ML18016A710

Rev 0 to Calculation SIC-98-108, Evaluation of Limiting Flaws for Structural Adequacy in Lower Canopy Seal Repairs at Shearon Harris Nuclear Plant.

ML18016A710
Person / Time
Site:	Harris
Issue date:	11/03/1998
From:	STRUCTURAL INTEGRITY ASSOCIATES, INC.
To:
Shared Package
ML18016A709	List: ML18016A708 ML18016A710
References
SIC-98-108, SIC-98-108-R, SIC-98-108-R00, NUDOCS 9811120034
Download: ML18016A710 (31)

Text

c Nov-03-98 18 16 STR+RAL INTEGRITY(408) 403T8 8964 P 03 FO.E No: RVSI433Q-302 CAI.CULA.TION S'I'RVCT URAL.

IN'I'F.GMTY PACKA.GE PROJECT No: %VSI-33Q Associates, Inc.

PROJFCT NAMF.: Lower Canopy Seal Weld Repairs for Sheanon Harris CLIFNT: Welding Services CAI CUI.ATI()N'I'ITI.F.: Evaluation of Lin>iting Flaws for Structural Adequacy in Ia>wcr Canopy Seal Repairs at Shearon llarris Nuclear Plant PROBI.FM S'I'A'CEMENT QR OBJECTIVE OF THE CAI.CULATION:

Demonstrate that thc through wall flaw size detectable by visual examination i>> less than the critical flaw size for both axially angnahtres 8c D te Date 1-7 Initial Issue AO- Al iz/cg V

)I RO- 84

~c cc/p/ye co- C3 DO- D4 SIC-98-108 k'ag<<J nf 7 98iii20034 98ii04 PDR 8

ADQCK 05000400 PDR

0 Nov-03-98 18= 16 STRU RAL INTEGRXTY(408) 40 78 8964 P 04 I.O INVuODUCVrOr At the request of thc NR(: and in support of the use ol'isual exan)ination rather than dye p< netlant examination ol the, completed weld overlay repair to thc lower canopy seal weld at Shearon Harris, Structural Integrity Associates (SI) performed several analyses to determine the critical llaw size in the repaired location. 'l'he purpose of these, analyses is to demonstrate, that a through wall Aaw could be detected by visual examination having a size wllich is sulficicntly smaller than the critical tiaw size, thus assuring sufficient safety margins. CPA't will review the critical flaw sizes determined in this calculation to confirm that the resulting sixes arc detectahlc with margin by the visual technique.

2.0 GE() METRY Thc design geometry of the repair is illustrated in Figure l. For the purpose of the present evaluation, thc component was modeled as a pipe with outside radius equal to the distance from the drive centerline to thc canopy seal weld (3.225 inches) and wall thickness equal to the minimum anticipated overlay thich>ess (0.36 inches), as shown on Figurc ]. 'l'hrough eall axial and circurnfcrcntial flaw>> werc evaluated. These geometries are considered to he reasonable representation>> of the actual design geometry. The model geometries are shown in I-igure 2.

3.0 APPLIE<D STRL<'SSES For conservatism, the applied stress was assumed to act a>> a rncrnbrane stress at the Code, allowable mcmb<ane stress magnitude (Pm = Srn). t4> disrinction was made hetwccn the hoop and axial directions in this regard, although realistically, the axial direction should be half of thi>>

value. Based upon discussions with plant personnel, there arc no bending loads prescnr.

Therefore, bending stresses were not considered.

Revision Preparer/Date Checker/Date Q <'IsA<<

f-ile No. WSl-33 -302 Pa~e 2 of 7

Nov-03-98 18- 15 STRU RAL INTEGRITY(408) 40 78 8964 P 05 I

4.0 MA'I'FMALPROPFRTIES Thc allowable stress, Sn), wa>> taken to be 16.2 ksi at 650 F which is typical of 304 stainless steel.

The Alloy 625 to bc used in the, weld overlay repair has a significantly higher allowable stress at this temperature so use of t.he stainless steel value is conservative. l'he flow stress for thi>>

component was taken as 3 Sm.

For linear clastic fracture mechanics evaluations, the Kr,. was taken as 135 ksi ~in, which i>> very conservative f'r this material at this temperature (the weld metal will be applied using an automated gas shielded process).

