Text

Rev 1 to SAR for HN-215H Radwaste Shipping Cask
	ML20151V987
Person / Time
Site:	07109222
Issue date:	03/24/1988
From:	; WESTINGHOUSE HITTMAN NUCLEAR, INC.
To:	;
Shared Package
ML20151V968	List: ML20151V964; ML20151V987; ML20265D533; ML20265D538;
References
	STD-R-02-016, STD-R-02-016-R01, STD-R-2-16, STD-R-2-16-R1, NUDOCS 8805030263
	Download: ML20151V987 (130)
	v • d • e

{{#Wiki_filter:_ _ _ Docum nt Number: Rov: Rev Dct : WESTINGHOUSE STD-R-02-016 1 3-24-88 HITTMAN NUCLEAR M ': SAFETY ANALYSIS REPORT FOR THE HN-215H INCORPORATED 4 } RADWASTE SHIPPING CASK Prepared Checked Director Technical Q.A. Rev. Rev Dote By By E.1gineering Product Manager EWR sn clat te r ,q $( O 8 025 12-11-87 Y ', ~ i l#III h,bf of cd81 ECN 1 3-24-88 6 M IS 88-033 l l l l O FORM 01(B) p.g. 1 of 127 e80503o263 880325 PDR ADOCK 07109222 B PDR

i i i 4 i 9 l-i i ' i i 1 i i i i I l' l SAFETY ANALYSIS REPORT FOR THE ) HN-215H RADWASTE SHIPPING CASK i REVISION 1 j i Referencing 10CFK71 TYPE "A" Packaging Regulations STD-R-02-016 i I 1 i 1 I Westinghouse Radiological Services Division i 1256 North Church Street Moorestown, New Jersey 08057 i j 3 d 0024k l

STD-R-02-016 TO THE USER This document and the referenced drawings have been compiled to facilitate i the U.S. Nuclear Regulatory Commission review and certification process by presenting in a consolidated form all of the information pertinent to the certification of this cask. As such, this document is extensively based on excerpts of information and precedent in the public record associated with NRC certificate 71-9176, which describes casks similar in design to the one described herein. However, this document and the refe-enced drawings have been prepared to embody all of the design detail and commitments sufficient to warrant licensure and be appropriate for reference in a cask certificate. 1 O a 1 0 0024k i

STD-R-02-016 TABLE OF CONTENTS i ?.52 1.0 GENERAL INFORMATION 1-1 1.1 Purpose 1-1 i 1.2 Package Description 1-1 1.2.1 General Description 1-1 1.2.2 Materials of Construction, 1-1 Dimensions & Fabricating Methods 1.2.3 containment Vessel 1-2 i 1.2.4 Neucron Absorbers 1-2 1.2.5 Package Weight 1-2 1.2.6 Receptacles 1-2 1.2.7 Containment Penetrations 1-2 ) 1.2.8 Tiedown Lugs 1-3 1.2.9 Lifting Devices 1-3 1.2.10 Pressure Relief System 1-3 1.2.11 Heat Dissipation 1-3 l j 1.2.12 Coolants 1-3 1.2.13 Protrusions 1-3 1.2.14 Shielding 1-3 1.3 Operational Features 1-3 1.4 Contents of Packaging 1-4 l 4 i 2.0 STRUCTURAL EVALUATION 2-1 i i i 2.1 Structural Design 2-1 2.1.1 Discussion 2-1

l 2.1.2 Design Criteria 2-1 i

i i .i 0024k 11 j

STD-R-02-016 1 l TA3LE OF CONTENTS (continued) O ?*KL 2.2 Weights and Center of Gravity 2-1 f 2.3 Mechanical Properties of Materials 2-1 2.4 General Standards for all Packages 2-2 2.4.1 Chemical and Galvanic Reactions 2-2 2.4.2 Positive Closure 2-2 2.4.3 Lifting Devices 2-3 2.4.3.1 Package Lifting Lugs 2-3 1 2.4.3.2 Primary & Secondary Lifting 2-6 Lugs 2.4.4 Tiedowns 2-8 2.5 Standarda for Type "B" and Large Quantity Packaging 2-20 () 2.5.1 Load Resistance 2-20 2.5.2 External Pressure 2-21 l 2.6 Normal Conditions of Transport 2-22 i 2.6.1 Heat 2-22 2.6.2 Cold 2-22 l 2.6.3 Pressure 2-23 I i 2.6.4 Vibration 2-24 1 2.6.5 Water Spray 2-24 2.6.6 Free Drop 2-24 I I 2.6.6.1 Flat End Drop 2-25 2.6.6.2 Side Drop 2-26 1 2.6.6.3 Corner Drop 2-28 2.6.7 Corner Drop 2-51 ,j () 2.6.8 Penetration 2-51 i l I i 0024k 111

STD-R-02-016 TABLE OF CONTENTS (continued) = 2.7 Hypothetical Accident Conditions 2-51 2.8 Special Form 2-51 + 2.9 Fuel Rods 2-51 2.10 Appendix 2-52 2.10.1 Intentionally Blank 2-52 2.10.2 Volume and Area Estimates Corner 2-53 Impact on a cylinder 2.10.3 Cask Binder Specification 2-57 2.,10.4 Intentionally Blank 2-66 2.10.5 ANSYS Capabilities 2-67 2.10.6 Cask Lid Analysis 2-75 3.0 THERMAL EVALUATION 3-1 1 3.1 Discussion 3-1 3.2 Summary of Thermal Properties of Materials 3-3 3.3 Technical Specification of Components 3-3 a 3.4 Thermal Evaluation for Normal Conditions of 3-3 Transport 4 3.4.1 Thermal Model 3-3 3.4.2 Maximum Temperatures 3-4 3.4.3 Minimum Temperatures 3-4 i 3.4.4 Maximum Internal Pressures 3-4 J r 3.4.5 Maximum Thermal Stresses 3-5 3.4.6 Evaluation of Package Performance 3-5 for Normal Conditions of Transport 3.5 Hypothetical Thermal Accident Evaluation 3-5 1 J i 0024k iv i I

STD-R-02-016 TABLE OF CONTENTS (continued) O, i Dl&L 3.6 Appendix 3-5 4.0 CONTAINMENT 4-1 4.1 Containment Boundary 4-1 4.1.1 Containment Vessel 4-1 4.1.2 Containment Preparation 4-1 4.1.3 Seals and Welds 4-1 l 4.1.4 Closure 4-1 4.2 Requirements for Normal Conditions of Transport 4-1 4.2.1 Release of Radioactive Material 4-1 4.2.2 Pressurization of Containment Vessel 4-2 l 4.2.3 Coolant Centamination 4-2 O 4.2.4 Coolant Loss 4-2 1 4.3 Containment Requirements for the Hypothetical 4-2 i Accident Conditions 5.0 SHIELDING EVALUATION 5-1 i 5.1 Discussion and Results 5-1

6.0 CRITICALITY EVALUATION

6-1 i 7.0 OPERATING PROCEDURES 7-1 i 7.1 Lifting 7-1 7.2 Removal / Installation of Casks Lids 7-1 7.3 Cask Loading 7-3 7.4 Removal / Installation of Cask From Trailer 7-4 i 4 7.5 Containment Penetration Seals 7-5 J 7.6 Preparation for Shipment 7-5 7.7 Receiving a Loaded Cask 7-5 i 0024k v l 1

m__.___-_..__.. i-j. STD-R-02-016 l i l 1 j TABLE OF CONTENTS'(continued) i 4 i i M i t 8.0 ACCEPTANCE TESTS AND MAINTENANCE PROGRAM 8-1 8.1 Acceptance Tests 8-1 4 8.2 General Maintenance Program 8-2 i s j l .i i I, 1 -i i i i .i l i t J I i i i r i t l i 1 1 l i i 1 1 l. i I I i i i { l Ii i I@ l l i. r l 0024k vi i l L-.

STD-R-02-016 1.0 GENERAL INFORMATION l-1.1 Purpose The purpose of the following document is to provide the information and engineering analysis that demonstrates the performance capability and structural integrity of the HN-215H Radwaste Shipping Cask and its compliance with the requirements of 10CFR71. + 1.2 Package Description 1.2.1 General Description The HN-215H Shipping Cask is a top-loading, shielded container designed specifically for the safe transport of low specific activity radioactive waste materials between nuclear facilities and waste disposal sites. The radioactive materials can be packaged in a variety-of different type disposable containers. The HN-215H Shipping Cask is a primary containment vessel for radioactive materials. It consists of a cask body, cask lid, and a shield plug being basically a top-opening right circular cylinder which is on its vertical axis. Its principal dimensions are 83el/2 inches outside diameter by 92-1/4 inches high with p a cavity of 77-1/4 inches diameter by 80-1/4 inches V high. i 1.2.2 Materials of Construction, Dimensions and Fabricating Methods The c=W certifice' ua drawing for the RN-213M cast, drawing STD-02-077, provides the overall dimensions as well as the materials of constructions. The walls of the cask contain a lead thickness of 1-7/8 inches encased in a 3/8 inch thick inner steel shell and a 7/8 inch thick outer steel shell. The top and bottom ends of the cylindrical cask are constructed of a pair of 2 inch thick stacked steel plates. 1 The top serves as a removable cask lid and is secured to the cylindrical cask body by eight high strength ratchet binders. A 29 inch secondary cask lid is j located in the center of the primary lid and is secured to the primary lid by eight 3/4 inch studs. ) Lifting lugs and tiedown lugs are a structural part of i the package. 1 0024k 1-1 j ,,----,---re ,- - ~ - - - - -. - +,-

,---n,

STD-R-02-016 1.2.3 Containment Vessel The inner shell and inner end plates of each cask serve as the containment vessel and its mechanical configuration is described in the foregoing paragraph. A 50 Durometer neoprene gasket is employed in both the i primary and secondary lid interfaces. Waste products will be contained in 55 gallon drums, in heavy gauge disposable steel liners, in high integrity containers, in crates or other suitable palletized forms. 1.2.4 ' eutron Absorber g There are no materials used as neutron absorbers or moderators in the HN-215H package. 1.2.5 Gross Package We'ight The respective gross weights of the cask components and its designated maximum payload are as follows: Cask Body 31,800 Closure tid 5,450 O Shield Plug 1,150 Total Cask (unloaded) 38,400 lbs Maximum Payload 20,000 lbs Gross Package Weight 58,400 lbs 1.2.6 Receptacles I There are no internal or external structures j supporting or protecting receptacles. i 1.2.7 Containment Penetrations The cask is provided with a 3/4 inch pipe drain line sealed with a pipe plug. Its use is for removal of entrapped liquids, such as rain or decontamination l fluids. A pressure tap is also included in the primary lid design. It censists of a 1/4 inch diameter hole l drilled at a 30' angle through the lid top plate sealed with a pipe plug. i ) 0024k 1-2

STD-R-02-016 q 1.2.8 Tiedown Lugs Tiedown lugs are a structural part of the package. ' From the cask certification drawing, it can be seen that four reinforced tiedown lug locations are provided. Refer to Section 2.4.4 for a detailed s.nalysis of their structural integrity. 1.2.9 Lifting Devices Lifting devices are a structural part of the package. From the cask certification drawing, it can be seen that three reinforced lifting locations are provided. Refer to Section 2.4.3 for a detailed analysis of their structural integrity. 1.2.10 Pressure Relief System There are no pressure relief valves. 1.2.11 Heat Dissipation There are no special devices used for the dissipation of heat. The package maxinum structural design capacity is 400 watts. However, decay heat limits l based upon the shielding capabilities of the cask are l given on page 3-2. 1.2.12 Coolants There are no coolants involved. 1.2.13 Protrusions i There are no outer or inner protrusions, except for the lif ting and tiedown lugs described above. 1.2.14 Shielding The contents will be limited such that the radiolo-gical shielding provided will ensure compliance with DOT and IAEA regulatory requirements. Should lead slump occur, as the result of a flat end drop, the deeply steeped lid will provide full shielding protection. 1.3 Operations 1 Features Refer to the cask certification drawing of the packaging. There are no complex operational requirements connected with the HN-215H 1 i package and none that have any transport significance. 0024k 1-3

STD-R-02-016 1.4 Contents of Packaging This application is for transporting the following radioactive materials as defined in U.S.A. and I.A.E.A regulations: I a. Type "A" quantities in normal or special form; b. Fissile quantities are those limited to the amounts as generally licensed under 10 CFR 71.18 & 71.22; h c. L.S.A. materials greater than Type "A" quantities; d. The chemical and physical form of the package contents will be in all forms, other than liquids. This will include ion exchange resins in a devatored or solidified state, typical PWR or BWR solidified radioactive waste and miscellaneous contami-j nated materials such as pipe, wood, metal scrap, etc. All wastes will be contained within a separate disposable container. These containers will isolate the contents from the cask. O O 0024k 1-4

STD-R-02-016 O 2.0 ITRUCTURAL EVALUATION 2.1 Structural Design 2.1.1 Discussion The principal structural member of the HN-215H package is the containment vessel described in Section 1.2.1. The above components are identified on the cask certification drawing, drawing No. STD-02-077. A detailed discussion of the structural design and performance of these components will be provided below. 2.1.2 Design Criteria The HN-215H cask has been designed to be a simple, strong paskage that will provide maximum flexibility for usage as well as minimum potential exposure to operating personnel. Its size and shielding capacity will allow a variety of payloads to be safely transported. The shield top and bottom are constructed of two laminated steel plates. Cylindrical side valls have an external skin of.875 inches and an internal skin of.375 inches thick plate. These two plates encase a 1.88 inch thickness of lead. Pertinent dimensions of the HN-215H package are provided on the cask certification drawing. The package has been designed to provide well defined load paths which lend themselves to simple, highly reliable structural analysis methods. No new state-of-the-art approaches O have been used for analytical evaluation. All analytical techniques used throughout the SAR are proven methods that have been used in past submittals. Details of these methods are given where used. Regulatory Guide 7.8, "Load Combinations for the Structural Analysis of Shipping Casks", was used in evaluating the HN-215H package. Materials properties used in the analysis can be found in Section 2.3. 2.2 Weights and Center of Gravity The weight of the HN-215H cask and payload is summarized in Section 1.2.5. The center of gravity for the assembled package is located at the approximate geometric center of gravity. 2.3 Mechanical Properties of Materials The HN-215H package is fabricated of ASTM A516 Gr. 70 steel except as noted below. Material properties of the A516 steel are as follows: 70,000 psi F = g 38,000 psi F = eu l F, 42,000 psi (.6 Fg) = ! (N F,y 22,800 psi (.6 Fgy) d 0024k 2-1 _,--n

STD-R-02-016 The vertical plates of the lifting /tiedown lugs are constructed of ASTM s A514 or A517 steel. Material properties used for these steels are as follows: 110,000 to 135,000 psi F = eu 100,000 psi F = gy F, 66,000 to 81,000 psi (.6 Fg) = F,y 60,000 psi (.6 Ftu) = The lid standoffs are constructed of AISI 1018 or equivalent steel plate. Material properties used are as follows: 69,000 psi F = g 40,000 psi F = ey F, 41,400 psi (.6 Feu) = F,y 24,000 psi (.6 Feu) = Lead shielding will possess those properties referenced in ORNL-NSIC-68, Table 2.6, page 84. O Lid studs are fabricated of ASTM A320 Grade L-7 or equivalent steel. Properties used for analysis are as follows: Bar Properties (Per ASTM A320-78) 125,000 psi F = e 105,000 psi F = gy 2.4 General Standards This section demonstrates that the general standards for the package are met. 2.4.1 Chemical and Galvanic Reactions The shield is constructed from heavy structural steel plates. All exterior surfaces are primed and painted with high quality epoxy paint. There will be no galvanic, chemical or other reaction la air, nitrogen or water atmosphere. 2.4.2 Positive Closure j As described in Section 1.2.1, the positive closure system consists i of a primary lid secured by eight high strength ratchet binders and { a secondary lid affixed with eight 3/4 inch diameter studs. In l addition, each package will be sealed with an approved tamper indicating seal to prevent inadvertent and undetected opening. 0024k 2-2

STD-R-02-016 i O Calculate weld neutral axis assuming no contribution I b from the horizontal lugt d = Distance from horizontal lug center line to neutral axis (NA) j Section A d Axd j 1 (.854)(8) = 6.83 5.0 34.16 2 (.854)(11) = 9.39 - 6.5 -61.06 16.22 -26.90 -26.90 -1.66 in. d= = 16.22 The stress due to the moment is M M"I Wheret M = 219,000 in-lbs O i I z l+Ada+72+A22} I = 2(I gg =1 (.854) (8)8 = 36.4 in' I I t 12 J 8 A = (.854) (8) = 6.83 in j g I = 1.66 + 1.0 + 8.0 = 6.66 in d 2 i F 3 (.854) (11)s = 94.7 in' I I 2 12 8 A = (.854) (11) = 9.39 in 2 d = 1.0 + 5.5 - 1.66 = 4.84 in 2 = 2(36.4 + (6.83)(6.66)8 +494.7 + I j (9.39)(4.84) ) = 1308 in j C = 9.0 + 1,66 = 10.66 in l-1308 = 122.7 ins I 10.66 0024k 2-5

STD-R-02-016 2.4.3 Lifting Devices ( There are four lifting lugs for the package, three lifting lugs for the lid assembly (primary and secondary lids) and a single lifting lug for the secondary lid. All lifting lugs are evaluated versus the requirements of 10 CFR 71 Section 71.45. 2.4.3.1 Package Lifting Lugs For conservatism, the package is assumed to be lifted by only two of the four identical lifting lugs. The maximum package weight is 58,400 lbs. The lug load is calculated as: P = Wa /N; where W Package Weight = g Load Factor, 3 g's a = Number of lugs N = (58,400) (3)/2 87,600 lbs. P = O ^ P. Y 8 =19, e-IS A sl $l4/CI1 t'll Il 4 s.s o 1 .fN s7 O l 0024k 2-3

i I STD-R-02-016 4 Using the conventional 40' shear expression: d-{cs40') j yld F,y t(e P = 2(60,000) 2(2.5 M ces 40') = 2 r ) 370,200 lbs. = yld,3 M,s, EL 370,200 -1 +3.23 = = 87,600 The weld stresses are composed of pure shear and l tension / compression due to the moment. Pure shear on veldt F = s A i g I Wheret F, Shear Stress = A, Weld Area - Lw x tv = L, 2(8" + 11") = 38" (Considering only = the vertical i j welds attaching i the ASTM A514 plate to the i ~ cask.) i (.5")(1.00) + (.5")(.707) =.854" t = l (Groove + fillet wald) I l A 38" (.854") = 32.3 in.8 = I w j 600 )

Then, T*

2.712 psi i = a I 32.3 ? Moment force on Weldt i i Maximum Moment - M = 87,600 (2.5") = 219,000 in-lbs. f i !O i i 1 0024k 2-4 i i

STD-R-02-016

Then, q-

219,000 = 1785 psi y 122.7 Combined Stress: /(F,): + (p p F = K e = /(2712)8 + (1785)8 = 3247 psi The allowable stress for E70 weld rods is 30% of the tensile strength of 70,000 psi, or F, = (.30)(70,000) = 21,000 psi The lug veld Margin of Safety ist F 21.000 [-1= 3,247 - 1 = +5.47 M.S. = C Therefore, it can be safely concluded that the lifting lugs will act yield under a load equal to three times the weight of the package. Should a lug experience a load in excess of 370,200 lbs., it will begin to shear O out locally through the eye, and will have no adverse V effects upon the package's ability to meet other 1 requirements. 1 2.4.3.2 Primary and Secondary Lid Lifting Lugs The primary and secondary lid lifting lugs are identical in size and shape. The following analysis conservatively considers the maximum lug load in order to assess both primary and secondary lid lugs. The maximum lid weight is 5,450 lbs. Using three lugs the load per lug ist (5.450 lbs) (3 g's)/3 lugs P = t 5,450 lbs/ lug P = t This is greater than the secondary lug load oft 3(1150 lbs) = 3450 lbs. pee % / h f.I + O WT 9 7 1,,,,, 1 0024k 2-6

I STD-R-02-016 ) Using the conventional 40' shear out equation, the O yield capacity ist cs 0*) P, = F,y2t (e d l l Wheret F,7 = 22,800 psi (yield) l j t = 1.0 in. 1 i' d = 1.0 in. E " t*3 i"* d P, = (22,800)(2)(1.0)(1.3 - (1.0) cos 40') 2 P = 41,810 lbs. i s i The yield Margin of Safety, using the maximum lug i load, ist b -1= 80,g M.S. = P 5,450 t I = +6.67 O ) The yield capacity of the lug-to-lid weld may be estimated ast l P, = F,y

A,

I Wheret 4 21.000 (E70 Weld Rod) I F = sy A, L,

t, 8

= L, 2(6.0" + 1.0") = 14.0" = (0.5)(.707) =.354" (Fillet Weld) t = .j w A, (14.0)(.354) = 4.95 in.8 = Thent i l P (21,000)(4.95) = 103.929 lbs. = 4 a The lus-to-lid weld Margin of Safety ist M.S. = b - 1 = 103.929 - 1 = +18.07 3 P 5.450 j b l l 0024k 2-7 l i -. 2

STD-R-02-016 i Therefore, it can be concluded that the primary and i d secondary lid lifting lugs are more than adequate to l resist a load equal to three times their maximum leads. As for the package lifting lugs, the lid lifting lugs fail by local shaarout through the eye and therefore, have no adverst effect upon the r package's ability to meet other requirements of 10CFR71. Since the lid lifting lugs are not capable of reacting the full package load, they will be covered during transit. f 2.4.4 Tiedowns Four tiedown lugs are provided to resist transportation induced loads. The required load factors are: A = 10g (longitudinal) A = 5g (lateral) y A, = 2g (vertical) The four tiedown lugs are located at 90' intervals around the package sidewall at an elevation above the package base. The tiedown arrangement for the HN-215H cask is shown in Figure 2.4.4-1. Tiedown cables are assumed to be fastened to the trailer O at the same elevation as the base of the cask as shown (i.e., top i of trailer deck). From the geometry given in the sketch, the cable tension due to horizontal accelerations can be determined by summing moments about the opposite bottom corner of the package. For the longitudinal acceleration case: A We = 2(P d + P h) x y h i 4

But, f

A We = 2P (B d + B h) g T a x j Solving for P

T

{ l Ae T =W( ) long 2 3,d + B,h Similarly, the cable tension due to the lateral acceleration ist Ae r P Y ) T,g = W (B d g 2 +Bh j O l 0024k 2-8

