_ __ Date 31Z912OO9 Dote: 3/29/2009 ILevek LeYeI:.:::III III_ __ Date 3/2912009 Dote: 3/29/2009 Poge 22 of 255 vwow3Nr0i File 0900354.301 No.: 0900354.301 Page A-2 of A-3 A-3 File No.: 0900354.301 Page A-2 of Revision: 0 F0306-01 RO F0306-0IRO

tJ Structural Integrity Associates, Inc.

V StructuralIntegrityAssociates, Inc.

I Austenitic Aust..nitic Piping Piping 8' HITACHI HMCH Pn¥Kt: Perry Unit 1 Flow Evaluation Sheet Flaw Evaluation Sheet WedO. 1813-N6C-KB WiIId /0: l81J-N6C-KB flIIm 00fa st.t: APR-09-209-09 S amDataght: APR.()9.2Q9-09 dkxcatmw: 3 1ndIcaIIon: 5IIInf 00fa Sh Data st.t: ,set:NiA W/A lMm4t I1JmIr1I. ffIIIIIrCIIf ~

flow T1nugIt

"'- VAN Throup. !MIl- 0.31 0.3 0.3 "r'--"-

Trwnab . 1.12 1.1 U

FlwLmVO

"., un,tII T 1655 16.55 15.6 16.6 '"Trnmansd.

T'-.d. .20 L20 U 12 S rk swa.s.pauCfIMT- $.-

"SdPwa 0.34 0.35 0.35 A.SME e an 16 260 . Mm.. 263 Dddmda ASHE 5K1Ion ICI, 2G01 EIIIIan. ZOD3 MdIndo TABLE AudimVk SbIIIt.

IW-3S1*2 AuDIItIc TABU! 1W8-:J514.2 Sbwk UO 1.0LOh Mo Muh lnd IndI NoIIIInai Thdma - "-"Ice

'YIIIcIIr.a kmnvko oA all 0.00 0.0 0.05 0.10 0.15 sufam'%

s..tac."

10.48 10AS 10.0 10.60 10.88 10.88 10.88 10.98 sthusagtm SUIsurfaa "

10.48 l0A8 10.0 lQ.60 10.8 10.88 10.98 10.98 Srk"e %

s..tac."

10.50 10.s0 SuLmtxfos S 10.50 10.s0VV 1126 1126 1126 1126 -

0.20 025 1llS 11.38 IUS 11.38 0.30 1258 11.58 11.58 11.58 0.35 1176 11.76 1.76 11.76 -

0.40 11.96 11.96 11.96 11.96 -

0.45 o.so 0,50 12.06 12.oa 12.34 12.34 12.08 12.08 12.34 l2.34 Aflavd Alwed AIbwd AIkMecI 10.0 10.s0 10.50 10.s0 a=

0= 0L150 0.150 011vake:- 009 a/lvuIue-V.

0.009 1.000 V_ LOOO Flow is Flaw isSubsurface Subsurface Allowed alt-AlawedaJt- 10.5%

10.5" aIt-aft - 12.5%

125" law b-wuMhCtm FlalrIsUl' ....... by by Tallie TOM@ MW'-3m1-1W8-351W.

_>mIOl F.*dvm om ASHE ecn ru itASI4E ngifoedm-acodn 1110 WA-U andA t 11W""3200 andASTliirm. n IndIaItian is In SubSwdoC Planar flaw Pona Haw WDel' 1W""3320

!#A-3320 , 1W""332G-l rWA-3320-1 jEvaluated

ýMouated By. RadIal Andre' Rodid By AandrW

().A..,'

tl /.....77 Ch' Revee By:

ReIIiewed Bly.______ ~~

Levek 11 level: II Date:

Data: 3/28/2009 3/28/2009 IILevek l8ve/; III III Daft 3/28/2009 Date: 3/28/2009 Pogoi23Of24 Z3 Of Z4 P,6=OC -3fERIO File No.: 0900354.301 No.: 0900354.301 Page A-3 of A-3 File Revision: 0 F0306-01RO0 F0306-01RO

l) Structural Integrity Associates, Inc.

C StructuralIntegrityAssociates, Inc.

APPENDIX B APPENDIXB OUTPUT PC-CRACK OUTPUT 0900354.301 File No.:

File No.: 0900354.301 0900354.301 Page B-B-11 of B-8 B-8 Revision:

Revision: 0 F0306-OIRO F0306-01RO

lJ Structurallntegfity Associates, Inc.

V StructuralIntegrity Associates, Inc.

Structura~

pc-CRACK pc-cv=

VersioD (C) Copyri9ht (C) structural IDteg:ity t=

Copyright 'et fo%"

fazt Windows Version 3.1-98348 3.1-90345 Integrity ~soci Windows

'54 - 'S8 "ge Amsociates.

. . .s, IDc.

Inc.

3315 2215 ~deDA*laden EXpressway.

Expressway, Suite S~ite 24 24 Saa San Jose, Jose, CA CA 98118-1557 95115-1537 Voice: 405-970-0200 408-878-8200 Fax:

Fam: 40B-978-8ge4 408-978-5944 E~i~:

E-uail: pccrack szuctint.cc=

pccrackistructiAt.CaD Linear Elastic Fractuxe Mechanics Date: Mon nate: Hon Apr oe 0 17:22:12 2009 17:22:13 Input Data ;md Input and lI.esul"s Results f"ile:

rile: F._PLP=.LrK PY_PLPlIQ.LlM 0900354: Pe%ry

Title:

0800354:

Titl.: Przzy )IEA NeA and and NGCNeC rlawFlaw Evaluation Cases:

Load Cases:

Stress Stress CoefficieDts Coefficient*s Case ID CO C1 Cl C2 C3 C2 Type Type Unit lfembr ODit membrane...... 10 10 o0 o0 o0 Coeff Residual lI.e .. idual CoConzat

.... " 20 o0 o0 o0 Caeff Coeff

Through Wall

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

Stress Coeff -------

Wall

.al~

Depth Depth c......

Case Unitt M*uabr UDi Heoabr lI.eaidual C Residual Case Ca**

0.0000 0;0000 10 10 20 0.0200 0.0301) 10 10 20 o.oeoo 0.0600 10 10 21) 20 0.0900 0.1)900 10 10 20 20 0.1200 10 10 20 20 0.1500 10 10 20 0.1300 0.1800 10 10 20 20 0.2100 0:2100 I0 10 20 20 0.2400 0.2"1)0 10 10 20 20 0.2700 10 10 20 20 0.3000 10 10 20 20 Crack Model:

Crack HDde~: CenterCeaner Cracked Cracked Plate P~ate UnderUDder Renowe

~e Tension Stress T ..... ion Stres ..

Crack Parameters:

Para.e~e%D:

Plate Plate Halt Width:

Bal£ Width: o.eooo 0.6000 Crack depth:

Crack depth: 0.2000 0.3000 Co CD == RmAote Tension Re.ote Tenaion St~eD5 Stress All

~l a~hez other stress coe£ficieutD are neglected.

B~zeDS coefficients Deg1ccted~

~-----StreBs -- Stress IDte .... ity Factor-Intensity -

Factor--------------------

Crack Crack Case Case Case C:ase size Siae Unit MeHmbr UDit Hembr Residual Re .. idua~ C c:

0.0060 1.37302 1.27302 2.74604 2.74604 Paqe: 1 Page:

File No.:

No.: 0900354.301 0900354.301 Page Page B-2 B-2 of B-8 ofB-8 Revision: 0 F0306-OIRO F0306*0IRO

C tJ Structural/ntegr;1y StructuralIntegrityAssociates, Inc.

Associates, Inc.

0.0120 1.942011 1.94209 3.88417 3.18417 0.01110 0.0150 2.27926 2.37926 4.7&IIS3 4.7 853

5. 49695 0.0240 2.74848 Z.74548 5~49US
6. 14906 0.0300 0.0200 2.01745 3.07453 6.14906 0.0360 0.0260 3.37018 2.23015 e.74026 15.740315 0.0420 3.64303
2. 64202 7. 25605 7.2860S 0.0480 0.04110 3.B9804 2.59804 7.7960B

'1.7960B 0.OS40 0.0540 4.U8n 4.12869 8.2'1'73B 8.27725 0.0600 4.36752 4.28752 8.73503 B.72502 0.0660 4.SBf45 4.5845 9.1'1291 9.17291 0.0720 0.0720 4.79701 4.79701 9.59403 0.07!\)

0.0750 5.00041 5.00041 10.0008 10.0005 0.OB4\)