5.0 ANALY'I'ICALAPPROACH Two analysi>> methodologies were employed. The limit load (net section collapse) rnctlrod is considered most appropriate for evaluation of through wall flaws in this very ductile rnatcrial.

I'hi>> method is described in Appendix C of ASME Section XI [1]. For comparison, linear clastic fracture mechanics (LEFM) method>> were also applied. Thi>> <<pproach is very conservative for thi>> material, duc to its ductile hchavior.

Four cases were studied. These were:

1. Through wall axial llaw: Limit load.

2. Through wall axial flaw: I.EFM

3. Through wall circumferential llaw: Limit load.

4. I'hrough wall circumferential flaw: 1.L'FM.

No Code salcty margins were ir>eluded in thi>> evaluation, since thc objective is to gct a reasonable view of thc relationship between dctcctab1e and critical flaw>>ice>>.

Revision 0 Prcparcr/Date Checker/Date

+

File No. XVSI-33Q-302 rr J3/~<

Pa<e 3 of 7

Nav C}G-98 18: 18 STRLIIRAL ZNTSGRZTY(408) AolTG GGGA P 06 The results I rom each case are summarized helow.

6.0 RES UL,TS 6.l Through Well Axial I}law: Limit I.oad This case follows the methodology underlying ASME Section XI, IWB-364] and Appendix C.

Thc Sl program pc-CRACK [2] was used to p<<rform the analysis. The pc-CRACK result( arc attached in Appendix A to thi>> rcport. 'I'he conclusion is that an axial flaw could be at least 4.8 inches long h<<fore leading to incipient collapse. Thi>> i>> much longer than is physically achievahlc, since cracking would be expected to he confmed to the weld overlay material and vicinity, which, in thc axial direction, extends approximately 1 inch.

6.2 Through Wall Axial l}law: LEFM i'his analysis assume>> that brittlo failure is thc operative mechanism. Thc pc-CRACK program is used with this analy>>is. A fracture, rncchanics rood<<l of a through wall crack in a. cylinder under internal pressure was used, together with an assumed fracture toughness K<}-. 135 ksi gin . Thc pc-CRACK results are shown in Appendix B. '1'he <<onclusinn i>> that for this set ol a>>sun>ption>>,

thc critical Aaw length is greater than 5.05 inches.

6.3 Thrnugh Wall Circumferential Flaw: Lhnit Load This analysis used hand calculations using the methods of Section XI Appendix C. The SI program ANSC was also used to pctform a s<<parate analysis of the same configuration. The analysi>> assumed a through wall circumferential flaw, and determined the critical flaw length using limit load technique>>. Thc conclu>>ion is that such a flaw could be l32 around the cylinder Revision 0 Preparer/Date Checker/Date ~/~/ss i'ile No. WSI-33Q-302 Pac 4 of 7

Nov-03-98 18 15 STRU RAL INTEGRITY(408) 40 78 8964 P 07 l

before rcachingtr critical size. This corresponds to a flAw apploxilnately 7.43 inches l<)ng.

Computer output is included in Appendix C of this rcport.

6.4 Through %Vali Circumferential I<law: LI'f<M This analysis assumed that the failure mode was brittle I'ailurc. 'I'he pc-CRACK program was used with a through wall circurnfcrential llaw in a cylinder under remote tension fracture mechanics model. A KI, l35 ksi Jin was conservatively assun>cd. l'he conclusion of this analysis was that the critical flaw length for this sct of assumpl.ions was approxitnately 7.3 l inches. The computer output is included in Appendix D.

7.0 CONCLVSIONS The above results demonstrate that, under a variety of conservalivc assumptions, the, critical flaw size predicted for thc repair geometry is in all cases significantly longer than thc flaw length which is expected to be detectahlc by a visual exatnination under magnification, as proposed by COL.

Thi>> will bc confirmed by CPKL.