=-. STD-R-02-016 i i

O n

46' .h 'JC .g s .4 5* 6 Li d' m 4 O ? z a K l [ l f/1777(f/ / / // /?////f// ~ r ( i I B B,B are cable direction cosines. If 1 is the ) ciblelenlth: Y 1 1 x " */1 Ph"B P or B P 8 x g g 1 B = y/t P B,P = g y B, = h/1 Tigure 2 4.4-1 i i i 1 0024k 2-9 t

STD-R-02-016 The cable tension due to the vertical acceleration is simply: 4P = A,W = 4B,PT y Solving for P 3 T P AW vert " 1 4 B, a For conservatism, these three loads may be assussd to coincide for the most severely loaded cable: A,c Ac A, y T " w (B,d P + ) 2 +Bh B,d +Bh 2B, g y TABLE 2.4.4-1 CASK T!!Dolet CABLE F0ftC28 Gross outside Outside d' h Cable Cable Cask Weight 01ameter Height Length Tension Model (ib.) (in.) (in.) (in.) (in.) (in.) Br, By B: (ib.) O iti-215H $8,400 83.5 88.25 73.0 70.6 74.5 4224 .944 257,900 I I O 0024k 2-10

4 STD-R-02-016 i i O The cable focce calculated for the RN-215H cask is 257,900 lbs utilizing the above equations. The tiedown lug is made of three i plates welded together as shown in the sketch below. The tiedown cable is attached to the lower hole. The cable lies in a vertical l plane which also is the lug plane of synenetry. Therefore, no twisting moments are induced in the lug. i J i ) i

3. C'**21'a 1

,f [ d i e' + \\ 2*g o \\ t g .( Act* 9 N.4. o 3*t i 4&n l 9.dt. ^ 4 j .F \\ ., 7 1 b 1 p o f W i I O l 4 1 d 4 1 l The tiedown lug capacity is calculated using the 40' shearout ]! expression at the tiedown eyes. d 09 t (e 2F,y P = d-}es t l i iiO 1 1 Oo24x 2-it I

STD-R-02-016 + From the figure above: 2" .t = e d 2.5" d = Thent P( = 2(60,000)(2")(2.5 - M cos 40*) 2 = 370,200 LBS. Using the maximum cable tension of 257,900 lb. the yield Margin of Safety is: M,s,. 370,200, g, g,44 257,900 The cable load consists of both horizontal and vertical components. l The cask produces a cable load which introduces both a bending moment and a shear load into the outer shell through the lug to shell weld. The weld stresses in the lug-to-shell weld are composed of pure j shear and tension / compression due to the moments. j Pure shear on weld due to vertical component of the lus load, P y Py F =- s A, l The vertical component of force ist 1 P = (.948)(257,900) = 244,489 lbs. Y g a i Trom Section 2.4.3.1, Package Lifting Lugst 1 i A,= 32.3 in.: 1

Then, l

F' = - 7.569 psi 9 j 32.3 i i The moment force on the veld is the summation of the moments due to the horizontal and vertical components of the force, ort O M = F e, T 'M + H y 0024k 2-12 .i m . m m ..-m

STD-R-02-016 O Wheret V F = 244,489 lbs. y i e - 2.5" y F = (.224)(244,489) = 54,766 lbs. H e = 4.84" H Then, assuming a CCW moment is positive. M = (244,489)(2.5) - (54,766)(4.84) = 346,155 in-lbs Again, from Section 2.4.3.1, Package Lifting Lugst 8

= 122.7 in 346,155 2821 psi F

= g 122.7 Combined Stresst j F = /(7569): + (2821)8 - 8078 psi e The lug-to-shell weld Margin of Safety is F 21.000 M.S. =2 -1= - 1 = 1.60 Fe 8,078 I The stresses induced into the outer shell by the tiedown lugs were determined using the finite element analysis program ANSYS, Revision 3, Update 67L, available on the Boeing Cosputer Services (BCS) National Network, MAINSTREAM - EKS. The capabilities are outlined in Appendix 2.10.5. I The Finite Element model consisted of a 45' section of the cask outer shell, cask wall top plate, and one-half the lug. The length of the cask model below the tiedown lug was sufficient to eliminate any end (boundary condition) effects from affecting the final j results. To react to the lug loads, the nodes along the bottom of the inside and outside shells were constrained from displacing i vertically. For symmetry, the nodes along the sectional cuts were i onstrained from displacing circumferential1y and rotating about the X (radial) and Z (tertical) axes. i i I Springs were introduced between the inner and outer shells at locations where the shells displaced radially towards each other (compression only) to account for the presence of the lead. The corresponding spring stiffness was estimated for a column of lead I 0024k 2-13

-. ~... - STD-R-02-016 1 l i I i as k = AE/L. Since the purpose of the springs was to prevent i , O fictitious localized bending stresses, placement of the lead spring j was conservatively chosen as one every four inches. l The model, with exception of the spring elements, was' defined entirely of quadrilateral shall elements. The geometry plots are 4 illustrated in Figures 2.4.4-2 to 2.4.4-5. Figures 2.4.4-2 and -3 j have omitted the side lug plate for clarity. The quadrilaterai shell element has both bending and membrane stress capabilities l j with six degrees of freedom at each nodet translations in the nodal x, y, and a directions and rotations about the nodal x, y, and : axis. Each element, either triangular or quadrilateral in shape, was defined by four nodes that lie in a plane. The j thickness at each node in an element was defined in a real constant l l~ table for each element type. ] The element size was decreased in the area of the lug for greater j accuracy. Furthermore, to enhance to model definition, the node l directly adjacent to each of the lug attachment nodes was linerly l' l constrained to move with that node (e.g., Node 2 was linearly constrained to move with Node 1. Node 14 with Node 13, Nodes 99 and i 12'3 to save with Node _111, etc.) to simulate the presence of the l i two-inch wide lug plates. l A 281,000 lb. load was introduced as a 89,000 lb. outward radial l component combined with a 267,000 lb. downward vertical component I lO ^ at Node 622. This is conservatively higher than the cable tension l l V for the HN-215H cask. The lug hole was omitted to decrease the j complexity of the model as any local effects of the hole would not j directly affect the reaction of the outer shell. 1 i Other than the springs between the inner and outer shells, the l contribution of the lead strength was neglected. Also, for 2 conservatism, the cask wall top plate was defined as being one-half j inch thick. j The maximum combined stress occurred at Element 232, directly below the lug, on the outside of the outer shell. The 20.749 psi combined stress was comprised of a 22,792 psi compreseive longitudinal stress, a 5004 psi compressive circumferential stress, 4 and a 164 psi shear stress as shown on page 2-19a. A description of how to interpret element stress output is provided in Appendix 2.10.5. The second highest stress area in the outer shell occurred i around the end of the horisontal lug. In this area, the element with the highest stresses. Element 88, contained a combined stress of 18,203 psi. J l ] The largest outward radial displacement of the outer shell. 0.0417 ) j inches, occurred at Node 1. The largest inward radial displacement j j on the outer shell. 0.0331 inches, occurred at Node 386. 1 Lo 4 0024k 2-14 1 ) i

STD-R-02-016 i The Margin of Safety of the outer shell ist M.S. = 38,000 - 1 = +0.83 I 4 20,749 i j In order to preclude damage to the cask under extreme loads, the tiedown lug is designed to fail prior to the veld or cask shell. The ultimate shearout capacity of the lug, using roughly the I j-highest strength A517 steel (F, = 135,000 psi), which occurs: l 2 F, =.6 (135,000) = 81,000 psi The minimum ultimate capacity of the weld or shell (using a minimum 4 value of F, for A516 plate): , 281,000 (.6)(70,000) 1,186,000 lbs. p = veld j 9922 , 281,000 (.6)(70,000) 567,179 lbs. p = 20,749 .V Thus, failure of the lug vill not damage the cask. O i l i i t i i i 1 i ( ) 0024k 2-15 l --_,-----,,,-,,.,..--,,---w. w,.,, .,,-.,,,e

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\\ I 4 I EL: 220 NODES: 251 252 240 239 MAT: 1 AREA: 1.00 110l*.1001: 70.0 70.0 PRESS: 8. 0049 SHELL 63 i l MX.MY.MXY: 257.14 25.650. 198.54 NX.NY: -36.207 -11.373 XC,YC.20: 40.0 10.4 -19.5 Ter 5X.5Y.TXY: 2072.3 -3577.4 2594.4 5MX.5MN.1MX: 3082.9 ~4588.0 3835.4 A: 68.7 SIGE: 6685.7 MID 5X.5Y.1XY: 57.139 -3778.5 1838.5 SilX. SitN. itlX : 320.27 -4041.6 2180.9 A: 75.4 5!GE: 4210.9 i 33I SX.5Y.1XY: -1958.0 -3979.5 -517.36 SMX,5tlH. IttX : -1833.3 -4104.2 1135.4 A: -76.4 SIGE: 3561.8 EL: 221 NODES: 253 254 242 241 MAT: I AREA: 1.00 110P.7001: 70.0 70.0 PRESS: 8. SUAD SHELL E3 MX.MY.MXY: -171.38 -571.28 .32176E-09 MX.NY: .39650E-09 1677.8 XC.YC.ZC: 41.3 .500 -20.5 j ISP SX.5Y.1XY: -4910.5 -16368. -8.7198 SitX. 5ftN. T MX : -4910.5 -16368. 5729.0 A: -90.0 5 IGE: 14549. MID SX.5Y.iXY: -3567.4 -11891. -4.7198 SMX.5MN.iMXr -3567.4 -11892. 4162.0 A: -89.9 5 IGE: 10569. SBT 5X.5Y.IXY2 -2224.4 -7414.5 -8.7198 SMX.SitN ittX: -2224.3 -7414.6 2595.1 A: -89.9 5 IGE: 6590.2 EL: 232 NODES: 254 253 265 266 MAT: 1 AREA: 1.00 T10P.ISOT: 70.0 70.0 PRESS: 8. SUAB 5NELL 63 i MX.MY.MXY: -494.06 -1235.7 74.940 MX.NY: 196.20 -223.10 XC.YC.ZC: 41.3 .500 -21.5 IOP X Y TXYz -5004.3 -22792. 163,98 Stix SHN IttX: -5002 8 -22794. SL9L 4 A: 49.5 SM : bMt' RTFlYI}5DXY= -2539.9 -15378. -245.66 sitd5HdHW: -243f5 -15384. 6675.1 A: -88.8 SIG = 5 l 331 SX.5Y.iXYz 124.42 -7964.0 -735.29 5ttX. 5MM. ittX: 984.8% -8024.4 4504.6 A: -85.3 SIGE: 85595 1 l EL: 222 NODES: 242 254 255 243 MAI: 1 ARIA: 1.00 TiOP.100T: 70.0 70.0 PRES 5: 8. GUAD SHELL 53 l MX.MY.MXYs -827.94 -331.89 -234.39 MX.NY: -2000.4 638.06 XC.YC.ZC: 41.3 1.50 -20.5 ISP 5X.5Y.TXY: -15417. 329.54 -5883.5 5MX.5MM.IMX: 2285.0 -17373. 1828.8 A: -14.4 SIGE: 18621. MID SX.5Y.1XY: -19458. 2440.9 -4478.4 5tlX. 5 TIN. itlX: 3844.0 -11853. 7448.4 A: -17.4 51GE: 14171. BUT 5X,5Y.IXY: -5482.0 4552.2 -3073.3 SilX. 5MN.1MX: 5418.6 -6348.4 5883.5 A: -15.7 SIGE: 19201. EL: 233 MODE 5: 254 266 267 255 MAT: 1 AREA: 1.00 TiOP,100!: 70.0 70.0 PRESS: 8. SUAD $NELL 63 l m MX.MY.MXY: -1962.9 -563.19 -95.530 NX.NY: 431.03 805.63 XC.YC.ZC: 41.3 1.50 -21.5 '. TOP SX.5Y.TXY: -20896. -2999.7 -3346.2 SilX. 5ftN. ittX: -2394.6 -21502. 1553.5 A: -10.3 SIGE: 20410. --. MID SX.5Y. IXY: -13641. 844.95 -2494.0 5MX.5 TIN.1MX: 1329.8 -14125. 7727.6 A: -10.2 SIGE: 14835. 'O SEI SX.5Y,TXYs -6384.8 4689.6 -2041.9 5ttX. 5MN. ittX: 5054.1 -6749.3 5901.7 A: -10.1 SIGE: 18257.

9 Etz 243 NODES: 277 274 266 265 MAT: 1 AREA:

1.00 if0F.T90i: 70.0 70.0 PRESS: 8. GUAD SHELL F3 MX.MY.MXY: -397.40 -731.08 20.165 MX.NY: -70.656 -453.33 XC YC.ZC: 41.3 .500 -22.5 l 10F SX.5Y.TXYz -2737.1 -21445. 13te.2 SelX. 5ttN. ittX: -2645.8 -21537 9445.4 A: 86.0 SIGE: 20393. MID 5X.5Y.IXY: 377.19 -15716. 1152.2 Sl1X. 5MN. INX: 459.27 -15798. 8128.6 At 45.9 SIGE: 16033. BOI SX,5Y.IXY: 3493.5 -9986.7 194.15 SMX.5MN.iHX: 3564.4 -19060. 6812.0 A: 85.8 SIGE: 12238. ) Els 244 MODES 2 278 279 267 266 MAT: 1 AREA: 3.00 TiOP.ISOT: 70.0 70.0 PRESS: 8. gMAD SHELL 63 i ttX.MY.MXY: -347.97 -437.75 7.322I MX.NY: 294.61 -378.86 XC.YC.ZC: 41.3 1.50 -22.5 i ler SX.SY.TXY: -2930.9 -18467. 2629.4 5MX. 5fth. IllX: -2497.9 -18900. 8201.2 A: 88.7 SIGE: 17784. i MID SX.5Y.TXYs -203.89 -13470. 2572.0 SetX. StIN. iMX: 277.34 -13951. 7114.1 A2 79.4 SIGE: 19892. ) Bei SX.SY.IXY: 2523.1 -8471.6 2514.7 5ttX. SitH. IrlX: 3070.9 -9019.5 6045.2 A: 77.7 SIGE: 19485. Ett 223 N00ES: 255 256 244 243 MAT: 1 AREA: 1.00 110F.iB01: 70.0 70.0 PRESS: 8. GUAO SHELL 63 MX.MY.MXY: 36.279 -406.89 255.21 MX.MY: 309.96 597.90 XC YC.ZC: 41.2 2.50 -20.5 IDF SX.5Y 1XY: 1754.6 -I3342. 5276.2 5MX.5MN.TMX: 3415.8 -15004. 9209.7 A: 72.5 SIGE: 16971. (o MID 5X.5Y.1XY: 1470.3 -30154. 3276.2 SMX. SitH. IttX: 2330.1 -11014. 6671.8 A: 75.3 SIGE: 12345. -4 DST SX.5Y.IXYz 1186.0 -6965.1 1276.2 SilX. 5MN.1MX: 1381.2 -7168.2 4270.7 A: 41.3 SIGE: 7941.4 y ] ~EL: 234 NODES: 267 268 256 255 MAT: I AREA: 1.00 ITOP.100T: 70.0 70.0 PRES 5: 8. 4UAD SHELL 63 7 MX.MY.MXY: -40.983 -608.52 134.54 MX.NY: 439.32 -36.808 XC.YC.ZC: 41.2 2.50 -21.5 o 4 ISP 5X.5Y.IXY: -339.27 -15185. 3576.1 SMX. StlN. ittX: 477.23 -16002. 8239.6 A2 77.1 SIGE: 16246. ttID SX.5Y,IXY: 295.37 -19417. 2678.5 SilX. SitH. I rlX : 927.80 -18049. 5988.4 A: 76.7 SIGE: 11541. 33I 5X.5Y.IXV: 930.01 -5647.7 1780.9 5MX. 5MN.181X: 1381.2 -6099.0 3740.1 A: 75.8 SIGE: 6894.2 2 s EL2 245 NODE 5: 279 280 268 267 MAT: 1 AREA: 1.00 TiOP.150t: 70.0 70.0 PRESS: 9. SUAD SHELL 63 MX.MY.MXY: -123.10 -490.04 26.081 NX.NY: 3/3.54 -159.44 XC.YC.ZC: 41.2 2.50 -22.5 !10P 5X.5Y.iXY: -1489.2 -19712. 2876.6 5tlX. 5ttH.1MX : -813.75 -15307. 7246.7 A: 78.3 SIGE: 14917. MID 5X.5Y 1XY: -444.45 -18871. 2672.2 SilX. SitH. iMX : 200.49 -11516. 5858.4 A: 76.4 SIGE: 18688. 33I 5X.5Y.IXY: 520.25 -7031.1 2467.4 5tlX. 5ttH.1 MX : 1255.2 -7766.1 4510.7 A: 73.4 SIGE: 8463.8

STD-R-02-016 4 2.5 Standards for Type "B" & Large Quantity Packaging LI This section demonstrates that the standards of Section 71.13 and 71.51, 10CFR71, for Type "B" and large quantity packagings are met. 2.5.1 Load Resistance The requirement for load resistance is that, when simply supported at its ends, the cask must be able to withstand a uniformly distributed load equal to five times the cask weight. Conservatively, the outer shell alone is assumed to support this load as a beam. Accordingly, the stress is: MC S =- g I 1 M = SWL = (5)(1/8) (58,400)(88.25) = 3.221 x 106 in-lb 8 C = D = 83.5 - 41.75 in. 2 wd - d' 4 4 I= 64 64~ - 81.75 ) w (83.50 = = 193,843 in and the corresponding stress is: 6 (3.221 x 10 )(41.75) = 694 psi S =- e f I 193,843 j which results in a Margin of Safety of: MS = Fev 1 = 38,000 - 1 = +53.75 S 694 g Therefore, the package can safely react the "Load Resistance" condition. O i 0024k 2-20

l 5 i STD-R-02-016 ^ 2.5.2 External Pressure U An external pressure of 25 psig is reacted by the external shell in hoop compression. The stress can be calculated as follows* F = Pr/t Where: 25 psig P = (83.5 .875)/2 = 41.31 inches r = .875 in. (outside shell only) t = (25)(41.31)/.875 = 1180 psi F = Margin of Safety: M.S. = (Fty/F)-1 = (38,000/1180) - 1 + 31.2 = The analysis is conservative due to the presence of the lead and O', internal shell. The lead assures buckling stability of the shell. Pressure across the end is carried in plate bending by a minimum of two inch thick steel plates top and bottom. Assuming a circular plate, unifornly loaded and with edges simply supported, the stress can be calculated as follows: 2 3W(3M+1) /8 vMt (Per "Formulas for Stress f = and Strain" by Roark) Where: (25) w(83.50)2/4 = 136,900 W = t = 2" 1/.33 = 3 M = f = ( (3)(136,900x10)]/(8x (3)(2)2] r f, = 13,618 psi Margin of Safety: M.S. = 38,000/13,618 - 1 M.S. = +1.79 0024k 2-21 , _..... ~ _

STD-R-02-016 MAR 241988 7 -~s It is therefore safe to conclude that the containment vessel can react a 25 psig external pressure without loss of contents. 2.6 Normal Conditions of Transport The HN-215H cask has been designed and constructed, and the contents are limited (as described in Section 1.2.3 above), such that the performance requirements specified in 10CFR71 will be met when che package is subjected to the normal conditions of transport.specified in Subpart F of 10CFR71. The ability of the HN-215H package to satisfactorily withstand the normal conditions of transport has been assessed as described on the following pages. i 2.6.1 Heat A detailed thermal analysis can be found in Section 3.4 wherein the package was exposed to three combinations of solar heating, internal decay heat and-130*F. ambient air. The steady state analysis conservatively assumed a 24-hour day as maximum solar heat load. The maximum steady state temperature was found to be 192*F. These temperatures will have no detrimental effects on the package. 2.6.2 Cold The HN-215H cask containment components are constructed of A516 - x Grade 70 ferritic steel. This material provides appropriate resistance to brittle fracture failures in accordance with the i recommendations for Category III payloads as setforth in NUREG CR-1815. Specifically, package materials selections comply with criteria established in Section 5.3 of NUREG CR-1815. l l 1 (s_,/ i 4 0024k 2-22

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STD-R-02-016 2.6.3 Pressure O A differential pressure of 0.5 atmospheres will be reacted by the lid and its associated closures comprised of ratchet binders for the primary lid and studs for the secondary lid. Loads on the primary lid ratchet binders are calculated as: 2 P, = AP/N; where: A wD = 4 14.7/2 psi P = 8 N = For the worst case loading: P = x(81.82): x 14.7 x1 4,831 lbs. = s ~ T 4 2 The rated load of the ratchet binder is 100,000 lbs. (see Appendix 2.10.3). Thus, the Margin of Safety is: M.S. = 100,000 - 1 = 19.69 4,831 For the secondary lid stids, the load is: O P = w(33.87)* x (14.7) x 1 = 828 lbs s 4 2 8 i 1 The tensile strength of the 3/4-10 UNC, ASTM A320 Grade L-7 studs (minor thread dia. = 0.309) is: P = (105,000)(.309) = 32,450 lbs. A Thus, the margin of safety ist M.S. = 32,450/838 - 1 = 37.72 Stresses induced in the cylinder portion of the cask are conservatively estimated by assuming the pressure differential is totally borne by 3/8 inch thick inner shell. The hoop and longitudinal stresses are: f = PR/t = (

)(

) = 757 psi h 2 .375 f = PR/2t = (I ) ( .63) (1) = 379 psi g 2 .375 2 1 Assuming these biaxial stresses are additive, f,g = fh* i = 757 + 379 = 1136 psi 0024k 2-23

STD-R-02-016 The margin of safety is: 38,000/1,136 - 1 = 32.45 M.S. = Pressure across the end is carried in plate bending by the 2 inch (minimum) thick steel plates top and bottom.. Assuming a circular plate, uniformly loaded and with edges simply supported, the stress can be calculated as follows: 8 3W(3M+1)/8xMt (Per "Formulas for Stress and Strain" by f = Roark) (7.35) (w) (83.50)*/4 = 40,250 lbs. Where: W = t = 2" 1/.33 = 3 M = f = (3)(40250)(10)/8w (3)(2)8 4,006 psi f = r Margin of Safety: M.S. = 38,000/4006 - 1 = + 8.48 O It can therefore be concluded that the packaging can safely react an atmospheric presstire of 0.5 times standard atmospheric pressure. 4 2.6.4 Vibration j Shock and vibration normally incident to transport are considered to have negligible effects on the package. I 2.6.5 Water Spray Since the package exterior is constructed of steel, this test is not required. 2.6.6 Free Drop The free drop height specified by Subpart F of 10CFR71 for the HN-215H package is 12 inches, since the package is greater than 30,000 lbs. gross weight. Three drop orientations are possibles flat end drop, side drop and corner drop. For the flat end drop, the most critical condition will be settlement of the unbonded lead shield at the end opposite the point of impact. For the side drop, local flattening and i impact onto a lifting lug will be evaluated. For the corner drop, the most critical conditions will be impact on the lid edge and its effect on the closure. 0024k 2-24

STD-R-02-016 2.6.6.1 Flat End Drop The evaluation of flat end impact upon settlement of lead shielding closely follows Shappert's approach for a cylindrical lead shield, outlined in Section 2.7.3 of his Cask Designer's Guide, ORNI.-NSIC-68, February ~1970. The lead settlement distance is given by: RWH AH = 2 2r ) (t,c, +Ro ) tr(R Where: AH = Settlement depth (in.) Drop Height (in.) = 12" H = Outer lead radius (in.) = 40.88 in. R = W Weight of Lead (1bs.) = 16,290 lbs. = r = Inner lead radius (in.) = 39.00 in. j t = Thickness of external steel shell (in.) s =.875 in i o, = Steel dynamic flow stress, 50,000 psi J 1 o = Lead dynamic flow stress, 5,000 psi p3 Therefore the settlement depth, 4H, equals 0.068 l inches. This modest settlement "void" in the lead shield,.068 inches, cannot transmit radiation because of the stepped design of the package ends. The innermost solid steel end plates completely back (shield) lead settlement regions at both ends of the package. Thus, lead settlement due to a flat end drop does not compromise, nor alter, the integrity of radiation shielding in any fashion. O 0024k 2-25

STD-R-02-016 2.6.6.2 Side Drop The effect of a side drop on the cask shielding capabilities is evaluated using the methods outlined in Section 2.7.2 of Shappert's Cask Designer's Guide, j ORNL-NSIC-68. The governing equation (2.13) is ~ ' y (0

R ('pb

) + 2 (R/L)(Ee/t,) + F2 (0) =F t,RLo, t, Where: W = cask weight (1bs.) = 58,400 lbs. 12 in. H = Fl (0) = 0-1/2 sin 20 F2 (0) = sin O(2-cos 0) - 0 o, = 50,000 psi o = 5,000 psi pb e = 6.35' t, = outer shell thickness = 0.875 in, t, = end plate thickness = 4.00 in. The flattening of the cask is equal to: d = R(1-cos 9) Therefore: d = 0.256 inches Shielding is reduced by side impact as follows: % Shield Reduction = ( E ' )(100) T 360 s Where: T, = Normal Shield Thickness = 0.875 inches Therefore: % Shield Reduction = 0.33 This insignificant reduction of shielding demonstrates that side impact does not compromise the integrity of the package's shielding in any measurable fashion. 4 0024k 2-26 i .. _ _ ~. _. _ _ -. -. _ _ _ _.. _.., _ _ _. - - - _ ~..

