ML20199L409

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Rev 0 to L-001337, Containment Liner Leak Chase Channel Assessment
ML20199L409
Person / Time
Site: LaSalle  Constellation icon.png
Issue date: 11/03/1997
From: Eberhardt A, Namperumal R
SARGENT & LUNDY, INC.
To:
Shared Package
ML20199L389 List:
References
L-001337, L-001337-R00, L-1337, L-1337-R, NUDOCS 9712020014
Download: ML20199L409 (109)
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COMMONWEALTH EDISON COMPANY CALCULATION TITLE PAGE PAGE NO.: 1 CALCULA flON NO.: L-001337 X SAFETY RELATED D REGULATORY RELATED 0 NON SAFETY RELATED CALCUl.ATION TITLE: Containment I iner Leak Chase Channel Assessment STATION / UNIT: LaSalle County / Unit i SYSTEM ABBREVIATION: NA EQUIPMENT NO.: w => N A PROJECT NO.: a => 10248-012

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TEV: 0 5TAfDs: Approvef--

VA EiERIACTEOR CITRDN NO.

ITATE:_ _7 A

PREPARED BY: A.C. Eberhardt/ /2 A fM g# DATE: 10/28/97 REVISION

SUMMARY

Initiallssue ELECTRONIC CALCULATION DATA FILES REVISED: NA (Name ext / size /date/ hour; min / verification method / remarks)

DO ANY ASSUMPTIONS IN Tills CALCULATION REQUIRE LATER VERIFICATION YESO NO X REVIEWED BY: R. Namnerumalt.

)ceM DATE:lo _h 47 REVIEW METilOD: Detailed COMMENTS (C, NC OR Cl): Cl APPROVED BY: ____{M k.A Yfil DATE: l[-3.-47 9712020014 971126 PDR ADOCK 05000373 P

PDR

'O' W

COMMONWEALTH EDISON COMPANY CALCULATION TABLE OF CONTENTS PROJECT NO. 10248-012 PAGE NO 2 CALCULATION NO. L-001337 REV. NO. O DESCRIPTION PAGE NO.

SUB PAGENO.

TITLE PAGE 1

REVISION

SUMMARY

l TABLE OF CONTENTS 2

PURPOSE / OBJECTIVE 3

METIIODOLOGY AND ACCEPTANCE CRITERIA 3

ASSUMPTIONS 3

DESIGN INPUT 34 REFERENCES 4

CALCULATIONS 5 to 25.1 5.1,5.2,12.1,13.1.18.1,25.1

SUMMARY

AND CONCLUSIONS 26 ATTACllMENTS Al - A7, B1 - B7, C1 - C8, D1 - D39

.1

i C:Ic. No. L-001337 Rev. O Proj, No. 10248-012 Pag] No. 3 This Calculabon has been prepared useg Mathcad Plus 5, S&L Program t4 umber 03.7.54s 5.0 Purpose and Oblective To perform a design assessment of 2" and 3" containment liner leak chase channels in the suppression peal and drywell. Discrepancies between design material y eH strength and specified minimum rnaterial yield strength are addressed. In addition, the margin betwi en specified yield and ultimate tensile strength as determined from vendor supplied certified material t:rst reports (CMTRs) will be verified. Results are given in terms of margin factor wt.ich is dcfined as the ratio of allowable stress divided by actual stress. TNs calculation is performed in response to PlF # L1997-06237, Methodoloav and Ace 6ctance Criteria This calculation shall be perfoimed in accordance with the applicable documents listed as Design inputs below.

The acceptance crtena used for this assessment is given in Subsection 4.3.2 of the LaSalle Design Assessment Report (DAR) (D.I. 32). Applicable load combinations are defined in Tab e 4.3-2 of the DAR.

Allowable stresses for load combinations 1 through 3 are per the 1969 AISC Specification. However, it has been demonstrated in previous calculations (see D.l. 33) that the goveming load combinations involve either hydro-dynamic loads or jet impingement loads. For these load combinations, the allowable stress is limited to 0.95 fy. As permitted in Ref, 3, Sect. lil.2.a. a 10% increase in minimum specified yield strength will be used to account for straia i,ete offects associated with impact loads. The allowable stress used for weld assessment is 21 ksi for allload combinations.

Assumptions There are no unvenfied or unconservative assumptions used in this calculation.

Deslan inputs (Check where applicable " APP")

APP

1) 1 DC-SE-01-LS, Rev. 7, Structural Project Design Criteria
2) _ AISC's Manual of Steel Construction. Eiahth Edition
3) 1 AISC's Manual of Steel Construction. Seventh Edition da) _,,,,,, ACl 318 Buildino Code Reauirements for Reinforced Concrete Structures.1983 4b),_,,,,,, ACI 349 Buildina Code Reauirements for NSR Concrete Structures.1980 5)

AISI's Cold Formed Steel Desian Manual.1983

6) 1 DC-SE-02 LS, Rev. O Seismic Response Spectra
7) 1 DC-SE-03-LS through DC-SE 09-LS, All Rev. O, Hydrodynamic Response Spectra 8)

Calcutaten 802-100.2, Rev. O, Pages 25-37, Peak g-values for Pipe Supports

9) _ Calculation 802100.2, Rev. 8, Pages 41-44, Peak g-values for Pipe Supports in the Drywell
10) _ _ Calculation 802-100.2, Rev. 8, Page 40, Peak g-values for Electrical Supports in the Dryweil 11)

Calculation 795, Rev. O, Pages 42-43, Peak g-values for Cable Trays and Conduits 12)

DIT No. LS-EPED-0077-01 and Calculation No. GDS-3.6.6, Rev.1, Reduced Conduit Weights

13) _ S&L's SD&D Report No. 78, Rev 4, Concrete Masonry Walt Design 14)

S&L's SDS-ES 0, Rev.1, Loads, Load Combinations, and Allowables

15) _,_ S&L's SDS-E11.0, Rev. 2 Hilti Kwik Bolt Design
16) _,_ S&L's SDS E11.0, Rev. 3 Hitti Kwik Bolt 11 Design
17),_ S&L's SDS-E30.0, Rev. O Cable Tray Design CAL 1337Z.MCD

C Ic. No. L-001337 RIv. 0-ProJ, No. 10248-012 Pcg2 No. 4 j

18),,,,,,,, S&L's SDS E31.0, Rev. 2 Cable Tray Support Design 19).,,,,,,,,,

S&L's SDS-E33.0, Rev. 3 Conduit and Conduit Support Design l

20)1 S&L's SDS-E37.0, Rev. 5 Pipe Support Design 21),,, ' SEL's SDS-E41.0, Rev. 2 Wold Design 22),,,,,,,,,

S&L's SDS-E44.0, Rev. 0 Embedmont Plate Desgn 23)__,,,,

Calculation 802104.4, Rev,9, Pages 4 5, Design Equations for Embedmont Plates 24)1 LaSalle County Station Updated Final Safety Report, Rev.11 25)1 LaSalle County Station Drawing S-384, Rey, U j

. 26)

S&L's GDS-3.6.3, Rev. 3 27)

S&L's Projec+ Instruction LSNS 22, Rev. 3 28)1 NUREG \\CR 2913. "Two Phase Jet Loads" Published Jan.1983 by SANDIA National Laboratories -

29)_ S&L's Project instructen LSNS-16, Appendix 1, Rev,0 30)1 CBI Shop Drawings (See specific references below for Revision nos.)

I 31)1 SRV & LOCA Loads on Downcomer Bracing and Gusset Plates, NSLD Calc. 3C71179-002) 32)1 LaSaile County Station Mark ll Design Assessment Report, Rev.10 c

33)1 LaSalle Calculation 164," Suppression Pool Liner Assessment & Anchorage Assessment" i

34)1 LaSalle Calculaten 3C7-1075-001," Loads due to Loss of Coolant Accident in LaSalle Containment,"

Rev. 6 35)1 LaSaile Specification J-2534,

1 i

- References

1. PIF # L1997 06237 g
2. Stand-ll! Structural Analysis, S&L Program # 03.7.065-20.2)
3. USNRC Standard Review Plan 3.6.2, Rev.1, July 1981 i

GLOBAL UNIT DEFINITIONS :

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General Description A total of three cases are considered to cover all variations in configuration, material properties, and governing l

load combinations. These three cases are described below as part of the calculation index.

Calculation index The calculation is divided into three sections to consider the following cases:

Pages 5 to 11, 2"x1"x 3/16" stainkss steel channel subject to allloads in the suppression pool.

i Pages 12 to 17, 3x4.1 channel subjected to jet Impingement loads in the drywell and hydro-dynamic LOCA and SRVloads in the suppression pool.

Pages 18 to 24. 3x4.1 channel with one leg shortened by 1/2" to accommodate a thickened embed plate. This configuration is analyzed for hydro-dynamic LCX;A and SRV loeos in the suppression pool.

Case 1: 2"x1"x 3/16" Stalniees Steel Channel Preparation of inout to Stand Computer Mgl3,L 4

- This model includes the 2" channel as well as the half coupling and test plug connection detail shown in Section D-D on CBI dwg. 34, Rev. 3. This model covers all 2" channels on the well and basemat. Joint coordinates are m

center line coordinates. Addrtional joints are provided so that stresses can be determir.ed at the end of the fillets at each comer of the channel. Member properties of the channel web and flanges are based on a thickness tw of 3/16" and an e'fective width of 3.0". This is based on the criteria given in D.I. 20, Fig. 37.6.6 4

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Calc. No. L-001337 Rev, O Proj. No. 10248-012-Paga No. 6 Effective width - b = ba - 12 tw b = 3.0 *in - C 2 x 1 x Slit" Properties of Flanne and Web 3 b = 3.0 in t := g in AY = b t 3 t to t AY = 0.5625 *in (Z = g~ d IZ = 0.00165 *in Note that Ax is calculated in the Stand program using the values of YD and ZD. Arbitrary values of IX, lY, and AZ are input to Stand but are not used in the analysis. Member Pra== ties of 1/4" Dia. 3000 lb. half couclina From Catalog W-68 Bonney Forge. Allentown, PA A 1,125 in B = I in 8 Wall thickness t= t = 0.16 *in b=B use t = 0.17 in ^ b = 0.875 in t AY = 0.1488 in 3 b1 12 = T2' Note that Ax is calculated in the Stead program using the values IZ = 0.0003582*la of YD and ZD. Arbitrary values of IX, lY, and AZ are input to Stand d but are not used in the analysis. CAL 1337Z.MCD

C:Ic. No. L-001337 Rev. O Proj. N3.10248-012 Paga No. 7 Loads:

The previous Calculatiori No.164 (D.I. 33) identdied the following critical loads: Maximum Accdont Pressure = 45 psi (Ref. 32 Table 1,1 1) and LOCA Poolswellimpact. As shown in Table 2 of D.I. 34, loads due to pool swell impact act on structures above the suppression pool located between El. 700'-2" (High water level in the supprestion pool) and El. 718'-8" (Max. height of poolswell). The maximum value of pool swell impact pressure (= 643 psi)is used in this analysis. Member Lotds Member loads due to poolswell act on members 1 and 2. The magnitude is equal to the pressure times the member width. Ibf Unifo m icad, membem i and 2. GX = (643 + 45) 3.0 g GX = 2064 *-- Poolowellimpact pressure on circular half coupling and plug: From D.I. 34. Table 3, the maximum value of pool swell impact pressure acting on circular pipe sections is 48.88 psi. Uniform load, member 10: GX = (48.88 + 45) 0.875 GX = 82.14 = Memberloads on Members subjected t Accident Prvesure = 46 pol Ibf Uniform load, mems. 3 to 7 & 9: GX1 : 45 3.0 g GX1 = 135.0+ CAL 1337Z.Mc0

C:lc. N3. L-001337 Rev. O _ Proj. No. 10248-012 P ga No. 8 Ibf Uniform load, rnembers 11 & 12: GX2 : 45 0.875 y GX2 = 39.4 +- Uniform load, member 8: Load on member 8 is equal to balance of load not acting on member 11. GY : GX1 - GX2 GY = 95.6'f Joint 1.osds Member loads do not represent 100% of the pressure load acting on the channel because member length is based on center to conter dimensions. Therefore, length times member width will not completely represent the total surface area subjected to pressure loads. For this reason, Joint loads are used to appy the additional load that acts on the missing surface area. Joint loads due to poolswell are applied to Joint 3. The magnitude is equal to the pressure times the missing surface area of the channel flange. Flange lengtn = 1" Length modeled in Staad =.9063" Effective width = 3.0" Missing surface area: A = (1 .9063) in 3.0-in 2 A = 0.28 in Pressure load = 688 psi FX : 688 psi A FX = 193.4 albf CAL 13372. MOD 4 e

_.m..- -. + a n._u,,_ +a a 2 a sa., --r n C Ic. No. L-001337 R;v. O Proj, N3.10248-012 Pag 3 No. 9 Evaluate joint force at Joints 3 & 6 due to LOCA Wassure = 45 psi FY = 45 psi A FY = 12.65'Ibf , Thermal 1.oad: As stated in the previous Calculation 9o.164 (D.I. 33) the channel is analyzed with and without the effects of temperature. The temperature changa for the poolswellload condition is 76 deg. F. Verlations in Material Propertler, Review of Vendor-supplied CMTRs shows that ASTM A276 Type 304 material has been supplied with two types of finishes. Hot, tished material has a yield of 30 ksi and an ultimate of 75 ksi, whereas cold. finished material has a yield of 45 kai and an ultimate of 90 ksi. CMTRs are revewed to determine.ne appropriate design yield strength for each channel configuration. Material Yielti Stronath The following documents related to Vendor Specification 2534 are provided in Attachment 4 of the calculations: 1, Stores and Metal Venfication Summary & Supplement Sheets, File # 5.1 CCM

2. FStorial Heat Number Sheet Fi',e No. 8.16-2, Document #18
3. Certified Material Test Reports, File No. 5.2 These documents identify the following material heats for 2x1x3/16" channels:

Min. Specified Heat No. Yield Strength 2'5755 30,000 psi F30188 30,000 psi 30660 45,000 psi 30706 45,000 psi 30844 45,000 psi 40523 30,000 psi 42379 30,000 psi For the cases shown above, design yield strength is controlled by min. specified yield strength = 30 ksi. As permitted in Ref. 3, Section Ill.2.a. a 10% increase in min, specified design yield strength is used to account for strain rate effects associated with dynamic effects of LOCA loads such as jet impingement and poolswell j impact loads CAL 1337Z MCD

Calc. N3. L-001337 Rev. O Proj. N3.10248-012 Pag 3 No.10 Therefore, the allowable stress is: Fb = 0.951.130.0-kal Fb = 31.35 ksi Results of Stand 111 Analysis: Results of the aralysis are shown in Attachment A. Maximum member stress occurs in member 1 = 29.00 ksl. (See Page A7) Fb Mar 11 : ygg l ' Mar 11 = 1.08 l Check weld based on reactions at Joints 1 and 8 (Max. reaction occurs at joint 1). 2 2 5 fw, (1.434 .4467 y, Weld force: 3in fw = 0.50 - Fw = 0.707 21 ksi hin Weld Allowable: Fw = 2.78 - Mar 12 = -

  • Mar 12 = 5.56 I

CAL 1337Z.MCD i

Calc. Ns. L-001337 Rev. 0 - Proj.Ns. 10248-012 Page Ns.11 Check 3/16 weld between Channel and couplina for test niun: Diameter of circular weld a B = 0.875+ln Assume 1/2 of weld length is effective for Member no.11 and 12, each. B Therefore, weld length = L = 3.14159 y t = 1.37 *in M!d allowable = Fwi = Fw L Fwi = 3.83

  • kip fw : (.0743

.0499 )3 kip 2 2 Actual force in weld (Member 12 govems); fw = 0.09' kip Mar 13 = Fw1 g Mar 13 = 42.75 Inspection of this large margin shows that the half coupling and its attachment weld can easily resist the pool hydrodynamic loads. CAL 1337Z McD ) ) i \\

Cdc. No. L-001337 R2v. O Proj. No. 10248-012 P ga No.12 Case 2: 3x4.1 Channel Sublocted to Jet Impinnement Loads EIeyaration of Input to Staad Computer Model This model covers the following two configuretions:

1. Leak Test Assembly 39-EE located in the suppression pool (see CBI Dwg. No. 39, Rev. 5)
2. All 3 ASTM A36 leak chase channels in the drywell.

