ML121230295

From kanterella
Jump to navigation Jump to search

Reply to Request for Additional Information Relief Request - Proposed Alternative - Use of Alternate ASME Code Case N-770-1 Baseline Examination
ML121230295
Person / Time
Site: Palisades 
(DPR-020)
Issue date: 04/30/2012
From: Gustafson O
Entergy Nuclear Operations
To:
Document Control Desk, Office of Nuclear Reactor Regulation
References
PNP-2012-041
Download: ML121230295 (67)
v • d • e


Text

Entergy Nuclear Operations, Inc.

Palisades Nuclear Plant 27780 Blue Star Memorial Highway Covert, MI 49043 Tel 269 764 2000 Otto W. Gustafson Licensing Manager PNP-2012-041 April 30, 2012 10 CFR 50.55a U. S. Nuclear Regulatory Commission ATTN: Document Control Desk Washington, DC 20555-0001

Subject:

Reply to Request for Additional Information Re: Relief Request -

Proposed Alternative - Use of Alternate ASME Code Case N-770-1 Baseline Examination Palisades Nuclear Plant Docket 50-255 License No. DPR-20

References:

1.

Entergy Nuclear Operations Inc. letter, "Relief Request - Proposed Alternative - Use of Alternate ASME Code Case N-770-1 Baseline Examination," dated April 26, 2012

2.

Dear Sir or Madam:

NRC Electronic Request, "Palisades - Relief Request - Proposed Alternative - Use of Alternate ASME Code Case N-770-1 Baseline Examination - ME8492," Request for Additional Information, dated April 27, 2012 Entergy Nuclear Operations, Inc. (ENO) submitted a request for relief from ASME Code Case N-770-1 on April 26, 2012 (Reference 1). ENO received an electronic request for additional information (RAI) from the Nuclear Regulatory Commission (NRC) concerning the submittal on April 27, 2012 (Reference 2). ENO and the NRC held a conference call on April 30, 2012, to clarify the RAI.

The attachment contains the ENO response to the RAI.

PNP 2012-041 Document Control Desk Page 2 This letter contains no new commitments and no revisions to existing commitments.

Sincerely, OWG/jse : Reply to Request for Additional Information Re: Relief Request -

Proposed Alternative - Use of Alternate ASME Code Case N-770-1 Baseline Examination cc: Administrator, Region III, USNRC Project Manager, Palisades, USNRC Resident Inspector, Palisades, USNRC

ATTACHMENT 1 REPLY TO REQUEST FOR ADDITIONAL INFORMATION RE:

RELIEF REQUEST - PROPOSED ALTERNATIVE-USE OF ALTERNATE ASME CODE CASE N-770-1 BASELINE EXAMINATION

Background

By letter dated April 26, 2012, Entergy Nuclear Operations, Inc., submitted the proposed altemative, "Use of Altemate ASME Code Case N-770-1 Baseline Examination," for U.S. Nuclear Regulatory Commission (NRC) review and acceptance.

The request proposed an altemative to the requirements of the American Society of Mechanical Engineers (ASME) Boiler and Pressure Vessel Code (Code) Case N-770-1, as required and conditioned by Title 10 of the Code of Federal Regulations, Part SO (10 CFR SO) paragraph SSa(g)(6)(ii)(F)(3). Specifically, ENO states that obtaining the required examination coverage of essentially 100 percent is unattainable due to limitations imposed by design and geometry, and requests relief from the required baseline examination coverage on the basis that compliance with the requirements would be a hardship without a compensating increase in the level of quality or safety, per 10 CFR SO.SSa(a)(3)(ii). In order to complete our review, the Piping and NDE Branch requests additional information.

Nuclear Regulatory Commission (NRC) Request

1.

Please provide more detailed diagrams than those in Figures 3 through 7, in of the relief request. Please clearly identify the weld material and provide axial and circumferential scan diagrams for each weld configuration that has actually been scanned.

Entergy Nuclear Operations, Inc. (END) Response A table of Alloy 600 susceptible calculated weld volumes is provided with the requested detailed weld diagrams in Enclosure 1.

NRC Request

2.

Please provide additional information for the 4" PORV weld clearly identifying the materials of construction, weld repair history, and the geometry of the components.

Especially important are the onlay weld thickness and number and order of weld passes, any post-weld machining details and wall thickness of the various sections, including the dissimilar metal butt weld.

END Response Materials of construction: The relief valve nozzle assembly within the pressurizer head was constructed from A-S08-64 CI. 2 material with a minimum 7/32" 304 Page 1 of 3

stainless steel cladding. The replacement safe end is SA-479 Type 316 material (Ref. 3). The welding filler material used for the onlay is Alloy 690 (ERNiCrFe-7, Code Case 2142, UNS N06052) material (Ref. 2). The safe end replacement drawing indicates that the length of the full, final thickness onlay covers the remaining Alloy 600 buttering material from the original safe end weld by a minimum of 1/4" (Ref.1).

Weld repair history: A weld repair was performed on the safe end-to-pipe interface (vice safe end-to-nozzle) in 1993. The safe-end was machined (shortened) to remove the original weld to the stainless steel pipe. This is the safe end that was subsequently replaced with the new safe end design in 1995.

Geometry of the components: The final geometry of the components, including the welds, is shown in References 1 through 4.

Onlay weld thickness: The weld thickness of the onlay was specified as a minimum of 1/8" build-up with the first layer to be approximately 1/16" thick (Ref. 2, Note 6).

Number and order of weld passes: From the welding records and procedures, this weld was made using a minimum of two layers. The number and order of weld passes per layer was not recorded.

Post-weld machining details: No specific post-weld machining details were provided in the work package. The final weld onlay thickness was given as "1/8" (with a tolerance of +0",-1/32") after grinding/machining" (Ref. 2, Detail A).

Additionally, it is specified that "The first layer shall not be violated during the final machining" (Ref. 1, Note 8).

Wall thicknesses of various sections. including the butt weld: The PORV nozzle is nominally 1.75" wall thickness and the replacement safe end wall thickness at the nozzle varies between 1.19" and 1.5" thick at the weld end. The thickness of the sections through the butt weld varies between the 1.75" and 1.5" wall thickness transition of the nozzle to the safe end.

References (see Enclosure 2):

1. VEN M1-LA Sheet 1 - Palisades PORV Nozzle Safe End/Spool Piece Replacement
2. VEN M1-LA Sheet 2 - Palisades PORV Nozzle Safe End/Spool Piece Replacement
3. VEN M1-LA Sheet 3 - Palisades PORV Nozzle Safe End Replacement Hardware
4. VEN M1-LA Sheet 4 - Palisades PORV Nozzle Safe End/Spool Piece Field Machining Page 2 of 3

NRC Request

3.

Due to the limited coverage and elevated temperatures of the pressurizer, and in accordance with question 29 of the July 12, 2011 Code Case N-770-1 public meeting summary (ADAMS Accession Number ML112240818), we request that a PWSCC flaw evaluation of the 4" PORV weld welds mitigated by Alloy 52 inlay be performed. As a result of this flaw evaluation, please provide a basis for reasonable assurance of structural integrity and leaktightness for the interval for which relief is requested. We have provided recommended crack growth rate improvement factors in the answer portion to question 29. Please provide this information as soon as possible, preferably no later than April 30, 2012. The NRC staff has previously performed a similar flaw analysis of Alloy 52 inlayed dissimilar metal butt welds. This information can be found in ADAMS under Accession Number ML101260554.

END Response The flaw evaluation is provided in Enclosure 3.

Page 3 of 3

ENCLOSURE 1 Detailed Diagrams 15 Pages Follow

Alloy 600 Susceptible Volume Calculation - lR22 Inner l/3T Coverage Outer 2/3T Coverage Weld Axial Scan for Cire Cire Scan for Axial Combined Axial Scan for Cire Scan for Axial Flaws Flaws Coverage Cire Flaws Flaws Notes PCS-4-PRS-1P1-1/

100%

0%

50%

100%

0%

165 (PORV)

PCS-2-DRL-2A1-1/

100%

62.5%

81.3%

85%

66%

273 41S-40.6%

100%

60L-1oo%

43L-0%

PCS-2-CHL-1A1-17 68L-100%

Combined - 20.3%

(100% volume 43.4%

92%

/274 60S-0%

(100% volume scanned, with Combined - 66.6%

credit for I

scanned, no credit unqualified 43L) for unqualified 43L) 63.6%

72.8%

I PCS-3-PSS-1B1-1/

I 68.2%

60%

73%

77 (100% scanned 7" of (100% scanned 7" of 11" circumference) 11" circumference) 63.6%

72.8%

PCS-3-PSS-2A1-1/

68.2%

60%

73%

275 (100% scanned 7" of (100% scanned 7" of 11" circumference) 11" circumference)

NOTE:

WELD CONFIGURATION AND COVERAGE

SUMMARY

PCS-4-PRS-1P1-1 PT 1165 NOZZLE TO SAFE END INCONEL 82 ALLOY REMNANT ~

1--

INCONEL 52 WELD SAFE END

}\\

316 SIS MATERIAL ALLOY 52 WELD BUTTER _LL---+------

AND ONLAY 1.3" LD

(().

2.1"

... 1 1 ~.2n INCONEL 182 WELD BUTTER

=

(Y)

(Y)

~I CARBON STEEL NOZZLE

- WELD OUTLIINE

- SUSCEPTIBLE MATERIAL UPPER 2/3 0% CIRCUMFERENTIAL SCAN HZJI2I% AXIAL SCAN

- CODE REOUIRED VOLUME 12.5% CIRCUMFERENTIAL SCAN 82.1% AXIAL SCAN IIIIIIIIIIB - SUSCEPTIBLE MATERIAL LOWER 1/3 0% CIRCUMFERENTIAL SCAN 1

DRAWING NOT TO SCALE 1121121% AXIAL SCAN L:\\CAO-ProJect o,."Wlngs\\ProJmlsc\\PCS-4-PRS-IPI-1 PT 1165-I.OGN

SAFE END 40* TO 50*

SAFE END PHASED ARRAY SCAN DIAGRAM WELD PCS-4-PRS-1P1-1 PT 1165 NOZZLE TO SAFE END TRANSDUCER (TYP) r~

TRANSDUCER <TYP)

NOTE:

DRAWING NOT TO SCALE CIRCUMFERENTIAL SCAN 40* TO 50*

AXIAL SCAN RXXX1 - AREA NOT SCANNED

~~i - AREA SCANNED 2

L:\\CAO-ProJect OrOWlngs\\ProJmlSC \\PCS PRS-1Pl-l PT 1165.0GN

NOTE:

WELD CONFIGURATION AND COVERAGE

SUMMARY

WELD PCS-2-DRL -2AI-I/PT 273 NOZZLE TO PIPE ALLOY 600 NOZZLE N

.7 11 SIS PIPE I

I =

1(0 1(")

I.

