Text

Public QSA Global, Inc., Safety Analysis Report, Revision 14
	ML23125A153
Person / Time
Site:	07109187
Issue date:	04/01/2023
From:	; QSA Global
To:	; Office of Nuclear Material Safety and Safeguards
References
	Download: ML23125A153 (1)
	v • d • e

Safety Analysis Report QSAGLOBAL Model 865 Type B(U) - 96 Transport Package April 2023 Revision 14

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Pagei Contents SECTION 1 - GENERAL INFORMATION ................................................................................................. 1-1

1.1 INTRODUCTION

.. . .. ....*..... ... .*..* *..** .**. .** **. **...*..**.*. .*.. ...**.. ...*........... .. .. . .. **..* ...*. .**. .**. .. ....*****. ***..*..** 1-1 1.2 PACKAGE DESCRIPTION .............. ....... ........................ ... .... ........... ................. .. ...... ............... ...... . 1-1 1.2.1 Packaging ... ........... .............................. .. .............. ... ... ........................ ... ............ ........ ............ 1-2 1.2.2 Contents .. ... .... ... .......... ........................ ... ........................................ ... .. .......... .................. .. .. . 1-5 1.2.3 Special Requirements for Plutonium ........ ................. ..................... ...................................... 1-5 1.2.4 Operational Features.............................. ................... ............ ............................................... 1-5 1.3 APPENDIX .... ..... ... . ... .. ...... .. ..... ................. ........... .................. ......... .............. ......... ...................... 1-5 SECTION 2 - STRUCTURAL EVALUATION ............................................................................................ 2-1 2 .1 DESCRIPTION OF STRUCTURAL D ESIGN ... ........... ........ .... .. .......... .. ....................... .. ....................... 2-1 2.1. 1 Discussion ................ .... ... .............................................................................................. .. ..... 2-1

2. 1. 2 Design Criteria ....... ........................... ... ...... ....................... .................... ................................ 2-1 2.1 .3 Weight and Centers ofGravity .... .. ..... ................... .... ........................................................... 2-1

2. 1. 4 Identification of Codes and Standards for Package Design ...... .. ......................................... 2-1 2.2 MATERIALS .. ..... .. ... ... .. . . .......... ............................. .. . ... ........ .. ... ... .... ... .. .............. .. .. .. .................... 2-2

2. 2. 1 Material Properties and Specifications ..................................................... .. ....................... ... 2-2 2.2.2 Chemical, Galvanic or Other Reactions ............................................................ .................. . 2-3 2.2.3 Effects of Radiation on Materials................................................ .. ........... .......... .. ................. 2-3 2.3 FABRICATION AND EXAMINATI ON . ... ...... ....... .......................... ....................... ... .. ........ ...... . .... ..... .. . 2-3 2.3.1 Fabrication ......... ... ................................................. ............................................................... 2-3 2.3.2 Examination ............. ............... ... ...................................... ................... ................. ..... .. ......... . 2-4 2.4 GENERAL REQUIREMENTS FOR A LL PACKAGES .............. ... .. ..... ................... ......... .. ...................... 2-4 2.4.1 Minimum Package Size ............. ... .................................................. ............... .... .......... ...... ... 2-4 2.4.2 Tamper-Indicating Feature .................................................... .. ... .... ............. ............... .......... 2-4 2.4.3 Positive Closure.. ............... .... ...... .. ........................ ............. ...................................... .. .. .. .. .... 2-4 2.5 LIFTING AND TIEDOWN STANDARDS FOR ALL PACKAGES .. .............................................. ... ... .. .. .. ... 2-4 2.5. 1 Lifting Devices ........................................................................... ........................................... 2-4 2.5. 2 Tie-Down Devices ............................................................................................ ........ .......... 2-1 3 2.6 NORMAL CONDITIONS OF T RANSPORT ........... ... ......... .................. .. ........ ............. ....... ................. 2-18 2.6.1 Heat .................................................................... .................... ... .................... .. .. ................. 2-1 8 2.6.2 Cold .............................................. .......................................... ......... .. ............... .................. 2-19 2.6.3 Reduced External Pressure ......................... ............................ .. .... .......................... ........ .. 2-19 2.6.4 Increased External Pressure ......... ............... ................................................................... ... 2-20

2. 6.5 Vibration ............ ....... .......... ........................................... ................. .. .. ............................. ... 2-21 2.6.6 Water Spray........................................................ .. ..... ...... .. ......... ........................................ 2-21 2.6. 7 Free Drop ............ .............................. ..................................... ... ... ................... .. .. ....... ........ 2-21

2. 6.8 Corner Drop .. ... ........ ... ....... .................................... .. .... .... ... ... .. ..... .... ........ .... .... .................. 2-24 2.6.9 Compression or Stacking .. ................. ........... .... ......... ... ........................... ....... .. ................. 2-24 2.6. 10 Penetration .. ......... .. .. .. ... ......................................................................... ... .. ............ ....... 2-24 2.6.11 Summary ........................................ ... ... ...... .................................................................... 2-26 2.7 HYPOTHETICAL ACCIDENT C ONDITIONS .......... ... ................ ... ... .. .. ...... .. ...... .......... ......... .... ........ .. 2 -27

2. 7. 1 Free Drop .......................................................... .. .................................... ................. ....... ... 2-27 2.7.2 Crush .. .......... .... ...... .......... .. ..................................................... ... .......... .... .... ............ .... .... .. 2-30

2. 7.3 Puncture ........ ...... ...... .. ....................................................................................................... 2-30 2.7.4 Thermal .................................................................................. ................... .. ....................... 2-32

2. 7. 5 Immersion - Fissile Material ......... ..... ....... .................................... ...................................... 2-36

2. 7. 6 Immersion - All Packages ...................... ................ ... .... .. .............. .... ............................... ... 2-36

2. 7. 7 Deep Water Immersion Test (for Type B Packages Containing More than 105 A 2) .... ....... 2-37

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page ii

2. 7. 8 Summary of Damage ......................................................................................................... 2-37 2.8 ACCIDENT CONDITIONS FOR AIR TRANSPORT OF PLUTONIUM OR PACKAGES WITH LARGE QUANTITIES OF RADIOACTIVITY .................................................................................................................................. 2-41 2.9 ACCIDENT CONDITIONS FOR FISSILE MATERIAL PACKAGES FOR AIR TRANSPORT ......................... 2-41 2.10 SPECIALFORM .......................................................................................................................... 2-41 2.11 FUELRODS .............................................................................................................................. 2-41 2.12 APPENDICES ............................................................................................................................. 2-41 2.12.1 Test Plan 84 Rev 1 (March 1999) .................................................................................. 2-42 2.12.2 Test Plan 84 Report Minus Appendix A (March 2000) .................................... ....... .. ..... 2-43 2.12.3 Model 865 Finite Element Analysis (June 2000) ........................................................... 2-44 2.12.4 USDOT Special Form Certificate USA/0179/S-96 Revision 13 .... .. ... .. ..... ..... .. ... .. .. .. ..... 2-45 SECTION 3 -THERMAL EVALUATION ...................................................................................................3-1

3.1 DESCRIPTION

OF THERMAL DESIGN ....... .. ........... .. ... .................................................................... 3-1

3. 1. 1 Design Features ................................................................................................................... 3-1

3. 1. 2 Decay Heat of Contents ...................................................................................................... 3-1 3.1.3 Summary Tables of Temperatures ................. .. ... .. .. .. ........... .. .............................................. 3-1 3.1.4 Summary Tables of Maximum Pressures ............................................................................ 3-2 3.2 MATERIAL PROPERTIES AND COMPONENT SPECIFICATIONS ....... .. .. .. .. .. .... .. ........ .. ................... .. .... 3-2