Joint coordinates are center line coordinates. Additional joints are provided so that stresses can be determined at the end of the fillets at each comer of the channel. Member pgerties of the channel web and flanges are based on an effective width of 1.00". Test couplings are not modeled for channels ir. the drywell because the design evaluation of the dry.vell channels is govemed by jet impingement loads which are defined ia D.I. #35, Sketch JF-1 A on Page 2 2 7. The presence of a test coupling is not significant in the evaluation of "EE" assemblies because it is attached to a vertical channel which is not a highly loaded member in the assembly. Member Propertlee Gud 1 Flance ProDertlee fMembert 1. 2. 6. 7) b : 1.in t = 0.273 in 3 bt AY :b-t 12 3-IZ = 0.0016955 in' 2 AY = 0.273 in Note that Ax is calculated in the Staad program using the values of YD and ZD. Arbitrary values of IX, lY, and AZ are input to Staad but are not used in the analysis. C3:4.1 i *eb Properties fMembers 3. 4. 5) b : 1.in t = 0.170 in 3 A :bt IZ = b 12 d IZ = 0.0004094 in 2 Note that Ax is calculated in the Staad program using the values A = 0.1700 in of YD and ZD. Arbitrary values of IX, lY, and AZ are input to Staad but are not used in the analysis. CAL 13?72.MCD e

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Csic, No!L-001337 Rev. 0

Proj,No. 10243-012 Paga No. _13 -

Leeds: Critical Assembly for C3x4.1 Evaluation Review of CBI Dwes. 32 Rev. 4 and 39 Rev. 5 indicates that all 3" leak test channels in the suppressirsn pool have the inside leg of the channel shortened by 1/2" to accommodate attachment to the thickened liner embed plate. See Seedon A4 on Dwg. 32, Secten D-D on Dwg. 39 and the related table which give the "C" dimension of 1/2". The only exception to this is Leak Test Ass'y EE on Dwg. 39 which has a "C" denension of 0". This assembly is analyzed as a separate case since its specific configuration is more severe that those channels that have a C dimension = 1/2*. The previous Calculation No.164 (D.I. 33) identified the following crhical loads: Maximum Accident Pressure = 45 psi (Ref. 32. Table 1.t 1) and LOCA Poolsweli impact Revie;. of CBI Dwgs. 34 through 37. Rev. 3,7,3,6, respectively, shows that Ass'y EE is used at 8 locatens: Four at El. 679' 0" and four at El. 726' 0". (Dwgs 1D through 1G, Revs. 8,7,4,6, respectivoi;.) These elevations will be used to reduce the poolswell impact loads on these critical channels. I As shown in Table 2 of D.I. 34, loads due to pool swellimpact act on structures above the suppression pool located between El. 700* 2" (High water lavel in the suppression pool).and El. 718'-8" (Max. height of poolswell). Based on Table 2, none of the "EE" assemblies lie in the zone subject to Poolswell impact forces Other forces acting on the Ass'y EE leak test channels are taoulated in the load combination table given on ~ page 26 of Calc.164 (Ref. 33). Atter pool swell impact, the next most entcal load combination is #8 which is jet impiagement load. This load case govems the design of A36 channels in the drywell. Jet loads in the suppression pool cre much str. aller than in the drywell. The jet pressure on the basemat is a maximum of 33 - pai and reduces to zero at El. 700'-2" (See Fig. 4 in D.I. 34) The related joint and member loads for the jet impingement load in the drywell are cesenbod below. + After pool swell impact, the next most critical load combination for channels in the suppression pool is Case #7 which applies a vertical pressure of 197.03 psi and horz. pressure of 161.13 psi Results of the Ass'y EE analysis for Load Combinations 7 are presented below Results for the other 3" channels which have a "C" dimension = 1/2" and which are located in the poolswell impact zone are evaluated later using another Stead lit model (See Case 3 below). Review of CBI Dwgs. 288 through 291 and 294 through 297, Rev. 3,3,3,4,3,3,2,3. respectively, shows that 3x4.1 channels (ASTM A36) have been used as leak chase channels in the drywell. Channels in the drywell are z not subject to hydrodynamic impa et loads, therefore the critical load for these channels is jet impingement. See load combination #8 in the load combination table given on page 26 of Calc.164 (Ref. 33). cAusuz.uco t .l

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~- C:Ic. No. L-001337 R;v. O Proj. No. 10248-012 Pcga No.14 Member Loads Member loads due to Load Combination #7 applies a vertical pressure of 197.03 psi and horz. pressure of 161.13 psi.. The magnitude of the member foad is equal to the pressure because the member width is 1". The vertical pressure is applied to members 1 & 2 and the horz. pressure is applied to Members 3 to 5. The load on members 6 and 7 is the same as on members 1 and 2 minus the drag loads. From Calc.164, Page 21, the LOCA drag load is 71.56 psi and the SRV drag load is 1.67 PSI. Net Load on Members 6 & 7: GX : (197.03 - 71.56 - 1.67) psi GX = 123.80

  • psi Jet Impingement loads on Members 3,4, and 5 As shown on Pages 26 and 27 of Calc.164, Load Case 8 is the jet impingement pressure load of 467 lbs/in acting on members 3. 4. and 5 which represent the channel web.

Note: See Page 25 for further discussion of jet loads in the containment drywell area. l l Joint Loads Member loads do not represent 100% of the pressure load acting on the channes because member length is based on center to center dimensions. Therefore length times member width will not completely represent the total surf ace area subjected to pressure loads. For this reason, Joint loads are used to apply the additionalload tha' octs on the missing surface area Joint loads for Load Combination 7 are applied to Joints 3 and 6. The i magnitude is equal to the pressure times the missing surface area of the enannei fiange and web. Flange length = 1.41" Web length = 3" Length modeled in Staad = 1.325" Length modeled in Staad = 2.727 l Effectue width = 1.0" { l Missing surface area: Aw = (3 - 2.727)d 90 Af (1,41 - 1.325).in 1.0 in 2 Aw is distributed to joints 3 and 6. therefore: Af = 0.0850 *in t Aw Aw = 7 2 Aw = 0.14 *in CAL 1337Z.MCO

Calc, No. L-001337 Rev, O Proj. N2,10248-012 Page N). 15 1 I 1 i h l l \\ Pressure load for Jt. 3 in X & Y directions = 197.03 pel &.161.13 poi, respectNey ) FX

  • 197.03 pel Af FY
  • 161.13 pol Aw FX = 16,75'Ibf FY = -21.99 'lbf Pressure load for Jt. 6 in X & Y directions =.123.8 pel &.161.13 po8..wpectNely

] FX * -123 8 prl Af FY = 161.13 pol Aw J - FX = -10.523 'Ibf FY = -21.99 'Ibf i I E reluate Joint Force at Joints 3 & 6 due to Jet Pressure = -467 pel FY r -467 psi Aw i Fi = 63.75 'Ibf i [9rmal1,.eadli i As stated in the previous Calculation No,164 (D.I. 33) the channelis analyzed with and without the effects of tempe.aturs. The teniperature. ;hange for the poolsweil load cond tion is 76 dog. F. and the change for Jet it.1pingement Loc'J is 30 deg. F. The 30 dog. change is accomplished by using a load factor of 0.4 in Load Combinatic:) 5. t ~ i i TN.13374WCf1 ~ ...... - _., ~..,. -. _. - -. - - - - -. -.... - -, -. ~.. -, -, -.. -.

Calc, No. L-001337 Rev. O Proj, No. 10248-012 Pago No.16 i 1 l MotorialYleid Stronath I The following documents related to Vendor Specification 2534 are provided in Attachment 4 of the calculations:

1. Stores and Metal Ver(cation Summary & Supplement Sheets, File # 5.1 CCM
2. Material Heat Number Sheet, File No. 8.16 2, Document #18
3. Certrfied Material Test Reports, File No. 5.2 3

l These documents identify the following material heets for the 3m4.1 channels in Arsen:bly 39 EE in the suppression pool: Men. Speelfied Actual Ultimate Heat No. Yield Strength Strength Per CMTR I 4007G 30,000 pel 85,350 l 40489 45,000 pel 89,200 j For the cases shown above, design yield strength is equal to the min. speedled yield strength = 30 ksi. As permitted in Ref. 3, Section lil.2.a. a 10% increase in the design yloid strength is used to account for strain rate effects associated with dynamic effects of t.OCA loads such as }et impingement and poolswell impact loads. Therefore, the allowable stress for channels in the suppression pool is: 4 1 j Fbi = 0.95-1.130.0 kol Fbt = 31.35 *ksi 1 The CBI CMTR documents identdy the following material heats for the ASTM A36 3x4.1 channels in drywell: Min. Specified ActualTensile Heat No. Yield Strength Strength Per CMTR 93063 36,000 psi 68.100 psi 94541 36,000 psi 72,300 pel Design yield strength is equal to the min. specified yield strength = 36 kel. In addrtion, a 10% increase in min, specified design yield strength is used as permitted to account for strain rete effects associated with jet _ impingement loads. Therefore, the allowable bending stress for channels in the drywell is: Fb2 2 0.95-1.136.0 kol Fb2 = 37.62 *ksi calm 7zuco -?' g 'mw yn v y--c-wc-y=+-++-py--va-spige y ur ar yyee g -9 wr7 4&e+y-e ww--N-g----, geyy-W gg--ew gyr-ww-e----a----a-1ev- -1r-m--- 'w. gig-eup"'- iw--h-* p+vv 4 e7w* w- - - --w---M-w q

Calc. No. L-001337 Rev. O Prof. No. 10248-012 Page No.17 ( r Itasults of Stand til Analvels: Results of the anaysis are shown in Attachment 8 For the 3m4.1 channels in Assembly 39-EE in the suppression pool, the rnaximum member stress due to hydrodynamic load (LC #1) occurs in member 4 (12.57 kol), and Fbi is the allowable stress. For A36 channels in the drywell. the maximum member stress due to jet impingement occurs in member 4 (35.77 kol), and Fb2 is the allowable stress. Assambly 39 EE ASTM A 36 Channels in Drywell Mar 21s Mar 21 = g g Mar 21 = 2.49 Mar 21s = 1.05 Check weld based on reactions at Joints 1 and 8 (Mex. reaction occurs in LC. #5). fw (.2038 +.7005 ) 8. kip 2 2 Wold force: i fw = 0.73

  • kip z

Weld Allowable: Fw : 0.707 21 kal 3g in Fw = 2.78 kip . Mar 22 - Mar 22 = 3.82 I i l CAL 1337EMCD 1 ,,.,,,,---.m,, ,e

l Cdc. No. L-001337 R;v. O Proj. No. 10248-012 Page No.18 4 Case 3: 3n4.1 Channel With Short Lea t Prenaration of input to Staad Computer _M2dfl This model covers all 3x4.1 channels billed on CBI Dwg. Nos. 32 (Rev. 4) and 39 (Rev. 5) other than those identified as Leak Test Assembly 39 EE (See Case 2). All Case 3 channels have one leg shortened by 1/2" as shown on Dwgs. 32 (Section A-A) and 39 (Section D-D). Joint coordinates are center line coordinates. Additionaljoints are provided so that stresses can be determined at the end of the fillets at each corner of the channel. Member properties of the channel web and flanges are based on an effective width of 1.00". Test couplings are not modeled for this configuration because Ass'y A (Dwg. 32) and Detail E (Dwg. 39) show that test couplings on these assemblies are always mounted on a verticalleg of the assembly. The vertical leg is not the critical member for pool hydrodynamic loads because these im9act loads primarity act in the vertical direction. Thus, the prest., of a test coupling in the suppression pool is only significant when it is attached to a honzontal chat. 1. Member Properties Member properties are the same as those used in the Case 2 model. Mater lal Yield Stronath The following documents related to Vendor Specification 2534 are provided in Attachment 4 of the calculations:

1. Stores and Metal Venfication Summary & Supplement Sheets, File # 5.1 CCM
2. Matenal Heat Number Sheet. File No. 8,16-2. Document #18
3. Certified Material Test Reports, File No. 5.2 These documents identify the following material heats for the 3x4.1 channels billed on CDI Dwgs. 32 and 39; Min. Specified Actual Ultimate Heat No.

Yield Strangth Strength per CMTR 30?S4 45,000 psi 91,400 40079 30.000 psi 85,350 40489 45,000 psi 89,200 CAL 1337Z MCD l i

l b'DOl 9 0 9

  1. Y*'

$fia A b N ohr"L ~ 0 N E~ $ e s r o.one a Lu,xey o

  • n,, g o,,,

telety Related Non Betoh-Asisted Paes /[, / of Caent Prepared by Dole Ptoleet Reviewed by Dole Prof. No, / C 7,6 t $ -C /1 Equip.No. Approved by Dele 9 . $ 'f/ 8.D k 0b c % -.L tb-If

  • p

{ m i .b ....~....,,/...- ~..~ K..t-._....yl... 0.::, 2 r O. c..._..-.i s .. ~....... _. .. a h ~. -..n. .. -m\\ f n. t }-.- _ i ^' .w I l W -.-- A. h A.n n t 4. v -.. _ : - _..-.l Prope.h 4... _- C.e.4-. a - S " $ Y$ t.- J L. f - -- -.-....-.-.- ~.-. E f.... 0 17 3 [o 14 T_ Cco./L DO i AW_ _ _ jsa -bl .__ _._k._5_4. Y. - ) O C. 5 1 o _... _ _ o.._T.H _ _ _. _O.S_(..,...._...__... ..5_._. 0. _. _.._ p. ) n. - _. n. .n. d ..... l... M f-. 5 .. -21% _..k ' f ' h h. _.. _... d.h4){v 1c. < /[C #3

7. -. 2. 7.%

C.7/9 h ed 8 5SG I (s b -7 7._7 . S + 4 = ao wS-w--e-6=- .-M-Wu' .s'.O.-4 w M i. -. _M.