0.0540 5.111763 5.19763 10.3952 10.3953 0.0900 2951 5.311951

5. 10.779 0.0960 0.0960 5.57675 5.57675 '11.1535 11.1525 0.1020 0.1020 5.75n5 5.75995 11.5199 0.1080 0.1050 5.9311414 5.92964 11.5792 11.!793 0.1140 8.11628 6.11E211 12.2326 0.1200 6-29028 6.2902e 12.5806 12.SII06 0.1260 0.12150 6.462 8.462 12.924 0.1320 0.1220 8.6217a 6.631711 12.2626 13.2U6 0.13BO 0.1250 6.79992 13.59911 13.5995 0.1440 li.!l6671 6.96671 13.9334 0.1600 0.1500 7.U24 7.1324 14.2648 14.2645 0.1560 0.lS60 7.29724 14.5945 14.8945 0.1620 0.1620 7-48146 7.4U46 14.9229 14.9229 0.1650 0.1680 7.e2527 7.62527 15.2505 15.2505 0-1740 0.1740 7.788ell 7_75889 15.5779 15.S778 0.1500 0.1800 7.1152S1 7.95251 15.905 IS. 905 0.1560 0.1860 5.11622 1I.11ea2 16.2326 111.2326 0.1920 0.1920 .m20052 B.2B053 16.5611 16.sell 0.1950 0.1980 . 44521 B.44531 16.5906 16.81106 0.2040 0.2040 8. 81084 17.2217 B.U084 17.2217 0.2100 B.77732 0.77722 17.5546 17.SS46 0.21150 0.2160 8.114U 8.9449 17.5898 17.81!98 0.2220 0.2220 9.11379 18.2276 18.2276 0.2280 0.2250 9.28416 1I.2B4115 16.5692 18.5683 0.2340 9.4562 9.45152 18.9124 18.91%4 0.2400 9.62009 9.630011 19.2602 0.2460 0.%4150 9.80602 9.B0602 19.612 0.2520 9.9842 9.9B42 19.96584 19 .11684
0. 2550 0.2580 10.1648 10.164B 20.3296 20.32S15 0.2640 0.21540 10.2481 10.3481 20.6962 0.2700 10.5242 10.5342 21.06B4 21.0684 0.2760 0.27110 10.7225 10.7235 21.4469 21.44159 0.2520 0.2B20 10.916 10.lIle 21.822 0.2880 0.2550 11.1121 11.1121 22.2242 0.2940 11.2121 11.3121 22.6241 22.11241 0.2000 0.3000 11.5161 23.0222 23.0322 Crack Growth Lawa:

Gr~h Lawn:

, L .... ID:

Law ID: Sect XI hus Sect Aus Air Air, Model:

Hadel: ASHE Section XI XI -- anstenitic stainless steel agstenibic abainleas in air environment steel in enyiro~t da/dX = C - 10^F

  • 5 k dKI3.2 where S == 1.0 1.0 for for R << 0 1.0 + 1.8

= 1.0 1.6 ** R II fDr for 0 << II < 0.79 3 <

-42.5 +

-43.5 + 57.97 ** a3 fDr for 0.79 < a3 < 11 0.'19 F

r = code specified specified func*ion function t14umeratuxe of temperature P~age: 2 P'"'I": 2 File No.: 0900354.301 Page B-3 ofB-8 of B-8 Revision: 0 F0306-OIRO F0306-OIRO

t>

V Structurallntsgrity Associates, Inc.

StructuralIntegrityAssociates, Inc.

dR =

dK = J:.aa FmaR - l.'tm:i1l lad, a

A = = ltIaill rain  !/ ~Kmax wbe~e:

where:

C C

  • 10~rl OF =

= ,.840ae-010 1.Bt03e-010

~.

is fo~for ~ the CUE~eA~ly currently 8elec~ed Selected uni~. units of:

farce: Up fa~ce: kip length; ;Lach length: inch

~empera~w:e:

temperature: 550.

550.00000000 FFahrenheit

..hr..ah.. .i~

material Fracture Toughness Ric:

Material Ka~e~~a1 ID:

MD: Alloy l8Z 182 Depth RIC lac 0.0000 Z00.0000 200.0000 0.8000 O.SOOO Z00.0000 eOO.OOClO 1.0000 1.0000 Z00.0000 eoo.OOOO 1.5000 1.5000 200.0000 eoo.OOOO Inltial Ini~~al crack .i.e:

crack siuze 0. *1780 Cl.1750 Man. crack a~.e=

Max. sire= [.3000 0.3000 Number of blocl

!lumber blockse ..,= 1 PrzLn incrtement of blocit='

P:d.,,~ .iz>=_nu block- 11 Cycl ....

Cycles C .. l.c.

Calc. Pr.iD~

Print Crk. <Ont.

CEIl.. Gzw. Kat..

Mat.

Subblock SubbJ.ock !Ti_

/Time incre.

incZ'e~ incre. Law il1c:re. !.a" ttIc KIc Per:ryl p.,rryl 200 200 11 1 Sect Sec~ Xr ,us XI Au .. Air hE Alloy Al.l.oy 182 182 lma lain Subblock SubbJ.ock C.....

Case ID baa ID Scale Seal.. ract.or Factor C ltIain

.. oe ID Scale Case Scal.. ract.or Factor Pe*ryl Perry! Residual llesidu.a1 Conat Const 1.6000 1.5000 Residual lleaidua1 Conet Const 1.&000 1.5000 Unit.

tJD:L Membrane Co ltc.brAfte 5.5000 6.5000 er..

Crack cIL gronh 9Z~b rresults: ...,ul.tts:

Total TDt. ..l Subblock Subblock Cycles ... Cycles D..Dn Cycl

/Tie

/TDIr!. /Tlime Cycle ..

/TDIr!. mos b in lRain Del~

DeltaK R R

DaDn ID ..Dt.

/DaDt Da 0.. ..

a a/thk

.. /t-hIL Bl.DCIL:

Block: 1 7

1 1 6. 64e+001

~.64e+OCl1 22.34e+001

.34e+001 4.20e+001 4.30 ..+001 0.25 0.3S .39e-005 7.39 .. -00& 7.29e-005 7.39.. -005 0.17S1 0.1751 0.29 0.29 22 2 6. GSe+O01 6.1!.5e+ClCll 2.

2.3S a5e+001

.. +001 4. 20e+001 4.30 .. +001 0.28 0.35 7. 3ge-00S 7.39e-005 7.29.,-00S 7.29e-005 7

o .17S1 0.1751 0*.29 0.29 3 6.

3 6.6S 68e+001

.. +001 2.

2.3& 28e+001

..+001 4.30e*001 4.20 .. +001 0.25 0.3S 7.40e-006 7.40.. -00& .40c-005 7.40 .. -005 0.1752 0.29 0.29 4..

55 4 6. 65e+001 5

G.e5e+001 52 aE.I!S -5es+001

.. +OOl 2.

2.35 35e+001 2.25e+001

..+001 2.35..+001

4. 30e.001 4.30 ..+001 4.20e+001 4.30 ..+001 0.25 0.35 0.28

'1.41.,-005 7.41e-008 7.41e-005 7.41 .. -005 7.41e-005 7.41.. -005 7.41 .. -005 7.4le-005 0.17532 0.1'1113 0.1784 0.29 0.29 0.25 0.1'54 0.29 0.29 6 6a E.ESe+001 E.E5e+001 22.25.,+001

.25e+001 4.20e+001 4.30 ..+001 0.28 0.25 7.42e-005

7. 42e-005 7.42.. -005 7.42e-005 0-1754 0.1754 0.29 0.29 "7

7 '17 6.65e+001 2.35e+001 2.35.,+001 4.21e+001 0.25 7

E.65e+00l 4.ale+001 0.35 7..42e-005 43.,-00S 7.4te-005 7.43 .. -00S 0.1755 0.17S5 0.29 0.29 8II B G.E6e+001 6.E6e+OO1 2.25e+001 2.35.,+001 4.21e+001 4.31.,+001 0.25 7.42e-005

7. 43e-005 7.43e-005 7.43.. -005 0.3S 0.1756 0.29 0.29 9 9 6.66e+001 2.

2.35 25e+001

.. +001 4. 81e+001 0.25 7.44e-005 7.44e-005 0-1757 9 9 6. 66e+00l ".31 ..+001 0.35 7.4'1.,-005 7.44 .. -005 0.1'15'1 0.29 0.29 10 10 6. 66e+001 2.

10 10 6.E6e+001 2. 35e+001 35e+001 4.21e+001 4.21 .. +001 0.25 0.3S ?4e--005

.7.4Se-005 7.45e-005 7.45 .. -005 0.1'57 0.1757 0.29 0.29 11 11 6.96e+001 2.35e+001 4. 21e+001 0.25 7.48e-005 7.45e-005 11 11 6.e6e+001 2.35 .. +001 4.31"+001 0.35 7. 45e-005 7.45.. -005 0.1758 0.29 0.29 Pa.ge: 23 Page:

File No.: 0900354.301 Page B-4 of B-8 ofB-8 Revision: 0 F0306-01RO F0306*01RO

tJ Structural V Structural Integrity Integrity Associates, Associates, Inc. Inc.