3. 2. 1 Material Properties ............................................................................................................... 3-2

3. 2. 2 Component Specifications .................................................................................................... 3-3 3.3 GENERAL CONSIDERATIONS ........................ .... ............................................................................ 3-3 3.3.1 Evaluation by Analysis ......................................................................................................... 3-3 3.3.2 Evaluation by Test ................................................................................................................ 3-3 3.4 THERMAL EVALUATION UNDER NORMAL CONDITIONS OF TRANSPORT ........................................... 3-3 3.4. 1 Heat and Cold....................................................................................................................... 3-3 3.4.2 Temperatures Resulting in Maximum Thermal Stresses ..... .. ... .. .. .. .......... ......... .. ... .. ... .. ...... 3-8 3.4.3 Maximum Normal Operating Pressure ................................................................................. 3-8 3.5 THERMAL EVALUATION UNDER HYPOTHETICAL ACCIDENT CONDITIONS ......................................... 3-9 3.5. 1 Initial Conditions ................................................................................................................... 3-9 3.5.2 Fire Test Conditions ......................................... ............. .. ...... .... ..... ..... ..... .......... ............... 3-10 3.5.3 Maximum Temperatures and Pressure .............................................................................. 3-10 3.5.4 Temperatures Resulting in Maximum Thermal Stresses .......... .. ... .. ... .. ... .. ... .. ........... ........ 3-10 3.5.5 Fuel/Cladding Temperatures for Spent Nuclear Fuel.. ....................................................... 3-10

3. 5. 6 Accident Conditions for Fissile Material Packages for Air Transport ............. .. ........ .. ........ 3-1 O 3.6 APPENDIX ................................................................................................................................. 3-10 SECTION 4 - CONTAINMENT ..................................................................................................................4-1

4.1 DESCRIPTION

OF THE CONTAINMENT SYSTEM ............................................................................. .4-1

4. 1. 1 Special Requirements for Damaged Spent Nuclear Fuel ....... .. .. .. ... .. ............ .. .... .. ........ .. .... 4-1 4.2 CONTAINMENT UNDER NORMAL CONDITIONS OF TRANSPORT ...................................................... .4-1 4.3 CONTAINMENT UNDER HYPOTHETICAL ACCIDENT CONDITION ....................................................... 4-1 4.4 LEAKAGE RATE TESTS FOR TYPE B PACKAGES ........................................................................... .4-1 4.5 APPENDIX ................................................................................................................................... 4-2 SECTION 5 - SHIELDING EVALUATION ................................................................................................. 5-1

5.1 DESCRIPTION

OF SHIELDING DESIGN .......................................................... .................................. 5-1

5. 1. 1 Design Features ................................................................................................................... 5-1 5.1.2 Summary Table of Maximum Radiation Levels .................................................................... 5-1 5.2 SOURCE SPECIFICATION .......................................................... .................. .......... .. .... ........... ....... 5-3 5.2.1 Gamma Source .................................................................................................................... 5-3 5.2.2 Neutron Source .................................................................................................................... 5-3 5.3 SHIELDING MODEL ...................................................................................................................... 5-4

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page iii 5.3.1 Configuration of Source and Shielding .......... .... ......... .................. ..... ..... .......... ...... .............. 5-4 5.3.2 Material Properties ............................................................................................................... 5-4 5.4 SHIELDING EVALUATION ................................ .... ............. ......... .................. ..... ................ ...... ....... 5-4 5.4.1 Methods ....................................................................................................... ..... .................... 5-4 5.4.2 Input and Output Data .......................................................................................................... 5-4 5.4.3 Flux-to-Dose-Rate Conversion ............................................................................................. 5-5 5.4.4 External Radiation Levels ..................................................................................................... 5-6 5.5 APPENDIX ................................................................................................................................... 5-6 5.5.1 Assessment of Model 865 for Actuator Assembly Component Importance ..... ..... ............... 5-7 SECTION 6 - CRITICALITY EVALUATION .............................................................................................. 6-1 SECTION 7- PACKAGE OPERATIONS ................................................................................................. 7-1 7.1 PACKAGE LOADING ................................................................ ..................................................... 7-1 7.1. 1 Preparation for Loading ........................................................................................................ 7-1 7.1.2 Loading of Contents ............................................................................................................. 7-2 7.1.3 Preparation for Transport ..................................................................................................... 7-3 7.2 PACKAGE UNLOADING ................................................................................................................. 7-4 7.2.1 Receipt of Package from Carrier .............................................................. ..... ........... ............ 7-4 7.2.2.1 Removal of Contents ....................................................................................................... 7-5 7.3 PREPARATION OF EMPTY PACKAGE FOR TRANSPORT ............ ....................................................... 7-5 7.4 OTHER OPERATIONS ................................................................................................................... 7-6 7.4. 1 Package Transportation By Consignor ................................................................................ 7-6 7.4.2 Emergency Response .......................................................................................................... 7-6 7.5 APPENDIX ................................................................................................................................... 7-6 SECTION 8 -ACCEPTANCE TESTS AND MAINTENANCE PROGRAM ............................................... 8-1 8.1 ACCEPTANCE TEST ..................................................................................................................... 8-1 8.1.1 Visual Inspections and Measurements ...................... ... .... .. ................................................. 8-1 8.1.2 Weld Examinations ............................................................................................................... 8-1 8.1.3 Structural and Pressure Tests .................. ............................................................................ 8-1 8.1.4 Leakage Tests ...................................................................................................................... 8-2 8.1.5 Component and Material Tests ........ .... ......... .... ............. .... ..... .... ............... ........... ..... .......... 8-2 8.1.6 Shielding Tests ..................................................................................................................... 8-2 8.1. 7 Thermal Tests....................................................................................................................... 8-2 8.1.8 Miscellaneous Tests ........ .... .... ..... .... ..... .... .... .... ..... .... ......... ......... ..... ................................... 8-2 8.2 MAINTENANCE PROGRAM ............................................................................................................ 8-3 8.2.1 Structural and Pressure Tests ...... ............. ................. ......... ......... ..... .......... ..... ..... ...... ......... 8-3 8.2.2 Leakage Tests ...................................................................................................................... 8-3 8.2.3 Component and Material Tests ............................................................................................ 8-3 8.2.4 Thermal Tests ................................ .... ............. .... ......... .... .............. ..... ..... ..... ..... ..... .............. 8-3 8.2.5 Miscellaneous Tests ............................................................................................................. 8-3 8.3 APPENDIX ......................................... .... ............. ........ .... ......... ..... .... ..... .......... .......... .................. 8-4 SECTION 9- QUALITY ASSURANCE ....................................................................................................9-1 9.1 U.S. QUALITY ASSURANCE PROGRAM REQUIREMENTS ............................ .......... ........................... 9-1 9.2 CANADA QUALITY ASSURANCE PROGRAM REQUIREMENTS ........................................................... 9-1

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page iv List of Tables TABLE 1.2.A: MODEL 865 PACKAGE INFORMATION .. .......... ......... ................................................................ .............. 1-I TABLE 2.2.A: MECHANICAL PROPERTIES OF PRINCIPAL SAFETY RELATED TRANSPORT PACKAGE MATERIALS ... 2-2 TABLE 2.6.B:

SUMMARY

TEMPERA TURES NORMAL TRANSPORT ....... ... .. ...... ... ...... ... ....... ............................. ......... 2-18 TABLE 2.7.A:

SUMMARY

OF DAMAGES DURING TEST PLAN 84 ........... ................... ...... ........... .... ... ...................... ... 2-38 TABLE 3.1.A:

SUMMARY

TABLE OF TEMPERATURES ................................................................................................. 3-1 TABLE 3.1.B:

SUMMARY

TABLE OF MAXIMUM PRESSURES ................. ....................... .. ... ..... ......... ........................... 3-2 TABLE 3.2.A: THERMAL PROPERTIES OF PRINCIPAL TRANSPORT PACKAGE MATERIALS ................... .................... 3-2 TABLE 3.4.A: INSOLATION DATA****************************************************************************************** **** **** ******************************* 3-5 TABLE 5.1.A: MODEL 865 TEST UNIT TP84(A) AFTER TRANSPORT TESTING

SUMMARY

TABLE OF EXTERNAL RADIATION LEVELS EXTRAPOLATED TO CAPACITY OF 240 Cl IR-192 (NON-EXCLUSIVE USE) ....................... 5-2 TABLE 5.1.B: MODEL 865 TEST UNIT TP84(B) AFTER TRANSPORT TESTING

SUMMARY

TABLE OF EXTERNAL RADIATION LEVELS EXTRAPOLATED TO CAPACITY OF 240 Cl IR-192 (NON-EXCLUSIVE USE) ....................... 5-2 TABLE 5.1.C: MODEL 865 TEST UNIT TP84(B) AFTER TRANSPORT TESTING ......... .............. .................................. 5-3 TABLE 7.1.A: MODEL 865 PACKAGE INFORMATION ......................... ....... ........... ..... ...... ..... .. .... ....... ................. .... ..... 7-1 List of Figures FIGURE 1.2.A - MODEL 865 TRANSPORT PACKAGE** ********************************************************* **************************************** 1-2 FIGURE 1.2.B-MODEL 865 TRANSPORT PACKAGE KEY COMPONENTS .......... ................ .. ....................................... 1-2 FIGURE 1.3.A - SKETCH OF MODEL 865 PREPARED FOR TRANSPORT .......... .............. .......... ................................... 1-6 FIGURE 2.5.A - HANDLE CROSS SECTION ........................ .................... ................... .... ......... ... .. ......... ........................ 2-5 FIGURE 2.5.B- FLAT BAR CROSS SECTION* ****************** ******** ****** ********** ********************** ***** ** *************** **** ***** ***** ********** 2-5 FIGURE 2.5.C - WELD CROSS SECTION ....... .... ......................................... ... ....... ...... ........... ..... ......... ............. .. .. ........ 2-6 FIGURE 2.5.D-WELD DIMENSIONS **************************************************************************************************************************** 2-7 FIGURE 2.5.E - LIFTING CASE 1 ************************************************************************************************* **** ****** ******* ******** ******** 2-7 FIGURE 2.5.F - FORCE SYSTEM APPLIED TO HANDLE ............................................................................................... 2-9 FIGURE 2.5.G - LIFTING CASE 2 ....................................... ...................................................... ........ ........................... 2-10 FIGURE 2.5.H - LIFTING CASE 3 ******************************************************************************************************************************** 2-11 FIGURE 2.5.1- FORCE SYSTEM APPLIED TO FLAT BAR LINKS ................................................................................. 2-12 FIGURE 2.5.J - GENERAL CASE OF TIE-DOWN ............................................................... ........... ... ... ......................... 2-13 FIGURE 2.5.K- RESULTANT FORCE ON LINK WELD ................................................................................................ 2-17 FIGURE 2.6.A- MODEL 865 (TP84(A)) 1.2 M DROP TEST ORIENTATION TOP DOWN DROP ............ ..................... 2-22 FIGURE 2.6.B- MODEL 865 (TP84(B)) 1.2 M DROP TEST ORIENTATION SIDE DROP ....................... ................. .. . 2-23 FIGURE 2.6.C - MODEL 865 COMPRESSION TEST ORIENTATION ............................................. ............................... 2-24 FIGURE 2.6.D- MODEL 865 TP84(A) PENETRATION TEST ORIENTATION ........................... .... ............................... 2-25 FIGURE 2.6.E - MODEL 865 TP84(B) PENETRATION TEST ORIENTATION .............................................................. 2-26 FIGURE 2.7.A- MODEL 865 (TP84(A)) 9 M DROP TEST ORIENTATION* END DROP ........ .................. ... .... ............ 2-28 FIGURE 2.7.B- MODEL 865 (TP84(A)) 9 M DROP TEST ORIENTATION* SIDE DROP ............................................ 2-29 FIGURE 2.7.C-MODEL 865 (TP84(A)) PUNCTURE TEST ORIENTATION COVER BOLTS OF THE PACKAGE ......... 2-31 FIGURE 2.7.D- SECTION THROUGH PROJECTOR WELDMENT ........ .......................................... ............................... 2-34 FIGURE 3.4.A- MODEL OF CYLINDRICAL PACKAGE FOR HEAT ANALYSIS ................... ... ............... .......... ................ 3-3 FIGURE 5.1.A- PROFILE ORIENTATION FOR THE MODEL 865 ..................................... ....... ........... ............................ 5-1 FIGURE 5.4.A- SAMPLE SURFACE CORRECTION FACTOR DISTANCE CRITERIA ...................................................... 5-5 FIGURE 5.5.A - INSPECTED CONFIGURATION ..................... ......................................................................................... 5-7 FIGURE 5.5.B

COMPLIANT CONFIGURATION ........ ....... ..... ................. .. ..... .... ..... ....... ..... .. ..... ..................................... 5-7

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 1-1 Section 1 - GENERAL INFORMATION 1.1 Introduction The Model 865 is designed as an industrial radiography device and transport package for Type B quantities of special form radioactive material. It conforms to the Type B(U)-

96 criteria for packaging in accordance 10 CFR 71, 49 CFR 173, and IAEA Regulations for the Safe Transport of Radioactive Material TS-R-1 (2009 Edition) and SSR-6 (2018).

This submission is formatted in accordance with NUREG-1 886 "Joint Canada - United States Guide for Approval of Type B(U) and Fissile Material Transportation Packages" dated March 2009.

12 Packa e Description The Model 865, shown in Figures 1.2.A and 1.2.B, is constructed in accordance with descriptive drawing R86590 in Section 1.3. Its general dimensions are 12 1/4 inches (311 mm) long by 7 5/8 inches (194 mm) in diameter, and has a maximum weight of 60 lbs (27 kg) including contents. The general package information is shown in Table 1.2.A.

Table 1.2.A: Model 865 Package Information Isotope Maximum Chemical/ Maximum Maximum Maximum DU 4 Maximum Capacity 1 Physical Form Content Weight Decay Heat3 Weight Package Weight lr-192 240Ci Metal 1 gram 4.8 Watts 42Ibs 60lbs (Special (8.89 TBq) (19 kg) (27 kg)

Form) 2 1

Maximum Activity for lr-192 is defined as output Curies as required in ANSI N432 and 10 CFR 34.20 and in line with TS-R-1 and SSR-6 and Rulemaking by the USNRC and the USDOT published in the Federal Register on 26 January 2004.

2 Special Form is defined in 10 CFR 71, 49 CFR 173, IAEA TS-R-1 and SSR-6.

3 Maximum decay heat for lr-192 is calculated by correcting the output activity to content activity. A factor of 2.3 is used for lr-192 to account for source capsule and self-absorption in this conversion.

4 DU = Depleted Uranium

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 1-2 Figure 1.2.A - Model 865 Transport Package 1.2.1 Packaging Figure 1.2.B, with the following paragraphs, describe the major components of the transport package.