8.0 RE&'ERENCrS ASM t." Boiler and Pressure Vessel Code, Section Xl, l989 Edition, No Addenda.

2. Structural Integrity Associates, pc-CRACK, for Windo>vs, Version 3.0, March 1997.

Revision Prc parer/Date Checker/Date Pile No. WSI-33Q-302 Pa~e 5 of 7

l I i

Nav-03-98 1.8= 16 STRU RAL INTEGRITY(408) 40 78 8964 P 08 r I 0.07 to 0.08 l5 Bleaet late Ihteteee Seeaea 0~ heQ lte Steaea I

0.155 to 0.1RYR 5.550 040 O~ ~ W e'~

.~

I iat~~~

cM".iKK8,'

e eetet&eÃp" ha Shorn ttetet tea L tea 0.I5e te 0.15tett 0a0

+te 55e~ Scca~

~y'he'.~ M" Figure I. Weld Overlay Design Revision 0 Preparer/Date Checker/Date I-'ile No. WSI-33Q-302 Pa e Ci of 7

Nov-03-98 18= l6 STRU RAL INTEGRITY(408) 40 78 8964 P 09 t = 0.36" t= 036 I

I I I I I I I I I I I I I I I I I I I I I I I I I I

I I I I I I I I I I I I I I I I I I I I

I I I I I I I I I I I I I I I I I I I I

rl I, l r

95I88n)

Figure 2 Revision Preparer/Date z/

Checker/I3ate 1

<</oh['ile No. WSl-33 -302 Ptr ~<<7 of 7

Nov-03-98 18. 16 STR RAL INTEGRITY(408) 40 78 8964 P 10 Appendix A Throt)gh Wall Axial Flaws, Limit Load Revision Preparer/Date Cl)eel'er/Date Vile No. WSI;33Q-302 Pa e A-0 of A-1

~ ~

Nov-CL3-98 18 16 STRU RAL INTEGRITY(408) 40 78 8964 tm pc-CRACK for Window" Version 3.0, Mar. 27, 1997 (C) CopyrighC '84 - 97 ~

Structural Integrity Associates, Inc.

3315 Almaden Expressway, Suite 24 San Gose, CA 95118-1557 Voice: 408-978-8200 Fax: 408-978-8964 E-mail.: infoc@scructint. corn Date: Tue Nov 03 16:52:28 1998 Pile: WSI33Q-l..CNS Allowable Flaw Size Evaluation Using ASME Section XI, IWB-3640/50 Procedures and Criteria For Axial Crack in Stainless Sceel Piping WSI-33Q: NSCC OF AXIAL FLAW Material i specified as Gas Tungsten-Arc Weld (GTAw)

Material properties:

Design stress = 16.2000 Flow stress = 48.6000 Pipe geomecry:

Outer diameter 6.4500 Wa31 chickness 0.3600 Crack geometry:

Crack depth = 0.2000 Crack lengch 1.0000 The flawed pipe is assumed to fail under limit load condition.

The allowable flaw size is determined using code formulas.

and user specified safecy factors.

Membrane tress (Pm) 16.2000 (safety factor 1.OOOO)

Design scress a 16.2000 Pm/ Sm 1.0000

" Stress ratio 1.0000 (Includes S. F.)

a/c 0.5556 1/sqrc(Rt) 0.9551 crit. 1/ qrt(Rc) ~ 4.4542 allowable a/c 0.7500 1/sgrc(Rt) 0.00 0.50 1.00 2.00 3.00 4.00 5.00 Allowable a/t 0.7500 0.7500 0.7500 0.7500 0.7500 0.7500 0.1000 6.00 7.00 8.00 9.00 10.00 11.00 12.00 Allowable a/t 0.1000 0.1000 0.3.000 0.1000 0.1000 0.3.000 0.1000

Nov-Ai3-98 18= 17 STRU RAL INTEGRITY(408) 40 78 8964 Appendix 8 Thrcugh Wall Axial Flaws, LEI M Revision Prop arcr/Date Checker/Date File N(). WSI-33 -302 Pa c H-O ()f B-4

1 Nov-08-98 18: 17 ETRuJRAL ZNTEGRZTV(498) 40+IB 8964 tm pc-CRACK for Windows Version 3.0, Mar. 27, 1997 (C) Copyright '84 '97 St4ruCtural Integrity Associates, Inc.