12 12 12 6.664+001 6.6&..+001 2.:5&+001 2.3&.+001 4.21:+001 4.31.,+001 0.25 0.3S 7.46:-006 7.46.,-00S 7. tee-005 0.1789 7.456-ODS o .118!i 0.29 0.2~

13 12 13 a.66.+001 6.660:+001 2.35e+001 2.<I&e+001 4.21.+001 4.31e+00l 0.25 0.3a 7.46.-00 7.4<<1e-00& 7. Ue-005 0.17 7.406-0D O.11e6 0.29 0.29 14 14 14 6.67.+001 6.<<1'1.+001 2.384+001 2.3S.+001 4.210-001 4.31.+001 0.23 0.35 7.47?-005

'I. 47e-OO& 7 ** 7 .. -005 0.17e 7.47.-005 O.11E 0.29 0.251 ll5 18 15 6.6?7+001 6.67 .. +001 2ý25e+O01 2;3& .. +001 4.31a+001 4.81e+001 0.38 0.3& 7.45e-005

'I.4I1e-00& 7.4I1e-008 0.1761 7.45e-008 0.1'161 0.29 0.2!'

16 16 18 6.67+4001 6.6'1.+001 2.38e+001 2.3&.+001 4.22.+001 4.112.+001 0.25 0.3S 7.48#-00

'I.4Ie-OO& 7.411 .. -005 0.1762 71.45.-00G 0.1'162 0.29 0.29 17 17 17 6.67.e+001 6.6'1.+001 2.33e+001 2.3& .. +001 4.22.*001 4.32e+001 0.25 0.3S 7.49.-005

'1.4h-00& 7.4ge-008 0.1762 7.49c-00O 0.1'163 0.29 0.29 ll! 18 18 6.67.+001 6.6'1.+001 2.26.+001 Z.36.+001 4.:22+001 t.32.+001 0.25 0.3& 7.50.-005 7.50e-005 7.50D-00O 7.50.-005 0.1762 0.17e3 o .2~

0.29 19 19 19 6.67.+001 6.6'1 .. +001 2.36.+001 2.315e+00l 4.22+001 4.32 ..+001 0.25 0.35 7.30e-005

'I.SO ..-005 7.50.-005 7.60e-005 0.1764 0'.1'164 0.29 0.2~

20 20 ZO 6.686+001 6.611..+001 2.36e+001 2.315 ..+001 4.22.+001 4.32e+001 0.28 0.3S 7.51e-005

'1.51e-005 7.51e-005 0.1768 7.81.-005 0.1'1e8 0.29 0.29 Zl 21 21 6.680+001

6. 68e+OOl 2.36C+001 2.<l15e+00l 4.22+001 4.32e+001 0.28 0.3S 7.82.-005

'1.5Ze-005 7.52C-005 0.1766 7.52e-005 0.1'166 0.29 0.29 22 ZZ 22 6.680+001 6.118.. +001 2.360+001 2.<l15e+00l 4.32C+001 4.3Z.,+001 0.25 0.35 7.52e-005

'1.52 ..-005 7.52 .. -005 0.1766 7.82r-005 0.1'166 0.29 0.29 Z2 22 23 6.68.÷001 6.118.+001 2.26e+001 2.36e+00l 4.22w.001

  • . :I%e+001 0.25 0.3S 7.532-005

'1.52.-005 7 .. 53.. -005 0.17e7 7.52e-005 0.1'111'1 0.211 0.29 Zt 24 Zt 6.68.+001 6.1111.+001 2.36e+001 Z.26"+001 4.32c+001 4.3Z .. +001 0.38 0.3S 7.54e-00 7.&4e-00& 7.54e-005 0.176a 7.84c-005 O.l'1ee 0.29 0.2~

25 25 Z5 6.69%e001 II. 6ge+OOl 2.36e+001 2.26..+001 4.22e+001 4.33e+001 0.25 0.35 7.54e-005

'1.S4e-00S 7.54e-005 7.5te-005 0.1769 0.1769 0.29 0.29 26 26 26 6.69.+001 1I.6ge+001 2.26e+001 2.3I1e+OO1 4.32e+001 4.2ae+001 0.25 0.35 7.553-005 7.55..-005 77.65e-005 O55e-003 0.1769 0.17U 0.29 0.29 Z7 87 Z7 6.696+001

6. 6ge+001 2.36e+001 2.36"+001 4.23e+001
  • . 33e+001 0.23 0.35 7.56.-005

'I.&6e-005 7.56.-00O 7.S6e-005 0.177 0.17'1 0.20 0.30 Zll 28 Z8 6.69e+001

6. 6ge+00l 2.369+001 Z.315"+001 4.22e+001 4.33.,+001 0.25 0.35 7.56.-005
7. 56e-005 7.86.-00O 7.Slie-005 0.17710.17'11 0.30 0.30 2!1 29 29 6.69.+001 8.l!!Ie+001 2.36e+001 2.36"+001 4.33e+001 4.33e+OOl 0.28 0.3& 7.57e-005
7. 57e-005 7.57.e-005 7.57e-005 0.1772 0.1'1'12 0.30 0.30 30 20 ao 6.69e4001 e.<<Ige+001 2.26e+001 2.36e+OOl 4.22.e001 4.33.,+001 0.235 0.3& 7.7e-005
7. 57e-005 7.57e-005 0.1772 7.57c-005 0.1'172 0.20 0.30 31 21 a1 6.70e÷001 41.'10..+001 2.36e+001 z.<lee+OOl 4.22c+001

".33.,+001 0.25 0.35 7.588-005 7.SlIe-005 7.588-005

'1.58e-005 0.17720.1'173 0.20 0.30 32 az 6.?Oe+001 32 4.3ae+00l 0.28 2.26..+001 4.33e+001 11.'10..+001 2.36.+001 0.3& 7.59.-005

'1.5Pe-005 7.59.-00D 7.SP .. -005 0.1774 0.1174 0.20 0.30 33 23 33 4.70.+001 6.70e+001 2.36e+001 2.311.,+001 4.3e.0÷01

  • . 33.,+001 0.38 0.35 7.59e-003

'1.5ge-005 7.59e-00D 0.1775 7 .5P.,-005 0.1'1'1& 0.20 0.30 at 34 34 6.7.e+001 6.70..+001 2.37.+001 2.3'1"+001 4.34e+001 4.<14.,+001 0.23 0.3& 7.60e-005 7.IIOe-005 7.6-G-DOS 7.60e-005 0.1778 0.177& 0.20 0.<10 35 25 35 6.70e+001 6.70.. +001 2.27.+001 2.37e+001 4.34O+001 4.34.,+001 0.35 0.35 7.61.-005

'1. 61e-005 7.61D-005 7.61e-005 0.1776 0.1776 0.20 0.30 36 26 36 6.70e÷001 6.70.+001 2.27.+001 2.:n.+001 4.24O+001 4.34,,+001 0.25 0.35 7.61.-005

'1.61,,-005 7.61e-005 7.61e-005 0.1277 0.17'17 0.20 0.30 37 21 37 6.71.4001 e.71e+001 2.37.+001 2.27e+001 4.34e÷001

".34.,+001 0.235 0.3e 7.62.-00 7.112e-00e 7.62.-0DS 7.6Z .. -008 0.1778 0.1'1711 0.20 0.30 ae 28 38 6.71.+001 6.71e+00l 2.37.+001 Z.37"+001 4.24e÷001 4.34.,+001 0.25 0.35 0.35 7.62.-DOS

7. 63e-005 7.62e-005 7-62r005 7.63,,-005 0.1779 7-62e-005 0.17'19 0.30 0.30 39 29 39 6.71e+001 6.71 ..+001 2.27.e+001 2.37"+001 4.24e+001 4.34.,+001 0.35 7. 63e-005 7.63e-005 0.17'790.1779 0.20 0.30 40 40 40 6.71e+001 2.37.+001 6.71e+001 2.37",+001* 4.24+001

".34.,+001 0.25 0.3e 7.645-005 7.64e-005 7.64.-005 7.64e-005 0.178 0.1711 0.20 0.30 41 41 tl 6.71.+001 6.'11e+001 2.37e+001 2.37"+001 4.24a+001 4.3.,,+001 0.23 0.35 7.685-005 7.IISe-OOS 7.65.-00D 7.6Se-005 0.1781 0.1'1111 0.30 0.<10 42 42 fo2 6.'12e+001 2.37.+001 6.72.+001 2.37e+001 4.25.+001

".35.+001 0.25 0.35 7.65e-005

'1.ESe-OOS 7.65.-005 7.65.. -005 0.1782 0.17112 0.20 0.30 43 49 41 6.72.+001 6.'I2e+00l 2.27.+001 2.37",+001 4.25D+001

".35.,+001 0.25 0.35 7.66e-005 77.66,,-005 7.66e-00O 7.66.. -005 0.1'1112 0.30 0.1782 0.30 4t 44 4t 6.72*+001 2.37.+001 6.72,,+001 2.37e+00l 4.25e+001

4. 35e+00l 0.25 0.35 .67e-005 7.e7e-005 7.67.-00O 7.67e-005 0.-1782 0.1183 0.30 0.30 45 45 45 6.72e+001 2.37e+001 6.72 .. +001 2.<17..+001 4.25e+001 4.3Se+001 0.35 0.35 7.67e-005
7. 67e-005 7.67e-005 7.67.,-005 0.178*

