Text

C-CSS-099.20-063, Rev 1, Shield Building Design Calculation. Part 2 of 7
	ML15280A310
Person / Time
Site:	Davis Besse
Issue date:	09/03/2014
From:	; FirstEnergy Nuclear Operating Co
To:	; Advisory Committee on Reactor Safeguards
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ML15280A293	List: L-15-310, C-CSS-099.20-069, Rev 0, Shield Building Laminar Cracking Limits; ML15280A287; ML15280A303; ML15280A304; ML15280A305; ML15280A306; ML15280A308; ML15280A309; ML15280A310; ML15280A311;
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	L-15-310, TAC ME4640 C-CSS-099.20-063, Rev 1
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Attachment A:

Evaluation of the Seismic Analysis Loading Considering the Observed Laminar Cracking of the Shield Building Calc. No:

Sheet No:

Sheet Rev.:

C-CSS-099 1

of 58 001

.20-063, Rev. 001 Attachment A:

Evaluation of the Seismic Analysis Loading Considering the Observed Laminar Cracking of the Shield Building List of Sections Sections Al.

Introduction A2.

References A3.

Laminar concrete crack map A4.

Finite element analysis A5.

Discussion on as-built condition A6.

Summary A7.

Conclusion A8.

ANSYS input and outputs Page no.

2 2

2 5

15 16 17 18

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

2 of 58 Building Sheet Rev.:

001 1.

Introduction During the concrete removal in the Shield Building (SB) for 2011 Reactor Vessel Closure Head (RCVH) replacement, laminar concrete cracks were observed in the architectural flute shoulders, spring

line, and two steam line penetration areas along the Outer Face (OF) reinforcements layer (Ref. A6).

The entire SB wall has been scanned using Impulse-Response (IR) testing, and cracking locations have been reported (Ref. A5).

During inspections of the Shield Building as part of Long-Term Monitoring of this condition, it was determined that the laminar cracking condition had propagated in several shoulder regions of the structure (Ref. A6).

The purpose of this attachment is to examine the validity of using the original seismic analysis results for the existing SB with the observed laminar concrete cracks.

Note that seismic analysis results will be the direct loading inputs for the new design calculation, so this attachment focuses on verifying that the original seismic analysis loading is still acceptable for the existing SB with the laminar cracks.

For this propose, three different Finite Element (FE) stick models with different levels of cracking and effective flutes, are created and their results (i.e.,

natural frequencies and mode shapes) are then compared with the available original analysis results (See Section 4).

Also, an as-built condition previously reported in Ref. A4 is discussed in Section 6.

It should be noted that these FE models are similar to the stick model used in the original SB design with the same methodology and the same modeling parameters with only one exception that the cross sectional properties are updated to account for the effect of different levels of the laminar cracking to assess its impact on the dynamic characteristics of the Shield Building.

All relevant ANSYS inputs and outputs are provided in Section 8.

2.

References Al - Updated Safety Analysis Report (USAR) for Davis-Besse Nuclear Power Station No.

1, Rev. 29 A2 - Davis-Besse Nuclear Power Station Unit 1 Design Criteria Manual, Rev. 25 A3 -Calculation No. VS01/B01-03, Seismic Analysis of the Containment Structures, Rev. 0 (10/04/1976)

A4 - Calculation No. VS11/B01-01, Shield Building Seismic Analysis, Rev. 1 (06/08/1981)

A5 - Bechtel Document No. 25593-000-GOJ-GEG-00001, Shield Building Exterior Elevation IR Test Data Through 24 July 2012, Rev. 0 A6 - FENOC Condition Report 2013-14097: Shield Building Laminar Crack extends A7 - FENOC Drawing C-111B, Sheet 1, Shield Building Continued Data for Core Bore Inspections 3.

Laminar concrete crack map Figure Al shows the laminar concrete crack map of the SB wall scanned/detected by using Impulse Response (IR) testing (Ref. A5), where cracked area are marked as pink while non-cracked areas are presented as grey.

It can be seen that most of the cracks occur at the architectural

flutes, and not all the flutes are cracked (some flutes @

Shoulders 1,

14, 15, & 16 are still intact and not cracked in some elevations).

For a further analysis purpose, this crack map has been divided into 4 regions with different levels of cracks.

See Section 4 for details.

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

3 of 58 Building Sheet Rev.:

001 During Long-Term Monitoring inspections of this condition during 2013, it was determined that the laminar cracking condition had propagated in several shoulder regions of the structure. The propagation has extended previously existing cracks in the plane of the outer main steel reinforcement mat of the building.

While the cracks propagated into previously un-cracked areas, the width of the cracks remains within previously observed crack widths (Ref A6, A7).

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 4 of 58 001 Elevation (ft)

Figure Al.

The IR test results (Ref. A5) and four separate regions of laminar cracking considered

Attachment A:

Evaluation of the Seismic Analysis Loading Calc.

No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 5 of 58 001 4.

Finite element analysis Figure A2 shows the Finite Element (FE) model used in the original seismic analysis and design of the SB.

As shown in this figure, the SB was modeled as a simple cantilever-type beam structure consisting of 13 beam elements and 14 nodes from EL 565' to EL 812.75'.

In this analysis, the same methodology and the same modeling parameters are used except for the sectional properties.

The sectional properties of each beam are calculated considering different levels of cracks in the following three different FE models:

Model-1:

No laminar cracking The original seismic analysis FE model is not available, so this model becomes the baseline of the original FEA results and verifies the FE models with different cracking levels developed in this attachment.

Model-2:

Laminar cracking in all flutes/shoulders Not all the flutes/shoulders are cracked, but they are conservatively assumed to have the laminar cracking.

Model-3:

Laminar cracking based on the crack map Four different regions with different cracking levels are considered, i.e. more accurate than Model-2.

'.SHIELD. SLOG.,

TOPOF AUXILIARY BUILDING EL.S6i>0' CONTAINMENT PURGE INLET LINE 4 MAIN STEAM LINE £Lj646'-6"i EL646-6'

.*c ELt>43-0 if<L EQUIPMENT HATCH-EL.65B'-3' i FUEL LRANS£ta TUBES £L.570^'

E-812-9 I

EL 660-0" fL.MO'-O" Mass point numb>>r

- Mr*

number

- Member numtw MATHEMATICAL MODEL FOR SHIELD BUILDING 4

HGURE I

Figure A2.

The Finite Element (FE) model used in the original SB seismic analysis (excerpted from Ref. A3)

Attachment A:

Evaluation of the Seismic Analysis Loading Considering the Observed Laminar Cracking of the Shield Building Calc. No:

C-CSS-099.20-063, Rev. 001 Sheet No:

6 of 58 Sheet Rev.:

001 Davis Besse SB stick FE modeling parameters Number of nodes:

Nnode' =

14 Number of members:

>>eimnt :=

13 ORIGIN* :=

1 mwmww i :=

1.. Xnode

-Nelmnt Sectional properties:

Rin:= 69.5ft (Inner face radius)

Rour=72ft (Outer face radius)

= 21.456ft""

(Flute cross section area, VS01/B1-3)

= 1110.773ft2 (SB wall cross section area, VS01/B1-3)

Second moment of inertia of SB:

A^.*- 1110.773ft2

%<-21.456ft2 Iw<-2782283.312t4 R;<<<<- 69.5ft (VS01/B1-3)

Note that the same methodology in the original seismic analysis calc (VS01/B1-3) is utilized to calculate the 2nd moment of inertia of the flute (i.e., using an equivalent radius considering flute areas) con :=

150pcf fc:=4000psi Ec used:= 524751^

Gc used:= 20990Cksf (VS01/B1-3)

Number of flutes considered in the onginal seismic analysis calc (VS01/B1-3):

EL E L

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 7 of 58 001 Num:=

(Node #)

Node

=

(Elev)

Elev.

(# Of Fit)

(W. kip) 1 3

4 6

7 S

9 10 11 12 13 14 L4 13 1C 9

S 6

J 4

3 i

1 812.75ft SOlft 774.5ft 74Sft "20ft 692 ft 660ft 646.5ft 643ft 609ft 603 ft 5S9.5ft 570.75ft 565 ft u

i 1

1

=

4 4

I i

j

]

4035kia

-PSSTkip 5102 kip 5244 kip 53S6kip 5771.kip 4290 kip 1526 kip 3311km 3526kip 1697 km 2791 kip 2120-lop 0-kip (Effect. # of Fit after crack)

FLc:=

Note that the effective number of flutes after the crack is determined based on the crack map.

Model-1:

No carck (ori<

Ax (ft2):

Ay (ft2):

Kft*):

^l 1-13 12 10 q

3 7

5 5

-i 2

i

\\

H<?v

=

i S12.75 r

1 774.5

743, 692 6:'"

646.5 c43 6C 9 603 539.5 5/0.75 565 SB desian) 2 v_f.'n

^3-

ft 1554.0 1282.4 1232.4 1232.4 1232.4 1196.6 1196.6 1175.1 1175.1 1153.7 1153.7 1153.7 0.0

ft-

= 1554ft2 Ax14 2991468ft4 I14 :=

777.0 641.2 641.2 641,2 641,2 641.2 598.3 598.3 587.6 537,6 576.3 576.3 0.0 ft-2 Oft4 2.991-106 3.228-106 3.228-106 3^28-106 3.223-106 3.228-106 3.004'106 3.004-106 2.948*106 2.9-3-106 2.392'106 2.892-106 2.392' 106 0

4 w

=

4035 4637 5102 5244 5386 c

4290 1526 3526

!-': 7 275:

2120 0

kip

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 8 of 58 001 Model-2:

Cracks in all flutes (not all the flutes are cracked, conservative)

It is assumed that all the flutes are cracked, so the concrete cross section of all flutes is excluded.

This is simple and conservative assumption since not all the flutes are cracked.

Ax (ft*):

Ay (ft*):

I (ft*):

>."oi ode

=

11 10 As.

Elev 5

=

1 _. 75 8C1 774,5 743 720 6? 2 660 546.5 643 609 603 539.5 70.75 1

1554ft2 (Zero flutes for the entire SB wall)

= 2991468ft 0ft 1554.G 1110.8 me L110.fi me 1110.8 m:

3 1110.3 1110.8 in::

1110.8 1110.8 1110.8 c

777 555 555 555 555 555 555 555 555 555 555 555 555

,0 A

A A

4 4

ft" 2.991 10<<

2.781-106 2.781106 2.731 106 2.781-106 2.781-106 2.781'IC*

2.781-106 2.781-106 2.781-106 2.781-106 2Jr;i 10s 2.-31 106 0

ft 4035 4687 5102 52-4 5336 5771 4290 1526 3311 3526 1697 2791 2120 kip

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 9 of 58 001 Model-3:

Cracks in some flutes and elsewhere (based on the crack map, more accurate)

Based on the crack map, the SB wall is divided into the following 4 regions having different levels of cracks and/or different effective numbers of flutes.

Region-1 (EL 801.0 - 812.75):

No crack Region-2 (EL 774.5 - 801.0):

70% of the area is cracked @ OF rebar layer Reqion-3 (EL 643.0 - 774.5):

20% of the area is cracked @ OF rebar layer Region-4 (EL 565.0 -643.0):

No crack Cross sections are linearly prorated by using a factor, Fck. based on the crack map.

Fck..

= 0%

(Regk>n-1)

Fck,

= 70%

j.= 3.8 j

=9.. 14 Fck.

= 20K Fct

= 0%

Fct (Region-2)

(Region-3)

(Region-4)

Reductions of the sectional area and the 2nd moment of inertia due to the crack aiong the OF rebar layer AA:=

cc Rout" cc 2

2';

Aw~ Acc AA=138.812-ft" cc 3in cc AI= 3.597>: 105-ft4 Nodej 14 13 12 10 9

n o

7 6

5 4

3 2

I

Elev

=

S12.75 301 774.5 74S 720 692 660 54 5.:

643 609 503 5S9.5 570.75 565 ft 0

s s

8 8

B 4

4 3

3 2

2 2

0 (original # of flutes)

FLc

=

(Effective # of flutes,

where no crack)

Attachment A:

Evaluation of the Seismic Analysis Loading Calc.

No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 10 of 58 001 Ax (ft2):

Ay (ft*):

I (ft-):

Node

=

14 11

^ Afl - Fcl^ AA Ax.

a<-FLc.

Bev

=

312."5 501 774.5 720 692 560 646.5 543 609 503 570.75 Ax

=

1554.0 1056.5 1125.9 1125.9 1125.9 1125.9 1104.:

1104.5 1153.7 1153,7 L153.7 1153.7 1153.7 0.0 ft*

=

1554ft" Oft"

= 2991465ft Ay =

-i 777,0 52-3.3 563.0 563.0 563.0 563.0 552.2 552.2 576.8 575.3 575.S 576.S 576.8 0.0 ft" 2.991 106 2.640-106 2.320-106 2.320-106 2.820-106 2*820'106 2.765-106 2.765-106 2.392-106 2.392-S/

2.392-106 2.392-10s 2.892'1O6 0.000 ft 1-4035 46S7 5102 5244 5335 5771

-290 1526 3311 3525 1597 2791 2120 0

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

11 of 58 Building Sheet Rev.:

001 The above three FE stick models have been simulated using ANSYS version 13.0, and their results are then compared with the available original seismic analysis results.

Note that only the natural frequencies and mode shapes in the lateral direction are available from the original seismic analysis calculation as shown in Figure A3, so Model-1 represents the original SB design condition and is considered as a reference/baseline for comparing mode shapes from Models-2 & -3.

Table Al shows the natural frequencies and Mass Participation Factors (MPFs) calculated from the three FE models and the natural frequencies from the original seismic analysis, and the corresponding mode shapes are also presented in Figure A4.

The FEA results and comparisons are summarized as follows:

The 1st FE model (no crack) generates the same natural frequencies as the original ones.

The maximum natural frequency difference between Model-1 and the original one is calculated as 0.3% at the 4th mode.

For the first 2 modes, the calculated natural frequencies are 2.97Hz and 10.55HZ, i.e. the same and 0.2% different than the original natural frequencies (2.97Hz and 10.52Hz).

Note that the sum of MPFs for the first two modes is more than 90% of the total effective mass, which means that the first two modes have the largest contributions to the dynamic behaviors of the SB.

Also, the corresponding mode shapes for the first four modes are similar to those of the original model (See Figures A3 & A4).

The 2nd FE model (conservative approach) generates similar natural frequencies as the original ones.

The maximum natural frequency difference is calculated as 5.2%

for the 3rd mode.

The calculated natural frequencies are generally smaller than natural frequencies from the original

model, which results from the reduction of the stiffness by excluding the concrete cross sections for all flutes.

Similar to the 1st FEA results, the sum of MPFs for the first two modes is calculated as about 90%

of the total effective

mass, and the corresponding mode shapes are same as the 1st FEA results as shown in Figure A4.

The 3rd FE model (based on the actual crack

map, so considered as more accurate) also generates natural frequencies similar to the original ones.

The maximum natural frequency difference is calculated as 4.8% for the 3rd mode.

