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Addendum to Application for Amend of License SNM-1107 Re Revision of Certificate of Compliance 5450,adding Registration as User of Model RCC-4
	ML20126D647
Person / Time
Site:	07105450
Issue date:	04/02/1980
From:	; WESTINGHOUSE ELECTRIC COMPANY, DIV OF CBS CORP.
To:	;
Shared Package
ML20126D645	List: ML20126D643; ML20126D647;
References
	NUDOCS 8005050104
	Download: ML20126D647 (81)
	v • d • e

{{#Wiki_filter:- _ _ _ _ _ i ~ 8005050 d, Addendun to Application for Amendment of License Smi-1107 for NFD Shipping Packages, dated July 13, 1973 ~ ~ 14. RCC-4 Pachacina 14.1 Pachacing Descriction Designation-RCC-4 Shipping Ccntainer Gross Weight-8400 pounds Fabrication - The design and fabrication details for shipping containers in the RCC-4 series are given in Equipment Specifica:ica E-953511 and Westinghouse drawings 1460E92 and 1460E94, which are attached as Appendix L to cur application dated January 1979 on Docket 71-5450. West-inghouse drawing 1460E96 is also included in that Appendix L to indicate the location of, and the method of retaining poison plates in the packaging, -when they are required. Coolents - Not applicable 14.2 Contents Descriction The descriptions and discussions given in Section 4.2 of reference 1 will be directly applicable in all respects if "and Appendix L" is added after " Appendix A" and drawing 1460E96 is substituted for " drawing 684J580." i 14.3 Compliance with Subcart C of 10CFR71 The descriptions and discussions given in Section 4.3 of reference 1 will be directly applicable in all respects if " Equipment Specification E-953511 is cubstituted for " Equipment Specification E-676200." 14.4 Limits and Controls The Fissile Class II Limit, Fissile Class III limit and the Procedural Controla presented in Sections 4.4, 4.5, and 4.6 of reference 1 respectively, will apply directly if " Equipment Specification E-953511" is substituted for " Equipment Specification E-676200." l l = 4 1 l

y l y a' .T.~: pocijMLNT ' NO: CRC-70-1 ATTA,C8 MENT 1.- ~ '-.. j, ' h = \\ ISSUI DATE: 1/13/70 i 1 I q i i { ........t j .'. 'l { ,8 REPORT ON TEST ~ t OF FRESl! FUEL SHIPPING CONTAINER P_/N: 708R001-1 ~ 30 FT. DROP TESTS & ~ PIN DROP ..'~ r '.FOR t BADCOCK L WILCOX COMPANY = PO!fER GENERATION DIVISION - MUCLEAR POh'ER GE!iERATION DEPT. L Y. N C H B U. R G, VIRGINIA ~ ~ TESTS PERFOP!iED BY 6 CONTAINER RESEARCH CORPORATION GLEN RIDDLE, PA. ~ ~ ~ ... REPORT DATE: 13 January" 1970. ~ ' <. TEST DATE: ,6-7 January 1970 [ F:Ot:TATt::sR HUSEARCit CORPORATIO:1 p-.....,,

DOCU:.EliT NO: CRC-70-4 ISSUE DATE: 1/13/70 I. i TABLE OF CONTENTS i -.} + .PAGE SECTION TITLE 1.0 Purpose 1 l 2.0 Summary 1 3.O Conclusions t ,l 4.0 Recommendations 1 5.0 Container Description 2 6.0 Method of Test 2 7.0 Tests s. 3 7.1 Drop ?.1 Bottom Drop - Rotational ~ 3 ?

7. 2 Drop !2 Cover Drop - 30 Angle

, - - -- - 3, 1 7.3 Drop #3 40 in. Pin Drop '4. 1 8.0 Test Results 4 APPENDIX A Test, Diagrams APPEt: DIX D Test Photographs = l s. g..p. r s .e- ! COMTA.I!!ER ICSEAP.Cl! CO!LDODisTION Glen Riddle, PA 19037

ISCUT: D.h.Til : 1/13/70 t l.0' PURPOSC: .I 1.1., The purp'ose of the tests herein is to verify by prototype testing that the design and construction of the FRESH FUEL SHIPPING CONTAINER will retain the contents in a nuclear safe configura-tion through a hypothetical accident co'ndition of a 30 Ft. Free Drop. NUCLEl.R SAFE CONFIGURATION is defined for this purpose as the two fuel assemblics, the boron-steel poison plates, and the steel strongback plates retained in essentially design relationsliic; and all retained within the container shell. 2.0 S U b'J 1A iY : 2.1 All of the' required clements for a nuclear safe configuration were main,tained upon complet' e inspection of the contaa,.ner fo'llow, ing the final drop test. ~ 2.2 The final clearances as well as a record of darrage to the container are listed in Section 8.0 TEST RESULTS..

3. 0' CONCLUSIO;iS:

3.1 Dased on the satisfactory final c5ntainer configuration, both ~ internal and external, it was unanimously concluded by 'all attending witnesses as well as the report writer that the container more than adecuntcly performed its desired functions. Much greater damage was anticipated"than was actually experi-onced and no further. modification of the container 'is required to improve its performance under these extreinely severe test conditions. 4.0 ' RECOFJ.!E:!DATIONS : CONTAI!;CR P.ESEARCII CORPORJ TIO;! Glen Riddle, PA 19037 Dage 1 ie

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( :. - 1 'ISSUC DATE: 1/13/70 4.1. since the tests herein were performed on.a prototype container ) which had previously been qualification tested and documented '- (Referenec: Container Research Corporation Document Mo: CRC, 10 dated 12/10/69), there is every reason to believe that this container design has the structural integrity required to ful-fill its mission. 4.2 It' is hereby recommended that this container P/n 208R001-1 be granted approval for shipment of production fresh fuel cells 5.0 CONTAIMER DESCRIPTION: 5.1 The container description in Section 4.0 of Document io:- CRC-69-lO applies with the exception of Para. 4.2 Physical Data ~ ~~

which is modified below:

~ WEIGHTS: ~ Container & Frame 3940 lbs. '(same) g Fresh Fuell Cells (2) 3300 lbs. (was 3000) 7300 lbs. (was 6940) s 6.0 METHOD OF TEST:

6.1 GENERAL

.Two dummy fuel cells (1680 lbs. ea.), were installed in, the prototype container and the container cover was secured as ready, ' for shipment. 6.1.1 The container was then subjected to the follouing test sequence: a.) Drop il Bottom Drop - 30 Rotational b.) Cover removed for examination of contents ^ c.) Drop #2 Covcr Drop - 30 to horizontal d.) Drop ?3 40 inch Pin Drop (invorted) ~~ c.) Cover removed for examination of contents 1 l CO :TI.l!.L*R RESUARCli CO?2OlG. TION 1 l Glen Riddic, PA 19037 i l paqc 2