STD-R-02-016 The potential for damage to the cask seal resulting from a side drop onto a tiedown lug is also evaluated. Because the lug is located at the upper end of the i I cask, the impact force will be shared by both upper and lower ends. If we conservatively assume, that the lug carries the entire load, then an estimation of the deceleration load can be calculated. j .- p-1 P ) (O O [ i, h Assuming that the lug plate of 514/517 steel deforms the softer 516 steel cylinder wall, a crush depth can be found using a dynamic flow stress of (o ) 50,000 8 psi: U = Ve, Where: U = Total energy - 58,400 (12) = 700,800 in-lbs. V = Crush volume 0 lug "lug = = (21)(2)6 = 426 Substituting and transposing: 6 = 700,800 .334 in. = 42(50,000) Note that this is less than half of the.88 wall thickness. O 0024k 2-27

STD-R-02-016 f Impact velocity is: O. = /2gh v = /2(386.4)12 96.3 in/sec. = Deceleration in g's is then, 96.3 a' - 35.9 g's = = 2g3 2(386.4)(.334) Note that this is within the range of the values found for the corner drop in Section 2.6.6.3 below. The tiedown lug extends r.o the top of the cylinder wall so the wall is backed by the cylinder top ring as well as the lead shielding below it, thus resisting gross radial deflection of the outside cylinder wall. The circularity of the cylinder in this area is insured by the stepped lid. Thus, the sealing surfaces in this area are expected to remain relatively undeformed assuring the preservaticn of the seal. 2.6.6.3 Corner Drop The impact energy associated with a corner drop will be absorbed by inelastic deformation of the corner. Using the "dynamic flow pressure" concept, total deformation of the corner is estimated and used to compute package deceleration. This deceleration is then used to check the integrity of the lid closure. Both steel and lead components of the cask are distorted upon corner impacts. The assessment of deformation and resultant decelerations is based upon a careful consideration of detail corner geometry for a range of assumed deformations. It is assumed that 4 the steel and plates of the cask undergo plastic flexural deformation and do not crush. This flexural deformation of the ends enforces a crushing of the contiguous lead side walls and the thin cylindrical external steel shell. The predictions of peak rigid body impact decelerations are based upon the crush geometry of the lead side walls and the associated external steel shell. Resultant deformation prediction estimates are based upon two energy balance techniques: o The plastic flow pressure concept O 1 1 0024k 2-28 . _. _. - -, _ _ _.. _. -,. _.... - ~. - - _ - -...

STD-R-02-016 l i - C- \\ o An integration of force - deflection relations based upon crush stress approaches. For the plastic. flow stress approach, properties of steel and lead are based upon recommended deformation basis values used by Shappert in the Cask Designer's Guide, ORNL NSIC-68, Section 2.7.1: o = 5,000 psi pb o, = 50,000 psi For the crush stress approach, steel crush properties are assumed.co be equal to approximately 1.5 times the yield stress, approximately the midpoint between yield and ultimate stress. This. conservative approach is intended to account for both strain rate effects and strair. hardening. This provides a crush stress equivalent for steel of 55,000 psi. For lead, the crush stress equivalent is taken as twice yield, .,r 1380 x 2 = 2760 psi, reference Table 2.6, Shappert, Cask Designer's Guide, ORNL-NSIC-68. Analytics used for this estimate are outlined in Appendix 2.10.2. The results are summarized in Table (" 2.6.6.3-1; detailed computer analysis results for the cask configuration follow the table. The deceleration resulting from impact onto the bottom corner of the cask is conservatively used in evaluating the drop onto the top corner of the cask. The actual deceleration for the top corner drop would be significantly less due to the bending of the lid top plate during impact. TABLE 2.6.6.3-1 CORNER IMPACT DEFORMATION & DECELERATION ESTIMATES 1 (1) Drop Crush Zone Geometry Load Height Weight Radius Volume Area Depth Factor 4 8 8 Cask (in) (1bs) (in) (in ) (in ) (in) (g's) HN-215H 12 58,400 41.785 15.4 34.5 1.12 32.6 (1) Intepolated for greatest crush depth prediction corresponding to a strain energy / kinetic energy ratio of unity. O 0024k 2-29

O 1 o O i hae. X l 4 I I i l CA5KCRN(CORMER) CORNER INFACT OF A CYLINDRICAL SHIELDED CASK 11.37.52. 83/02/03. PAGE l 2.75 E4 5HIELDING 4

58480.00 (Le5)

PACKAGE WEIGHT 12.888 (IN) DROP HEIGNI { PACKAGE RADIUS 41.785 (IN) 1 4 l 5t[EL DYNAMIC FLDW STRESS : Seest.se (PSI) l I' 51LEL CRUSH STRESS 550e8.08 (PSI) LEAD DYNAMIC FLOW STRESS : 5808.08 (PSI) I LJ

2768.08 (PSI) 4 LEAD CRU5H STRESS

.875 (IN) STEEL 5 HELL THICKNESS SIEEL 80Il0M THICKNESS 4.250 (IN) ORIENTATION ANGLE 43.28 (DEG) l I l i 1 4 i un 1 1 1 P3 i O b i i 4

O CASKCRN(CORNER) CCCMER IMPACI CF A CYLINDRICAL SHIELDED CA5K 11.37.52. 43/02/03. PAGE 2 c3 2.75 Et 5HIELDING ~ o 7

- CRUSH VOLUME **
FLDW SIRE 55 GA515*
- - CRU5H AREA ***
- IMPACT **
- CRUSN STRESS SA5I5 r CRUSN KINETIC SIRAlH ENERGY STRAIN ENERGY,

DEPTH E tat RGY TOTAL SIEEL LEAD EH[RGY RAllO TOIAL STEEL LEAD FORCE ACCEL. EN[RGY RAlle (IN) (IN-LS) (IN3), (IN3) (IH3) (IN-Lea (5E/KE) (IN2) (IN2) (IN2) (Le5) (G) (IN-Le) (5E/EE) l .35 783728. .4 .4 8.8 338. .00 .3 .3 e.e 18132. .3 453. .00 i .30 786640. .8 .e e.e 1865. .Se .9 .9 0.0 51273. .9 2188. .00 .15 789568. .1 .1 0.0 5138. .01 1.7 1.7 8.8 94178. 1.6 5825. .41 I .28 712488. .2 .2 e.e 19545. .81 2.6 2.6 8.0 144946. 2.5 11882. .82 .25 71540s. .4 .4 8.e 18417. .e3 3.7 3.7 0.0 202515. 3.5 20459. .43 .30 738320. .6 .6 8.e 29847. .e4 4.8 4.4 4.0 266143. 4.6 32205. .44 .35 721240 .9 .9 0.0 42696. .86 6.1 6.1 0.0 335298. 5.7 47241. .07 .40 724168. 1.2 1.2 e.e 59605. .88 7.4 7.4 0.0 489538. 7.8 65862. .09 I .45 727e88. 1.6 1.6 e.e 79999 .11 8.9 8.9 e.e 488549. 8.4 88314. .22 .Se 730084. 2.1 2.1 0.0 194086. .14 18.4 18.4 8.8 572045. 1.8 114829. .16 i .55 732920. 2.6 2.6 0.0 132067. .18 12.8 12.0 e.G 659789 11.3 145625. .28 .6e 735840 3.3 3.3 8.0 164129 .22 13.7 13.7 8.8 751577 12.9 188989. .25 .65 738isa. 4.e 4.s e.e 2e5451. .27 15.4 15.4 8.e a47232. 14.5 220879. .3e l .79 741688. 4.8 4.3 8.8 241286. .33 17.2 17.2 e.0 946596. 16.2 265725. .36 i .75 744600. 5.7 5.7 e.e 286559. .38 19.1 19.1 8.0 184953e. 18.e 315625. .42 .Se 747528. 6.7 6.7 0.0 336670. .45 21.0 21.8 S.0 1155947. 19.8 378764. .50 i .45 758448. 7.8 7.8 0.0 391692. .52 23.0 23.0 e.e 1265615. 21.7 431382. .57 ) .94 753360. 9.8 9.8 e.e 451775. .64 25.1 25.1 e.0 1378549. 23.6 497486. .66 .95 756280. 18.3 10.3 e.e 517862. .68 27.2 27.2 8.0 1494614. 25.6 569235. .75 1.80 75920s. 11.4 11.8 0.8 587695. .77 29.3 29.3 0.0 1613721. 27.6 646943. .45 N 1.05 762128. 13.3 13.3 8.8 663809. .87 31.6 31.6 e.8 1735791. 29.7 738681. .96 d, 1.18 765848. 14.9 14.9 0.0 745538. .97 33.8 33.8 e.e 1868747. 31.9 520595. 1.07 3.15 767960 16.7 16.7 8.e A33810. 1.e4 36.2 36.2 e.0 1983528.* 34.0 916826 1.19 1.28 77e888 18.5 18.5 0.8 926354. 1.28 38.5 38.5 0.0 2119943. 36.3 1819515 1.32 1.25 77388e. 20.5 28.5 0.0 1825691. 1.33 41.0 41.8 0.0 2252255. 38.6 1128798 1.46 1.38 776728. 22.6 22.6 0.0 1131144. 1.46 43.4 43.4 8.0 2388098. 48.9 1244807 1.60 i I 1.35 779644 24.9 24.9 0.0 1242830. 1.59 45.9 45.9 0.0 2526515. 43.3 1367672. 1.75 i 1.40 782560. 27.2 27.2 0.8 1360866. 1.74 48.5 48.5 0.0 2667462. 45.7 1497522. 1.91 l 1.45 785480. 29.7 29.7 0.0 1485364. 1.89 51.1 5.1.1 8.8 2510082. 44.1 1634440 2.08 1.50 788440. 32.3 32.3 e.0 1616437. 2.e5 53.5 53.8 8.8 2956731. 50.6 1775671. 2.26 l.55 791328 35.1 35.1 e.e 1754194. 2.22 56.5 56.5 0.0 3184165. 53.2 193e213. '2.44 4 1.40 794248 38.e 38.8 0.0 1898742. 2.39 59.2 59.2 8.e 3255542. 55.7 2e89226 2.43 1.65 797168. 41.0 41.0 0.0 2050187. 2.57 62.8 62.0 8.0 3488423. 58.4 2255825 2.83 1.78 500080. 44.2 44.2 0.0 2208633. 2.76 64.8 64.8 8.8 3563567. 61.0 2438125. 3.84 1.75 803008. 47.5 47.5 8.4 2374142. 2.96 67.7 67.7 0.0 3728948. 63.7 2612237. 3.25 1 1.Se 505920. 50.9 58.9 0.0

2546934, 3.16 78.6 70.6 8.8 38805e5.

66.4 2802273. 3.44 i 1.85 sesste. 54.5 54.5 e.e 2726988. 3.37 73.5 73.5 8.8 4042230. 69.2 3008342. 3.71 i 1.90 881760. 58.3 58.3 e.e 2984441. 3.59 76.5 76.5 0.0 4206088. 72.0 3286"b9. 3.95 4 1.95 414680. 62.2 62.2 e.8 3109394. 3.42 79.5 79.5 0.0 4372027. 74.9 3421082. 4.28 l 2.80 8176e0. 66.2 66.2 0.0 3311938. 4.05 82.5 32.5 8.0 4548039. 77.7 3643404. 4.46 m dQ l I x ) o a y 4 O b I i I l 1 i 1

STD-R-02-016 Loads due to impact on top corner Ig2 J Pp Binders react the forces due to payload, weight of the lid and the moment due to the impact point offset. Conservatively p ignoring the effect of the deflection of 8 the lid and deformation of the impacted Fu corner, the impact point is located as f shown. Binders are located as shown, a j distance of 1.9" inward from the corner of the octagon. F - 1.9" r = p, 7 f 2cos 22.5' L is equal to the outer radius of the F 1 D 7 cask body, d is the impact moment arm. d = 0.5 t -1 g F 3 With these dimensions, the distance from do / the pivot point to the ratchet binders can / be calculated: / 7 I I Bl " D B' sin 22.5 0 LB2 " D+#B PJef cos 22.5 IB3 " D+#B g4 Binder loads are assumed to increase 8 linearly with distance from the pivot 7 point. 5 3 Therefore: di 9, ~m B2 F F F F = = B2 B3, BI B3

8:

k A B3 B3 / ~ The pivot point is assumed to be at the / $3 outer edge of the lid / cask interface. The axial and lateral forces imposed by the cask body on the lid are assumed to pass through this point, therefore causing no moment. Summing moments due to the other forces: F, ( L ) + F ( L ) + F, (d ) = t D p D g 2Fg (t ) + 2Fg (1 ) + 2F (1 ) + F (t) 0024k 2-32

STD-R-02-016 'O The forces are the axial or lateral component of the \\ impact force. I F,=W11d (^g ( "" t P (A ) (cosa) F =W P S F, =W (A ) (cosa) t g t g (sina) i F, =VA Substituting the above and the expressions for under force: 11d (^g * ""( D} p(^g * ""( b t ^g c sa(d ) = W t 2t Ib3 + A Fb3 + B3 B2 B3 2 t'B1 F +W (A ) sina(t) 33 t g IB3 Collecting ter1ns: A ((Wiid

P)

D* "" + t(di cosa - tsina)) O 8 8 8 2F b3 (1B3 + B2

IB1)

= I B3 Solving for FB3, t e maximum nder force, B3 " ^g B3(("lid + p) b * **

t 1* '"~**I""))

F a m a 2(tB3 + IB2 + IB1) The interface forces between the lid and body are calculated as follows: F =A cosa (W -W -Wiid) + (Fbl+Fb2+ b3) adal t p F = A sina (W -W11d} lateral g g O i 0024k 2-33

i STD-R-02-016' l l l TABLE 2.6.6.3-2 LID INTERFACE FORCES Gross Payload Lid Body Lid Impact Impact Maximum Interface Interface Weight Weight Weight Dia. Dia. Angle Accel. Binder Axial Force Lateral Cask (1bs.) (1bs.) (1bs.) (in.) (in.) (deg.) (g's) Force (1bs.) Force (1bs.) (1bs.) HN-215H 58,400 20,000 6,600 83.50 84.93 43.90 32.6 92,800 1,121,000 1,171,000 I J l E .l 4 4 0024k 2-34 I - _.=,_.- --._...

STD-R-02-016 Thus, in this instance, the maximum binder force is (m) 92,800 lbs. w/ The allowable load of the binder is rated at 100,000 lbs. (see Appendix 2.10.3). Thus, the Margin of Safety is: M.S. = 100,000/92,800 - 1 = +0.08 The capabilities stated for the binders are established static allowables. They are manufactured from standard carbon steels and fail in the same manner as a bolt. Numerous studies have been conducted on the behavior of bolts under dynamic or impact loading. ORNL-TM-1312 Volume 12 Structural Analysis of Shipping Casks states that carbon steel bolts "possess better physics properties under conditions of shock ths.n indicated by static tests. Increases in the value of stress by a factor of 1.3 and a greater amount of strain before necking occurs were reported". This is substantiated by reference 5, 8, 9, 10, and 11 of the same document. Therefore, it can be concluded that the binders static allowable capabilities will not be lower under shock or dynamic loading. Thus, it can be concluded that the binders will react the impact load and retain the lid. In the case of a top corner impact directly above a binder lug, some bending of the ocatgonal lid corner may occur. This will decrease the distance between the cask binder attachment lugs and would normally induce a damaging compressive load in the binder. This, in turn, could result 's damage to the cask outer shell due to the moment induced in the binder lug. The binder design precludes this since it will allow a significant amount of axial deflection before it will take a compressive load (see Appendix 2.10.3). The lugs at each end of the binder will possess the following yield capability. j 4 O 1 n 0024k 2-35

STD-R-02-016 Body Lugs hI.7'k / t N :,=T / 4 / . i. us'o / ?" / f / 2't (d ") 4' - / Shear out: Using the standard 40* shear out relation: P, = F, 2t (e -1es O') d O Where: F,y = 22,800 psi e = 2.0 in. e = 1.5 in, d d = 1.125 in. P, = (22,800) (2) (2.0) (1.5 - 1.125 cos 40') 2 = 97.500 lbs. shear out i Wald Area: The weld stresses are composed of pure shear and tension / compression due to the moment. Pure shear on the veld F, = ,,P,,,, Aw O 0024k 2-36 l'.

STD-R-02-016 Where: F, = Weld shear stress A, = Weld Area = L, ' t, L = 2(9" + 2" ) = 22" t = (.5) + (.5) (.707) = 0.854" (Groove + fillet. weld) A, = (22) (.854) = 18.78 in.2

Then, P

F = s 18.78 The stress due to the bending moment is FB" z Where: P(2.3) M = z =1 c Ig+AdHH V I + = 4 1 (2) (.854)s = 0.1 in I = H 12 1 A = (.854)(2) = 1,71 in: H d = 4.5 in. H 51.9 in" i 1 (.854)(9)8 I = = y 12 i I =.1 + (1. 71)(4.5) 2 + 2(51.9) = 138.5 in" I c = 4.5 in 138.5 Z= = 30.78 ins 4.5

Then, F = P(2.3)

P = B 30.78 13.38 ] i i 0024k 2-37 t

STD-R-02-016 Combined stress cannot exceed the weld allowable shear g

stress, F, - 21,000 (E70 Weld Rods)

F* = /(F )2 + (p ) + 000 = = B 1.IU. 13.38 Solving for P: P = 228,840 lbs. Plate Area: Utilizing the same approach as above, the plate yield shear capacity is: Pure shear on plate: F = s A P Where: F, Plate Shear Stress = (9)(2) = 18 in.8 A =

Then, P

y 18 Moment force on plate: M = 2F A d = P(2.3) Bp Where F "I * # "' B A = 18 in.2 d = 2/3(4.5) = 3.0 in.