C:Ic, No, L-001337 R:v. O Proj,No. 10248 012 Page No.19 I Heat number 40079 has the lowest yield strength (Fy = 30 ksi, so the allowable stress is: Fbi = 0.951.130.0 ksl Fb1 = 31.35'ksi Loade: Critical Assembly for C3x4.1 Evaluation: Review of the above specified CMTRs shows that channels from host no. 40079 have a yield strength of 30 ksi. Based on previous calculations, it is necessary to reexamine the poolswell impact loads acting on the channels from heat no. 40079. t As shown in Table 2 of D.l. 34, ioeds due to pos m4s %. vet act on structures above the suppression pool located between El. 700'-2" (High water level in 9.17 g4r sion pool) and El. 718' 8" (Max. height of poolswell). Therefore, CBI dwgs. 34 through 37 (Revision Nos. 3, 't, 4,6, respectively) were reviewed to identify all'32'. and '39' Serics channel asserr blies that fall within the poolswell zone. The following four assemblies were found to be subjected to significant poolswell impact loads: 39-A,39-M,39-N,39-FF. Of these fo'ur, only Assembly 39 M had horizontal channels from heat no. 40079. The center line elevation of 39-M is 703' 6" (See CBI drgs.1E and 1F, Revs. 7 & 4, respectively). Due to the poolswell phenomenon, the most criticalload condition occurs when the lower flange of the bottorn et annelis impacted due to poolswell. This elevation corresponds to 702' 111/4". However, conservatively, poolswell for this case will be based on El. 704' 0". From Table 2 of D.I. 34, the poolswell impact at 704'-0" is 421.9 psi (A value of 422 psi will be used in this calculation. LOCA pressure is added to yield a total applied pressure of 422 + 45 = 467 psi. Other forces acting on Ass'y 39-M are tabulated in the load combination table given o'i page 26 of Calc.164 (Ref. 33). As stated earlier, jet impingement load is not a goveming load in the suppression pool. Therefore. after pool swell impact, the next most critical load combination for channels in the suppression poolis Case #7 which applies a vertical pressure of 197.03 psi and horz. pressure of 161.13 psi. The Stand model for this third configuration is analyzed for a total of nine load cases as desenbod below: Case 1. This case represents poolcwellimpact on the lower flange of the upper channel of Ass'y 39-FF. Case 2. This case represents poolswellimpact on the lower flange of the lower channel of Ass'y 39-FF, This case ccmbined with thermal load produces the highest stresses and is used to qualify all channel assemblies built using heat numbers other than 40079. I Case 3. This case represents poolswellimpact on the lower flange of the lower channel of Ass'y 39-M. CAL 1337Z MCD ~ ~ ~

Cric. No. L-001337 R:v O Proj. No. 10248 012 Pcg3 No. 20 Case 4. This case represents Case #7 which applies a vertal pressure of 197.03 psi and horz. pressure of 161.13 pol.. Case $. This case represents thermal effects due to accident temperature. Cases 6,7, 8. and 9 are the same as cases 1,2,3, and 4 combined with the appropriate thermal effects. hiember Loads t Load Case 1 Member loads due to poolswell + accident pressure acting on members 1 and 2. The magnitude is equal to the pressure times the member width. Uniform load Members 1 and 2: GX = (643 + 45).1.C GX = 688

  • i Member lads on Members subjected to Accident Pressure = 46 pel a

Unform load, Members 3 to 7: GX1 : 451.00 GX1 = 45.00

  • Joint Loadg Joint loads are appled to Joints 3 and 6 to account for the additional poolswell load or accident pressure that acts on surface area not represented by member length times width. The magnitude is equal to the pressure times the missing surface area of the channel flange and web.

Flange length = 1,41" Web length : 3" Length modeled in Staad = 1.325" Length modeled in Staad = 2.727 Effective width = 1.0" CAtt3372 MCo . _ _ _. _, i _.,,.. ~. _ _, _ _ _ _ _., _ _,,, -

C:lc. N3, L-001337 Rev. O Proj.No. 10248-012 Paga No. 21 Mir, sing surface area: 8 Aw (3 - 2.727) 1 in Af e (1.41 - 1.325) in 1.0 in Aw is distnbuted to joints 3 and 6, therefore: t Af = 0.0850 *in Aw l z Aw = 0.14 *in Pressure load for Jt. 3 in X & Y directions = 688 psi &. 45 psi, respectively FX = 688 psi Af FY : 45 psi Aw FX = $8.48'Ibf FY = -6.14 albf Pressure load for Jt. 6 in X & Y directions = 45 pel FX = -45 psi Af FY : -45 psi Aw FX = -3.825 lbf FY = -6.14 *lbf Load Case 2 Load Case 2 is the same as Load case 1 except that poolswellimpact pressure acts on Members 6 and 7 and Joint 6 instead of members 1 and 2 and Joint 3. Therefore, the loads for these members and joints are just the reverse case of Load Case 1. Load Case 3 Load Case 3 represents poolswellimpact on the lower flange of the lower channel of Assy 39-M. Member loads due to poolswell + accident pressure act on members 6 and 7. The magnitude is equal to the pressure times the member width. As stated earlier, the center line elevation of 39-M is 703' 6"(See CBI dwgs.1E and 1F, Revs. 7 3 4. respectively). Due to the poolswell phenomenon, the most entical load condition occurs when the lower flange of the bottom channel is impacted due to poolswell. This elevation corresponds to 702* 11 1/4". However, conservatively, poolswell for this case will be based on El. 704' 0". From Table 2 of D.I. 34, the pootswellimpact at 704' 0" is 421.9 psi (A value of 422 psi will be used in this calculation. LOCA pressure is added to yield a total appled pressure of 422 + 45 = 467 psi. CAL 1337EMCD o t I g

Calc. No. L-001337 Rev. O Proj. N3.10248-012 Page No. 22 4 Unrform load. Members 6 and 7; GX = (422 + 45) 1.0T GX = 467

  • Member loads on membero subjected to Accident Preneure = 46 pel Uniform load. Members 1 to 5-GX1 = 451.007 GX1 = 45.00*f Joint Loads:

Joint loads are the same as for load case 2 except for Joint 6. Pressure load for Jt. 3 in the -X direction = 467 pal: FX $ 467 psi. Af FX = 39.69'Ibf Load Case 4: Alternate Load Case 7 (Calculation 164) As shown on Pages 26 of Calc.164. there is an altemate Load Combination #7 which applies a vertical pressure of 197.03 psi and horz. pressure of 161.13 psi.. The magnitudes of the member loads and the joint loads are the same as Case 2 given on page 14 of this calculation except that the loads for these members and joints are just the reverse case, i e., the maximum pressure load (197.03 psi) acts on Members 6 and 7 and Joint 6 instead of Members 1 and 2 and Joint 3. CAL 1337Z.MCD v n--- n-, - ~ - -... -,, -.., -r-. e,,,

h Cde. Ns, L-001337 R;v. O Proj, No - 10248-012 Paga No, 23 i LeM Case 5: Thermal Load As stated in the previous Calculation No.164 (D.I. 33) the channel is analyzed with and without the effects of temperature. Since jet impingement load in the suppression poolla not a governing load condition, the temperatute change corresponding to the poolswellload condition of 76 dog. F is used in the analysis. kende Casee 6.7.8 and 9: 1 These cases are the same as Cases 1,2, 3, and 4 combined with thermal effects. Bagults of Standill Analysis: Results of the analysis are shown in Attachment C. Revow of member stresses shown on Page C7 shows that design of channels made from Heat No. 40079 is govemed by Load Combination 8 (f8 = 26.17 kal), and design of all other 3x4.1 channels covered in Case 3 is governed by Load Combination 7 (f7 = 39.04 kel). f8 26.17.ksi f7 = 39.04.ksi PracMure for Adjustina Deelan field Stress The CMTR for heat no. 40489 reports a yield of 51.6 kal and an ultimate of 89.2 ksi. The yield meets the ASTM specified minimum of 45 ksi for cold finished material, but the ultimate value is 0.8 kailess than the minimum value of 90 ksi. In order to maintain the ASTM specifed stress margin of 45 kal between yield and ultimate, the design yield stress is adjusted to meet the following cnteria: Fy max 5 Fu.45 ksl. Allowable Stress: As stated previously, the 3x4.1 channel covered under this Case 3 analysis were manufactured from the folicwing three heat numbers: Min. Specified Ultimate Strength Heat No. Yield Strength from CMTR 30304 45,000 psi 91,400 > 90,000 0.K. 40079 30,000 psi 85,350 > 75,000 0.K. 40489 45,000 psi 89,200 Revised Fy = 89,200 - 45,000 = 44,200 The heat number corresponding to Load Cases 3,4,8, and 9 is 40079, so Fy8 = 30.0 ksi. Due to the adjusted design yield strength. Heat No. 40489 has the next lowest effective yield strength and controls for Load Case 7, so Fy7 = 44.2 ksi CAL 1337tMcD e,--~w-=----+ y ~,,-r w e w w r x -r-v-we,

  • s---,--m

.vm.-- w-----n- -s-~> ,~,.w-n-er.,~~ ,,wo+ - -, - ~ ~ -e-+-.m--- ~-

I C:lc. No. L-001337 Rev. 0 - Proj. N3.10248-012 Page No. 24 i i i t The corresponding allowable stresses are: r b Fb8 5 0.951.130.0 kol Fb7 = 0.951.144.2 koi Fb8 = 31.35 +ksi Fb7 = 46.19 *ksi 1 1 The resulting design margins are: Fb8 Fb7 Mar 31 = y Mar 31a = y Mar 31 = 1.20 Mar 31a = 1.18 4 r Check weld based on reactions at Joints 1 and 8 (Max reaction occurs in LC. #2 at Jt. 8): P fw = 1.5924 .1064 [ kip [ 2 2 Wold force: fw = 0.60

  • kip Fw = 0.707 21 kal fgin z

Wold Allowable: Fw = 2.78' kip 7 Fw Mar 32 = y e Mar 32 = 4,63 t Call 337Z.MCD 6 + ,,~m,-.,,.. ...w.-.e, ,*.,,._....-,.y,_,...c. ...w.,e.. ... ~..., ,,.y em, .., _ e v. c,_,.w w =

I C:lc. No. L-001337 R:v. O Proj, No. 10248 012 Paga No. 25 l Discussion of.let imolnnement Loads on Liner Leak Chase Channels inside Containment Drywell in the previous calculation (D.l. 33), the main purpose of the analysis was to analyze channels subject to hydrodynamic impact loads in the suppression pool. The jet impingement forces were not part of the goveming load case in the suppression pool. This calculation includes qualrfication of ASTM A36 channels in the drywell, so a study is included here to document that jet loads act on the web of the leak chase channels and do not apply significant leading to the channel flanges. The UFSAR (D.l. 24), Section 3.6, Table 3.6-8 provides a list of postulated pipe breaks inside the containment. Two t/ pes of breans are postulated: Circurr'erential and Longitudinal. Circumferential breaks cause Jets to develop parallel to the axis to the pipe, whereas Longitudinal breaks cause jets which act perpendicular to the axis of the pipe. Review of Figs. 3 61 through 3.615 shows that large bore high pressure piping inside the containment is close to the liner only at the containment wall penetration locations and these are always honzontal pipe runs. Vertical pipe runs are always away from the containment liner plate. Therefore, a jet force would apply a significant force to the channel flanges only if th:sre is a postulated longitudinal pipe break at or very close to the containment wall pipe penetration. Figs. 3.61 through 3.615 and Table 3.6-8 can be used to determine the approximate location of alllongitudinal breaks inside the containment. Based on this information, the closest longitudinal breaks to the liner channels are the break numbers C214 and C214S shown in Figs. 3.6 3 and 3.6-6, respectively. Per Table 3.6-8, the pipewhip restraints which have been designed to restrain the pipe from whipping due to the postulated breaks at C214 and C214S are R 72 and R 88, respectively, These restraints are shown on LaSalle Dwg S 384, Rev. U (D.I. 25). Using the dimensions shown on the plan view, the radial distance from the RPV center line to these restraints is: D1 - [(27 ft + 7.125 in)2 (3.ft + 8 in)2f D1 = 27.Bbft The elbow at which the break occurs is located further from the liner than the restraint. Therefore, the beation of the restraint conservatrvely can be used as the break location. The sketch on the following page shows that the distance from the pipe break to the drywell liner is greater than 19.5 ft. According to NUREG \\CR-2913 (D.I. 28), pipo break forces are not significant at distances greater than 8 pipe diameters from the pipe break location. For the Main Steam line with a diameter of 26 in, this dirtance is: DIA : 2 Gin D8 ' 8 DIA D8 = 17.33 ft The distance to the liner is 19.5 ft which is greater that D8. Therefore, it can be concluded that none of the longituoinal or circumferential breaks inside the containment will apply a significant jet loads on the flanges of the ASTM A36 liner leak chase channels in the containment drywell. CAL 1337ZMCD w s-,, - --- - ,r ra - -,,. w -w + - -- - -

n, n---,

.,-,-ve---- c--,r-- ---n -,-e-

.- -. ~ -____-_ _ -._ - - - _ ~. _ _ _.-..- -. l Cebe. He. l. ~(,t9/ :n > 7 \\ Cohee. Yer ~ Seer geant. & L.tsndy *" g,y, g p,,, Salety Related Nom 3eeety44eeeted Page f, [, / of Done Propeted by C#eM meviewed by Done progeot Date Pro l, No, j h,j h[. /1 Egulp. No. Approved by )\\ 8 P@c be.? E ke= G M. / Z._. m _L o. nos eou WSof( PE~ l

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s.......