,2, It!STRU;17 MTATION :_ t NOT REOUIRED - NOT PROVIDED. I

7.0 TESTS

7.l' DROP Sl BOTTOM Dr.OP-ROTATION?.L: 'The loaded container was placed on the ground on its skids. A cable sling was attached to the lif ting eyes in the stacking b' rackets (one hook in each stacking bracket). The sling was then attached to a quick release mechanism on the cranc.' The container was then lif ted of f the ground in such a mannef that the. ~ to th'e AFT END raised of f the ground first to an ang1c of 30* horizontal (see sketch in appendix A).before the FMD END left the ground. The container was raised.to a height of 30 Ft..from the =- bottom of the skids at the FWD END to the ground. Th'is was ~ determin6d by a 30 Ft. length of string attached to the FWD END skids with a small weight at the end of the string which I just lef t the ground when the correct height was attained. " The. quick release was then actuated and the container fell freely to the gr und in the same attitude in whidh'it was suspended causing the AFT EMD to rotate to the ' ground af ter tlie FWD END struck. See appendix B for photographs of results. 7.1.1 The container was then opened ana exam 2.ned for damage.. See j Section 8 for TEST RESULTS. l l.' 7.2 DROP 42 COVER DROP - 30* ANGLE: The container was placed on its cover with the four skids ~ sticking straight up. The conta'iner was then rolled over 30* ~ toward its side until the sealing flange was at a 30* angle COMTAIUCR RESI;ARCl! CORPORATION 4 Glen Riddle, PA 19037 'vana 3 9 ..emen L

9 uur.:ve.r.vr av: c ac-i u .t ISS ISSUP, DATD: .1/13/70 .'from the horizontal (sce sketch in appendix A.) A sling was s .att$ched to the container and the quich release mechan'. ism on the crane. The container was raised to a height of 30 Ft. from the cover to the ground. The quick release was actuated and the container fell freely to the ground on its, cover. The container was not opened af ter. this test for fear of not being able to 'eplace the cover for,the pin drop test. r 7.3 40 INCH PIN DROP TEST: ~ A steel pin (site 6 in. dia. x 8 in. Ig. with 1/4 in. radius around top circumference) uns placed on. the ground and. the ' container raised above the pin to a height of,40 inches to the T' e container was angled,in such a. manner...as. j:o... ..-.- _. top of the pin. h J present the undamaged side of the' cover to the pin. Upon release, J ? the container cover struck the pin squarely and rolled over on , its side to 'tihe. floor. Ph'otograohs' were taken of the ~ ,' container and pin immediately thereafter. 7.3.1 The cont $iner was then uprighted and the cov- ~"oved for 'exami ation of the container contents. 7.3.2 See Section 8 for RESULTS OF THE TEST SERIES. 8.0 TEST RESULTS: 8.1 Photographs uere taken during the test series and are included in Appendix B. 8.1.1 The'following is a list of'the photographs and an explanation of what they depict: / PHOTO MO. DEPICTIOM .i 1 showing container prior to release during drop 01 CO:.T/sliiCR 1:BSEARCli CORPORATION Gl(:n niddic, PA 19037 e.ae. .o.e s o.

t DOCUMENT !!O: CRC-70-1 ,ISSU.E DATE: 1/13/70 l PilOTO NO. DEPICTION ^ l Botton Drop - 30' notational. NOTE: That the 1 ".~ ;. container angled in relation to crane boom. 2. Immediately after Drop 11. NOTE: The splintered skids (FWD END) i

3.

AFT EMD - this and suffered the rotational impact i s and bottom end, plate distortion'of 1 in. out of vertical plane. Also the pork chop was severely [- distorted. 3. showing cover removed - general view looking FND. The support rod brok'e l'oose from its storage position and.i.s'l.eanin.g against clamp bow. Frame c l and fuel cells essentially intact. 5. General view looking AFT'. .? 6. . Showing FWD END - left side shock mount broken lo,ose from, suspension, frame. Also note container ~ ' shell directly under frame is formed aroun'd skid angle. 7. Showing AFT END - right side shock mount broken loose and locally distorted channel adjacent,to,___,,,,'_,,, shock mount. Also side & top pressure pads loose as a result'of end gate pivot rods slipping out .of sleeve brackets whch f.rame bottome.d otit o'n. skid angic. This caused permanent sch in frame / rails yhich in turn loosened t!op & side' press ~ure t 1 pads. The fuel cell on this side slid AFT 5/8". 2.$['. s CONT /JhT.R ni: SEA!:C!! CO*1 pol % TION Glen Riddic, PA 19037 i

[ L ISSUri DttTE: 1/13/70 p}!OTO MO. DEPICTIOM t 2 8. Showing FMD EMD with 5/8" clearance between end, gate ,and' fuel cell as a result of cell shifting AFT. 9. , Showing local distortion of vertical poison plate caused by longitudinal bend,ing (1/2" out of plane). 10. Showing local distortion of frame alongside broken shear mount at AFT END. 11. ' Showing FMD END - bottom inside container - NOT"- ~ ) skin for::cd over shid angle fiom frame bottoming oEt.,, 12. Showing AFT END,vicw imediately af ter Drop 92

COVER DROP - I!WERTED.

- - 13. -" - - Showing 3/4 view from AFT END. e -- 14. Showing container in upright position after Drop 62. 3 15. ' She' wing staching b::acket depressed and tear in skin. 16.- Showing. container suspended'abovd. pin for Drop 03 40 in. PIM DROP TEST. 17. ,'Same as alG - opposite side." ~ 18. ' Showing Container, on its side idmediat'ely af t'er 40 in. ' PIN DROP. A 6 in, long cut through the skin resulted .from.the, sharp edge of the dummy fuel, cell inside " ~~'" the container striking,the skin directly on the pin. l 19. Showing container opened for e:< amination after ~ 40 in.' PIN DROP. NOTE: the frame is still suspended .by the shock mounts with the c):ception of one moun~t at cach end which broke from Drop El. Close'* indpection reveals all ofLthe 51 amp bows on the I COI TA MCR RESCA!!Cl! CORPORATION Glen Itiddic, PA 19037 D. b b + -s .-..pm-w #

ISSUE DATE: 1/13/70 P110TO MO. DEPICTION 4 i ') [ right side are ben't as a result of impact" from D::op 52

COVER DROP but still retain the fuel cells in a

" NUCLEAR SAFE CONFIGURATION". 20. Showing view looking AFT (right side) '- NOTE: cracks in clamp bows where they contact the pressure pads. I . Full fo ce of the impact from Drop E2 was taken by these members.and although four were loose after, the drop, the remaining fiv on this side were quite adequate to retain the fuel ecll in its relative position to the'other cell. 21. .. Showing view looking AFT - Left Side, MOTE: clamp ~ bows and pressure pads undamaged bilt. pressure pads . at 3 stations were loose from' frame distortion. . 22. Showing close-up view of AFT END NOTE: broken shock mount attachment.to the frame and end gate. pivot s pins out of their sockets. Also note that cicap bow on near side is cracked and loose but clamp. I how next to it is still tight and capable of restraining fuel cell. .l.. _. ~ Showing'FT END with fuel cell and end gate ass'y 23. A reinoved to expos ~e "T" support casting <thi.ch c'ame l through tests undamaged and maintained a "MUCLEAR [ SAFE COMPIGURATION" lateral spa,cing between cells of 2 11/lG". g y CONTAlt!CR RESCARCli CORPORATION Glen Riddle, PA 19037 n n__q n 7 '