The same or similar FEA results (i.e., MPFs and mode shapes) are obtained comparing to the 1st and 2nd FE models.

The comparison between the mode shapes for all three FE models shows very similar shapes in general, with only minor differences in the 3rd and 4th modes in Region-3, where the laminar cracking is present.

The additional crack areas do not affect seismic models 1

or 2.

Seismic model 1

evaluates the un-cracked structure.

All of the identified crack propagation is located within the shoulder areas of the Shield Building.

Seismic model 2

considers all 16 shoulders to be completely cracked.

Therefore, the newly identified crack propagation does not affect either of these models.

o The 3rd seismic model considered cracking based on the 2012 crack map. Based on the locations of the crack propagation, the affect on the existing model is as follows; o

REGION 1

Region 1 consists of Node 14, which contains the mass of the Shield Building dome. This region does not contain any flute/shoulders or any cracking in this portion of the structure.

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 12 of 58 001 o

REGION 2

Region 2

consists of Nodes 12 and 13 contain 8 flutes (or 16 shoulders). The model for this region was based on 70% of the area as being cracked, per Sheet 8 of Attachment A. Within this Region, an area of propagation has been identified on Shoulder 15 at Elevation 777. The existing model considers that 70% of this region is cracked. This model remains appropriate based on the previous crack map (i.e 70% cracked value is conservative based on map).

o REGION 3

Region 3

consists of Nodes 6 through 11 contain 8 flutes (or 16 shoulders). Two flutes were considered to be un-cracked, based on minor cracking that was considered to be negligible for this evaluation.

In Nodes 7 & 8 only one flute was considered to be un-cracked (2 shoulders).

Within this

Region, areas of propagation were identified on Shoulders 4,

5, 7,

and 15.

The existing model considers that 20% of this region is cracked.

This model remains appropriate based on the previous crack map, and percentage considered cracked.

o REGION 4

Region 4

consists of Nodes 1

through 5.

This region contains a

varying number of flutes depending on the elevation. The only node that was modeled with any previous cracking was Node 5. Node 5 consists of 3 flute areas (6 Shoulders).

In Node 5, 2 Shoulders were considered cracked.

Within this

Region, an area of propagation has been identified on Shoulder 13 at Elevation 633. The existing model for Region 4 remains acceptable based on the previous crack map, and percentage considered cracked.

Conclusion As discussed above, the discovery of crack propagation in the Shield Building wall does not adversely affect the existing analysis for the laminar cracking condition.

Based on the above discussion and engineering judgment the seismic analysis loading for the Shield Building contained in Attachment A of this calculation remains bounding for the combined effects of the laminar cracks and crack propagation conditions.

Table Al.

Comparison of the dynamic characteristic between the model including different levels of laminar cracking &

the original model used for the seismic analysis Mode no.

l 2

3 4

SUM Natural frequencies and mass participation factors Original Calculation (Ref. A3)

Freq (Hz) 2.97 10.52 20.65 29.02 MPF (%)

Not Avail.

Model-1 (no crack/Baseline)

Freq (Hz) 2.97 10.55 20.70 29.10 MPF (%)

74 16 4

2 96 Model-2 (conservative)

Freq (Hz) 2.86 10.09 19.57 27.72 MPF (%)

73 16 4

2 95 Model-3 (more accurate)

Freq (Hz) 2.90 10.20 19.65 27.87 MPF (%)

73 16 4

2 95 Frequency differences with respect to the original calculation (%)

Model-l 0.0 0.2 0.3 0.3 Model-2

-3.5

-4.1

-5.2

-4.5 Model-3

-2.2

-3.1

-4.8

-4.0

Attachment A:

Evaluation of the Seismic Analysis Loading Considering the Observed Laminar Cracking of the Shield Building Calc. No:

C-CSS-099.20-063, Rev. 001 Sheet No:

13 of 58 Sheet Rev.:

001 4

SUM 29.02 29.10 2

96 27.72 2

95 27.87 2

95 0.3

-4.5

-4.0 SLSol.05 EL->4fc E--I1O in EL4.4.O

u. 4 fa Eufcoa el <5&s.s f

j 1

j

/

7, 1

/

y.

\\

/

A

~

7 r.

\\

/

1

I

\\

Ss 1^

\\

]'

/

Figure A3.

Natural frequencies and mode shapes calculated from the original seismic analysis (Ref. A3)

Attachment A:

Evaluation of the Seismic Analysis Loading Considering the Observed Laminar Cracking of the Shield Building Calc. No:

C-CSS-099.20-063, Rev. 001 Sheet No:

14 of 58 Sheet Rev.:

001 t

(/)

c o

Model-1

-f a

re 71 r

r Model-2 MPF for this mode:

74%

r

[-

/

f I

I

/

-fl I

I

/

f lviodel-3

/

-1.5

-1.0

-0.5 0.0 0.5 1.0 1.5 Normalized modal displacement g

ro OJ LU a )

V mode

-Model-1

-Model-2 Model-3 1

Ss s

s

-i iA b-S r

ss,

^

MPF for this mode: 4%

r

^-*

5r<

F s.

sj le Or to n

HI

\\

n (ft) 1/1 c

o Q

Ele Model-1

\\

il it n

r r

Model-2 s,

s MPF for this mode:

16%

rrr

(

1" r

\\

s N

/

V>

1

/

s f

v/lodel-3

\\

A y

-1.5

-1.0

-0.5 0.0 0.5 1.0 Normalized modal displacement (b) 2nd mode 1.5 to g

to Model-1

(

s N

. T

r c

1 b

Model-2 MPF for this mode:

2%

r 5-Si s

\\

t

\\

)

\\/lodel-;

a b

/

r\\ n i

-1.5

-1.0

-0.5 0.0 0.5 1.0 1.5

-1.5

-1.0

-0.5 0.0 0.5 1.0 1.5 Normalized modal displacement (c) 3rd mode Normalized modal displacement (d) 4th mode Figure A4.

Mode shapes calculated from the three FE models for the first four modes

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

15 of 58 Building Sheet Rev.:

001 5.

Discussion on as-built condition The FE models developed herein are based on the original configuration (i.e., the same geometry, lumped-mass, and material properties), but different sectional properties are used to account for the effects of the laminar cracking.

After the original seismic analysis (Ref. A3), the SB has been re-evaluated for a higher seismic acceleration (0.20g) than the one (0.15g) used in the original SB

design, as well as for an as-built condition (Ref.

A4).

Reference A4 reports this as-built condition (i.e., lumped-weight @ EL 801' is increased from 4687kip to 5451kip), and its influence has been examined by comparing the natural frequencies with the original SB modal analysis.

In that reference, the maximum natural frequency difference is calculated as less than 1.7%,

which is insignificant.

Therefore, this examination uses the original lumped-weights (i.e., including 4687kip at EL 801') in order to evaluate only the impact of the laminar concrete cracks on the existing SB excluding the other effects.

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

16 of 58 Building Sheet Rev.:

001 6.

Summary The following summarizes the evaluation performed in this attachment:

The natural frequencies and mode shapes of the original as-designed SB were obtained from Ref. A3.

This was used as a

reference or a

baseline to examine the natural frequencies of the SB with the observed laminar cracking.

Only the natural frequencies and mode shapes are available in the original seismic calculation, so a baseline FE model (Model-1) was developed to re-create the baseline model representing the original SB.

The calculated natural frequencies and mode shapes of this model match those reported in the original calculation, Ref. A3.

Based on the IR testing results (Ref. A5), the entire SB wall was divided into four regions with different levels of cracking.

Accordingly, two more FE models with different cracking conditions, i.e. Model-2 (cracking in all flutes)

& Model-3 (cracking based on the crack map), were created by appropriately adjusting the SB cross sectional properties.

The natural frequencies for the first four modes calculated from Model-2 and Model-3 have good agreements with the original ones.

For the first two modes having significant (i.e.,

90%)

contributions to the dynamic behaviors, the maximum natural frequency difference with the original one is less than 5%.

Similarly, the corresponding mode shapes are also calculated for Model-1, Model-2, & Model-3.

All the mode shapes for the first four modes are compared and show good agreements.

It was observed that the 3rd and the 4th mode shapes in Region-3 are somewhat sensitive to the laminar concrete cracking.

However, the associated total MPFs are less than 6%

(= 4% +

2%),

which is considered insignificant based on its potential influence on the dynamic behaviors/responses of the SB.

The overall dynamic responses (i.e., natural frequencies, mode shapes, and MPFs) of all the three FE models are very similar and consistent, which demonstrates that the overall dynamic response of the Shield Building is not affected by the observed laminar cracking.

The discovered crack propagation was compared to the seismic models completed for this analysis.

It was determined that the models remain appropriate based on previously considered cracking.

Therefore it is determined this attachment remains bounding for the combined effects of the laminar cracks and crack propagation conditions.

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

17 of 58 Building Sheet Rev.:

001 7.

Conclusion in this examination, the dynamic characteristics of the existing SB was evaluated for the effects of the observed laminar cracking to assess any possible impact on the seismic loading by using three different FE models:

One includes no cracking (to simulate as-designed condition),

while the other two models have different levels of cracking and effective flutes.

The FEA results demonstrate that the laminar concrete cracking observed during the 2011 RCVH replacement has insignificant impact on the dynamic behaviors of the SB.

The mode shapes, frequencies, and effective mass participation of the models with the laminar cracking are very similar to those of the original SB (no laminar cracking).

Therefore, it is concluded that the seismic loading used in the original SB design (Ref. A3) is still valid and acceptable.

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

18 of 58 Building Sheet Rev.:

001 8.

ANSYS input and outputs

PROJECT DAVIS-BESSE 2013 SB new design-basis calc ORIGINATOR HOAN-KEE KIM CHECKER SHEN WANG SUBJECT Seismic analysis evaluation considering laminar cracking on SB JOB NO 25593 Examine the natural frequencies,

MPFs, and mode shapes of SB considering the different levels of the laminar concrete cracks.

Here, 3

different cases are examined as follows:

(1)

Case-1:

Original design (VS01/B01-03)

No

crack, used as reference data point (2)

Case-2:

Cracks in all flutes conservative since not all flutes are cracked.

(3)

Case-3:

Cracks in some flutes and elsewhere more

accurate, based on crack map Note that all modeling parameters are taken from the original seismic analysis calc except for the cross sectional properties of the beam in the cracked area.

i FINISH

/CLEAR,START n_case

=

1 lease no.

fname=STRCAT('SB_case',CHRVAL(n_case))

/filname, fname,l

/PREP7 (1)GEOMETRY

DIM,

ELEV, ARRAY, 14

[FT]

!NODE ELEV(1)=

1

565, 2

570.75, 3

589. 5, 4

603, 5

609, 6

643, 7

646. 5, 8

660, 9

692, 10

720, 11

748, 12 774.5, 13

801, 14 812.75

NUMSTR, LINE, 1

DO,I,1,14 K,

I, 0,

ELEV(I)

IF,I,GT,1,THEN L,

1-1, I

ENDIF

ENDDO K,

101,10,ELEV(l)

(2)MATERIAL SECTION

DIM,

AX1, ARRAY, 13

[FTA2]

DIM,

IZ1, ARRAY, 13

[FTA4]

DIM, WT1,

ARRAY, 13

[KIP]

if,n_case,eq,1,then

!ELEM i

AX1(1)=

IZ1(1) =

WT1(1)=

elseif i

!ELEM I

AX1(1) =

IZ1(1) =

WT1{1) =

i

elseif 1

1153.7,

2892E3, 2120.0,

,n

case, 1

1110.8,

2781E3, 2120.0,

,n

case, 1153.7,

2892E3, 2791.0, eq,2,then 2

1110.8,

2781E3, 2791.0, eq,3,then 3

1153.7,

2892E3, 1697.0, 3

1110.8,

2781E3, 1697.0, 4

1175.1,

2948E3, 3526.0, 4

1110.8,

2781E3, 3526.0, 5

1175.1,

2948E3, 3311.0, 5

1110.8,

2781E3, 3311.0, 6

1196.6,

3004E3, 1526.0, 6

1110.8,

2781E3, 1526.0, 7

1196.6,

3004E3, 4290.0, 7

1110.8,

2781E3, 4290.0, 8

1282.4,

3228E3, 5771.0, 8

1110.8,

2781E3, 5771.0, 9

1282.4,

3228E3, 5386.0, 9

1110.8,

2781E3, 5386.0, 10 1282.4,

3228E3, 5244.0, 10 1110.8,

2781E3, 5244.0, 11 1282.4,

3228E3, 5102.0, 11 1110.8,

2781E3, 5102.0, 12 1282.4,

3228E3, 4687.0, 12 1110.8,

2781E3, 4687.0, 13 1554.0 2991E3 4035.0 13 1554.0 2991E3 4035.0

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 19 of 58 001

!ELEM 10 11 12 13 AX1(1)=

1153.7, 1153.7, 1153.7, 1153.7, 1153.7, 1104.5, 1104.5, 1125.9, 1125.9, 1125.9, 1125.9, 1056.5, 1554.0 IZ1(1)=

2892E3, 2892E3,

2892E3, 2765E3,

2765E3, 2820E3,

2820E3, 2820E3,

2820E3, 2640E3, 2991E3 WT1(1)=

2120.0, 2791.0, 1697.0, 3526.0, 3311.0, 1526.0, 4290.0, 5771.0, 5386.0, 5244.0, 5102.0, 4687.0, 4035.0

endif MP, MP, MP, EX,

GXY, DENS, GRAV=

32.174

DO, R,I, 1,1,13 WT1(I)/GRAV

ENDDO ET, ET, (3)ELEMENT 1,

BEAM188 2,

MASS21.,

1 1

1 i

t 524757.

209900.

0.

ft/secA2

,WT1(I)/GRAV 2

!ksf

DO,I, 1, 13

SECTYPE, I,

BEAM, ASEC

SECDATA, AX1(I),IZl(I),0.0,IZl(I),,100 SECCONTROLS,AX1(I)*209900.0/2.0,,AX1(I)*209900.0/2.0

SECNUM, I

ENDDO

DO,I, 1,13 LSEL,S,LINE,,I LATT,1,,1,

, 101,,1

ENDDO

ESIZE, 100

LSEL, ALL

LMESH, ALL

DO,I, 1,13 NN=NODE(0,ELEV(I+1),0)

TYPE,2 REAL,I E,NN

ENDDO NN=NODE(0,ELEV(1),0)

D,NN,ALL ALLSEL,ALL EPLOT (4)ANALYSIS

/SOLU N_FREQ=20 ANTYPE,MODAL MODOPT,LANPCG,N_FREQ ALLSEL,ALL

/OOTPDT, fname,'ODT' SOLVE

/POST1

DO, I,1,N_FREQ SET,1,1 PRNSOL,U,X

ENDDO SAVE FINISH

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 20 of 58 001

<Outputfile:

SB easel.out>

ANSYS SOLVE COMMAND NOTE CP

=

There is no title defined for this analysis.