1.2'

~I

- WELD OUTLINE

- SUSCEPTIBLE MATERIAL UPPER 2/3 66% CIRCUMFERENTIAL SCAN 85% AXIAL SCAN

- CODE REOUIRED VOLUME 75% CIRCUMFERENTIAL SCAN 100% AXIAL SCAN 11I1IIIIII1I - SUSCEPT IBLE MATERIAL LOWER 1/3 62.5% CIRCUMFERENTIAL SCAN DRAWING NOT TO SCALE 100% AXIAL SCAN 1

L:\\ CAD-ProJect Dr<lwlngs\\Pr oJmlsc \\PCS-2-DRL-2Al-l PT 273-1.DGN

PHASED ARRAY SCAN DIAGRAM WELD PCS-2-0RL -2AI-I/PT 273 NOZZLE TO PIPE r

40" TQ 70°,

TRANSDUCER (TYP)

I I

I L

1 AXIAL SCAN J

CIRCUMFERENTIAL SCAN 2

L J

k'XX:XJ - AREA NOT SCANNED NOTE:

[___

I - AREA SCANNED DRAWING NOT TO SCALE L:\\CAD-ProJect Drowlngs\\ProJmlsc\\PCS-2-DRL-2Al-l PT 273.DGN

WELD CONFIGURATION AND COVERAGE

SUMMARY

WELD PCS-2-CHL -IAI-17 /PT 274 STAINLESS STEEL PIPE FILLET WELD STAINLESS STEEL VALVE NOTE:

N DRAWING NOT TO SCALE NOZZLE TO PIPE

.7 11 INCONEL WELD I

I =

1c.D 1M ALLOY 600 NOZZLE I.

1.2'

.1

- WELD OUTLINE

- SUSCEPTIBLE MATERIAL UPPER 2/3 100% CIRCUMFERENTIAL SCAN 92% AXIAL SCAN

- CODE REOUIRED VOLUME 40.6% CUMFERENTIAL SCAN 66.6% AXIAL SCAN IIIIIIIIIII! - SUSCEPTIBLE MATERIAL LOWER 1/3 20.3% CIRCUMFERENTIAL SCAN 66.6% AXIAL SCAN 1

L:\\CAO-ProJect Or<>Wlngs \\PrOJmlSC \\PCS-2-CHL - lAl-17 PT 274-1.DGN

VALVE WELD VALVE WELD NOTE:

MANUAL UT SCAN DIAGRAM WELD PCS-2-CHL-lAl-17/PT 274 NOZZLE TO PIPE CIRCUMF.

TRANSDUCER (lyP)

NOZZLE CIRCUMFERENTIAL SCAN L

j 70" & 70" & 70" &

70" &

60" 60" 60" 60" AXIAL SCAN 2

R2<X"5<J - AREA NOT SCANNED DRAWING NOT TO SCALE F

I - AREA SCANNED L:\\CAO-ProJect Orawmg,,\\ProJmI5c\\PCS-2-CHL-1Al-17 PT 274.0GN

WELD CONFIGURATION AND COVERAGE

SUMMARY

WELD PCS-3-PSS-IBI-I/PT 77 1

ALLOY 600 NOZZLE (Y).

(S)

ELBOW TO NOZZLE 1.0" I,

I I...

1.5"

.1 WELD OUTLINE SUSCEPTIBLE MATERIAL UPPER 2/3 73% CIRCUMFERENTIAL SCAN 60% AXIAL SCAN CODE REQUIRED VOLUME 72.8% CIRCUMFERENTIAL SCAN 63.6% AXIAL SCAN 111111111111 -

SUSCEPTIBLE MATERIAL LOWER 1/3 72.8% CIRCUMFERENTIAL SCAN 63.6% AXIAL SCAN NOTE:

DRAWING NOT TO SCALE l :\\CAO-ProJect Orowmg,,\\ProJmlsc \\PCS-3-PSS-1Bl-l PT 77-3.0GN

NOZZLE NOZZLE NOTE:

PHASED ARRAY SCAN DIAGRAM WELD PCS-3-PSS-181-1/PT 77 ELBOW TO NOZZLE I

RXX:2<1 - AREA NOT SCANNED

[773 - AREA SCANNED I

TRANSDUCER <TYPl AXIAL SCAN ELBOW CIRCUMF.

I

~

I 2

CIRCUMFERENTIAL SCAN L

~

ELBOW DRAWING NOT TO SCALE L:\\CAO-ProJect Ora.nngs\\ProJmlsc\\PCS-3-PSS-1Bl-l PT 77.0GN

PHASED ARRAY SCAN LIMITATIONS WELD PCS-3-PSS-IBI-I/PT 77 3

ELBOW TO NOZZLE TOTAL er(EXTRADOS)

CIRCUMFERENCE i

11"1 '

LENGTH NOT SCANNED 3" NOTE:

CIRCUMFERENTIAL SCAN (lNTRADOS) 180 0

I DRAWING NOT TO SCALE LENGTH NOT SCANNED 4 U

KXX><1 - AREA NOT SCANNED

[ 73 - AREA SCANNED er(EXTRADOS)

AXIAL SCAN (lNTRADOS) 18r2r L:\\CAD-Project Drowmgs\\ProJmlsc\\PCS-3-PSS-IBI-1 PT 77-2.DGN

SCAN COVERAGE NOT ACHIEVED IN LIMITED AREA WELD PCS-3-PSS-IBI-I/PT 77 4

ELBOW TO NOZZLE RXXX1 - AREA NOT SCANNED TRANSDUCER I t NOZZLE I

I I

NOTE:

DRAWING NOT TO SCALE L:\\CAD-ProJect Drawlngs\\ProJm15c\\PCS-3-PSS-1Bl-l PT 77-1.DGN

WELD CONFIGURATION AND COVERAGE

SUMMARY

WELD PCS-3-PSS-2AI-I/PT 275 1

ALLOY 600 NOZZLE (Y).

(S)

ELBOW TO NOZZLE 1.0" I,

I I

1.5" I

WELD OUTLINE SUSCEPTIBLE MATERIAL UPPER 2/3 73% CIRCUMFERENTIAL SCAN 60% AXIAL SCAN CODE REOUIRED VOLUME 72.8% CIRCUMFERENTIAL SCAN 63.6% AXIAL SCAN 111111111111 -

SUSCEPTIBLE MATERIAL LOWER 1/3 72.8% CIRCUMFERENTIAL SCAN 63.6% AXIAL SCAN NOTE:

DRAWING NOT TO SCALE L:\\CAD-ProJect Dr<>wmgs\\PrOJmlsc\\PCS-3-PSS-2AI-1 PT 275-3.DGN

NOZZLE NOZZLE L

NOTE:

DRAWING NOT TO SCALE PHASED ARRAY SCAN DIAGRAM WELD PCS-3-PSS-2Al-l/PT 275 ELBOW TO NOZZLE 2

40° TO 70° I,

I I,

I

~

K><X':Xl - AREA NOT SCANNED Ez73 - AREA SCANNED TRANSDUCER (lyP)

ELBOW ELBOW AXIAL SCAN CIRCUMFERENTIAL SCAN L:\\CAO-ProJect OrOWln95\\ProJm15c\\PCS-3-PSS-2Al-1 PT 275.0GN

PHASED ARRAY SCAN LIMITATIONS WELD PCS-3-PSS-2AI-I/PT 275 ELBOW TO NOZZLE TOTAL 0° (EXTRADOS)

CIRCU~~REN, i,

LENGTH NOT SCANNED 3" NOTE:

CIRCUMFERENTIAL SCAN ONTRADOS) 180 0

I DRAWING NOT TO SCALE LENGTH NOT SCANNED 4" K><X'><J - AREA NOT SCANNED

[==3 - AREA SCANNED 0°(EXTRADOS)

AXIAL SCAN ONTRADOS) 180 0

3 L:\\CAO-ProJect Or".. mgs\\ProJmlsc\\PCS-3-PSS-2AI-l PT 275-2.0GN

NOTE:

SCAN COVERAGE NOT ACHIEVED IN LIMITED AREA WELD PCS-3-PSS-2AI-I/PT 275 ELBOW TO NOZZLE K><"X'Xl - AREA NOT SCANNED n ---7] - AREA SCANNED TRANSDUCER I t I

NOZZLE DRAWING NOT TO SCALE 4

L:\\CAO-ProJect Or""ln9,,\\PrOJmlsc\\PCS-3-PSS-2AI-1 PT 275-I.OGN

ENCLOSURE 2 References

1.

VEN M1-LA Sheet 1 - Palisades PORV Nozzle Safe End/Spool Piece Replacement

2.

VEN M1-LA Sheet 2 - Palisades PORV Nozzle Safe End/Spool Piece Replacement

3.

VEN M 1-LA Sheet 3 - Palisades PORV Nozzle Safe End Replacement Hardware

4.

VEN M1-LA Sheet 4 - Palisades PORV Nozzle Safe End/Spool Piece Field Machining 4 Pages Follow

H G

c 3

9il.......
aIJ1I......

PRESSURIZER UPPER HEAD PLAN

~'J:!,.=,

5f~.foITO DlaT'.. IN'& DO

~I.::lu~ TO--.. ~

EXISTING CONFIGURATION

'mfol.I..'?

IIITMI. rw. _T'~

.,.HI-u.,... WP' IIU'r,..

~,..,,,.. I'\\IJ.. PllCTMTlOlf

.r A I I. =""-"Il'~ffi".'"...... II1D1. oGD.& -

&. ~

.. 'mr..,~'~

I. =..:.:tr.'''''.'1411",. _ITI~

  • . w:... __

"f.I"II'A..~ Of'"

  • . Wi: ~~S:TI~
  • IIIC1' wa.D M't
  • 1T.w.
7. PINAL..... MZ W4IU... MT... rat...
  • PIMf u....- -.e.L......... "... Tk.

'M P(1WT U'"..-...L. III1T *

'4IClLATID lUll_ rttw. ~1Nl".

I

~

H 3

~

/ ~

...,...... TU.. CIWI.. li!iiiii A

V' SECTION A-A Y~1'I1:L'" $1 REV.O

H
Ei£I-W DET A I L A 12211!578 IZ~4 go 13 I

I ::>

I"

.n n

n

~

~

1... ItM STEP I EXISTING CONFIOURATlON

~

WELDINO FITUI' t""" IN"",,,IOII" 1~""'ln.. ~ I '

(w.III:t Col) MIU CMIQJt COtTbth F\\LL "l-.(r-.,ION WI "IIr~J "'Il

!'!1 if¥"~::'

titM.(

  • .11 o

STEP 2 DEPOSI T WELD OVERLAY

~

tf;~

STEP 3 MACHINE WELD I'M' DETAIL II ICT."

1.1~'~..i:'<<G=Jo;...U"~"'ru\\!.r~~r

l. eE\\W~~ili£tr'_'~D~tw.

S."LOI'~,.l't.I'~~ ru::"t~Lcr KI~~~~,=-~~~-~JL 4.1:Z~~~Ii;1:v~~&=tCfJr fH(

LU'...,.. MillY MI ""'" fIUI..,.,.

  • . ~'~.1~~j:tun.o UP".,.T 7."*""'.T DttCNSIOJI'\\ -.: IlCItCAfU., AN ASfUlt"",,'iIt
    • l:~"'PT.A::~=.z:'~"!~rJJ~

1:w:!i'lo-

.1..