3315 Almaden Expressway, Suite 24 San Jose, CA 95118-1557 Voice: 408-978-8200 Fax: 408-978-8964 Y.-ma i I: infoestructint. corn Linear Elastic Fracture t1echanics Date: Tue Nov 03 16:53:36 1998 File: WST33Q-2. LFM

Title:

ttSI-33Q: ALLOWABLE FLAW IH CANOPY SEAL, AXIAL, LEFH Load Cases:

Stress Coefficients Case 1D CO Cl C2 C3 Type Membrane 16. 2 0 Coeif Crack Model: Through-Wall Axial Crack in Pressurized Cylinder Crack Parameters-Wall thickness: 0. 3600 Out:side diameter (Rm/t>-10): 6. 4500 HalE crack length(max a< 10(Rmt)"0.5): 5.0000 Stress due to pressure: CO in load case."..

Stress Intensi t:y Factor Crack Case Size Membrane 0.1000 9.35456 0.2000 13.746 0 '000 17.6058 0.4000 21.3552 0.5000 25.1509 0.6000 29.0652 0.7000 33.1333 0.8000 37.3717

Nov-93-98 18. 17 STRU RAL INTEGRITY(408) 40 78 8964 P.14 0.9000 41.7S69

1. DDOOr '6.3794 1.1000 51.1465 1.7DOO 56.0837 1.3DOO 61.1853 1.4000 44r~4 3 .5000 71. 8576 1.6000 17. 4'156 1.7000 83.1134 1.8000 88.9449 1.9000 94.904&

2.0000 100.987 2.1000 107 '86 2.2000 113.497 2.3000 119. 916 2.4000 126.437 2.5000 133.056 2.6000 139.769 2.7000 146.572 2.8000 153 461 2.9000 160.431 3.0000, 167.48 3.looo 174.603 3.2000 181.797 3.3000 189.059 3.4000 196.386 3.5000 203.774 3.60OD 211. 22 3.7000 218.722 3.8000 226.276 3.9000 233.879 4.oooo 241.529 4.1000 249.223 4.2000 756 95 4.3000 264.733 4.4000 272.543 g.bODO 280.387 4.6000 288.262 4.7000 296. 166 4.80OO 304. 095 4.900n 31.2.049 5.0000 320.024 Material fracture Laughncss:

MatexiaJ. ZD: Klc Dept:h Klc

Nov-03-98 18. 17 STRU RAL INTEGRITY{408) 40 78 8964 0.0000 135. 0000 0,2000'.8000 135.0000 135 0000 F

Load combirxation for critical crack size:

Load Case Scale I"actor Membrane 1.0000 Crack '1 otal Size K 0.1 9.35456 135 0.2 13.746 135 0.3 17.6058 13b 0.4 21-3552 135 0.5 25.1509 'l. 35 0.6 29.0652 135 0.7 33.1333 135 0.8 3/. 3717 135 0.9 41. 7869 135 1 46.3794 135 1.1 51.1465 135 1.2 b6.0837 135 1.3 61. 'I. 853 l35 1.4 66.4454 13b 1.5 71.8576 135 1.6 77.4156 135 1.7 83.1134 135 1.8 88.9449 135 1.9 94.904b 13 r5 2 100.987 135 2.1 107.186 135 2.2 1l3.497 135 2.3 119.916 135 2.4 126.437 135 2.5 133.056 l35 2.6 139.769 135

2. / 146. b'/2 135 2.8 l53. 461 'I 35 2.9 160.433 135 3 16/. 48 'l3 5 3.1 174.603 135 3.2 101.797 135 3.3 189.059 135 3.4 196.386 135 3.5 203. 7 /4 1 35 3.6 211.22 135 3.7 21.8.722 135

Nov-Q3-98 18= 17 STRU RAL INTEGRITY(408) 40 78 8964 3.8 226.276 135 3.9 '.233.879 135 241.529 135 4.1 249.223 135 4.2 256.959 135 4.3 264.733 135 F 4 272.543 135 4.5 280.387 135 200.262 135 4.7 296.166 135 1.0 304.095 1 3ri 4.9 312.049 135 320.024 135 Critic+1 exec:k sire 2.5294

~,

Nav 08-98 18: 18 STRUJRAL INTEGRITY(408) 40l78 8964 P. 17 Appendix C Through Wall Circumference.ial Flaws, l.imit Load Revision Preparer/Date g

~

Checker/Date !j/<'ilo No. WSI-33Q-302 Pa Tc C-0 of C-3' Q

li)q)8

i i i aluation NOTE: Inprrls are highlighted in the output below.