2.465 TIME=

16:32:52 NOTE CP

=

2.465 TIME=

16:32:52 No modes are being expanded (MXPAND command) and therefore the element results will not be written to the mode file.

For more efficient calculation of element results in the expansion pass of any downstream mode superposition

analyses, expand all modes during the modal analysis.

SELECTION OF ELEMENT TECHNOLOGIES FOR APPLICABLE ELEMENTS GIVE SUGGESTIONS ONLY ELEMENT TYPE 1

IS BEAM188 KEYOPT(1)=1 IS SUGGESTED FOR NON-CIRCULAR CROSS SECTIONS AND KEYOPT(3)=2 IS ALWAYS SUGGESTED.

ELEMENT TYPE 1

IS BEAM188 KEYOPT(15)

IS ALREADY SET AS SUGGESTED.

SOLUTION OPTIONS PROBLEM DIMENSIONALITY 3-D DEGREES OF FREEDOM UX UY UZ ROTX ROTY ROTZ ANALYSIS TYPE MODAL EXTRACTION METHOD PCG LANCZOS NUMBER OF MODES TO EXTRACT 20 GLOBALLY ASSEMBLED MATRIX SYMMETRIC LOAD STEP OPTIONS LOAD STEP NUMBER 1

NOTE CP

=

2.496 TIME=

16:32:52 The PCG solver has automatically set the level of difficulty for this model to 5.

CENTER OF

MASS, MASS, AND MASS MOMENTS OF INERTIA CALCULATIONS ASSUME ELEMENT MASS AT ELEMENT CENTROID TOTAL MASS

=

1538.1 CENTER OF MASS MOM.

OF INERTIA ABOUT ORIGIN MOM.

OF INERTIA ABOUT CENTER OF MASS XC

=

YC

=

ZC

=

0.0000 702.26 0.0000 IXX

=

IYY

=

IZZ

=

IXY

=

IYZ

=

IZX

=

0.7672E+09 0.000 0.7672E+09 0.000 0.000 0.000 IXX

=

IYY

=

IZZ

=

IXY

=

IYZ

=

IZX

=

0.8654E+07 0.000 0.8654E+07 0.000 0.000 0.000 MASS

SUMMARY

BY ELEMENT TYPE TYPE 2

MASS 1538.07 Range of element maximum matrix coefficients in global coordinates Maximum

=

4.505013218E+11 at element 6.

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 21 of 58 001 Minimum

=

4.654779604E+10 at element 5.

ELEMENT MATRIX FORMULATION TIMES TYPE NUMBER ENAME TOTAL CP AVE CP 0.000 0.000000 0.000 0.000000 matrix formulation CP

=

2, of eigenvalues converged=

of eigenvalues converged=

PCG LANCZOS EIGENSOLVER HAS CONVERGED SUCCESSFULLY THE REQUESTED 20 MODES HAVE BEEN FOUND SUCCESSFULLY 1

2 Time at end Iteration=

Iteration=

Iteration^

Iteration=

13 13 of 12 22 29 30 31 32 33 34 35 36 37 38 39 BEAM18 8 MASS21 element Number Number Number Number Number Number Number Number Number Number Number Number Number 49601603.

5 10 15 20 20 20 20 20 20 20 20 20 20 Wall=

Wall=

wall=

Wall=

0.1 0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2 0.2 ANSYS ENGINEERING ANALYSIS SYSTEM RELEASE 13.0 ANSYS Professional NLS 00203236 VERSION=WINDOWS x64 16:32:53 JUL 02, 2013 CP=

2.574 FREQUENCIES FROM PCG LANCZOS ITERATION MODE FREQUENCY (HERTZ) 1 2

3 4

5 6

7 8

9 10 11 12 13 14 15 16 17 18 19 20 2.972636123830 2.972636123830 9.623396870742 10.54549939584 10.54549939584 20.70395957799 20.70395957799 29.10202752737 29.10202752737 29.60053634338 35.46560948148 35.46560948148 44.03960132374 44.03960132374 49.20628176331 51.89369247264 51.89369247264 60.82468169537 60.82468169537 66.15310435791 ANSYS ENGINEERING ANALYSIS SYSTEM RELEASE 13.0 ANSYS Professional NLS 00203236 VERSION=WINDOWS x64 16:32:53 JUL 02, 2013 CP=

2.590 PARTICIPATION FACTOR CALCULATION X

DIRECTION

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 22 of 58 001 MODE 1

2 3

4 5

6 7

8 9

10 11 12 13 14 15 16 17 18 19 20 sum FREQUENCY 2.97264 2.97264 9.62340 10.5455 10.5455 20.7040 20.7040 29.1020 29.1020 29.6005 35.4656 35.4656 44.0396 44.0396 49.2063 51.8937 51.8937 60.8247 60.8247 66.1531 PERIOD 0.33640 0.33640 0.10391 0.94827E-01 0.94827E-01 0.48300E-01 0.48300E-01 0.34362E-01 0.34362E-01 0.33783E-01 0.28196E-01 0.28196E-01 0.22707E-01 0.22707E-01 0.20323E-01 0.19270E-01 0.19270E-01 0.16441E-01 0.16441E-01 0.15116E-01 PARTIC.FACTOR 1.9324 33.657 0.12255E-08 15.791 1.1649 0.44090 7.5394 5.6273 1.0497

-0.13487E-08

-3.2684

-0.33333 0.83296 0.16254 0.12383E-11 0.28853

-0.32345E-01 0.28698 2.3223 0.44367 RATIO 0.057417 1.000000 0.000000 0.469178 0.034610 0.013100 0.224011 0.167198 0.031189 0.000000 0.097109 0.009904 0.024749 0.004829 0.000000 0.008573 0.000961 0.008527 0.068999 0.013182 EFFECTIVE MASS 3.73436 1132.76 0.150196E-17 249.353 1.35688 0.194391 56.8431 31.6664 1.10188 0.181911E-17 10.6821 0.111107 0.693818 0.264190E-01 0.153339E-23 0.832485E-01 0.104622E-02 0.823590E-01 5.39298 0.196846 1494.28 CUMULATIVE MASS FRACTION 0.249910E-02 0.760564 0.760564 0.927435 0.928343 0.928473 0.966514 0.987705 0.988443 0.988443 0.995591 0.995666 0.996130 0.996148 0.996148 0.996203 0.996204 0.996259 0.999868 1.00000 RATIO EFF.MASS TO TOTAL MASS 0.242794E-02 0.736481 0.976518E-21 0.162120 0.882195E-03 0.126386E-03 0.369573E-01 0.205884E-01 0.716403E-03 0.118272E-20 0.694514E-02 0.722376E-04 0.451095E-03 0.171767E-04 0.996955E-27 0.541252E-04 0.680212E-06 0.535468E-04 0.350632E-02 0.127982E-03 0.971528 MODE 1

2 3

4 5

6 7

8 9

10 11 12 13 14 15 16 17 18 19 20 sum PARTICIPATION FACTOF FREQUENCY 2.97264 2.97264 9.62340 10.5455 10.5455 20.7040 20.7040 29.1020 29.1020 29.6005 35.4656 35.4656 44.0396 44.0396 49.2063 51.8937 51.8937 60.8247 60.8247 66.1531 PERIOD 0.33640 0.33640 0.10391 0.94827E-01 0.94827E-01 0.48300E-01 0.48300E-01 0.34362E-01 0.34362E-01 0.33783E-01 0.28196E-01 0.28196E-01 0.22707E-01 0.22707E-01 0.20323E-01 0.19270E-01 0.19270E-01 0.16441E-01 0.16441E-01 0.15116E-01 CALCULATION PARTIC.FACTOR 0.76438E-09

-0.82649E-10 35.806

-0.90210E-10 0.48469E-08 0.25414E-09

-0.73022E-09 0.83424E-10

-0.29437E-12 11.011 0.91303E-11

-0.28885E-09

-0.42436E-10

-0.89078E-08 6.8040

-0.24167E-11 0.54669E-10 0.14697E-10

-0.37445E-11

-0.58234E-11 Y

DIRECTION RATIO 0.000000 0.000000 1.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.307519 0.000000 0.000000 0.000000 0.000000 0.190024 0.000000 0.000000 0.000000 0.000000 0.000000 EFFECTIVE MASS 0.584275E-18 0.683078E-20 1282.08 0.813792E-20 0.234926E-16 0.645874E-19 0.533223E-18 0.695956E-20 0.866508E-25 121.244 0.833630E-22 0.834315E-19 0.180085E-20 0.793488E-16 46.2950 0.584035E-23 0.298875E-20 0.216009E-21 0.140214E-22 0.339115E-22 1449.62 CUMULATIVE MASS FRACTION 0.403053E-21 0.407765E-21 0.884426 0.884426 0.884426 0.884426 0.884426 0.884426 0.884426 0.968064 0.968064 0.968064 0.968064 0.968064 1.00000 1.00000 1.00000 1.00000 1.00000 1.00000 RATIO EFF.MASS TO TOTAL MASS 0.379874E-21 0.444112E-23 0.833564 0.529098E-23 0.152740E-19 0.419924E-22 0.346682E-21 0.452486E-23 0.563372E-28 0.788285E-01 0.541996E-25 0.542441E-22 0.117085E-23 0.515897E-19 0.300993E-01 0.379718E-26 0.194317E-23 0.140441E-24 0.911620E-26 0.220480E-25 0.942492 PARTICIPATION FACTOR CALCULATION 2

DIRECTION MODE FREQUENCY PERIOD PARTIC.FACTOR RATIO EFFECTIVE MASS 2.97264 2.97264 9.62340 10.5455 0.33640 0.33640 0.10391 0.94827E-01 33.657

-1.9324

-0.12276E-09

-1.1649 1.000000 0.057417 0.000000 0.034610 1132.76 3.73436 0.150706E-19 1.35688 CUMULATIVE MASS FRACTION 0.752015 0.754494 0.754494 0.755395 RATIO EFF.MASS TO TOTAL MASS 0.736481 0.242794E-02 0.979836E-23 0.882195E-03

Attachment A:

Evaluation of the Seismic Analysis Loading Calc.

No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 23 of 58 001 5

6 7

8 9

10 11 12 13 14 15 16 17 18 19 20 10.5455 20.7040 20.7040 29.1020 29.1020 29.6005 35.4656 35.4656 44.0396 44.0396 49.2063 51.8937 51.8937 60.8247 60.8247 66.1531 0.94827E-01 0.48300E-01 0.48300E-01 34362E-01 34362E-01 33783E-01 28196E-01 28196E-01 22707E-01 22707E-01 20323E-01 19270E-01 19270E-01 16441E-01 16441E-01 0.15116E-01 15.791 7.5394

-0.44090

-1.0497 5.6273

-0.53717E-09 0.33333

-3.2684

-0.16254 0.83296 0.21212E-10 0.32345E-01 0.28853 2.3223

-0.28698 3.4954 0.469178 0.224011 0.013100 0.031189 0.167198 0.000000 0.009904 0.097109 0.004829 0.024749 0.000000 000961 008573 0.068999 008527 103856 249.353 56.8431 0.194391 1.10188 31.6664 0.288553E-18 0.111107 10.6821 0.264190E-01 0.693818 0.449948E-21 0.104622E-02 0.832485E-01 5.39298 0.823590E-01 12.2182 0.920934 0.958671 0.958800 0.959532 0.980554 0.980554 0.980628 0.987720 0.987737 0.988198 0.988198 0.988198 0.988254 0.991834 0.991889 1.00000 0.162120 0.369573E-01 0.126386E-03 0.716403E-03 0.205884E-01

.187607E-21

.722376E-04

.694514E-02

.171767E-04

.451095E-03

.292540E-24 0.680212E-06 0.541252E-04 0.350632E-02 0.535468E-04 0.794381E-02 1506.30 0.979343 PARTICIPATION FACTOR CALCULATION

- - - - ROTX DIRECTION MODE 1

2 3

4 5

6 7

8 9

10 11 12 13 14 15 16 17 18 19 20 sum FREQUENCY 2.97264 2.97264 9.62340 10.5455 10.5455 20.7040 20.7040 29.1020 29.1020 29.6005 35.4656 35.4656 44.0396 44.0396 49.2063 51.8937 51.8937 60.8247 60.8247 66.1531 PERIOD 0.33640 0.33640 0.10391 0.94827E-01 0.94827E-01 0.48300E-01 0.48300E-01 0.34362E-01 0.34362E-01 0.33783E-01 0.28196E-01 0.28196E-01 0.22707E-01 0.22707E-01 0.20323E-01 0.19270E-01 0.19270E-01 0.16441E-01 0.16441E-01 0.15116E-01 PART IC. FACTOR 25135.

-1443.2

-0.69613E-07

-673.96 9136.3 4376.7

-255.94

-595.48 3192.3

-0.31428E-06 190.92

-1872.0

-90.755 465.09 0.12142E-07 18.797 167.68 1313.2

-162.29 1980.5 RATIO 1.000000 0.057417 0.000000 0.026813 0.363482 0.174123 0.010183 0.023691 0.127003 0.000000 0.007596 0.074476 0.003611 0.018503 0.000000 0.000748 0.006671 0.052246 0.006456 0.078793 EFFECTIVE MASS 0.631786E+09 0.208280E+07 0.484600E-14 454218.

0.834712E+08 0.191551E+08 65506.1 354598.

0.101906E+08 0.987703E-13 36449.0 0.350432E+07 8236.38 216305.

0.147418E-15 353.332 28115.0 0.172456E+07 26336.7 0.392230E+07 0.757027E+09 CUMULATIVE MASS FRACTION 0.834562 0.837313 0.837313 0.837913 0.948175 0.973478 0.973565 0.974033 0.987495 0.987495 0.987543 0.992172 0.992183 0.992468 0.992468 0.992469 0.992506 0.994784 0.994819 1.00000 PARTICIPATION FACTOR CALCULATION

- - - - ROTY DIRECTION ODE 1

2 3

4 5

6 7

8 9

10 11 12 13 FREQUENCY 2.97264 2.97264 9.62340 10.5455 10.5455 20.7040 20.7040 29.1020 29.1020 29.6005 35.4656 35.4656 44.0396 PERIOD 0.33640 0.33640 0.10391 0.94827E-01 0.94827E-01 0.48300E-01 0.48300E-01 0.34362E-01 0.34362E-01 0.33783E-01 0.28196E-01 0.28196E-01 0.22707E-01 PART IC. FACTOR 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 RATIO 0.000000 EFFECTIVE MASS 0.00000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 CUMULATIVE MASS FRACTION 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 24 of 58 001 14 15 16 17 18 19 20 44.0396 49.2063 51.8937 51.8937 60.8247 60.8247 66.1531 0.22707E-01 0.20323E-01 0.19270E-01 0.19270E-01 0.16441E-01 0.16441E-01 0.15116E-01 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 PARTICIPATION FACTOR CALCULATION

- - - - ROTZ DIRECTION MODE 1

2 3

4 5

6 7

8 9

10 11 12 13 14 15 16 17 18 19 20 sum NOTE Solution FREQUENCY 2.97264 2.97264 9.62340 10.5455 10.5455 20.7040 20.7040 29.1020 29.1020 29.6005 35.4656 35.4656 44.0396 44.0396 49.2063 51.8937 51.8937 60.8247 60.8247 66.1531 is done!