Then, 2F ( )(.0) = P(2.3)

B F P = B 46.96 0 0024k 2-38

STD-R-02-016 O Combined stresc cannot exceed the plate allowable U shear stress, F, = 21,800 psi F,=/(F,)2 + (p 1 + Psi B 18 46.96 P = 366,405 lbs. Outer Shell: The body lugs introduce a bending moment into the outer shell similar to the tiedown lugs in Section 2.4.4. Assuming bending about the body lug center, the moment induced in the outer shell is: g = P(4.0 - 1.7) = P(2.3) Again, assuming bending about the tiedown lug center, the moment induced in the outer shell by a 89,000 lb. outward radial load and a 267,000 lb. downward load (from the finite element analysis) is: y - 267,000(2.5) - 89,000(4.84) = 236,740 in-lbs. The maximum outer shell combined stress from Section 2.4.4, Tiedowns, is 20,749 psi. The outer shell yield capacity at the body lugs is: b = P(2.3) 38,000 = y 236,740 20,749 or P = 188,508 lbs. Lid Lugs: 3$ ^ 3.2f = = I' S t m 2.0 m. (A st& T 1 a o j

j h

. u.c 4/ Ar4 0024k 2-39

STD-R-02-016 The lug yield strength capability across net area O-(A-A) is: Pt" ty^ Where: F = 38,000 psi gy A = (3.25 - 1.125)(2.0) = 4.25 2 (38,000 psi)(4.25 in ) P = g W,500 28. Wet Area) \\ P = t Lug shear out capability is identical to that of the lower lug evaluated above (i.e., P, = 97,500 lbs.). Lug to lid attachment: V// h/'../ A ..a T / o <e-s4 4 j Weld Shearing: P, = F,A, Where: F, = 21.000 psi (E70 Weld Rods) (2)(2)(0.5)+(2)(3.5)(.854) A = y 7.98 in.2 = P, = (21,000 psi)(7.98 in.8) P, = 167,580 lbs./ lug 0024k 2-40

i STD-R-02-016 The weakest link in the binder lugs is the shearcut t failure. At this locatien, the minimum Margin of Safety is: 97,500 M.S. = -1 + 0.05 = 92,800 The ratchet binders load the lid top plate with a series of edge moments. The two inch plate of the casks will be evaluated for these loads. Both local and gross effects on this lid top plate are evaluated. For a maximum ratchet binder load of 92,800 lbs., the associated moment introduced into the top plate of the lid is estimated as: M = (92,800)(.375 + 3.5 - 1.50) = 220,400 in-lb. The local moment capability of an octegonal lid cover is estimated as follows' l M" 21. t c Where: e = 38,000 psi e = 1.0 inch I = bh8 = (18.35)(2)8 = 12.23 in.4 12 12 b = (2)(3.8) tan 67.5* - 18.35 Local moment capability is then: (38,000)(12.23) = 464,800 in-lb. M = 1 Thus, local moment yield Margin of Safety of the lid is: M.S. = 464,800 - 1 = + 1.11 220,400 l Gross moment capability is assessed using both the d j exterior and interior lid plates. For a uniform edge moment the expression relating stress to moment in a O circular plate is given by Roark ast ) i 0024k 2-41 j

STD-R-02-016 (^)' Y ' " "'6 For the 2" exterior plate: M = 38,000(2): = 25,330 in-lb/in. 6 For the 2" interior plate: M = 38,000 (2.0)2 = 25,330 in-lb/in. 6 The total edge moment capability is: 50,660 in-lb/in. For the circular lid of 83.50" diameter, the corresponding concentrated moment acting on 1/8th of the edge is: M = (50,660) (83.50) (H) = 1,661,160 in-lb. i 8 8 L Thus, the gross moment yield Margin of Safety of the lid is: M.S. = 1,661,160-1 = +6.54 O ' 220,400 The maximum bending stress in the lid can be approximated by applying a pressure load sgainst the lower lid plate which is made up both the lid weight and the weight of the payload. Total force is then l 1 F = (W11d + w )(A } # p p g = (6600 + 20,000) (32.6) cos (43.9') = 624,833 Distributing this force over the face of the lower ) plate the pressure, p, becomes P = F /A A = 11(38.63)* = 4688 in8 p = 624,833/4688 = 133.3 psi O 0024k 2-42

l STD-R-02-016 l The pressure on the secondary lid is applied to the primary lid as a ring load, W, with diameter equal to the bolt circle. Using a 32" bolt circle and a 29" diameter secondary lid place, the ring load is H W = 133.3 I (29)8 876 lb/in = H(32) or 14,026 lb/ radian A finite element model of the lid was used to calculate the stresses resulting from this loading and to evaluate the ability of the lid to act as a composite plate. (See Appendix 2.10.6). The maximum plate stress intensity calculated for the above loading was 33,830 psi and occurred at the lower surface of the lid at the edge of the access hole. The resulting Margin of Safety is 38,000 -1= +0.12 M.S. = 33,830 If a "loose" payload is assumed, an equivalent pressure load against the inside of the secondary lid can be calculated using the payload density, payload O depth and impact acceleration. Payload weight reacted by the lid is: T (20,000 B.) W = 80.25" (29")*w 1 - 2827 lb. P 217 gg,s 1728 in /ft 3 s Secondary lid weight: W = 1150 lbs. g Total force reacted by the secondary lid lugs is then: F *(w +w)*

"U T

p L g Where a is the impact acceleration and o is the 2 impact angle (s 45'). F = (2827 + 1150)(33.9)(.707) = 95.320 lbs. T Maximum bending stress in the lid can be found assuming a line load on the 1" plate at the outer diameter of the 2" plate directly below (diameter = 30.75 in.). Assume the outer edge of the 1" plate is simply supported (diameter = 35.8"). The maximum moment in the plate is given in Roark (5th Edition), Table 24, Case 9a, as: 0024k 2-43

STD-R-02-016 O M = va L e 9-Q f'o\\* Where I,9 =b b in d + - 1-( a), a 2 4 r, giving: M = 95,320 (35.8) (.1235) C 1r (30.75) = 4,362 in-lb/in. Plate bending stress is given by: 6M Ib"f 2 6(4362)/1 = 26,175 psi = Thus, even with this conservative assumption, the Margin of Safety is positive: M.S. = 38,000 -1 = + 0.45 26,175 The stress in the stud consis'ts of two parts, that due to preload and the impact loading. The preload force can be estimated using Equation 6-16 from Shigley, Mechreical Engineering Design, 3rd Edition: T = 0.20 T d bp Vtere T is the bolt torque (100 ft-lbs.), F, is the bolt preload and d is the bolt diameter (.75 in.) F = 100 ft-lb (12in/ft) = 8,000 lb. P .20(.75 in.) Impact force reacted by the bolt is: T = 95,320 11,915 lbs. = bi 8 J These brees are aco.' because the gasket "spring" is much sof ter than the stud "spring, thus preventing unloading of the gasket when an additional tension is applied to the bolt. Total force in the bolt is the::: F =T F bx bp + bi = 19,915 lbs. I 0024k 2-44 l

STD-R-02-016 O-Stud capacity is (for a 3/4-10 UNC ASTM A320 Grede L-7): P = F A = 105,000 (.309) = 32,450 lbs. g The Margin of Safety for the stad.e is then: M.S. = 32.450 1 = +.63 19,915 4 When impacts occur on the lid end, a normal comprr.ssive load of 1,121,000 lbs (Table 2.6.6.3-2) is then transferred from the lid to the lid closure ring. The loaded length is conservatively estimated by considering only the length of the section which would be deformed during the impact. This load is then transferred to the cask via direct compression of the lead shielding and the steel walls. i = 2RO Where: R = 41.75 in. O = cos" (1) .,f R See Appendix 2.10.2 s r=R-5 sina i 6 - 1.15 a - 43.28' r = 41.75 - 1.15 = 40.07 in, sin 43.25 0 = cos"I (40.07) 0.2844 rad. = 41.75 i= (2)('41.75)(.2844) = 23.75 in. The minimum yield bearing capacity of the.19 x 1.50" bearing ring (AISI 1018 or A-36) ist F = (23.75)(1.50) (36,000, => 1,282,500 lbs. B The associated Margin of Safety ist M.S. = ly282,500 -1 + 0.03 = () 1,121,000 0024k 2-45 j 4 I

1 i STD-R-02-016 l (\\ The lateral load transferred between the lid and the \\_ l cask is estimated as 1,171,000 lbs. The load is initially transferred from the exterior lid plate to the interior lid plate via a 1/2" circumferential bevel weld. The interior lid plate transfers this load to the cask body by direct compression. This compressive load is trancierred across a deeply i stepped recess of the interior lid plate within the cask inner cavity. The load yield capability of the circumferential lid weld ist i F, = F,A, F, ' wD ' t, = (21,000)(w)(77.25) (.5) = 2,548,224 lbs. = i The associated Margin of Safety is: 2,548,224 -1 +1.18 M.S. = = 1,171,000 Therefore, it can be concluded that the package can survive a normal corner drop on the top corner. The damage to the area immediately _ adjacent to the impact crush zone for the bottom corner drop is minimal. The base plata-to-outer shell weld is O partially crushed but thin does not affect the cask integrity. The drain plug is located well outside the crush area and therefore, will not be damaged. The integrity of the cask base can be demonstrated for the bottom corner drop using the base interface forces given in Table 2.6.6.3-3. The interface forces result from body force loads t imposed upon the cask, payload end lid as indicated in the following free body diagrams: 1 1 0024k 2-46

1 l STD-R-02-016 b d Where: A i

== can ~ (d/t) ) = s 43.25* f W = t tal weight T ji a = load factor g 11 / j f T. 4 F T " w *Ic't. force t **1 T 9 imp 0 F = F cos e, g Ts g lo$gitudinal ) I s, impact force F 1,J,,in=, TC i F Fs = F TS ,1 y impact force The cask body (sides and bottom) internal forces are: Where: l d j W = weight of e cask g F =W a coss 1 43,3 C3 cs " c g ?f s F F' 0 b *** B S lg unknown lid s V g interface s S forces and s y s

moments, g

'w 0 e respect-y ively. Similarly, the payload forces are: i i F

Wa cos

p at xp F

Wa sin

Ps pg Where: W = payload weight p \\ <; O 0024k 2-47 i

. ~. - . -.. _. ~ + i l STD-R-02-016 l I 4 TABLE 2.6.6.3-3 l I I CASK BASE LOADS DUE TO BOTTOM IMPACT i r 4 INSIDE OUTSIDE OUTSIDE LOAD DrfDFACE Ft)RCES CASK WEIGHT DIAMETER DIAMETER HEIGHT FACit)R AXIAL SHEAR MCSIDrf MODEL (1bs) (in.) (in.) (in.) (g's) (ib.) (ib.) (in-lb) +6 +6 +6 x10 x10 x10 4 i HN-215H 58,400 77.25 83.5 88.75 32.6 1.237 1.191 52.75 i f 2 i 1 ) i i i l 1 h l ? I l I 4 l i i f I t l i i f 1 I. I t i 1 i ) 0024k 2-48 t m._..-,.___~,.

STD-R-02-016 ,A Now, based upon the payload and cask body forces, the lid interface forces F3, V3 3 and M can be estimated: Axial: FB+ F +F 0 = ce pc g(e FB" ~* + p Shear: V -F 3 F, 0 = p V = a (W + W ) sin = S g c p Moment: My+F, E+F, E=0 e c p p g (W x + W E ) sin = M = -a B cc pp Assuming that the stress due to the moment varies linearly with distance from the cask center, the i stress due to the moment can be calculated using simple beam theory. Assuming that the base plate-to -outer shell weld carries the entire load: F f" 3 = wDe Where: O F ,000 lb. = B 83.5 - 2(0.875) = 81.75 in. D = l .5 +.707(.75) = 1.03 in. t = 1 f 1.237 4.676 psi = = g w (81.75)(1.03) fb" I Where: M 50,750,000 in-lbs. = 3 1 81.75/2 = 40.88 C = w(r)st = w(40.88)8(.88) = 188,802 in." I = 1 , 50.750,000 (40.88) g 10,989 psi = 188,802 1 i Suunning the forces: i t v f 10,989 + 4676 15,655 psi = = T \\ 0024k 2-49 i i ) l'

STD-R-02-016 The Margin of Safety is V M.S. = 21.000_ -1= +.34 15.655 Assume that the shear component V is carried entirely bythe.5inchfilletveldjoininlthetwobase plates. f v =.L. Aw k'here: V, = 1,191,000 lbs. A,= w(81.7$ - 2(1.5)) (.707)(.5) = 87.46 in.8 fv = 1, 1,000 13,618 psi = 87.46 Margin of Safety is: M.S. = 21,000 - 1 = +.54 13,618 O The maximum bending stress in the base can be V evaluated by applying a pressure loading which reflects the payload weight and the weight of the base plates. Conservatively use the loadings from the lid analysis and consider the base to be simply supported plate with a diameter of 83.5". Applying the 138.6 psi load over the entire plate the moment becomes (using Tabic 24 Case 10 from Roark): .20625 = e he88* . 8 M .83.5 .20625 (138.6) 49830 in-lb/in i = = 2 Bending stress is then f 6(4 830) 18690 psi = = = b 38,000 M.S. - 1 +1.03 = 18,690 e The ability of the plates to act as a composite can be inferred from the results of the finite element J \\ 0024k 2-50

+ STD-R-02-016 analysis used for the lid evaluation where a much higher bending stress resulted in a relatively small weld stress. (See Appendix 2.10.6). Thus, the cask base is seen to be capable of withstanding the corner drop impact and maintaining the cask integrity. 2.6.7 C,orner Drop 4 This requirement is not applicable since the HN-215H cask is fabricated of steel. 2.6.8 Penetration From previous container tests, as well as engineering judgment, it can be concluded that the 13 pound rod would have a negligible effect on the heavy gauge steel shell of the cask. 2.7 HYPOTHETICAL ACCIDENT CONDITIONS Not applicable for Type "A" packages. 2.8 SPECIAL FORM l 4 Since no special form is claimed, this section is not applicable. 2.9 FUEL RODS Not applicable. l i 1, i i l ] 0024k 2-51

l STD-R-02-016 2.10 APPENDIX 2.10.1 Intentionally Blank i a 1 i i j 1 1 1 i i l \\ 1 i 1 l i

l

] 0074k 2-52 i I _.

.= __ 1 STD-R-02-016 l J I j i APPENDIX 2.10.2 VOLUME AND AREA ESTIMATES CORNER IMPACT ON A CYLINDER 1 j e i i i i l l ^ l 1 I i a 0024k 2-53 1 -y er-r--- ,.,..,w __,-9 ,r_...-,.,g -_,wy, ,__.q, _,,+.,vm ,e.e.,~9. ww ywmgy.y..

STD-R-02-016 1.0 Volume Estimates 1,1 Total Volume The geometry and nomenclature of this model ist er. E a. A I s(x-r ) tan = /* V $&iCRUSH DEPTH sin a. 1 x / (RL d)h + The volume of the shaded differential slice shown ist dV=(R-x)hdx 8 8 8 8 (R -x )

(x-r) sin = dx

= The total volume'is (R _x )h (x-r) dx l'r a 2 tana V = g Evaluation givest 2 tans { (Ra-r )3/2 + a 2 (Ra-r ) - rRa [J - sin ~ (I)]) 8 V = g 3 2 2 2 R Or: V = 2 tan = {.t +y3 - tB 2 - sin (.#) ) ~ 8 8 8 g 3 2 2 2 R Wheret (R -r )h; 8 a J t= 6 r=R sin = i i 0024k 2-54 1 l

i e STD-R-02-016 i 1.2 Component Volumes The steel volume is composed of side and bottom portionst i v "Yside + bot s dde R0 (R-r)t, tan = V = Vbot "b l Where: 0 = cos-1 (I) R t, = external steel side thickness (in) t = steel end thickness (in) b i The lead area represents the residual VL " v ~ Y I (v ~v ) >0 t s e s =0

(V -V,) <0 t

2.0 Area Estimates 2.1 Total Area f i The differential contact area ist { dA = { ~*)

dx j

cos = The total area ist I 8 8 2 / (R -x ) dx A = g cos a r i 2.2 Component Areas { -l The steel area (of the side walls) ist A = 2t R0 * (1 + * "

( E= ) ]

1 -1 + s s O c The lead area is the residual i A = A -A,; ( A -A,) > 0 g g g =0

(A'-A ) < 0

!O 4 0024k 2-55 t

STD-R-02-016 3.0 S,r *,a Energy Estimates ..I Flow Stress Approach S. E. = V,

o,p + V
e g

gp Where e,p = steel flow stress o = lead flow stress gp 3.2 Crush Stress Approach S.E. =,l I ((F - 6,g)] g + F,g) (6g g g 2i Where ^ # se + ^t tc F = s g g g o,, = steel crush stress o = lead crush stress g o = assumed crush' depth at the i* step g O 0024k 2-56

I STD-R-02-016 1 1 1 j r i I l 1 t i i APPENDIX 2.10.3 CASK BINDER SPECITICATION i 1 1 a i. 4 i i I 9 I .I 1 e i 1 i .I 1 J 0024k 2-57 t

STD-R-02-016 1.0 Binder Reference Drawing STD-02-077 for design details. 1.1 Bolt Strength J Bolt yield capacity is (for a 1-1/4-12UNT, ASTM A320, Grade L-7) P =F ty^ " i 1.2 Lug Strength (Ref. Hughes Structures Methods Manual, Section 4.4, Lugs, on following pages) 1 l Lug Yield Capacity ist P = 2KDty F y ty Wheret Efficiency Factor.(Use W/D Ratio in Figure K = 4.4.1-1) 2.65 3.00 W = = D 1.13 1 1.51 K = 4 i 1.13 D = 4 .94 t = Yield Factor (Use K Yactor in Figure 4.4.1-2) y = 1.05 = L ) 38,000 (ASTM A-516, Grade 70) F = gy P = 2(1.51) (1.13) (.94) (1.05) (38,000) = 127,993 lbs. 1.3 Pin Strengths (Ref. Drawing STD-07-077, Note 13) Upper Pint Double shear yield capacity = 117,000 lbs. Lower Pin: 1" Dia, Grade 8 bolt J P = 2F,yA ] I O 0024k 2-58 I

~.. _ _____. _ ___ _ _ _ _. i s I STD-R-02-016 i I i Wheret I 2 F (.6) (130,000) = 78,000 psi ] = 3 sy A 1 (1)8 =.785 in.8 ] 4 I 4 2(78.000) (.785) = 122,460 lbs, f l P = I Y 3 I Rated binder capacity is 100.000 lbs. Bolt yield capacity is the minimum l l at 112,665 lbs. The resulting Margin of Safety ist l i M.S. = Py - 1 = 112,665 - 1 = + 0.13 ( ~ I i T* 100,000 l i I l 4 i i I i 1 1 1 1 l i 4 i I t ] i 1 ',I

,h 1

1 j l 1 0024k 2-59

!_-____,,___.-______.~,.,-

l o ^ STD-R-02-016 i i ) i i l l ) 1 l 4 s l-1 f + t i

i j

STRUCTURES METHODS MANUAL 4 Hughes Aircraft Company Space Systems Division El Segundo, California 1 i 1 j Tebruary 1966 j i i SSD 60048R l i l I l l i 0024k 2-60 l i i

STD-R-02-016

4. 4 LUC 5 The following analytical procedure should be used for the design of lugs and shear pins. This analysis is based on static loading and does not consider the effects of multiple applications of near limit loads.

The design charts encompass the following types of failure for a lug-pin combination (see Figure 4.4 1): 1) Tension across net section 2) Shear tearout or bearing 3) Hoop tension at tip of lug 4) Pin shear 5) Pin bending These charts represent envelopes of structural failure and are not identifible to a specific failure mode. Lugs should be conservatively designed, as their weight is usually ) small in relation to their importance, and inaccuracies in manufacturing are difficult to control. Applicable fitting and casting factors shall always be used in the analysis. Margins of safety for presentation in the stress I analysis report shall be based upon the pin size and lug hole diameter shown l O on the engineering drawing, Mabetaapass j t - = \\ j mee toa l Tigure 4. 4-1. Failure Modes { 4.4-1 0024k 2-61 , _. _ _ -. _ _ _ _ _ _, _ _ _ ~

STD-R-02-016 \\

4. 4.1 Symmetrically Loaded Luga O

Axial Lead i i 1) Allowable ultimate axial load a) Enter Figure 4.4.1 1 with R/D and W/D to obtain the minimum K. Use the approgriate W/D curves indicated by the material clas sification in Table 4.4.1 1. ' b) Compute allowable load by Pu, KDtFtu' s c) Compute the margin of safety in the normal manner. 2) Allowable yield axial load a) Enter Figure 4.4.1 2 with the minimum K determined in 1 above to obtain y. b) Comp'.te the allowable load by Py = y (F y/TN) Pu t (Lug yielding is based on a permanent set of 0.02 times the pin diameter), c) Compute the margin of safety in the normal manner. j Lateral Load 1) Allowable ultimate lateral load a) Compute the allowable ultimate axialload per above mentioned proc edure. b) Enter Figure 4. 4,1 3 with 4, angle of load application, to obtain (P /P). Use the appropriate curve indicated by the 6 mate rial clas sification in Table 4. 4.1 1. c) Compute allowable load by P6 =(P 6 /P)Pu' d) Compute the margin of safety in the normal manner. j 2) Allowable yield lateral load a) Compute the allowable yield axialload as previously mentioned in the axial load procedure. b) Enter Figure 4. 4.1 3 with 6, angle of load application, to j obtain (P6 /P). Use curve 2 dy. c) Compute allowable load by Pg = (P g /P)P. y d) Compute the margin of safety in the normal manner. I 4.4.1 1 a 0024k 2-62 -~-.n..-.-.- .,, - -.. ~, - - - -, -.,. ~ - -, -, -, - - - -,,, - - - - - - - - - -

STD-R-02-016 TAB LI 4.1.1 1. MATERIAL CLA55!T! CATION Applicable W/D Curves for Critical Crain Dir ec tion - Tig. 4. 4.1 -1,3 hterally 2 Material kng Sho rt aded Lugs i 7 II'4*4'I'3 I Longi. Trans. Trans. tudinal verse ve r s e*

i Carbon and alloy steels -

AISI g rad e s 1 1 1 1 18-8 stainles s steels 4 4 4 4 2014-T6 plate 1 1 5 4 2014-T6 die forging 1 1 5 4 2014.T6 hand forged billet Area 5 36 square inches 1 1 5 4 Area > 36 square inches 1 3 5 4 2024-T4 extruston 2 2 2 4 2024-T4 bar 2 2 5 4 2024-T3 plate 2 2 5 3 2024-T4 plate 8[l 2 2 5 3 7075-T6 extrusion 1 1 1 4 7075 T6 plate t s 1 inch 1 1 5 4 t > 1 1nch 2 2 5 4 7075-T6 rolled bar 1 5 5 4 O(d 7075-T6 die forging 1 1 5 4 7075-T6 hand forged billet Area s 16 square inches 1 2 5 4 16 square inches < area s 36 square inches 1 3 5 4 Ar e a > 36 s qua r e inc he s 2 3 5 4 195-T6 ca sting 3 3 3 4 { 220-T4 ca sting 3 3 3 3 356-T6 SC ea sting 3 3 3 4 3 56 -T6 P. M. c a s ting 3 3 3 4 Ti 6Al-4V forgmg 1 1 3 4 Mag. ZK60A die forging 1 1 3 4

Us e the curves designated herein for Tigures 4. 4.1-1 and 4. 4.1-3 1 Us e curve 2 for all yield computations 2 Curve A is to be used for all aluminum alloy, hand forged billet when the long transvers e grain direction is the same as that critical for R/D shown in Figure 4. 4.1-1 3 Curve B is to be used for all aluminum alloy plate, har and hand forged billet when the short transverse grain direction is the same as that critical for R/D shown in Tigure 4. 4.1-1, and for die forgings when the j

lug contains the pa rting plane in a normal direction. 1 4.4.1-2 0024k 2-63 i i

l 1 i STD-R-02-016 i ( 1 r

_. stri e 70 148k8 i F64 peest a.yset_

4 -. i ~* - ' = _ ~ _ 3- . i._ _, .S . ".. ' '-2 8 ..___b,

m 7.g:

g "j _M.g::Ex::J 7 a i:-._ ;.. - ,,, -i__ ,3.:

i. --

1 u ,,?,5 -.-,--~s 7.,,g .w E - - - < - ~~ \\ i .-o _e ~' 86 - '. - - _.m. _. _-y r. -'..-r .. -a M. l u... _,, -_ w v ~ i. t_._, . _ _ _ 4_ ..,-..-~.:. ' I " i d',- 3 - - w _ 5.. '.g... -u.

v. _. _ _ -.

g ) . u_ i g _.- -.- '. g.m: _ f_ -... e = -. -. 'w_ , y i 3e . =. =. - - r- . s_.. -d .. _, _ ~ a,. :,;.a _ . _P' - " - ' ~ ' y__._ l-_.g-,.-- - - -, f, i -?--- e-*-' ~~ u -- - =, _ ~ ~. - - I="": ~-e- ' _e +s p**.-

4.,f:

s q s,, e- -

ggg.

g.