DOCUti!:NT NO: CRC-70-4 isSU:-I DATE: 1/13/70 '8.2 ' Measurements of container shell distortion disclosed that t I that basic configuration of the base had been little affected I bhthedroptestsandthe'naximumdistortionresultedfrom. the COVER DROP (Drop #2). 8.2.1 The ends of the cover received the full force of the impact directly on the two stacking brackets which were depressed Actual 'to a greater degree than the cover shell itself. measurement disclosed the cover shell had been unifornly I depressed 3 inches throughout its ler.gth. (See Fig. I) =- ORIGINAL SHELL r ~.. -.C U RVATU RE .e 3m psmessmw l I-ii g y:R 5 1 E N h T H ,._L____ ' ;_s .l .. g gg FIG I 8.2.2 At no time during the tests did the sealing flange hardware cither break or even loosen.. All were checked after each drop. i 8.2.3 The photographs in APPENDIX 3 clcarly show external areas of' local container distortion uhich, considering the drop g heightc, were of minor consideration. CO;; Tali:CR REGEAI:CH CORPORATION Clcn Riddle, PA 19037 ...=n

1 ISSU1;. DATE : 1/33/70 l t .._ APPENDIX A

~ ~ " - -

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ATTACHMEN 2 COMPARISON OF CONTAINER SUBJECTED TO 30-F00T DROP TEST

AND W RCC4 FUEL ASSEMBLY SHIPPING CONTAINERS i

s PARAMETER TESTED W RCC4 Skin Material STL 1010-1020 STL 1010-1020 Skin Thickness (in) .089 .104 Length (in) 197 21 7 Width (in) 44.5 44.5 Height (in) 47.25 47.54 Shell Radius (in) 20.7 20.7 Loadedlleight(lb) 7300 8825 Weight per unit 37 41 length of shell (lb/in) P rcent increase in weight per 10 unit length Percent increase in skin 17 thickness Cover reinforcement STL 1010-1020,.190 material and thickness (in) Container shell closure 1/2-13 T-bolts, 42 1/2-13 T-bolts, 50 hardware-type and number Container': internals suspension Lord shock mount,18 Lord shock mount, 24 system - type and number t

Test results documented in CRC-70-1 (Attachment 1)

s Detemination of minimum distance between pairs of fuel assemblies subsequent to 10CFR71, Appendix B, accident sequence. 1. Purpose To determine the minimum scparation between pairs of fuel assemblies subsequent to the accident sequence outlined in 10CFR71, Appendix B. If the separation is greater than four inches, then the accident sequence will not produce an arrangement that is more reactive than that analyzed under General Criticality Standards. 2. Method Using the test results (Attachment'l) from a similar coistainer which i was subjected to the drop tests. outlined in 100FR71, Appendix B, and design comparision data for the tested container and the proposed RCC4 container (Attachment 2), the minimum distance between pairs of fuel assemblies can be quantified. 3. Assumptions a. Top to top container configuration will be used as structural material in support frame limits spacing of assemblies in bottom-to-top and top-to-bottom configurations (Figure 3-1). b. Each container sustains a 3-inch depression in its lid. c. When subjected to fire, the shock mounts of both containers burn away. ~ d. A zero gravity condition is assumed to allow the container ~ ~ internals and fuel assemblies to get as close as possible. 4. Results Using the information contained in W drawings 1548E5% 1596E22, and 1596E23,together with the information in Attachments 1 and 2, the minimum distance between pairs of fuel assemblies is 15.75 inches. '5. Conclusion Since the calculated separation distance between fuel assembly pairs subsequent to the Appendix B accident sequence is far greater , than that assumed in the General Criticality Standards, the accident sequence does not produce a more reactive fuel assembly arrangement than that which is analyzed. l m.. .,m, .,w.-v,

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~ l 1 I i' A yl \\\\ C$ k :~'=-s~~ - S 3 l'. [h J_l - _0____.l,--------:-, -- - -.O _ s y.,.O -i ^ 1- .3 p, ~ s \\\\ /Y/ O' \\ h 17.953 fuel Fuel \\\\ \\j )j ./ i. + Y'y%o-A , U' L ~ 4,375 7.875 j d _- 1 (k - s. . l t,jy. s,' e .5 gap 15.75 Setween .9 s. h(,, ;. b.h./ 5 .( z'$, p/ a8> P' ~ \\, / .c:t l i { Fuel fuel

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1 1 I l ATTACHMENT 4 l l COMPARIS0N OF RCC3 AND RCC4 ^ \\ l SHIPPING CONTAINER INTERNALS SUPPORT FRAME DESIGNS 1 PARAMETER RCC3 RCC4 i i Overall Length, in 160.96 189.99 [ Material STL 1010-1020 STL 1010-1020 [ i Number of cross members 8 10 l Cross member design REF Drawing Number of clamping frames 7 9 Clamping frame design REF Drawing Weight of loaded internals, lbs 4736 5434 Number of shock mounts 18 24 L6ad per mount, lbs 263 226 Load per unit length of loaded support frame, lb/in 29.4 28.6 1 i %~

ATTACHMENT 5 Calculation to determine effect of compressive loading on container shell. (10CFR71,AppendixA-9)

Purpose:

To ascertain that no deformation of the container shell will occur when loaded per the conditions of 10CFR71, Appendix A-9. Assumptions: 1. 5 times the loaded container weight will be the applied load 2. Load is uniformly distributed 3. Container is in normal position for transport i t W y W = 196 lb/in y l'.- d e i P P f 4 225 in y P a -. ~.. - __________m, s - ~... - - - -. - -.y 4 ,.,,,em7 ,-w,,

Calculations: For a 1 inch section of the shell, the stress is: S = P/A = 196/(1)(.104) 2 S = 1885 lb/in 2 S allowable = 30,000 lb/in

== Conclusion:== The container shell will not deform under the compression criteria specified in 10CFR71, Appendix A-9 \\ e

] 5 ATTACHMENT 6 Calculation in support of 10CFR71.32a (Load Resistance) i

Purpose:

To demonstrate that the container structural materials do not yield when loaded to 5 times the weight of the folly r loaded container. Assumptions: 1. Container treated as simply support beam 2. Uniformly distributed load equal to 5 times the loaded weight is applied to container Calculations: 1. Determine loading: Wcontainer = 8825 lbs W =5w = 44125 lbs Total c bcontainer = 225 in Load /in = 44125 lb/225 in = 196 lb/in W = 196 lb/in d 22.25 /k .104 /\\ /. I

2. Moment M = 1/8 WL 196 ) = 1240312 in lbs = 8 3. I of shell I= - 4 4 , 3.14 (22.354)4 - 3.14 (22.25)4 4 4 4 I = 3624 in 4. Stress in Shell S= ,1240312 (22.354) 3624 2 S = 7650'lb/in 2 S = 30000 lb/in allowable

== Conclusion:== Stress experienced by container under the assumed conditions is far below allowable values.