I Case N: The neutral axis is located such that a + p ( n (this is checked below)

I (n - adit) - (P joi)n

(

Reference:

"Engineering Methods for the Assessment of Ductile Fracture Margin in Nuclear Power Plant Piping," S. Ranganath and H.S. Mehta, 1983.)

P,'= (2'vries) '(2 sinI3-dlt sin a)

Pm=

input: , PSl z Pb trl PSI Gl Safety Factor, SF =

Pm*SF =

16,200 psi Enter the input in the shaded regions Pb'SF =

PSL and click on the buffon above to solve.

Sm= 0 PSI D3 3Sm = psi= or 48,600 65.755 1.147636014 radians, so crit. flaw size 132 Results: = 1.570796327 - 0.573818007 dft- 0.5236 r P [1]

30939.72094 ~ - dit sin ( 1.147636014 3 f2]

Solving by trial and error: I3 Pb'rom from f1] f2] Difference P Computed dit Pb (Pb Pm)*SF+Pm (') a I n SF (radians) (psi) 0A7338 -0.07 27.1 YES ~ 1.000 Fite = Lirn-toad. xls (Case rt1i 11/3/98

Nov-03-98 18.18 STRU RAL INTEGRITY(408) 40 78 8964 P 19 Appendix D

'hrough Wall Circutnferen(ial flaws, f.EFM Revision 0 Pre parer/Date gg)g ij t.".hecker/Date

~l( ] r

/~ ~

File No. WSI-33Q-302 Pa e D-O ol 0-4

Nov-0P-98 18 18 STRU RAL INTEGRITY(408) 408 8 8964 tm pc-CRACK for Windows Version 3 0, Mar. 2 !, 1997 (C) Copyright '84 '97 Structural Integri t.y Associates, Inc.

3315 Almaden Expressway, .uite 24 San Jose, CA 951]8-1557 Voice: 408-978-8200 l'ax: 408-978-8964 E-mail:infoostructint. corn Linear Elastic l'racture Mechanics Date: Tue Nov 03 16:54:05 1998 File: WST33Q-4.LFH Title; wSX-33Q: ALLOWABLE FLihl< IH CANOPY SEAL, CTRC, LEFH Load ( ases

'ase Stre" Coefficient ID Cp C'l C2 C3 Type MEMBRANE 16. 2 0 CoeEE Crack Model: Through-Wall Circ. Crark in Cylinder Under Tension And Bending Crack f'arametors:

Wa11 thlcknes.",: 0.3600 Out.".ide diameter: 6.4500 HalE rrack length: 4.4532 Poisson ratio: 0.3000 stress Intensity Factor-Crack Case Size MEMBRANE

0. 0891 8. 57925 0.1781 12. 1753 0.2672 14. 9978 0.3563 17. 4568 0 19 7162

~

0 r,344 21. 8632

0. 6234 23.952'l

0. 712!> 26.0199

I Nov-03-98 18: 18 STRU RAL INTEGRITY(408) 40 78 8964 0.80]6 28.0936 0.8906  ; 30.1938 0.9797 32.3366 1.0688 34.5352 1.1570 36 '953 1.2469 39. 0677 I .3360 41.3952 1.4250 43.7787 1.5141 46.2202

].6032 48.722

].6922 b1.2869

'L.7813 b3.9183 1.8703 56.6198 1 9594 59.39b6 2.0485 62.2501

2. 'l 375 6b.188]

2.2266 68.2147 2.3157 71.3354 2.4047 74 5563 2.4938 77.8834 2.5829 8]..3234 2.6719 84.8837 2.7610 88.571b 2.8501 92.3951 2.9391 96. 3631 3.0282 1OO.484 3.1172 104.769 3.2063 ]09.227 3.29b4 113.87 3.3044 '118.71 3.4735 123.759

3. 5626 1.29. 031

3. 6bl6 l34.54 3.'I,407 l40.303

3. 8298 146.336

3. 9188 ],52.658

4. 0079 '159.288

4. 0970 ].66.247

4. 1860 ]73.558 4.2751 ],81.247

4. 3641 189.339 4.4b32 197.865 Materi.al fracture toughness:

material ID: K1C Depth Klc

Nov-03-98 18= 19 STRU RAL INTEGRITY(408) 40 78 8964 P 22 0.0000 135.0000

'lar) OOOO 0.2000'.9ooo 135.0000 Load combination tor critical crack size:

Load case Scale Factor HEI IBRANE 1.0000 crack Total.