SOURCE SHIELD ROO&CAPSULE ENCASEMENT HOLDER BOTTOM I TOP l:ND ENO ACl\JAi OR GUARD Figure 1.2.B - Model 865 Transport Package Key Components

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 1-3 Except for the shield assembly, and some components of the lock assembly, all materials of construction are stainless steels. The major components of the package consist of the following :

Source capsule and Rod Assembly

Stainless steel welded shield encasement

Shield (Depleted Uranium)

Source Actuator and Lock assembly

Actuator Guard and Shipping Cover

Handle Weldment

Housing Support The external surfaces of the Model 865 are smooth stainless steel and are easily decontaminated. Because the Model 865 is designed for underwater use, there are no materials, which will degrade due to short-term exposure to water.

1.2.1.1 Stainless Steel Welded Shield Encasement The package consists of a stainless steel cylindrical housing which contains a depleted uranium shield onto which two brass support rings are fitted. The shield is secured in position by locating the brass support rings into two stainless steel plates welded onto each end of the cylindrical housing. The shield is prevented from rotating inside the housing by an offset stainless steel pin with bronze sleeve extending from the lower shield collar into the shield. The brass rings also prevent a eutectic reaction between the steel and uranium at elevated temperatures.

1.2.1.2 Shield (Depleted Uranium)

The depleted uranium shield provides the primary radiation protection for the Model 865. When the source is in the shielded position , the shield limits the transmission of gamma rays to a maximum dose level of 200 mR/hr (2 mSv/hr) at the package surface and 10 mR/hr (0.1 mSv/hr) at one meter from the surface of the package. Additional shielding above the radioactive source is provided by the tungsten source rod assembly.

1.2.1.3 Source Capsule and Rod Assembly The Model 865 radioactive source assembly contains a special form source capsule contained within a source rod assembly. During rad iography, actuation of the source rod and movement of the source is accomplished by pneumatic actuation. During transport, the source rod and source are locked in the shielded position within the Model 865 package.

The Model 865 incorporates a positive visual indication of source position.

This is accomplished by means of the source rod assembly, which emerges from the actuating cylinder as the source is exposed. The emergent length of the rod indicates the position of the source. When the source is in its fully shielded storage position , the rod is no longer visible. During rad iography,

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 1-4 the source rod is spring biased into the shielded position during source retraction.

1.2.1.4 Source Actuator and Lock Assembly The package is key operated to prevent unauthorized personnel from actuating the source rod. The unit can only be locked when the source assembly is in the shielded storage position. The package locking components are part of the actuator base welded on the package. When in the locked position, a plunger style lock secures the source rod in the actuator base and prevents movement of the source when the plunger lock is engaged. The remaining components of the actuator assembly are not relied upon in securing the source within the Model 865 package during transport, although the actuator piston and the actuator spring are additional mechanisms during transport which retain the source rod assembly in the fully shielded position should the plunger style lock fail during transport.

These components are applicable primarily for operation of the Model 865 as a radiographic device, although these components do provide some limited, effective shielding for the top of the package.

1.2.1.5 Actuator Guard and Shipping Cover During transportation the actuator and lock assembly is protected by a stainless steel actuator guard and a stainless steel shipping cover. The actuator guard is bolted to the container weldment with its bolts during transport. The shipping cover is bolted to the container weldment over the actuator guard and fitted with a seal wire to serve as a tamper indicating seal during transport. The cover acts as a secondary securing mechanism which ensures the source rod remains in the shielded position in the container should the plunger style lock fail during transport.

1.2.1.6 Housing Support The Model 865 is fitted with two folded stainless steel feet (housing supports) welded to the shield encasement. The housing supports allow the unit to be stabilized on a flat or large cylindrical surface. These supports also incorporate r&inforcement parts that add strength when used to attach the Model 865 to set-up fixtures during radiographic operations.

1.2.1. 7 Handle To assist in lifting the package, there is a stainless steel tubular handle, again fixed to the projector weldment by means of stainless steel handle mounts.

The handle is suitable for manual or mechanical lifting and may assist in securing the package during transportation.

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 1-5 1.2.2 Contents The Model 865 transport package is designed to transport special form capsules containing the lr-192 . The maximum package source decay heat for lr-192 in Table 1.2.A. has been adjusted to account for content activity of the source. Actual content to output activity varies based on the capsule configuration as well as variations in isotope self-absorption. A factor of 2.3 was used for lr-192 to convert output activity to content activity as this factor reflects the worst case variation for lr-192 sources transported in this package. The source capsule is loaded into the Model 865 device and secured according to the procedure described in Section 7.

The maximum weight of the source is also listed in Table 1.2.A. The content weight value is calculated based on the package capacity and the lowest specific activity of lr-192 (200 Ci/gram) used in source production for these devices.

Note: lr-192 of higher specific activity can be used, but this would produce sources with lower total mass of the contents. The value listed in the Table 1.2.A. is the maximum content mass.

1.2.3 Special Requirements for Plutonium Not applicable. This package is not used for the transportation of plutonium .

1.2.4 Operational Features The containment system for the Model 865 transport package is the radioactive source capsule referred to in Section 4.1 of this Safety Analysis Report. This package does not involve complex containment systems for source securement. The sources for this package are all special form , welded capsules. The capsules are loaded into the 865 source rod assembly which is held securely in the container by components of the source actuator/lock assembly attached to the upper shield collar. The plunger lock on the source actuator assembly base engages the source rod and prevents it from moving the source to the exposed position during transport.

When the Model 865 device is prepared for transport,

the source rod is maintained in the fully shielded position by means of the actuator piston connected to the source rod which is held in the fully shielded position by the actuator spring,

the lock plunger is engaged in the locked, secured position by a key lock,

an actuator guard is installed over the actuator assembly and a shipping cover is secured over the actuator guard to further protect the actuator assembly and prevent movement of the actuator piston/source rod assembly from the shielded position during transport.

The 865 transport container is assembled and secured as described in Section 7.

1.3 Appendix

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 1-6 Figure 1.3.A. shows a sketch of the Model 865 package as prepared for transport.

Additional drawings of the Model 865 transport package are enclosed in this appendix.

Section 1.3.1 contains a detailed drawing to support USN RC review of this package design. Section 1.3.2 contains a drawing for use by shippers of this container for transport.

Figure 1.3.A - Sketch of Model 865 Prepared for Transport

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 1-7 1.3.1 Drawing R86590

Security related information withheld per 10 CFR 2.390.

Safety Analysis Report for the Model 865 Transport Package QSA Global; Inc. April 2023 - Revision 14 Burlington , Massachusetts Page 1-8 1.3.2 R865-USER

Security related information withheld per 10 CFR 2.390.

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-1 Section 2 - STRUCTURAL EVALUATION This section identifies and describes the principal structural engineering design of the packaging, components, and systems important to safety and compliance with the performance requirements of 10 CFR Part 71 , TS-R-1 and SSR-6.

2.1 Description of Structural Design 2.1 .1 Discussion The Model 865 transport package is described in Section 1.2, "Package Description."

2.1 .2 Design Criteria The Model 865 transport package is designed to comply with the requirements for Type B(U) packaging as prescribed by 10 CFR 71, IAEA TS-R-1 and SSR-6. All design criteria are evaluated by a straightforward application of the appropriate section of these requirements.

In addition to the transport design criteria, the Model 865 transport package meets the performance requirements for industrial radiography devices in ANSI N432-1980 and ISO 3999:2004(E). When used as a radiography device, the Model 865 is designed to function in underwater environments up to 2,025 feet below sea level.