~ - e. =.. t..~ -3 n a -- -.. - ~ ~', p* ;; w a. + _.. _ - i -- :: -,u.+e-r- - -- - .= -.. J~.;;g -.-.e_{_,-- - - - - -1 --":a..4- '-f,__ y ,i

s. ---

i...--..,. 1 ...-7-- e. .._.. -; _.;;f,-- . -a.= = ._L; =-,_. -. = = =.

==

g _-- ;.,,,,,,,,,,,,,, i s i. ~ =,._-_ __ __. y _,_, _ _ 1 7,., - - -.r-.m n-g g c._ _r; y of. . j _ -- an ,,, t... n.,,,,,,, .~-- _. ;= :y,p.. _. _;,:-4_ - ~.-...s v. u........,~, l .. a.,s. sa...... s<. \\ V -.,. M_.-m n e ~ --m. .:1- _._ m. s _ i-1 ,--g== g ,,,,,,,,,1,,,,,, I.. -...,. . ; :. t. . - -w __ jJf t =- ' "J .r. --ia _-X .._ =.c3.. __,,_,,;

.j.--

<,11.......(.--;-m.=_------

. i 4 : - :. ;..:.*.- -a n _f ._ _ g =.:-..?. 4.. f.;-@ ;"=g:-.ye.. .sy; L. i s J ,4. J.... ~,-,. 4 _. t' .1.__..._ . -. L=.1+.--+-.e==.. --i._. ,o '~ ~~~ h,. g, M, 1 - ~ 88" ~~ 7"""-" 8,e a $ e #,, g:- - .m ,,.====----f _... i = = _; _ _ j_-47.- , _ _ --.=JL. T il 4 J - gr d ll AI 4- .a =g. _n gg j r e, . a. - a =. =.::1Y. ' __. 4 ~ i i f it Lv. -J-i I ~~ 40 .. _ _..__-- ;..:..t .=. ~ - ' - - w_ 4-hi l temgak easie piettti f L--- g ,,t_, T semea6...esotetos g r_ m r - r- ,.hy !.nt s.* e c e ,e t 4e,t 4 6 seain Diet tech r . i--. i-- - 4---' e--- am o se es 64 Asis se 4 tJ SJ terittoCT Pente, a Figure 4. 4.1 1. Axially Loaded Lug Design Chart C 4.4.1-3 0024k 2-64

STD-R-02-016 i J ~__+ u .-). . I l.:.. :. 4.. --[. 4 r L- : -i=_4 i;j w-r i lefr.- xm.-. s. rr;-w c. t. .i.,..a rt --i.t e, I wriMa4= +I i ..IH L ~4-- MI:~.-~4 'g 7,"~e,.~ 7-. Mm .L 'M ~ ' " ^ - ea a .w -. g,, ,.= --.1 w. r-u,.,,,

-- A p =. _--

. 'm - I u.---%__,,--=.,...,_-<3- - c-j =1 4::r=;- 2.-T=~ T. = 4-L:3= ".^.i' -X.T_.. =' :-- =.a _...,, : + _.- s b..~. ; c.._...1. : :-r-_

--- = ~

o a,.e i. .: - r-.. -- r..= + r:n-- .L -:,,.p-w- ..- m. ._.._.'T. .'- M -T _r..*r 7 h % 2 D I--T N D '.~~.U, -- L l; ' ~ 2 c2 m, , --.u.e ~.;. _.a., --- 1. m. -a ..:-a r--- L- _.....M rg J;! :fi 0 02 04 44 04 10 at i4 644 el Le 22

3. 4 3.4

(#81 Cit'eCY Fat'Ot, a Tigure 4. 4.1 2. Yield Correction Factor for Axially Loaded Lugs V _mr- -g ..,.,,,,,.e,.

stegeTC948.1 #ce seosts 3.04 W ;.4rq s es., *: a..ww a.'.;, g g

[ L:**.'a' :%t _

St

.*et38?* a..t.: e i.e.tl DC Ma , ; gga.. v y.g _-;,uj :

4. *%: l=C o* g o: g g g,a a 2, g,,og;. ye g agan,g gr j g

5..m ,efwe ll 14 h:* a**.' *. 45 e *. a r: e e ve,g. p/,4,.M-1. _v .e.t t a**.* *:.. s t *.c.a. t t e s:*.s as s-en-a -mA. -m m _ _ mcWSs=ymm 74 -"3 - - ~ hN 1=C".GN _ w Mp m z.,.7. g_ &* - ~ ' ' 'y g' % VT. L t8 -^ ~* 1* Wh$ 5'? .h mmm es:g w%, - - _.- r'. -;;.- T an F m : -- - %wm r 4 r:: [..% w wg.... v

4 -m m

= - - - -n gy_a ,-gg.g v. .e / i I. fO 1

e.*+t es..sa 4

e as t, ..e ,e no 4NE$ 4 M 644.18 e Tigure 4. 4 1. n Late r N-Lug Le i., N I 0024k

I STD-R-02-016 i l i 1 APPESTIX 2.10.4 (Intentionally Blank) i i l l 0024k 2-66

j i t STD-R-02-016 i i 1 l 1 t i i t i 4 I l 1 APPENDIX 2.10.5 4 ANSYS CAPABILITIES l 4 4 i I a i 'I a i i d l, I i I i 1 i I l 1 i } l I t J J I 1, l 1 I i 0024k 2-67

I l STD-R-02-016 ANSYS USER'S MANUAL ABSTRACT The AN$y$ computer program is a large-scale general purpose computer program for the. solution of several classes of engineering analysis problems. Analysis capabilities include static and dynamic; elastic, plastic, creep and swelling; buckling; small and large deflections; steady state and tran'slent heat transfeF and fluid flow. The matrix displacement method of analysis based upon finite elpent idealiza-tion is employed throughout the program. The library of finite elements available numbers -ore than forty for static and dynamic analyses, and twenty for heat trans-fer analyses. This variety of elements gives the ANSYS program the capabllity of analyzing two-and three-dimensional frame structures, piping systems, two-dimen-sf onal plane and axisymetric solids, three-dimensional solids, flat plates, axi-symetric and three-dimensional shells and nonlinear problems Including Interfaces and cables. Loading on the structure may be forces, displacements, pressures, temperatures or response spectra. Loadings may be arbitrary time functions for linear and non-linear dynamic analyses. Loadings for heat transfer analyses include Internal heat generation, ccnvection and radiation boundaries, and specified tenparatures or heat flows. The AN$y$ program uses the wave front (or "frontal") direct solution method for the system of simultaneous linear et,tions developed by the metrix displace ont O method, and gives results of high a uracy in a minimum of computer time. The pro-gram has the capability of solving orge structures. There is no limit on the number of ele ents used in a problem. TFsre is no "band width" limitation in the problem de fini tion ; however, there is a "wave f ront" restriction. The '% ave front" restrie-tion depends on the amount of core storage available for a given problem. Up to 576* degrees of freedom on the wave f ront can be handled In a large core. The wave front limitation tends to be restrictive only for analysis of arbitrary three-dimensional structures. AN$y$ has the capebility of generating substructures (or superelements). These substructures may be stored in a library file for use in other analyses. Substruc-turing portions of a redel can result in considerable coguter time savings for non-linear analyses. Gannetry ointtino is avallable for all elements In the ANSYS library, including 1sometric, perspective, section views, and hidden line plots of three-dimensional 4 structures. Plotting routines are also available for the plotting of stresses and displacements f rom two-and three-dimensional solid or shell analyses mode shapes from dynamic analyses, distorted geometries from static analyses, transient forces and displacecents vs. time curves f ree translent dynamic analyses, and stress-strain plots f rom plastic and creep analyses. Postprocessing routines are available for algebrate modification, dif ferentiation, and integration of calculated results. Root-sum-square operations may be performed on selsmic modal resul ts. Response spectra may be generated from dynamit. analysis results. Results f rom various loading modes may be combined for harmonically loaded exisymetric i; O .4tructures. ] An optional 1152 wave f ront is available on some very large computers. 1 A45 TRACT a.) 0024k 2-68

STD-R-02-016 The Input data for the AN5YS program has been designed to'meke It as easy as O possible to define the problem to the coneuter. Options for dultiple coordinate systems in cartesian, cylindelcal, or spherical coordinates are available, as well as multiple region generation capabilities to minimize the input data for repeating regions. Sophisticated geometry generation capabilltles are included for two-dimensional plane and axisyrretric structures and for Intersecting three-dinensional shell and solid structures. The ANSYS program capabilities are continually being enhanced by the addition of new or improved elements, new analysis espabilities, and new Input, output and graphic techniques. The ANSYS USER'S MANUAL is modified periodically to reflect the latest additions. l O ABSTMCT I a.2 0024k 2-69

STD-R-02-016 4,63 1 4.63 QUADRILATERAL $HEl.L This element has both bending and membrane capabilitlet. Both In plane and f normal loads are permitted. The element has six degrees of freedom at sach node: translations in the nodal x, y, and 2 directions and rotations about the nodal x, y, and z ames. Another four-node shell element ($TIF43), restricted to a rectangular or parallelogram shape, has rotated material axes and in plane pressure capabilities i available. 5 The quadrilateral shell has options for verlable thicknesses, elastic foundation supports, suppressing extra shapes, and for concentrating pressure loadings. Stress l stiffening and large rotation capabilities are included. 4.63 1 Inout Data 1 The geometry, nodal point locations, loading,and the coordinate system for this element are shown in Figure 4.631. The element is defined by four nodal points, four thicknesses, an elastic foundation stif fness, and the orthotropic fr.sterial procerties. The material X-olrection corresponds to the element x-direction. The shear modulus term is optional and if it is not included it is coguted from the other input material properties. The thickness 15 assumed to vary smoothly over the area of the element, wi th the thickness input at the four nodal paints. If the element has a constant thickness, only TK(I) need be Input. If the thickness is not constant, all four thicknesses must be input. The elastic foundation stiffness (EF5) is defined as the pressure required to produce a unit normal deflection of the foundation. The elastic foundation cambil-Ity is bypassed if EFS is less than, or equal to, zero. The element loading can be either surface temperatures or pressure, or a co41-nation of both. The positive direction of pressure Is along the positive element z-axis. The pressure loading may be uniformly distributed over the face of the element (KEYSUS(2)=0), or a curved shell loading (KEYSUB(2)=1) consisting of an equivalent element load applied at the nadal points may be used. The latter loading produces { nore accurate stress results in curved shells because certain fictit ' element l bending stresses are elimirated. The KEY $UB(1) option is used to suppress the extra displacement shapes as de-scribed in Section 4.0.6. The KEY $UB(IA) option allows deleting the nominal in-plane rotational s tiffness as described in Section 4.0.7. A sunmary of the shell element parameters is given in Table 4.63 1. A general description of element input, in-cluding the special features, is given in Section 4.0.2. 4.63.2 Outout Data a) Printout - The printout associated rlth the shell elenunt is sumarized in Table 4.63.2. Several items are Illustrated in Figure 4.63 2. A general description of element printout is given in Section 4.0..). Line 2 includes the shear forces NI and NY in the element x and y faces, respectively (posltive in the positive element a direction). The poeents about the a face (MX), the moments about the y face (MY), and the twisting eccent (MXY) are also printed in line 2. The forces and moments are O calculated per unit length in the element coordinate system. The optional edge printout is valid only along free edges of the element. 1 STIF63 0024k 2-70 i

STD-R-02-016 4.63 2 The next three lines include the stresses for top, alddle, and bottom eleeent O. surfaces, respectively. The combined stresses $X and $Y and the twisting stress TIY are the combination of the membrane stresses and the stresses corresponding to the caculated bending coments, respectively. The positive bending stresses occur on the top face of the element for the positive banding moments shown in Figure 4.63 3 Nodal stresses may be obtained from the POST 25 printout, see Section 6.25. b) Post Data - The post data associated with the shell element is sh o..n be i m The O ta arar wri t ten on file TAP!!2, if requested, as described in Section 4.L L.

1. $X(MIO)*TK 9-11. $X,$y,7XY[ TOP) 33-35. XC,YC,2C

2. $Y(nl0)*TK 12-17 $-il,$,[Ml0,80T]

36-37. AREA,TTCP 2

3. TXY(MID)nTK

,,15-20. $Mx,$MN TNI[ TOP),, I*33-}9*.TBOT88ES$

- 4 4-5.

NX,*,Y 21-22. $1GE.A[ TOP] i,6-8; M y !,$XY, 23-32. 18-22 $ [MID,80T) 4.63 3 Thesev The me,srane stiffness Is the same as for the membrane shell element ($TIF41), including the extra shapes. The bending stif fness Is formed f rom the bending stif f-ness of four triangular shell elements ($TIF53). Two triangles have one diagonal of the element as a com-en side and two triangles have the other diagonal of the element as a comon side. The stiffness is obtained from the sum of the four stiffnesses divided by two. 4.63.4 Assumotions and Restrictions O Zero area ele'wnts are not allowed. This occurs most often whenever the ele-rents are not nuncered properly. Zero thickness elements or elements tapering down to a zero thickness at siy corner are not allowed. The applied transverse thermal credient is assumed to be line~ar through the thickness and uniform over the shall surface. An assemblage of flat shell elements can produce a good approximation to a curved shell surface provided that each flat element does not extend over more than a 15' arc. If an elastic foundation stiffness in Input, one-fourth of the total is applied at each noce. Shear i ef f ection is not included in this thin-shell element. A triangular element may be forced by defIntng duplicate K and L node nurters as described in Section 4.0 9 The extra shapes are automatically deleted for trl-angular elements so that the mer6rane stiffn' ass reduces to a constant strain formu-lation. The four nodal points defining the element should lie in an exact flat planet however, a small out-of-plane tolerance Is permitted so that the element may have a slightly warped shape. A slightly warped element will produce a warning message in the printout. If the warpage Is too severe, a fatal message results and a triangular elvent should be used, see Section 4.0 9. The triangular shape is recommended for large deflection analyses since a four-node element may warp during deflection. The out of-plane (normal) stress for this elenant is assumed to be zero.

O STIF63 0024k 2-71

STD-R-02-016 ] !() fatLC 4.63.1 0040#1 LATERAL SwCLL l ELCWCNT Nant STIF61 + No. Or NOBE5 6 !.JeRet i QEGREES OF FRICDON P(9 N00E 6 UseUY,UZeROTAeROTTee0TZ j etal CONSTANTS 5 Tv(!)eTKtJ1.TKIRiefvtLletF5 174 tJi e TM tMl e TR tL a OEF AULT TO TR t ill NATERIAL PRO *CeflES 6 CteEY.ALet.AL8YeNUAve0CNS ) nxY (0*T10 Natl ) (DIRECT!ON 1-J 15 Al 1 peC55uet$ 1 kntMAL PWC$$U#C ACTING ON FACE 1 (U5C NEG ATIVE PRES $u#C FOR I n##051TC LO A0,1 ngl 7t**Ekafvat5 3 TTopeT50TTON SotCIAL FtatueC5 STRC55 tT!rFENINGe LARGC WOTAfl0N <tv5WHill 8 = INCI UDC E ATR A 015PL AcrwCNT SMapt5 1 - 5V**RE55 CAf aA Oll'LactN(NT SMAdr$ j

EY509tlas 0 = lite **ltu!CZ IN=#LANC 80TATIONAL sitFFwC55 O

1 = NO INa#L ANC #0T ATIONAL STIFFNC55

Cf5Udtil 4 = FLAT SkCLL setsluet Lc40!NG 1 = cu#vt0 5=CLL PRC550dC LO ACING (CYSU81281 0 = NO FOGC PRINTOUT N = COGF PRINTOUT AT EDGC N (No 1,3,1 og 6) i 1

l 1 i 1 i O l 1 STIF6) I 0024k 2-72

STD-R-02-016 4.63 4 = o - u,e. b 4 L TTCP a y g. / \\ , i., 's TK(K) q

T,*

l .g g i

i

T l l I K.L l h l g RF45tRE J y (Tri. Option) Y ^ Note - x and y are in the plane of the elvaent. l x is parallel to IJ. l x

O Figure 4.63.1 Quadrilateral Shell 4

NY Element a l Coordinate System n EX l SY / $X(TOP) EX / $X(MID) I SX(BOT) g MY 7

Y 0

J l g -x i Figure 4.63.2 Quadrilateral Shell Cutput sTIF6) 1 0024k 2-73 I 1

4.63.5 STD-R-02-016 O TASLE 4.63.2 DUADRILATERAL SMCL'L CLEMENT PRINTOUT EXPLANATIONS ) NUwSEs OF ^ LABEL CONSTANTS FOIMAT EAPLANATION LINE 1 EL 1 15 ELEWENT Nuw9ER NODES 6 415 N0 DES - !,J,x,L 447 1 13 MATERIAL NUMSER AMEA 1 GIO.3 AREA TTOP,7807 2 2F7 1 SURFACE TEppERATURES - TCP.80TT0v PkESS 1 011 6 50RF ACE PRES 5URE LINE 2 MA,MY,eAY 3 3G13.5 MOWENTS IN ELEMENT A AND Y OIRECTIONS NA.NY 2 2013.5 SMEAR FORCES AC,YC,2C 3 3018.6 GLOSAL A,Y,2 LOCATION OF CENTROID LINES 3 - 5 O TOP, ulDOLE, OR ROTTON LC 5A.5Y.TAY 3 3G12.5 Cows!NCO #Ew84ANE AND BENn!NG STRE5sCS (ELEuCNT C00ADINATE51 SMR.5mN3TMA 3 3012.5 PRINCIPAL STNE55ES - 5tGwaA.StGNIN,TauwAA ANGLE OF P INCleAL STRESSES RELATIVE TO A 1 /61 R ELtuCNT A-Y ARES SIGE 1 012 5 EDV! VALENT STAC55 L INES 6-9 EDGE PRINTOUT (PRINTED ONLY IF MEY50R(2SI

1,7,3, 04 el LOC 2

216 EDGE 40 DES F DRCE/LENGTN 8 4613 5 (SE.5Y,TAY AT EDGE) * (THICENC55), MA.MY,mRY AT EDGE, NA NY AT EDGE STRESSES 8013.5 51,5Y.T AY AT EDGE. (MA.4Y,MAY AT EDGE) * (6/tTNICMNE55*.211, (NA,NY AT EDGCI. (1 5/THICMNC55) O STIF63 0024k 2-74

STD-R-02-016 O APPENDIX 2.10.6 CASK LID ANALYSIS O O 0024k 2-75

STD-R-02-016 The HN-215H cask lid was analyzed for a pressure load plus a ring load which ,gi simulated the axial impact force imposed on the lid due to its own weight and the weight of the payload. The lid was modelled and analyzed using ANSYS (See Appendix 2.10,5). The lid was considered to be two circular plates connected by two continuous welds as shown in figures 2.10.6-1&2. The remaining interface batveen the plates was represented with gap elements which allowed compressive load transfer but no tensile loads. A coefficient of friction of.5 was used to model the contact friction between plates. A 10 psi pressure was applied to the entire lower surface of the lower plate. A corresponding ring load was applied to the upper surface of the upper plate at a radius of 16" to represent the secondary lid loading. The upper plate was simply supported at its outer edge. The stresses resulting from the analysis are given on the folicwing pages. The maximum stress is found in Element I with a stress intensity of 2450.5 pei. As expected, the stresses decrease with increasing radius. Note also that stresses Elements 8 & 9 and 150 & 151 are relatively low indicating the welds allow the 2" plates to act together as a 4" composite plate. O l O 0024k 2-76

riguro 2,10.6-1 STD-R-02-016 f *k e m U k 1 e(f! - 5 0 \\ 1 4- !,a 3 s 4 'g s Wk, d _; { i 9 ak e \\ != I

h 4 a i

LE

[ la L 6l i

1 i 2 $s i t; + 3' : g 9 i , u, sg to &d 1 $l! = \\ 4 i k 1 sqss e e i I'sSah 3 Y i (! j b i O F "ie H t ( ') L ! W h k a,.i[5 lk = w -i + ,f. k k C q' \\ 1-. ~ l# g 2-s [3s s I 4 ^ ~ sk \\ n g m .o +, s -s 4 %t 4 I .b. . b-N Q4 E O 1 0024k 2-77

STD-R-02-016 O / t I x

kn y g

( E! a; i 13 Ti B; 4' W 1 k Ti B' B! 9;:

4T fi Yt ! 9 i

!~ j

i t v i t'titit 3

,t ; m .$l f\\ ) '~ ' t' o N = y I i u g q% &h D i t % q i t a: 5 1 f I N N h E A d .o' t t g ea = = ci is 4 4 d 4 l E <,g g Q I g i s D --H--- j g 4 m 4 44S$ d S t. t t j.. g ww e ss ( g N. A d i s %s. 3 I e s w a s{- _s. s g m OS 4 7-1 14 I 2-78

STD-R-02-016 hkY/- kM C ^ W47 'A A S /AfWfJM-47,} / U E-p7. r wo ' .4/ = J=a e a,no-a Bryws!/ e' -b (%n) pn/M] < esr's s'i

kM & )

/ Wo Act &<xit \\ GA) - 0 (/ b) = 0 er ) - 0 (*)= 0 d@ (w) }$ns4/ fu n. _ df/wh-(i)~ / "i } } (1 ) P a.. Sd*M d w C740 7? A G ') G > 0 hk (2 ) $ = f hSWYJN$ ,, pp, p~g T (O).:u?n;t+*l,!c(s#46,pg,,- 1 (f) 97dW' / e6 y/o-o k/s . fi .= O 0024k 2-79

l i i i l oo i N D= X l &a4%YS - EssGINEERING AalALYSIS SYSTEM SEgl58 eat 3 UPDAIE 67L SIS ses JesetE l.1979 SMAasSeat AssAL16IS SYSIENS. Isec. sleeSleeI. FEsastSYLy&asI A 35342 recedef (412) 746-3384 j AasALYSIS -blet-2856{ FACKAGE. seestlISAL le PSIG PeESSageE 16.73S6 ?/ 3re3 CFs 3e.537 maa ELEstEssi SleESSES messa 33sgE a S. Leae STEra 3 ITERAIIs003 le Cist. ITER.s 20 SR I seseESz 8 6 7 2 stAls I wSLs 7.500 2-5 SOLID 42 Cs IS.se -1.758 IEMPs 20.e As 45.4 S.E.s 2458.5 SIGEs 2448.2 1 SY.3EY.SZs -94.843