Size K Klc 0.0890642 8.57925 135

0. 'I.78128 'I2.1753 135

0. 267193 14.9970 135 0.356257 17.4560 id'35 o.nns32] 19.7162 0 534385 21.8632 '1 35

0. 623449 23.9521 l35 0.712sln 26.0199 135

0. 8015/8 28.0936 135 0.090642 30.1938 135 0.979706 32.3366 13S

1. 068'/7 34.5352 135

1. lb'/83 36 7953 135 1.2469 39. 06'/7 135 1.33596 41.3952 135 1.42503 43.7787 135

'I . 5'1409 46.2202 135 1.60316 48.722 135 1.69222 51.2069 135 1.'/8j28 53.9183 135

'1.87035 56.6198 135 1.95941 59.3956 :I 35 2.04848 62.250L 13 )

2.13754 65.1881 l35

2. 2266 68.2l47 135

2. 31567 71.3354 135 2.40473 5563 'L35 2.4930 77.883n l35 2.58286 01.3234 135 2.67193 84.8837 135 2.76099 88.5715 135 2.05005 92.3951 135 2.93912 96.3631 135 3.02018 100.404 135 F 11'/25 ion.-/69 135 3.20631 109.227 135 3 '9538 113.87 135

Nov-03-98 18= 19 STRU RAL INTEGRITY(408) 40 78 8964 P 23 3.38444 118.71 13r 3.473/ ~,123 759 135 3.56257 129.031 l35 3.65163 134.54 13r5 3.7407 140.303 1 Rr5 3 '2976 146.336 '135 3.91882 152.658 135 4.00789 1,59.288 135 4.09695 166.247 135 4.18602 173.558 135 4.27508 '181.247 13b 4.36415 189.339 135 4.45321 197.865 135 Critical cr<~ck size 3.6591

Nov-03-98 18= 19 STRU RAL INTEGRITY(408) 40 78 8964 P 24 c<LCUr.axrON FILE No: iVS I-33Q-301 STRl.JCTVRAL PACKA.GE PRO JEC'1'o: WSI-33Q INTEGRITV Associates, lnc.

PROJF CT NA5IL<: Repair ol Sl>caron Ilarris Part Length CRDM lower Canopy Seal Weld CLIENT: Welding Services CALCVLATIONTITLK:Weld Overlay Design Lower Canopy Seal Weld Overlay Repair PROBLEM STA'I'EMENT OR OLIL<'CTIVROF THE CALCULATION:

See next page.

Project Mgr. Preparer(s) A Document Affected Revision Description Approval Checker(s)

Revision Pages Signature 8c Signatures S Date Date l-6 Original Issue li 3/qP ii p/pa ii/~gy SIC l 07 Page~ of

Nov-03-98 18= 19 STRU RAL INTEGRITY(408) 40 78 8964 P 25 1.0 INTROP[JCTION A tower canopy seal weld (CSW) on a part length drive penetration at Shcaron 1larris h<<s developed a leak. Leaks have previously beer) identified at numerous other PNRs.

The leak l<)cation will he repaired by applying a weld overlay repair. Such a repair restores the, prcssure integrity of the lrr<<ation, restores thc full desigrr load carrying capability of the rrrigir>al conrponcnt. and adds additronal material to allow lor continued crack growth, assumirrg an aggressive Aaw prop rgation mechanism.

The weld overlay repair has been applied to nuclear plant austcnitic stainless srccl prcssure retaining cornponcnts <<t. over 700 locationssillcc 1983. Thi>> repair technique was iAcorpor<<ted into r lrc ASME Code by ASME Sectirrn XI Code Case N-504 f'l l. This code case was <<ccepted by tfre NRC in Regul<<tory Guide 1.147 Revision 11 [2].