2.1 .3 Weight and Centers of Gravity The transport package weighs a maximum of 60 lbs (27 kg). The shield includes a maximum of 42 lb (19 kg) of DU shielding. The center of gravity of the 865 transport package is located along the cylindrical axis of the package at a distance of 3.4 inches (86 mm) above the bottom surface.

2.1.4 Identification of Codes and Standards for Package Design See Section 2.1.2 relating to design criteria of the package. Any applicable, specific codes or standards related to the finished assemblies for this transport package is specified on the drawings contained in Append ix 1.3. All component fabrication (including assembly) is controlled under the QSA Global, Inc. Quality Assurance Plan approved by the USNRC and ISO. All welding under this plan, performed after 21 November 2005, adheres to the standards referenced on the drawings in Appendix 1.3.

All hardware meets the standards referenced on the drawings in Appendix 1.3. All external fabrication deemed critical to safety is either verified to equivalent in-house standards or dedicated as appropriate for use prior to release as part of this transport package.

In general, the design meets the applicable requirements for Type A and Type B(U) containers as specified in 49 CFR, 10 CFR 71 and IAEA regulations identified in Section 1.1.

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-2 2.2 Materials 2.2.1 Material Properties and Specifications Table 2.2.A lists the relevant mechanical properties (at ambient temperature) of the principal materials used :n the Model 865 transport package. The location and use of these materials is shown on the drawings contained in Section 1.3. The applicable sources are listed after the table.

Table 2.2.A: Mechanical Properties of Principal Safety Related Transport Package Materials Tensile Yield Elongation Strength, Strength, Material Form Spee:ification Condition (% in 2 in) minimum minimum

"'(% in 4 D}

(KSI) (KSI)

ASTM F738M Stainless Steel ISO 4017, ISO Class 50, NA Grade A2, A3, Fastener 72 30 4014 and/or 70 or 80 (See Note A)

A4 or AS ISO 3506-1 Stainless Steel ASTM A276 or Bar Annealed 70 25 30 i 304/304L A479 1' Stainless Steel ASTM A240 or I Plate Annealed 70 25 30 304/304L A666 Stainless Steel Forging ASTM A182 Annealed 70 25 30 304/304L Stainless Steel ASTM A269, Tube Annealed 75 25 30 304/304L A511 or A554 Tungsten Bar ASTM 8777 Any Class 94 75 2 Depleted Casting Ref.#1 , P.822 As Cast 58 29 4 Uranium Resource

References:

1. American Society for Metals, Metals Handbook Ninth Edition, Volume 2 Properties and Selections:

Nonferrous Alloys and Pure Metals, 1979.

2. American Society for Metals, Metals Handbook Ninth Edition , Volume 3 Properties and Selections:

Stainless Steels, Tool Materials and Special-Purpose Metals, 1980.

3. National Aerospace Standard, NAS1330, Nut, Blind Rivet- Countersunk Head. Note: Two fasteners used

-One per NAS1330N8E with 10,400 lb-min ultimate thread strength and one per NAS1300N5E with 6,870 lb-min ultimate thread strength. Both tested per ASTM F606.

NOTE for Table 2.2.A:

A. Not Applicable - Fastener length less than 2.5 times nominal thread diameter.

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-3 2.2.2 Chemical , Galvanic or Other Reactions The safety related materials used in the construction of the Model 865 transport package are listed in Table 2.2.A of this SAR. During operation as a radiography device, the Model 865 is designed to be submersed in water. Seawater, in particular, may act as an electrolyte and assist the process of bimetallic corrosion .

The bimetallic corrosion of phosphor bronzes and tin bronzes in contact with austenitic stainless steel may be quite severe in a marine environment; particularly if the area of stainless steel is large compared to the area of bronze. However, the two metals are only in contact within the projector weldment, which is sealed against water ingress by rubber O-ring seals, which form part of the actuator assembly. Crevice corrosion occurs typically between nuts and washers or around the thread of a screw or the shank of a bolt. Crevices can also occur in welds, which fail to penetrate, and under deposits or films on the steel surface. Type 304 stainless steel has a critical crevice temperature below -2.5°C and is therefore susceptible to crevice coriOsion. The Model 865 units, which are used in an environment where chloride is present, particularly a marine offshore application , are checked during maintenance procedures for signs of corrosion .

(See Section 8.) These units have been used by radiographers in the USA since 1984 with no evidence of significant corrosion occurring from use which would adversely effect the package ability for safe transport.

To prevent the possible formation of a eutectic alloy of stainless steel and depleted uranium at elevated temperatures during the Hypothetical Accident Conditions thermal scenario, defined by 10 CFR 71 .73(c)(4) , brass spacers have been used. The spacers are located between the depleted uranium shield and stainless steel package weldment.

With this construction , there will be no significant chemical or galvanic reaction between package components during normal or hypothetical accident conditions of transport.

2.2.3 Effects of Radiation on Materials Depleted uranium, tungsten, steel and brass have been used in this package, as well as other transport packaging , for decades without degradation of the package performance over time. The Model 865 has been transported since 1984 with no sign of material degradation due to irradiation from the package contents. Components such as nitrile rubber seals/a-rings used in the package are routinely replaced during service/maintenance which limits field use and radiation induced degradation impacts on the package integrity.

2.3 c-,... ..*,.. +*nn nrl J::xarrination 2.3.1 Fabrication Package components are procured, manufactured and inspected for use under QSA Global, Inc. NRC approved QA Program Number 0040. This QA program is based on the application of guidance contained in NUREG/CR-6407 "Classification of Transportation Packing and Dry Spent Fuel Storage System Components According to Importance to Safety (1996). Quality Class A components necessary to maintain containment and integrity on the package are considered to be important to the package

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington , Massachusetts Page 2-4 safety. All newly fabricated transport packages will be evaluated and documented for compliance to the drawings provided in Section 1.3 prior to initial use of the containers as a Model 865 transport package.

2.3.2 Examination Sections 7 & 8 describe the acceptance testing and routine maintenance requirements for shield containers and package components used on the Model 865 packages.

2.4 General Requirements for All Packages 2.4.1 Minimum Package Size The transport package exceeds the minimum size requirements since the package measures 12 1/4 inches (311 mm) tall, 5 1/4" wide (133 mm) and 7 5/8 inches (194 mm) deep.

2.4.2 Tamper-Indicating Feature This package incorporates a seal wire attached to at least two of the bolts securing the shipping cover over the lock and actuator fasteners of the package. This seal wire is not readily breakable, therefore if it is broken during transport, it serves as evidence of possible unauthorized access to the contents.

2.4.3 Positive Closure This package does not involve complex containment systems for source securement.

The radioactive material is sealed inside a special form capsule placed inside the Model 865 source rod and holder assembly. During transport, the source rod assembly is held securely in the device by components of the lock, actuator and cover assemblies. The lock assembly components are part of the actuator base which is welded to the shield encasement. These features maintain positive closure of the transport package and containment of the radioactive material during transport.

2.5 Liftin and Tiedown Standards for All ackages 2.5.1 Lifting Devices The Model 865 is a portable device, which is designed to be lifted manually or with mechanical assistance by its tubular handle. It is reasonable to assume that no other part or method of lifting will be used. The lifting analysis will therefore focus on the ability of the tubular handle and connecting welds to resist the applied loads. All elements must remain within yield when subjected to the weight of the Model 865 with a factor of safety of three. The mass of the Model 865 is 60 lbs. (27 kg) , therefore the applied load is (3)(27 kg)(9.81 m/s2) = 795 N.