1 - l ATTACHMEffT 7 Calculation to verify adequacy of clamping frame bolt at 30-foot drop conditions

Purpose:

To verify that clamping frame bolt will not fail under loading sustained in 30-foot drop accident (10CFR71, Appendix B-1) Assumption: The container shell envelope is designed to accommodate shock mount system deflections experienced by accelerations of 69's. For accelerations greater than 6g's, the container internals will contact the container shell and, thus, change the mode of loading on the clamping frame and bolt (ie from tension to l compression). Therefore, 6g loading will be used as the maximum tensile loading on the bolt. A p \\ 1 t i k 4 10320 a 9 11.10 4.25 / .05~

P I Calculation: The side clamping frame and bolt are loaded as shown in the sketch. The equation for the moments about the pivot point is: 6 11 =0 0 10320 (4.25) = F cos 45 (0.5) + F cos 45 (11.10) B B 9 4873 in/lb =.3535 FB + 7.85 FB 595 lb = FB Are.a'of.5 dia bolt is.1416 in Tensile stress in clamping frame bolt is 2 ,) h b 4202 lb/in = n

== Conclusion:== Stress in clamping frame bolt during 30-foot drop is well below allowable limits. I I

ATTACHMEllT 8 RCC4 Shipping Container top and bottom support analyses

Hinge Plates Design Criterion _ Neither the top closure assembly hinge plates not the welds that secure them shall yield in the 6g minus x-direction acceleration. Verification The loading and the shear area on the hinge plates are as shown. b (fh J Corner Assembly }[9553D74,it20 - 1/8 inch weld as Hinge Plate - N b P = 2732 lb D p Corner Assembly Loads and Securing Welds The load P is one eighth of the total 69 inertial load 2 and the shear area in each hinge plate is 0.585 in The shear stress is thus: 2 2 = 4,670 lb/in = 585 n T Each plate is welded in place with four 1.31 in'ch lengths of 1/8 inch filet. Weld stress is 2 = 4(1 ( 25/ E) = 5,900 lb/in t Conclude that neither the top closure assembly hinge plates, nor the welds that secure them, yield in the 69 minus x-direction acceleration.

Top closure hinge pins

Purpose:

To determine the shearing stress in top closure pins Assumptions: 69 loading 6(1720 lb) = 10320 lb P v -t-t Pin A Pin B ShearA=ShearB=h / sheared area of pin = 10320 = 5160 = 5160 (.5)2(2) 2 .39 / 4 2 d (2) 4 2 Shear A = Shear B = 13230.77 lb/in 2 Allowable shear for 1010-1020 carbon steel = 14500.00 lb/in

== Conclusion:== Allowable shear > maximum actual shear l l l

Corner Post Design Criterion The bolts securing the top closure post to the top cross frame base tube shall not yield in a 69 minus x-direction acceleration. Discussion The top closure post, E 9553D74 or 9553D75 items 1 or 2 carries loads shown in the minus 6g acceleration case. Reaction R is imposed on one of the securing bolts. 2 vary for the XLR and 414 loadings per the Loads F) and F2 tabulation. The maximum bolt load R is imposed in the 414 2 case and is 13,136 lb. The required yield stress in the bolt material is 13,136 lb 2

66,900 lb/in a

Y v(0.5in)274 L u Top Closure Post, H 9553074 items 1 or 2 \\ F N d F2 k o R m 2 N e g o e, Y n R; Shear Moment Loading, Shear and h c.ents on Top Closure Post Due to 6g Minus x-Direction Acceleration t F j 2 XLR Top Closure 0 5463 414 Top Closure 2731 2731 .,i - -. _ _..

~ 4 The bolt material is ASTM 354 grade BC which has a 2 minimum tensile yieid of 109.000 lb/in, Conclude that the bolts securing the top closure post to the top cross frame base tube do not yield in a 6g ,minus x-direction ac'celeration. Design Criterion The top closure post shall not yield due to a 6g minus-x-direction acceleration. Verification The former diagram shows that the maximum beam moment reaction. The moment occurs at the logation of the R2 is maximum in the case of 414 shipments having value 30,696 in 1b. The moment of inertia of the section taking credit for the solid sections only is based on 3 the familiar 1/12 bh. The maximum fiber stress is, ,, (30,696 in ib)(0.7 5 in) = 44,077 0.522 in" 2.25' e r o re Post ( N.A. 4 1.53 I = 0.522 in h / j i Top Closure Post Section at Point of Reaction R, f The upright material is ASTM A572 grade 50 which has yield stress exceeding 50K. Conclude that the top closure post will not yield due to loadings imposed.in the 69 minus x-direction acceleration case. 6 r y eu-wwe<-

Jack Screw Buckling Load Design Criterion -The jack screws that secure the fuel top nozzle shall not buckle in the 69 minus x-direction acceleration. Verification The maximum inertial loading is on the jack screws that operate with the z-bars and is 5160 pounds on each screw. The actual and analytical equivalent loadings along with relevant dimensions are shown in the sketch. Buckling will occur at the critifal load, PrP', which Shames gives as 22 = n v El (pCR)n 4Lz 6 4 = (1)2,2 (30x10 )(n*.4056 ) 4(3.42)2 64 (PCR))=8,408 pounds i P = 5160 lb ?, i I L> LP t u 3.42 if l l / / / / /s // /, ///// I l l ,1 e 0.4056 Basic Minor Dia. Analytical Equivalent Loading Actual Loading Actual and Analytical Equivalent Loadina on Jack Screw in 6g Itinus x-dir. Acceleration ~ Conclude that the jack screws will not buckle in the 6g minus x-direction acceleration case.

Jack Screw Thread Strength Design Criterion The jack screw thread shall not yield in a 6g minus x-direction acceleration. Verification Two jackscrews share _the 69 minus x-direction inertial load from each fuel assembly. Each jack ' screw carries a maximum load of 5160 pounds. R.C. Boucher tabulates shear area for threads of a 0.50013UNC 2A bolt in " Strength of Threads", contained in volume 32 of Product Engineering, dated 2 November 27, 1961. The value quoted is 0.7821 in per inch of bolt length. Since one inch of thread engages with the applicable bar the thread stress is 2 2 = 6598 lb/in 8 in) The jack screw material is ASTM 354 grade BC which has 2 minimum tensile yield of 109,000 lb/in. Minimum shear yield 2 is 54,500 lb/in by deduction. Conclude that the jack screw threads will not shear in the 6g minus x-direction acceleration. Stress ( Design Criterion j Stress in the 2-bar shall not exceed material yield in a 6g minus x-direction acceleration. W r-r a ~ - - - - - - n- .-n ,n,.. -~,-wwvg~ r.e, 7,w--..

i Verification Although the.bar is a Z shape it is treated as straight

in this analysis. The loading, shear force distribution and moment distribution are as diagrammed. The center