0.1784 0.20 0.30 46 46 46 6. 72e+001 2.27.+001 6.72.÷001 2. 37e+001 4.25e÷001

".35.,+001 0.25 0.35 7.66.-005 7.6I1e-005 7.68.-00O 7.68.. -005 0.1788 0.1785 o.ao 0.20 4? 47 47 6.72..+001 2.3.4+001 6.72.+001 2.<17..+001 4.25*+001

4. 35e+001 0.25 0.3e 7.69.-005 7.. ege-00:' 7.69e-00O 7.69.. -005 0.1788 0.1785 o.ao 0.20 48 48 48 6.73 ..+001 2.376+001 6.732.001 2.37';'+001 4.25e+001

".3Se+001 0.25 0.3S 7.69e-005 7.69.,-005 7.69.-00O 7.6ge-005 0.1786 0.1786 0.20 0.30 foB 49 411 6.'13.+001 2.27.-+001 6.72.4001 2.37.,+001 4.25e+001 4.35,,+001 0.25 0.35 7.70&-005 7.70.-005 7.70.-00D 7.70e-005 0.17e7 0.1787 0.20 0.30 50 50 50 6.732+001 6.73.. +001 2.38.÷001 Z.<l8e+00l 4.25c÷001

".35.. +001 0.25 0.35 7.71.-00D 7.71.,-00:' 7.71.-00D 7.71e-005 0.1788 0.17118 0.30 0.30 51 51 51 6.73,,+001 2.32e+001 6.72e+001 2.38e+001 4.36.+001 4.36e+OO1 0.35 0.35 7.7.e-005 7.71e-005 7.71.-00O 7.71.. -005 0.1789 0.1789 0.200.30 52 52 52 6.73.+001 2.38.+001 6.73e+001 2.38e+001 4.26.+001

  • . 3E.,+001 0.25 0.35 7.72.-005
7. 72e-005 7.72e-00S 7.72e-005 0.1789 0.1'189 0.30 0.30 e3 8a sa E.73e+OOl 2.38e÷001 6.72.+001 Z.3ee+001 4.36.4001 4*.3I1e+001 0.23 0.<1& 7.73e-0O3 7.73..-005 7-72.-00S 7.73e-005 0.179 0.179 0.20 0.30 54 54 54 6.74.+001
6. 74e+001 2.28e+001
2. <l8e+001 4.36e+001 4.36.,+001 0.35 0.35 7.73e-005 7.73.. -005 71.7.-00D 7.73e-005 0.1791 0.1191 0.200.30 55 55 55 6.74.4001 2.3.e+001 e.74e+OOl z.<le ..+OOl 4.26e+001
  • . 36e+001 0.235 0.35 7.74e-005 7.74..-005 7.74.-00O 7.74e-005 0-1792 0.1712 0.20 0.30 SCi 56 56 6.74 ..+001 2.28.+001 6.74.+001 2.38e+00l 4.36e+001 4.36 .. +001 0.25 0.3S 7.75e-005 7.75..-005 7.75e-006 7.75.. -005 0.1792 0.11112 0.30 0.30 57 57 57 6.74.+001 6.74.,+001* 2.28e4001 2.38"+001 4.26.÷001 4.360:+001 0.25 0.35 7.76.-005
7. 76e-005 7.76.-00D 7.7600-005 0.1792 0.1'193 0.20 0.30 58 58 58 6.74.+001 E.740:+001 2.328+001 2.38e+aOl 4.24.+001
  • . 36.,+001 0.35 0.35 7.76.-005 7.76.. -005 7.76.-005 7.76e-00S 0.1794 0.17114 0.20 0.3a 59 59 59 6. 75e+001 2.38.+001 6.75e+001 2.311 ..+001 4.26a+001 4.36e+001 0.35 0.35 7.77.-005 7.7700-005 7.77e-00S 7.77.,-00& 0.1795 0.1795 0.30 0.30 60 eo 60 6.75.+001 E.75e+001 2.38e+001 2.311e+001 4.27.+001 4.37.,+001 0.35 0.35 7.7.e-005 7.78e-005 7.785-008 7.78e-005 0.1798 0.17P& 0.30 0.30 61 6.73.4001 e.75e+001 2.28.e001 2.3I!"+001 4.372e001
  • . 37e+001 0.25 7.78e-005 7.75e-005 0.1796 0.20 61 III 0.35 77.7ee-005 7.7Be-005 0.17Pti 0.30 62 62 E2 6.75e4001
6. 75e+001 2.38.+001 2.3e ..+001 4.27w÷001 4.37,,+001 0.25 0.35 7..7?9-005 7ge-005 7.79.-00D 7.7ge-005 0.1797 0.1797 0.20 0.20 62 63 62 63 6.75c4001 2.38.+001 6.75e+OOl Z.2e,,+001 4.37e+001 4.37,,+001 0.25 0.35  ?.SOr-OD5 7.eO,,~005 7.-0B-005 7.BOe-005 0.1798 0.179B 0.20 0.30 64 64 64 lit 6.75e+001 2.36.+001 6.76e+OOl 2.3e"+001 4.27e+001 4.37 ..+001 0.25 0.3e 7.80e-005
7. BOe-005 7.50.-005 7.BOe-005 0.1799 0.1'1911 0.20 0.30 65 65 65 65 6.76e+001 2.28.+001 6.76e+001 2.311.+0Dl 4.27.+001 4.37",+001 0.25 0.35 7.815-005

'1.81,,-005 7.81.-00O 7.Bl.,-005 o.nn 0.1799 0.20 0.30 66 66 66 66 6.76.+001 6.'lh+OOl 2.39.+001 2.3ge+001 4.27.D+001

4. 31e+001 0.35 0.3S 7.82.-005

'1.U,,-005 7.826-00O 7.8200-005 0.18 0.111 o.ao 0.20 67 67 67 67 6.76.4001 2.39e+001 6.'l6e+001 2.3ge+01)l 4.27e+001 4.31.,+001 0.25 0.35 7.82.-005

'1. 82e-005 7.82c-005 7.82",-005 0.1801 0.1801 o.ao 0.20 68 68 68 68 6.76.4001 6.760:+001 2.29.+4001 Z.2ge+OOl 4.28e0÷01 4.38.,+001 0.25 0.35 7.12e-005

7. 83e-00S 7.852-005 7.83e-005 0.1802 0.1802 0.20 0.30 69 6!1 69 69 6.776+001
6. 76e+00l 2.39e+001 ".38",+001 0.35 2.3ge+OD1 4.28i+001 0.35 7.84.-005

'1.84 ..-005 ?.84.-00S 7 .. 84e-00S 0.1803 0.1803 0.20 0.30 70 70 70 70 6.77.4001 2.39*.001 4.28e+001 0.35 7.84.-005 7-5640-005 6.7'1e+001 2. 3ge+001 4.38e+00l 0.35 '1.84 ..-005 7:84",-005 0.1802 0.11103 0.30 0.30 71 71 71 71 6.77.+001 6.7'1 ..+001 2.29e+001

2. 3ge+001 4.28.+001 4.38.,+001 0.235 0.35 7.25-005

'1. 85e-005 7.85C-00D 7.85.,-005 0.1804 0.11104 0.30 0.30 72 72 72 72 6.77 ..+001 2.39e+001 6.77a+001 4.a8e+OO1 0.25

2. 3ge+001 4.29.+001 7.86.,-005 7.86.-00D 0.35 '7.86-005 7.8600-005 0.1808 0.1805 0.30 0.30 72 7a 72 13 6.77e+001 2.29e"001 6.77.+001 2. 3ge+001 4.38.+001 4.38.,+001 0.25 0.35 7.87.-005
7. 87e-005 7.87.-00O 7.117",-005 0.1806 O.lllOti 0.30 0.30 P",p: 40 Page. 4 File No.: 0900354.301 File No.: 0900354.301 Page Page B-5 B-5 of B-8 ofB-8 Revision: 00 Revision:

F0306-01RO F0306*01RO

l} StructuralIntegrityAssociates, C StructurallntBgrity Associates, Inc. Inc.

74 711 6.77.4001 2.39 74 6.77.+001 711 .. +001 2.39e+001 11.111 .. +001 C.S8o÷001 0.25 7.