PERIOD 0.33640 0.33640 0.10391 0.94827E-01 0.94827E-01 0.48300E-01 0.48300E-01 0.34362E-01 0.34362E-01 0.33783E-01 0.28196E-01 0.28196E-01 0.22707E-01 0.22707E-01 0.20323E-01 0.19270E-01 0.19270E-01 0.16441E-01 0.16441E-01 0.15116E-01 PARTIC.FACTOR

-1443.2

-25135.

-0.68747E-06

-9136.3

-673.96

-255.94

-4376.7

-3192.3

-595.48 0.76509E-06 1872.0 190.92

-465.09

-90.755

-0.71468E-09

-167.68 18.797

-162.29

-1313.2

-251.38 CP

=

RATIO 0.057417 1.000000 0.000000 0.363482 0.026813 0.010183 0.174123 0.127003 0.023691 0.000000 0.074476 0.007596 0.018503 0.003611 0.000000 0.006671 0.000748 0.006456 0.052246 0.010001 EFFECTIVE MASS 0.208280E+07 0.631786E+09 0.472612E-12 0.834712E+08 454218.

65506.1 0.191551E+08 0.101906E+08 354598.

0.585366E-12 0.350432E+07 36449.0 216305.

8236.38 0.510765E-18 28115.0 353.332 26336.7 0.172456E+07 63191.8 0.753168E+09 2.590 TIME=

16:32:53 CUMULATIVE MASS FRACTION 0.276538E-02 0.841604 0.841604 0.952430 0.953033 0.953120 0.978553 0.992083 0.992554 0.992554 0.997207 0.997255 0.997543 0.997554 0.997554 0.997591 0.997591 0.997626 0.999916 1.00000 ANSYS BINARY FILE STATISTICS BUFFER SIZE USED=

16384 0.062 MB WRITTEN ON ELEMENT MATRIX FILE:

SB_casel.emat 0.062 MB WRITTEN ON ELEMENT SAVED DATA FILE:

SB_casel.esav 0.062 MB WRITTEN ON MODAL MATRIX FILE:

SB_casel7mode FINISH SOLUTION PROCESSING ROUTINE COMPLETED CP

=

2.683 ANSYS RESULTS INTERPRETATION (POST1)

ENTER ENTER

/SHOW,DEVICE-NAME FINISH TO ENABLE GRAPHIC DISPLAY TO LEAVE POST1 NOTE CP 2.699 TIME=

16:32:53 Reading results into the database (SET command) will update the current displacement and force boundary conditions in the database with the values from the results file for that load set.

Note that any subsequent solutions will use these values unless action is taken to either SAVE the current values or not overwrite them

(/EXIT,NOSAVE).

DO LOOP ON PARAMETER=

I FROM 1.0000 TO 20.000 BY 1.0000 USE LOAD STEP 1

SUBSTEP 1

FOR LOAD CASE 0

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

25 of 58 Building Sheet Rev.:

001 SET COMMAND GOT LOAD STEP=

1 SOBSTEP=

1 CUMULATIVE ITERATION=

1 TIME/FREQDENCY=

2.9726 TITLE=

PRINT U

NODAL SOLUTION PER NODE POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

1 FREQ=

2.972 6 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000 2

0.33328E-04 4

0.15919E-03 6

0.26475E-03 8

0.31463E-03 10 0.63092E-03 12 0.66594E-03 14 0.80461E-03 16 0.11382E-02 18 0.14367E-02 20 0.17308E-02 22 0.19969E-02 24 0.22443E-02 26 0.23430E-02 MAXIMUM ABSOLUTE VALUES NODE 2 6 VALOE 0.23430E-02

ENDDO INDEX=

I POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

2 FREQ=

2.972 6 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000 2

0.58046E-03 4

0.27726E-02 6

0.46110E-02 8

0.54798E-02 10 0.10988E-01 12 0.11598E-01 14 0.14014E-01 16 0.19823E-01 18 0.25023E-01 20 0.30145E-01 22 0.34779E-01 24 0.39089E-01 26 0.40806E-01 MAXIMUM ABSOLUTE VALUES NODE 2 6 VALUE 0.40806E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

3 FREQ=

9.6234 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

26 of 58 Building Sheet Rev.:

001 1

0.0000 2

-0.10935E-10 4

0.36441E-10 6

0.60531E-11 8

-0.60485E-11 10

-0.37145E-12 12

-0.69429E-12 14

-0.70520E-11 16

-0.75870E-11 18 0.11797E-10 20 0.28326E-11 22

-0.78858E-11 24 0.81497E-14 26 0.25005E-11 MAXIMUM ABSOLUTE VALUES NODE 4

VALUE 0.36441E-10 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

4 FREQ=

10.545 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 UX 0.0000 0.33003E-02 0.13929E-01 0.20913E-01 0.23672E-01 0.35031E-01 0.35616E-01 0.36802E-01 0.32362E-01 0.21264E-01 0.54055E-02

-0.11336E-01

-0.27017E-01 26

-0.32257E-01 MAXIMUM ABSOLUTE VALUES NODE 14 VALUE 0.36802E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

5 FREQ=

10.545 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 MAXIMUM NODE UX 0.0000 0.24346E-03 0.10275E-02 0.15427E-02 0.17462E-02 0.25841E-02 0.26273E-02 0.27148E-02 0.23873E-02 0.15686E-02 0.39875E-03

-0.83626E-03

-0.19930E-02

-0.23795E-02 ABSOLUTE VALUES 14

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

27 of 58 Building Sheet Rev.:

001 VALUE 0.27148E-02 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

6 FREQ=

20.704 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 UX 0.0000 0.35535E-03 0.14568E-02 0.20064E-02 0.21550E-02 0.18378E-02 0.17109E-02 0.10686E-02

-0.91396E-03

-0.19778E-02

-0.17252E-02

-0.41293E-03 0.12015E-02 0.16187E-02 MAXIMUM ABSOLUTE VALUES NODE 8

VALUE 0.21550E-02 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

7 FREQ=

20.704 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 MAXIMUM NODE VALUE UX 0.0000 0.60765E-02 0.24912E-01 0.34310E-01 0.36852E-01 0.31426E-01 0.29257E-01 0.18273E-01

-0.15629E-01

-0.33820E-01

-0.29502E-01

-0.70611E-02 0.20546E-01 0.27681E-01 ABSOLUTE VALUES 8

0.36852E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

8 FREQ=

29.102 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 UX 0.0000 0.89339E-02 0.34756E-01 0.41666E-01 0.40932E-01

-0.56465E-02

-0.98956E-02

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

28 of 58 Building Sheet Rev.:

001 14

-0.24476E-01 16

-0.29898E-01 18 0.35979E-02 20 0.32223E-01 22 0.22819E-01 24

-0.12149E-01 26

-0.21419E-01 MAXIMUM ABSOLUTE VALUES NODE 6

VALUE 0.41666E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

9 FREQ=

29.102 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000 2

0.1S665E-02 4

0.64833E-02 6

0.77722E-02 8

0.76354E-02 10

-0.10533E-02 12

-0.18459E-02 14

-0.45657E-02 16

-0.55771E-02 18 0.67115E-03 20 0.60108E-02 22 0.42567E-02 24

-0.22662E-02 26

-0.39954E-02 MAXIMUM ABSOLUTE VALUES NODE 6

VALUE 0.77722E-02 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SDBSTEP=

10 FREQ=

2 9.601 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000 2

-0.97354E-11 4

-0.26303E-10 6

-0.13238E-10 8

0.28010E-10 10

-0.96803E-11 12

-0.28612E-10 14 0.14728E-10 16

-0.34504E-11 18 0.20999E-11 20

-0.14081E-11 22 0.10922E-11 24

-0.19196E-12 26

-0.44475E-12 MAXIMUM ABSOLUTE VALUES NODE 12 VALUE

-0.28612E-10 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

11 FREQ=

35.4 66 LOAD CASE=

0

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

29 of 58 Building Sheet Rev.:

001 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 UX 0.0000

-0.77158E-02

-0.28884E-01

-0.30033E-01

-0.26617E-01 0.32231E-01 0.33511E-01 0.29589E-01

-0.26793E-01

-0.262 67E-01 0.19980E-01 0.30625E-01

-0.80335E-02

-0.18693E-01 MAXIMUM ABSOLUTE VALUES NODE 12 VALUE 0.33511E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

12 FREQ=

35.4 66 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 UX 0.0000

-0.78691E-03

-0.29457E-02

-0.30629E-02

-0.27146E-02 0.32871E-02 0.34176E-02 0.30177E-02

-0.27326E-02

-0.26789E-02 0.20377E-02 0.31233E-02

-0.81931E-03 26

-0.19065E-02 MAXIMUM ABSOLUTE VALUES NODE 12 VALUE 0.34176E-02 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

13 FREQ=

44.040 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 UX 0.0000 0.30221E-02 0.10350E-01 0.77634E-02 0.50502E-02

-0.21913E-01

-0.19802E-01

-0.38575E-02 0.39851E-01

-0.36937E-01

-0.15054E-01 0.42356E-01

-0.32390E-02

-0.18134E-01

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

30 of 58 Building Sheet Rev.:

001 MAXIMUM ABSOLUTE VALUES NODE 22 VALUE 0.42356E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

14 FREQ=

44.040 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 UX 0.0000 0.58972E-03 0.20196E-02 0.15149E-02 0.98547E-03

-0.42759E-02

-0.38641E-02

-0.75273E-03 0.77764E-02

-0.72077E-02

-0.29377E-02 0.82652E-02

-0.63204E-03

-0.35385E-02 MAXIMUM ABSOLUTE VALUES NODE 22 VALUE 0.82652E-02 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

15 FREQ=

4 9.206 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 MAXIMUM NODE VALUE UX 0.0000

-0.13785E-13 0.33996E-13

-0.51631E-13 0.64917E-13

-0.83214E-12 0.20269E-11

-0.14104E-12 0.17073E-13 0.16636E-13

-0.10754E-13

-0.18997E-13 0.14710E-14 0.14497E-13 ABSOLUTE VALUES 12 0.20269E-11 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

16 FREQ=

51.894 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000 2

0.14611E-02 4

0.46698E-02 6

0.21942E-02

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

31 of 58 Building Sheet Rev.:

001 8

0.52212E-03 10

-0.10178E-01 12

-0.81047E-02 14 0.43622E-02 16 0.17222E-01 18

-0.39471E-01 20 0.50634E-01 22

-0.36653E-01 24

-0.12738E-02 26 0.13778E-01 MAXIMUM ABSOLUTE VALUES NODE 20 VALUE 0.50634E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

17 FREQ=

51.894 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 MAXIMUM NODE VALUE ux 0.0000

-0.16380E-03

-0.52351E-03

-0.24598E-03

-0.58532E-04 0.11411E-02 0.90857E-03

-0.48903E-03

-0.19306E-02 0.44249E-02

-0.56763E-02 0.41090E-02 0.14280E-03

-0.15446E-02 ABSOLUTE VALUES 20

-0.56763E-02 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

18 FREQ=

60.825 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 MAXIMUM NODE VALUE UX 0.0000 0.19894E-02 0.54580E-02 0.18891E-03

-0.21894E-02

-0.58163E-02

-0.37259E-02 0.71065E-02

-0.19608E-02 0.73616E-03

-0.28879E-03 0.96403E-04 0.44339E-04

-0.48642E-04 ABSOLUTE VALUES 14 0.71065E-02 POST1 NODAL DEGREE OF FREEDOM LISTING

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

32 of 58 Building Sheet Rev.:

001 LOAD STEP=

1 SOBSTEP=

19 FREQ=

60.825 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE OX 1

0.0000 2

0.16099E-01 4

0.44167E-01 6

0.15286E-02 8

-0.17717E-01 10

-0.47066E-01 12

-0.30150E-01 14 0.57506E-01 16

-0.15867E-01 18 0.59570E-02 20

-0.23369E-02 22 0.78010E-03 24 0.35879E-03 26

-0.39361E-03 MAXIMUM ABSOLUTE VALUES NODE 14 VALUE 0.57506E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

20 FREQ=

66.153 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 IS 18 20 22 24 26 MAXIMUM NODE VALUE UX 0.0000 0.36390E-02 0.90117E-02

-0.22509E-02

-0.61696E-02 0.39463E-02 0.30196E-02

-0.32161E-02 0.66472E-03

-0.17886E-03 0.53182E-04

-0.17551E-04 0.78049E-05 0.16761E-05 ABSOLUTE VALUES 4

0.90117E-02 ALL CURRENT ANSYS DATA WRITTEN TO FILE NAME=

SB_casel.db FOR POSSIBLE RESUME FROM THIS POINT EXIT THE ANSYS POST1 DATABASE PROCESSOR ROUTINE COMPLETED CP=

2.714

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 33 of 58 001

<Outputfile:

SB case2.out>

ANSYS SOLVE COMMAND NOTE CP

=

There is no title defined for this analysis.

3.323 TIME=

16:33:15 NOTE CP

=

3.323 TIME=

16:33:15 No modes are being expanded (MXPAND command) and therefore the element results will not be written to the mode file.

For more efficient calculation of element results in the expansion pass of any downstream mode superposition

analyses, expand all modes during the modal analysis.

SELECTION OF ELEMENT TECHNOLOGIES FOR APPLICABLE ELEMENTS GIVE SUGGESTIONS ONLY ELEMENT TYPE 1

IS BEAM188 KEYOPT(1)=1 IS SUGGESTED FOR NON-CIRCULAR CROSS SECTIONS AND KEYOPT(3)=2 IS ALWAYS SUGGESTED.

ELEMENT TYPE 1

IS BEAM188 KEYOPTU5)

IS ALREADY SET AS SUGGESTED.

SOLUTION OPTIONS PROBLEM DIMENSIONALITY 3-D DEGREES OF FREEDOM UX UY UZ ROTX ROTY ROTZ ANALYSIS TYPE MODAL EXTRACTION METHOD PCG LANCZOS NUMBER OF MODES TO EXTRACT 20 GLOBALLY ASSEMBLED MATRIX SYMMETRIC LOAD STEP OPTIONS LOAD STEP NUMBER 1

NOTE CP

=

3.338 TIME=

16:33:15 The PCG solver has automatically set the level of difficulty for this model to 5.

CENTER OF

MASS, MASS, AND MASS MOMENTS OF INERTIA CALCULATIONS ASSUME ELEMENT MASS AT ELEMENT CENTROID TOTAL MASS

=

1538.1 CENTER OF MASS MOM.

OF INERTIA ABOUT ORIGIN MOM.