' hub is assumed to transmit no portion of the bending moment along the beam. If the two side ligaments transmit the entire load they are stressed to o, where 2 o = (19086 in ib)(0.50 in) = 114,516 lb/in 1/12 (1 in)(1 in)J The material yield stress is quoted by note 4 of drawing 9553D72 at 120K to 140K. Conclude that stress in the Z-bar will not exceed material yield in a 69 minus x-direction acceleration. f. Z-Bar Thread Strength Design Criterion ~ The t'hread through Z-bar tapped holes shall no't yield in a 6g minus x-direction acceleration. Verification Two jackscrews share the 69 minus x-direction inertial load from each fuel assembly. Each Z-bar (W_ 9553072) hole is' loaded, therefore, to 5160 pounds. R. C. Boucher tabulates shear area for threads of a 0.50013UNC 2B hole in " Strength of Threads", contained in volume 32 of Product Engineering, dated November 27, 1961. 2 The value quoted is 1.1231 in per inch of threaded hole length. Since the Z-bar threaded hole is one inch long the 2 2 in ) = 4594 lb/in thread stress is 2 2 The material shear yield stress is 60,000 lb/in. Conclude' that the thread through the Z-bar tapped holes will not yield in a 69 minus x-direction acceleration. l l L

o @g}tgm,5229fl Bottom Support Plate Stress Design Criterion Stress in the XL shipping container support frame' bottom support shall not exceed yield due to a Sg x-direction acceleration. Verification Since it is symmetrical, consider only half of the bottom support plate. The plate edges are considered built in as shown in the sketch and the 69 loading is considered equally distributed over the plate surface, at intensity value q. i o a/b = 0.85 2 Bottom Support q = 97.4 lb/in l 16 Plate f / B = i.455 y / / 8 " I 4l9 2 / o = 1.151 / 1 ) [2 = 0.971 4 n / .c / l / // f/ f f // ///// ~ a = 9.75 Analyfgcal Model for Bottom Support plate Stress Calculation Definitions t = plate thickness = 0.75 in o, = bending stress in plate parallel to side a ab = bending stress in plate parallel to side b R_= reaction force normal to the plate surface exerted by the boundary support on the plate edge, lb/in B),8 '! and /2.are functions of a/b given_in the reference. 2 1

At y = 0 and z = b... -B qb2 g 2

-32,000 lb/in, and Max. o,

2 t qb = 1088 lb/in R2" 2 At y = a and z = o , B)qb1 2 Max. b" 2 = -33,300 lb/in, and t R) = 1289 lb/in The maximum stress in the plate is slightly over the commonly accepted yield value. The yield value is actually somewhat higher than 30 as Shames lists the value for annealed 2 1020 at 48,000 lb/in. In addition, the analysis neg'lects the stiffening effect of the gussets, 9553093, items 3, and any yielding in the plate would be local and of the self-relieving variety. Conclude that the bottom support will not yield in the 69 x-direction acceleration. Bottom Support Welds i Desion Criterion The welds and bolts which secure the bottom support must not yield in a 69 x-direction acceleration. Verification, Welds l The weld along the y=o edge is a 3/16" fillet which has a i strength of 1800 lb/ inch of weld. The normal reaction i force along this weld has a maximum value of 1088 lb/in which is well below the 1800 lb/in allowable limit. ~

Conclude that the weld along the side where x=o is clearly of sufficient strength. The weld along the z=o edge (base plate to support plate connection) is a 1/4" fillet weld which has a strength of 2400 lb/in of weld. The normal reaction force along tihis weld has a maximum value of 1289 lb/in which is well below the 2400 lb/in allowable limit. Conclude that the weld along the side where z=o is clearly of sufficient strength. Verification, Bolts The bolts, oriented on vertical axes (z-axes) running through the bottom support, and axle that restrain the half-plate shown previously are sketched below. O 10.5 Support ~ Frame Centerline yg i As.L --- 1289 lb/in Bottom Support .b/+ _[.:yl,A,:=f/ ~ a C y / ra 4 b Y. __ a_ y Axle l \\ Bolts = W 1460E93, item 13 Load and Restraining Bolts on Bottom Support I

The bolts support a total load of 15,561 lb, which is assumed equally shared between the bolts, 7780 lbe The shear stress in each is 2 t=f7 = 54,943 lb/in r The" bolt material is ASTM 354 grade BC which has a minimum 2 tensile yield of 109,000 lb/in. By deduction, the minimum 2 shear yield is 65,400 lb/in, Conclude that the bolts which secure the bottom support will not yield in the 6g x-direction acceleration. t 't i Ref. Roark & Young, Formulas for Stress and Strain, 5th Edition, p. 399 case lla- ~ > -cw ,,~<--r. ,__,,,_.,,_,,m.,

ATTACHMEllT 9 Analysis of RCC4 shipping container tiedown features for verification of conformance to 10CFR71 l

/ The following analysis of the RCC4 tiedown system is conservative as it assumes a package loaded weight of 11200 pounds while the estimated loaded weight of the RCC4 package is expected to be approximately 8800 pounds. l

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l o F., (f)oT: W w.4 2 ALLOWABLE S T R F sst.5 ~ A. Li FTIN G . A T T.AC H H E N T.s M A'f t fG AL ' A ST M A 36 S TETL (Mlld Ff : 36 000 Psi R.cf. NAtwAL. o r STEEL .Y / (MIN) F :w : 58,000 P51 ~coNST. 678 Eb P,5'-lfs' y F-6 cau.): Vsc(rt)= Ps-(ss, ow)= i l. 6* Ps i CA(Ny)= le,on is i T3(o,11.):. L0 i-$ (cdi,).,60(j j,6m) = 6 % O PSI AL L, Slitj.,R STg.ss: ALL. Lu=ARING Stim.Li:Ebr(nIQ:!.Ci%1Q: 1 rOk600):17.4 e?5! b ALL. BEtelNG $TRu$ t E } (6 }l.)T l,5 PE O.J!.):18 01/co):f/1cq?:; M A TL: R I A L.'. W E L D I1 F T A L ALLoWABtt STES 5 ^ !?gse ?! l(Lf H.;i!#.L @ 6Tret orm.Ipnf.r-!.: F t 041t.)= '/1. (l 3/oo) =/> 8 oo N1 A Lt. 5 N t A R 5p rS s = F3Wy = 4 0 R 0110: do OW)= 408o P5.L e g J' t g

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h. @ :'.} l. '.. $ b '.h,' ? * * ? k. L

' 7 j A L L, 5!:. D A R STR F.1.s = F.s(41!.):, L F.I.(al!.) ,6 06,o a)= 21,I,o o Ps i A L L, B U ARIN G 5TRr51 + Fbr(<il.) = ! IPKall-): 1 &(36 co): C4;ooo P5) j M /71~ u.r. 'i t. l. ' \\/J t"L b b's E T A L (~ F s(nit.)= b,6oo P5 !(l's NA!N.41 aF STt FL toNsT.P"ia.j'5-RAT r a I A L ', "A N" B DLT s : FN,: 03 000 PSI Fh,J l 2 f,0(h> PS j / p -{ (6,li.) x.7 S F tu : 93f79 ps! 2. Ffy ALL. M E/.R STIU;5.5' Fs(c.!i.)=>!Fi(c.JI.).@VM: 9,2% l La J T 9-TF7 o ?