0.3S 7. 87e-00S87-008 7.850-00,5 7.£17 ..-005 7.57.7-005 o0.1806

.1II0e 0.30 0.20 75 75 75 75 6.77 +001 2.39

..e.78.+001 6.77.+001 .. +1)1)1 2.39o+001 4.38 ..+001 4.28.+0D1 0.25 7.811 0.35 .. -005 7.IIBe-005 7 .8o-005 0.11107 0.1807 0.30 0.20 2.39O+001 4.38.4001 78 "70 6.78.+001 2.3ge+001 16 8.7I1e+001 78 2.29.+001 4.311 .. +001 4.39+0OG1 0.25 7.119 0.35 .. -005 7.111

7. t9.-00 ..-005 7.530-005 0.111011 0.1808 0.30 77 77 77 0.78.÷001 2.3ge+00l 71 1I.7IIe+001 2.29e4001 4.1ge+001 4.29eD001 0.35 7.119 .. -005 7.11ge-005
7. e9.-00 7.590-005 0.11109 0.1809 0.30 0.30 711 78 "711 8.711.+001 6.78e.001 2.39.+001 2.29o+001 1I.3h+00l 4.290+001 0.3S 7.90.-005 7.90 0.25 7.90.-005 ..-005 7.900-005 0.1111 0.181 0.30 0.20 79 79 71 79 41.711 .. +001 2.3ge+00l 6.78.+001 2.39o+001 4.lh+00l 4.39e+001 0.35 7.91 .. -005 7.91e-005
7.91-005 7.910-005 0.1111 0.181 0.30 0.20 110 50 80 6.711..+001 2.39 .. +001 80 1I.3h+00l 4.39.c001 0.25 7.

0.3S 91e-OOS 7.91e-005 7.910-005 7.910-005 0.11111 0.1011 0.30 0.20 81 Ii. 7ge+001 2.39 2.29:+001

.. +001 4.39 .. +001 0.25 7.92 0.35 7.92e-005.. -005 7.I2e-005 7.92e-005 0.1812 0.30 Il III 81 6.79e+001 6.79em001 2. 404+001 4.29e+001 0.20 B2 112 112 82 Ii. "7ge+001 2.40 6.79.+001 ..+1)01 2.40e+001 4.39 ..+001 4.29a+001 0.3S 7.932-005 7.93 0.23 7. 93e-005 7.-920-00C .. -005 0.1813 0.1812 0.30 0.20 82 113 6.7ge+001 113 6.79.÷001 2.40.o001 02 2.40.,+00i 4.3ge+OOl 4.39.+001 0.35 G. 23 7.94.,-005

7. 94e-00G 7.911.,-005 7.940-005 O.lB14 0.1814 0.30 0.30 1111 54 84 8.7ge+001 114 6.79e.001 2.40e+OOl 2.40e+001 4.3ge+00l 4.409+001 0.35 7. 94e-005 7.94e-005 0.25 7.94.,-005 7.94.-005 0.11114 0.1814 0.30 0.30 as 85 85 85 e. 7ge+001 2.40 6.79e+001 .. +001 2.40.+001 4.40,,+001 4.40e+001 0.25 7.

0.35 95e-005 7.95e-005 7.95e-005 7.950-005 0.11115 0.1815 0.30 0.30 118 86 a8 6.7""+001 2.40e+00l 6.590+001 2.40.+001 '.110,,+001 4.40O+001 0.35 7. 98e-005 7.96 7.960-005 .. -005 7.96.-005 O.lele 0.1816 0.30 0.30 117 57 87 8.IIOe+001 2.40e+OOl 4.40 .. +001 0O.35 7.96 0.35 7. .. -005 7.98 96r-005 .. -005 7.96e-005 0.11117 0.1817 0.30 0.20 6.80c+001 2.40e+001 4.40O+001 58 liB 88 6.80.4001 2 80 6.110..+001 .* 0 .. +001 2.40a+001 11.110.,+001 4.40§o001 0.3S 7.97 ..-00& 7.97.,-005

0. 35 7.970-005 7.97C-005 0.18111 0.1815 0.30 09 B9 119 6.80.*001 Z.40 89 6.110..+001 .. +001 2.40.+001 11.110 .. +001 4.400+001 0.3S 0.25 7.911
7. ..-005 7.98 980-005 .. -005 7.990-005 0.1818 0.118 0.30 gO 90 90 6.80.÷001 2.40e+001 90 6.110..+001 2.40e+001 .... Oe+OOl 4.40C+001 7. 9ge-00& 7.1111 0.35 7.990-005 .. -005 7.990-005 0.1819 0.30 91 91 91 6.110 .. +001 2.40 6.810+001 .. +001 2.40.+001 44.40oe001

.* 0..+001 0.35 7.99 0.25 7. .. -00& 7.91 990-005 .. -005 7.990-005 0.182 0.30 92 92 1112 6.81G+001 2.40.+001 92 6.111.+001 2.40a+001 11.110 ..+001 4.410*001 11 .. 00.-00& 8.00.-005 0.35 S.000-005 8.000-005 D.U21 0.1821 D.30 0.20 92 93 93 8.111 93 .. +00'1 2.40 6.81.+001 .. +1)1)1 2.40.+001 4.111 ..+001 4.41.÷001 0.35 0.25 8.01.. -00& 5.01O-005 a.01O-005 II.Ol .. -00S 0.11122 O.Izz 0.30 94

!It 94 6.81.+001 2.4D 94 6.1I1e+001 .. +DOI 2.40c÷001 4.41 .. +DOl 4.41c+001 0.35 8.D2 .. -005 1I.02 0.25 d.02e-005 .. -D05 5.02.-005 0.18Z2 0.1822 D.30 0.30 95 96 95 95 8.111 .. +001 2;4D.+llOl 6.81.+001 2.40.+001 44.41o+001

.* 1.+DOl 0.35 11.02.,-005 5.020-005 II.OZ .. -D05 5.02.-005 0.1822 0.30 0.20 96 96 96 96 6.111 .. +001 2.40.,+001 6.82.+001 2.410+001 4. 41 .. +DOl 4.41c+001 0.35 0.35 8.030-005 B.D3e-D05 B.03e-006 S.02.-005 0.lB24 0.1824 0.30 97

!17 117 6.82.4001 2.Ue+llOl 97 6.8Ze+001 2.41e+001 4.U .. +00l 4.41o+001 0.35 1I.04e-005 B.04e-D05 8.040-005 5.0,0-005 D.IB25 0.1825 0.30 ge 98 8.IIZ.+001 2.41.+001 0.25 95

!III 6.82.÷001 2.41.+001 11.111 ..+001 4.41e+001 0.2S 1I.04e-00S 8.040-005 B.04e-005 5.04.-005 0.1826 0.30 99 99 11.112

!19 .. +001 2.41 6.82.÷001 .. +001 2.41.+001 4. II l ..+D 0 1 4.41e+001 0.35 B.05.. -005 8.05 0.25 8.050-005 .. -D05 5.050-005 D.1112S 0.1826 0.30 0.20 100 100 100 6.112e+001 10D 6.82.+001 2,41e+001 2.41.+001 4.41 .. +001 4.410+001 D.35 0.3,5 8.06 8.00e-005.. -005 8.06 .. -0D5 5.06o-005 D.IBZ7 D.1827 D.30 0.20 101 0.25 101 1D1 101 6.112 ..+001 2.

6.82.+001 41 .. +DOl 2.41o+001 II.U ..+001 4.421a001 0.35 11.07 .. -005 8.07

.07e-008 .. -0D5 8.070-005 0.18Z8 0-.18z 0.30 102 IDZ 6.520+001 2.41 102 6.82.+001 ..+001 2.41.+001 4.42,,+001 4.420+001 0.35 8.07 .. -005 1I.07 0.25 8.070-005 .. -0D5 8.07.-00C D.1829 0.1829 0.30 0.20 102 103 102 6.8ie+OD1 ID3 6.502+001 2.41e+0012. 41e+OOI 4.U .. +00l 4.42e+001 8.0Ile-005 1I.08e-DD5 0.35 8.080-005 8.080-003 D.183 0.182 0.30 0.20 104 104 6.113e+001 6.832+001 2.41.+0012.41 ..+001 4.U ..+00l 4.42eG001 0.25 1I.0ge-005 0.3S 8.09e-005 8.0ge-005 a.09.-005 D.lS3 0.152 0.31 0.21 105 105 ID5 105 6. 2.41 ..+0Dl 83.. +0D1 2.41.+001 6.08.+001 4.42 4.420001.. +001 S.10..-005 B.l0 0.35 8.10o-005 .. -0D5 a.1G.-005 D.1831 0.1821 0.31 106 106 6.83 1D6 .. +001 6.82.4001 2.41e+0012.41 ..+001 4.42.,+001 4.42e+001 0.35 8.10o-005 B.I0e-OD5 B.I0.,-005 8.100-005 0.11132 0.1822 0.31 107 107 6.113.,+001 10-: 2.41e+00l 6-.803e01 2.41.+001 4.tZe+OOl 4.42.÷001 8. lle-OOS 8.11.-005 0.35 5.11e-005 8.11e-OD5 D.1113a 0.1032 0.31 105 108 105 6.84.+001 1011 6.84 .. +001 2.tl.,+OOl 2.41.+001 11 .* 2.. +001 4.42e+001 0.35 8.12.,-005 5.12.-005 0.25 8.12.-005 B.12.. -D05 D.1824 0-1824 0.31 0.21 109 109 IDII 6,B440+001 2.41 109 6.840+001 .. +001 2.41.+001 4.U 4.4.+001 .. +OD1 0.385 11.12 D.35 .. -00& B.ll

.120-005 .. -OOS 5.120-005 D.1B34 0.1834 0.31 110 llD 6.114oo+D01 2.41 110 6.84.÷001 .. +001 2.41e+001 4.43 .. +0Dl 4.42oe001 0.25 8.12 D.3S 8.12e-005..-005 8.13e-DD5 5.120-005 0.lB3S 0.1823 0.31 111 111 6.84 .. +001 2.41 111 6.84e+001 .. +001 2.42o+001 4.43.. +0D1 4.42e÷001 0.25 8.