STEP *

~ __ ~~~~~~:v.~

________ ~~i:::::~~~::::::~~~

REPLACEMENT HAIIDWA!tE 6

.. w f...-n ~"

IF.

~

IC.~ _-.a: K"I!'III_ I'CfI -. *...-...

.... =....oC!.!.~:r.:\\"~~_

iB :1'

- '7~

~-- ~

ir-'I-I

--~---'

I

'R._..

. ;:;tnH.. "L...

'\\:::!:::J

EEl

--- --. -.---r--;-*--*-c----I ---

STEP 1 PRELIMINARY MACHINING

~l:;JU

~~I!,:E,)

SZIIIZ II'.,.V T'Ll STEP 2 WELDING

[~-~

~~~~~~~~~k~~~---.

~ssss4

~-------------------~~.M------------------_i r....

~~.."p STEP 3 FINAL MACHINING o REPLACEMENT SAFE END/SPOOL PIECE LMII..l.~=-'".::tt."'~~ ~I.:.I:!""" I~u...

.. 'r.:'i1!.~&'f~.::.I."'U" ~Tf~_

'~':l'\\Ml..g,~

So'l:"1&'.f...:l'lo'Wd'lfl :;,tr r.=""-..,l..;:.,.

4..."...... fNCIM2\\.lf1'...... _

MtIII"'...... t.... " 'PeS.

.............. Dlll'RTIGJII "'"'" as llltuUIID.

""I\\~':1m 'W'~.w.u - ---

7, C~.'rnm. GIl ITM&OI4T~ 0' nc..... fINaL *

""""Tf:J~'=~,'.:&.~;S.~

  • I'ROYIDIO iBMiie~.... :.

rm::JiD!III

....,- _...,......,.qy","-,,,

wu:~=---=;:e:=.,r::.~

2 3

R.2S1'.e3

!5 6

A sa: tint)

C24M' G

i===rl

-'-------T-

no. "J i

I I

. I t.."\\ '1." V. _~.I-. -.-. -. -. -.- --J

'-'-'~"T'

o REPLACEMf:NT SAFE END/SPOOL PIECE ASS' Y

~~ l"MA'r I

~

J

.. -.... _.:~~:l !

I

\\ [

1~'t2: A

_.. _..... i ~

.. U3H1N

'-II-

"loe DETAIL A c

o F

II NOT'S;.

'*=~"~i~cf!w~:~'!'i~~~

z. ~~fl~I~N12 :"~HT::.~t~.18. g'I.rl47.:e~
l.,~ '-E";iJ,!4 ~~':k~:-\\ ~tT~O~~JtFU JrJ,\\.IoCS MO. '~EP * :JJ TRAVE......

~-' ** II\\:...... ~'NG OlST 8[TVl.IH PiPit,.., NOZA( IHOI. THI

""'SUte:MfWT 15 T:g lAteEN M'UR MACHINING w'L.a I'fIEP5 THE NOZZL(

AHD"',]'J!.

  • itT NI!W SUfi'FAtES...,TEA MACH1NlNG-I 1;

I' 2 r

t. r

~

3 I! Ii Ii I:

I

~ I r

~

il II t

1:

\\:

I.

ENCLOSURE 3 Flaw Evaluation 40 Pages Follow

ATTACHMENT 9.1 ENGINEERING REPORT COVER SHEET & INSTRUCTIONS Engineering Report No.

PLP-RPT-12-OO091 Rev 0

ENTERGY NUCLEAR Engineering Report Cover Sheet Engineering Report

Title:

Page _I _

of 40 PWSCC Crack Growth Evaluation of Palisades PORV Nozzle Weld Postulated Flaw IPI 0 ANOI 0 EC No. 3698S New

~

IP2 0 AN02 0 Engineering Report Type:

Revision 0 IP3 0 ECH 0 Cancelled o

Superseded 0

Superseded by:

App6cable Site(s)

JAF 0 GGNS 0 Report Origin:

PNPS 0 RBS 0 VY 0 WF3 0 o Entergy 18I Vendor WPO 0 PLP

~

Vendor Document No.: _______ _

Quality-Related:

18I Yes o No

~epMedby : ____

~V~en~d~o~r~-~S~tru~c~t~ur~a~II=n~te~g~ri~ty~A~Ss~o~ci~at=e~s ___ ___

Responsible Engineer (Print Name/Sign)

Date: ----

Design Veri tied: ____

-=D;.;;e.;;.;si;6;lg.;.;.n....:V-=e.::..;ri.::..;fi.;;,;ca~l.::..;io~n~pe..=.:..:r~.;;,;or:..::;me=dc...;b;.o/,y_V;,.,;e:.:;n:.::d.;;,;or=---__

Design Verifier (if required) (Print NamelSign)

Date: -----

Reviewed by:

HM Stacks ?IA Jf;L Date:

Date:

EN-OC-147 REV 5

l)

Stlvcturallntegrity Associates, Inc."

CALCULATION PACKAGE PROJECT NAME:

Palisades PORV Nozzle Flaw Evaluation CONTRACT NO.:

10348796 CLIENT:

Entergy Arkansas Inc.

CALCULATION TITLE:

PLANT:

Palisades File No.: 1200535.301 Project No.: 1200535 Quality Program: IZI Nuclear 0 Commercial PWSCC Crack Growth Evaluation of Palisades PORV Nozzle Weld Postulated Flaw Document Affected Revision Pages o

1-20 A-I - A-19 Revision Description Initial Issue Project Manager Approval 10;; & Date

.... H_-

tV'rr~

Barry Smith 4/30112 Preparer(s) &

Checker(s)

Signatures & Date

~~

S.S. Tang 4/30/12

~i2 G. A. Miessi 4/30/12 Page I of20 F0306*01RI

Table of Contents

1.0 INTRODUCTION

......................................................................................................... 4 2.0 TECHNICAL APPROACH.......................................................................................... 4 3.0 DESIGN INPUTS.......................................................................................................... 4 3.1 Nozzle Dimensions and Material Specification................................................4 3.2 Operating Conditions and Loadings.................................................................. 5 4.0 ASSUMPTIONS............................................................................................................ 5 5.0 CALCULATIONS......................................................................................................... 5 5.1 Screening Criteria.............................................................................................. 5 5.2 Allowable Flaw Size.......................................................................................... 6 5.3 Crack Model...................................................................................................... 6 5.4 Stresses.............................................................................................................. 7 5.4.1 Normal Operating Stresses................................................................................ 7 5.4.2 Weld Residual Stress.......................................................................................... 7 5.5 Crack Growth Evaluation.................................................................................. 8 5.5.1 Primary water stress corrosion cracking.......................................................... 8 6.0 RESULTS OF ANALySIS........................................................................................... 9 6.1 Pressure Stress................................................................................................... 9 6.2 Allowable Flaw Size.......................................................................................... 9 6.3 PWSCC Crack Growth...................................................................................... 9

7.0 CONCLUSION

S AND DISCUSSIONS....................................................................... 9

8.0 REFERENCES

............................................................................................................ 10 APPENDIX A PC-CRACK' OUTPUT............................................................................. A-I File No.: 1200535.301 Revision: 0 List of Tables Page 2 of20 F0306*01RI

Table 1: Crack Growth Results............................................................................................... 12 List of Figures Figure 1: Nozzle Configuration.............................................................................................. 13 Figure 2: Nozzle Dimensions................................................................................................. 14 Figure 3: Determination of Failure Mode............................................................................... 15

  • Figure 4: Semi-Elliptical Longitudinal Crack in Cylinder..................................................... 16 Figure 5 : As-Welded Residual Stress..................................................................................... 17 Figure 6: Curve-fitted As-Welded Hoop Residual Stress....................................................... 18 Figure 7: Stress Intensity Factor............................................................................................. 19 Figure 8: Crack Growth Results in Onlay Region.................................................................. 20 File No.: 1200535.301 Revision: 0 Page 3 of20 F0306-01RI

1.0 INTRODUCTION

A relief request is submitted by Entergy for waiving the baseline examination of the power operated relief valve (PORV) nozzle dissimilar metal weld (DMW) for axial flaws for one plant operating cycle due to lack of sufficient coverage. The safe end/spool piece was replaced in 1995. It contains an Alloy 52 partial onlay covering the Alloy 82/182 nozzle butter and the original DMW remnant.

This calculation is to perform an evaluation on the primary water stress corrosion cracking (PWSCC) crack growth such that a postulated initial flaw in the onlay would not growth through the onlay and the weld butter/remnant within an additional 2 years.

2.0 TECHNICAL APPROACH The evaluation consists of

1. Allowable flaw size evaluation based on the guidelines of ASME B&PV Code,Section XI, IWB 3600 and Appendix C [4]
2. Evaluation of the PWSCC to compare end of evaluation period flaw size to the allowable flaw size. The crack growth analysis is based on a postulated crack in the onlay, stress and crack growth rates from pertinent MRP documents [6, 7, 9]. The evaluation period includes operation since the replacement of the safe-end/spool in 1995 plus one additional fuel cycle of 18 months.

3.0 DESIGN INPUTS 3.1 Nozzle Dimensions and Material Specification The Palisades PORV nozzle is a 6 inches outside diameter component, cOIUlected to a safe-end/spool piece assembly, as shown in Figure 1 [1]. At the connection with the nozzle, the safe-end has an OD of 6 inches and, at the other end of the assembly, the spool piece is 4 inches, Schedule 120. The detail dimensions of the nozzle to safe-end weld are shown in Figure 2 [2].

At the weld onlay location, the PORV nozzle inside diameter is 2.75 inches with an outside diameter of 6.5 inches, resulting a wall thickness of 1.875 inches. There is also a remnant of the previous Alloy 182 (Alloy 600) Ni-Cr-Fe weld [1]. The weld butter along with the previous weld remnant is at least V4 inches wide. The thickness of the onlay is 0.125 inch [1]. The width of the onlay is not provided in Figure 2 [2] but should be wider than V4 inches, the width of the butter with weld remnant.

The pressurizer head nozzle is low alloy steel, A-508-64 Class 2, similar to SA 508 Class 2 [Section 5.2, 3] with Type 304 stainless steel cladding [Section 5.2, 3]. The nozzle safe end is SA-479 Type 316 File No.: 1200535.301 Revision: 0 Page 4 of20 F0306-01RI

[Sheet 3, 1]. The attached piping is SA-376 TP 316 [Section 5.2, 3]. The weld butterlremnant is Alloy 182 Ni-Cr-Fe [1].

The replacement weld is Alloy 52 [1] with GTA W weld procedure [Note 4, 2].

3.2 Operating Conditions and Loadings The operating pressure and temperature of the pressurizer PORV nozzle are 2100 psia and 643 of, respectively [Table 6-1 and Section 8.2, 3].

The minimum yield strength and tensile strength at normal operating temperature of Alloy 600 (based metal of Alloy 182) is 29.7 ksi and 80.0 ksi, respectively, [Table 6-1, 3].

The minimum yield strength and tensile strength of Alloy 690 (base metal of Alloy 52) is 27.5 ksi and 80 ksi at 650 F [4].

4.0 ASSUMPTIONS The following assumptions are used:

1. Alloy 182 is assumed to have the same mechanical material properties as Alloy 600, its equivalent base material. Alloy 182 is the corresponding weld wire for Alloy 600 and their compositions closely match.
2. The flaw is postulated to be an active stress corrosion flaw. Fatigue crack growth rate is much smaller compared to PWSCC and not considered in this evaluation.
3. The flaw is contained in the Alloy 182 remnant weld and butter.
4. No weld repair is assumed. UT was performed during the replacement of the safe end/spool pIece.
5. A flaw is postulated to exist from the time of the replacement of the safe-endIDMW weld.

5.0 CALCULATIONS 5.1 Screening Criteria The determination of the failure mode: limited load (LL), Elastic-Plastic Fracture Mechanics (EPFM) or Linear Elastic Fracture Mechanics (LEFM). is per ASME Boiler and Pressure Code (B&PV),Section XI Appendix C, Article C-4000 [4], reproduced in Figure 3. The failure mode depends on product form, flaw location (in weld or base metal) and type of weld.