' %5 5 A,Ekl % _ __.'...._.__ _ s ~h... -. _. +.=--.-*.-_-.--w_-ie...-+.. -4 i. k i\\ p.. - ..g. ..E. ',.E. .. LOC,'#/l.OT., Is ! - ..Pipc h.cbt-t0 ._._. _. 3 - 7 2._ _ ..... s a. _ R. - 6 9.. & n v i e. h (.. h ~ 5 I j. l k, hI e e +- 8 h -0 . AD5h3 -, k I %PY (Cp".o bidd ~ i 4 a, ~- u nd e.... ~

Ccic. Na. L-001337 R:v. O Prcj. No. 10248 012 PcgaNo.26 Fut_. SUWAARY AND CONCLUSIONS In response to PIF # L1997-06237, three channel configurations have been evaluated in the suppression pool and the drywell. This assessment has been performed using minimum specifed material yield strength as determined from vendor suppled certrfed material tot,t reports (CMTRs). In addrtion, the design yield strength is reduced, if necessary, to maintain a minimum of 45 ksl between yield and ultimate. Results are given in terms l of the margin factor which is defined as the ratio of allowable stress divided by actual stress. All margin factors are greater than 1.0 thus demonstrating that all leak chase channels have been found to meet the acceptance enteria and are thus able to serve as part on the containment pressure boundary. Margin factors are summarized below. Channel Section Etd i Case 1: C 2 x 1 x 3/16 Marti = 1.08 Mar 12 = 5.56 Case 2: Assembly 39 EE Mar 21 = 2.49 Mar 22 = 3.82 Drywell Channels Mar 21a = 1.05 Case 3: Mar 31 = 1.20 C3x4.1, Heat No. 40079 Mar 32 = 4.63 All other C3x4.1 in Mar 31a = 1.18 Suppression Pool l l l f CAL 1337Z MCO

Calculation L-001337, Rev. O Pro,tect No. 10248-012 Attachment A Pago A1 of 7 PAGE NO. 1 S T A A D - !!! Revision 20.2 Proprietary Program of Research Engineers, Inc. Date-OCT 21, 1997 Tine = 9: 5:13 USER ID: SARGENT & LUNDY ENGRS

1. STAAD PLANE 2XIX3/16 CHANNEL & TEST PLUG
2. INPUT WIDTH 72
3. UNIT INCHES POUND
4. JOINT COORDINATES
5. 1 0. 0.s 2 0.

7394; 3 0..9063; 4.1669.9063; 5 1.6456.9063

6. 6 1.8125.9063; 7 1.8125.7394; 9 1.8125 0.
7. 9 0.5475.9093; 10 1.264.9063: ?1.5475 2.33; 12 1.264 2.33 C. MEMBER INCIDENCES
9. I 1 2s 2 2 3; 3 3 4; 4 4 9; 5 5 6; 6 6 7; 7 7 8
10. B 9 10; 9 10 5; 10 9 11; 11 11 12; 12 10 12
11. MEMBER PROPERTY AMERICAN
12. 1 TO 9 PRI IX.1 1Y 8.E-4 IZ 1.65E-3 AY.5625 AZ.3 YD.1875 ED 3.00
13. 10 11 12 PRI IX.1 !Y 4E-4 II 3.582E-4 AY.1488 AZ.1 YD.17 ZD.875
14. MEMBER RE* EASE
15. 10 12 START MZ
16. CONSTANTS
17. E STEEL ALL IB. POISSON STEEL ALL
19. DENSITY STEEL ALL
20. BETA 0. ALL
21.
  • STAINLESS STEEL
22. ALPHA 99E-7 ALL
23. SUPPORTS
24. 1 8 PINNED
25. LOAD 1 LC 4,5,7
26. JOINT LOAD
27. 3 FX 193.4 FY -12.65
28. 6 FX -12.65 FY -12.65
29. MEMBER Lot.D 30, 1 2 UNI GX 2064.
31. 3 4 5 9 UNI GY -135,
32. 6 7 UNI GX -135.
33. 8 UNI GY -95.6 34, 10 UNI GX B2.14 35, 11 UNI GY -39.4
36. 12 UNI GX -39.4
37. LOAD 2 THERMAL
38. TEMP LOAD
39. 3 4 5 8 9 11 TEMP 76.
40. LOAD COMB 3
41. 1 1. 2 1.

Calculation L-001337, Rev. O Project No. 10248-012 Attachment A Page A2 of 7 .. PAGE NO. 2 2XIX3/16 CHANNEL & TEST PLUG

42. LEAD LIST ALL
43. PERTOPN ANALYSIS PR0BLEM STATIST!CS NUMBER OF JOINTS / MEMBER +LEEMENTS/ SUPPORTS =

12/ 12/ 2 ORIGINAL /rINAL BAND-WIDTH = 5/ 2 2, TOTAL DEGREES OF TREEDOM = 32 TOTAL PRIMARY LOAD CASES = L SIZE OF STIrrNESS MATRIX = 2Bb DOUBLE PREC. WORDS REORD/ AVAIL. DISK SPACE = 12.02/ 1069.3 MD, EXMEM = 1.02 MB ++ PROCFSSING ELEMENT STITTNESS MATRIX. 9: 5:14 ++ PR0(,ESSING GLOBAL STIFTNESS MATRIX. 9: 5:14 ++ PROCESSING TRIANGULAR TACTORIZATION. 9: 5:14 ++ CALCULATING JOINT DISPLACEMENTS. v 5:14 ++ CALCULATING MEMBER FORCES. 9: 5:14

44. PRINT JOINT DISP LIST 3 6 i

l I

Calculation L-001337. Rev. O Project No. 10248-012 Attachment A Pcg] A3 cf 7 2XIX3/16 CHANNEL & TEST PLUG -- PAGE No. 3 ) JOINT DISPLACEMENT (INCH RADIANS) STRUCTURE TYPE = PLANE JOINT LOAD X-TRANS Y-TRANS Z-TRANS X-ROTAN Y-ROTAN 3-ROTAN 3 1 0.00652 0.00002 0.00000 0.00000 0.00000 -0.v0293 2 -0.00060 0.00000 0.00000 0.00000 0.00000 0.00056 3 0.00505 0.00002 0.00000 0.00000 0.00000 -0.00237 6 1 0.00645 -0.00004 0.00000 0.00000 0.00000 -0.00358 2 0.00060 0.00000 0.00000 0.00000 0.00000 -0.00056 3 0.00713 -0.00004 0.00000 0.00000 0.00000 -0.00414

                            • END Or LATEST ANALYSIS RESULT '**********
45. PRINT HEMBEP. FORCEL LIST 1 4 7 9 10 22 r

Calculation L-001337 Rev. O Project No. 10248 012 Attachment A P;g3 A4 cf 7 2XIX3/16 CHANNEL & TEST PLUG -- PAGE NO. 4 HEMBER END FORCE 3 STRUCTURE TYPE = PLANE ALL UNITS ARE -- POUN INCH HEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION HOM-Y HOM-Z 1 1 1 -446.67 1434.44 0.00 0.00 0.00 0.00 2 446.67 91.68 0.00 0.00 0.00 496.42 2 1 0.00 -32.51 0.00 0.00 0.00 0.00 2 0.00 32.51 0.00 0.00 0.00 -24.04 3 1 -446.67 1401.93 0.00 0.00 0.00 0.00 2 446.67 124.19 0.00 0.00 0.00 472.38 4 1 4 625.78 -486.00 0.00 0.00 0.00 -373.03 9 -625.38 538.18 0.00 0.00 0.00 178.77 2 4 32.51 -0.26 0.00 0.00 0.00 29.46 9 -32.51 0.26 0.00 0.00 0.00 -29.56 3 4 658.29 -487.06 0.00 0.00 0.00 -344.36 9 -657.09 538.44 0.00 0.00 0.00 149.21 7 1 7 716.66 654.98 0.00 0.00 0.00 447.39 8 -716,66 -555.17 0.00 0.00 0.00 0.00 2 7 0.00 32.51 0.00 0.00 0.00 24.04 8 0.00 -32.51 0.00 0.00 0.00 0.00 3 7 716.66 687.50 0.00 0.00 0.00 471.43 8 -716.66 -587.68 0.00 0.00 0.00 0.00 9 1 10 690.17 -629.97 0.00 0.00 0.00 192.75 5 -690.17 681.48 0.00 0.00 0.00 -442.97 2 10 32.51 0.00 0.00 0.00 0.00 29.46 5 -32.51 0.00 0.00 0.00 0.00 -29.46 3 10 722.68 -629.97 0.00 0.00 0.00 222.21 5 -722.68 681.48 0.00 0.00 0.00 -472.43 10 1 9 -46.06 66.85 0.00 0.00 0.00 0.00 11 46.06 49.85 0.00 0.00 0.00 12.08 2 9 0.00 0.00 0.00 0.00 0.00 0.00 11 0.00 0.00 0.00 0.00 0.00 -0.01 3 9 -46.06 66.84 0.00 0.00 0.00 0.00 11 46.06 49.85 0.00 0.00 0.00 12.07 12 1 10 74.29 -6.25 0.00 0.00 0.00 0.00 12 -74.29 -49.85 0.00 0.00 0.00 31.04 2 10 0.00 0.00 0.00 0.00 0.00 0.00 12 0.00 0.00 0.00 0.00 0.00 0.01 3 10 74,29 -6.24 0.00 0.00 0.00 0.00 12 -74.29 -49.85 0.00 0.00 0.00 31.05

Calculation L-001337, Rev. O Project No. 10248 012 Attachment A Page A5 of 7 2XIX3/16 CHANNEL 6 TEST PLUG -- PAGE NO. .............. tNo or t.ATest ANAtysis Result "" "" " ""

46. PRINT SUFFORT REACTIONS q

4 i ( ~

p Cak,ulation L-001337, Rev. O Project No. 10248-012 - Attachment A Page A6 of 7 PAGE NO. 6 2XIX3/16 CHANNEL & TEST PLUG i SUPPORT REACTIONS -UNIT POUN INCH STRUCTURE TYPE = PLANE- { 4 JOINT LOAD FORCE-X TORCE-Y FORCE-Z HOM-X HOM-Y MOH Z i 1 1 -1434.44 -446.67 0.00 0.00 0.00 0.00 l 2 32.51 0.00 0.00' O.00 0.00 0.00 i 3 -1401.93- -446.67 0.00 0.00 0.00 0.00 8 1 -555.17 716.66 0.00 0.00 0.00 0.00 l 2 -32.51 0.00 0.00 0.00 0.00 0.00 3 -587.68 716.66 0.00 0.00 0.00 0.00 i r ? . * * * * * '" * '

  • END OF 1ATEST ANALYSIS RESULT ' * * "'
47. PRINT MEMBER STRESSES LIST 1 4 7 9 s

I l l-t e s ..---er,---. vc ,,,-,m...r,.-y.-- ...,,.--,,e, e. ,...._-~..+.....,..,......_,..~.-.,.--m,-..m..-.-..-ou,

Calculation L401337, Rev. O Project No. 10248-012 Attachment A Page A7 of 7 2XIX3/16 CHANNEL & TEST PLUG -- PAGE NO. 7,/ FTs N A L, MEMBER STRESSES ALL UNITS ARE POUN/SQ INCH i MEMB. LD SECT AXIAL BEND-Y BEND-Z COMBINED SHEAR-Y SHEAR-Z j 1 1 .0 794.1 7 0.0 0.0 794.1 2550.1 0.0 1.00 794.1 7 0.0 28205.6 20999.7 163.0 0.0 2 .0 0.0 T 0.0 0.0 0.0 57.8 0.0 1.00 0.0 7 0.0 1365.8 1365.8 57.8 0.0 3 .0 794.1 7 0.0 0.0 794.1 2492.3 0.0 1.00 794.1 7 0.0 26839.8 27633.9-220.0 0.0 4 1 .0 1112.5 C 0.0 21240.2 22352.8 865.4 0.0 1.00 1111.0 C 0.0 10157.3 11269.0 956.8 0.0 2 .0 57.8 C 0.0 1674.1 1731.9 0.5 0.0 1.00 57.8 C 0.0 1679.6 1737.4 0.5 0.0 3 .0 1170.3 C 0.0 19$66.2 20736.4 865.9 0.0 1.00 1169.6 C 0.0 8477.6 9647.2 957.2 0.0 7 1 .0 1274.1 C 0.0 25420.0 26694.1 1164.4 0.0 1.00 1274.1 C 0.0 0.0 1274.1 987.0 0.0 2 .0 0.0 C 0.0 1365.8 1365.8 57.8 0.0 1.00 0.0 C 0.0 0.0 0.0 57.8 0.0. 3 .0 1274.1 C 0.0 26785.8 20059.9 1222.2 0.0 1.00 1274.1 C 0.0 0.0 1274.1 1044.8 0.0 9 1 .0 1227.0 C 0.0 10951.5 12178.4 1119.9 0.0 1.00 1227.0 C 0.0 25168.7 26395.7 1211.5 0.0 2 .0 57.0 C 0.0 1674.1 1731.9 0.0 0.0 1.00 57.8 C 0.0 1674.1 1731.9 0.0 0.0 3 .0 1284.8 C 0.0 12625.6 13910.3 1119.9 0.0 l 1.00 1284.0 C 0.0 2684?.8 20127.6 1211.5 0.0

                          • END OF LATEST ANALYSIS RESULT **************

i

48. FINISH

..............

  • E N D O F S T AAD-I I I * * * * * * * * * * * * * * *
  • * *
  • DATE= OCT 22,1997 TIME- -9: 5:15 ****

For questions on STAAD-III,. contact: Research Engineers, Inc at Ph: (714) 974-2500 Fax: (714) 921-2543 n i i m e-w-w--v-+,-ww-5-ww%,,,,--y,-w wm ww- ,-vv-wr+,y-,,,,,--w, i-,--e 4-+m.w--v- +,w,-c.e-vr= -a m e s-- mm - e - m m-- r rm w mw or v= w-w ww-r w-1r, W-a e v-n=-w-*--

Calculation L 001337, Rev. O Project No. 10248-012 Attachment B Page B1 Cf 7 PAGE NO. 1 S T A A D - III Revision 20.2 Proprietary Program of Research Engineers, Inc. Date= SEP 30, 1997 Time = 10:42:16 USER ID: SARGENT 6 LUNDY ENGRS

1. STAAD PLAht 3X4.19 CHANNEL
2. INPUT WIDTE 72
3. UNIT INCHES POUND
4. JOINT COORDIVATES 5.10.0.;20..774; 3 0. 1.325; 4 0.551 1.325; 5 2.176 1.375
6. 6 2.727 1.325; 7 2.727 0.774; 8 2.727 0.
7. MEMBER INCIDENCES
8. 1 1 2; 2 2 3; 3 3 4; 4 4 5; 5 5 6; 6 6 7; 7 7 8
9. MEMBER PROPERTY AMERICAN 10.12 PRI IX.1 IY.0016955 II.0016955 AY.273 AZ.2 YD.273 ZD 1
11. 3 4 5 PRI IX.1 IY.0004094 II.0004094 AY.170 AZ.2 YD.170 ZD 1
12. 6 7 PRI IX.1 IY.0016955 II.0016955 AY.273 AZ.2 YD.273 ZD 1
13. CONSTANTS
14. 5 STEEL A!L
15. POISSON STEEL ALL
16. DENSITY STEEL ALL
17. BETA 0. ALL
18.
  • STAINLESS STEEL
19. ALPHA 99E-7 ALL
20. SUPPORTS 21, 1 0 PINNED
22. LOAD 1 LC 4. 5,7
23. JOINT LOAD
24. 3 TX 16.75 FY -21.99 25, 6 FX -10.523 FY -21.99
26. MEMBER LOAD
27. 1 2 UNI CX 197.03
28. 3 4 5 UNI GY -161.13 29, 6 7 UNI GX -123.8
30. LOAD 2 JET IMPINGEMENT
31. JOINT LOAD
32. 3 FY -63.75 33, 6 FY -63.15
34. MEMBER LOAD
35. 3 4 5 UNI GY -467.0
36. LOAD 3 THERMAL
37. TEMP LOAD
38. 3 4 5 TEMP 76.
39. LOAD COMB 4
40. 1 1. 3 1.
41. LOAD COMD 5 JET IMPINGEMT + THERMAL

Calet,lation L.001337, Re/. O Project No. 10248-012 Attachment B Page B2 of 7 3X4.19 CRANNEL -- PAGE NO. 2