194.S2 3.4424

-2548.4 SME.SMel.lMus -89.924 -100.64 9.3544 l 2 asseESs 2 7 8 3 ftAis I weLa

7. Set 2-3 S3 LID 42 l

Cs 85.88 -1.2Se TEMPS 78.e As 39.2 5.8.8 8771.2 SIGEs 3723.e SY.IIY.12s -32.333 -131.27 1.4041 -1883.5 SME.58es. IttKs -32.293 -131.29 49.500 1 t 3 IsetESs 3 (s 9 4 OIAg a 3 wet s 7.See 2.d (gg33 g2 ] Cs 15.00 .7500 30MPs 78.e As -74.5 S.I.s 3131.2 SIGEs 1813.5 SY.IMY.Sza Se.2g4 -152.31 -48.847 -8844.0 SetK.58st. INKS 67.222 -149.29 118.25 4 speeESs 4 9 Is S stat a I vets 7.500 2-3 SeE33 42 l 1 Cs 35.88 2500 1Egys 78.e As -44.1 S.I.8 366.29 SIGEs 317.23 1 Sr.1xv.SZs -114.39 -86.8844 -98.951 -375.18 Seek.SMel. letus -a.el34 -195.49 93.339 i 5 IsetESa 4 11 12 7' SEAT s 1 vet s

3. 9 38 2 3 SeL33 42 N

Cs RS.7S -l.75e IE8EPs 70.e as II.9 S.I.s 2443.9 SISEs 2335.5 l SY.1EY.SZs -251.74 25.164 68.247 -24e3.8 Seek. Sees.letKm 34.306 -264.68 1S1.39 j 6 IseeESs 7 33 33 3 stAls 3 wet s 3.934 2 9 SOLIS 42 O i Cs IS.75 -1.2$4 WEMrs 70.8 Am 33.3 S.g.a 1786.e SIGEs 163ts 9 i SY 13Y.Sla -108.87 -20.244 52.393 -86SS.2 SitK.Sfut. lftKs 38.891 -153.08 91.947 j 7 steefss a 13 14 9 play s 1 wets 3.933 2.D SOLIS 42 1, Ca 15.75 .750s IEers 7s.0 As 75.7 S.I.s 8809.3 SIGE8 3837.2 SY.8XY.SZs 157.92 -S4.686 67.868 -938.56 SetK.Saus.lsegs 177.74 -74.426 326.e4 3 steeES 9 14 15 38 ISAis 3 wets 3.933 2 9 SSLES 42 Cs IS.7S .2S44 1Eers 78.8 As -55.9 S.I.s S83.53 SISEs 558.37 l SY 1EY SZa 4.3204 -144.42 -236.S8 -349.49 SftK.Seul, segga 164.44 -344.74 254.59 9 assefsa Bel le6 387 182 ftAis I vets 3.954 2-8 SOLIS 42 Ca 12.75 .2500 IE8tPs 70.8 As -31.7 S.I.s 742.96 SIGEs 737.36 SY.1MY.52s -214.04 513.44 -327.07 326.9S $8tK.SMII. lftK a 315.63 -416.01 365.82 la asseESs le2 387 188 les stAls I weet s 3.9 38 2-9 SOLIS 42 4 4 e Cs 35.75 .7See TEfra Fe.e As 18.8 S.I.s 1857.9 SIGEs 1828.8 i SY.35Y.SZu -82.384 242.86 64.244 1863.4 Seet. Sees.leeKa 254.42 -94.449 174.43 I 31 gesaggs 333 les let 104 ptA g a 1 vet s 3.934 2-D SOLIS 43 l Cs 35.75 1.25e y ggys 7s.e As 34.1 S.g.a 373e.3 SIGEs 1676.4 m j SY.1XY.S2s S6.449 132.SS 96.298 1761.4 Sfet.Sful. 5MEs 195.24 -0.9455 103.59 g a 12 asseESs get let 3le les Mais ' 1 vets 3.934 2-D SSEIS 42 Cs 15.75 3.758 Iffra 70.0 As &c.g S.I.s 2428.7 SIGE: 2142.7 7 j SY.tuv.SZa 66.955 24.944 34.813 2427.7 Sper.Spel. Iput s 85.925 S.970s 39.978 o N l 8 l 13 seeSESs Il 36 37 32 Mats g vela 32.54 2 0 SOLIS 43 3 I Ca 14.75 -l.7Se IE8EPs ye.e Ar 3.2 S.I.s 2323.4 SIGE: 2323.9 m j SY.13Y.sla -444.4e -3.9776 27.597 -2325.4 Sect.Seel. ssets -2.4117 -494.34 243.94 14 teseESs 82 B7 18 13 fe&T s I wSLs 12.S6 2-8 SOLID 42 I I i

i -____- _____-__ o l CD w s-PC I ~ EC.YCs 16.75 -3.254 sEMPs 74.s as 12.S 5.I.: 1597.1 SIGEs 1513.5. ) SE.SY.vXY.52s -148.69 25.228 34.850 -8563.3 SMX.5MM.IMus 33.881 -150.27 92.041 Eta 15 NGDESs 13 IS 19 14 Mets ! Vets 12.56 2-3 Sgtgg 42 NC.YCs 16.75 .7500 TEMPS 70.e As -85.4 S.I.s 992.64 SIGEE 954.28 SX.SV.IXY.S2s 332.e3 53.254 -18.347 -889.81 SMX.SMN.lMX* 152.83 52.419 65.232 l Ets 16 peDE%s 34 19 20 15 MAva 3 wets 12.56 2-5 SetIt 42 j XC.YCs 16.75 .2500 TEMPS 70.e as -79.3 S.I. 827.33 SIGE 813.68 SX.SY. ixV.SZ a 849.77 101.64 -139.82 47.169 SMM.5MM.IMX* 875.05 76.360 399.34 Ets 17 NGSESs 20 Ill WSEPs .000000 USLIDEs.008133 FNs -34.589 FSs -17.255 SiAT* -2 etDSta -2 2-D GAP 32 Eta 33 meSESs 346 Ill 112 107 MAT 1 Vets 12.56 2-3 SOLID 42 XC.YCs 16.75 .2500 IEMPs 70.0 As -10.3 S.I.s 954.26 SIGE 940.62 SX SV.TEY.52s -943.52 -76.400 -162.98 -18.575 SMX.SMN.!MX* -46.778 -973.14 463.38 4 a { Eta 39 WOOESs 387 332 383 ISS Mais I vets 32.56 2-D SSLIS 42 ? XC.YCs 36.75 .754e 3EMPs ye.e as -10.2 S.I.s 1976.6 SIGts 1881.s l SN.SY.!XV.52s -234.77 -73.623 -29.815 836.49 SMK.SMW.IMx -68.284 -240.11 45.914 Eta 2e meetSa let 313 114 tot Mais 3 vets 12.56 2-D SOLID 42 l NC.YCs 16.75 8.250 TEMPS 7e.0 as 67.3 S.I s 1650.4 $1GEs 1573.7 SN.SY.IIY.12s 56.324 -33.230 58.918 1593.4 SME.SMN.IMX* 310.33 -57.414 33.s63 Ets 21 NeeESs get 334 335 33e Mais 3 vet s 12.56 2-5 SOLIS 42 I EC.YCs 16.75 1.750 TEMPS 70.0 Am 32.3 S.3,s 2348.7 SIGEs 2304.7 i SE.SY.TXY.SZs 355.62 -8.1411 49.984 2333.9 SMX.SMM.INXs 362.34 -14.466 384.4e o .ss 22 meeESs i6 2 22 17 M.is i vet s 32.69 2-. Seti. .2 BC.YCs 18.25 -3.750 TEMPS 79.4 as -1.9 S.I.m 2175.9 SIGEs 1939.2 4 l SN.SY.TXY.S2s -434.79 -9.8349 -28.642 -2185.1 SMK.SMN.5MEs -9.1622 -639.44 315.15 i Et a 23 metESs 37 22 23 la MAis I Wets 11.49 2-9 Set 3. 42 ' ^ l BC.YCs 38.25 -1.250 TEMPS 7e.0 as -31.2 S.I.s (456.7 SISEs 1355.2 j SM.SY.lMY 52s -210.95 4.7954 ~44.374 -1443.2 SME.SMN.IMXs 13.544 -219.7f

116.64 1

j sts 24 hetESs IS 23 24 19 Mets 1 Wets 13.69 2-3 Sette 42 NC.YCs 14.25 .750s EEMPs 7e.e as -76.8 S.I s g54.96 SIGE: 359.33 l SK.SY.1XY.SZa 257.94 26.318 -57.377 -687.59 SME.5MM.lMxs 271.37 12.443 329.24 ) sts 25 NeeESs 19 24 25 20 Mats 1 Wels 13.69 2-3 Sg(33 g2 EC.YCs 18.25 .2500 TERPs 79.8 As 43,3 S.I.s $33.32 S I GE ** 601.63 SM.SY.IXY,32s 592.52 -24.439 20.526 9.7793 SMK.SMm.5MXs 593.28 -25.121 349.16 5 L rSu 25 136.SEPs .000 esc.Sts.Es ..eSi,9 En -232.73 ESs -i43.sy Sr.is 1 .t.Sia i 2-. S., 32 1 Eta 26 i j Eta 27 deeESs 111 336 117 112 Mais 3 vets g3.49 2-3 Setta 42 i NC.YCs 38.25 .2540 iEMPs 70.0 Am 2.S 5.I.= 662.73 SIGEs 661.30 4 SN.SY.IXY.SZa -653.25 6.9998 28.784 S.3743 SMX.SMN.lMX: 8.2524 -654.48 331.37 Eta 28 metESs 112 317 118 133 Mais 3 Mets 13.69 2-3 SOLIS 42 U2 1 BC.YCs 18.25 .7500 30MPs 70.. As -9.9 S.I.s 1842.4 SICEs 927.5g ri j SM.SY.1XY.52s -337.20 -43.378 -47.659 497.85 SMX.SMM.lMX -35.534 -344.73 154.45 j# 7 ~ 1 Eta 29 ESs las ti. ist 1:4 Mais i vets i3. 9 2.. S.t3. 42 t NC.YCs 38.25 1.258 WEMrs 70.0 As -75.7 S.I.s 1447.2 SIGEs 1489.2 C) i SX.SY.TxY.52s 124.38 -26.554 -41.220 1450.2 SMK.5MN.lMXs 134.a4 -37.935 85.943 i' s CD Eta 30 MSSESs 114 139 120 315 Mais 1 vers 13.69 2-3 Sgtgg 42 cN 3' i 4 I t

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I Wels 21.56 2-3 Set 13 42 d

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4 I i i c) o PJ 1 F i / Eta 94 MesESs 56 41 62 57 Mets 3 wet s 22.69 2-3 SSLIS 42 XC.YCs 30.25 -8.750 1EMPs 78.0 As -4.0 S.g.s 1353.4 SIGE8 1283.5 1 SX.SY.IXY.SZa -4et.23 -9.7449 -28.319 -1361.1 SMX.SMM.IMXs -7.7474 -451.22 208.74 1 Ets 95 meSES 57 42 43 58 MAis 3 vets 22.69 2-8 SSLIB 42 XC.YCs 34.25 -3.254 IEMPs 7s.O As -9.6 S.I.s 943.72 SIGEs 823.36 SX.SY.1XY.52s -357.58 -5.9418 -68.879 -939.42 SMX.SMN.INXs 4.3828 -367.75 186.e3 l Eta 96 WSSESs 58 63 64 59 Mars 3 wets 22.69 2-D SSLID 42 ] XC.YCs 38.25 .7500 IEMPs 70.e As -11.1 S.I.s 524.52 StGEs 462.39 SX.SY.1XY.Sla -388.66 -3.2229 -62.292 -519.53 5MX.5MN.IMXa S.9f?S -328.87 164.93 Eta 97 hetes 59 64 45 68 Maga 1 vet s 22.69 2-9 SSLIO 42 J XC.YCs 30.25 .2500 TEMPS 7e.e as -6.0 S.I.s 263.e2 SIGE 229.85 } SX.SY.1XY.SZa -257.79 .56724 -27.454 -98.474 SMX.SMM.lKXs 2.3303 -268.69 131.51 i j. Ets 93 mesESs 65 156 NSEPs.Sege52 DSLIDEs.e84346 FNs 8. FSs S. stays 3 SLDSTs 3 .Z-9 EAP 32 Eta 99 meSESs 151 156 357 352 Main l* vet s 22 49 2-D SSL3D 42 XC.YCs 3e.25 .250e TEMPS 70.8 As -85.4 S.I.s 229.20 SIGEs 198.96 l. SX.SY.1XY,SEs 226.84 .63474 -18.356 tes.le SMX.SMM.IMXs 224.36 .84289 314.45 Eta gee meeESs 352 157 158 353 Mais ! Vet s 22.69 2-D SOLIS 42 i XC.VCs 30.25 .7500 TEMPS 7e.8 As -88.9 S.I.s 517.59 ilGEs 448.75 i da SX.SY.TXY Szz 266.58 .62437 -43.946 511.84 SMX.5MN.1MXs 173.59 -6.4541 140.02 8 j 00 Ets teg meDESs 153 ISS 159 154 Maim 1 VDia 22.69 2-0 SSLIS 42 C" XC.YCs 30.25 1.258 IEMPs 7s.e As -82.4 S.I.s 927.77 SIGEs 416.66 l SX.SY.1XY.SZa 305.34 -1.3764 -41.415 920.89 SMX.SMM.IMXs 318.43 -6.8726 358.45 j Ets le2 meeESs 354 359 360 155 Mais 1 USt a 22.69 2-3 Set:3 43 i XC.VCs 59.25 3.75e IEMPs 70.0 as -84.7 S.I.s 3334.0 SIGEs 3198.3 1 ] SX.SY.1XY. SZ s 346.23 .15294 -19.964 1332.7 SMX.5MN.lMXs 347.38 -1.2999 174.34 Eta ISS betESs 63 66 47 62 Mais 3 yets 23.81 2-D Set 3D 42 NC.YCs 31.75 -1.750 TEMPS 78.? As -6.2 S.I.s 1260.8 SIGE8 3142.5 SX.SY.1XV.SZa -294.31 -9.4329 -38.127 -1266.1 SMX.SMM.IMXs -4.8786 -297.67

345.08 St s 3D4 meSES 62 67 63 Mais 8 Ust a 23.81 2-3 $6 TIS 43 XC.YCs 31.75

-1.250 TEMPS 79.8 As -13.6 S g.s 9e3.27 SICEs 788.22 SX.SY.tXV.SZa -334.47 -8.4319 -7s.eOS -897.33 SMK.5MN.IMXs 5.9683 -348.87 177.41 i Eta 105 metESs 63 64 69 64 Main 1 wets 23.81 2-9 58t3D 42 i XC.YCs 31.75 .758e IEMPs 7e.0 As -9.9 S.I.s 535.97 SIGEs 489.48 i SX.SV.IXY.52s -370.79 -1.9274 ~46.629 -526.23 SMX.SMN.1MXs 9.7457 -382.37 194.e4 j j Ets le6 usSESs 64 49 70 SS MAis 3 WSt u 23.51 2-8 SetID 42 XC.VCs 31.7% .2500 TEMPS 7e.e As -4.5 S.I.= 432.77 SIGEs 348.6e u3 i SX.SY.TXV.SZa -434.92 .45230 -32.835 -855.64 SMX.SMN.IMXs 3.3537 -489.42 2e4.39 H ) t3 Eta te7 meSES 7e 16: wSEP=.seee72 uSt3 des eee324 ruz e. FSa e. stats 3 StsSis 3 2-4 SAP 12 j, Ets ses menfss 156 161 162 157 MATS ! VSta 23.8% 2-9 SSLIS 42 $3 XC.YCs 31.75 .250e 1EMPs 70.8 As -86.4 S.I.s 323.25 SIGEs 288.84 oJ EX.SY.1XY.SZa 328.36 .355e3 -28.234 137.58 SMX.SMN.1MXu 321.63 -1.6246 165.63 j) } Ets let meDESs 157 362 163 ISS MAis I WSt a 23.81 2-3 SetIS 42 t MC.YCs 38.75 .7584 IEMPs 78.9 As -83.3 S.I s 516.01 Slots 451.32 s j SX.SY.iXY.SZa 310.27 -2.2137 -37.384 589.45 SMX.SMM.IMXs 314.61 -6.5598 160.59 l 1 ? ij

M o C) i PJ s It s 340 p0DESs 154 16S 164 159 MATS I vets 23.81 (C.YCs 31.75 1.2Se IEMPs 78.8 As -37.3 S.3.s 447.77 5?AEs 779.77 2-3 Setta 42 SX.SY.1XY.52s 304.09 2.3786 -42.63e 484.54 SMX.SMM.2HXs lle.se -3.7252 154.86 it s lit hetes: 159 164 165 16e MAls 3 vets 23.31 (C. YC s 31.75 3.750 TEMPS 78.8 As -36.5 5,3.s 1256.1 SICEs 1838.4 2-D SSLIB 42 SX.SY.fXY.52s 289.68 .81266 -17.475 1254.2 SMX.5MN.EMXs 298.77 -1.9034 146.34 It s 132 meDES 71 72 47 Mais 3 Wels 24.94 (C.YCs 33.25 -1.754 10MPs 78.4 As -11.4 S.I.s 1865.8 SICEs 3090.5 2-3 SOLIS 42 SX.SY.1XY.12s -167.36 -9.7735 -33.851 -1868.9 SMX,$MM.tMXs -3.1384 -173.72 85.307 ft s 333 poeES 47 72 73 64 MATS 3 vets 24.94 (C.YCs 33.25 -1.25e TEMPS 7e.0 As -33.4 S.I.* 661.98 SICEs 754.39 2-9 SetIS 42 SX.SY TXY.SZn -293.63 -6.1259 -72.714 -45e.76 SMX.SMM.tMXs 11.224 -318.97 161.30 It s 334 mong$a 6a 73 74 49 MATS 3 Wel s 24.94 (C. YC s 33.25 .7500 T EMP s 7e.8 As -13.4 S.3.s 544.48 SIGEs 507.45 2-D SetID 42 4X.SY.TX7.S2s ~434.24 -S.6117 -83.176 -540.20 SMX.SMM.lMXs 6.2782 -451.17 228.72 ts 135 metes 69 74 75 70 Mais a vot s 24.94 (C.YCs 33.25 .2588 TEMPS 73.e as -3.3 S.I.= 573.98 SICEs 5e3.33 2-9 SDLIB 42 SX.SY.fXY.52s -372.99 -2.8588 -33.367 -224.63 SMX.SMN.tMX .92713 -574.91 284.99 l Its 316 N00ESs 75 166 USEPs.48e945 WStIDEs .000268. FNs 3. 4 l FSs 8. STAta 3 DLDST 3 2-3 4AF 32 !t s 117 metes: 161 166 367 362 Mats 1 Vet s 24.94 b3 (C,4C s 55.25 .2500 (EMPs 78.0 As -88.e S.I.s 48G.61 SI4Es 154.49 2-9 SetID 42 j $3 SX,1Y.TXY.52s 4e9.74 .9 era 4E-et -14.006 177.83 SMX.SMN.IMXs 414.22 .34751 205.31 -4 I fta IIS N#8Ess 162 I67 364 363 Mais 1 wet s 24.94 I (C.YCs 33.25 .7500 TEMPS 70.0 As -82.4 1.1.s 533.26 SiCEs 456.87 2-9 Set ta 42 SX.SY.1XY.52s 354.21 S.8279 -47.022 515.02 SMX.SMN.fMXs 360.44 f.7543 379.36 fi s att usefss 163 164 169 164 MAfs 1 99l a 24.94 l (C.YCs 33.25 1.25e IEMPs 78.8 As -83.3 S.I.s 454.37 SIGE: 747.13 2-3 SetID 42 SX.SY.tXY.12s 287.44 -2.5813 -34.547 843.52 SMK.SMN.IMXz 291.51 -6.6491 149.08 4 i it s 883 NS9ESs 164 169 178 165 MAis l' vet s

24. 94 (C.YC: 33.25 1.750 TEMPS 70.e As -34.s S.I.s 3:44.1

$1GEs 1342.4 2-3 59119 42 SM.SY.IXY 12s 241.94 .30684 -16.445 1143.0 SMX SMN.iMX* 243.11 -1.8644 322.09 It s 123 mesEsa 71 74 77 72 MAis I Wels 26.06 dC.Yfs

34. 7J-

-1.75e TEMPS 70.8 As -44.3 S.I.s 1894.1 $3GE: 3833.2 2-9. SOLIS 42 j SX,31,1XYg u s -31.655 -9.5288 -41.342 -1863.3 SMX.SMN,lMK: 33.764 -51.944 41.356 ft s 322 N88ESs 72 77 73 73 Maim 1 vets 26.06 i (C.YC s 34.75 -I.23e TEMPS 70.e As -84.4 S.8.s 836.87 SISEs 738.25 2-3 setta 42 . SX.SY.IXY.S2s -268.19 2.2813