File No.: 1200535.301 Revision: 0 Page 5 of20 F0306-01RI

5.2 Allowable Flaw Size Appendix C of the ASME B&PV Code,Section XI [4] provides the procedure for determining the allowable flaw sizes in piping component based on the failure mode as described in Section 5.1. For LL or EPFM failure modes, the allowable flaw sizes depend on the stress ratio. For LEFM failure mode, the allowable sizes are based on applied stress intensity factor, K and material fracture toughness, K1c.

The stress ratio is defined as:

SR = SFmO"h O"f SR = O"h O"f where O"h = pRm/t for LL failure mode for EPFM failure mode SF m

= safety factor per Article C-2622 of Section XI [4]

Rm = mean pipe radius t

= pipe wall thickness O"r = flow stress

= (O"y+ O"u)/2 O"y = yield strength o"u = ultimate strength (1)

(2)

(3)

The allowable flaw sizes for LL and EPFM failure modes are determined from Table C-5410-1 and Table C-6410-1 to 2 for an axial flaw under different operating conditions, respectively.

5.3 Crack Model An elliptical longitudinal crack in a cylinder model [5], illustrated in Figure 4, is used in the evaluation.

This crack model is subjected to an arbitrary stress profile expressed a 3rd order polynomial The stress intensity factor, K, is given in the general form of where KI = stress intensity factor, Mode I Fi = influence coefficients, File No.: 1200535.301 Revision: 0 (4)

(5)

Page 6 of20 F0306-01RI

Cj = coefficients in Eq (4)

=index for 0, 1, 2, or 3 Per the guidelines of Reference 4, a flaw aspect ratio oflla = 6 is used in the onlay region. For the PWSCC crack growth in the weld butter/remnant region, a semi-circular flaw is used based on the understanding that the growth in the length direction due to PWSCC is limited to the width of the weld butter/remnant.

5.4 Stresses 5.4.1 Normal Operating Stresses For the evaluation of the postulated axial flaw, the operating stresses are due to pressure. For an axial crack, the applied loading is hoop stress due to internal pressure which is calculated using the thin - wall cylinder equation with the outside radius. This is more conservative than using the thick-wall equation even-though the radius to thickness ratio at the weld location is less than 10. The hoop stress is calculated as:

PR u h =-

t where O'h = hoop stress R = outside radius t

= wall thickness (6)

Equation (6) is also conservative compared to the hoop stress calculated from Equations (1) and (2) because of the use of outside radius.

5.4.2 Weld Residual Stress From Reference 2, it is shown than the onlay is part of the machine weld prep before the Alloy 52 butt weld is performed. Thus, the weld residual in the nozzle to safe-end weld is primarily due to the typical butt weld residual stress, since any residual stress from the onlay is heat treated from the welding of the butt weld.

Typical as-welded through-wall residual stress in the RPV outlet nozzle and pressurizer surge nozzle are provided in Reference 6 and shown in Figure 5. These weld residual stresses are provided at the center line of the weld. It is shown that these as-welded residual stress through-wall distributions are very similar, at an almost constant 55 ksi through the wall thickness, t, from about 20% to 100% of the wall thickness. The wall thickness at the weld location of these two nozzles is about 2.5 inches and at a larger diameter. Also, these residual stresses are much higher than the yield strength of the current weld metal of Alloy 52, at 27.5 ksi. In addition, the postulated flaw is at the weld butter and remnant, not at the center of the weld; therefore, the applied residual stresses are expected to be lower.

File No.: 1200535.301 Revision: 0 Page 7 of20 F0306-0tRt

In addition MRP 109 [9] provides guidance on a generic welding residual stress distribution for austenitic pipe welds. For an axial crack under hoop stress, a 15 ksi constant through-wall residual stress is proposed.

The residual stress depends on the material yield strength and the component wall thickness. Higher yield strength would produce higher residual stress. Greater wall thickness would reduce residual stress on the inside surface. Since the PORV nozzle has a thinner wall thickness than the RPV nozzle and Alloy 52 has a lower yield strength than Alloy 821182, the effect of these two conditions would tend to offset each other. Considering the offsetting effects, the higher as-welded residual stresses from the RPV nozzle case, Figure 5 (a), is used in the flaw growth evaluation.

The through-wall as-welded hoop residual stress in Figure 5 (a) is curve fitted to a 3rd order polynomial for use in the PWSCC crack growth evaluation.

5.5 Crack Growth Evaluation 5.5.1 Primary water stress corrosion cracking The general form of the PWSCC for Alloy 182 is as follow [7]

[Qg (1 1 J]

P a = exp - R T - T ref

\\ c4"alloyforienrK where a = crack growth rate at temperature (in/h)

Qg = thermal activation energy for crack growth (31.0 kcaVmole)

R = universal gas constant (1. 1 03xlO-3 kcaVmole-OR)

T = absolute operating temperature at location of crack, (OR)

Tref= absolute reference temperature used to normalize data (l076.67°R) a

= power law constant, 2.47x1O-7 at 617 OF falloy

= 1.0 for Alloy 182/132, 0.385 for Alloy 82 forien t = 1. 0 K = crack tip stress intensity factor (ksi.Jin)

~ = exponent, 1.6 (7)

Per References 8 and 10, the MRP-115 [7] PWSCC rate for Alloy 182 with a factor of 100 reduction (slower) is used for Alloy 52.

For crack growth analysis, crack growth rate for Alloy 52 is used in the onlay. When the crack grows into Alloy 182, the rate switches to Alloy 182 crack growth rate.

A postulated initial crack size of 0.0625 inches, per the recommendation of Reference 10, is used.

File No.: 1200535.301 Revision: 0 Page 8 of20 F0306-01RI

The fracture mechanics evaluation of the postulated flaw in the weld butter/remnant is performed using the fracture mechanics program pc_CRACK' [11].

6.0 RESULTS OF ANALYSIS 6.1 Pressure Stress Using Equation (6), with a pressure of2085 psig, outside radius of3.25 inches and wall thickness of 1.875 inches, the pressure hoop stress is calculated to be 3.61 ksi.

6.2 Allowable Flaw Size The flow stress for Alloy 600 is (80 + 29.7)/2 = 54.85 ksi. With SFm = 2.7 from Subarticle C-2622 [4]

for normal operating conditions, the stress ratio is calculated to be 2.7*3.61/54.85= 0.18.

Since the welding procedure is GTA W [2], the failure mode would be LL based on the determination of failure mode shown on Figure 3. The allowable size from Table C-541O-1 [4] for a stress ratio of 0.18 is 75% of the wall thickness for any flaw length.

6.3 PWSCC Crack Growth Due to the limitation of the crack model, a wall thickness of 1.875 inches with a R/t= 1 instead of the actual R/ t = 0.73 is used to calculate the stress intensity factor and crack growth. The use of a larger R/ t in the crack model is conservative because it would give a higher stress intensity factor. In addition, the stress due to pressure is adjusted by a factor of 1.58 to account for the crack face pressure of2085 psig.

The curve fit to Equation (4) of the as-welded residual hoop stress is shown in Figure 6. The pressure stress is taken as constant through-wall using Co in Equation (4).

The stress intensity factors due to pressure and as-welded residual stress are shown in Figure 7.

The crack growth results for the onlay are presented in Figure 8. The crack growth results for both the onlay and Alloy 182 are summarized in Table 1.

The output from pc_CRACK' is attached in Appendix A.

7.0 CONCLUSION

S AND DISCUSSIONS An evaluation has been performed for a postulated flaw in the onlay for crack growth due to PWSCC.

The evaluation used the hoop stress due to operating pressure and a conservative residual stress profile.

Different crack growth rates were used for Alloy 52 onlay and Alloy 182 weld butter/remnant. A semi-File No.: 1200535.301 Revision: 0 Page 9 of20 F0306-01RI

elliptical flaw with an aspect ratio of lIa = 6 was used in the onlay region but switched to a semi-circular flaw within the Alloy 182 to account for the fact that the PWSCC crack growth in the width direction would remain within the PWSCC susceptible Alloy 182.

It is shown that it takes 23.86 years for a postulated initial crack size of 0.0625 inches to grow through the onlay. Once it reaches the Alloy 182, it takes only 1.03 years to grow to the allowable flaw depth.

It should be noted that the evaluation presented is conservative as described below:

8.0

1.
2.
3.
4.
5.
6.
7.

This residual stress profile used in the fracture mechanics and crack growth evaluation is conservative. The maximum residual stress of - 55 ksi is higher than 0.5 Sy of the yield strength of Alloy 182. At the inside surface, the residual stress of 20 ksi is also higher than 0.5 Sy of Alloy 52. MRP-109 recommends the use ofa constant hoop residual stress ofO.5S with S=30 ksi for Alloy 821182 DMW butt weld..

A semi-circular flaw is used in the Alloy 182 butter/remnant. For consideration ofPWSCC in the weld butter/remnant Alloy 182, the flaw would grow in a tunneling fashion. The assumed semi-circular crack would give a higher stress intensity factor than a tunneling flaw at the deepest point of the crack.

The residual stresses at normal operating conditions are expected to be less than in the as-welded condition.

REFERENCES Drawing #VEN-M1-L-A, Sheets 2 and 3, 'Palisades PORV Nozzle Safe End Spool Piece Replacement,' Rev. O.

Drawing #1230804E (VEN-MI-L-A, Sheet 1, Rev. 0), 'Palisades PORV Nozzle Safe End/Spool Piece Replacement,' Rev. o.

EA-A600-05, 'Alloy 600 Program-Inputs, (BWNT Calc. No. 51-1235040-00), Rev. 0,2/15/95.

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

American Petroleum Institute, Fitness for Service, API 579-1 / ASME FFS-1, June, 2007.

Materials Reliability Program: Evaluation of the Effect of Weld Repairs on Dissimilar Metal Butt Welds (MRP-114), EPRI, Palo Alto, CA: 2004, 1009559.

Materials Reliability Program: Crack Growth Rates for Evaluating Primary Water Stress Corrosion (PWSCC) of Alloy 82, 182, and 132 Welds (MRP-115), EPRI, Palo Alto, CA: 2004, 1006696.

8. Memorandum, T. R. LupoId,

Subject:

Summary of Public Meeting between the Nuclear Regulatory Commission Staff and Industry Representatives on Implementation of ASME Code Case N-770-1, August 12,2011.

9. Materials Reliability Program: Alloy, 821182 Pipe Butt Weld Safety Assessment for US PWR Plant Designs: Westinghouse and CE Design Plants (MRP-109), 1009804, July, 2004.

File No.: 1200535.301 Revision: 0 Page 10 of20 F0306-01RI

10. Ruland, D. L., Brust, F., Zhang, T., Shim, D. 1., Wilkowski, G. 'Evaluation of the Onlay Process as a Mitigation Strategy for Primary Water Stress Corrosion Cracking in Pressurized Water Reactors,' A~ril, 2010.
11. pc-CRACK M, Version 4.0.1, Structural Integrity Associates, 2010.

File No.: 1200535.301 Revision: 0 Page 11 of20 F0306-01RI

Region Onlay Alloy 182 File No.: 1200535.301 Revision: 0 Table 1: Crack Growth Results Crack Size in)

Initial Final 0.0625 0.125 0.125 1.56 Time (year) 23.86 1.03 Page 12 of20 F0306-OIRI

File No.: 1200535.301 Revision: 0 I

~

I t::::-:::::..~-

PRESSl.fl I ZEi'! UPPER HEAD PLAN

-~. -

!iIfI'>NG *

.;;w

~

i. :r..~""".-

EXIST ING CONFIG'JRAT!ON OETAiL. A Figure 1: Nozzle Configuration

~..

_-c:.'I:D"'I.&r~

~-

"l!l:iW~fI'

'1!5I."IM~~

""!:II1'.:I.l".a=rI-<l:-'-