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E..__P....,_ R. 6..__.1.9.....,

a Ft (ALL.) e i 2 (13,600) = 6E00 PSI i ._A_LL.5fIEAR STRESS: F (_A_u.)sf>..F.t..(A.u._.)__ 6. 6.. s ~ 4 0 80 Psi '. l _ SUPER SE D E S grcTJOR St P F A L L_owABLE...STRE.SS ri$_._ ..__.._..._..____....ii l l ..... 3 - 8 A... _ 4

. Qujoi O m , w ;.. -9 ALL AREAS EXCLUDING LlFTING ATTACHMENTS s. M ATERI AL ~, A.I. S l._ h.1 0 7 0...1 0 4 0 S r EE L. SVERA'GE_.PjAN.S.lC.AL PROPERTlES. EXPE.CTED' ~ (M.its Fty.= 30,000 PSO MS1 No.1010 c (tntN) Ft u ? 48,000 Psij F t (ALL.) = Ft y =*. 3 0,00.0.P5l.<. 75(Ftu) = 3G,000 PS\\ H.L. SHEAR STRES s.=.Fs(nu..)M, G Ft (ALL') =. 6 G3o,eo)< '0,600 PS I LL. BEAPJNG STRESS = Pbn(Au.)= 1.5 Ft (Au..') = 1.6(3c,00o): 4s,000Fst /TERIAL: WELD hETk(. u ...EdALL ) f l3 600 PS) (REE MANUAL OF STEEL C'oNST. 3 6

ED., P5 -1 > )

lE ABoyE ALLOWABLE STR ES SES EXCEED THE' CTUAL STRE.SSES ' )N ALL CONDITION S.

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2 l$,,.= 0 (70r.v7s/(2) &rh 2 Pd n el -- h/y (c irl) + 2 /?vg.(2d 1 c/) i- + 2 W 7 (<<'+ 2 e t f =0 2 %g.\\ 6 7 ~ 22,4 00 < / 3 '7 +.2 Tva n207+ + 2 't?v-. n 2 92.- 0 548 Re v Sc7+ ??vi = 3,0GO, 6'00 a ~~ ~ ~ ~ - 2 T(y3 e '/?v, t Sv7 '~ =- 1: 'j?y,, 'v-5 254. 8 - O. 93 8 3 7?v, 27y.l D. 968 3 /Eva f Ts 4 5259.8 ' //, 2 00 l l.OGI?idi,1Pv,

==59 HEP l .) ~ b l -

c ur: qo.y __ w nn. a .. ~ x e ~ ..h $/i l ~j a no Es..... pv s ta g i I, 06 / 7 2h t 0,5MH % = ' 5~8M 2 3'780-L Bs (=X%). 'R v, = 0 l?v, 3980* )3 q. = p b p (,' 1*.* o k.y.., / '7(23. t-Os 1 a CUS=C K.' 'Ev,, /9 3 / '? =- Rys 3WO

== L5 i'760 = ~ R'v,. 1706 =

2 - //200-

.k 2 = 1 l [p?A t. 22400 O. !1

l 9

. $.8 i.

l -- A= / '~ ~, { T,. )

I *.

% s

l. I. Ve,{o*

om y i I ~ to Oh -..,s. m .. o sam % 6 A ~ei M \\ S gh _../ k' a tb --- i ( s 4 'h \\1 O

g. q 5m n

= a 2 > 4 1,' s g . G <o p'. ,9 e CA G W Ne _~- i _., s

-@ r r

v [ <? A i ea ,9 c [ a y p x l i l J-, g g j 4 y l my i n ew.v )$ lI d. e 10. g c:e .P b .4 c. 1 % D Q d f' s' M W>t N* y u. J t-F y ci n ' ;,- .qj.i y,. <-_5 i m c3 y-- .t. y

e m

e c) q ,o. D . _,._i l I y 4 (o g se ~) m ~ h, N u B i, t g.. w t-d 3

3 y

t .5 o >u I p la + -- 9 sq. -e - y-. ~_ h g g ~ N N 9 _] o L% y \\ f W

~ *~

gj o .n e U .9 t >t co p q. r 'f + 4 a 1. g f_A a 4 3 v. s; gm r ii s. 41 9 ss i m.a. y U j Y N h s,: C a e hj. x. = .o c,. .t. ai s-et U I~ .- f-

i. q k-g I-a 4

O, C4 ~ ~q. 5'. ? _ -u a. k w ;; / .. ~. _ _.,, _ -.... _.

-QQ) on to3h eav.A .v/7 - 56,000 L1is ..'.%.ooa - 54 000.& as . % - h i. % =. l l./.K3 0 Las T. 4 f_ _. __ . ~ _. _ c/ N I i 1 j3-l N x / / / ( Wr _ _..y ' m. h I l ST troR ) \\ _c w m =20 L / j=lA<. s %~. -/ g. RTven G.' b i ...y S y cy ( . -...,,,f 7.s r .~ lI

18. 5

.~ ~ n-=: -- z. l

I7 or-(f o~) a hv. s ] THE 7t?Aus $1?sm C o pt P o y s u r I V T '.. A T P L i s.c O' 722A C7 / O//S ON 7//.5 7/.E 3c27,4 . SDo/iv7 9 '//?5. /ND/V/.D.'/A-t 721_=AC7/DNS 2-1 ki ANb / .A1? 2 COH$/N27) /N 77/E 7~b)?c.ss k am M ib CHIiv'GN - /At 7sts PWrNE

l/ E 2 E t c A L

'7]ec.?.;ig T Vr.:e TNi= CG. 2EAc rto tv ?=ni? c s t A t 7 /->. 2 h-ri,or /J 7?sr. l%hEMr FGM T/0^t.' G l1'g. ~ 0 Oktb PointT C) m S ve h >c 2$.5 -I-' V Tito y x l h W T k 2 0 = 0 G) T '- WT + ST tion

== 0 l .[. QS 2 1-pa = 0,' 6.) .G vn. =:. 0,' - 2,yr f T V E 'e. =0 T G h b R,,, Hir ( 2 o. J __ / g),,.,9 7 .2s.s-l /1 vag' ~1 cc, opp y6 .= 7 .20,s //3 9 0 Las Ts Tf vse e- = ~x i... k.. 1 e / e d e

m ma. m .g a. m.. .a eeu'4. .A -+ 4 mi.._a _h.-- 4 m, a as-A. Q a ) w t z) ...x Tev. A - N ~ ...... _f*/._D h / $. _ O b /__ 7 / 2 N/b/B !..Ci Yl2'DO!Yh/ To/ft/T$ TEAC* C va rai ru.riou is muwa nv r 70- w 2Ar/o r l'OR C (3S.27?y, 2'S V WTC, -70 k/y [ JA /15 Off 3 loc Ni/pb/s}, l-pi?i 2 0ts TA /.,' i 2 x Traov. = 72 tiore VIy = nl X 3C; COO = 0,'6h + L 753 '~~ =