42. 2 1. 3 0.40
43. LOAD LIST ALL i
44. PERTORM ANALYSIS PR0BLEM STATISTICS NUMBER OF J0!NTS/MEMBF8t+ ELEMENTS / SUPPORTS =

8/ 7/ 2 ORIGINAL /TINAL 'oAND-WIDTH

  • 1/

1 3, TOTAL DEGREES OF TREEDOM = 20 TOTAL PRIMARY 14AD CASES = SIZE OF STIrlHESS MATRIX - 120 DOUBLE PREC. WORDS REQRD/ AVAIL. DISK SPACE = 12.01/ 1070.8 MB, EXMEM = 1.02 MB ++ PROCESSING ELEMENT STIrrNESS MATRIX. 10:42:17 ++ PROCESSING GLOBAL STIrrNESS MATRIX. 10: 42:1'l ++ PROCESSING TRI ANGULAR TACTORIZATION. 10:42:18 ++ CALCULATING JOINT DISP 1ACEMENTS. 10:42:18 ++ CALCULATING MEMBER FORCES. 10:42:18

45. PRINT JOINT DISP LIST 3 6

,c

Calculation L-001337 Rev. O Project No. 10248-012 Attachment B Page B3 ef 7 3X4.19 CHANNEL -- PASE NO. 3 J0!NT DISPLACLMENT (INCH RADIANS) STRUCTURE TYPE = PLANE JOINT LOAD X-TRANS Y-TRANS Z-TRANS X-ROYAN Y-ROTAN Z-ROTAN 3 1 0.00245 -0.00004 0.00000 0.00000 0.00000 -0.00200 2 0.00006 -0.00012 0.00000 0.00000 0.00000 -0.00251 3 -0.00102 0.00000 0.00000 0.00000 0.00000 0.00072 4 0.00143 -0.00004 0.00000 0.00000 0.00000 -0.00129 5 -0.00035 -0.00012 0.00000 0.00000 0.00000 -0.00223 6 1 0.00235 -0.00004 0.00000 0.00000 0.00000 -0.00001 2 -0.00006 -0.00012 0.00000 0.00000 0.00000 0.00251 3 0.00102 0.00000 0.00000 0.00000 0.00000 -0.00072 4 0.00337 -0.00004 0.00000 0.00000 0.00000 -0.00152 5 0.00035 -0.00012 0.00000 0.00000 0.00000 0.00223 END OF LATEST ANALYSIS RESULT ************** ee+++++*******

46. PRINT MEMBER FORCES LIST 1 4 7

Calculation L-001337, Rev. O Project No..10248-012-Attachment B Page B4 of 7 -- PAGE NO. 4 3X4.19 CHANNEL i MEMBER END itRCES STRUCTURE TYPE = PLANE 4 ALL UNITS ARE -- P9CN INCH MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-2 TORSION MOH-Y MON-2 l 1 1 1 215.09 86.47 0.00 0.00 0.00 0.00 2 -215.09 66.03 0.00 0.00 0.00 7.91 2 1 700.50 -201.91 0.00. 0.00 0.00 0.00 2 -700.50 201.91 0.00 0.00 0.00 -156.28 3 1 0.00 -4.70 0.00 0.00 0.00 0.00 2 0.00 4.70 0.00 0.00 0.00 -3.64 4 1 215.09 81.76 0.00 0.00 0.00 0.00 2 -215.09 70.74 0.00 0.00 0.00 4.27 5 1 700.50 -203.19 0.00 0.00 0.00 0.00 2 -700.50 103.79 0.00 0.00 0.00 -157.74 l 4 1 4 191.35 104.32 0.00 0.00 0.00 -23.55 5 -191.35 157.52 0.00 0.00 0.00 -19.67 2 4 201.91 379.44 0.00 0.00 0.00 -12.43 5 -201.91 379.44 0.00 0.00 0.00 12.43 3 4 4.70 0.00 0.00 0.00 0.00 6.23 5 -4.70 0.00 0.00 0.00 0.00 -6.23 4 4 196.05 104.32 0.00 0.00 0.00 -17.32 5 -19f.05 157.52 0.00 0.00 0.00 -25.90 i 5 4 203.79 379.44 0.00 0.00 0.00 -9.93 5 -203.79 379.44 0.00 0.00 0.00 9.93 f 7 1 7 268.29 112.61 0.00 0.00 0.00 50.08 8 -268.29 -16.79 0.00 0.00 0.00 0.00 2 7 700.50 201.91 0.00 0.00 0.00 156.28 8 -100.50 -201.91 0.00 0.00 0.00 0.00 3 7 0.00 4.70 0.00 0.00 0.00 3.64 8 0.00 -4.70 0.00 0.00 0.00 0.00 4 7 268.29 117.31 0.00 0.00 0.00 53.72 8 -268.29 -21.49 0.00 0.00 0.00 0.00 y 5 7 700.50 203.79 0.00 0.00 0.00 157.74 8 -700.50 -203.79 0.0C 0.00 0.00 0.00 ...........*** END OP LATEST ANALYSIS RESULT ************** i

47. SECTION 0.

5 1. MEMB 4

48. PRINT SUPPORT REACTIONS 1

e -a..,.-aa ww-we.-,,s.e..w.- ,ww',< ,.,,,,w,-n-nn ,,,;,+-v. a -,v.-.e,,,,-.,g,.,,_n-ww-,,,_.e_., ,-n, ~,,,-,q .w-- --v-, , e-N

Calculation L-001337, Rev. O Project No. 10248-012 Att:chment B Pag] B5 cf 7 -- PAGE No. 5 3X4.19 CHANNEL SUPPORT PEA 0TIONS -UNIT POUN INCH STRUCTURE TYPE = PLANE JOINT LOAD TORCE-X FORCE-Y FORCE-Z MDM-X MOM-Y MOM Z 1 1 -86.47 215.09 0.00 0.00 0.00 0.00 2 201.91 700.50 0.00 0.00 0.00 0.00 3 4.70 0.00 0.00 0.00 0.00 0.00 4 -81.76 215.09 0.00 0.00 0.00 0.00 5 203.76 700.50 0.00 0.00 0.00 0.00 8 1 -16.79 268.29 0.00 0.00 0.00 0.00 2 -201.91 700.50 0.00 0.00 0.00 0.00 3 -4.70 0.00 0.00 0.00 0.00 0.00 4 -21.49 268.29 0.00 0.00 0.00 0.00 5 -203.19 700.50 0.00 0.00 0.00 0.00

  • * * * * * * * * * * * *
  • EN D O F LAT E S T ANALY S I S RE SU LT * * * * * * * * * * * * * *
49.
  • UNIT INCH KIP
50. PRINT MEMBER STRESSES LIST 1 4 7 1

i f Calculation L-001337, Rev. O Project No.10248 012 Attachment B Page B6 of 7 1 -- PAGE No. 6 3X4.19 CRANNEL t HEMBER STRESSES l ALL UNITS ARE POUN/SQ INCH MEMB LD SECT AXIAL BEND-Y BEMD-Z COMBINED SHEAR-Y SHEAR-Z t 1 1 .0 787.9 C 0.0 0.0 787.9 316.7 0.0 i 1.00 787.9 C 0.0 636.7 1424.5 241.9 0.0 2 .0 2565.9 0 0.0 0.0 2566.0 739.6 0.0 1.00 2565.9 C 0.0 12581.7 15147.7 739.6 0.0 3 .0 0.0 7 0.0 0.0 0.0 17.2 0.0 1.00 0.0 7 0.0 293.1 293.1 17.2 0.0 4 .0 787.9 C 0.0 0.0 787.9 299.5 0.0 l 1.00 787.9 C 0.0 343.6 1131.4 259.1 0.0. .0 2565.9 C 0.0 0.0 2566.0 746.5-0.0 1.00 2565.9 C 0.0 12699.0 15264.9 746.5 0.0 1 4 1 .0 1125.6 C 0.0 4890.4 6015.9 611.6 0.0 i 0.50 1125.6 C 0.0 11445.9 12571.5 15t.5 0.0-1.00 1125.6 C 0.0 4083.4 5209.0 926.6 0.0 2 .0-1187.7 C 0.0 2570.8 3767.5 223f. 0 0.0-0.50 1187.7 C 0.0 34583.0 35771.6 J.0 0.0 1.00 1187.7 C 0.0 2579.8 3767.5 2232.0 0.0 i 3 .0 27.7 C 0.0 1294.0 1321.6 0.0 0.0 0.50 27.7 C 0.0 1294.0 -1321.6 0.0 0.0 1.00 27.7 C 0.0 1294.0 1321.6 0.0 0.0 4 .0 1153.2 C 0.0 3596.4 4749.6 613.6 0.0 0.50 1153.2 C 0.0 101's1.9 11305.2 156.5 0.0 1.00 1153.2 C 0.0 1377.4 6530.6 926.6 0.0 5 .0 1198.8 C 0.0 2062.2 3261.0 2232.0 0.0 O.50 1198.8 C 0.0 34066.3 35265.1 0.0 0.0 1.00 1198.8 C 0.0 2062.2 3261.0 2232.0 0.0 7 1 .0 982.7 C 0.0 4031.6 5314.3 412.5 0.0 1.00 982.7 C 0.0 0.0 982.7 61.5 0.0 2 .0 2566.0 C 0.0 12581.7 15147.7 739.6 0.0 1.00 2566.0 C 0.0 0.0 2566.0 739.6 0.0 3 .0 0.0 C 0.0 293.1 293.1 17.2 0.0 1.00 0.0 C 0.0 0.0 0.0 17.2 0.0 4 .0 982.7 C 0.0 4324.7 5307.4 429.7 0.0 1.00 962.7 C 0.0 0.0 982.7 78.7 0.0 5 .0 2566.0 C 0.0 12699.0 15264.9 746.5 0.0-1.00 2566.0 C 0.0 0.0 2566.0 745.5 0.0

  • * * * * * * * * * * * *
  • EN D O F LAT ES T AN ALY S I S RE S U LT - * * * * * * * * * * * * * *

$1.

  • PARAMETERS

$2.

  • CODE AISC
53.
  • CHECK CODE 1 TO 12 14 70 22

-54. FINISH I i ..************* END OF STAAD-III *************** t k-l- ~i ^ L... _,,..._

Calculation L 001337, Rev. O Project No. 10248-012 Attachment B Pag] B7 of 7 '" DATE= SEP 30,1997 TIME-10:42:19 "" For questions on STAAD-III, contact: Research Engineers, Inc at Ph: (714) 974-2500 rax: (714) 921-2543 4 ---r---,

h d ' Calculation L-001337. Rev. O Project No. 10248-012 Attachment C - Page C1 of 8

f-PAGE NO.

1~ S T A A D - III Revision 20.2 + Proprietary Program of Research Engineers, Inc. Datea OCT 28, 1997 Time = 13:37: 2 USER IDI SARGENT & LUNDY ENGRS

1. STAAD PLANE 3X4.19 CHAhNEL
2. INPUT WIDTH 72
3. UNIT INCHES POUND
4. JOINT COORDINATES 5.10.

5;20..774; 3 0. 1.325 4 0.551 1.325; 5 2.176 1.325

6. 6 2.727 1.325; 7 2.727 0.774; 8 2.727 0.

'7. MEMBER INCIDENCES 8, 1 1 2; 2 2 3; 3 3 4 4 4 5: 5 5 6; 6 6 7; 7 7 8

9. MEMBER PROPERTY AMERICAN
10. 1 2 PRI IX.1 IY.0016955 IZ.0016955 AY.273 AZ.2 YD.273 ZD 1 11, 3 4 5 PRI IX.1 IY.0004094 IZ.0004094 AY.170 AZ.2 YD.170 ZD 1
12. 6 7 PRI IX.1 IY.0016955 IZ.0016955 AY.273 AZ.2 YD.273 ZD 1
13. CONSTANTS
14. E STEEL ALL
15. POISSON STEEL ALL
16. DENSITY STEEL ALL
17. BETA 0. ALL
18.
  • STAINLESS STEEL 19, ALPHA 99E-7 ALL
20. SUPPORTS 21, 1 d PINNED
22. LOAD 1 LC 4,5,7 UPPER CHANNEL
23. JOINT LOAD
24. 3 FX 58.48 FY -6.1425 25, 6 FX -3.825 FY -6.1425
26. MEMBER LOAD 27, 1 2 UNI GX 688.

28, 3 4 5 UNI GY -45,

29. 6 7 UNI GX -45
30. LOAD 2 LC'4,5,7 LOWER CHANNEL
31. JOINT LOAD
32. 3-FX 3.825 FY -6.1425
33. 6 FX -58.48 FY -6.1425
34. MEMBER-LOAD 35.-1-2 UNI GX 45, 36, 3 4.5 UNI GY -45.
37. 6 7 UNI-CX -688.

38; LOAD 3 LC 4,5,7 CHANNEL AT EL. 703'-0"

39. JOINT LOAD 4

40.-3 FX 3.825-rY -6.1425

41. 6 FX -39.69 FY -6.1425 g

e e-- g-ry r ---r y a7y r y-wr r-- m ~. e-t .,2 + tw<rr-e -+%d 9

i j Calculation L-001337, Rev. 0 Project No. 10248 012 Attachment C Page C2 of _8 - -- PAGE NO. 2 3X4.19 CHANNEL

42. MEMBER LOAD

-43.-1 2 UNI GX 45.

44. 3 4 5 UNI GY -4b.

,45. 6 7 UNI GX -467.