S4.CS4

-439.84 SMM.SMM.1MXs 27.786 -293.69 160.74 u) It s 323 meet $s 73 78 73 74 Mais 3 vets 26.06 ,a ] (C.YCs 34.75 .7500 IEMPs 7e.e As -7.6 S.I.s 573.38 SICEs 554.76 2-3 Selig 42 e SX.SY.iXY.52s -497.54 17.907 -70.055 -546.05 SMM.SMM lMXs 27.23p -584.89 267.07 t$ i 3' 1 fts 124 heDE5s 74 79 se 75 MAls 1 Wels 26.06 [3 j (C.YC s 34.75 .2See IEMPs 73.3 As -3.2 S.I.s 754.97 SICEs 641.39 2-9 SOLIS 42 I SX.SY txY 52s -747.93 6.4349 -41.694 -297.12 SMX.SMN,InXs 3.7363 -750.23 379.48 } It s 325 heDE5s 30 171 gSEPs.83es31 g$ttpfs.000193 FNs e. FS: e. STATc 3 OLD$ts 3 2-8 CAP 12 3s" 1 4 ) i 4 i i

l l i CD i C3 kJ s~ ] Pc Ets 126 meDEss 166 371 172 167 Main 1 Vels 26.06 2-D SOLIS 42 4 I XC.YCs 34.75 .2500 IEMPs 78.3 As -34.9 S.I s 439.73 Sgg[a 425.29 SX.SY.1xY SZa 492.3F 5.2545 -26.524 217.87 SMX.5MN.tMXs 493.61 3.817s 244.9e I Ei s 32y peDEss 167 172 173 165 Mais 1 Vets 24.06 2-3 SetIB 42-XC.YCs 14.75 .7588 IEMPs 70.e As -87.4 S.I.s $25.24 5IGEs 47s.92 SX SY.TXY.528 376.75 -25.526 -18.617 503.36 SMX.SMM.IMX* 377.61 -25.847 201.75 Ei s 32s meDEss 168 173 174 169 MAir i Vets 26.e4 2-9 S3 LIB 42 ' I XC.YCs 34.75 1.258 1EMPs 33.3 As -e2.3 S.I.s 827.42 SIGE8 722.80 SX,8Y.1XV.SZE 342.23 -5.1474 -42.524 814.49 SMM.SMN.1MXs 333.g1 -jg.923 159.47 4 Ets 129 meDEss 169 174 175 17e MAis 1 Vets 26.06 2-3 Split 42 XC.YCs 34.75 8.758 TEMPS 33.s As -83.3 S.I.s 1114.2 StGEs le33.3 i i SX.SY.tXY.52s 182.29 .74331 -19.944 1811.3 SMX.SMN.IMXs 184.45 -2.5955 93.671 y. l Eta 12$ NSDES 76 31 82 77 MAfs ! VGLs 27.19 2,9 SDLID 42 ) XC.YCs 36.25 -1.754 10MPs 70.0 As -77.$ S.I.3 1826.4 SIGEs 1942.4 SX.SY.tXV.SZa 166.13 -9.9462 -41.542 -930.54 SMX.SMM.IMXs 175.44 -19.217 97.327 i Ets 333 NSeESs 77 42 83 78 Mais 3 vois 27.19 2 9 SeLID 42 XC YCs 36.25 -1.253 ygMrs 73,3 As -23.9 S.3,s 775.54 SIGEs 644.85 SX.SY.IXY.52s -212.45 -48.682 -94.813 -775.43 SMX.SMM.lMXs .76882E-St -254.09 327.01 j Eta 332 NS9ESs 73 33 34 79 Mais 1 Wels 27.19 2-9 SOLID 42 oo XC.YCs 56.25 7584 IEMPs 70.4 As -30.5 S.I.s 60s.53 SIGEs 585.30 5 00 SK.SY.1XV.528 -683.59 -52.542 -107.12 -641.61 SMX.5MM.1MXz -32.825 -433.35 384.26 e Els 333 meeESs 79 84 45 St Mega 3 yets 27.19 2-3 SOLIS 42 i XC.YCs 36.25 .2500 TEMPS 73.3 As -1.1 S.I s 497.52 SIGEs 1st.83 444.76 1 SX.SY.IXY SZs -914.25 -87.341 -36.759 -341.47 SMX.SMM.IMXs -17.825 -914.55 j SLs 134 metESs SS 176 USEPs.084054 USLIDEs.33g387 pus 8. ESs S. STAls 3 SLDSTs 3 2-D SAP 32 I Ela 135 MSDESs 171 176 177 172 MATS I Wels 27.19 2-D SOLIS 42 3 XC.YCs 36.25 .2500 IEMPs 78.5 As 84.1 S.I.s 569.44 SIGEs 493.47 SX.SY.luY.SZa 539.30 -29.024 19.338 237.35 SMX.SMM.5MXs 539.76 -29.681' 284.72 i .ts >>6 ESs i72 177 17. 173 M.is .s a 27.>9 2-. S. lid 42 i XC.YCs 36.25 .7500 30MPs 30.2 As -88.3 S.I.s SG4.07 SIGEs 474.16 4 SX SY.1XY.12s 474.22 53.198 -65.977 331.16 SMX.SMM.IMXs 434.31 43.Ss4 228.61 l 1 i Eta 337 metes = 173 178 179 174 Mays 1 WGLs 27.39 2-3 SOLIS 42 XC.VCs 36.25 4.254 IEMPs 70.0 As -33.y S.g.a 368.0F SIGEs 477.46 SX Sv.TXY SZa 268.9e 26.142 -39.918 787.62 SMX.SMM.Inna 275.29 19.749 127.77 2-9 SSLIS 42 i Et a I SS meDESs 174 179 ISO 375 M4is g gets 27.39 MC.YCs 36.25 8.750 TEMPS 38.8 As -82.5 5.I.s 1945.3 SIGEs 932 4g l i SK.SV.TXV.S2a 124.09 .32417 -16.624 1843.4 SMX.SMM.IRXs 126.28 -1.4647 44.475 v2 H Eta 339 WSDEss at 86 87 82 MAls 1 V6ts 23.22 2-3 SOLID 42 C3 d MC.YCs 37.5F -3.758 IEMPs 78.8 As 77.6 S.I.s If.7s.S SIGEs 993.33 j, SX.SY.1XY.SZs 37s.33 -18.434 43.652 -941.56 SMX.SMM.IMXs 379.72 -28.058 103.89

o Eta 148 NSDE5s 52 SF G4 83 MAfs I V6t s 21.22 2-9 SSLIB 42 b3 8

XC.YCs 37.5F -1.25e TEMPS 74.0 As 36.2 S.I.s 667.39 SIGEs 644.26 SX.SV.EXV.52s -79.481 -64.619 23.347 -714.54 SMX.SMM.lMXs -47.456 -96.543 24.529 [3 os Els 143 heDEss 43 SS 49 84 Mais 3 vets 21.22 2-D SSLIB 42. XC.YCs 37.57 .7540 IEMPs 38.0 As -14.2 5.I.s 488.32 SIGEs 441.66 i l i

l 1 } l C3 C) >J e-l Pc I I, 1 SM.SY.TKY.SZa -434.39 -123.04 -314.81 -566.58 SME.SMM 1MXs -85.256 -473.58 193.33 .s 142 mesESs 84 49 96 45 Mais 3 Vet s 21.22 2-3 SetIS 42 2.YCs 37.57 .2400 1EMPs 70.0 As -10.0 5.I.* 1132.5 SIGEs 1861.s d 65.SY.tXv.SZs -1270.7 -18.918 -228.39 -517.15 SMX.SMM.INXs 28.450 -1381.3 466.27 .s 343 meeESs 176 181 582 IFF MATS 1 WGt s 21.22 2-9 Sells 42 2.YCs 37.5F .2588 IEMPs 70.0 As -79.7 S.I.s 714.25 StGEs 626.41 l lI.SY.Exv.SZs 784.73 226.34 -222.70 484.16 SME.SMN.INxs 862.67 348.42 357.12 .s les posESs 177 182 183 IFS MATS 1 Wets 21.22 2-3 SSLIS 42 0.YCs 37.5F .7598 IEMPs 70.3 As -86.9 5.1.s 377.08 SIGEs 334.99 LE.SY.1XV.SZs 227.25 110.27 -6.2605 486.93 SMX.SMM.lMXs 227.59 109.93 58.829 ) 4 ts 345 meeESs 178 383 144 379 Mats 1 vet s 23.22 2-D SOLID 42 I .YCs 37.57 1.254 IEMPs 70.8 As 69.9 S.I.s 738.83 SIGEs 652.17 i 5X,SY.1XY.52s 232.64 50.364 7F.384 759.75 SMX.SMM. INKS 261.87 21.729 119.6F to 344 metes

179 184 185 ISS Mals 1 yets 21.22 2-9 SetID 42 S

948.83 SMK.'5Mk ICES j

.YCs 37.57 E.758 IEMPs 70.0 As 75.9 S.I.s IS32.5 INKS 218.!!

-2.5145 110.38 EX.SY.TKY.SZs 295.07 30.529 52.831 1838.0 j PJ to 347 meeES: 86 98 92 87 MATS I vets 9.595 2-D SOLIS 42 j 8 2.YCs

38. 38

-1.754 IEMPs 70.0 Am 53.4 S.I s 978.40 SICfr 433.24 0$ BE.SY.1XY.SZa 34.423 13.635 48.864 -942.27 SNK.SMM.tMhz 68.731 -16.673 42.702 y La 148 mesEss SF 92 93 SS Mars ! VOL s 9.595 2-9 SSt19 42 i 2.VCs

18. 38

-1.258 IEMPs 73,3 Sa 29.8 S g.a 776.5e SISEs 694.88 i EE.SY.1XY.SZa 9.8944 118.24 85.326 -617.46 SME.SMM.gMgs 159.05 -38.984 98.982 i } to 149 mesESm SS 93 94 49 Mats 1 Wets 9.595 2-D SSLID 42 4

.YCs 38.58-

.7580 TEMPS 70.0 As -2.S S.I.s 539.47 SIGEs 467.25 } EE.SY.1xY.SZa -121.97 455.65 -12.273 -383.28 SME.5MN.IMEs 154.19 -122.51 139.35 l to ISS meeESs 49 94 95 90 Mets 3 yets 9.595 2-3 SetID 42

.YCs 38.34

.2500 TEMPS 70.0 As -18.3 S.I.s 3357.S SIGEs 1875.7 4 Ex.SY.1xY.SZs -332.86 -287.20 -669.16 -374.5F SMM.SMM.lMus 333.74 -3353.8 478,yy l to 151 meetSa ISI IS4 187 IS2 MAis I vets 9.595 2-D Setit 42 1 0.FCs 38.38 .2500 10MPs 70.4 As -34.2 S.I.= 489.57 SIGEs 407.83 bM.SY.fMY.SZu -29e.e4 -193.54 -199.01 -4 5.#.9 5 SMK.SMM.IMas -36.996 -446.56 204.74 i 2-3 Setta 42 to 152 WeetSe IS2 187 ISS 383 MATS ! Vet s 9.595 .YCs SS.it .7548 IEMPs 74.0 Am 63.3 S.I.= S68.7e SIGEs 498.95 SE.SY.INY Sf s 148.46 -78.125 166.5e 394.33 SME.SnN.IM*5 232.75 -162.37 197.54 ts 353 meeESs 183 ISS 349 184 MATS 1 Wets f.595 2-3 SetID 42 u) C.YCs 14.38 1.258 IEMPs 70.0 As 67.8 S.I.s Sea.9e SIGCr yet.59 4 + Su.SY.1xv.SZs 286.93 -44.939 127.48 711.93 SNK.5MN.IMX8 268.17 -96.973 182.97 ts a to i34 meeESs ist 189 3,. iS5 Mais 1 vet s .595 2-. S.tl. 42 i

.YCs

34. 3s 3.754 TEMPS 79.8 As St.2 S.I.s 1967.4 SIGEs 934.28 c) j Sm.SY.TxY.SZa 376.33 1.1043 67.134 3454.9 SMX.SMM thda 387.79

-10.555 199.17 da t CD l Le 155 metes 186 191 192 IS7 MATS 1 Wels 22.01 2-8 S9t19 42 i C.vCs 39.19 .2548 IEMPs 78.8 As -23.2 S.I.= 658.40 SIGEs 641.15 @[ l SK.SY.1xv.SZs -723.94 -270.45 -238.66 -204.82 SMM.SMN.39:s -167.99 -826.39 329.20 t. .56 me.Ess it, i92 its it. .Ars i Y.ts 22..i 2.. .ti. 4, C.YC: 39.89 .7500 IEMPs 70.0 As -59.7 S.I.s 558.21 SIGEs 483.42 b i f i

l o CD I >J s~ Pr 7 I 1 SX.SY.TKY.SZa -52.559 -149.77 -121.58 297.45 SMM.Snn.Inxs 18.439 -260.74 13 9'. 6 e i.25.193 194EMP s M.ATs 2-9 SSLIS 42 it s 157 meDESs ISS 149 I vets 22.38 <C.YCs it.it 74.. s -.4.s S..a 764.37 SicEs 669. 5 j SX SY iMY.52s 2e4.45 -77.616 -la.432 485.66 SMM.SnN.tMxs 205.61 -78.776 142.19 i I !L. 354 heefSs 189 1 94 195 19e Mais I vats 22.81 2-D SDLIB 42 (C.YCs 39.19 3.75e TEMPS 7e.e As -89.7 S.I s le75.9 SICEs 934.69 1 SE.SY.5xY.SZs 438.24 -25.533 -2.4139 IPSe.3 Smt.SMN.IMXs 438.25 -25.545 231.98 it s 859 'kSDESs 191 196 397 192 Mels & Vet s 22.64 2-9 SOLIS 42 ~ (C.YC s 43.31 .2500 TEMPS ye.e as -4.6 S.I.s 355.58 SIGE: 333.44 SK.SY.tMY 52s -348.40 49.972 -28.209 2.3368 SME.SMN.IMEs $2.224 -303.33 177.79 l it = 3&e neeESs 392 197 198 393 Mars I vets 22.44 2-e totas 42 (C.YCs 40.33 .7500 1EMPs Fe.e as -34.8 S.I.* 587.74 Stets 515.94 i ,f Sm.SY.txY.p2= -ree.07 -23.5 2 -364.Se 267.44 SMx.SMM. Mrs 77.925 -see se 189.11 i I' Et a 343 MSOESs 193 ISS 199 1 94 Mats l' wets 22.64 2-3 SOLID 42 wo EC.YCs 40.38 3.25e IERPs 73.0 as -52.1 S.3,8 753.67 SICEs 659.57 j C3 SX.SY.1MY.52s 73.244 4.2773 -136.64 651.51 SMX.SMM.thas 179.49 -182.14 140.92 4 j It s 842 metESs 194 199 204 195 MATS 3 vot s 22.64 2-3 Setle 42 6C.YCs 40.33 1.754 WEMPs 7e.e As -82.4 5.I.8 974.44 SIGEs 565.9e SE.SY.1XV.52s 351.73 50.634 -38.828 1824.1 SMK.SMM.5Mxa 354.65 45.7e4 155.47 j it s 363 MSSESs 1 94 288 202 197 Mais 1 C01s 23.27 2-D SetID 42 (C.YCs 41.44 .2544 IEMPs 70.0 As -25.4 S.I.s 155,29 SIGES 143.78 I SX.SY.1XY.52s -92.544 -11.343 -4 9.8 3 e 59.641 SMK.SMM.INXs 12.308 -!!4.21 64.255 it s let meeESs 197 2e2 2e3 198 Mais 1 tels 23.27 2-9 Sette 42 (C.VCs 43.44 .7500 TEMPS 78.e As -44.8 S.I.s 458.e4 SIGEs 397.57 j SN.SY.TNY.52s -46.264 -45.854 -383.43 388.94 SMM.SMN.BMXs 55.72e -147.14 1st.43

t s I65 neaEsa 198 203 294 199 Mets 1 Wets 33.27 2-D SetIt 42 j

(C YCs 41.44 1.254 3EMPs ye.e as -57.3 S.E.s 779.78 SIGEs 682.79 SE.SY.1XV.SZa -12.338 -830.97 -131.44 S63.54 DNK.SMM.IMEs 72.92e -216.22

144.37 it s 364 useESs 199 204 205 200 M458 I Wet s 23.27 2-3 Setts 42 4C.YCs 41.44 4.750 TEMPS 70.0 as -77.3 S.!.s le7e.e Syggs 943.32 Sx SY.iMY.52s 127.38

-196.54 -77.640 854.15 SME.SMM.3 Mas 144.74 -211,98 179.34 i ri s C3 1 i 8 PG 4 8 1 CD v4 i 0 C) w l 0% i 1 i

STD-R-02-016 3.0 THERMAL EVALUATION O\\ A thermal analysis for the HN-215H cask has been conducted for normal transport conditions. The performance of the packaging under normal. conditions of transport is described below. 3.1 Discussion The mechanical features of the packaging have been described in Section 1.2.1. There are no special thermal protection sub-systems or features. A very conservative heat load of 400 watts is used to evaluate cask temperatures. However, a much lower heat load is used to calculate the difference in temperature between the payload centerline and the cask surface. These loads (given on page 3-8) are much more realistic because they are based upon the shielding limits of the cask. The external surface of the packaging is predicted to exhibit maximum temperatures ranging from 176'F to 190*F, depending upon the quantity of internal decay heat assumed. The lower temperature predicticn assumes no internal decay heat load of 400 watts. These maximum temperature predictions assume conditions consistent with the Normal Transport "Heat" requirements, specifically: o Direct sunlight (mid-summer) o Ambient Air at 130'F ( o Still air Solar flux is calculated from insolation values given in N.R.C. Regulatory Guide 7.8. The solar flux is assumed constant so that conservative steady state conditions are analyzed. Further conservatism is incorporated in the analysis by assuming the cask base is an adisbatic boundary (no heat loss). The analysis also shows that the internal decay heat (400 watts) raises inside surface temperatures above the external temperatures by less than 0.3*F. Maximum decay heat loads for the HN-215H cask are given below. These are based on a "worst-case" payload of Cesium 137 solidified in concrete. The other payload isotope of interest, Cobalt 60, is shielding limited to much lower Curie levels and thus is not considered here. The total activity is limited by the shielding capability of each cask, assuming a 10mR/hr dose rate at 6 feet from the cask. The values for the KN-215H cask are given in the table on the following page. l 0024k 3-1

STD-R-02-016 d Decay Specific Cask Total Total Heat Activity Volume,6 Activity Heat

Limit 3

Cask uCi/cm8 cm x10 (Curies) (Watts) (Watts) HN-215H 152 6.15 934 4.5 9.0

Based on a conversion of.0048 Watts / Curie for Cesium 137.

The decay heat limit is roughly twice the calculated decay heat to ensure that loading of the casks is governed by shielding considerations and to give added conservatism to the centerline temperatures calculated below. The temperature at the center of the cask can be calculated if we can conservatively assume that the heat flow is entirely radial. The problem can then be treated as a long circular cylinder with uniformly distributed heat sources (Page 53, Krieth, Principles of Heat Transfer, 3rd Ed.) The maximum temperature is given as: i T =T + 4k Where : i T, = outer surface temp. (*/) I radius of outer surface (f t) r = g i k - Thermal conductivity of cylinder material (BTU /hr.ft.*F) The differences between cask centerline temperature and the temperature at the payload outer surface are calculated below using the decay heat limit where: 5'o $3, 4k Cask Decay Heat AT (*F) Limit o Concrete Asphalt Watts BTU /hr (ft) (K=0.8) (K-0.1) i ft* [] HN-215H 9.0 .32 3.22 46 3.68 4 U 0024k 3-2

i STD-R-02-016 /~') The centerline temperature increase is very small for the solidified concrete (_,/ payload. The asphalt temperatures are significantly higher, but these temperatures are based on an activity level which could not be attained in practice because of the lower self shiciding of the asphalt. These results snow that the thermal environment under normal conditions of transport do not have any significant effect on the casks or their payload. 3.2 Summary of Thermal Properties of Materials Only threi of the cask materials were employed in this analysis. They were obtained from conventional handbooks as follows: Thermal Conductivity Steel 25.0 BTU /hr ft *F Lead 18.6 BTU /hr ft *F Concrete 0.8 BTU /hr ft *F Asphalt 0.1 BTU /hr ft *F Surface Emissivity /Absorbitivity f-Steel 0.8 i 3.3 Technical Specification of Components Not applicable - no special thermal sub-systems. 3.4 Thermal Evaluation for Norual Conditions of Transport The thermal analysis for Normal Transport "Heat" and "Cold" conditions is presented in Section 3.6, Appendix. 3.4.1 Thermal Model As outlined in Section 3.6, the unknown external cask temperature was determined by solving for the temperature at which the heat input to the cask system equaled heat output. Input heat consisted of a solar flux (calculated from Reg. Guide 7.8) plus the internal decay heat. Heat output consisted of the sum of free-convection losses and radiation losses to a prescribed ambient air sink temperature (130'F "Hot", -40'F "Cold"). Heat loss was allowed only over the vertical cylindrical sides and the top. Connective film coefficients were taken from McAdams empirical values for free convection. The analysis to determine cask centerline temperature conservatively (T assumes that only radial conduction takes place (i.e., as infinitely \\s_) long cylinder). The decay heat sources are assumed to be distributed evenly throughout the cask interior. 0024k 3-3

STD-R-02-016 3.4.2 Maximum Temperatures Predicted maximum temperatures are: External Internal Surfaces Surfaces No Internal Heat 185.6*F 185.6*F 400 Watts Internal Heat 190.3*F 190.6'F 3.4.3 Minimum Temperatures Predicted minimum temperatures are: External Internal Surfaces Surfaces No Internal Heat -40'F -40*F 400 Watts Internal Heat -30.7'F -30.8'F 3.4.4 Maximum Internal Pressures Assume the package contains water loaded at 70*F. At maximum temperature (190.87'F), the pressure would increase as shown below: The partiti pressures of water and air at 70'F are: P = 0.36 psi

wh P

= 14.7 .36 - 14.34 psi ac The partial pressures at 191* are: P = 9.54 psi wh P,e = 14.34 (191 + 460)/(70 + 460) = 17.61 psi The internal pressure differential is thus: P = 9.54 + 17.61 - 14.7 - 12.45 psi

Referenect 1967 ASME Steam Tables O

4 0024k 3-4

i STD-R-02-016 3.4.5 Maximum Thermal Stresses In Section 2.6.3, the critical elements of the cask were evaluated for a pressure differential of 0.5 at (7.35 psi). The internal pressure due to maximum temperature therefore increases stresses predicted in Section 2.6.3 by the factor: 12.45/7.35 = 1.69. The loads and margins of safety thus become: Allmiable j Item Stress Load / Stress Margin 1 Secondary Lid Stud 1399 lbs. 32,450 lb. Large Primary Lid Binders 8165 lbs. 45,000 lb. Large Shell 1920 psi 38,000 psi Large Lid 6777 psi 38,000 psi + 4.61 3.4.6 Evaluatien gf Package Performance for Normal Conditions of Transport As the result of the above assessment, it is concluded that under normal conditions of transport: 1. There will be no relcase of radioactive material from the containment vessel; 2. The effectiveness of the packaging will not be substancially reduced; 3. There will be no mixture of gases or vspors in the package which could, through any credible increase in pressure or an explosion, significantly reduce the effectiveness of the package. l 3.5 Hypothetical Thermal Accident Evaluation j i Not applicable for Type "A" packages. 3.6 m ndix A Thermal Analysis - Normal Conditions of Transport Hot and cold ambient condition cases are analyzed with the following assumptions: Hot Direct sunlight Ambient Air 6 130*F Internal heat load, 0 & 400 Watts ba 0024k 3-5