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-5 2.5.1.1 Section Properties 2.5.1.1.1 Tubular Handle 0 019 022 Figure 2.5.A - Handle Cross Section Design strength, Py = Y0 _2 = 210 N/mm 2 where Yo.2 is 0.2% proof stress for grade 304 stainless steel.

Gross area, Ag =~ x ((22 mm) 2 - (19 mm)2) = 97 mm 2 Second moment of area, I =~ x ((22 mm) 4 - (19 mm) 4 ) = 5,102 mm 4 Section modulus, z = 22 ~ m/ 2 = 464 mm 3 Radius of gyration, r = fI.Ag

= 7.3 mm 2.5.1.1.2 Flat Bar Figure 2.5.B - Flat Bar Cross Section 2

Design strength , Py =Y02 =210N/mm Gross area, Ag = 19 mm x 6.35 mm = 121 mm 2 Second moment of area,

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-6 19 mm x (6.35 mm)3 lxx = 12

= 405 mm 4

_ 6.35 mm x ( 19 mm) 3 _

lyy - - 3,630 mm 4 12 Section modulus,

_ 405 mm 4 _ 3 Zxx - _ mm/ 2 - 128 mm 6 35

_ 3,630 mm 4 _ 3 Zyy - 19 mm/ 2 - 382 mm Radius of Gyration, rx = . fu = 1.8 mm pi,;

2.5.1.1.3 Connecting Welds 3.2 r ~45° Ll I. I3.2

Figure 2.5.C - Weld cross Section Throat thickness, t = 3*2.;;m= 2.25 mm From reference 1, the design strength of the weld may be taken as:

Pw = 0.46Us where, minimum UTS of gr. 304 stainless steel, Us = 500 N/mm 2

. Pw = 230 N/mm 2

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-7 y

X I I 11x+t 10.9 Iv

~

I~ .

6 Figure 2.5.D - Weld Dimensions Area of weld, Aw= (23.6 mm x 10.9 mm) - (19.1 mm x 6.4 mm) = 135 mm 2 Second moment of area of weld, I = 23.6 mm x (10.9 mm) 3

_ 19.1 mm x (6.4 mm) 3

= 2 130 mm4 xx 12 12 '

Modulus of weld, Zxx = 1 0.9 1mm

"" I = 391 mm 2

3 2.5.1.1.4 Case 1 795N 6.4 795N Figure 2.5.E - Lifting Case 1

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-8 (1)

(2)

(3)

(2) & (3) into (1)

T3 + T3 cos 550 = 795N cos35° T3 = [, + : :550 ] =468N cos35° Therefore, substituting back into (2) & (3), T1 = 662 N and T2 = 571 N Now, Taking moments about A, 152.4 mm x F2 + 6.4 mm x T1sin 45° = (152.4 mm + 82.6 mm) x T2sin35.2° (5)

Substituting for T1 and T2 into (5) and rearranging, F2 = ((235 mm x 571 N x sin35.2°) - (6.4 mm x 662 N x sin45°))/152.4 mm = 488 N Substituting F2 into (4)

F1 =795 N- 488N

= 307 N

Safety Analysis Report for the Model 865 Transport Package QS, Bur 468N 3 2 7N 6 .4 l 5 2 .4 8 2 .6 468N 310N 485N Figure 2.5.F - Force System Applied to Handle Applied compression force, T3 = 468 N Effective length, LE = 2L = 2 x 82.6 mm = 165.2 mm Slenderness, 'A, = LE/r = 165.2 mm/7 .3 mm = 23 Compression capacity of tube, Pe= xPcA9 py Where, Pc = 1, for plastic, compact or semi-compact sections a= o.49 il 0 = 0.40 x=l (ref. 2.5.1.1 .1 for additional equation values)

Therefore, Pc 1 x1 xA9 Py

= 97 mm 2 x 210 Nmm 2

= 20,370 N > 468 N Applied bending moment, M = (327 N x 83 mm)+ (468 N x 6.4 mm)

= 30,136 Nmm Moment capacity, Mc

= 210 Nmm 2 x 464 mm 3

= 97,440 Nmm > 30,136 Nmm

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington , Massachusetts Page 2-10 Combined bending and compression stress check E + M = 1 Pc Mc 468 N + 30,136 Nmm = 0.33 < 1 20,370 N 97,440 Nmm Conclusion : The handle does not yield when the Model 865 is lifted with the aid of an attachment in the orientation shown in case 1.

2.5.1.1.5 Case 2 795N 93 .7 58 .8

~~~~~~~~~~~~~~ ~~ ....*~--:-:--c--:--:---:-:~

~~~~~~~~~~~~~~ ~ ~~~~~~~~ '

795N Figure 2.5.G - Lifting Case 2

= 795 N (1)

Taking moments about A, 795 N x 93.7 mm = 152.5 mm F2 F2 = 488 N (2)

Substituting (2) into (1)

= 795 N -488 N

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-11

= 307 N Maximum applied moment, M = 307 N x 93. 7 mm

= 28,766 Nmm < 97 ,440 Nmm From reference 1, Section 4.2, Tension capacity of flat bar,

= 121 mm 2 x 210 Nmm 2

= 25,410 N > 488 N Tension capacity of weld, Ptw = AwPw (see 2.5.1.1.3 for Aw calculation)

= 135 mm 2 x 230 Nmm 2

= 31,050 N > 488 N

Conclusion:

All elements of the handle are within yield capacity. A single weld group is capable of resisting the applied load in tension without yielding.

2.5.1.1.6 Case 3 795N Figure 2.5.H - Lifting Case 3

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-12 572N Figure 2.5.1- Force System Applied to Flat Bar Links Section and weld most heavily stressed at Point A Applied tensile load, F1 = 795 N x sin46°

= 572 N Tensile stress on weld = FtfAw

= 572 N/135 mm 2

= 4.3 N/mm 2 Applied shear load , Fs = 795 N x cos46°/2

= 276 N Shear stress on weld = 276 N/135 mm2

= 2.1 N/mm 2 Applied bending moment, M = Ix 552 N x 32 mm2

= 8,832 Nmm Applied bending stress= 8,832 Nmm/128 mm 3

69 N/mm 2 Maximum combined stress on weld

.J ( [(69 N /mm2 + 4.3 N /mm 2 ) 2 + (2.1 Nmm2 )]2 = 73 N/mm 2 < 230 N/mm 2 Conclusion : The lifting force is applied to the flat bar and connecting weld both of which have been demonstrated above to be within yield.

Therefore, the lifting device is capable of supporting more than three times the weight of the transport package as required by 10 CFR 71.45(a).

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page2-13 2.5.2 Tie-Down Devices The following design analysis calculates the minimum tension required in the tie-down lashings to achieve a no-slip condition and to prevent overturning without the requirement for chocks.

L PL y,Mg L ~

~

_y,_M_g---i--------,-

9-

~'

YL X Q) @

~,~ ~

~Mgt-y.Mg <r

r:

Mg

~,~

..c: ~

<.1 CD ~

ZL X Figure 2.5.J - General Case of Tie-Down

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-14 2.5.2.1 Design Assumptions (i) The coefficient of friction between the package and transport bed is known.

(ii) The center of gravity of the package is known.

(iii) All lashings are independent.

2.5.2.2 Design Forces All applied forces are assumed to act through the center of gravity of the package and are resolved into components along the three orthogonal axes shown in Fig. 2. 5.J . The applied forces are determined by calculating the product of the given acceleration and the total mass of the package.