0.3S 14e-005 11.14 8.14.-00s ..-005 8.14.-DOS 0.1II3S 0.1826 0.31 0.21 112 112 CI.84..+001 2.42e+00l 112 6.8054001 2.42.+001 .... 3.. +0Dl 4.420+001 0.35 II.

0.35 15e-005 II.

8.1-00S 15.. -0D5 5.15-00D5 0.1837 C.1537 0.31 0.21 112 113 113 6.B5a+00l 2.42e+00l 112 6.85.001 2.42.+001 4. 43 .. +0Dl 4.423e001 0.35 5.15.-005 8.16e-OD5 0.25 8.1Se-00S 8.15.-005 0.1838 0.183S 0.31 114 6.118e+00l 2.

114 6.850+001 lU 42.,+llOl 2.42.+001 4.113 .. +0Dl 4.43.÷001 0.25 B.16 0.36 8.16.005 .. -006 8.16 .. -006 5.16.-00C 0.1839 0.1829 0.31 115 115 115 CI.S5e+001 2.

115 6.a85.001 42 .. +0ll1 2.42.+001 4."3.,+OD1 4.43e+001 0.325 8.17 0.35 8.17-00S ..-005 1I.17.,-D05 5.17o-005 0.1839 0.1829 0.31 0.21 116 116* 6. II 5e+00 1 2.42 116 6.85.e001 116 .. +001 2.42.+001 4. 43 ..+0Dl 4.432÷001 0.25 8.

0.35 18e-00S 8.1B 8.18.-005 .. -005 S.18o-005 0.184 0.31 117 11I 6.115e+001 2.42 .. +0ll1 11'1 4 .* 3.. +001 0.25 B.le 0.35 8.180-005.. -005 8.1B .. -D05 5.18C-005 D.lSU 0.1841 0.31 1i1 118 6.a55+001 2.42e+001 4.442a001 1111 6.B5a+00l 2.42 118 6.86*4001 .. +001 2.42.+001 4.44 4.44.4001.. +001 0.3S 0.25 8.19 5.19.-005.. -005 8.11 .. -D05 8.19.-005 0.1842 0.1542 0.31 0.21 119 11111 119 6.86e+D01 2.42 11111 6.864+001 .. +001 2.42.+001 4.44 ..+001 4.44c4001 0.36 0.25 8.20.005 B.20e-D05 8.20e-005 8.20G-00S D.1843 0.1842 0.31 0.21 120 1%0 120 6.116e+001 2.42 12D 6.864+001 .. +001 2.42.+001 ".44 4.44e+001..+001 0.35 11.21 8.21.-00G II. Zl .. -DOII

.. -005 5.21.-00D D.1843 0.1843 0.31 0.31 121 121 121 6.116e+OD1 2.42e+00l 121 6.86.+001 2.42e+001 4. 44 ..+D01 4.44e+001 0.35 8.21.-005

8. 21e-005 8.21 ..-DD5 8.21C-005 0.1844 D.1844 0.31 122 122 6.86e+001 2.42 122 6.86e+001 122 ..+001 4.44 ..+D01 0.3, B.220-003 D.35 5.22e-005
8. 22e-005 11.22 ..-005 D.11145 2.42.+001 4.44&+001 0.35 5.22.-005 0.1545 0.31 0.31 122 123 122 6.86e+001 2.42.+001 123 6.874+001 2.42e+001 4 .***+001 4.44.+001 0.35 8.23.. -005 8.22 ..-005 8.22e-005 D.184e 0.1846 0.31 0.21 124 124 6. 87..+D01 2.42 124 6.87.+001 124 .. +001 2.42.+001 4. 44 .. +D01 4.44.+001 0.35 8.24e-00& 8.2"e-OD5 0.25 8.24.-005 8.24a-005 D.IB47 0.1847 0.31 0.21 125 125 125 6. 87.. +DOl 2.42 125 6.07e+001 .. +0Dl 2.42e+001 4 .....+001 4.445.001 0.35 B.24e-00& 8.24 0.25 8.24e-005 .. -DD5 5.24.-005 0.1848 D.1S48 0.31 126 126 126 6.117 .. +D01 2.

126 6.874+001 42 ..+DDl 2.42e+001 4.45.,+001 4.45B+001 D.35 0.25 8. 25e-005 8.25.-005 8.25r-005 B.25..-005 0.1848 D.1848 0.31 0.31 0.1049 127 127 127 6.117.+001 2.U.+00l 127 6.87.+001 2.43&+001 4.45,,+ODl 4.45a+001 0.25 8.26 D.3S 8.26.-005..-005 8.26.-005 B.26e-DD5 0.1849 D.31 0.21 125 12B 128 6.88.+001 128 2 6.87e+00l 2.432+001 .* 3..+001 1I.1I5e+001 0.3S B.27.,-00S 0.35 8.27.. -D05 8.27e-005 8.27.-005 0.1058 O.lBS D.31 0.21 4.45.+001 129 121 129 129 6.88.+001 2. 44e+OOl 6.IIB ..+001 2.43.+001 4.45e+001 4.45.+001 0.35 0.35 8.27 8.270-005..-00S 8.27e-OD5 8.27.-005 D.18S1 0.1851 D.31 0.21 130 130 120 13D 6.85.+001 6.88.. +001 2.42.+001

2. 44e+ll01 '.45,,+001 4.45e+001 0.3S 8.211 0.25 8.28.-00S..-005 1I.211.,-D05 5.25.-005 0.1852 0.1852 0.31 0.21 121 131 121 6. 88.. +D01 2.42.4001 131 6.88.4001 2.U.,+001 4 ** 5.. +001 0.3S 8.29..-005 0.23 8.2I1e-D05 8.29e-005 8.29.-005 0.11153 0.1852 0.31 0.21 122 4.45.+001 la! 122 6.118.+001 2.4324001 132 6.90.+001 2.Ue+001 4.45e+001 4.45e+001 D.3S 8.30.,-005 0.25 6.30-00G5 8.30e-D05 8.300-005 D.1SS3 0.1852 0.31 0.21 122 122 6.89.+001 2.432+001 0. 1854 121 133 6.118 .. +001 2.Ue+00l 4.45..-+001 4.45ao001 0.35 8.31 0.35 8.31o-005 8.3101-005

..-005 B.2l1-005 0.1854 0.31 0.21 134 1311 13.

124 6.59.+001 2 .....+0ll1 e.IIge+OOl 2.43e+001 4.46.. +0D1 4.46e+001 0.25 11.31..-005 8.310-005 0.35 8.21.-005 8.31e-OD5 0. 1855 0.1855 0.31 0.21 125 126 135 6.89e+002 125 6.1111..+001 2-42e+001 2.Ue+OO1 4.46e+001 4.1I~.. +ODl 11.32.,.-005 B.22.-005 D.3S 8.32V-005 0.25 8. 32.. -DDS 0.11156 0.1856 0.31 0.21 Paq.. : 55 Page:

File No.: 0900354.301 0900354.301 Page Page B-6 of B-8 B-8 Revision: 0 F0306-01 RO F0306-0IRO

l) StructuralIntegrityAssociates, V Structurallntegr;ty Associates, Inc. Inc.