OF INERTIA ABOUT CENTER OF MASS XC

=

YC

=

ZC

=

0.0000 702.26 0.0000 IXX

=

IYY

=

IZZ IXY

=

IYZ

=

IZX

=

0.7672E+09 0.000 0.7672E+09 0.000 0.000 0.000 IXX

=

IYY

=

IZZ

=

IXY

=

IYZ

=

IZX

=

0.8654E+07 0.000 0.8654E+07 0.000 0.000 0.000 MASS

SUMMARY

BY ELEMENT TYPE TYPE 2

MASS 1538.07 Range of element maximum matrix coefficients in global coordinates Maximum

=

4.170589253E+11 at element 6.

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 34 of 58 001 Minimum

=

4.39129527E+10 at element 5.

ELEMENT MATRIX FORMULATION TIMES TYPE NUMBER ENAME TOTAL CP AVE CP 1

13 BEAM188 2

13 MASS21 Time at end of element Form Preconditioner

=

Load Step=

1 Mode=

1.

Iteration=

0.000 0.000000 0.000 0.000000 matrix fonro 0

Cum.

Iter.=

1 Iteration=

Iteration=

12 Number 22 Number 30 Number 32 Number 33 Number 34 Number 35 Number 3 6 Numbe r 37 Number 38 Number 39 Number of eigenvalues of eigenvalues of eigenvalues of eigenvalues of eigenvalues of eigenvalues of eigenvalues of eigenvalues of eigenvalues of eigenvalues of eigenvalues ion CP

=

3 CP=

3.354 converged=

converged=

converged' converged' converged' converged' converged' converged' converged=

converged' converged'

.35402155.

5 10 19 20 20 20 20 20 20 20 20 Wall' Wall=

Wall' Wall' Wall=

wall=

Wall' Wall=

Wall' Wall' Wall' 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 PCG LANCZOS EIGENSOLVER HAS CONVERGED SUCCESSFULLY THE REQUESTED 20 MODES HAVE BEEN FOUND SUCCESSFULLY ANSYS ENGINEERING ANALYSIS SYSTEM RELEASE 13.0 ANSYS Professional NLS 00203236 VERSION=WINDOWS x64 16:33:15 JUL 02, 2013 CP=

3.385 FREQUENCIES FROM PCG LANCZOS ITERATION MODE FREQUENCY (HERTZ) 1 2

3 4

5 6

7 8

9 10 11 12 13 14 15 16 17 18 19 20 2.864356152505 2.864356152505 9.230689483331 10.09228623778 10.09228623778 19.56979412461 19.56979412461 27.71597548243 27.71597548243 28.01297847515 33.62201384960 33.62201384960 41.19442743602 41.19442743602 46.47563826620 48.40024545503 48.40024545503 58.46951664097 58.46951664097 63.84375410699 ANSYS ENGINEERING ANALYSIS SYSTEM ANSYS Professional NLS 00203236 VERSION=WINDOWS x64 16:33:15 RELEASE 13.0 JUL 02, 2013 CP=

3.401 PARTICIPATION FACTOR CALCULATION X

DIRECTION

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 35 of 58 001 MODE 1

2 3

4 5

6 7

8 9

10 11 12 13 14 15 16 17 18 19 20 sum FREQUENCY 2.86436 2.86436 9.23069 10.0923 10.0923 19.5698 19.5698 27.7160 27.7160 28.0130 33.6220 33.6220 41.1944 41.1944 46.4756 48.4002 48.4002 58.4695 58.4695 63.8438 PERIOD 0.34912 0.34912 0.10833 0.99086E-01 0.99086E-01 0.51099E-01 0.51099E-01 0.36080E-01 0.36080E-01 0.35698E-01 0.29742E-01 0.29742E-01 0.24275E-01 0.24275E-01 0.21517E-01 0.20661E-01 0.20661E-01 0.17103E-01 0.17103E-01 0.15663E-01 PARTIC.FACTOR 33.527 1.8781 0.18036E-08 15.912 0.91229 0.36231 7.6249 1.7638 5.4843

-0.37225E-10 0.40269 3.7674 0.12758 0.93976

-0.25982E-12 0.62481E-01 0.26190 0.28664 2.0699 0.15225E-09 RATIO 1.000000 0.056019 0.000000 0.474595 0.027211 0.010807 0.227427 0.052608 0.163580 0.000000 0.012011 0.112370 0.003805 0.028030 0.000000 0.001864 0.007812 0.008550 0.061739 0.000000 EFFECTIVE MASS 1124.05 3.52743 0.325287E-17 253.182 0.832281 0.131272 58.1395 3.11096 30.0777 0.138571E-20 0.162158 14.1933 0.162778E-01 0.883154 0.675090E-25 0.390388E-02 0.685921E-01 0.821644E-01 4.28457 0.231788E-19 1492.75 CUMULATIVE MASS FRACTION 0.753009 0.755372 0.755372 0.924980 0.925538 0.925625 0.964573 0.966658 0.986807 0.986807 0.986915 0.996424 0.996434 0.997026 0.997026 0.997029 0.997075 0.997130 1.00000 1.00000 RATIO EFF.MASS TO TOTAL MASS 0.730817 0.229341E-02 0.211490E-20 0.164610 0.541119E-03 0.853480E-04 0.378002E-01 0.202264E-02 0.195554E-01 0.900939E-24 0.105429E-03 0.922796E-02 0.105832E-04 0.574195E-03 0.438919E-28 0.253816E-05 0.445961E-04 0.534203E-04 0.278567E-02 0.150700E-22 0.970529 PARTICIPATION FACTOR CALCULATION Y

DIRECTION MODE 1

2 3

4 5

6 7

8 9

10 11 12 13 14 15 16 17 18 19 20 sum FREQUENCY 2.86436 2.86436 9.23069 10.0923 10.0923 19.5698 19.5698 27.7160 27.7160 28.0130 33.6220 33.6220 41.1944 41.1944 46.4756 48.4002 48.4002 58.4695 58.4695 63.8438 PERIOD 0.34912 0.34912 0.10833 0.99086E-01 0.99086E-01 0.51099E-01 0.51099E-01 0.36080E-01 0.36080E-01 0.35698E-01 0.29742E-01 0.29742E-01 0.24275E-01 0.24275E-01 0.21517E-01 0.20661E-01 0.20661E-01 0.17103E-01 0.17103E-01 0.15663E-01 PARTIC.FACTOR

-0.21365E-08 0.78923E-09 35.623

-0.11253E-09 0.60980E-09

-0.64152E-08

-0.93718E-09

-0.32960E-12

-0.36809E-11 11.381

-0.20987E-10 0.15952E-09

-0.14423E-09

-0.18141E-09

-6.8538 0.20627E-10 0.77875E-09

-0.25235E-09

-0.39057E-12 5.4621 RATIO 0.000000 0.000000 1.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.319488 0.000000 0.000000 0.000000 0.000000 0.192398 0.000000 0.000000 0.000000 0.000000 0.153330 EFFECTIVE MASS 0.456463E-17 0.622891E-18 1268.99 0.126638E-19 0.371861E-18 0.411551E-16 0.878301E-18 0.108634E-24 0.135489E-22 129.529 0.440452E-21 0.254459E-19 0.208023E-19 0.329113E-19 46.9743 0.425466E-21 0.606444E-18 0.636814E-19 0.152542E-24 29.8341 1475.33 CUMULATIVE MASS FRACTION 0.309397E-20 0.351618E-20 0.860141 0.860141 0.860141 0.860141 0.860141 0.860141 0.860141 0.947938 0.947938 0.947938 0.947938 0.947938 0.979778 0.979778 0.979778 0.979778 0.979778 1.00000 RATIO EFF.MASS TO TOTAL MASS 0.296776E-20 0.404981E-21 0.825052 0.823352E-23 0.241770E-21 0.267576E-19 0.571039E-21 0.706300E-28 0.880899E-26 0.842153E-01 0.286366E-24 0.165440E-22 0.135249E-22 0.213977E-22 0.305410E-01 0.276623E-24 0.394288E-21 0.414033E-22 0.991772E-28 0.193970E-01 0.959206 PARTICIPATION FACTOR CALCULATION Z

DIRECTION CUMULATIVE RATIO EFF.MASS MODE FREQUENCY PERIOD PARTIC.FACTOR RATIO EFFECTIVE MASS MASS FRACTION TO TOTAL MASS 1

2 3

4 2.

2.

9.

10 86436 86436 23069

.0923 0.34912 0.34912 0.10833 0.99086E-01

-1.8781 33.527

-0.19408E-09

-0.91229 0.056019 1.000000 0.000000 0.027211 3.52743 1124.05 0.376670E-19 0.832281 0.236305E-02 0.755372 0.755372 0.755929 0.229341E-02 0.730817 0.244897E-22 0.541119E-03

Attachment A:

Evaluation of the Seismic Analysis Loading Calc.

No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 36 of 58 001 5

6 7

8 9

10 11 12 13 14 15 16 17 18 19 20 10.0923 19.5698 19.5698 27.7160 27.7160 28.0130 33.6220 33.6220 41.1944 41.1944 46.4756 48.4002 48.4002 58.4695 58.4695 63.8438 0.99086E-01 0.51099E-01 0.51099E-01 0.36080E-01 0.36080E-01 35698E-01 29742E-01 29742E-01 24275E-01 24275E-01 21517E-01 20661E-01 20661E-01 17103E-01 17103E-01 0.15663E-01 15.912 7.6249

-0.36231 5.4843

-1.7638

-0.11815E-08 3.7674

-0.40269 0.93976

-0.12758 0.67249E-10 0.26190

-0.62481E-01 2.0699

-0.28664 0.11218E-08 0.474595 0.227427 0.010807 0.163580 0.052608 0.000000 0.112370 0.012011 0.028030 0.003805 0.000000 0.007812 0.001864 0.061739 0.008550 0.000000 253.182 58.1395 0.131272 30.0777 3.11096 0.139597E-17 14.1933 0.162158

.883154

.162778E-01

.452238E-20

.685921E-01 0.390388E-02 4.28457 0.821644E-01 0.125839E-17 0.925538 0.964486 0.964573 0.984723 0.986807 0.986807 0.996315 0.996424 0.997015 0.997026 0.997026 0.997072 0.997075 0.999945 1.00000 1.00000 0.164610 0.378002E-01 0.853480E-04 0.195554E-01 0.202264E-02 0.907609E-21 0.922796E-02 0.105429E-03 0.574195E-03 0.105832E-04 0.294029E-23 0.445961E-04 0.253816E-05 0.278567E-02 0.534203E-04 0.818162E-21 1492.75 0.970529 PARTICIPATION FACTOR CALCULATION

- - - - ROTX DIRECTION MODE 1

2 3

4 5

6 7

8 9

10 11 12 13 14 15 16 17 18 19 20 sum FREQUENCY 2.86436 2.86436 9.23069 10.0923 10.0923 19.5698 19.5698 27.7160 27.7160 28.0130 33.6220 33.6220 41.1944 41.1944 46.4756 48.4002 48.4002 58.4695 58.4695 63.8438 PERIOD 0.34912 0.34912 0.10833 0.99086E-01 0.99086E-01 0.51099E-01 0.51099E-01 0.36080E-01 0.36080E-01 0.35698E-01 0.29742E-01 0.29742E-01 0.24275E-01 0.24275E-01 0.21517E-01 0.20661E-01 0.20661E-01 0.17103E-01 0.17103E-01 0.15663E-01 PARTIC.FACTOR

-1403.9 25061.

-0.11049E-06

-530.42 9251.3 4437.7

-210.86 3110.6

-1000.4

-0.68773E-06 2154.0

-230.24 525.09

-71.288 0.38431E-07 152.88

-36.471 1171.4

-162.22 0.62679E-06 RATIO 0.056019 1.000000 0.000000 0.021166 0.369158 0.177078 0.008414 0.124125 0.039920 0.000000 0.085952 0.009187 0.020953 0.002845 0.000000 0.006100 0.001455 0.046745 0.006473 0.000000 EFFECTIVE MASS 0.197085E+07 0.628029E+09 0.122081E-13 281347.

0.855864E+08 0.196929E+08 44464.0 0.967608E+07 0.100081E+07 0.472978E-12 0.463967E+07 53008.2 275721.

5081.94 0.147697E-14 23371.0 1330.15 0.137228E+07 26315.9 0.392871E-12 0.752678E+09 CUMULATIVE MASS FRACTION 0.261844E-02 0.837010 0.837010 0.837384 0.951093 0.977257 0.977316 0.990172 0.991501 0.991501 0.997666 0.997736 0.998102 0.998109 0.998109 0.998140 0.998142 0.999965 1.00000 1.00000 PARTICIPATION FACTOR CALCULATION

- - - - ROTY DIRECTION ODE 1

2 3

4 5

6 7

8 9

10 11 12 13 FREQUENCY 2.86436 2.86436 9.23069 10.0923 10.0923 19.5698 19.5698 27.7160 27.7160 28.0130 33.6220 33.6220 41.1944 PERIOD 0.34912 0.34912 0.10833 0.99086E-01 0.99086E-01 0.51099E-01 0.51099E-01 0.36080E-01 0.36080E-01 0.35698E-01 0.29742E-01 0.29742E-01 0.24275E-01 PARTIC.FACTOR 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 RATIO 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 EFFECTIVE MASS 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 CUMULATIVE MASS FRACTION 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 37 of 58 001 14 15 16 17 18 19 20 41.1944 46.4756 48.4002 48.4002 58.4695 58.4695 63.8438 0.24275E-01 0.21517E-01 0.20661E-01 0.20661E-01 0.17103E-01 0.17103E-01 0.15663E-01 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 PARTICIPATION FACTOR CALCULATION

- - - - ROTZ DIRECTION MODE 1

2 3

4 5

6 7

8 9

10 11 12 13 14 15 16 17 18 19 20 sum NOTE Solution FREQUENCY 2.86436 2.86436 9.23069 10.0923 10.0923 19.5698 19.5698 27.7160 27.7160 28.0130 33.6220 33.6220 41.1944 41.1944 46.4756 48.4002 48.4002 58.4695 58.4695 63.8438 is done!

PERIOD 0.34912 0.34912 0.10833 0.99086E-01 0.99086E-01 0.51099E-01 0.51099E-01 0.36080E-01 0.36080E-01 0.35698E-01 0.29742E-01 0.29742E-01 0.24275E-01 0.24275E-01 0.21517E-01 0.20661E-01 0.20661E-01 0.17103E-01 0.17103E-01 0.15663E-01 PARTIC.FACTOR

-25061.

-1403.9

-0.10258E-05

-9251.3

-530.42

-210.86

-4437.7

-1000.4

-3110.6 0.21861E-07

-230.24

-2154.0

-71.288

-525.09 0.10858E-09

-36.471

-152.88

-162.22

-1171.4

-0.85068E-07 CP

=

RATIO 1.000000 0.056019 0.000000 0.369158 0.021166 0.008414 0.177078 0.039920 0.124125 0.000000 0.009187 0.085952 0.002845 0.020953 0.000000 0.001455 0.006100 0.006473 0.046745 0.000000 3.401 TIME EFFECTIVE MASS 0.628029E+09 0.197085E+07 0.105235E-11 0.855864E+08 281347.