~~~~

...... 1l"&:&&.-----

.a.mD~

"-....r----

...=........... A:M_

~~--

..==~~.::;:;..-:.:..

Page 13 of20 F0306-01RI

File No.: 1200535.301 Revision: 0 DETAIL A STEP 3 MACHINE WELD PREP OETAII.. A Figure 2: Nozzle Dimensions Na<t--".

BUTiERING Page 14 of20 F0306-01RI

Base material flaw C-5000 C-4210 Wrought product I

I Weld material flaw Nonflux welds C-5000 L

Ferrite

<20%

Flux welds C-6000 t

Cast product I

Ferrite

'20%

In the course of preparation FIG. C-4210-1 FLOWCHART FOR SELECTING ANALYSIS METHOD FOR AUSTENITIC PIPING File No.: 1200535.301 Revision: 0 Figure 3: Determination of Failure Mode Page 150[20 F0306-01RI

File No.: 1200535.301 Revision: 0

-~.~- -- --~.. t - ____. __

u T

2c 1

I I

--.._._. __. ___. __ J u. _

- ~-

Figure 4: Semi-Elliptical Longitudinal Crack in Cylinder Page 16 of20 F0306*01RI

70000 60000 50000 40000 30000 t::- 20000

! 10000 II) i 0

II).10000 Thru Wall Stesses (Weld Centerline)

~ - -

/

~

-'"'~

~

~

/

L

~

~

..... ~

  • 20000
  • 30000

-40000

  • 50000

~

o 70000 60000 50000 40000 30000 20000 10000 o

  • 10000

-20000

-30000

-40000

-50000

-60000 File No.: 1200535.301 Revision: 0 10 20 30 40 50 60 70 Percentage Through Wall (from 10)

(a) RPV Outlet Nozzle Thru Wall Stresses (Weld Centerline)

~

./

L

~

~

~

./'

o 20 40 60 80 100 Percentage Through Wall (from ID)

-- Axial

.......... Hoop I (b) Pressurizer Surge Nozzle Figure 5: As-Welded Residual Stress so 100 Page 17 of20 F0306-OJRI

60

~

-. * *.-~

~

~

~

V Iv = 10.413x3 - 53.744x2 + 82.529x + 16.6231

.~

50 I.

/,

I 10 o

o 0.2 File No.: 1200535.301 Revision: 0 Hoop Stress Poly. (Hoop Stress) 0.4 0.6 0.8 1

1.2 1.4 1.6 1.8 2

Crack Depth (in)

Figure 6: Curve-fitted As-Welded Hoop Residual Stress Page 18 of20 F0306-OIRI

160 140 -

~ Pressure

~As-welded Residual 120 100 C

~

I 80

-iii lII:

60 40 20

./ /"

./ /"

/ /'

/

V-

/'

o o

0.2 0.4 0.6 0.8 1

Crack Depth (in)

Figure 7: Stress Intensity Factor File No.: 1200535.301 Revision: 0

/

/

/"

V 1.2 1.4 1.6 Page 19 of20 F0306-01RI

0.3....----:--.....,--- ---- ----

0.2 Q)

N i:i5 u

ro U 0.1 o

5 10 15 20 25 30 35 40 Blocks Note: 1 block corresponds to 1 year File No.: 1200535.301 Revision: 0 Figure 8: Crack Growth Results in Onlay Region Page 200[20 F0306-01RI

File No.: 1200535.301 Revision: 0 APPENDIX A PC-CRACK' OUTPUT Page A-I of A-19 F0306-01Rl

Output for Onlay Region pc-CRACK 4.0 Version Control No. 4.0.1.0 (LEFM + Codes & Standards)

Structural Integrity Associates, Inc.

www.structint.com info@structint.com Date: 04/30/2012 14: 13 Input Data read from D:\\E_Drive\\Palisades-PORV-1200535\\MRPI14Inlay.pcf Analysis

Title:

Palisades Units Selected: US Customary Linear Dimensions - inches Stress - ksi Temperature - deg F Time - hours Analysis Type: Crack Growth (LEFM)

Crack Growth Calculation Method - Cyc1elTime Stepping Maxinum Number of Load Blocks = 40 Block Print Interval = 1 Crack Model: 305-Semi-Elliptical Longitudinal Crack in Cylinder on the Inside Surface (API 579)

Crack Depth, a =

0.0625 Half Crack Length, c =

0.1875 Wall Thickness, t =

1.8750 Inside Radius, Ri =

1.8750 Aspect ratio fixed Maximum alt = 0.8 Crack Depth Print Increment for SIF Tabulation = 0.1 Total Load Cases: 2 Load Case 1 :Pressure Type: Stress Coefficients Input by User Coefficient CO =

Coefficient C 1 =

File No.: 1200535.301 Revision: 0 3.6140 0.0000 Page A-2 of A-19 F0306*01Rl

Coefficient C2 :=

Coefficient C3 :=

0.0000 0.0000 Load Case 2:MRP-114 Rsd Type: Stress Coefficients Input by User Coefficient CO :=

Coefficient C 1 =

Coefficient C2 :=

Coefficient C3 =

16.6230 82.5290

-53.7440 10.4130 Total Load Sub-Blocks: 1 Load Sub-Block # 1 Load Sub-block Name: PWSCC Maximum Load Case Multiplier Load Case ID 1.5800 Pressure 1.0000 MRP-114 Rsd Growth Law: PWSCC Cydesffime: 8760 Temperature: 643 Calc. Interval: 10 Print Interval: 4000 Material: 1 Sample Material 1: Only a sample PWSCC Equation QglR :=

2.818E+04 Tref =

617.0000 alpha :=

2.470E-09 beta =

1.6000 K Threshold =

0.0000 f-alloy

=

1.0000 f-orient =

1.0000 Primary Water Stress Corrosion Cracking (PWSCC) Crack Growth Law The Crack Growth Rate (at temperature T) inlh (or m/h) is given by:

File No.: 1200535.301 Revision: 0 Page A-3 of A-19 F0306-01Rl

da/dt = exp[-Qg!R(l/(T+TO) - lI(Tref+TO)]*Alpha*falloy*forient*(Kmax)"Beta where Qg!R, Alpha, falloy, forient, Beta = empirical constants T = Temperature in deg R (or deg K)

TO = 273 deg C or 460 deg F depending on the selected units Tref= Reference Temperature in deg R (or deg K) da/dt = 0 for Kmax < K Threshold No. of Data in the KIC Table = 3 Crack Depth KIC 0.0000 1000.0000 0.1000 1000.0000 6.0000 1000.0000 messages/W arnings:

Number of Warnings in Inputs: 0

- - - - - - - - - - ANALYSIS RESULTS - - - - - - - - -

STRESS INTENSITY FACTORS Load Case # 1: Pressure

Crack Dimensions ------------

a c

aft cia a

0.0625 0.1875 0.0333 3.0000 0.1625 0.4875 0.0867 3.0000 0.2625 0.7875 0.1400 3.0000 0.3625 1.0875 0.1933 3.0000 0.4625 1.3875 0.2467 3.0000 0.5625 1.6875 0.3000 3.0000 0.6625 1.9875 0.3533 3.0000 0.7625 2.2875 0.4067 3.0000 File No.: 1200535.301 Revision: 0 K at tip 1.5503 2.4605 3.0774 3.5577 4.0890 4.6086 5.1092 5.6140 Page A-4 of A-19 F0306-01RI

e Bfnlc",,."/IIIftIIY Associates. Inc.-

0.8625 2.5875 0.4600 3.0000 6.2402 0.9625 2.8875 0.5133 3.0000 6.8767 1.0625 3.1875 0.5667 3.0000 7.5242 1.1625 3.4875 0.6200 3.0000 8.2850 1.2625 3.7875 0.6733 3.0000 9.2431 1.3625 4.0875 0.7267 3.0000 10.2350 1.4625 4.3875 0.7800 3.0000 11.2595 Load Case # 2: MRP-114 Rsd

Crack Dimensions ------------

K at tip a

c aft cia a

0.0625 0.1875 0.0333 3.0000 8.4869 0.1625 0.4875 0.0867 3.0000 16.6339 0.2625 0.7875 0.1400 3.0000 24.3493 0.3625 1.0875 0.1933 3.0000 31.7958 0.4625 1.3875 0.2467 3.0000 40.0742 0.5625 1.6875 0.3000 3.0000 48.5592 0.6625 1.9875 0.3533 3.0000 57.0299 0.7625 2.2875 0.4067 3.0000 65.5884 0.8625 2.5875 0.4600 3.0000 75.3843 0.9625 2.8875 0.5133 3.0000 85.2928 1.0625 3.1875 0.5667 3.0000 95.2656 1.1625 3.4875 0.6200 3.0000 106.5607 1.2625 3.7875 0.6733 3.0000 120.3105 1.3625 4.0875 0.7267 3.0000 134.4339 1.4625 4.3875 0.7800 3.0000 148.8767 CRACK GROWTH ANALYSIS RESULTS Total Subblock Cycles Cycles ITime ITime Kmax Kmin Blocks:

1 4000.0000 4000.0000 11.0264 8000.0000 8000.0000 11.1176 8760.0000 8760.0000 11.1350 Blocks:

2 1.276E+04 4000.0000 11.2273 1.676E+04 8000.0000 11.3205 1.752E+04 8760.0000 11.3383 Blocks:

3 File No.: 1200535.301 Revision: 0 DaDn DeltaK

/DaDt 2.131E-07

2. 160E-07 2.165E-07
2. 194E-07 2.223E-07 2.229E-07 a

0.0633 0.0642 0.0644 0.0652 0.0661 0.0663 aft 0.0338 0.0342 0.0343 0.0348 0.0353 0.0354 Page A-5 of A-19 F0306-01Rl

e 8tnR:Irn/I",.".", AssoclatJs, Inc.-

2.152E+04 4000.0000 2.552E+04 8000.0000 2.628E+04 8760.0000 Blocks:

4 3.028E+04 4000.0000 3.428E+04 8000.0000 3.504E+04 8760.0000 Blocks:

5 3.904E+04 4000.0000 4.304E+04 8000.0000 4.380E+04 8760.0000 Blocks:

6 4.780E+04 4000.0000 5.180E+04 8000.0000 5.256E+04 8760.0000 Blocks:

7 5.656E+04 4000.0000 6.056E+04 8000.0000

6. 132E+04 8760.0000 Blocks:

8 6.532E+04 4000.0000 6.932E+04 8000.0000 7.008E+04 8760.0000 Blocks:

9 7.408E+04 4000.0000 7.808E+04 8000.0000 7.884E+04 8760.0000 Blocks:

10 8.284E+04 4000.0000 8.684E+04 8000.0000 8.760E+04 8760.0000 Blocks:

11

9. 160E+04 4000.0000 9.560E+04 8000.0000 9.636E+04 8760.0000 File No.: 1200535.301 Revision: 0 11.4326 11.5279 11.5461 11.6426 11.7400 11.7586 11.8572 11.9569 11.9759 12.0768 12.1788 12.1983 12.3015 12.4058 12.4258 12.5314 12.6382 12.6587 12.7668 12.8762 12.8971 13.0079 13.1199 13.1413 13.2547 13.3695 13.3914 2.258E-07 0.0672 0.0358 2.288E-07 0.0681 0.0363 2.294E-07 0.0683 0.0364 2.325E-07 0.0692 0.0369 2.356E-07 0.0701 0.0374 2.362E-07 0.0703 0.0375 2.394E-07 0.0713 0.0380 2.426E-07 0.0722 0.0385 2.432E-07 0.0724 0.0386 2.465E-07 0.0734 0.0391 2.499E-07 0.0744 0.0397 2.505E-07 0.0746 0.0398 2.539E-07 0.0756 0.0403 2.574E-07 0.0766 0.0409 2.580E-07 0.0768 0.0410 2.615E-07 0.0778 0.0415 2.651E-07 0.0789 0.0421 2.658E-07 0.0791 0.0422 2.694E-07 0.0802 0.0428 2.731E-07 0.0813 0.0433 2.739E-07 0.0815 0.0434 2.776E-07 0.0826 0.0440 2.815E-07 0.0837 0.0446 2.822E-07 0.0839 0.0447 2.861E-07 0.0850 0.0454 2.901E-07 0.0862 0.0460 2.908E-07 0.0864 0.0461 Page A-6 of A-19 F0306-01Rl

(;ltntcln/I",.", Assocfates, Inc.-

Blocks:

12 1.004E+05 4000.0000 13.5077 2.949E-07 0.0876 0.0467 1.044E+05 8000.0000 13.6253 2.990E-07 0.0888 0.0473 1.051E+05 8760.0000 13.6478 2.998E-07 0.0890 0.0475 Blocks:

13 1.091E+05 4000.0000 13.7669 3.040E-07 0.0902 0.0481

1. 131E+05 8000.0000 13.8875 3.083E-07 0.0914 0.0488
1. 139E+05 8760.0000 13.9105 3.091E-07 0.0917 0.0489 Blocks:

14

1. 179E+05 4000.0000 14.0327 3.134E-07 0.0929 0.0495 1.219E+05 8000.0000 14.1563 3.179E-07 0.0942 0.0502 1.226E+05 8760.0000 14.1799 3.187E-07 0.0944 0.0504 Blocks:

15 1.266E+05 4000.0000 14.3052 3.232E-07 0.0957 0.0510 1.306E+05 8000.0000 14.4319 3.278E-07 0.0970 0.0517 1.314E+05 8760.0000 14.4562 3.287E-07 0.0972 0.0519 Blocks:

16 1.354E+05 4000.0000 14.5847 3.334E-07 0.0986 0.0526 1.394E+05 8000.0000 14.7148 3.382E-07 0.0999 0.0533 1.402E+05 8760.0000 14.7396 3.391E-07 0.1002 0.0534 Blocks:

17 1.442E+05 4000.0000 14.8715 3.440E-07 0.1015 0.0542 1.482E+05 8000.0000 15.0050 3.489E-07 0.1029 0.0549 1.489E+05 8760.0000 15.0305 3.499E-07 0.1032 0.0550 Blocks:

18 1.529E+05 4000.0000 15.1659 3.549E-07 0.1046 0.0558 1.569E+05 8000.0000 15.3029 3.601E-07 0.1060 0.0565 1.577E+05 8760.0000 15.3291 3.610E-07 0.1063 0.0567 Blocks:

19 1.617E+05 4000.0000 15.4681 3.663E-07 0.1078 0.0575 1.657E+05 8000.0000 15.6089 3.716E-07 0.1092 0.0583 1.664E+05 8760.0000 15.6358 3.727E-07 0.1095 0.0584 Blocks:

20 1.704E+05 4000.0000 15.7785 3.781E-07 0.1110 0.0592 1.744E+05 8000.0000 15.9231 3.837E-07 0.1125 0.0600 1.752E+05 8760.0000 15.9507 3.848E-07 0.1128 0.0602 File No.: 1200535.301 Page A-7 of A-19 Revision: 0 F0306-01Rl

Blocks:

21 1.792E+05 4000.0000 16.0974 3.904E-07 0.1144 0.0610 1.832E+05 8000.0000 16.2460 3.962E-07 0.1160 0.0618

1. 840E+05 8760.0000 16.2744 3.973E-07 0.1163 0.0620 Blocks:

22

1. 880E+05 4000.0000 16.4251 4.032E-07 0.1179 0.0629
1. 920E+05 8000.0000 16.5778 4.092E-07 0.1195 0.0637
1. 927E+05 8760.0000 16.6070 4.104E-07 0.1198 0.0639 Blocks:

23 1.967E+05 4000.0000 16.7620

4. 165E-07 0.1214 0.0648 2.007E+05 8000.0000 16.9190 4.228E-07 0.1231 0.0657 2.015E+05 8760.0000 16.9491 4.240E-07 0.1234 0.0658 Blocks:

24 2.055E+05 4000.0000 17.1085 4.304E-07 0.1252 0.0668 2.095E+05 8000.0000 17.2700 4.369E-07 0.1269 0.0677 2.102E+05 8760.0000 17.3009 4.382E-07 0.1272 0.0679 Blocks:

25 2.142E+05 4000.0000 17.4649 4.448E-07 0.1290 0.0688

2. 182E+05 8000.0000 17.6310 4.516E-07 0.1308 0.0698 2.190E+05 8760.0000 17.6628 4.529E-07 0.1311 0.0699 Blocks:

26 2.230E+05 4000.0000 17.8316 4.599E-07 0.1330 0.0709 2.270E+05 8000.0000 18.0026 4.670E-07 0.1348 0.0719 2.278E+05 8760.0000 18.0354 4.683E-07 0.1352 0.0721 Blocks:

27 2.318E+05 4000.0000 18.2091 4.756E-07 0.1370 0.0731 2.358E+05 8000.0000 18.3852 4.829E-07 0.1390 0.0741 2.365E+05 8760.0000 18.4189 4.843E-07 0.1393 0.0743 Blocks:

28 2.405E+05 4000.0000 18.5978 4.919E-07 0.1413 0.0754 2.445E+05 8000.0000 18.7792 4.996E-07 0.1433 0.0764 2.453E+05 8760.0000 18.8139 5.011E-07 0.1436 0.0766 Blocks:

29 2.493E+05 4000.0000 18.9983 5.090E-07 0.1457 0.0777 2.533E+05 8000.0000 19.1851 5.170E-07 0.1477 0.0788 File No.: 1200535.301 Page A-8 of A-19 Revision: 0 F0306-01RI

e ltnlclu,. "rIIy AssocIatts, Inc.-

2.540E+05 8760.0000 19.2209 5.185E-07 0.1481 0.0790 Blocks:

30 2.580E+05 4000.0000 19.4109 5.268E-07 0.1502 0.0801 2.620E+05 8000.0000 19.6035 5.351E-07 0.1523 0.0812 2.628E+05 8760.0000 19.6404 5.368E-07 0.1527 0.0815 Blocks:

31 2.668E+05 4000.0000 19.8363 5.453E-07 0.1549 0.0826 2.708E+05 8000.0000 20.0349 5.541E-07 0.1571 0.0838 2.716E+05 8760.0000 20.0729 5.558E-07 0.1575 0.0840 Blocks:

32 2.756E+05 4000.0000 20.2749 5.648E-07 0.1598 0.0852 2.796E+05 8000.0000 20.4797 5.739E-07 0.1620 0.0864 2.803E+05 8760.0000 20.5190 5.757E-07 0.1625 0.0867 Blocks:

33 2.843E+05 4000.0000 20.7273 5.851E-07 0.1648 0.0879 2.883E+05 8000.0000 20.9387 5.946E-07 0.1672 0.0892 2.891E+05 8760.0000 20.9792 5.965E-07 0.1676 0.0894 Blocks:

34 2.931E+05 4000.0000 21.1942 6.063E-07 0.1700 0.0907 2.971E+05 8000.0000 21.4124 6.1 63E-07 0.1725 0.0920 2.978E+05 8760.0000 21.4542 6.182E-07 0.1729 0.0922 Blocks:

35 3.018E+05 4000.0000 21.6762 6.285E-07 0.1754 0.0936 3.058E+05 8000.0000 21.9015 6.390E-07 0.1780 0.0949 3.066E+05 8760.0000 21.9446 6.410E-07 0.1784 0.0952 Blocks:

36 3.106E+05 4000.0000 22.1739 6.518E-07 0.1810 0.0965 3.146E+05 8000.0000 22.4066 6.627E-07 0.1837 0.0980 3.154E+05 8760.0000 22.4512 6.648E-07 0.1842 0.0982 Blocks:

37

3. 194E+05 4000.0000 22.6880 6.761E-07 0.1868 0.0997 3.234E+05 8000.0000 22.9285 6.876E-07 0.1896 0.1011 3.241E+05 8760.0000 22.9745 6.898E-07 0.1901 0.1014 Blocks:

38 3.281E+05 4000.0000 23.2193 7.016E-07 0.1929 0.1029 File No.: 1200535.301 Page A-9 of A-19 Revision: 0 F0306-01RI

lJ8IntcInI,.,."" AssocIates. Inc.-

3.321E+05 8000.0000 23.4678 7.137E-07 3.329E+05 8760.0000 23.5155

7. 160E-07 Blocks:

39 3.369E+05 4000.0000 23.7685 7.283E-07 3.409E+05 8000.0000 24.0255 7.4lOE-07 3.416E+05 8760.0000 24.0748 7.434E-07 Blocks:

40 3.456E+05 4000.0000 24.3365 7.564E-07 3.496E+05 8000.0000 24.6023 7.697E-07 3.504E+05 8760.0000 24.6532

7. 722E-07 Maximum number of blocks reached. The analysis terminated.