136 126 Ii. 8ge+001 2.43.,+001 136 6.e89e+001 12e 4.46 .. +001 2.432+001 4.46r001 0.25 8.33~-005 0.35 8.23-005 8.33e-005 8.22e-005 0.1115'1 0.1857 0.1557 0.31 0.21 0.21 2.42:+001 4.468+001 0.25 8.342 -O2 B.24 e008 137 127 128 137 6.59.4001 2.43,.+001 6.lIt.,+001 13'1 6.89e+001 128 2.42.+001 4.46,.+001 4.46+001 0.35 8.34,.-005 0.35 e.348-005 B.34,.-005 5.24e-005 0.185'1 0.1858 0.31 0.21 1311 129 13B 1i.8t..+0*01 2.43 129 6.89.+D01 ..+001 4.46.c001 2.43e+001 *. 46 ..~001 0.35 8.34,.-005 8.35.-005 8.8 ...-005 5.248-005 0.11158 0.1853 C.31 0.21 129 140 1~9 140 6.89.+001 6.90.+001 2.43 ..+001 2.42e+001 *. 46.,+001 4.46.+001 0.25 8.aSe-00s 0.35 8.36.-005 8.~5e-005 8.26r-005 0.18S~

0.188 C.31 0.31 140 141 140 141 6.tO..+001 6.90e+001 2.43 ..+001 2.42e+001 *. 46 .. +001 4.46e+001 0.25 11.36 0.35 ..-005 8.37.-005 8.36.,-005 5.37.-DOS 0.18E 0.1861 0.31 0.21 141 141 141 142 0.90 .. +001 6.90e+001 2.43 ..+001 2.44e+001 4.40 ..+001 4.474e+001 0.32 11.37 0.35 ..-005 8.37r-005 II. 37e-00S S.27-005 O.leel o.1e86 0.31 0.21 142; 142 142 142 6.90..+001 6.90.+001 2.44.,+001 2.44e+001 4:4'7,,+001 4.47e+001 0.25 8.37 0.35 ..-005 8.38.-005 O 8.37 .. -005

.28e-005 0.1862 0.1862 0.31 0.31 143 144 143 144 11.90..+001 6.90e÷001 22.44e+001

.....+001 4.47 .. +001 4.47.+001 0.25 1I.3e 0.35 ..-001i 8.39.-00 15.alle-005 5.23.-00 0.1863 0.1863 0.31 144 145 144 148 41.90.. +001 6.910+001 2.44 ..+001 2.44e"001 4.47 ..+001 4.47.+001 0.35 1I.3h-005 0.25 8.40.-005 11.31.,-005 8.40.-DOS 0.11U13 0.1864 0.3i 0.21 145 146 145 146 6.111 .. +001 6.91e+001 2.44e+001 2.44.+001 4.41.,+001 4.47e4001 0.35 0.23 8.40 ..-005 8.41-005 !l.40.,-005 8.41.-005 0.le64 0.18648 0.31 0.21 146 147 146 147 6. tl .... 001 O.91+001 22.44.+001

.....+001 4.41.,+001 4.47.+001 0.28 lI.n 0.35 ..-OOIi 8.41.-DOS 8.41 5.41.-00.. -005 0.1865 0.1865 0.31 0.31 147 148 141 148 6.111 .. +001 6.91e+001 2.44 .... 001 2.44""001 4.47.,+001 4.47e+001 0.25 8.41 0.35 ..-005 8.42.-005 !l.n .. -005 8.42.-DOS 0.186e 0.1887 0.31 0.21 148 149 14B 149 6.91 .. +001 6.91.+001 2.44 .... 001 2.448+001 4.47 ..+001 4.47a+001 0.28 8.U 0.35 .. -001i 8.4.e-00 B.42.,-005 89,42-005 0.186'1 0.1868 0.31 0.21 149 150 149 140 6.91 .. +001 6.92.+001 2.44 ..+001 2.44e+001 4.41 .. +001 4.487+001 0.28 lI.n 0.3S ..-005 8.44.-00D 15.n.,-005 8.44.-00D 0.186B 0.1868 0.31 0.21 150 151 150 181 6.tZ .. +001 6.92e+001 2.44 ..+001 2.44e+001 4.4Be+001 4.48.+001 0.38 11.44 0.35 ..-005 8.48.-005 B.n .. -005 8.4%e-005 0.1116a 0.1889 0.31 0.21 1152 III 151 151 0.92 ..+001 6.92.+001 2.44 ..+001 2.44e+001 4.48 .. +001 4.48.e001 0.35 0.35 1I.4l1e-001i 8.45e-00D 8.t5 .. -005 8.46.-005 0.le61 0.187 0,31 0.21 152 152 152 152 6.92..+001 6.92e+001 2.44 ..+001 2.44e+001 4.4B,,+001 4.48.+001 0.25 1I.4Se-00S 0.35 8.46.-00D 8.45 .. -005 B.46e-00O 0.18'1 0.1871 0.31 0.21 153 154 I53 154 6.12 ..+001 6.92e4001 2.44 ..+001 2.44e+001 ** 411.,+001 4.488+001 0.25 B.U 0.35 ..-OOS 8.47e-00 B.46 .. -005 8.47.-005 0.18'11 0.1872 C.31 0.21 15.

154 IS.

154 6.tZe+001 6.92.+001 2.44 ..+001 2.44e+001 *. 4B ..+001 4.48e+001 0.28 8.47 0.35 ..-005 8.48.-005 8.t7.-005 8.487-005 0.11172 0.1872 0.31 0.21 155 156 155 158 li.la.,+OOl 6.93.+001 2.44 ..+001 2.454e+001 4.48 .. +001 4.48e+001 0.35 11.48 ..-005 0.25 8.49.-DOS 8.t15 .. -005 8.49.-D0S 0.18'13 0.1872 0.31 0.21 156 151 IS6 157 6.93 .. +001 6.93e+001 2.45 ..+001 2.45e+001 4.4B ..+001 4.48.+001 0.35 8.49 0.25 8.49.-00..-005 8.U.,-00S 8.49.-005 0.11173 0.1874 C.31 0.31 157 156 15'1 158 6.93.. +001 6.93.+001 2.45 ..+001 2.45e+001 4.48 ..+001 4.49.+0O1 0.35 0.25 B.4h-005 8.40.-005 8.49 8.50.-00.. -005 0.1874 0.1875 0.31 0.31 1511 159 158 159 lI.t2.+001 6.9 2+001 2.45 ..+001 2.45.4001 4.4te+001 4.49.+001 0.25 8.50 0.35 ..-005 8.51e-00 B.50.-005 8.51.-005 0.18'15 0.1878 0.21 0.31 159 160 159 160 6.ta.,+001 6.94.+001 2.45 ..+001 2.45e+001 t.49 .. +001 4.49e+001 0.3S 0.32 8.51.,-005 8.82.-00D B.51 .. -005 5.5l2-005 0.18'1£ 0.1877 0.31 0.21 160 161 160 161 11.94 ..+001 6.94e+001 2.45 .. +001 2.45e+001 ".49.. +001 4.49e+001 0.25 8.52.,-005 0.35 8.53.-00D 8.5Z .. -005 8.52.-005 0.18'17 0.1878 0.31 0.31 161 162 161 161 6.94 ..+001 6.94.+001 2.45.,+001 2.45.+001 4.4t..+001 4.49.+001 0.25 0.25 8.53 ..-005 8.532-005 B.53 .. -00S 0.82.--0S 0.111711 0.1879 0.31 0.21 UZ 162 16Z 162 lI.t4 ..+001 6.94.+001 2.45 .. +001 2.45e+001 4.411 .. +001 4.49c001 0.25 8.5a.,-005 0.35 8.54.-00 II.Sa .. -005 8.524-005 0.18'19 0.1879 0.31 0.31 In164 163 164 6.94 ..+001 6.94.+001 2.45 .. +001 2.45.+001 4.411.+001 4.49e+001 0.28 11.54.,-005 0.35 8.55.-008 B.5 .... -005 8.58.-005 0.18'19 0.188 0.31 0.21 1U164 164 168 6.94 ..+001 6.98.+001 2.45 .. +001 2.458+001 4.49.+001 4.49.*001 0.32 S.5l1e-005 0.311 8.56.-00 8.55e-00S 8.66.-D-0 O.lSe 0.1881 0.31 0.31 us 166 US 166 6.9Se+00l 6.95e+001 2.45 .. +001 2.45.+001 4.4h+001 4.509+001 0.35 0.32 8.56 ..-005 8.57.-DOS B.S6 .. -005 8.57.-005 0.1881 0.1882 0.31 0.21 166 167 IE6 167 6.95.+001 6.9,.+4001 2.45e+001 2.45e+001 4.50 .. +001 4.50e+001 0.35 8.57.,-005 0.23 8.57.-005 B.57.-005 8.57.-0D 0.1882 0.1883 0.31 0.21 167 168 16'1 168 E.9Se+00l 6.95e+001 2.45 .. +001 2.45e+001 4.50 .. +001 4.50e+001 0.35 8.57.,-005 0.35 8.5.e-005 B.57 8.588-0D.. -005 0.18S3 0.1884 0.31 0.31 16e 169 168 169 6.9Se+00l 6.956+001 2.45 .. +001 2.45e+001 ".50 .. +001 4.50e+001 0.35 a.58 0.35 .. -005 8.59.-005 8.SB .. -005 80.9.-005 0.11184 0.1885 0.31 0.21 169 170 169 170 6.9&..+001 6.96.+001 2.45 .. +001 2.46.4001 4.50 .. +001 4.50e+001 0.25 8.5h-00S 0.35 8.60.-005 8.59 .. -005 8.60.-005 0.1885 0.1885 0.31 0.31 170 171 l-?O 111 6. 96e+00l 6.96.+001 2.46 ..+001 2.46.+001 4.50 .. +001 4.50e+001 0.26 8.60.,-005 0.35 5.61.-005 8.6il .. -005 8.61.-005 0.1885 0.1886 0.31 0.31 I'll 171 I'll 171 6. 96e+00l 6.96+4001 2.46 .. +001 2.46.+001 4.50 .. +001 4.50+.0O1 0.26 8.61 0.35 .. -005 8.61.-DOS 8.61 .. -005S 8.61.--0 o .18se 0.1887 0.31 172 172 172 172 II. 96e+00l 6.96.+001 2.45 .. +001 2.46.+001 4.50 .. +001 4.560+001 0.25 8.61 0.35 .. -005 8.62.-005 11.61 8.62.-00.. -0011 0.11187 0.1888 0.31 0.31 173 174 173 174 E.II6e+OOl 6.96.+001 2.46 .. +001 2.46e+001 4.50 .. +001 4.51e+001 0.25 S.62 0.35 .. -005 8.62.-005 8.62 .. -005 8.62.-00D 0.1888 0.1889 0.31 0.31 174 178 174 175 6.116e+00l 6.97.+001 2.4fi .. +00l 2.46e+001 4.51 .. +001 4.518+001 0.35 0.25 8.63.-005 8.64.-00D lI.n .. -005 8.64.-005 0.1889 0.189 0.31 0.21 175 176 1'15 176 6.9'1""001 6.97e+001 2.46 .. +001 2.46e+001 4.51 .. +001 4.S1.+001 0.:15 0.38 8. 64e-005 8.6.4-005 B.64e-005 8.654-005 0.189 0.1891 0.31 0.32 1711 177 176 177 1I.9'1e+00l 6.97.+001 2.45e+OOl 2.46.+001 4.51 .. +001 4.51.+001 0.311 0.25 lI.fiSe-OOIi 8.66.-00D 8.65e-005 B.66.-00D 0.18111 0.1893 0.32 0.32 17'1 178 1'7'1 178 ti.9'1 .. +001 6.97.+001 2.46 .. +001 2.46e+001 ** 51 ..+001 4.51c+001 0.35 0.3 8. 66.. -001l 8.66e-005 8.66 ..-005 8.66.-005 o.lUl 0.1892 0.32 0.32 1711 179 178 179 6.97 .. +001 6.97e+001 2.46..+001 2.46e+001 4.51 .. +001 4.51u+001 0.35 S.66e-OOli 0.25 6.67e-005 15.tifi .. -OOS 8.67e-005 0.18t2 0.1892 0.32 0.22 179 180 1'19 180 6. t'1 .. +001 6.987+001 2.46..+001 2.46e+001 4.51.+001 4.S1w+001 0.25 8.67.-005 0.28 8.66.-005 8.6'1 8.678-00.. -005 0.18n 0.1894 0.32 0.32 180 181 180 181 6.t8.. +001 0.98.+001 2.46..+001 2.46.+001 4.51 .. +001 4.82a÷001 0.23 II.