44464.0 0.196929E+08 0.100081E+07 0.967608E+07 0.477897E-15 53008.2 0.463967E+07 5081.94 275721.

0.117891E-19 1330.15 23371.0 26315.9 0.137228E+07 0.723651E-14 0.752678E+09

=

16:33:15 CUMULATIVE MASS FRACTION 0.834392 0.837010 0.837010 0.950720 0.951093 0.951152 0.977316 0.978646 0.991501 0.991501 0.991572 0.997736 0.997743 0.998109 0.998109 0.998111 0.998142 0.998177 1.00000 1.00000 ANSYS BINARY FILE STATISTICS BUFFER SIZE USED=

16384 0.062 MB WRITTEN ON ELEMENT MATRIX FILE:

SB_case2.emat 0.062 MB WRITTEN ON ELEMENT SAVED DATA FILE:

SB_case2.esav 0.062 MB WRITTEN ON MODAL MATRIX FILE:

SB_case2.mode FINISH SOLUTION PROCESSING ROUTINE COMPLETED CP

=

3.479 ANSYS RESULTS INTERPRETATION (POST1)

ENTER

/SHOW,DEVICE-NAME TO ENABLE GRAPHIC DISPLAY ENTER FINISH TO LEAVE POST1

DO LOOP ON PARAMETER=

I FROM 1.0000 TO 20.000 BY 1.0000 USE LOAD STEP SUBSTEP SET COMMAND GOT LOAD STEP=

TIME/FREQUENCY=

2.8644 TITLE=

1 FOR LOAD CASE 0

1 SUBSTEP=

1 CUMULATIVE ITERATION PRINT U

NODAL SOLUTION PER NODE

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

38 of 58 Building Sheet Rev.:

001 POSTl NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

1 FREQ=

2.8 64 4 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 MAXIMUM NODE VALUE UX 0.0000 0.55771E-03 0.26654E-02 0.44344E-02 0.52814E-02 0.10659E-01 0.11261E-01 0.13646E-01 0.19582E-01 0.24909E-01 0.30156E-01 0.34894E-01 0.39284E-01 0.41003E-01 ABSOLUTE VALUES 26 0.41003E-01

ENDDO INDEX=

I POSTl NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

2 FREQ=

2.8644 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 MAXIMUM NODE VALUE UX 0.0000 0.31243E-04 0.14931E-03 0.24841E-03 0.29586E-03 0.59712E-03 0.63083E-03 0.76443E-03 0.10970E-02 0.13954E-02 0.16893E-02 0.19547E-02 0.22006E-02 0.22970E-02 ABSOLUTE VALUES 26 0.22970E-02 POSTl NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

3 FREQ=

9.2307 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000 2

-0.13902E-10 4

0.41453E-10 6

0.11089E-10 8

-0.18654E-11 10 0.58293E-13 12

-0.95616E-12

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

39 of 58 Building Sheet Rev.:

001 14

-0.79397E-11 16

-0.12860E-10 18 0.11318E-10 20 0.72581E-11 22

-0.42420E-11 24

-0.11472E-11 26

-0.71758E-12 MAXIMUM ABSOLUTE VALUES NODE 4

VALUE 0.41453E-10 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

4 FREQ=

10.0 92 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 UX 0.0000 0.31656E-02 0.13396E-01 0.20173E-01 0.22922E-01 0.34514E-01 0.35169E-01 0.36656E-01 0.33028E-01 0.22130E-01 0.60594E-02

-0.11084E-01

-0.27146E-01

-0.32267E-01 MAXIMUM ABSOLUTE VALUES NODE 14 VALUE 0.36656E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

5 FREQ=

10.092 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000 2

0.18150E-03 4

0.76806E-03 6

0.11566E-02 8

0.13142E-02 10 0.19789E-02 12 0.20164E-02 14 0.21017E-02 16 0.18937E-02 18 0.12688E-02 20 0.34741E-03 22

-0.63551E-03 24

-0.15564E-02 26

-0.18500E-02 MAXIMUM ABSOLUTE VALUES NODE 14 VALUE 0.21017E-02 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

6 FREQ=

19.570 LOAD CASE=

0

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

40 of 58 Building Sheet Rev.:

001 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 UX 0.0000 0.27106E-03 0.11159E-02 0.15520E-02 0.16793E-02 0.15439E-02 0.14535E-02 0.97923E-03

-0.67501E-03

-0.16101E-02

-0.14433E-02

-0.36357E-03 0.98468E-03 0.13032E-02 MAXIMUM ABSOLUTE VALUES NODE 8

VALUE 0.16793E-02 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

7 FREQ=

19.570 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 UX 0.0000 0.57046E-02 0.23485E-01 0.32663E-01 0.35341E-01 0.32492E-01 0.30590E-01 0.20608E-01

-0.14206E-01

-0.33886E-01

-0.30375E-01

-0.76514E-02 0.20723E-01 0.27425E-01 MAXIMUM ABSOLUTE VALUES NODE 8

VALUE 0.35341E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

8 FREQ=

27.716 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000 2

0.26378E-02 4

0.10313E-01 6

0.12564E-01 8

0.12479E-01 10

-0.47192E-03 12

-0.17891E-02 14

-0.65472E-02 16

-0.10230E-01 18 0.23241E-03 20 0.10233E-01 22 0.75928E-02 24

-0.39172E-02 26

-0.66480E-02

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

41 of 58 Building Sheet Rev.:

001 MAXIMUM ABSOLUTE VALUES NODE 6

VALUE 0.125S4E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

9 FREQ=

27.716 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 DX 0.0000 0.82021E-02 0.32067E-01 0.39067E-01 0.38803E-01

-0.14674E-02

-0.55629E-02

-0.20358E-01

-0.31809E-01 0.72267E-03 0.31818E-01 0.23609E-01

-0.12180E-01

-0.20671E-01 MAXIMUM ABSOLUTE VALUES NODE 6

VALUE 0.39067E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

10 FREQ=

28.013 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000 2

-0.20542E-12 4

0.62930E-12 6

0.92273E-12 8

-0.13682E-11 10

-0.75884E-13 12 0.37662E-12 14

-0.36824E-12 16 0.12844E-12 18 0.25652E-12 20 0.20651E-12 22 0.14237E-12 24

-0.53468E-12 26 0.14123E-12 MAXIMUM ABSOLUTE VALUES NODE 8

VALUE

-0.13682E-11 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

11 FREQ=

33.622 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000 2

0.88718E-03 4

0.33479E-02 6

0.35899E-02

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

42 of 58 Building Sheet Rev.:

001 8

0.32511E-02 10

-0.32838E-02 12

-0.34973E-02 14

-0.34244E-02 16 0.24728E-02 18 0.28779E-02 20

-0.19095E-02 22

-0.31534E-02 24 0.86390E-03 26 0.18235E-02 MAXIMUM ABSOLUTE VALUES NODE 6

VALUE 0.35899E-02 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

12 FREQ=

33.622 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 MAXIMUM NODE VALUE ux 0.0000 0.83001E-02 0.31322E-01 0.33586E-01 0.30416E-01

-0.30722E-01

-0.32720E-01

-0.32037E-01 0.23135E-01 0.26925E-01

-0.17865E-01

-0.29502E-01 0.80823E-02 0.17060E-01 ABSOLUTE VALUES 6

0.33586E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

13 FREQ=

41.194 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 MAXIMUM NODE VALUE UX 0.0000 0.42070E-03 0.14711E-02 0.12095E-02 0.86507E-03

-0.29339E-02

-0.27148E-02

-0.85920E-03 0.55325E-02

-0.50018E-02

-0.20435E-02 0.57855E-02

-0.59720E-03

-0.23404E-02 ABSOLUTE VALUES 22 0.57855E-02 POST1 NODAL DEGREE OF FREEDOM LISTING

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

43 of 58 Building Sheet Rev.:

001 LOAD STEP=

1 SOBSTEP=

14 FREQ=

41.194 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 OX 0.0000 0.30988E-02 0.10836E-01 0.89092E-02 0.63719E-02

-0.21610E-01

-0.19997E-01

-0.63287E-02 0.40751E-01

-0.36842E-01

-0.15052E-01 0.42615E-01

-0.43989E-02

-0.17239E-01 MAXIMUM ABSOLUTE VALUES NODE 22 VALUE 0.42615E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

15 FREQ=

46.476 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 UX 0.0000

-0.22714E-12 0.82734E-12

-0.38461E-11 0.14723E-11

-0.13552E-12

-0.50272E-13

-0.51866E-13 0.40137E-13 0.48450E-13

-0.31643E-13

-0.52821E-13 0.13931E-13 0.30975E-13 MAXIMUM ABSOLUTE VALUES NODE 6

VALUE

-0.38461E-11 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

16 FREQ=

4 8.400 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 UX 0.0000 0.28604E-03 0.94629E-03 0.54721E-03 0.23393E-03

-0.21368E-02

-0.17594E-02 0.60856E-03 0.41505E-02

-0.91920E-02 0.11800E-01

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

44 of 58 Building Sheet Rev.:

001 22

-0.87131E-02 24 0.58944E-04 26 0.29778E-02 MAXIMUM ABSOLUTE VALUES NODE 20 VALUE 0.11800E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

17 FREQ=

48.400 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000 2

0.11990E-02 4

0.39665E-02 6

0.22937E-02 8

0.98055E-03 10

-0.89569E-02 12

-0.73749E-02 14 0.25509E-02 16 0.17397E-01 18

-0.38530E-01 20 0.49460E-01 22

-0.36523E-01 24 0.24707E-03 26 0.12482E-01 MAXIMUM ABSOLUTE VALUES NODE 20 VALUE 0.49460E-01 poSTl NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

18 FREQ=

58.470 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000 2

0.19073E-02 4

0.53489E-02 6

0.52131E-03 8

-0.18230E-02 10

-0.70285E-02 12

-0.46092E-02 14 0.81380E-02 16

-0.19937E-02 18 0.65389E-03 20

-0.22603E-03 22 0.70538E-04 24 0.25554E-04 26

-0.30842E-04 MAXIMUM ABSOLUTE VALUES NODE 14 VALUE 0.81380E-02 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

19 FREQ=

58.470 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

45 of 58 Building Sheet Rev.:

001 2

0.13773E-01 4

0.38626E-01 6

0.37645E-02 8

-0.13164E-01 10

-0.50754E-01 12

-0.33284E-01 14 0.58767E-01 16

-0.14397E-01 18 0.47219E-02 20

-0.16322E-02 22 0.50937E-03 24 0.18453E-03 26

-0.22272E-03 MAXIMUM ABSOLUTE VALUES NODE 14 VALUE 0.58767E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

20 FREQ=

63.84 4 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 MAXIMUM NODE VALUE UX 0.0000 0.46829E-12 0.19203E-11 0.73450E-12 0.12628E-11

-0.32455E-11

-0.38844E-11

-0.99392E-12 0.66030E-11

-0.59678E-11

-0.24424E-11 0.69080E-11

-0.71240E-12

-0.27947E-11 ABSOLUTE VALUES 22 0.69080E-11 ALL CURRENT ANSYS DATA WRITTEN TO FILE NAME=

SB_case2.db FOR POSSIBLE RESUME FROM THIS POINT EXIT THE ANSYS POST1 DATABASE PROCESSOR ROUTINE COMPLETED CP=

3.510

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

46 of 58 Building Sheet Rev.:

001

<Output file:

SB case3.out>

ANSYS SOLVE COMMAND NOTE CP

=

4.103 TIME=

16:33:30 There is no title defined for this analysis.

NOTE CP

=

4.103 TIME=

16:33:30 No modes are being expanded (MXPAND command) and therefore the element results will not be written to the mode file.

For more efficient calculation of element results in the expansion pass of any downstream mode superposition

analyses, expand all modes during the modal analysis.

SELECTION OF ELEMENT TECHNOLOGIES FOR APPLICABLE ELEMENTS GIVE SUGGESTIONS ONLY ELEMENT TYPE 1

IS BEAM188 KEYOPT(1)=1 IS SUGGESTED FOR NON-CIRCULAR CROSS SECTIONS AND KEYOPT(3)=2 IS ALWAYS SUGGESTED.

ELEMENT TYPE 1

IS BEAM188 KEYOPT(15)

IS ALREADY SET AS SUGGESTED.

SOLUTION OPTIONS PROBLEM DIMENSIONALITY 3-D DEGREES OF FREEDOM UX UY UZ ROTX ROTY ROTZ ANALYSIS TYPE MODAL EXTRACTION METHOD PCG LANCZOS NUMBER OF MODES TO EXTRACT 20 GLOBALLY ASSEMBLED MATRIX SYMMETRIC LOAD STEP OPTIONS LOAD STEP NUMBER 1

NOTE CP

=

4.134 TIME=

16:33:30 The PCG solver has automatically set the level of difficulty for this model to 5.

CENTER OF

MASS, MASS, AND MASS MOMENTS OF INERTIA CALCULATIONS ASSUME ELEMENT MASS AT ELEMENT CENTROID TOTAL MASS

=

1538.1 MOM.

OF INERTIA MOM.

OF INERTIA CENTER OF MASS ABOUT ORIGIN ABOUT CENTER OF MASS XC

=

YC

=

ZC

=

0.0000 702.26 0.0000 IXX

=

IYY

=

IZZ

=

IXY

=

IYZ

=

IZX

=

0.7672E+09 0.000 0.7672E+09 0.000 0.000 0.000 IXX

=

IYY

=

IZZ

=

IXY

=

IYZ

=

IZX

=

0.8654E+07 0.000 0.8654E+07 0.000 0.000 0.000 MASS

SUMMARY

BY ELEMENT TYPE TYPE MASS 2

1538.07 Range of element maximum matrix coefficients in global coordinates

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 47 of 58 001 Maximum

=

4.146594576E+11 at element 6.

Minimum

=

4.566439999E+10 at element 5.

ELEMENT MATRIX FORMULATION TIMES TYPE NUMBER ENAME TOTAL CP AVE CP 1

13 BEAM188 2

13 MASS21 Time at end of element Form Preconditioner

=

Load Step=

1 Mode=

1.

curEqn=

14 totEqn Factor Done=

1%

Iteration=

12 Number 22 Number 30 Number 32 Number 33 Number 34 Number 35 Number 36 Number 37 Number 0.000 0.000000 0.000 0.000000 matrix formulation CP

=

4.13402653.