2.0 MA'1'ERIAT.S Thc original canopy seal weld and adjacent CRDM rnatcrial are <<ornposcd of 'I'ype 304 stainless steel. Thc weld overlay will bc applied using thc austenitic nickel based Alloy 625. This material is suitable for welding on Type 304, is highly resistant ro ntcchanisms such as intergranular stress corrosion cracking (to which stainless steel Type,304 is generally susceptible), <<nd has higher strength than the Type 304 material of the original components. I or the purpose of designing thc wc)d overlay, thu S = 16.2 ksi at 650"F for Type 304 St<<inless Steel will conscrvativcly used, rather than the higher S, = 23.3 ksi of Alloy 625 [3].

Revision 0 Preparer/Date 4 "l~ f~

C:hecker/Date File No. WS]-26Q-301 Pa~e 2 of 6

1 Nov-03-98 l8=20 STRU RAL INTEGRITY(408) 40 78 8964 3.0 A.PPLIHD STRFSS Thc design hasi>> for the original canopy seal weld wa>> a limiting membrane stress of P, > assurncd that P =S, =162Ksi 4.0 WL<f.D OVERLaY DESTCN THICKNFSS Thc Structural Integrity Associates fracture mechanics computer program pc-CRACK [4] will bc used to deter<<nine the n>inimum required thickne>>s. This program incorporates the analysis rncthod>>

of ASME Section XI, TWB-3640 and Appendix C l5J, which arc endorsed hy Code Case N-504 and NUREG-03 I 3, Revision 2 [6].

I'he pc-CRACK. output is included as Table 1. Thc analy>>is detcrniined that a mininiuin overlay thickness of .0511 inches is required to restore the structural integrity of the cornponcnt.

5.0 WELD OVERI.AY LIFE ASSESSMLNT Tn addition to thickness of thc weld overlay repair required for structural integrity (.0511 inches), an allowance is require<<I to account for the potential for c<<intinucd crack growth. A total weld overlay thickness of 0.36 inches or greater is to bc applied, to provide this extra assurance as shown in f'igure 1.

Separate calculations 17, 8i, docwncnt the component specific residual stress analysis and the detailed repair lifcasse>>>>ment, considering coniinuing crack growth by an aggressive IGSCC mechaiiisni. The crack growth predicted duc to IGSCC'. will conservatively bound po>>sible Ilaw growth due to other, much slower mechanisms such as fatigue.

Revision Preparer/Date D.b //s/>0 Checker/Date 8P  %/e Pa c 3 of 6 File. No. XVSI-2(iQ-301

Nov-03-98 18 20 STRU RAL INTEGRITY(408) 40 78 8964 P 27 ft is cxpccted that the effective service lil'e of this repair will be in excess of 40 years, based upon similar analyses pcrforrned for other planLs.

6'HFERFNCHS AS M E Section XI Code Case, N-S04 USNRC Regulatory Guide 1.147, Revision 11 ASME Section IIIAppendices, 1989 Edition

4. Structural Integrity Associates, c-CRACI< for Windows, version 3.0, March 27, 1997

5. ASMI=. Section XI, 1989 Edition

6. NUREG-0313, Revision 2, issued with Generic letter 88-01, 1988

7. SI Calculation WSI-33Q-303 (forthcoming)

8. Sl Calculation WSI-26Q-304 (forthcon)ing)

Revision Preparer/Date L0D ~/~/N

(:hecker/Date Fi le No. WSI-2(rQ-301 Pa ie 4 of 6

J Nov-03-98 18= 20 STRU JRAL INTEGRITY(408) 40 78 8964 P 28 0.07 to 0.08 ~

15 Blrmd Into As Shayn Minter Sc~

0.~ tnt Q. af OrLg~l Weld I P'hRtR t

~ Ill g g/I O.l~

0.155 to rXu~a.

+g <htg'4 j w~~ ~y'Ihtdmess + >>/~/ps M5 to Q.IRPR hcQ O.SSa Bknd Into Ttttekcr hs Shawn

'~u l'igure 1. Weld Overlay Design Revision Preparer/Date 'I/9/zt Checker/Date R" (7  %/y File Nn. WSI-26Q-30 I Pa~e 5 oF 6

Nov-03-98 18=20 STRU RAL INTEGRITY(408) 40 78 8964 P 29 Table l PO-CRACK OutPut, Weld OVerlay f3esign Tm pc-CRACK for Window Version 3.0, Mar. 27, 1997 (C) Copyright '84 - '97 Strucrural Integrity A"sociates, Inc.