2 D

Tu. //ne Tt/02 ^" \\fi 2.f,7e 80 v o '? . (.- 809 18J E6#99 i o )?Tc,llc.? Sy.sio,y(q) l8,000 l-BS =- = '2T'O x Tm., 76 e ;;c., = = Wy .2>*lYO0 5'Cos, Q m.'-p &y = 229'or Unrnc/\\ t.'w s'l x T'i dm Trz. v.e2 = V;/y

0. I '7 2 9-x l13.9 9 =-

I H3. 6 L 133 = l ~ ~ -.... -.,._--__-._.:.-_.3:90:.- i

qu; vi-g-tav. A u f."-xTlrvma )?.7 4,,;2a =-

=

/, 0,33 75 k ll390 ?> 8 44 as = = T7_c vgn 1&r + vm:. =___3,.6._4. f L8S_ = c o/~ y g viii;' = x y vc:a. WV 0,/525 x ll3 9 0 l73'7 L 8)_ = '~ e e t e e /\\ t G S S e e II - ti i ? M 3-21

~. -., ~., -... a ~~ ~ ' ~ ~ \\ g 7: ~~" i n'Q

n. s

~ 'N. g

S a

,g aV w

f- .u, _W Cd Q D 4-p W e

py-7 to

[, II 'g 4 i, s. t a e a d .e g i r, ) P.~.,__ c3 .i=;=3 ? I-c-.---.---{j 4

g. % 9 D

{.A 7 ( b l' CC CC. g J-

(v?

= l. { t 4 4'. r i t a y 'l -J [l g N> f.:.o s g C$ o } g,n) g to. o ( 0"g S.'N k -d: 5 3 D I D 5 I D ~ D b li o y a t p i k .a y y D a us E O E 4 h ~ u b k S 4 o qu m a f,cf N.cdNod i t s ef t, ' h-s g .h T ,lf ~ l,

C5-

^ sa y[. Th

l

. y[Y It w v ..e o e s,p o 'k E $ $' I 4! it u o as 3 t i / W J .J. a o 5 g [ NN$ .l tu o s s y ' ' ~ - l g\\~- 4 ta s f~ n no m C4 ]

4. y 4

__ }...... .si q -G-I 1 l o o$si 8 6 ,U o o V o ns n u g I!! F 4% n g ~ m s i e w tl h ll II 2 $$Vi d i r,,, r Ge 4 > 4 Ue g (" i: i-ji L-o N d u u I a .J J .J r N< "+ ----- \\ 'I ] N NNN i, b. -g - -- Od u> n .i y u l b ll O' b Il I m" it ts io G o' e d e e .a a o n.i o e 't (. 3 g ( u Q C N J __._ - P-m~ l.rj%.a ' t :... ~ - et t te l = o e p 2 e y ) ? nt w

Q'OF Q uss 2t a uo/a 'A s ifoe

T L g u og.,

2c. i //o/z i =

L,

'R a vcn Rt.s vei = % ue T e i. v.m T u s H0.2 .= T L 9-l-hR L '? yo 12, = f g,g y g St 7 vest.

= S 8 vn=

S. 2 v'c tt ~ = t L 4 v.1it 12.st kid 'ileAc770/v A P,P.L/ E f3 Oy do7W = sir e OF FcR WA R D 12 N D. /1onaw r EQuATtou 2 /1,, u =: O (Poivrs

ff'L)

I ll 2 R u 3 vse x of f. lf ' k [HHi) ~ h (eal+M/) +- +2 hs-wm 2 e +,e') + 2 % mz (ol+ 2e 1 {}

== 0 ' i + 2 7 i. a vc e + 2 R l Va n. + Q) .2 ti?i?T .- O i t 2 7?tN va:t =0 + 2 Ti. g m t - l'!i. 4 2 T. 2 noz -l 2 ??ti noe i-

E tion.

0 t i l + 2 k usa. + 2 % we.: 0 -= l / VII14. ' ' i L 3 V:?YL g.g.:f

l CD L non

??. s rion = % nm ~ kick ~ i D %s-va.2'.- % va:- (Gnva new Dam'r To SG) LD % t'a 2. % na > ~ u e \\

i n.)o;=609 . s. / j 7 s v. 4 h I//$) L l lje. ~* L 3 j/:.'t.) t.S if.:n L ? No.2 .~ = - //2 ovo l 4, Q C] LM g = @ h, 7 ~ ve 4 T:.a vmc + 2.'Rt3vra e,fg t2havee. h = kg. % nciz (+t 2 xlh t.2&;g ) = '2u. Vsu E015 h.sve:z '= @i '7 (iD t^!@ l ~ 2 't?u 2. int at G ? t / / 2. 0 0) N G. O. 5 [ ? 5 ' L 3 v.c; k 2 73 # =O ( AQ9. 3 Pcu2vir;? 612, 0.)p

== 2sm_= W,. u n n 830.60 B.S . _ = .T 492/.3 4 Rr = 33 T/.,nda: B30 f >< f77 = 424 9 e.sr ~?, Tu acit 830.6

== 155 3 ?S, / i8s = 7f 2'3..

23., O F 106: 2 C~ M /* Ti 2 D O Wit F u ?c.e.s. su///pr.?Y ps 7//E, 7'O//75 2 (4 Jupi= Eft OBV/st/ sly T//.e ff0JT JTEA/N l','.'i?N 702 hlCLN BR/rt /Ob/ / ~ COMPOM.v!O Wz,. \\ b A W.D 'W Ai?2 b/7? 2c 7ED T Al Jilot/h!, Topg L OA b ~ TEN Y/0// I'Q1N 13 S ~ g p, (o/tro.V JJ A/ /" 75 & A k/J I ' \\/5.Q T/C AL (.0:!Ci7tt:.._BiWS%$:.3.: 3 Wi 9.2 A f /4 00o / 2 hh. I931. '7 \\lt.... I36.3.S-9 G54. 4- _ /4 G00 3,654.4 2 i . 43/8.7 = .....,,, _., _ =. -(.. t i I g h!. 830.6 l'?000 t / 4 ?!v ' 5 76 0.

i

/8,. 84... 0.. l!./-- .3..S...f.p. .-...t ,y [ , @f 54,G '/f,90b /8,000

. co Nome.V

., ! -..mm,, 1 e ,I. f.;. lI $)

f -2.'.T

.....---...,....j.,, ~~ s . Q4. O F-lC'~ i s. V T G V. A l 'T/h..T..). O Whj STRESS b s ~ m n I.....f.,... e, ig g g p_.s s n F I n D..'sy5..N N ).1 f4.y g _...bh5.h.XJJ m. N q y J s \\

b)\\,

o O S lO g g l 5

a%c W 4T W V

s ~ 1 u l l} II.h 1 Of,, O<t &s T ~; \\ O [, ' fy l i n I a u J j gA yi / ~ e+ \\/ 1

..__,e.'_.

1 g a s '1: O h. e1 l G O 4 3 g g m .yq, t9 / -n s J- / .W. -. 2 s en 8 m ss. M o 3 ,l IL l o .L L t-y,.