Number of Runtime Warnings: 0

      • End of pc-CRACK output ***

File No.: 1200535.301 Revision: 0 0.1957 0.1044 0.1963 0.1047 0.1991 0.1062 0.2021 0.1078 0.2026 0.1081 0.2056 0.1097 0.2087 0.1113 0.2093 0.1116 Page A-IO of A-19 F0306-01RI

Output for Alloy 182 Region pc-CRACK 4.0 Version Control No. 4.0.1.0 (LEFM + Codes & Standards)

Structural Integrity Associates, Inc.

www.structint.com info@structint.com Date: 04/3012012 14:23 Input Data read from D:\\E_Drive\\Palisades-PORV-1200535\\MRPI14Butter.pcf Analysis

Title:

Palisades Units Selected: US Customary Linear Dimensions - inches Stress - ksi Temperature - deg F Time - hours Analysis Type: Crack Growth (LEFM)

Crack Growth Calculation Method - CyclelTime Stepping Maxinum Number of Load Blocks = 40 Block Print Interval = 1 Crack Model: 307-Semi-Elliptical Longitudinal Crack in Cylinder on the Inside Surface (Zahoor)

Crack Depth, a =

0.1250 Half Crack Length, c =

0.1250 Wall Thickness, t =

1.8750 Inside Radius, Ri ::::

1.8750 Aspect ratio fixed Maximum alt = 0.85 Crack Depth Print Increment for SIF Tabulation :::: 0.1 Total Load Cases: 2 Load Case 1 :Pressure Type: Stress Coefficients Input by User File No.: 1200535.301 Revision: 0 Page A-ll of A-19 F0306-01RI

Coefficient CO =

Coefficient C 1 =

Coefficient C2 =

Coefficient C3 =

3.6140 0.0000 0.0000 0.0000 Load Case 2:MRP-114 Rsd Type: Stress Coefficients Input by User Coefficient CO =

Coefficient C 1 =

Coefficient C2 =

Coefficient C3 =

16.6230 82.5290

-53.7440 10.4130 Total Load Sub-Blocks: 1 Load Sub-Block # 1 Load Sub-block Name: PWSCC Maximum Load Case Multiplier Load Case ID 1.5800 Pressure 1.0000 MRP-114 Rsd Growth Law: PWSCC Cycles/Time: 8760 Temperature: 643 Calc. Interval: 10 Print Interval: 50 Material: 4 Alloy 82/182: Description goes here PWSCC Equation QglR = 2.818E+04 Tref =

617.0000 alpha = 2.470E-07 beta =

1. 6000 K Threshold =

0.0000 f-alloy

=

1.0000 f-orient =

1.0000 Primary Water Stress Corrosion Cracking (PWSCC) Crack Growth Law File No.: 1200535.301 Revision: 0 Page A-12 of A-19 F0306-01RI

The Crack Growth Rate (at temperature T) inlh (or m/h) is given by:

da/dt = exp[-QgIR(lI(T+TO) - lI(Tref+TO)]* Alpha*falloy*forient*(Kmax)"Beta where Qg/R, Alpha, falloy, forient, Beta = empirical constants T = Temperature in deg R (or deg K)

TO = 273 deg C or 460 deg F depending on the selected units Tref= Reference Temperature in deg R (or deg K) da/dt = 0 for Kmax < K Threshold No. of Data in the KIC Table = 2 Crack Depth KIC 0.0000 1000.0000 2.5000 1000.0000 messages/W amings:

Number ofWamings in Inputs: 0

- - - - - - - - - - ANALYSIS RESULTS - - - - - - - - -

STRESS INTENSITY FACTORS Load Case # 1: Pressure

Crack Dimensions ------------

a c

alt cia a

0.1250 0.1250 0.0667 1.0000 0.2250 0.2250 0.1200 1.0000 0.3250 0.3250 0.1733 1.0000 0.4250 0.4250 0.2267 1.0000 0.5250 0.5250 0.2800 1.0000 0.6250 0.6250 0.3333 1.0000 0.7250 0.7250 0.3867 1.0000 File No.: 1200535.301 Revision: 0 K at tip 1.0704 1.7920 2.4163 2.9616 3.4442 3.8783 4.2759 Page A-13 of A-19 F0306*01RI

lJDnlrn' """,., AssocIatIs, Inc.-

0.8250 0.8250 0.4400 1.0000 4.6476 0.9250 0.9250 0.4933 1.0000 5.0022 1.0250 1.0250 0.5467 1.0000 5.3468 1.1250 1.1250 0.6000 1.0000 5.6872 1.2250 1.2250 0.6533 1.0000 6.0280 1.3250 1.3250 0.7067 1.0000 6.3724 1.4250 1.4250 0.7600 1.0000 6.7226 1.5250 1.5250 0.8133 1.0000 7.0799 Load Case # 2: MRP-114 Rsd

Crack Dimensions ------------

K at tip a

c aft cIa a

0.1250 0.1250 0.0667 1.0000 8.5710 0.2250 0.2250 0.1200 1.0000 15.4165 0.3250 0.3250 0.1733 1.0000 22.2639 0.4250 0.4250 0.2267 1.0000 29.1135 0.5250 0.5250 0.2800 1.0000 35.9554 0.6250 0.6250 0.3333 1.0000 42.7702 0.7250 0.7250 0.3867 1.0000 49.5300 0.8250 0.8250 0.4400 1.0000 56.1984 0.9250 0.9250 0.4933 1.0000 62.7315 1.0250 1.0250 0.5467 1.0000 69.0780 1.1250 1.1250 0.6000 1.0000 75.1802 1.2250 1.2250 0.6533 1.0000 80.9745 1.3250 1.3250 0.7067 1.0000 86.3915 1.4250 1.4250 0.7600 1.0000 91.3573 1.5250 1.5250 0.8133 1.0000 95.7933 CRACK GROWTH ANALYSIS RESULTS Total Subblock Cycles Cycles

/Time

/Time Blocks:

1 50.0000 50.0000 100.0000 100.0000 150.0000 150.0000 200.0000 200.0000 250.0000 250.0000 300.0000 300.0000 350.0000 350.0000 400.0000 400.0000 450.0000 450.0000 File No.: 1200535.301 Revision: 0 Kmax Kmin 10.3239 10.4017 10.4804 10.5600 10.6406 10.7222 10.8047 10.8883 10.9729 DaDn DeltaK

!DaDt a

aft 1.918E-05 1.941E-05 1.965E-05 1.989E-05 2.013E-05 2.038E-05 2.063E-05 2.089E-05 2.115E-05 0.1260 0.1269 0.1279 0.1289 0.1299 0.1309 0.1319 0.1330 0.1340 0.0672 0.0677 0.0682 0.0687 0.0693 0.0698 0.0704 0.0709 0.0715 Page A-14 of A-19 F0306*01RI

i)Btnrclll,./ ""."", AssocIates, Inc.-

500.0000 500.0000 11.0585 2.141E-05 0.1351 0.0720 550.0000 550.0000 11.1451

2. 168E-05 0.1362 0.0726 600.0000 600.0000 11.2329 2.195E-05 0.1373 0.0732 650.0000 650.0000 11.3217 2.223E-05 0.1384 0.0738 700.0000 700.0000 11.4116 2.252E-05 0.1395 0.0744 750.0000 750.0000 11.5027 2.280E-05 0.1406 0.0750 800.0000 800.0000 11.5948 2.310E-05 0.1418 0.0756 850.0000 850.0000 11.6882 2.339E-05 0.1429 0.0762 900.0000 900.0000 11.7827 2.370E-05 0.1441 0.0769 950.0000 950.0000 11.8785 2.401E-05 0.1453 0.0775 1000.0000 1000.0000 11.9754 2.432E-05 0.1465 0.0781 1050.0000 1050.0000 12.0736 2.464E-05 0.1477 0.0788 1100.0000 1100.0000 12.1731 2.497E-05 0.1490 0.0795 1150.0000 1150.0000 12.2738 2.530E-05 0.1502 0.0801 1200.0000 1200.0000 12.3759 2.564E-05 0.1515 0.0808 1250.0000 1250.0000 12.4793 2.598E-05 0.1528 0.0815 1300.0000 1300.0000 12.5841 2.633E-05 0.1541 0.0822 1350.0000 1350.0000 12.6902 2.669E-05 0.1554 0.0829 1400.0000 1400.0000 12.7978 2.705E-05 0.1568 0.0836 1450.0000 1450.0000 12.9067 2.742E-05 0.1582 0.0843 1500.0000 1500.0000 13.0172 2.779E-05 0.1595 0.0851 1550.0000 1550.0000 13.1291 2.818E-05 0.1609 0.0858 1600.0000 1600.0000 13.2425 2.857E-05 0.1624 0.0866 1650.0000 1650.0000 13.3575 2.897E-05 0.1638 0.0874 1700.0000 1700.0000 13.4741 2.937E-05 0.1653 0.0881 1750.0000 1750.0000 13.5922 2.978E-05 0.1667 0.0889 1800.0000 1800.0000 13.7120 3.020E-05 0.1682 0.0897 1850.0000 1850.0000 13.8334 3.063E-05 0.1698 0.0905 1900.0000 1900.0000 13.9565 3.107E-05 0.1713 0.0914 1950.0000 1950.0000 14.0813 3.152E-05 0.1729 0.0922 2000.0000 2000.0000 14.2079 3.197E-05 0.1745 0.0930 2050.0000 2050.0000 14.3363 3.244E-05 0.1761 0.0939 2100.0000 2100.0000 14.4664 3.291E-05 0.1777 0.0948 2150.0000 2150.0000 14.5985 3.339E-05 0.1794 0.0957 2200.0000 2200.0000 14.7324 3.388E-05 0.1811 0.0966 2250.0000 2250.0000 14.8683 3.438E-05 0.1828 0.0975 2300.0000 2300.0000 15.0061 3.489E-05 0.1845 0.0984 2350.0000 2350.0000 15.1459 3.542E-05 0.1863 0.0993 2400.0000 2400.0000 15.2878 3.595E-05 0.1880 0.1003 2450.0000 2450.0000 15.4317 3.649E-05 0.1899 0.1013 2500.0000 2500.0000 15.5778 3.704E-05 0.1917 0.1022 2550.0000 2550.0000 15.7261 3.761E-05 0.1936 0.1032 2600.0000 2600.0000 15.8765 3.819E-05 0.1955 0.1042 2650.0000 2650.0000 16.0292 3.878E-05 0.1974 0.1053 File No.: 1200535.301 Page A-15 of A-19 Revision: 0 F0306-01Rl

~AvcIU"'I"""'" AssocIatts, Inc.-

2700.0000 2700.0000 16.1842 3.938E-05 0.1994 0.1063 2750.0000 2750.0000 16.3416 3.999E-05 0.2013 0.1074 2800.0000 2800.0000 16.5013 4.062E-05 0.2034 0.1085 2850.0000 2850.0000 16.6635