STD-R-02-016 i Shade l Cold .i Ambient Air @ -40*F Internal heat = 0 & 400 Watts Steady state solutions of the above conditions with. maximum heating loads are obtained giving conservative temperature predictions. Simplified cask geometry used in the analysis: 4 f//f / /_ f s o s NN % NN v',- QA -@\\ s. n m s sat y s% Q 0.55,, ~ s -9 met. RATE O oero,- / p g a lEAb f A NN Nx Nx \\ NN I ^ = bIMENSIONS (N) cask momt L@ L@ L@ L@ M215H o.157 6,% 7.oR o.354 0 0024k 3-6

STD-R-02-016 External Convective & Radiative Heat Transfers J Heat is lost to surroundings via convective and radiative heat transfer. No heat transfer through the cask base is considered. Convection hA(T oo} O -T, q ~ = ext ext g For free convection McAdams (W.H. McAdams, Heat Transmission, 3rd El., McGraw-Hill, NY, 1954.) gives: h=0.29(E) for vert. cylinders L =0.27(b) for horiz. plates (upheated) L Thus: q h,A,AT+hgAT=(h,A,+hA)AT = TT AT AT = (.29 ( - ) A, +.27 (-) A ) AT T L L c B Where Lc " *"'* 0' 8 L = outside diameter 3 A, = sL L B T" L A 4 B Radiation q cA, c (T -Ty) K (T,xt" - T,oD = = Where: ~0 G =.1714 x 10 e =.8 A = A,+hT E Evaluating K: ^to A A Cask B c side E K d 8 Model (ft) (ft) (ft ) (ft") (ft ) BTU /HR/'R HN-215H 6.96 7.39 40.11 161.67 201.78 .2769 0024k 3-7

I STD-R-02-016 Solar Heat Load Solar loads are calculated using insulation values given in U.S.N.R.C. Regulatory Guide 7.8. They are: 2 2950 BTU /ft for the top surface 8 1475 BTU /ft for the vertical projected aren of the cylinder These values are total insolation for a 12 hour day. The vertical surface insolation value must be multiplied by the projected vertical area (height & diameter) and both are converted to heat flux, 2 BTU /ft /hr. solar = 2950 AT+ 1475 LL cB 12 12 = 245.83 AT + 122.92 L LcB Steady State Solution Setting total energy flow equal to zero: 9 ~S =0 1n out Payload decay heat is taken as 400 Watts or 1365 BTU /hr. ] Solar load is assumed constant at maximum flux found above. Thus: S 9 + 9 in solar internal 245.83 AT + 122*92 b g + 1365 e Sout " 9 radiation + 9 convection 4-Tj)+.2!T K(T -T A,+.2 T,xg-T, A )(Text" oo = t T ) \\B ] k c Text values for the packages under three load cases are given in the Table on Sheet 3-9. The load cases are: 1. Direct sunlight, ambient air at 130'F, 400 Watt internal heat load. Os 2. Direct sunlight, ambient air at 130'F no internal heat load. 3. No sunlight, ambient air at -40'F, 400 Watt internal heat load. 4 0024k 3-8

l I '" STD-R-02-016 CASK EXTERNAL TEMPERATURES L L A A q C as.t, Load e B s T in K Text Model Case (M) (M) (FT ) (M8) (BTU /HR) (*F) 3 1 17,545 179.9 HN-215H 2 7.39 6.96 161.7 40.1 16,180 .2769x106 176.6 3 1,365 -30 7 4 a ] i f I I 1 t I l l 0024k 39 -v~w= w --- - - - - ,w_ g e __,._,,.. _..,, _ _, _, _, _ _ _ _ _ _

4 STD-R-02-016 (~T Conductive Heat Transfer Evaluation e. v W %e >.?.h.. i lid wall R,gg = RHd + Rwall + pb + wall " ut in 6T = R,gg q t k = 25 BT.*!!'R FT *F R =- 11d U 1 1 w 4 l " ~' (L (* A B t =L (* D /kA A = w(L - 2(LA +.375 +.375))LC Steel R = in w w B g,2 12 t =.375" =.C313 ft R ^ ~" out " w w B C t= .875/12 =.0729 ft Lead in(#o/ 1) = r = L /2 ) R 3 g B (A+ r = (L ~ 12 k = 18.6 BTU /HR FT *F i =L C Values for R,gg and AT given in the following table, wheret AT is calculated byt AT = q R,gg and q = 400(3.41) = 1365 BTU /hr O 0024k 3-10 %F

I STD-R-02-016 TEMPERATURE DIFFERENCE ACROSS CASK WALL t R R l Cask WALL L10 EFF AT Model HR 'F HR 'F HR 'F ('F) STU BTU BTU HN-215H 89.4 435 74 .101 5 9 1 I P a 1 i i i. i 1 4 4 i l 0024k 3 11 L---..-.-_..-,,_....---.....-.--...-,,_..-.-....-.,.--_-._...---.._..~

i STD-R-02-016 I i 4.0 CONTAINMENT This chapter identifies the package containment for the normal conditions of transport.. r 4.1 Containment Boundary i 4 4.1.1 Containment Ves_sel ) i The containment vessel claimed for the HN-215H cask is the inner l shell of the shielded transportation cask as described in Paragraph 1.2.3 and the cask certification drawing. 4.1.2 Containment Penetration A pressure tap is included in the design as described in Section 1.2.7. It is sealed with a 3/4" NPT pipe plug. t A drain line is also included in the design as described in Section i i 1.2.7. It is sealed with a 1/2" NPT pipe plug. ~ ll 1 4.1.3 Seals and Welds i Two neoprene seals are used to seal the cask lids. The first is attached to the primary lid and seals the primary lid cask body interface. The second is also attached to the primary lid and O seals the secondary primary lid interface. They are described in Section 1.2.3, abeve. The integrity of the seals is demonstrated using a soap bubble leak { test done in accordance with operating procedures. { 4.1.4 Closure 8 The closure devices for the primary lid consist of eight 1.25 inch diameter high strength ratchet binders as described in Section 1.2, above and eight 3/4-10 UNC studs and nuts to close the secondary i i lid. 4.2 Requirements For Normal Conditions of Transport f The following is an assessment of the package containment under ^ normal conditions of transport as a result of the.tnalysis j performed in Chapters 2.0 and 3.0, above. In summary, the containment vessel was not affected by these tests. (Refer to Section 2.6, above). l 4.2.1 Release of Radioactive Material i Normal conditions of transport will, have no effect on pressurizing the containment vessel. !O j j 0024k 4-1 i 1 --,_-__,__.,___U

i STD-R-02-016 I i 4.2.3 Coolant Contamination vi This section is not applicable since there are no coolants l involved. 4.2.4 Coolant Loss i Not applicable. l 5 i i 4.3 Containment Requirements For The Hypothetical Accident Conditions Not applicable for Type "A" packages. I I J u 4 l i t 4 1 1 l l h i 1 1 1 i i i i i i 1 1 i 1 0024k 4-2 4 r --ww g- .r+,. --w,--,-.-m,w-,wc-+-,w-i-. .. - e, - -ww_ w. - ._aw-- m e,e w

STD-R-02-016 i e 5.0 _ SHIELDING EVALUATION I 5.1 Discussion and Results The RW-215H cask consists of a lead and steel containment vessel which provides the necessary shielding for the various radioactive materials to be shipped within the package. Tests and analyses performed under Chapters 2.0 and 3.0 above have demonstrated the

1111ty of the containment vessel to maintain its shielding integrity under normal conditions of transport. Prior to each shipment, radiation readings will be taken based on individual j

loadings to ensure compliance with applicable regulations. 1 ( 1 l t l l l () 0024k 5-1

STD-R-02-016

6.0 CRITICALITY EVALUATION

Not applicable for the HN-21!H cask. t d ) l 4 'l l 4 i 0024k 6-1 i v-

1 ) STD-R-02-016 7.0 OPERATING PROCEDURES g V This section describes the procedures to be followed in using a HN-215H i cask. Any maintenance activity, such as inspections, lubrication, gasket i replacement / repair, etc. described in this section is described in more detail in Section 8.2, General Maintenance Program. 7.1 Lifting 7.1.1 The cask shall always be lifted using the four (4) provided lifting lugs only. The lifting lugs are the vertically oriented lugs on the sides of the cask spaced at 90* around the cask circumference. 7.1.2 The primary lid lifting lugs shall only be used to lift the cask lid (primary lid with secondary lid installed) or the primary lid alone. The secondary lid lifting lug shall only be used to lift the secondary lid. 7.2 Removal / Installation of Cask Lids 7.2.1 Removal of the Primary Lid (or Cask Lid) 7.2.1.1 Release each ratchet binder handle from its storage position. 7.2.1.2 Engage the flip block to the sprocket wheel in the direction necessary to loosen the ratchet binder. 7.2.1.3 Loosen the ratchet binder by pulling the handle in the appropriate direction. l 7.2.1.4 Remove the retaining pin from the upper ratchet binder pin and then remove the upper ratchet binder pin. 7.2.1.5 Remove the three (3) primary lid lifting lug covers. 7.2.1.6 Using the three (3) primary lid lifting lugs, suitable rigging and exercising caution in the handling of the primary lid due to possible contamination of the underside of the lid, remove the primary lid. 7.2.2 Removal of Secondary Lid 1 7.2.2.1 Remove the secondary lid holdown stud nuts. 7.2.2.2 Remove the secondary lid lifting lug cover. 1 7.2.2.3 Exercising caution due to the possible contamination i of the underside of the secondary lid, remove the secondary lid. 2 O 0024k 7-1

STD-R-02-016 I 7.2.3 Installation of primary Lid 7.2.3.1 Prior to installation, inspect gasket for the following: a. Gasket fully secured to the cask, b. Gasket not cut, ripped or gouged. c. Gasket is resilient. d. Gasket is free of debris, dirt and/or grease. t 7.2.3.2 Prior to installation, verify that the date of gasket change reflects compliance with the annual change requirements for the cask. 7.2.3.3 Using the three (3) lif ting lugs on the primary lid and auitable rigging, lift and place lid on cask using alignment guides to ensure proper positioning. Take care not to damage gasket. 7.2.3.4 Secure the primary lid to the cask as follows: a. Install the upper ratchet binder pin through the upper ratchet binder connector and the lid closure

lug, b.

Tighten the ratchet binder by engaging the flip block to the sprocket wheel and rotate the ratchet binder. Torque to 100 (2 10) ft-lbs. c. Disengage the flip block. Rotate and secure the handle to its storage position. d. Install the three (3) primary lid lifting covers. 1 7.2.4 Installation of Secondary Lid 7.2.4.1 Prior to installation, inspect gasket for the following: a. Gasket fully secured to the primary lid. b. Gasket not cut, ripped or gouged. l c. Gasket is resilient. d. Gasket if free of debris, dirt and/or grease, 3 l A 1 0024k 7-2 ,v., m, ,m.,.

t STD-R-02-016 i l O 7.2.4.2 Prior to installation, verify that the date of gasket change reflects compliance with the annual change requirements for the cask. 7.2.4.3 Using the one (1) lifting lug on the secondary lid and suitable rigging, lift and place lid into the opening on the primary lid. Use alignment pins,to ensure proper positioning. Take care not to dhmage gasket. 7.2.4.4 Install the secondary lid stud nuts and torque to.100 (+10,-0) ft-lbs. 7.2.4.5 Install the secondary lid lifting lug cover. l 7.3 Cask Loading 7.3.1 Survey empty cask and the vehicle carrying it to determine the y ] loose and fixed contamination levels. Limitations pertaining to j contamination levels shall be defined by regulations imposed on I the user by the applicable governing bodies. 7.3.2 Inspect cask lid fasteners to ensure that all are present and l undamaged, t 7.3.3 Check to ensure that cask lid (primary and secondary) lifting lus covers are with the cask. 7.3.4 Remove primary lid in accordance with Section 7.2.1. 7.3.5 Remove secondary lid in accordance with Section 7.2.2, if required. i 7.3.6 Inspect interior of cask for standing water. t ) NOTE: Water must be removed prior to shipment. l I 7.3.7 Inspect interior of cask for obstructions to loading. 7.3.8 Inspect interior of cask for defects which might affect the cask integrity or shielding afforded by the cask. 7.3.9 If loading drums on drum pallets, proceed as follows: 1 a. Load drums on each pallet. j b. For maximum shielding, position higher dose rate drums in the center of the pallet and toward the front and rear of the trailer. 4 l c. Place slings around or along side drums to prevent pinching or j damage to the slings by the lids or top pallet in the cask. d. Place the loaded pallets in the cask, i I 0024k 7-3

STD-R-02-016 ' h e. For the cask lids removed for the loading process, inspect v cask lid gaskets, install lids and secure as described in respective sections. 7.3.10 If loading preloaded containers, proceed as followst a. Ensure all lids, plugs, caps, etc. are installed on container. b. Place container into the cask. c. Install shims / storing between container and cask as necessary to secure the container in position. d. For the cask lids removed for the loading process, inspect cask lid gaskets, install lids and secure as described in respective sections. 7.3.11 If loading into container inside cask, proceed as followst a. Place empty container in the cask, b. Install shims / shoring between contatner and cask as necessary to secure the container in position. c. Inspect primary cask lid gasket, install and secure primary lid as described in respective section. l d. Load the waste into the container through the secondary lid opening. e. Install the liner lid, plugs, caps, etc. onto the container. f. Inspect secondary lid gasket, install and secure secondary lid j as described in respective section. 7.3.12 Install camper-proof seals on the cask lids. 7.4 Removal / Installation of Cask from Trailer i 7.4.1 Cask Removal Trailer 7.4.1.1 Loosen ratchet binders / turnbuckles as necessary to rencve pins from shackles at the cask and of tiedown system. 7.4.1.2 Remove pins from shackles. 7.4.1.3 Using four (4) cask lifting lugs and suitable rigging, lift cask off trailer. NOTE: Do not use cask lid lifting lugs to lift the cask. ' f 7.4.2 Cask Installation on Trailer I b 7.4.2.1 Using four (4) cask lid lugs and suitable rigging lift cask and place cask in proper position within the shear ring. 0024k 7-4

STD-R-02-016 NOTE: Do not use cask lid lifting lugs to lift the cask. Os 7.4.2.2 Inspect tiedown lugs and shackles on cask and trailer i for cracks and uear which would affect their strength. 7.4.2.3 Inspect tiedown cables to ensure they are not damaged (crimped, frayed, etc.) 7.4.2.4 Inspect tiedown ratchets / turnbuckles to ensure they are in proper working condition. 7.4.2.5 Install a shackle through the cask end of each tiedown cable and attach the shackle to the cask tiedown lug. 7.4.2.6 Tighten ratchet binders / turnbuckles as necessary to secure cask on trailer. 7.5 Containment Penetration Seals 1 If the camper-proof seal on the cask cavity drain line or vent line has been removed, the pipe plug used to seal that line must be removed and properly reinstalled. Installation of the pipe plugs used to seal the esvity drain line and vent line shall be done using a pipe joint sealing compound. Pipe plugs shall be torqued to 20 (22) ft-lbs. Immediately af ter installation of the plug a new camper-proof seal shall be installed. 7.6 Preparation for, Shipment 7.6.1 Perform radiation surveys of cask and vehicle, including a determination of surface contamination, to ensure compliance with 10CFR71.47 and 10CFR71.87 and complete the necessary shipping papers, certifications, and checklists. ] 7.6.2 Placard vehicle and label cask as necessary. 7.7 Receiving a Loaded Cask j The receiver, carrier and shipper are to follow the instructions of 10CFR20,205 when a package is delivered. These instructions include surveying the external surface of the cask for radioactive contamination, i J I 1 O 0024k 7-5 i

STD-R-02-016 fm 8.0 ACCEPTANCE AND MAINTENANCE f 1 V 8.1 Acceptance Tests i Fabrication of the HN-215H cask meets the requirements of Subpart D of 10CFR71. Fabrication is implemented and documented under a Quality Assurance program in accordance with the applicable requirements of 10CFR71, Subpart H. 8.1.1 Visual Inspection The packaging shall be inspected visually for any adverse condition in materials or fabrication using applicable codes, standards, and drawings. Materials are specified under the ASTM code. Weld procedure and welder qualifications are in accordance with ASME Section IX. Prior to painting, non-destructive testing of welds is accomplished as described in the cask drawings. 8.1.2 Structural and Pressure Tests After fabrication is complete. the cask assembly is subjected to a pneumatic pressure test of 8 psig (-0 psig, +1.0 psig). The cask is visually inspected after the pressure test. The acceptance criterion is no change has occurred to the cask as a result of the test. () 8.1.3 teak Tests -3 A leak test of a sensitivity of at least 10 STD cc/see shall be performed using a test fixture (with calibrated pressure gauge and pre-set relief valve) mounted into the cask body drain plug cavity or the lid vent line. Air is introduced at a maximum rate of 0.5 psig/ min until the test pressure of 8 psig (-0 psig, + 1.0 psig) is reached. All joints on the test fixture, primary lid and secondary lid gaskets are bubble tested. The pressure in the isolated cask is also monitored for at least 30 minutes. The acceptance crittria aret No leaks evidenced by the bubble solution. No pressure loss over a 30 minute time frame. The system will be depressurized at a rate not exceeding approximately 2 psig/ min, the test fixture removed and the drain or vent line plus reinstalled. The installation of the plug is to be done in accordance with Section 7.0. O 0024k 8-1

STD-R-02-016 8.1.4 Component Tests 8.1.4.1 Gaskets Prior to painting, seating surfaces are to have a 125 RMS minimum finish. I.eak testing (See Section 8.1.3) of the cask will be final acceptance for gasket design. 8.1.5 Tests for Shielding Integrity Upon completion of the lead shielding pour, a gamma scan is done of the cask wall to verify lead thickness and the lack of any voids or impur. ties in the poured lead. The gamma scan procedure contains acceptance criteria for verification that lead thickness is not less than 1-7/8 inches. All gamma scanning will be conducted on a 2 inch grid system. 8.1.6 Thermal Acceptance Tests No thermal acceptance testing will be performed on the HN-215H cask. 8.2 General Maintenance Program t 8.2.1 Genaq O. Maintenance and repair of the HN-215H cask is controlled by the Westinghouse Radiological Services Division Quality Assurance program. The casks and trailers annually undergo three (3) routine technical inspections. These inspections are proceduralized in cask maintenance and repair procedures. 8.2.2 Gaskets 8.2.2.1 Gask.ats shall be inspected for resiliency and complete adhesion to the appropriate surface during each use of the respective lids. 8.2.2.2 Gaskets in good condition but not adhered to the appropriate surface shall be reattached as follows: a. Gently pull gasket away from its normally secured ) location until it cannot be removed further without damaging the gasket. b. Remove residual adhesive from the appropriate l surface. Clean with solvents which are recommended by the adhesive manufacturer's instructions. O 0024k 8-2

STD-R-02-016 j 1 c. Reapply gasket adhesive to the gasket and appropriate surface and reattach in accordance with the adhesive manufacturer's instructions. 8.2.2.3 Gaskets which cannot be sealed or are obviously damaged must be replaced in their entirety. Damage '[ may include cuts, nicks, chips, indenta,tions, or any i other defect apparent to the naked eye shich'would affect sealing integrity.- Removal of the gasket, preparation of the lid surfaces, adhesive ~use and gasket installation shall be performed per Section 8.2.2.2. 1 8.2.2.4 All gaskets shall be replaced after 12 months of installation on the cask regardless of apparent condition or cask usage. 8.2.2.5 A leak test, according to Section 8.1.3, shall be _ performed at least once within the twelve (12) sonthe 4 prior to any use. 3 j 8.2.2.6 Any painted surface in contact with the gasket shall j be maintained in good condition. Any loose, chipped. J or scratched painted surface which would affect seal integrity shall be repaired prior to further cask use. ) 8.2.3 y, elds 8.2.3.1 All welds have been completely checked'in accordance with ASME Code requirements using visual, magnetic particle and radiographic methods during fabrication. The cask drawing delineates these inspections. In-use j ] inspections should not be required unless the cask has, i been involved in an accident or has been lif ted i improperly or in an overloaded condition. In those t cases, inspection shall include the followingt a. Drop or accident: All accessible cask body and i lug welds and primar*/ lid ratchet binder lug welds j shall be magnetic particle inspected in accordance with ASME Code Section III Division I, Subsection I NB, Article NB-5000 and Section V, Article 7. These inspections may be performed with the painted finish in place. b. Improper or overloaded lift: All welds on the cask primary or secondary lid which were in use at the time of the improper or overload lift shall be magnetic particle inspected per the requirements delineated above. O l 0024k 8-3 i - _ _ _. _ _.-_ -,_. - ~-

STD-R-02-016 8.2.3.2 Whenever welding to the cask is required it shall be b performed utilizing weld procedures and welders qualified in accordance with ASME Code Section IX requirements. 8.2.4 Studs and Nuts 8.2.4.1 All studs and nuts shall be inspected during each removal of the secondary lid and superficially with each cask use. Replacement shall be made if the following conditions are presents a. Deformed or stripped threads. b Cracked or deformed hexs on nuts. c. Elongated or scored grip length area on studs. d. Severe rusting or corrosion pitting. 8.2.4.2 In general, all studs and nuts shall be inspected for damage at least once a year under normal usage conditions and replaced when the conditions delineated in Step 8.2.4.1 are present. 8.2.5 Ratchet Binders 8.2.5.1 The ratchet binders are designed for long term use with minimal maintenance. They are inspected for satisfactory operation and general condition before each use. l 8.2.5.2 Filling of the lubricant reservoir is accomplished very infrequently on an as needed basis using standard j automotive chassis lubricant. A lubricant reservoir i is provided. Dry threads or hard operation will indicate the need for additional lubricant. 8.2.5.3 Any ratchet binder which received impact or suspected overloading in an accident must be completely disassembled and inspected or replaced. Causes for rejection during a damage inspection shall include: l a. Cracks in the jaws or joining bolt. i b. Deformation of the jaws or joining bolt. c. Excessive rust or corrosion pitting in the threads of the jaw or joining bolt, 1

O i

0024k 8-4 k

STD-R-02-016 8.2.6 Painted Surfaces 8.2.6.1 Painted surfaces shall be cleaned using standard commercial equipment, chemical solutions, and procedures. 8.2.6.2 Chipped or scratched surfaces which could affect seal integrity shall be repainted prior to further cask use. Other chipped or scratched surfaces shall be repainted at the time of the next routine technical inspection referenced in Section 8.2.1. 8.2.6.3 Guide stripes and cask ider.tification markings shall be repainted when they are chipped, peeled off, faded or illegible. O h i O 0024k 8-5 L

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6.0 CRITICALITY EVALUATION

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6.0 CRITICALITY EVALUATION

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