0 Cum.

Iter.=

1 CP' 4.150 Iteration=

Iteration=

Iteration' Iteration=

Iteration=

Iteration' Iteration=

Iteration=

38 Number 39 Number 84 Job CP sec=

4.165 Factor Wall sec=

37.5 of eigenvalues converged' of eigenvalues converged=

of eigenvalues converged=

of eigenvalues converged' of eigenvalues converged' of eigenvalues converged=

of eigenvalues converged=

of eigenvalues converged' of eigenvalues converged' of eigenvalues converged' rate' 0

5 10 19 20 20 20 20 20 20 20 20 Wall' Wall=

Wall=

Wall' Wall=

Wall=

Wall'

.0 Mflops 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 PCG LANCZOS EIGENSOLVER HAS CONVERGED SUCCESSFULLY THE REQUESTED 20 MODES HAVE BEEN FOUND SUCCESSFULLY ANSYS ENGINEERING ANALYSIS SYSTEM RELEASE 13.0 ANSYS Professional NLS 00203236 VERSION=WINDOWS x64 16:33:30 JUL 02, 2013 CP=

4.196 FREQUENCIES FROM PCG LANCZOS ITERATION MODE FREQUENCY (HERTZ) 1 2

3 4

5 6

7 8

9 10 11 12 13 14 15 16 17 18 19 20 2.903994305065 2.903994305065 9.340880515069 10.19987239561 10.19987239561 19.65158518424 19.65158518424 27.86844239898 27.86844239898 28.21483087499 33.88659668099 33.88659668099 41.31990737496 41.31990737496 46.57583122022 48.63280165716 48.63280165716 58.65294849131 58.65294849131 64.09646437767 ANSYS ENGINEERING ANALYSIS SYSTEM RELEASE 13.0 ANSYS Professional NLS 00203236 VERSION=WINDOWS x64 16:33:30 JUL 02, 2013 CP=

4.196

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 48 of 58 001 PARTICIPATION FACTOR CALCULATION X

DIRECTION MODE 1

2 3

4 5

6 7

8 9

10 11 12 13 14 15 16 17 18 19 20 sum FREQUENCY 2.90399 2.90399 9.34088 10.1999 10.1999 19.6516 19.6516 27.8684 27.8684 28.2148 33.8866 33.8866 41.3199 41.3199 46.5758 48.6328 48.6328 58.6529 58.6529 64.0965 PERIOD 0.34435 0.34435 0.10706 0.98040E-01 0.98040E-01 0.50886E-01 0.50886E-01 0.35883E-01 0.35883E-01 0.35442E-01 0.29510E-01 0.29510E-01 0.24201E-01 0.24201E-01 0.21470E-01 0.20562E-01 0.20562E-01 0.17049E-01 0.17049E-01 0.15601E-01 PARTIC.FACTOR 33.488 1.8394 0.19806E-08 0.89099 15.923 0.40886 7.6834

-1.4923 5.5324

-0.47608E-10 0.44365 3.9674 1.0257 0.12381

-0.11740E-10 0.28021 0.64977E-01 1.9067 0.26326 0.75879E-10 RATIO 1.000000 0.054926 0.000000 0.026606 0.475473 0.012209 0.229434 0.044563 0.165202 0.000000 0.013248 0.118469 0.030627 0.003697 0.000000 0.008367 0.001940 0.056936 0.007861 0.000000 EFFECTIVE MASS 1121.48 3.38340 0.392291E-17 0.793866 253.538 0.167164 59.0347 2.22709 30.6069 0.226654E-20 0.196829 15.7399 1.05196 0.153285E-01 0.137823E-21 0.785171E-01 0.422199E-02 3.63548 0.693048E-01 0.575763E-20 1492.02 CUMULATIVE MASS FRACTION 0.751651 0.753918 0.753918 0.754450 0.924379 0.924492 0.964058 0.965551 0.986065 0.986065 0.986197 0.996746 0.997451 0.997461 0.997461 0.997514 0.997517 0.999954 1.00000 1.00000 RATIO EFF.MASS TO TOTAL MASS 0.729145 0.219976E-02 0.255053E-20 0.516143E-03 0.164841 0.108684E-03 0.383822E-01 0.144797E-02 0.198995E-01 0.147362E-23 0.127971E-03 0.102335E-01 0.683947E-03 0.996602E-05 0.896078E-25 0.510490E-04 0.274498E-05 0.236366E-02 0.450595E-04 0.374340E-23 0.970058 PARTICIPATION FACTOR CALCULATION DIRECTION MODE FREQUENCY PERIOD PARTIC.FACTOR RATIO EFFECTIVE MASS CUMULATIVE MASS FRACTION RATIO EFF.MASS TO TOTAL MASS 1

2.90399 0.34435 0.26088E-08 0.000000 0.680607E-17 0.461946E-20 0.442506E-20 2

2.90399 0.34435 0.84342E-09 0.000000 0.711365E-18 0.510228E-20 0.462504E-21 3

9.34088 0.10706 35.565 1.000000 1264.90 0.858518 0.822389 4

10.1999 0.98040E-01 0.14892E-08 0.000000 0.221759E-17 0.858518 0.144180E-20 5

10.1999 0.98040E-01

-0.13696E-09 0.000000 0.187571E-19 0.858518 0.121952E-22 6

19.6516 0.50886E-01

-0.45782E-08 0.000000 0.209599E-16 0.858518 0.136274E-19 7

19.6516 0.50886E-01

-0.10267E-08 0.000000 0.105407E-17 0.858518 0.685320E-21 8

27.8684 0.35883E-01 0.13152E-11 0.000000 0.172967E-23 0.858518 0.112457E-26 9

27.8684 0.35883E-01

-0.30908E-11 0.000000 0.955306E-23 0.858518 0.621105E-26 10 28.2148 0.35442E-01 11.459 0.322185 131.300 0.947635 0.853667E-01 11 33.8866 0.29510E-01

-0.17209E-08 0.000000 0.296136E-17 0.947635 0.192537E-20 12 33.8866 0.29510E-01 0.54839E-09 0.000000 0.300734E-18 0.947635 0.195526E-21 13 41.3199 0.24201E-01

-0.23499E-09 0.000000 0.552214E-19 0.947635 0.359030E-22 14 41.3199 0.24201E-01 0.15893E-10 0.000000 0.252601E-21 0.947635 0.164232E-24 15 46.5758 0.21470E-01

-6.9125 0.194361 47.7832 0.980067 0.310669E-01 16 48.6328 0.20562E-01 0.10319E-09 0.000000 0.106479E-19 0.980067 0.692288E-23 17 48.6328 0.20562E-01

-0.37906E-10 0.000000 0.143686E-20 0.980067 0.934192E-24 18 58.6529 0.17049E-01

-0.34777E-12 0.000000 0.120945E-24 0.980067 0.786342E-28 19 58.6529 0.17049E-01

-0.17527E-09 0.000000 0.307188E-19 0.980067 0.199722E-22 20 64.0965 0.15601E-01 5.4193 0.152376 29.3688 1.00000 0.190946E-01 sum 1473.35 0.957918 PARTICIPATION FACTOR CALCULATION 2

DIRECTION CUMULATIVE RATIO EFF.MASS MODE FREQUENCY PERIOD PARTIC.FACTOR RATIO EFFECTIVE MASS MASS FRACTION TO TOTAL MASS 1

2.90399 0.34435

-1.8394 0.054926 3.38340 0.226766E-02 0.219976E-02

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 49 of 58 001 2

3 4

5 6

7 8

9 10 11 12 13 14 15 16 17 18 19 20 2.90399 9.34088 10.1999 10.1999 19.6516 19.6516 27.8684 27.8684 28.2148 33.8866 33.8866 41.3199 41.3199 46.5758 48.6328 48.6328 58.6529 58.6529 64.0965 0.34435 0.10706 0.98040E-01 0.98040E-01 0.50886E-01 0.50886E-01 35883E-01 35883E-01 35442E-01 29510E-01 29510E-01 24201E-01 0.24201E-01 0.21470E-01 20562E-01 20562E-01 17049E-01 17049E-01 0.15601E-01 33.488

-0.27147E-09 15.923

-0.89099 7.6834

-0.40886 5.5324 1.4923

-0.82402E-09 3.9674

-0.44365

-0.12381 1.0257 0.12812E-10

-0.64977E-01 0.28021

-0.26326 1.9067 0.65489E-09 1.000000 0.000000 0.475473 0.026606 0.229434 0.012209 0.165202 0.044563 0.000000 0.118469 0.013248 0.003697 0.030627 0.000000 001940 008367 007861 056936 000000 1121.48 0.736976E-19 253.538 0.793866 59.0347 0.167164 30.6069 2.22709 0.679016E-18 15.7399 0.196829 0.153285E-01 1.05196 0.164151E-21 0.422199E-02 0.785171E-01 0.693048E-01 3.63548 0.428879E-18 0.753918 753918 923847 924379 0.963946 0.964058 0.984572 0.986065 0.986065 0.996614 0.996746 0.996756

.997461

.997464

.997517

.997563 1.00000 1.00000 0.729145 0.479155E-22 0.164841 0.516143E-03 0.383822E-01 0.108684E-03 0.198995E-01

.144797E-02

.441471E-21

.102335E-01

.127971E-03 0.996602E-05 0.683947E-03 0.106725E-24 0.274498E-05 0.510490E-04 0.450595E-04 0.236366E-02 0.278842E-21 1492.02 0.970058 PARTICIPATION FACTOR CALCULATION

ROTX DIRECTION MODE 1

2 3

4 5

6 7

8 9

10 11 12 13 14 15 16 17 18 19 20 sum FREQUENCY 2.90399 2.90399 9.34088 10.1999 10.1999 19.6516 19.6516 27.8684 27.8684 28.2148 33.8866 33.8866 41.3199 41.3199 46.5758 48.6328 48.6328 58.6529 58.6529 64.0965 PERIOD 0.34435 0.34435 0.10706 0.98040E-01 0.98040E-01 0.50886E-01 0.50886E-01 0.35883E-01 0.35883E-01 0.35442E-01 0.29510E-01 0.29510E-01 0.24201E-01 0.24201E-01 0.21470E-01 0.20562E-01 0.20562E-01 0.17049E-01 0.17049E-01 0.15601E-01 PARTIC.FACTOR

-1375.3 25039.

-0.15483E-06 9271.2

-518.79 4474.8

-238.12 3140.5 847.15

-0.48008E-06 2265.1

-253.30

-69.358 574.58 0.72746E-08

-37.576 162.04

-148.77 1077.5 0.36686E-06 RATIO 0.054926 1.000000 0.000000 0.370277 0.020719 0.178718 0.009510 0.125428 0.033834 0.000000 0.090466 0.010116 0.002770 0.022948 0.000000 0.001501 0.006472 0.005942 0.043034 0.000000 EFFECTIVE MASS 0.189138E+07 0.626927E+09 0.239709E-13 0.859549E+08 269138.

0.200241E+08 56700.6 0.986288E+07 717664.

0.230474E-12 0.513088E+07 64161.9 4810.59 330141.

0.529203E-16 1411.96 26258.5 22133.3 0.116104E+07 0.134584E-12 0.752445E+09 CUMULATIVE MASS FRACTION 0.251365E-02 0.835701 0.835701 0.949935 0.950293 0.976905 0.976980 0.990088 0.991041 0.991041 0.997860 0.997946 0.997952 0.998391 0.998391 0.998393 0.998428 0.998457 1.00000 1.00000 PARTICIPATION FACTOR CALCULATION

- - - - ROTY DIRECTION ODE 1

2 3

4 5

6 7

8 9

10 FREQUENCY 2.90399 2.90399 9.34088 10.1999 10.1999 19.6516 19.6516 27.8684 27.8684 28.2148 PERIOD 0.34435 0.34435 0.10706 0.98040E-01 0.98040E-01 0.50886E-01 0.50886E-01 0.35883E-01 0.35883E-01 0.35442E-01 PARTIC.FACTOR 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 RATIO 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 EFFECTIVE MASS 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 CUMULATIVE MASS FRACTION 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000

Attachment A:

Evaluation of the Seismic Analysis Loading Calc.

No:

Considering the Observed Laminar Cracking of the Shield Sheet No:

Building Sheet Rev.:

C-CSS-099.20-063, Rev. 001 50 of 58 001 11 12 13 14 15 16 17 18 19 20 33.8866 33.8866 41.3199 41.3199 46.5758 48.6328 48.6328 58.6529 58.6529 64.0965 0.29510E-01 0.29510E-01 0.24201E-01 0.24201E-01 0.21470E-01 0.20562E-01 0.20562E-01 0.17049E-01 0.17049E-01 0.15601E-01 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 PARTICIPATION FACTOR CALCULATION

- - - - ROTZ DIRECTION MODE 1

2 3

4 5

6 7

8 9

10 11 12 13 14 15 16 17 18 19 20 sum NOTE Solution FREQUENCY 2.90399 2.90399 9.34088 10.1999 10.1999 19.6516 19.6516 27.8684 27.8684 28.2148 33.8866 33.8866 41.3199 41.3199 46.5758 48.6328 48.6328 58.6529 58.6529 64.0965 is done!

PERIOD 0.34435 0.34435 0.10706 0.98040E-01 0.98040E-01 0.50886E-01 0.50886E-01 0.35883E-01 0.35883E-01 0.35442E-01 0.29510E-01 0.29510E-01 0.24201E-01 0.24201E-01 0.21470E-01 0.20562E-01 0.20562E-01 0.17049E-01 0.17049E-01 0.15601E-01 PARTIC.FACTOR

-25039.

-1375.3

-0.11336E-05

-518.79

-9271.2

-238.12

-4474.8 847.15

-3140.5 0.27549E-07

-253.30

-2265.1

-574.58

-69.358 0.66344E-08

-162.04

-37.576

-1077.5

-148.77

-0.42505E-07 CP

=

RATIO 1.000000 0.054926 0.000000 0.020719 0.370277 0.009510 0.178718 0.033834 0.125428 0.000000 0.010116 0.090466 0.022948 0.002770 0.000000 0.006472 0.001501 0.043034 0.005942 0.000000 4.196 TIME EFFECTIVE MASS 0.626927E+09 0.189138E+07 0.128505E-11 269138.

0.859549E+08 56700.6 0.200241E+08 717664.

0.986288E+07 0.758927E-15 64161.9 0.513088E+07 330141.