Tie-down members 1 & 4 resist acceleration ax, therefore, P1x = P4x Tie-down members 1 & 2 resist acceleration ay, therefore, P1y = P2y All tie-down members resist acceleration az, therefore, P1z = P2z = P3z = P4z The maximum tension will occur in tie-down 1:

2.5.2.3 Calculation of General Case of Tie-Down 2.5.2.3.1 Input information Acceleration factor in x-direction, Yx = 10 Acceleration factor in y-direction, yy =5 Acceleration factor in z-direction, Yz =2 Height of attachment to package, H = 0.14 m Length of Package, L = 0.153 m Width of Package, W = 0.127 m Distance to center of gravity, PL = 0.094 m Distance to center of gravity, 'AW = 0.0635 m Height to center of gravity, h = 0.078 m Angle of tie-down, a = 45 deg Angle of tie-down, ~ = 45 deg Coefficient of friction, µ = 0.2 (metal/metal)

Total mass of package, M = 27 kg p = 0.61

'A = 0.50

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-15 2.5.2.3.2 Determination of Individual Tie-Down Forces Consider acceleration ax The package is subjected to a longitudinal acceleration ax. The vertical components of the tension in the tie-down, which arise from the longitudinal acceleration, will generate a friction force between the package and the conveyance platform, which will oppose the applied force.

Vertical load imported to platform = 2P1xsin<j> + Mg(1-yz)

Horizontal load on package = Max

= 2P1xCOSq>COSa + µ[2P1xsin<j> + Mg(1 - Yz)]

Rearranging, P1x = Mg[yx-u( 1-1z)]

2(cos<j>cosa + µsin<!>)

Tension in tie-down 1 to stop slip, P1x = 2,106 N Consider overturning about 2,3 due to acceleration ax

= 2P1xHcos<j>cosa + 2P1xlsin<j> + Mg(1-~)L Rearranging, P1x = Mq[yxh + (1-{3)fo-1)L]

2[Hcos<j>cosa + Lsin<j>]

= 624 N Consider spinning about 6,7 due to acceleration ax. P1x must be large enough to induce sufficient friction between the package and freight bed to prevent spinning of the package.

yMg(H-h) + Mg(yz-1 )~L = µH[2P1xsin~ + Mg(1-yz)]

Rearranging, P1x = Mg[yx{H-h) + {yz-1 )(BL+ µH)]

2µHsin~

= 4,963 N Therefore, P1x is governed by spinning about 6,7.

Similarly, considering acceleration ay.

Vertical load imparted to platform = 2P1ysin~ + M(g-ay}

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-16 Horizontal load on package = Mgyy

= 2P1ycos<j>sina + µ[2P1ysin<j>+Mg(1-yy}]

Rearranging , P1y = Mghy-µ(1-yz}}

2(cos<j>sina+µsin<j>)

Tension in tie-down 1 to stop slip, P1y = 1,084 N Consider overturning about 3,4 due to acceleration ay.

Mgyyh + Mgyy(1-'A.)'vV =2P1yHcos<j>sina + 2P1yWsin<j> + Mg(1-'A.)W Rearranging, P1y = Mghyh + (1-'A.)(yz-1 )W) 2[Hcos<j>sina + Wsin<j>]

= 376 N Consider spinning about 7, 8 due to acceleration ay.

yyMg(H-h) + Mg(yz-1 )'A.W = µH[2P1ysin<j> + Mg(1-yz)]

Rearranging, P1y = .M.g[yy(H-h) + (yz-1 )('A.W+µH)]

2µHsin<j>

= 2,686 N Therefore, P1y is governed by spinning.

Finally, vertical acceleration az.

4P12sin<j> = Mg(1-yz)

Rearranging , P1z = Mg(1-yz) 4sin<j>

The individual tie-down forces are thus:

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-17

= P1x + P1y + P1z: 7,743 N

= P1v + P1z = 2,780 N

= P1z = 94 N

= 5,057 N 2.5.2.4 Maximum load on handle It is assumed that P1 and P4 are attached to the package at the same point on handle.

Resultant Maximum Load on Handle = P1 + P4 I I

= 9,248 N Angle of Resultant Load from x-axis = 191. 9° It is also assumed that P2 and P3 are attached to the package at the same point.

Resultant Load on Handle = I P2 + P3 I

= 2,781 N Angle of Resultant Load from x-axis = 316.9° 11.9° 6539N Figure 2.5.K - Resultant Force on Link Weld

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-18 The weld is subjected to a shear force equal to the horizontal resultant of the maximum tensile load from the tie-down system on an individual link; Maximum horizontal resultant force = (9,248 N)cos45°

= 6,539 N CJsw = 6,539 N/135 mm 2

= 48.4 N/mm 2 < 230 N/mm 2 Therefore, the weld will not be subjected to stresses greater than the weld design strength in the tie-down case considered.

2.6 Normal Conditions of Transport 2.6.1 Heat The heat source for the Model 865 transport package is 240 Ci (output activity) of lr-192 which is conservatively equivalent to 552 Ci (content activity). This generates approximately 8.6 milliwatts per Curie based on 1.46 MeV/decay which results in a worst case heat generation from the source of 4.8 Watts (see Table 1.2.A). The thermal evaluatlon for the heat test is described in Section 3.

Resource references:

Table of Isotopes, Volumes I & 11 , Eighth Edition. John Wiley & Sons, Inc. , 1996.

Assuming the entire decay heat, 4.8 Watts, is absorbed by the package, this would result in a worst case package surface temperatures shown in Table 2.6.B.

2.6.1.1 Summary of Pressures and Temperatures T a bl e 2..

6 B S ummary T emperat ures Norma IT ranspo rt Temperature Model 865 Comments Condition lnsolation 62.9°C Section 3.4.1.1.

(38°C in full sun) (145.2°F)

Decay Heating 44°C Section 3.4.1.2 (38°C in shade) (111°F)

Evaluation of pressures for this package are contained in Section 3.4.2 and summarized in Table 3.1.B. As demonstrated in Section 3.4 for the Normal Transport Condition thermal assessment, the package containment can withstand this pressure differential with no adverse effect on the containment.

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-19 2.6.1.2 Differential Thermal Expansion Any thermal expansion encountered during Normal Transport will be insignificant with respect to the manufacturing tolerances for the components of the package.

2.6.1.3 Stress Calculations Stress calculations for normal transport of this package are contained in Sections 2.5.1 and 2. 7.4. Results of these calculations demonstrate that the package meets the requirements for Normal Transport.

Section 2.5.1 demonstrates that the package fabrication is satisfactory to meet the stress associated with the lifting requirements of 10 CFR 71.45(a). Section 2.7.4 addresses the package ability to satisfactorily withstand the thermal stresses generated under Hypothetical Accident Transport Conditions. Since the Hypothetical Accident Thermal Transport Conditions are more severe than the Normal Transport Thermal conditions and the package is compliant to the Hypothetical Accident conditions, by direct comparison the package will meet the thermal stresses generated under Normal Transport conditions.

2.6.1.4 Comparison with Allowable Stresses All stresses calculated in Section 2.6.1 are well below strengths for the materials of construction . Further, the Model 865 package was fully tested and passed under Normal Conditions of transport. It is therefore concluded that the Model 865 package will satisfy the performance requirements specified by the regulations.

2 .6 .2 Cold An ambient air temperature of -40°C (-40°F} in still air and shade has no effect on the safety of the package. The safety materials: stainless steel, tungsten, bronze and depleted uranium retain their mechanical properties at this temperature. There are no components of the Model 865 that have increased susceptibility to failure by any mechanism at ambient temperatures of -40°C. Though the tungsten source rod can exhibit brittle tendencies, the reduction in temperature will not adversely affect the relative brittleness of the tungsten rod. Therefore, it is concluded that the Model 865 transport package will withstand the normal transport cold condition.