0.35 68.,-001i 8.69.-005 8.68.,-005 8.69.-DOS O.lUt 0.1895 0.32 0.22 1111 182 181 182 1I.ge .. +00l 6.984+001 2.46..+001 2.46e+001 4.S2 .. +001 4.852+001 0.35 1I.61e-001i 0.38 8.70.-005 11.119 .. -0011 B.70.-D05 0.lS9S 0.1896 0.32 0.22 182 182 182 182 6.98 ..,+001 6.98.+001 2.46.,+001 2.46e+001 4.52 .. +001 4.52e.001 o.as 8.70 0.36 ..-005 8.71e-0OS 8.70.,-005 8.71.e-DO 0.1896 0.1897 0.32 0.22 183 184 183 184 6.118 .. +001 6.98e+001 2.46..+001 2.476+001 4.52 .. +001 4.52e+001 0.35 8.71 0.28 ..-005 8.71.-00S B.'11 .. -005 8.71.-005 0.18117 0.1898 0.32 0.22

'lB4 18 184 188 6.98..+001 6.989+001 2.47..+001 2.47.+001 4.52 .. +001 4.52e+001 0.35 8.71 0.35 ..-005 8.72.-005 11.71 .. -005 8.72e-005 0.1898 0.1898 0.32 0.22 1115 186 1811 186 0.11"'+001 6.99.+001 2.47..+001 2.47e+001 4.S2 .. +001 4.52e+001 0.:15 8.n 0.35 ..-005 8.72.-00 8.72.,-0011 8.72.-005 O.lUe 0.1899 0.22 0.22 186 187 IB6 187 6.n..+00l 6.99c+001 2.47..+001 2.47e+001 4.52 .. +001 4.52a+001 0.3S 8.73 0.35 ..-005 0.743-005 8.73 .. -005 8.74.-DOS 0.18U 0.19 0.22 0.32 187 188 1B7 188 6.9te+00l 6.99.+001 2.47 ..+001 2.47e+001 4.S2 .. +001 4.52e+001 0.35 88.74r-005 0.35 .. 74.....,005 11.74.,-005 8.7Se-005 O.H 0.1901 0.32 0.22 11lB 189 188 189 6.99..+001 6.99e+001 2.47..+001 2.47.+001 4.SZ .. +001 4.52.+001 0.25 8.75..-005 0.25 8.76.-005 8.75 ..

8.76.-005 -005 0.1901 0.1902 0.32 0.32 189 190 189 190 6.11,.,+001 7.004+001 2.47 .. +001 2.474+001 4.53.,+001 4.52.÷001 0.3S 1I.'16e-005 0.35 8.76e-005 8.76.,-005 8.76.-005 0.11102 0.1302 0.32 0.32 190 191 190 191 '1.00 ..+001 7.00e+001 2.47 .. +001 2.47.+001 4.53 .. +001 4.52e+001 0.35 8.7.6 0.35 ..-005 8.77e-00D 8.'16.. -005 8.77.-00D 0.1903 0.1904 0.32 0.22 191 192 li1 191 7.00 .. +001 7.00m+001 2.47 .. +001 2.47.+001 4.53.,+001 4.52L+001 0.35 8.77 ..-005 0.25 8.78e-005 8.'1'1 .. -005 9.77a-005 0.lB04 0.1905 0.32 0.32 192 192 liZ 192 7.00..+001 7.00.+001 2.47 .. +001 2.47e+001 4.53 .. +001 4.52e8001 0.35 8.78 0.25 .. -005 8.79.-005 8.78.. -005 8.79.-006 0.1905 0.1905 0.32 0.32 193 193 7.00..+001 2.47 .. +001 4.53.,+001 0.35 8.7h-005 8.79.. -005 0.1905 0.32 194 194 194 7.00.+001

'1.00.,+001 2.47.+001 2.4'1 .. +001 4.52.÷001 4.53.,+001 0.25 8.80e-DO5 0.35 8.80 .. -005 8.80.-00D e.'80.. -0oS 0.1906 0.19015 0.32 0.32 US195 195 US 7.01.4001 1.01 .. +001 2.47.+001 2.47 ..+001 4.52e+001 4.S3.. +001 0.28 8.81--005 0.35 8.111 .. -005 8.91.-005 8.81.. -005 0.1907 0.1907 0.22 0.32 196 196 196 196 7.01e+001 7.01 ..+001 2.47.+001

2. 47 ..+1101 4.54e÷001 4.S.e+00l 0.25 8.81.-005 0.35 8.81.. -005 8.81.-005 B.81..-005 0.1908 0.190e 0.32 0.32 197 197 197 19'1 7.01e+001

'1.01 .. +001 2.47e+001 2.47..+001. 4.54e÷001 4.54 .. +001 0.25 8.82e-005 0.35 11.112.. -00:1 8.82.-00D 11.112.. -005 0.1909 0.190' 0.32 0.32 Paq .. : t6 a.ge:

File No.: 0900354.301 0900354.301 Page B-7 of B-8 Revision: 0 F0306-OIRO F0306-0IRO

e V Structurallntegr;ty Structural Associates, Inc.

IntegrityAssociates, Inc.

1ge 190 '7.010+001 2.43e+00I.

UII 1.61,+002 *. U.,+llOl 0.238 2.45e+llOl *.54u+001 8.83e-OD5 0.291 8.S3e-005 B.82e-O00 0.3& 8.92e-003 0.191 0.22 0.32 199 199 199 7.01*+001 199 '7.01e+00l 2.4$e+00I.

2.4!1e+lllll 4.Ste+00l 0.88 4.54e+001 8.8te-005 B-64e-005 0.35 8.84e-005 8.84e-005 0.1912 0.1911 0.32 0.32 4

200 200 200 '7.0Z.. +001 2.48e ZOO I.OZe+0O1 2.4!1e+Olll 4.5t.,+001 0.23 001. 4.54e+001 0.3S e.85e-008 0.55c-005 0.91i2 e.8Se-005 8.88e-OD5 0.191Z 0.22 0.32 End of PC-CRAM Output.

Page: I7 Paqe: '7 File No.: U0U0354.3U1 Hle No.: 0900354.301 Page B-8 Page ofB-8 B-8 of B-8 Revision:

Revision: 00 F0306-OIRO F0306-OIRO

Retrieved from "https://kanterella.com/w/index.php?title=L-09-122,_Calculation_0900354.301,_Rev._0,_Flaw_Evaluation_for_N6A_and_C_Nozzle_to_Safe_End_Welds.&oldid=2561717"