3315 Almaden Expressway, Suite 24 San Pose, Ch. 95118-1557 Voice: 408-978-8200 Fax: 408-978 8964 E-mail: infoustructint.corn Structural Reinforcement Sizing Evaluation wsiflw

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Date: Tue Nov 03 l4 : 34: 40 1998 File:

D6 Waiflw n/gt'ys wall thickness 0.0750 Membrane tress 16.2000 Safety factor 3.0000 Bending scress 0.0000 Safecy factor ~ 1.0000 Scres Ratio 3.0000 Allowable stress 16.2000 Flow stress 48.6000 L/Circum 0.00 0.10 0.20 0.30 0.40 0.50 0.60 Final a/c 1.0000 1.0000 0.8955 0.7744 0.6963 0.6475 0.6182 Reinforcement thick. 0.0000 0.0000 0.0088 0.0218 0.0327 0.0408 0.0463 0.70 0.80 0.90 1.00 Final a/t 0.6025 0.5967 0.5947 0.5947 Reinforcement thick. 0.0495 0.0507 0.0511 0.0511 Revision preparer/Date lt /3/f g Ct>eeker/Date I'ile No. WSI-26Q-30 l Pa e 6 of 6

'ttachment 2 to SERIAL: HNP-98-161 SHEARON HARRIS NUCLEAR POWER PLANT DOCKET NO. 50-400/LICENSE NO. NPF-63

SUMMARY

OF CAMERA TESTING WELDING SERVICES INCORPORATED

Mr. Ed Black We(ding Services, Inc.

Carolina Power and Light 2225 Skyland Ct.

Shearon Harris Power Plant Norcross, GA 300?1 New Hill, NC Telephone (770) 4524005 Fax (770) 7294242 Phone 919-362-2335 FAX 919-362-2375 Email edwin.black@epic.corn 11/3/98 Re: 8X Camera System

Dear Mr. Black,

To support your CRDM repair project during the Shearon Harris RF08 refueling outage, WSI is providing remote video equipment. This remote video system used on the CRDM overlay is equivalent to the systems used at the following sites for similar repairs:

Prairie Island 1995 1997 1998 North Anna 1998 Point Beach 1998 It is an 8-power video camera and monitor system capable of providing suitable remote visual inspection of the Control Rod Drive Mechanism canopy seal weld overlay.

Attached is a copy of a letter sent to the Prairie Island project.

Ifyou have any further questions I may be reached at:

919-362-2978 919-362-2801 Sincerely, John Dickson QA Site Manager

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2225 SO'lAND COO AT NOAOAOOS. QCOHGtA XN71 TELEPHONE (404) 4524005 FAX (404) 12&8242 June 21, 1995 Mr. Dick Cooper Northern States Power Company 1717 'iVakonade Drive East Welch, MN 5S089 FAX: 612-330-7603 SUB JLCT: Prairie Island Nuclear Plant

%'Sl ReSerence No.: 35049-2 Dear Mr. Cooper.

Pcr your request, we have performed several tests to evaluate the capabiTities of thc camera systcnt used in the perfonnance of the acid repair of Prairie Islands CROM Seals. The intent of this testing is to provide data to be used by NSP to evaluate thc adaIuacy of this camera for the performance of adequate visual inspection of the veld. overlay. The testing described was not perfoancd as a safety relauxi procedure, 'I'he tcstino was performed as foliose:

1. 'Hm video fmnt end of the 7/SI vreId head eras connected to aV CR and monitor of thc same make and tnodcl as thc system used on site.

2. A mockup of a canopy scat housing simila in configuration to thc Prairie Island design vras overlayed in a similar conGguration as the repair performed at the site, A .0005 inch diameter wire and a.00l inch diameter wire each, A inches Iong, werc taped to thc surface of the weld overlay on thc housing.

3. Thc two >vires were Qhned using the weld head fioat cnd, and the weld bead Hghting for illumination.

4. WSl's site QC representative, GmJJ Caul, reviewed the tape and eras able to see both wit's on the surface of the veld.

A copy of the tape, samples of thc two wires used, and additional camea information ate if included with this letter for your review. Please lct mc liow you need additional information.

Sincerely, Pedro I:. Arnador Senior Project Manager 3'2DOC

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