4810.59 0.440159E-16 26258.5 1411.96 0.116104E+07 22133.3 0.180670E-14 0.752445E+09 16:33:30 CUMULATIVE MASS FRACTION 0.833187 0.835701 0.835701 0.836058 0.950293 0.950368 0.976980 0.977934 0.991041 0.991041 0.991127 0.997946 0.998384 0.998391 0.998391 0.998426 0.998428 0.999971 1.00000 1.00000 ANSYS BINARY FILE STATISTICS BUFFER SIZE USED=

16384 0.062 MB WRITTEN ON ELEMENT MATRIX FILE:

SB_case3.emat 0.0 62 MB WRITTEN ON ELEMENT SAVED DATA FILE:

SB_case3.esav 0.062 MB WRITTEN ON MODAL MATRIX FILE:

SB_case3.mode FINISH SOLUTION PROCESSING ROUTINE COMPLETED CP

=

4.228 ANSYS RESULTS INTERPRETATION (POST1)

ENTER

/SHOW,DEVICE-NAME TO ENABLE GRAPHIC DISPLAY ENTER FINISH TO LEAVE POST1

DO LOOP ON PARAMETER=

I FROM 1.0000 TO 20.000 BY 1.0000 USE LOAD STEP SUBSTEP SET COMMAND GOT LOAD STEP=

TIME/FREQUENCY=

2.9040 TITLE=

1 FOR LOAD CASE 0

1 SUBSTEP=

1 CUMULATIVE ITERATION=

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

51 of 58 Building Sheet Rev.:

001 PRINT U

NODAL SOLUTION PER NODE POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

1 FREQ=

2.9040 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 MAXIMUM NODE VALUE UX 0.0000 0.55130E-03 0.26348E-02 0.43836E-02 0.52209E-02 0.10538E-01 0.11147E-01 0.13561E-01 0.19522E-01 0.24872E-01 0.30143E-01 0.34900E-01 0.39359E-01 0.41084E-01 ABSOLUTE VALUES 26 0.41084E-01

ENDDO INDEX=

I POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

2 FREQ=

2.904 0 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000 2

0.30281E-04 4

0.14472E-03 6

0.24077E-03 8

0.28676E-03 10 0.57882E-03 12 0.61226E-03 14 0.74486E-03 16 0.10723E-02 18 0.13662E-02 20 0.16557E-02 22 0.19169E-02 24 0.21619E-02 26 0.22566E-02 MAXIMUM ABSOLUTE VALUES NODE 2 6 VALUE 0.22566E-02 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

3 FREQ=

9.34 09 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000 2

-0.19330E-10 4

0.50266E-10 6

0.12001E-10

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

52 of 58 Building Sheet Rev.:

001 8

-0.40027E-11 10 0.77401E-12 12

-0.10464E-12 14

-0.79245E-11 16

-0.16349E-10 18 0.13958E-10 20 0.88367E-11 22

-0.62606E-11 24

-0.97573E-12 26

-0.22339E-12 MAXIMUM ABSOLUTE VALUES NODE 4

VALUE 0.50266E-10 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

4 FREQ=

10.200 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 MAXIMUM NODE VALUE UX 0.0000 0.17436E-03 0.73844E-03 0.11130E-02 0.12653E-02 0.19125E-02 0.19521E-02 0.20453E-02 0.18571E-02 0.12557E-02 0.36002E-03

-0.60007E-03

-0.15301E-02

-0.18179E-02 ABSOLUTE VALUES 14 0.20453E-02 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

5 FREQ=

10.200 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 MAXIMUM NODE VALUE UX 0.0000 0.31160E-02 0.13197E-01 0.19891E-01 0.22613E-01 0.34179E-01 0.34885E-01 0.36552E-01 0.33188E-01 0.22441E-01 0.64339E-02

-0.10724E-01

-0.27344E-01

-0.32488E-01 ABSOLUTE VALUES 14 0.36552E-01 POST1 NODAL DEGREE OF FREEDOM LISTING

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

53 of 58 Building Sheet Rev.:

001 LOAD STEP=

1 SOBSTEP=

6 FREQ=

19.652 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 MAXIMUM NODE VALUE ux 0.0000 0.29700E-03 0.12245E-02 0.17090E-02 0.18532E-02 0.17511E-02 0.16526E-02 0.11274E-02

-0.70729E-03

-0.17775E-02

-0.16384E-02

-0.46827E-03 0.11138E-02 0.14701E-02 ABSOLUTE VALUES 8

0.18532E-02 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

7 FREQ=

19.652 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 MAXIMUM NODE VALUE UX 0.0000 0.55814E-02 0.23011E-01 0.32117E-01 0.34827E-01 0.32908E-01 0.31057E-01 0.21186E-01

-0.13292E-01

-0.33404E-01

-0.30789E-01

-0.87998E-02 0.20932E-01 0.27627E-01 ABSOLUTE VALUES 8

0.34827E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

8 FREQ=

27.868 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 UX 0.0000

-0.21728E-02

-0.85167E-02

-0.10452E-01

-0.10433E-01

-0.16644E-03 0.97312E-03 0.51856E-02 0.89807E-02 0.30444E-03 20

-0.86257E-02

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

54 of 58 Building Sheet Rev.:

001 22

-0.69147E-02 24 0.33727E-02 26 0.56855E-02 MAXIMUM ABSOLUTE VALUES NODE 6

VALUE

-0.10452E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

9 FREQ=

27.8 68 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 UX 0.0000 0.80550E-02 0.31573E-01 0.38747E-01 0.38676E-01 0.61703E-03

-0.36075E-02

-0.19224E-01

-0.33293E-01

-0.11286E-02 0.31977E-01 0.25634E-01

-0.12503E-01

-0.21077E-01 MAXIMUM ABSOLUTE VALUES NODE 6

VALUE 0.38747E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

10 FREQ=

28.215 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 UX 0.0000

-0.38571E-12 0.15359E-12 0.14341E-11

-0.11092E-11

-0.25788E-12 0.43023E-12

-0.21035E-12 0.70362E-13 0.20140E-12 0.16603E-12 0.14371E-12

-0.55239E-12 0.23017E-12 MAXIMUM ABSOLUTE VALUES NODE 6

VALUE 0.14341E-11 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

11 FREQ=

33.887 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

55 of 58 Building Sheet Rev.:

001 2

4 6

8 10 12 14 16 18 20 22 24 26 MAXIMUM NODE VALUE 0.95578E-03 0.36143E-02 0.39101E-02 0.35651E-02

-0.33537E-02

-0.36189E-02

-0.36945E-02 0.23190E-02 0.31136E-02

-0.17333E-02

-0.33326E-02 0.86586E-03 0.18121E-02 ABSOLUTE VALUES 6

0.39101E-02 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

12 FREQ=

33.887 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 UX 0.0000 0.85470E-02 0.32320E-01 0.34966E-01 0.31881E-01

-0.29990E-01

-0.32362E-01

-0.33038E-01 0.20737E-01 0.27843E-01

-0.15500E-01

-0.29802E-01 0.77429E-02 0.16205E-01 MAXIMUM ABSOLUTE VALUES NODE 6

VALUE 0.34966E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

13 FREQ=

41.320 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000 2

0.32772E-02 4

0.11547E-01 6

0.97706E-02 8

0.71982E-02 10

-0.22245E-01 12

-0.20721E-01 14

-0.70257E-02 16 0.41184E-01 18

-0.35695E-01 20

-0.16878E-01 22 0.42378E-01 24

-0.42698E-02 26

-0.16317E-01 MAXIMUM ABSOLUTE VALUES NODE 22 VALUE 0.42378E-01

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

56 of 58 Building Sheet Rev.:

001 pQSTl NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

14 FREQ=

41.320 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 MAXIMUM NODE VALUE UX 0.0000 0.39560E-03 0.13939E-02 0.11794E-02 0.86890E-03

-0.26852E-02

-0.25013E-02

-0.84809E-03 0.49714E-02

-0.43088E-02

-0.20373E-02 0.51156E-02

-0.51541E-03

-0.19696E-02 ABSOLUTE VALUES 22 0.51156E-02 poSTl NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

15 FREQ=

4 6.57 6 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000 2

-0.49154E-12 4

0.18051E-11 6

-0.91804E-11 8

0.32947E-11 10 0.16108E-11 12

-0.45365E-11 14 0.27692E-12 16

-0.32234E-14 18 0.41592E-14 20

-0.20975E-14 22

-0.36884E-15 24

-0.50496E-14 26 0.56057E-14 MAXIMUM ABSOLUTE VALUES NODE 6

VALUE

-0.91804E-11 pQSTl NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

16 FREQ=

48.633 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000 2

0.12455E-02 4

0.41326E-02 6

0.24783E-02 8

0.11386E-02 10

-0.93824E-02 12

-0.77529E-02 14 0.26035E-02

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

57 of 58 Building Sheet Rev.:

001 16 0.17815E-01 18

-0.39262E-01 20 0.49646E-01 22

-0.35563E-01 24 0.28697E-03 26 0.11588E-01 MAXIMUM ABSOLUTE VALUES NODE 20 VALUE 0.49646E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

17 FREQ=

48.633 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 MAXIMUM NODE VALUE ux 0.0000 0.28881E-03 0.95830E-03 0.57470E-03 0.26402E-03

-0.21757E-02

-0.17978E-02 0.60372E-03 0.41310E-02

-0.91044E-02 0.11512E-01

-0.82465E-02 0.66545E-04 0.26870E-02 ABSOLUTE VALUES 20 0.11512E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

18 FREQ=

58.653 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE UX 1

0.0000 2

0.12290E-01 4

0.34978E-01 6

0.49809E-02 8

-0.10183E-01 10

-0.52169E-01 12

-0.34503E-01 14 0.59519E-01 16

-0.14759E-01 18 0.49161E-02 20

-0.17120E-02 22 0.52441E-03 24 0.25763E-03 26

-0.25775E-03 MAXIMUM ABSOLUTE VALUES NODE 14 VALUE 0.59519E-01 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SUBSTEP=

19 FREQ=

58.653 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM

Attachment A:

Evaluation of the Seismic Analysis Loading Calc. No:

C-CSS-099.20-063, Rev. 001 Considering the Observed Laminar Cracking of the Shield Sheet No:

58 of 58 Building Sheet Rev.:

001 NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 UX 0.0000 0.16968E-02 0.48294E-02 0.68772E-03

-0.14059E-02

-0.72030E-02

-0.47638E-02 0.82178E-02

-0.20378E-02 0.67877E-03

-0.23638E-03 0.72405E-04 0.35572E-04 26

-0.35587E-04 MAXIMUM ABSOLUTE VALUES NODE 14 VALUE 0.82178E-02 POST1 NODAL DEGREE OF FREEDOM LISTING LOAD STEP=

1 SDBSTEP=

20 FREQ=

64.096 LOAD CASE=

0 THE FOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM NODE 1

2 4

6 8

10 12 14 16 18 20 22 24 26 MAXIMUM NODE UX 0.0000 0.14628E-12 0.12141E-11

-0.83437E-12 0.10169E-11 0.19232E-11

-0.10827E-10 0.15872E-13 0.31611E-11

-0.27497E-11

-0.12983E-11 0.32625E-11

-0.32872E-12

-0.12566E-11 ABSOLUTE VALUES 12 VALUE

-0.10827E-10 ALL CURRENT ANSYS DATA WRITTEN TO FILE NAME=

SB_case3.db FOR POSSIBLE RESUME FROM THIS POINT EXIT THE ANSYS POST1 DATABASE PROCESSOR ROUTINE COMPLETED CP

=

4.274

v t e Letter Sequence Other
TAC:ME4640, Steam Generator Tube Integrity (Approved, Closed)
Initiation Request, Request, Request, Request, Request, Request, Request, Request, Request, Request, Request Acceptance, Acceptance Supplement, Supplement, Supplement, Supplement, Supplement, Supplement, Supplement, Supplement, Supplement, Supplement, Supplement, Supplement, Supplement, Supplement Administration Withholding Request Acceptance Meeting Questions 28 February 2011 17 February 2011 17 March 2011 21 March 2011 18 March 2011 5 April 2011 30 March 2011 20 April 2011 2 May 2011 19 May 2011 20 June 2011 11 July 2011 12 July 2011 21 July 2011 21 July 2011 27 July 2011 11 August 2011 12 September 2011 9 September 2011 22 September 2011 11 October 2011 8 November 2011 22 November 2011 2 December 2011 2 December 2011 2 December 2011 27 December 2011 13 December 2011 21 December 2011 29 December 2011 12 July 2011 12 July 2011 12 July 2011 23 January 2012 30 January 2012 19 January 2012 1 February 2012 9 February 2012 27 January 2012 21 February 2012 22 February 2012 2 March 2012 27 February 2012 22 February 2012 24 February 2012 16 February 2012 27 February 2012 15 May 2012 28 February 2012 2 April 2012 ... further results Answers 18 March 2011 23 March 2011 23 March 2011 15 April 2011 20 April 2011 5 May 2011 24 May 2011 3 June 2011 24 June 2011 17 June 2011 22 July 2011 26 August 2011 17 August 2011 16 September 2011 7 October 2011 21 October 2011 9 November 2011 23 November 2011 13 January 2012 5 April 2012 14 June 2012 11 July 2012 16 August 2012 20 November 2012 21 January 2013 12 February 2013 28 February 2013 14 March 2013 19 April 2013 31 January 2014 11 March 2014 3 July 2014 29 July 2014 16 September 2014 28 October 2014 28 January 2015 15 April 2011 29 April 2011 9 March 2012 25 May 2012 Results Approval, Approval, Approval, Approval, Approval, Approval, Approval, Approval, Approval, Approval, Approval, Approval, Approval, Approval Other: L-11-114, Drawing No. M-042B, Rev. 35, Sampling System Sh. 2 Local Grab Samples, L-11-131, Drawing No. LR-OS041A2, Revision 1, Operational Schematic Emergency Diesel Generator Systems, L-11-334, Reply to Request Additional Information for the Review of the License Renewal Application Amendment No. 21, L-12-337, Review of the Safety Evaluation Report with Open Items Related to the License Renewal, L-12-341, Firstenergy Nuclear Operating Cos Initial Status Report in Response to March 12, 2012 Commission Order Modifying Licenses with Regard to Requirements for Reliable Spent Fuel Pool Instrumentation (Order Number EA-12-051), L-12-444, Submittal of Contractor Equivalent Margins Assessments for Reactor Vessel Welds (Nonproprietary Versions), L-12-456, Notification of Closure of Commitments Related to the Review of the License Renewal Application, L-13-257, Notification of Completion of a License Renewal Commitment Related to the Review of License Renewal Application TAC No. ME4640) and License Renewal Application Amendment No. 45), L-13-330, License Renewal Application Amendment No. 46 - Annual Update, L-13-341, Review of the Safety Evaluation Report Related to the License Renewal of Davis-Besse Nuclear Power Station, L-14-085, License Renewal Application (TAC No. ME4640) Amendment No. 48, L-14-206, License Renewal Application Amendment No. 50 - Annual Update, L-15-120, Notification of Completion of License Renewal Commitments Related to the Review of the Davis-Besse Nuclear Power Station, Unit No. 1, License Renewal Application and License Renewal Application Amendment No. 55, L-15-139, License Renewal Reactor Vessel Internals Inspection Plan, L-15-214, License Renewal Application Amendment No. 59 - Annual Update, L-15-309, License Renewal Application Amendment No. 60, L-15-310, C-CSS-099.20-069, Rev 0, Shield Building Laminar Cracking Limits, ML111050091, ML11110A089, ML11110A091, ML11110A092, ML11110A093, ML11110A094, ML11110A095, ML11110A105, ML11110A106, ML11110A107, ML11122A014, ML11126A017, ML11126A018, ML11126A019, ML11126A020, ML11126A021, ML11126A022, ML11126A023, ML11126A024, ML11126A025, ML11126A026, ML11126A032, ML11126A033, ML11126A034, ML11126A035, ML11126A036, ML11126A037, ML11126A038, ML11126A039, ML11126A040, ML11126A041, ML11126A042, ML11126A043... further results
MONTHYEAR2011-02-17 [Table View]

ML15280A310

Text

SUMMARY

SUMMARY

SUMMARY

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