46. LOAD 4 LC 4,5,7 PRESSURE LOAD = 197.03 PSI
47. JOINT LOAD
48. 3 FX 10.523 FY -21.99 49, 6 FX -16,75 FY -21.99
50. M.ABER LOAD
51. 1 2 UNI GX 123.8
52. 3 4.5 UNI GY -161.13

$3. 6 7 UNI GX -197.03 .54. LOAD 5 THERMAL '55. TEMP LOAD

56. 1 TO 7 TEMP 76.
57. LOAD COMB C
58. I 1. 5 1.
59. LOAD COMB 7
60. 2 1. 5 1.
61. LOAD COMB 8 CHANNEL AT EL. 703'-0"
62. 3 1. 5 1
63. LOAD COMB 9 PRESSURE LOAD + THERMAL
64. 4-1. 5 1.0 65.10AD LIST ALI.
66. PERFORM ANALYSIS PR0BLEM STATISTICS NUMBER OF JOINTE/ MEMBER +E EMENTS/ SUPPORTS =

8/ 7/ 2 ~ ORIGINAL / FINAL BAND-WIDTH = 1/ 1 5, TOTA' DEGRFES OF FREEDOM = 20 TOTAL PRIMARY LOAD CASES SIZE OF STIFFNESS MATRIX = 120 DOUBLE PPEC. WORDS RE0RD/ AVAIL. DISK SPACE = 12.01/ 1069.0 MB, EXMEM = 1.02 MB ++ PROCESSING ELEMENT STIFFNESS MATRIX. 13:3I: 4 ++ PROCESSING GLOBAL STIFFNESS MATRIX. 13:37: 4 ++ PROCESSING TRIANGULAR FACTORIZATION. 13:37: 4 ++ CALCULATING' JOINT DISPLACEMENTS. 13:37: 4 ++ CALCULATING MEMBER FORCES. 13:37: 4

67. PRINT JOINT DISP LIST 3 6 t

i - ~ - +.. -.m-*- - -.. -... ~, r mare.- ,.ir,r-e-v. r-e,-.- .m-. ~ -r--..er.--, n- --.r---- -,,---+v.. ~ - - + -, - -

iC la culation L-001337 Rev. O Project No.'10248-012 - Attachment C Pagh C3 of 8 -- PAGE NO. 3 3X4.19 CHANNEL r JOINT DISPLACEMENT (INCH RADIANS) STRUCTURE TYPE = PLANE JOINT LOAD X-TRANS Y-TRANS Z-TRANS X-ROTAN Y-ROTAN 2-ROTAN 3 1 0.00769 0.00001 0.00000 -0.00000 0.00000 -0.00811 2 -0.01160 -0.00003 0.00000 0.00000 0.00000 0.01242 3 -0.00765 -0.00002-0.00000 0.00000 0.00000 -0.00809 4 -0.00095 -0.00003. 0.00000 0.00000 0.00000 0.00050 5 -0.00083 0.00062 0.00000 0.00000 0.00000 0.00097 6 0.00687 0.00063 0.00000 0.00000 0.00000 -0.00714 7 -0.01250 0.00060 0.00000 0.00000 0.00000 0.01339 8 - -0.00848 0.00060 0.00000 0.00000 0.00000 0.00905 9 -0.00177 0.00059 0.00000 0.00000 0.00000 0.00147 6 1 0.00760 -0.00003 0.00000 0.00000 0.00000 -0.00425 E 2 -0.01189 0.00002 0.00000 0.00000. 0.00000 0.00594 -3 -0.00700 0.00001 0.00000 0.00000 0.00000 0.00395 4 -0.00106 -0.00004 0.00000 0.00000 0.00000 0.00111 5 0.00122 0.00100 0.00010 0.00000 0.00000 -0.00083 6 0.00882 0.00097 0.000v0 0.00000 0.00000 -0.00508 7 -0.01067 0.00101 0.00000 0.00000 0.00000 0.00511 0 -0.00658 0.00100 0.00000 0.00000 0.00000 0.00312 9 0.00016 0.00096 0.00000 0.00000 0.00000 0.00028

                          • END OF LATEST ANALYSIS RESULT **************
68. PRINT MEMBER FORCES LIST I 4 7 i

l 4 .-r-- +- r = w--vv-- =-v-, .w r- +m -v' e-~ - - - - - - - - - - - - - - - - - - - - ~ - - - - - - + -

Calculation L-001337, Rev.' O.. Project No.10248-012; Attachment C - Paga C4 of 8 -- PAGE NO. 4-3X4.19 CHANNEL MEMBER END FORCES STRUCTURE TYPE = PLANE ALL UNITS ARE -- POUN INCH MEMBER LOAD JT AXIAL SHEAR-Y' SHEAR-Z TORSION MOM-Y MOM-Z 1 1 1 -49.48 463.69 0.00 0.00 0.00 0.00 2 49.48 -275.18 0.00 0.00 0.00 101.22 2 1-241.35 -336.75 0.00 0.00 0.00 0.00 2 -241.35

349.08 0.00 0.00 0.00

-93.96 3 1 181.49 -225.46 0.00 0.00 0.00 0.00 2 -181.49 237.79 0.00 0.00 0.00 -63.46 4 1 257.07 -92.13 0.00 0.00 0.00 0.00 1 2 -257.07 126.06 0.00 0.00 0.00 -29.89 5 1 -1,34 -7.29 0.00 0.00 0.00 0.00 2 1.34 7.29 0.00 0.00 0.00 -2.00 6 1 -50.82 456.40 0.00 0.00 0.00 0.00 2 50.82 -267.89 0.00 0.00 0.00 99.23 7 l' 240.02 -344.03 0.00 0.00 0.00 0.00 2 -243.02 356.36 0.00 0.00 0.00 -95.95 8 1 180.16 -232.74 0.00 0.00 0.00 0.00 2 -180.16 245.07 0.00 0.00 0.00 -65.46 9 1 255.74 -99.42 0.00 0.00 0.00 0.00 2 -255.74 133.34 0.00 0.00 0.00 -31.89 4 1 4 162.39 -80.42 0.00 0.00 0.00 -110.93 5 -162.39 153.54 0.00 0.00 0.00 -79.17 2 4 377.70 210.42 0.00 0.00 0.00 170.36 5 -377.70 -137.2s 0.00 0.00 0.00 112.15 3 4 266.41 150.55 0.00 0.00 0.00 111.53 5 -266.41 -77.43 0.00 0.00 0.00 73.71 4 4 204.79 146.30 0.00 0.00 0.00. 13,07 5 -204.79 -115.54 0.00 0.00 0.00 11.92 5 4 7.29 -1,34 0.00 0.00 0.00 6.75 5 -7.29 1.34 0.00 0.00 0.00 -8.92 6 4 169.68 -81.75 0.00 0.00 0.00 -104.18 5 -169.68 154.88 0.00 0.00 0.00 -88.08 7 4 384.99-209.08 0.00 0.00 0.00 177.11-5 -384.99 -135.96 0.00 0.00 0.00 103.24 8 4 273.69 149.22 0.00 0.00 0.00 118.28 5 -273.69 -76.09 0.00 0.00 0.00 64.79 19 4 212.08-144.96 0.00 0.00 0.00 19.82 5 -212.08 116-87 0.00 0.00 0.00 3.00 '7 1 7-184.48 133.77 0.00 0.00 0.00 90.06 8 -184.48 -98.94 0.00 0.00 0.00 0.00 2 7- -106.35- -59.87 0.00 0.00 0.00 -252.42 -8 106.35 592.30 0.00 0.00 0.00 0.00 3 7 -46.49 -30.60 0.00 0.00-0.00 -163.51 8 46.49 392.06 0.00 0.00 0.00 0.00 v-y

t Calculation L-001337, Rev.' O Project No. 10248-012_ Attachment C pig 3 C5 of 8 3 3X4.19 CHANNEL -- PAGE NO. '5 l MEMBER END FORCES STRUCTURE TYPE = PLANE ALL UNITS ARE -- POUN-INCH MEMBER LOAD JT AXIAL SHEAR-Y' SHEAR-Z TORSION' MOM-Y MOM-Z a 4 7 226.31 79.48 0.00 0.00 0.00 '2.50 226.31 73.02 0.00 0.00 0.00 0.00. d B 5 7 1.34 7.29 0.00 0.00 0.00 5.64 8 -1.34 -7.29 0.00 0.00 0.00 0.00 6 7 185.82 ~141.G6 0.00 0.00 0.00 95.70 185.02 -106.23 0.00 0.00-0.00 0.00 8 105.02 -52.58 0.00 0.00 0.00 -246.78 7 7 8 105.02 585.10 0.00 0.00 0.00 0.00 8 7 -45.16 -23.32 0.00 0.00 0.00 -157.93 8 15.16 384.77 0.00 0.00 0.00 0.00 9 7 227.65 86.76 0.00 0.00 0.00 0.14 227.65 65.74 0.00 0.00 0.00 0.00 8 "' * ' " * * '

  • END OF LATEST ANALYSIS RESULT * " * * * " * ' * "
69. SECTION 0.

5 1. MEMB 4 1

70. PRINT SUPPORT hEACTIONS g

l I ) '-*'F T F ~'W' w

  • vr

,,,,c me _ y, y,

Calculation L 901337, Rev. O Project No. 10248-012 Att:chment C Paga C6 of 8 3X4.19 CHANNEL -- PAGE NO. 6 SUPPORT REACTIONS -UNIT POUN INCH STRUCTURE TYPE = PLANE JOINT LOAD TORCE-X FORCE-Y TORCE-Z MOM-X MOM-Y MOM Z 1 1 -463.69 -49.48 0.00 0.00 0.00 0.00 2 336.75 241.35 0.00 0.00 0.00 0.00 3 225.46 181.49 0.00 0.00 0.00 0.00 4 92.13 257.07 0.00 0.00 0.00 0.00 5 7.29 -1.34 0.00 0.00 0.00 0.00 6 -456.40 -50.82 0.00 0.00 0.00 0.00 7 344.03 240.02 0.00 0.00 0.00 0.00 8 232.74 100.16 0.00 0.00 0.00 0.00 9 99.42 255.74 0.00 0.00 0.00 0.00 8 1 -98.94 184.48 0.00 0.00 0.00 0.00 2 592.38 -106.35 0.00 0.00 0.J1 0.00 3 392.06 -46.49 0.00 0.00 0.00 0.00 4 73.02 226.31 0.00 0.00 0.00 0.00 5 -7.29 1.34 0.00 0.00 0.00 0.00 6 -106.23 185.82 0.00 0.00 0.00 0.00 7 585.10 -105.02 0.00 0.00 0.00 0.00 8 384.77 -45.16 0.00 0.00 0.00 0.00 9 65.74 227.65 0.00 0.00 0.00 0.00

                            • END OF LATEST ANALYSIS RESULT **************
71. PRINT MEMBER STRESSES LIST 1 4 7 l

) Calculation L-001337 Rev. 0 ' Project No. 10248-012 Attachment C-Pcga C7 of 8 =3X4.19 CHANNEL -- PAGE NO. 7 MEMBER = STRESSES ALL UNITS ARE POUN/SQ INCH-MEMB LD SECT AXIAL BEND-Y BEND-Z COMBINED SHEAR-Y SHEAR-Z 5 4 1 1 .0 181.2 T 0.0 0.0 181.3 1698.5~ 0.0 1.00 181.2 T 0.0 8149.3 8330.5 1000.0 0.0-2 .0 884.1 C 0.0 0.0 884.1 1233.5 0.0 1.00-884.1 C ' 0. 0 7564.3 8448.4 1278.7-0.0 3- .0 664.8 C 0.0 0.0-664.8= 825.8 0.0 1.00 664.8 C' O.0 5109.3 5774.1 871.0 0.0 4 .0 941.7 C 0.0 0.0 941.7 337.5 0.0 1.00 941 7 C 0.0 2406.5 3348.2 461.7 0.0 5 .0 4.9 T 0.0 0.0-4.9 26.7 0.0 1.00' 4.9 T 0.0 160.7 165.6 26.7 0.0 6. .0 186.1 T 0.0 0.0 186.2 1671.8 0.0 1.00 186.1 T 0.0 7988.6 8174.7 981.3 0.0 7 .0-879.2 C 0.0 0.0 879.2 1260.2 0.0 1.00 879.2 C 0.0 7725.0 8604.2 1305.4 0.0 8 .0 659.9 C-0.0-0.0 659.9 852.5 0.0 1.00 659.9 C 0.0 5270.0 5929.9 897.7 0.0 9 .0 936.8 C 0.0 0.0 936.8 364.2 0.0 1.00 936.8 C 0.0 2567.2 3504.0 488.4 0.0 4 1 .0 955.3 C 0.0 23030.8 23986.0 473.1 0.0 0.50 955.3 C 0.0 6380.9 7336.1 688.1 0.0 1.00 955.3 C 0.0 16436.8 17392.1 903.2 0.0-2 .0 '?21.0 C 0.0 35370.3 37592.1 1237,7 0.0 0.50 e'21.8 C 0.0 2958.5 5180.3 1022.7 0.0 1.00 2221.8 C 0.0 e,e85.5 25507.3 807.6 '0.0 3 .0 1567.1 C 0.0 23155.8 24722.8 885.6 0.0 0.50 1567.1 C 0.0 842.4 2409.5 670.5 0.0 1.00 1567.1 C 0.0 15303.2 16870.2 455.5 0.0 4 .0 1204.7 C 0.0 2713.9 3918.6 860.6 0.0 0.50 1204.7 C 0.0 10923.0 12127.6 90.5 0.0 1.00 1204.7'C 0.0 2475.0 3679.7 679.6 0.0 5 .0 42.9 0 0.0 1400.6 1443.5 7.9 0.0 0.50 42.9 C 0.0 1626.0 1668.8 7.9 0.0 1.00 42.9 C 0.0 1851.3 1894.2 7.9 0.0 6 .0 553.1 C 0.0 21630.2 22628.3 480.9 0.0-0.50 998.1 C 0.0 4754.9 5753.0-696.0 0.0 1.00 998.1 C 0.0 18288.1 19286.2 911.1 0.0 7 .0 2264.6 C 0.0 36771.0 39035.6-1229.9 0.0 0.50. 2264.6 C 0.0 4584.5 6849.1 1014.8 0.0 E1.00 2264,6 C 0.0 21434.2 23698.9 799.7 0.0 8 .0 1609.9 C 0.0 24556.4 26166.3 877.8 0.0 0.50 1609.9 C 0.0 2468.4-4078.3 662.7 0.0 1.00 1609.9 C-0.0 13451-9 15061.8 -447.6 0.0- -9 .0 1247.5 C 0.0 4114.6 5362.1 852.7 0.0 0.50 1247.5 C 0.0 9297.0 10544.5 82.8 0.0 l_ 1.00 1247.5 C-10. 0 623.7 1871.2-687.5 0.0 l l 7' 1 .0 675.8 C 0.0 7250.6-7926.3 490.0 0.0 1.00 675.8 C- -0.0 0.0 675.8 362.4 0.0-j. L E, _, ' u-. .=.

~ Calculation L-001337, Rev. O Project No..10248-012. Attachment C PCgo C8 of 8 Bj/ ClfJ A \\-- / 3X4.19 CRANNEL -- PAGE NO. MEMBER STRESSES .ALL. UNITS ARE POUN/SQ INCH MEMB LD SECT AXIAL BEND-Y BEND-Z COMBINED SHEAR-Y SHEAR-Z '2 .0 389.6 T 0.0 20321.7 20711.3 219.3 0.0 1.00 389.6 T 0.0 0.0 389.6 2169.9 0.0 3 .0 170.3 T 0.0 13168.5 13338.8 112.1 - 0.0 1.00 170.3 T 0.0 0.0 170.3 1436.1 0.0 4 .0 829.0 C 0.0 201.1 1030.1 291.1 0.0 1.00 829.0 C 0.0 0.0 829.0 267.5 0.0 5 .0 4.9 C 0.0 454.0 458.8 26.7 0.0 1.00 4.9 C 0.0 0.0 4.9 26.7 0.0-6 .0 600.6 C 0.0 7704.5 8385.2 516.7 0.0 1.00 680.6 C 0.0 0.0 600.7 389.1 0.0 7 .0 384.7 T 0.0 -19867.8 20252.5 192.G 0.0 1.00 384.7 T 0.0 0.0 384.7 2143.2 0.0 0 .0 165.4 T 0.0 12714.6 12880.0 85.4 0.0 1.00 l',, 4 7 0.0 0.0 165.4 1409.4 0.0 9 .0 833.9 C 0.0 655.1 1489.0 317.8 0.0 . 1.00 833.9 C C0 0.0 833.9 240.8 0.0

  • * * * * * * * * * * * *
  • END OF LATEST ANALYSIS RESULT * * * * * * * * * * * * * *
72. FINISH

.....********* END OF STAAD-III ***************

        • DATE-OCT 28,1997 TIME = 13:37: 5 ****

For questions on STAAD-III, contact: 4 Research Engineers, Inc at Ph: (714) 974-2500 Fax: (714) 921-2543 i 9 4 ~ , * ~. -m.- -, - --,, +._;,,

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3. Non Code Matt.