3.

s u

t-j (il y a l- <s m <W, x. J h i 1 k 1 \\ ~ s -,.4*- me (- j. l t ,., i

Qs o,v g) '~ ~ u,.,, ~ N 7 EM'- OV T OF TIE 30l./W F!bl.E 1_ i [Ol'l BifD=b 7~O!LC = OF TG, AND h& APP H?D HN?>EiR. ' AS* (> Rec ri ou or= v.s 'co mV). - 9t+g, C os 4 b '* $L43 I h. .2<

g. 'a m

{\\ ~ Kqc-Da07 Yg\\- C A ;Uk, 4 3,g s~

Dxistz U!Gr.it.%g Q

/42,000 a ~ L 45 m 0,'70'? ~ /$ A02. /-85 / am :l.s ', = &v rp v iwi,g ,g/w g rod 45 / D 42.?, LBs. 5 9 'la, lu.; 5 =

o.,,9,,

%s' 'i.' u.w %g = 25 780les, ~ t n .Sll;.% e kmdA (C00uaL= {II.5m) r A=2n b, 'i b ; 3.5== 5.25

2. -

a k w. 3-27

~

26 0_1 fl0 x s.... Te r=v. A r-f/f;2Al? [72??SS lhi P M T.6 924s 26'700' 49/O ' PJi -=

== Es_- A 525 < $ g e o v,== 2/G007Mi 7.313A 7?i,vG ST/ MSS /N M)LE Hoo.T 2.HC(.f t ??2D 9~D92 2 G 00 0 L M AM22^6tG 7/200 T . 4 0.4'd

N 7 70W

-hM WO MVS L.OA D 1 4 1 23Eii!?i.i.lG Ai?pA- /N TH.E /~/0L Al-2 lo it A= I.38>: 0. 0 5 " /. 0 3 5 i Y - ~ 3 1 l d -- /2fy .2-5. '/80 = .= /' g35- 'l f (l p_ k,_ ~ v / l h(*. l .....'...y...-.. (a. -- (,., -- nn i \\ } [g t.O g/ ' i.' f .t. '5 y a '5- ? S

29on f,,,-

ncv, I-L.A~f PLA7~E 75Eh/ DING e'\\ q f %-

s\\. %. EDGE 5 Fl.s.l:p / . / ' Yb ,,tv,,, oc { 's i pq j.: x /W[ {. l \\ l i l . ]/ y&s5 i 4 y -; '1 h 3 ~ s k. tv f _. 4 ;_ ~, i f.' l~ [ / I s 'N y l il Rr h> " O 5 3"[ O' = 3.5

r* - -

j %.- $ 430 L DS N -.a L_. g - J _2 01

... ~... _.. - QB)N Q3 ._.s N p v, (, Ccwotito^o cop!PA/MBLE w / T H. C 4 Sti A'O. 35 C ll\\! 'll i:F", Td).L.!?lt', FOR l i (A L /\\1 Pto R .J'/?EJJ AND / ,Si[?/?!id ' }A (ip 2 2. b 4 i!i EDIT 7 0K/ s' ~ S0l(hl7[? Sll) .?, (OC/ D (fAli ?'o;?/1 LcA D O Vi? % S/(A L.L CC/V(Eh!7{2( C C. )Elt: 1.A/t h I!i=A 0F 'l?!EDIM S fo j STt2i.=s 5 (' A T~ cIE^'TBQ

3 W' c"i dc92 n, ni t/

S s =- 2 'il im t 2 (i C y/ v-Rr N '9450 LDS bc i 7:20 ria. O.= To!cJo.v. b TM m = d-

3,7 mt

0,2'7 D, 75 f = THtC kivi=SS of PLA 7:n .=- a== 3,5 "' V = 0,s o b'l' (O!ll/bE*!?tiI?iE't) b;,%,}'(. i.y/; c. Lo & {ytj~///1 = fo e ~ 7 c 6 1s 't >: 9 450 ( 3,,7.t l 3 '... e ci'. 2 rc 3.4 (0, '75)'- 4 2 x 0 a, e r 2/Lh'7,0 4,7 x I,252 l= S;':__I2 '75 'i. 1Mi < Ss u. o, i = M,000 7'SI i (.. 3

{.. -

Qb,. Ol* l*:'L}- .g x rinsi. s WEL.D ST~2Esj!.g.s 3u.G TO T/_Q _.bp WN FC2C Q ( L CNG / 7 i' D/HA,t-TIFJHL /Ab/ T

S t--.

~ Fo (L lll'*lPl-lT*Il?.D (A L C lf Gh'l) hi ' >/ 2 ANA L.)' / G 3)Wiill D.YY \\l1>t.D A T? v A b '{ ~o ?< L l. ( 1I W I?.t. C ( O.t1 P O bl G N 'iT .T o "T'i"~t"T"f ~l ~f'7 '**T. I r t b,< g l 5 9 = 4.5 Rt. ~ /4,OCDLM Y af,,,,,, W[l< b 4, r-9 'PJMc7/0N / S., ct +b l$o 009

== '== g :=- t y1-9.5~ .(. Ti =- ' S, 33 3 L eT.S (11M. FORc &) p HIE T) A T&TA .A = -?.-- x 0 3, 3 75 lN L 2 b bbS S l SllEAi! J*tRE~JS S,

== = ik. 3 3 '7 7. ' ' Ss = - .2 % G 5 PS/ < S,i.x,'=13GooTs/ i (? ') O's io ( s

2o) or f o,3 .. s ~ 'Jov A ~ N U!AWi V'jERM 'i?EJttLMNf 7E T (. ly*. p . ~

b=

8 3 I f_ I ~ N I., e t . <p'r _v_3. <p, (0.. 4.5 I r. .__v. - 4 a = ~- ?! = /8.300 LBS T t 1?OAcrt0.v 6 h. g,5-9 o /sa ,L7 /c,2 s O C

== m - a. t.h 4.s-1 G.s u. 'ib,.==. /2, C00 lM (/fAc) AR:vA A ~2xcc x 095 "'2x4.5 <r O. 3 75== A = 3, 3 75 in - Stim ? Si 2i=$,' 'llA /2 600 . s== =.. . i i.- 4-3.375 1 ' S = 3 '223 TSI < Jn u.x.i = 13 GOD TC/ n"' S-a e %e 4 O

->s - k h D E h, \\ e 'ac e. i, ~ _h.(~. .. '/ V % = 8 1 6 '#- z 7.3 S, 7.< @JME ~ s Wi=LD A1?EA. I y yj A- =: 2,k O. 3 'i s n 1, 5 3 A= 't. I 2 5~ i n '. \\ l p v Rv 9 SHEA R. STIO2S S' 0#t = g A /,12:,.. 95/5 ' Psi < .s = p-f fi.% 3 < s,, w.,,, = / 3 6 o o 'P u 5 ij f: 9 L e Mass t 3-33 ...}}

ML20126D647

Text

6.1 GENERAL

7.0 TESTS

Purpose:

Purpose:

Purpose:

Purpose:

66,900 lb/in a

-32,000 lb/in, and Max. o,

3,7 mt

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