4. 126E-05 0.2054 0.1096 2900.0000 2900.0000 16.8282 4.192E-05 0.2075 0.1107 2950.0000 2950.0000 16.9955 4.258E-05 0.2096 0.1118 3000.0000 3000.0000 17.1653 4.327E-05 0.2118 0.1129 3050.0000 3050.0000 17.3378 4.397E-05 0.2139 0.1141 3100.0000 3100.0000 17.5130 4.468E-05 0.2162 0.1153 3150.0000 3150.0000 17.6910 4.541E-05 0.2184 0.1165 3200.0000 3200.0000 17.8718 4.615E-05 0.2207 0.1177 3250.0000 3250.0000 18.0556 4.691E-05 0.2230 0.1190 3300.0000 3300.0000 18.2422 4.769E-05 0.2254 0.1202 3350.0000 3350.0000 18.4319 4.849E-05 0.2278 0.1215 3400.0000 3400.0000 18.6247 4.930E-05 0.2303 0.1228 3450.0000 3450.0000 18.8206 5.013E-05 0.2328 0.1241 3500.0000 3500.0000 19.0197 5.099E-05 0.2353 0.1255 3550.0000 3550.0000 19.2222 5.186E-05 0.2379 0.1269 3600.0000 3600.0000 19.4280 5.275E-05 0.2405 0.1283 3650.0000 3650.0000 19.6372 5.366E-05 0.2431 0.1297 3700.0000 3700.0000 19.8500 5.459E-05 0.2459 0.1311 3750.0000 3750.0000 20.0664 5.555E-05 0.2486 0.1326 3800.0000 3800.0000 20.2864 5.653E-05 0.2514 0.1341 3850.0000 3850.0000 20.5102 5.753E-05 0.2543 0.1356 3900.0000 3900.0000 20.7379 5.855E-05 0.2572 0.1372 3950.0000 3950.0000 20.9695 5.960E-05 0.2601 0.1387 4000.0000 4000.0000 21.2052 6.068E-05 0.2632 0.1403 4050.0000 4050.0000 21.4450
6. 178E-05 0.2662 0.1420 4100.0000 4100.0000 21.6891 6.291E-05 0.2693 0.1437 4150.0000 4150.0000 21.9374 6.406E-05 0.2725 0.1453 4200.0000 4200.0000 22.1902 6.525E-05 0.2758 0.1471 4250.0000 4250.0000 22.4476 6.646E-05 0.2791 0.1488 4300.0000 4300.0000 22.7096 6.771E-05 0.2824 0.1506 4350.0000 4350.0000 22.9764 6.899E-05 0.2858 0.1525 4400.0000 4400.0000 23.2481 7.030E-05 0.2893 0.1543 4450.0000 4450.0000 23.5247 7.164E-05 0.2929 0.1562 4500.0000 4500.0000 23.8066 7.302E-05 0.2965 0.1581 4550.0000 4550.0000 24.0936 7.443E-05 0.3002 0.1601 4600.0000 4600.0000 24.3861 7.588E-05 0.3040 0.1621 4650.0000 4650.0000 24.6841 7.737E-05 0.3078 0.1642 4700.0000 4700.0000 24.9878 7.890E-05 0.3117 0.1663 4750.0000 4750.0000 25.2973 8.047E-05 0.3157 0.1684 4800.0000 4800.0000 25.6128 8.208E-05 0.3198 0.1706 4850.0000 4850.0000 25.9344 8.374E-05 0.3239 0.1728 File No.: 1200535.301 Page A-16 of A-19 Revision: 0 F0306-01RI

e Btnrt:IlI,.I.,r/Iy AssocIatts, Inc.-

4900.0000 4900.0000 26.2623 8.544E-05 0.3282 0.1750 4950.0000 4950.0000 26.5966 8.718E-05 0.3325 0.1773 5000.0000 5000.0000 26.9376 8.898E-05 0.3369 0.1797 5050.0000 5050.0000 27.2853 9.083E-05 0.3414 0.1821 5100.0000 5100.0000 27.6401 9.272E-05 0.3460 0.1845 5150.0000 5150.0000 28.0020 9.467E-05 0.3507 0.1870 5200.0000 5200.0000 28.3714 9.668E-05 0.3555 0.1896 5250.0000 5250.0000 28.7482 9.874E-05 0.3604 0.1922 5300.0000 5300.0000 29.1329 1.009E-04 0.3654 0.1949 5350.0000 5350.0000 29.5256 1.030E-04 0.3705 0.1976 5400.0000 5400.0000 29.9265 1.053E-04 0.3757 0.2004 5450.0000 5450.0000 30.3358 1.076E-04 0.3811 0.2032 5500.0000 5500.0000 30.7539 1.100E-04 0.3865 0.2061 5550.0000 5550.0000 31.1809

1. 124E-04 0.3921 0.2091 5600.0000 5600.0000 31.6171
1. 150E-04 0.3978 0.2122 5650.0000 5650.0000 32.0628 1.176E-04 0.4036 0.2153 5700.0000 5700.0000 32.5182 1.203E-04 0.4096 0.2184 5750.0000 5750.0000 32.9836 1.230E-04 0.4157 0.2217 5800.0000 5800.0000 33.4594 1.259E-04 0.4219 0.2250 5850.0000 5850.0000 33.9459 1.288E-04 0.4283 0.2284 5900.0000 5900.0000 34.4432 1.319E-04 0.4348 0.2319 5950.0000 5950.0000 34.9519 1.350E-04 0.4415 0.2355 6000.0000 6000.0000 35.4722 1.382E-04 0.4483 0.2391 6050.0000 6050.0000 36.0045 1.415E-04 0.4554 0.2429 6100.0000 6100.0000 36.5492 1.450E-04 0.4625 0.2467 6150.0000 6150.0000 37.1066 1.485E-04 0.4699 0.2506 6200.0000 6200.0000 37.6771
1. 522E-04 0.4774 0.2546 6250.0000 6250.0000 38.2612
1. 560E-04 0.4852 0.2587 6300.0000 6300.0000 38.8592 1.599E-04 0.4931 0.2630 6350.0000 6350.0000 39.4717 1.640E-04 0.5012 0.2673 6400.0000 6400.0000 40.0991 1.682E-04 0.5095 0.2717 6450.0000 6450.0000 40.7418 1.725E-04 0.5181 0.2763 6500.0000 6500.0000 41.4003 1.770E-04 0.5268 0.2810 6550.0000 6550.0000 42.0752 1.816E-04 0.5358 0.2858 6600.0000 6600.0000 42.7670 1.864E-04 0.5450 0.2907 6650.0000 6650.0000 43.4762 1.914E-04 0.5545 0.2957 6700.0000 6700.0000 44.2035 1.965E-04 0.5642 0.3009 6750.0000 6750.0000 44.9494 2.019E-04 0.5742 0.3062 6800.0000 6800.0000 45.7145 2.074E-04 0.5845 0.3117 6850.0000 6850.0000 46.4995 2.131E-04 0.5950 0.3173 6900.0000 6900.0000 47.3049 2.l91E-04 0.6058 0.3231 6950.0000 6950.0000 48.1316 2.252E-04 0.6170 0.3291 7000.0000 7000.0000 48.9802 2.316E-04 0.6284 0.3352 7050.0000 7050.0000 49.8515 2.382E-04 0.6402 0.3414 File No.: 1200535.301 Page A-17 of A-19 Revision: 0 F0306-01RI

e Bttuclrull,.""", AssocIatts, Inc.-

7100.0000 7100.0000 50.7461 2.451E-04 0.6523 0.3479 7150.0000 7150.0000 51.6649 2.523E-04 0.6648 0.3546 7200.0000 7200.0000 52.6087 2.597E-04 0.6776 0.3614 7250.0000 7250.0000 53.5782 2.674E-04 0.6908 0.3684 7300.0000 7300.0000 54.5744 2.754E-04 0.7044 0.3757 7350.0000 7350.0000 55.5981 2.837E-04 0.7185 0.3832 7400.0000 7400.0000 56.6502 2.923E-04 0.7329 0.3909 7450.0000 7450.0000 57.7315 3.013E-04 0.7478 0.3988 7500.0000 7500.0000 58.8431 3.l06E-04 0.7631 0.4070 7550.0000 7550.0000 59.9857 3.203E-04 0.7789 0.4154 7600.0000 7600.0000 61.1605 3.304E-04 0.7953 0.4241 7650.0000 7650.0000 62.3682 3.409E-04 0.8121 0.4331 7700.0000 7700.0000 63.6099 3.519E-04 0.8295 0.4424 7750.0000 7750.0000 64.8864 3.632E-04 0.8474 0.4519 7800.0000 7800.0000 66.1987 3.750E-04 0.8659 0.4618 7850.0000 7850.0000 67.5475 3.873E-04 0.8850 0.4720 7900.0000 7900.0000 68.9339 4.001E-04 0.9048 0.4826 7950.0000 7950.0000 70.3584

4. 135E-04 0.9252 0.4934 8000.0000 8000.0000 71.8218 4.273E-04 0.9463 0.5047 8050.0000 8050.0000 73.3247 4.417E-04 0.9681 0.5163 8100.0000 8100.0000 74.8675 4.567E-04 0.9906 0.5283 8150.0000 8150.0000 76.4506 4.722E-04 1.0139 0.5407 8200.0000 8200.0000 78.0740 4.883E-04 1.0380 0.5536 8250.0000 8250.0000 79.7377 5.051E-04 1.0629 0.5669 8300.0000 8300.0000 81.4412 5.225E-04 1.0887 0.5806 8350.0000 8350.0000 83.1839 5.405E-04 1.1153 0.5948 8400.0000 8400.0000 84.9647 5.591E-04 1.1429 0.6096 8450.0000 8450.0000 86.7819 5.784E-04 1.1715 0.6248 8500.0000 8500.0000 88.6337 5.982E-04 1.2010 0.6405 8550.0000 8550.0000 90.5172 6.1 87E-04 1.2315 0.6568 8600.0000 8600.0000 92.4291 6.398E-04 1.2631 0.6736 8650.0000 8650.0000 94.3652 6.613E-04 1.2957 0.6910 8700.0000 8700.0000 96.3204 6.834E-04 1.3294 0.7090 8750.0000 8750.0000 98.2885 7.059E-04 1.3643 0.7276 8760.0000 8760.0000 98.6831 7.104E-04 1.3714 0.7314 Blocks:

2 8810.0000 50.0000 100.6571 7.333E-04 1.4076 0.7507 8860.0000 100.0000 102.6265 7.564E-04 1.4449 0.7706 8910.0000 150.0000 104.5809 7.795E-04 1.4834 0.7912 8960.0000 200.0000 106.5088 8.027E-04 1.5231 0.8123 9010.0000 250.0000 108.3969 8.256E-04 1.5639 0.8341 Crack Depth, a = 1.5974 exceeds user-specified maximum = 1.5938 File No.: 1200535.301 Page A-18 of A-19 Revision: 0 F0306-01RI

Number of Runtime Warnings: 0

      • End of pc-CRACK output ***

File No.: 1200535.301 Revision: 0 Page A-19 of A-19 F0306-01RI

Retrieved from "https://kanterella.com/w/index.php?title=ML121230295&oldid=5259858"