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-'" Ai,11Y A55URANCi DOCUNisNT 'NDEX - -Specification A5 94. ALT _ Page of calculation L.ooi337 - Project No. 10248 012. . T,,1 Docutaont Titic

6. /4 Td5 ArrACHMENT D Page 3 Of 39 R/o-File Ndmber

[~ C P, 2 7 ' Contractor Name . Document Li, sting: C NT /2h ~ l ( ( Enc,ineer 5ignoCf Paper Count O9 ._,n..,._., .--,,,..e--.

.. _ _.. _ _. ~.. _ _ _ _. - Calculation L-001337 Project No. 10248-012 ATTACHMENT D 1 - Page 4 Of 39 R/o REYNOLDS ALUMINUM SUPPLY COMPANY META LS AND BUILDINC PRODUCT 5 4500 firth AVLNUE S. P O. DOX 10785. BIRMINGHAM, ALABAMA 35202 205/591234 f September 31, 1974 Chicago Bridge P. O. Box 774 Kankakee, Illinois 60901 Attention: Art Johnson Please use this letter as authorization to mark material on P.O.

  1. C73-6336-12A as follows:

I 6 pcs. Ht. # F30188 22 pcs. Ht. # 23755 l 39 pcs. Ht. # 17797 7 pcs. Ht. # 42379 Very truly yours, REYNOLDS ALUMINUM SUPPLY CO. /// Bob Littleton BL:rf cc: Tile l t I ll 1 in business smce 1914

Cs u o i3 ORYNCLD ALGMINUM SOPPLY "CMPANY p opls o ec o ATTACliMENT D CERTIFICATE OF TEST STAINLESS STEEL ['/ i~ Date di M DO /luYMb Customer Order No. 7.3- /,33 (o -/S /) Customer U u Address Consignee Consignee Order No. Address A'M7 O 7" O 7d 'l 9 Date of Shipment lavoice No. EdN-4"A MO Grade 80 Specification M ATERI AL stE M HEAT NUMBER NUMBER OF PIECESl SIZE CONDITION 1. F 30I C6 (,o AX( A 3// t. X / A 0 O**W a. A swr ii a x i n atis x i.p o nu, n-is,u 2 3. et 3 M Y f; AAI X J// G X / 74 f. /7797 .3 9 ,R X / A J//6 A / 20 f, 4A S ?') 7 A )( / X.3// t. A / ='l O 71-IS CHEMICAL ANALYSES st:M C MN P S Se CR Ns Cu Ta Cs Mo /. .044 44.0 CA/ 0/t ,46 / /./ f /. 7 f t A. 0 4 1.45.0 %. D I to .'70 1830 ?.60 \\ 3. .04

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, 0 5' i.47 .019 a c it 51 it. 2.R f.60 PHYSICAL PROPERTIES its M TENSILE STRENGTH l YlELD STRENGTH % ELONGATION HARDNESS REMARKS /. J'7 2 00 J 9,0 0 0 6'O 686. f 69.I gg gz A. 80 600 A 9,70 0 i 59 I R8 7O a, d'o. 200 39,700 &A b 7 8-19 y, 86, Aco 3 f, 4 0D f. n,7 00 3 s,to o 54 b_ R A l'L We certify that the chemical analyses and physical test results applying on the above order number are correct and true to the best of our knowledge and betini i Sworn and subscribed to before me Reynolds Aluminum Supply Company [ 7 ......~.s.. D..f i 9

y Addition 7-18'74 I c.icuiauon t-00im ITT Harper Inc. rRJ, Project No. 10248-012 8200 Lehigh Avenue. uorion Grove su 60053 ATTACHMENT D .(3126906-0000 Page 6 Of 39 R/o CERTIFIED TEST REPORT [ Date: 6/l4/74 HMH Register No.005439 'HETAt. GOODS SERVICE CENTER Cus t cre r : DIV ALCAN ALUM IIMO W. ADDISON STREET llMH Drawing No.* ."RA Nv,L I N PA Rr., I t.L. 60131 t.ddress. HMH Vork Order No. Purchase Orde r No. 2fw')l0S$ Descriptiun of litm-Weight and 'Le ng t h Material pieces S h alie

Sire, I

1090 LDS l 10/24' 304 STAINLESS STEtt. I CHANNEL 73 xi = 1/4" 13 PCS C-75-Ml f yr, <; ( n ~.- v..C -4 WM 1 n.p, tNtDu ~~ ~" ,g* {d-- e SPEC ASTM A276 Q -1/ S N CifiCATIC!l3 S S T.d b I bd b 4

a - __

Chemical Analysis g g ) 4h j kb-- -Si ~ MN ~, gj, 1 Heat Number

  • C 5

P CU M0 CR 7hk. 30S44 ,.06h 028 01Iyg.21 29 18.65 9.91 22 1.38 ^ Mechanical Propert les Heat Number Tensile Strength Yield Strength Elongat ion R of A Hardness 300 % 88,300 50.000 byt 69 04 3 1 1 reco rd f, of this Ve heret, certify that the above f igures are correct as contained in the I MO.C.MGR.

.. u.... u.g - ca P anoa '-oolm l nn ITT Morpor Inc. 8 x i Pr ject No. 10248 012 8200 LcN;h AveM. 3.*crion Grove.l!! 00053 ATTACHMENT .. f 8 o x..= n r :" (3121058-0000 Page 7 Of 39 l, 6/4/74 CIMHCED CERTIFIED TEST REPORT Date: ITEn HHH Register No.005090 toner: METAL GOODS SERVICE .DIV ALCA?l ALU:t HMH Drewing No. P.O. 00X 427 FRAl!xtiti PARK,.1LL. 60131

rcss :

HHH Work Order No. chose Order No. 2W0007 Description of item Ma ter i a,I ight and Sire. Length,, Pir;ce s Shape ..G m 4 hI.i,w w,9, 304 STAlfiLESS, STEEL 8045 LOS 2 x I x t/4" R/L l10 PCS CHAMNEL C. 73.4)37:55 . l.h.0 D .CtC4RS O'IN % t ' '- I D.4 L 5.'iiRC.. 62.2n?j._., i 0 SPLClHC.ECN.. ]})llg J 2y,, 9 lita rao,y,, 46 Chcunmd k4' N ~Y l Y f'((- ' 4,g y I { Chemical Analysis i g h / Hect Numbe r C S P CU M0 CR fil I Hff g[* 30599 000 012 022. 63 25 10.30 9.65 45 1.4 3m 30706 064 021 023 .31 .34 18.69 10.03 .24 !.43 1 1-30013 049 018 .023 26 28 18.68 9.90 .34 1.l Si Hechanical Propertles H2at Numbe r tensile Strength Yleid Strength %Elongotion R of A Hardness PCS LOS 30599 90,600 51.700 50 68 57 3GS 30'06 91.000 50,000 48 67 p 402 30013 89.200 49,300 51 70 2 13 as contained in the records of this j3 We he reb y ce r t ify hat the above figures are correct jo g company. %.2 wZ,G.C.lAS.'L 2 ~

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D () MATERI AL HEAT () M*j','({J,P Itsemblies O stas cave ts d NUMBEFI SHEET

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  1. 80"/2

/4fC 3 88[9/9 P***(39 It)* /3 8-/? 3 Pes 3PS914 l l 1 l I { 1 l l i l l l I ev \\ \\ Data taken from roc s' . dance wi applicable CB&l QA Manual. / /d!78 E CHKD/ / CBI Shop QA

  1. M Date g

DATE l { ] Contract No. t to, 30 P.eviewed (for material covered by code): / W Authorized Inspector (Shoo) /d DatW w / 3-6 33(o st.h of -

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  • 4 3t!n ?.0.00 7 M

Page 12 0f 39 I hl.b3 b. h$/. C.TilFIE0' TEST RC.10n7; Date:;g/jgf71, F lCtilt2GD c ,j ~ tilla nogistor flo. 00r.727, .o I j g* 2 g.5 i Fill 3 7' D - 'as / 1

?1CIFICAT10f1S HMH Drt.ulng flo. ~ b! 8f, 3

is g-,, } ; %g . N' 3Y l '-- ., -T 3 b f.g 50131 i t, E .py ---]T g h Y ' G. :

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.& J 1 Pster19 tion of Itcm s. s ualght and,..',' ( .llato r ial Piecen [ piispe \\y, S.!.:o Lanoth ~1 3610 LDS j i .I v. I Y' gl 208 'n/L 30l> $TAlt!LISS STEEL' 4 .x1x3/16 l

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.Tonslic ctrerach Yleid ength Elonga/on R of A. 11ardness l y V / / J-P'. J

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't.. n an bc.,l in 405... i 6 a _ Uo hmby certliy th,'t the abovo fl ured ara correct is contr.ined in tha rcur>ls of this yM t t g cc. pony. p ~ W [. I EddOlif. ' Dy._i '$ LT '/ llam.? cnd Titic

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  1. N O'*

"9 N * ,11400 W. ADDISoti STRElf ATTACHMENT D Address:. fFANF.IlN PAPK, II.L I,1.'Ol5 60131 Page 13 0f 39 e/o 4 HHH York Order No. ? Mao 675 Purchase Order No. . Weight and ..-..'. Description of item ~ Pieces Shape Sire Leryth Haterial ~ l 33f5 LM tI PCS CI'.t f 81.r L ?. x I x 3/16 19' I,/L 30's ; Trim.ELS ETELL ')20 LDS 11 PC', CHANf4L 3 x 1 3/4 s J/l6 17 -2!e 9/L 309,STilhLESS STEEL a. Chemical Analysis s Lil5 PCS 1 h0 CR NI Si HN i P CU Heat Number C S

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. 5) IMI ,730 51 0I .02I j.073 .30 29 2 Tl660 i-i

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.57 1.6 ' 72 I .v // t Mechanical Propert ies Heat Number Tensile Strength YleidJtrength Elongtion RCJ/A Hardness 30660 ?0.850# 55l1u0 tW .46 g 30549 36,400 43,750 M.S 69 v/ 9 ,v 40073 35.350 40,200 52.5 71 We bareby certify that the above figures are correct as contained in the records f th \\ s_.'.'- t' y ~ company. C.] k. Y m.,.a,- lqr 'U y, '........,,. ' '.. Name and T,it.le-Fora 14. - t ~....

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  • 8 b 4

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Material T pes' MATERI AL HEAT

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yl Piece-3 g N eo-3 g g Mark 3 z Material Host No, fg z Meterial Heat No. n Mark } Yk 0l f33l$. $ EMW Yi07 Affl Calculation L 001337 Project No. 10248-012 / 89. I J2pc r. go sfg 9 A~ITACHMENT D

  1. 3 Y' A N Pf 11'.

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4*499 $96 Ovsn. Un YEsr A6a / l jf 2.- 8 Pc.s 46489 39*8 B Pe 4. Go dA 9 3fE /os W L Eec rear s.ed 4.99 1 2.re s 4s484 I.99- /s do48 4 s ree 3i F-f.s. narL Lsa re sr-n ssst / 39-a t t-pes. Godt? = l $=) L 40 PC s. 40429 BY \\ \\ cnw / r~ E*Y $o $ ~ W l 5 b $ $ ' sl7l?f f D.t. f a ~ yh ' 4 DATE / No. 8 k Contract No. Reviewed (tor material covered by code): Authortred Inspectotl"%*e' / Date_ h33h Sh 2 of _

Calculation L.001337 oo as cav 41a Project No. 10248 012 Material Types: MATE RI Al. HEAT

1. Welded Asserablies ATTACHMENT D NEER SHEET

" a.' Page 16 0f 39 R. / o n oe Piece-3 Piece-i ,,fj Mark jE Material Heat No. I }E Meterial Heat No. Mark 295 ins d. L ene res e ass y' 39 2 von Leu re,r msv 3 9-18 z ec., So384 _{} 9 - I t 1As 40079 s

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oof as Etvd 78 Materia 1 Types: 6 MATERI AL HEAT 1 Welded Assemblies NUMBER SHEET

2. Non-Welded Code Matt.
3. Non Code Matt.

Piece. 3 g Piece. 1: g fg g Mark jE Material Heat No. i Mark ]2 Meterial Host No. 8& 4 EMx 'Tr#r g ss/ calculation L 001337 Project No. 10248-012 C Si-/6 Jp3g4 ATTACHMENT D k 33 YO489 Page 17 Of 39 A/c / 9-/7 d ac,7 9 3

  1. 34-3 J/t V 39 4 I<V

/ 39-34 doc 89 ' /31-3r 4s489 4-J 7 b_K Date op DATE / 6 Contract No. No. 8 Y [ Reviewed (for material covered by code): 'M Dm 9 73- 033 $ Sh I of _ Authorized inspector (Shop)

Cc!culation L 001337 Project No. 10248-012 ATTACHMENT D SUPPLEMENTAL

SUMMARY

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N A Materti Types: oo,,, MATERI AL HEAT NUMBER SHEET

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3, Non Code Matt. sg ( Piece-g g Piece-fg Mark, a Material Heat No, Merk Meterief Heat No. .37-[8 b [enk 76TT A s c 'V Calculation L 0013M Project No.10248 012 HT

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oo t86 ctv4 78 ~. Material Types

  • MATE Ftl AL HE AT
1. Welded disemblies NUMBER SHEET
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3 Non (' ode Matt. }I sl Piece. Piece-Material Heat No. }( h I Material Heat No, Mark Mark 89D 0 /uo W z rAr. rrsr a s,V calcutation L 001337

    1. &8 4eO74 Project No. 10248 012

/$9,23 ATTACllMENT D ~ /3 f. 2-r (v/Vo 4eo 7 4 page 21 or 39 R4 lA9-3 !!fV $ J f-Ef D 4. A t$ l'c ?> ,01E-E enti t enn re s r n e s 4' (39-3o w i[;eA'4% /39-2 9 ca, coo n l34-3 sne J r- ./31-4 piu tY /[Io 74 CH D Date CB Sho ~~ DATE 4 Contract No. No. 4 T._ n Rwiewed (for material covered by code): ll ((3' d 3 3[a W Sh E of - Authorized inspector (Shoo) 0

MJ. SIT'l<uSUltANLL DOCUHbliT TNDEY, s Sp cification % 5 9 4. Q Ll, Page of_ File Number

6. A Docut..ont Title d M r A's 8

Calculation L.001337 2~ [Nc$Qt3l8 032 I02 Contractor Name CB 1 6 Page 22 Of 39 (t/e Document Li, sting: C MT As e ~ Engineer Signoff Paper Count TO

f/lDlb!. l'.iU U O h !a200 Lehigh Avenue. Morion Grove,dooos3 Project No.102.is.'0l ~ WR P. O. # C,3 4, c/g 13121966-0000 ATTACllMENT D Pase 3 009 R/e-M b /0 JR NUMBER \\TE SHIPPED 16 /4V ERTIFIED TEST REPORT Datet 10/21/784 HHH Reglster No.005743 'EClflCATIONS A fTm A -9.~/ y, [M bD hu HMH Drawing No. 3Y l% x spo e igm HHH Work Orher No. i ..... g y ht..... Weight and

  • Descript lon of item Pieces Shape Size Length Haterial 3,320 Los 25 PCS CHANNEL 3xl 3/8x3/16" R/L 304 STAINLESS STEEL 4

SPEC: ASTil A 276 5 ,'C[igmic3,An9lysis 1 Y,., 1 Heat Number C P 5'C U ' N02' , C[ ' Ni St HH 40489 .051 021,' 030' .)4 709 '18'.56 9.96 .56

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5 ,,Hechanical Propert les' N Heat Number Tensilb Strength Yielf Strength Elongation R of A... Hardness r 10489 89, n0 51,600 50.0 68.0 r / 4 We hereby certify that the above figures are correct as contained in the records of this company. irm 74 ,/ ~ h: 1' n&l N.C. NAM 6M By Name'and TltIe c s,. .

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  • 16 8200 Lebegh Avenu

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  • Descriptlon of item

- - We i g h t and - -- -- - Pieces Shape Sire Leryt h Material j 3)l5 Lab tsl PCL Cf.t fil.r ( p, 3 l x,t/l6 19' l./L 304 31/141t$5 !TELL 8 'J/9 t 03 il PCS CH A'itli l 3xi 1/1 s,t/16

1. 21s !!/L 30',i, STI INLET $ STEEL.

Chemical Analysis L85 i Heat Number C 5 p P CU 1 NO CR HI 58 MN 0d .0?I /.073 .30 2!1 Id. 9.),k . E). IMI 2/30 C MO / / / / I ~ hup, l'.50 ~. I6 ~ l'. 60Y iS5' ~ ~ 0 U1' 37 .b7 [ I. 01I l .v vp w. 0iI .01d-011 70 19 1F.55 9.63 .57

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-f s 40079 Hechanical Properties Heat Number Tensile Strength Yle id,St rengt h Elonpallon RoJA Hardness I i ~ 30 % 0 ?0.85 W 55l100 kV . b lM / / / Y ,l l/ l / Vl \\ 30$49 86,400 43,750 46.8, , 69 / ,j 57.5, 71 ' 85,3(0 40,200 40073 as contalned in the records f th We hereby certify that the above figures are correct ' \\-vM ( C;k% p.,...;, J L) h- + company. ~. ,7 Nam and Title',.;.,. l' /' r n - 7 4. '..

- - - - ~ ____ _._ _ _ __ n Calcui: tion L.001337 ~"~~~~'~~ , h Pro}ect No. 10248 012 "' ~~ ' 7"~., +.',,{... d,' f. ($g Hl.'.. ."9

t ATTACHMENT D.

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p i a =h masoca-tcoo 9 .e cenTtrito Trti ptPont pate: 8/8/73 letH Aegister No. 002151-C C:storer! INWJ11ntAL $ERVICC CGT(R 155 Ethf sitEEY tHH orawing No. car 44l0GE, M SS. 02141 Address:

(30W
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HHH Work Order No. harch:se Or(cr No.515536 0 Description of lters / Weight and Length Heterial '$lic .Piccer Eh m ~ _ - -= ~' _~ 34 FC5 CHAMIL 3 m 143/8 x }/16" 18/24' 3c4 $TAlWLESS STEEL 3170 LDS ~ o SPEC ASHE 5A 479 Chemical Analysis P CU 'HO CR Ni 51 HN C0 f. Heat Hmber C, ~ 304ca 065' 020 " 022I .32 .35 16.73 10.43 5 45 ' 1 52 ' 10.2?[ 37' l.8) E I .37 .31 18.22 7 -303$4 067 021 .0?.3 -ww w-Hechanical Propertle$ ~ Hoat Nutcar Tentile $trenoth Yield $trengt,h $ florf at ion R of A-liardness PCS LOS =. ..3%o3 92.000 ' 52.200 ', 50.8 ' 71.5 20 185t i / I / / 30304 91.403 ' 5I.500 51.3< 78.7 < 14 iU' 4. --3--.,,-,_,-_-m. ,--,-.----,.------,v-me r,,, -r .---.+.v---.----..---.--.--.,.---~-,.--.m.-- ---4

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Material Types: Ofel CEv8'8 MATERI At. HE AT

1. Welded Assemblies
2. N: rewelded Code Matt.

NUMBER SHEET

3. N'n Code Matt.

ag Piece-3g Mark jz Material Heat No. }# ag Piece-3g Mark j2 Meterial Heat No. }; bSA lo da$l$.

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TPsT /951 / _ Calculation L-001337 Project No. l02.ts.012 l 32-f 3 opes Ctse79 __ ATTACllMENT D lc Page 27 0(39 R 7.02-2 /e f C$. doo 7 4 /32-3 po r ts JR 32-Q. le PC $ j I i I l 1 I l i i 1 !av \\ \\ C$s$o?$ k h,e$ ',"* /2b>//7V $ C"* ! l o t, DATEl l ah' / No. 3 E Gun .M Contract No. t. n.csu ,a., _ Reviewed (for material covered by codel: -or-.oe.t.r..o, ~ /

P' MATERI AL HEAT ' *f.' ed tsembli:t NUMBER SHEET

2. Nin Welded Code Matt.
3. N n C*'e Matt.

s{ Piece-3g ],. Piece-3g f;g Mark jz Material Hut No. 'Aark gz Material Heat No. $E O lAfW.

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< ib AY _ Calculation L-001331 Project No. 10248 012 dagf79 / gz _ g* 7fu ATTACllMENT D y32 - /O 40489 Page 28 0f 39 R/0 g ~ z/o l h0C / A :;$ W. L f A n' y 2 s7* A$s4 l$2 G 1 Pcs 4048cf V32 - li tra 40489 l 32O tass / L ta se 7'E s r* A ssV V32-8 ans doa s e /32 - /2 1tc 46489 32 E /AnW. L E A u: rest RosJ zu 4o489 /32 9 l32 13 40d89 ne s I I e 1 i l l 7 $Ysn' Y ~~ a Date /No!)P b C" [ DATEl Contract No. No.82 Reviewed (for material covered by code): k 0g N_

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9 Mat:rlal Types: so tal ctv 4 ti (" [V

1. Welded Assemtlies MATERI AL HEAT t

NUMBER SHEET

2. N:n Welded Code Matt.
3. N *n Code Matt.

gf, Piace-3g g# Piece. 5 g g Mark h2 Material Hast No. fy Mark jz Material Heat No, a ~ 32 F isg e 7ssr ges/ caiculation t.00:337 ll Pr ject No. 10218-012 ll '/ 32 7 2ter. 4 0 4 8 (f ATTACilMENT D 2res 4a1B9 Page 29 Of 39 A./o l4 /3 2. - /4 l l I t l l l t l i l l l l I I ata to an om reco F 'th icable CB&l QA Manual. 9 7 "' tg.3' 'DATE I / / A l e &==a (- F Contract No. No. Reviewed (for materlat covered by codel: n.osat ss a o, _ .. so,use i_,o,issoo,

00R NSWtk 1 "'r ....v. % .y-W:. \\ 9 _4 . Morton cro.nle0063 ITT Hcrpe PhVe!n"*u c -i -

  • ]l8200 Lehigh Avenui g g 600

$ 7' th ' A - b 3121966-8000 T'soi./ ss da ,gh ITEM,_ ~ , ORT Date: 10/21/74 ' M /V f/6, HMH Register No.005743 p. I L 001337 ERTIFIED TEST _R :P 3.' " ' 7 .,.,m. nnfaq 10248 01~' " ### "9 N0' hh .EN D t Calculation L-001337 g,*! Project No. 10248 012 ATTACllMENT D HMH Drawing No. U# HHH Vork Order No. Offl Page 30 0f 39 HHH Work. Order No. Item Longth Materlal -....Descrlptlon of item 3 8/L 304 STAINLESS STEEL -]t/16 19' l*/l 3n4 STtlNL.E55 !TELL

i y16 1'-74 B/L 30',i, STt INl.E55 ' STE EL 1

i O,. ..s".p ; sl yy Ni Chemical Analysis s 6 9.96 .56

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RofA, Hardness

'\\ 68*0 55lM0 M' M / r -, l / Y f l el 48 ., 69 y ) 43.750,j 52 3 " 71 } onteined in the records of this 40.200 'U*d8u f gores are correct a contalmd,In the records f t,h .g 6 ~w \\ '.WP& Y:.J 4' /7, gy. '.~- jo .'I'; Name,and T3tles, 2.. ,,b.

ut.Aa wwa. . w v. u.e.n.v.. ...............~... )UR P. u. # f i 3 D f' ~ DN~ b l0 JR NUMBER NT Oate: 10/21/74 16 /W N "* * '. TE s \\TE SHIPPED I HHH Register No 005743 'ECIFICATIONS A ('Tm A -9~/ ip caicuistion t.00:337 EM g 36Y f d Project No. 10248 012 MHDrawingNo. 13 ArrACllMENT D }y f 3 [ Pr) Page 31 Of 39 A/c. HHH Work Order No. l .., b Q - h.... s " Descript ion of item Weight and Pieces Shape Sire Length Haterial 3,320 L85 ~ 25 PCS CHANNEL 3xl 3/8x3/16" R/L 304 STAINLESS STEEL f t SPEC: ASTN A 276 - n. n. fi.,..,' Cpemical. A,nsyj ys t s ..w Heat Number C S P TCU M0- . C R' NI , Si HH ~ 40489 051 021,' 030'.h. 709. *18.56 9.96 .56 f 55 i 'y. * ' ". 3 _, I ge..t. .e . (. . >... 5

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,Hechanleal Propert les e, Heat Number Tensilb St rength Ylel[ Strength Elongation R of A... Hardness " 40489 89.200 '51.600 50.0 68.0 s / 4 We hereby certify that the above figures are correct as contained in the records of this l company. h ~ '%.eWl N.C. Ma tV A su g w .' y ,/ Name'and iltIe irm 74 / 'nv . <,gy v

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  • a Project No. 10248 012 h
  • ATTACilMENT D

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Y U*IN RR. Y D ,4 ~ g73po y,g e 4 g 4 e, ').... ' W. 'A r'. & T t' LOCATION 0- C# ENGINEERING NO. PIECES SUPPLIE R'S ID NO. PIECE MARK SERI AL NO. FABRICATED ff/YN //YIt/ ?-/d bdb-a l / /1A '-3 / .A &/ d s / 409*2 /= W W 6c9-3 / 1-J /71 9.)S't,.f .'_ : 2 /tt/,5 N-/Y 7//. 2 6 /s - w 'i)f-y' A 16 d 7/9-V -? /612 7.23. / L WM/ In -l9 fin 7 Vs f /4 Y 73/-y /. 3 3 ~ 7 3/ '( / 74/-Y I.V V _K4 nM in.i f r/W tri V / 153-V / 13/-// /V Y 100 jo J. v' 'Y 75/-/o J-Y ' ~ > ' ' liG 7 /- v' V \\ WKY/ I /M-/9 - 7]f' )17-{ / / ' " ^ 1V.n/ (s 93.;to / 'l 7/.i / 927-I ' ) 217.f 7 n17-Il I / XA U914 19 0 / S b li 1/5C 6' / 'hiSNil '. In /4 fil14 b93 IF i M3/V / 35 -N / //o h' $1-d ) pj3-/ ~l 80 883 "EV DEC 78 k Stenderd 607 3-1 fee inetruct6ons on using th6s f orm.

~._ _ _ __ _.._. _______;_ Cticulation L-001337 Project No. 10218 012 SUPPLEMENTAL

SUMMARY

SHEET fACHENT DMa lage 35 0f 39 FOR MATER'l AL VERIFICATION 60 0 8 3 REV il.f f CONTRACT NO. ! ' Y<$ 5M LOCATION ENGINEERING NO. PIECES ITEMID PIECE MARK SERIAL NO. FABRICATED m -t f w>-8 214 / / f&WY / / . = - - ///:fl ? / J-> / / 96W 1/7-/? l 2 17 /3 ' f / 1 77-4 / 293-/ / M9-Y ' / 293 f / f .293 -// / / ///-/2 594 3 I / i / 596-Y 0 10/J o d75o in. t; gr.i/ 7/>.) y'f w -3 > </ 7/Q/ /(o 7/6.2 / 7ac / /6 z2o 2 2 MM/ /d DV2 7 w1-5 / PW3 f., I

Calculation L-001337 Project No. 10248-012 ATTACllMENT D SUPPLEMENTAL

SUMMARY

SHEET Page 36 0(39 g/* 4 FOR MATERIAL VERIFICATION ( 604f8 AEVil.fi 3b LOCATION OY/ CONTRACT NO. ENGINEERING NO. PIECES ITEMID PIECE MARK SERI AL NO. FABRICATED lff/76 1/-A /s-f Jdr-3 / 171-s / W-5*~ / AV'-V / /dr.t / /7f-J / d4 NVf 7 />f }A-J '/ WI-& / J-10 MU-8 7 434-A / V TTl 90 7/-A lo?-/o ED6-2 / l 101 10 5a rt-8 i /0 4-10 68(o-3 Y /on-to 68 % 3 7 W3A, 3 __ 42 1/ tho./> 319 13 /,s, w ' 29)-// / b93-//f p.93./ ' 29}-a4 f1 N >f7-/// >43 -/t</ n d11/ / yD.,f/ n

_. - - -. _ _ - - -. - ~ - - Calculation L 001337 k . N Project No. 10248 012 ATTACilMENT D \\ SUPPLEMENTAL

SUMMARY

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Attachment K Referonces

References 1. NRC Inspection Report 50 373/78 33, dated January 19,1979 2. L. O. DelGeorge (Comed) letter to A. Schwencer (NRC), *LaSalle County Station, Units 1 and 2, Containment Leak Chase Channels," dated August 10,1981 3. L. O. DelGeorge (Comed) letter to A. Schwencer (NRC), 'LaSalle County Station, Units 1 and 2, Supplemental Information Concoming Containment Leak Chase Channels,' dated September 1,1981 4. L. O. DelGeorge (Comed) letter to A. Schwencer (NRC), *LaSalle County Station, Units 1 and 2, Containment Leak Chase Channels," dated October 1,1981 5. NRC Inspection Report 50 373/8128, dated November 6,1981 6. S. V. Athavale (NRC) letter to Donald F. Schnell (Union Electric Company), 'Containtnent Liner Leak Chase Channel Venting Callaway Plant Unit No.1 (TAC No. 72750),* dated March 14,1990 7. Stephen P. Sands (NRC) letter to Thomas J. Kovach (Comed), " Safety Evaluation of Containment Leak Chase Channels Byron, Unit Nos.1 and 2, Braldwood, Unit Nos.1 and 2 (TAC Nos. 72569, 73570,66476, and 66477)," dated May 17,1990 8. Licensee Event Report (LER) 50 373/97 030 00, dated September 17.1997 ,}}

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