2.6.3 Reduced External Pressure The authorized contents are special form source capsules that meet a minimum ANSI N43.6-2007 and ISO 2919-2012(E) classification of Class 3 for pressure. This classification is more limiting than the reduced external pressure requirement as it covers 25 kN/m 2 to 2 MN/m 2 .

In addition , on 17 October 1983, a prototype Model 865 package was subjected to a reduced pressure test. The Model 865 package was installed in a pressure chamber.

The pneumatic fittings of the exposure device were sealed. The pressure chamber was

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-20 connected to a vacuum pump. The internal pressure in the chamber was reduced to 6.9 kPa absolute (1 psia). The package was maintained at this reduced pressure for thirty minutes.

At the conclusion of the test, the package was removed from the pressure chamber and examined. There was no evidence of any deformation or damage, no impairment of any design features and the package operated satisfactorily. A shielding efficiency test performed subsequent to the completion of the test demonstrated that this reduced pressure condition did not reduce the shielding efficiency of the package.

Therefore, the reduced external pressure requirements of 3.5 psi in 10 CFR, 8.7 psi (60 kPa) in 49 CFR and IAEA will not adversely affect the package containment.

Reference:

ISO 2919-2012, Radiation Protection - Sealed radioactive sources - General requirements and classification.

2.6.4 Increased External Pressure The authorized contents are special form source capsules that meet a minimum ANSI N43.6-2007 and ISO 2919-2012(E) classification of Class 3 for pressure. This classification is more limiting than the reduced external pressure requirement as it covers 25 kN/m 2 to 2 MN/m 2 .

On 4 October 1983, a prototype Model 865 package was subjected to an external pressure test. A standard Model 865 package was fitted with an adapter attached to the source position indicator and two electrical switches used to indicate the position of the source assembly. The Model 865 was installed in a pressure chamber and the pneumatic fittings of the container were attached to the actuation air supply. The electrical switches were connected to the source assembly position indication system. A supply of argon was connected to the pressure chamber for pressure control. The internal pressure in the chamber was monitored with a pressure gauge.

The pressure in the chamber was increased to 350 kPa (50 psig). At this pressure, the Model 865 container was actuated for 100 complete expose and retract cycles. Upon completion of the sequence, the pressure was increased to 690 kPa (100 psig) and the container was actuated for an additional 100 complete expose and retract cycles. This procedure was repeated, each time increasing the pressure in the chamber by 350 kPa (50 psig) until the pressure reached 2.49 MPa (360 psig). With the container in an external pressure environment of 2.49 MPa (360 psi), it was actuated for a total of 1,010 complete expose and retract cycles. The container remained in this external pressure environment for two hours.

At the conclusion of this test, the container was removed from the pressure chamber and examined. There was no evidence of any deformation or damage and no impairment of any design features. The container operated satisfactorily both during and after the external pressure test. A shielding efficiency test performed subsequent to the completion of the Model 865 test program demonstrated that this external pressure

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-21 condition did not reduce the shielding efficiency of the package.

In the event of failure of the package seal , the source capsule is relied upon to provide the radioactive containment, therefore it is evaluated for its ability to withstand this external pressure. The authorized contents are special form source capsules that meet a minimum ISO 2919-2012 classification of Class 3 for pressure which proves the capsules ability to withstand a pressure of 2 MN/m 2 abs (290 lbtlin 2) . Under failure of the packaging seal, the source capsule would withstand an external pressure of 25 kPa (3.6 psi). Therefore, the increased external pressure requirements of 20 psi in 10 CFR 71 will not adversely affect the package containment.

2.6.5 Vibration On 31 August 1983, a prototype Model 865 package was subjected to a vibration resistance test as prescribed in International Standard ISO 3999-1977, Section 6.3. The test was performed by Associated Testing Laboratories, Inc., Burlington , MA.

The Model 865 was secured to the platform of a vibration machine. A resonant search was conducted with a maximum acceleration of 9.8 m/s2 over the frequency range of 5 Hz to 80 Hz. No resonant frequency was found. The device was then vibrated with a maximum acceleration of 9.8 m/s2 for seventy minutes at each of the following frequencies : 5 Hz, 8 Hz, 12 Hz, 20 Hz, 32 Hz and 80 Hz. At the conclusion of this test the package was removed from the vibration apparatus and examined.

There was no evidence of any deformation or damage and no impairment of any design features . There was no loosening of any fasteners. The package operated satisfactorily after the test. A shielding efficiency test performed subsequent to the completion of the vibration test demonstrated that there was no reduction in shielding efficiency of the package.

Since this test was performed, the Model 865 has been in active service since 1984.

Over this period there has been no evidence of vibration induced failure. It is therefore concluded that the Model 865 package will withstand vibration normally incident to transport.

2.6.6 Water Spray The Model 865 transport package is constructed of water-resistant materials throughout.

Therefore, the water spray test would not reduce the shielding effectiveness or structural integrity of the package.

2.6.7 Free Drop The drop test pad used in the 1.2 m free drop, 9 m drop, and puncture tests consists of a monolithic concrete base 7.4 ft x 7.5 ft x 1.25 ft thick. The approximate weight of the concrete was 9,500 lbs. A 3.9 ft x 4 ft x 1 in thick steel plate was embedded in this concrete slab at the time of its construction . Before and after testing , the drop pad was visually inspected for damage which could have a significant impact on package testing.

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington , Massachusetts Page 2-22 Two Model 865 test packages were subjected to a 1.2 m free drop test as per Test Plan

84. The results of these tests are documented in Test Plan 84 Report and demonstrate that the Model 865 maintains its structural integrity and shielding effectiveness under the Normal Conditions of Transport free drop test. Drop orientation impact locations for the 1.2 m free drop are shown in Figures 2.6.A and 2.6.B. The justification for these orientations is provided in Sections 2.6. 7 .1 through 2.6. 7 .3.

The Model 865 package maintained its structural integrity and shielding effectiveness under the normal transport drop test conditions and the package complies with the requ irements of this section.

2.6.7.1 Top Down Orientation The intent of this orientation was to challenge the shipping cover, actuator cover and cover bolts. If the cover can be removed in the drop test, damage may be caused to the actuator assembly and locking pin. The top down orientation was selected to cause removal or partial removal of the shipping cover and simultaneous failure of the locking pin and actuator assembly. Testing for this orientation (shown in Figure 2.6.A) was performed on test specimen TP84(A).

<J

<J Figure 2.6.A - Model 865 (TP84(A)) 1.2 m Drop Test Orientation Top Down Drop

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-23 Damage to TP84(A) was limited to impact witness marking on the top cover. As damage was minimal, this unit was used for further testing under the hypothetical accident conditions prior to package profiling.

There was no significant change in the radiation profile of the test specimen after all testing including the 1.2 m (4 ft) drop test (See Section 5).

2.6.7.2 Side Drop Orientation The intent of this test orientation was to cause damage to the locking mechanism and package weldment in an attempt to cause the source to be moved from the shielded position. Testing for this orientation (shown in Figure 2.6 .B) was performed on test specimen TP84(8).

<J

<J Figure 2.6.B - Model 865 (TP84(B)) 1.2 m Drop Test Orientation Side Drop Damage to TP84(8) was limited to a slight flattening of the cover at the point of impact. As damage was minimal, this unit was used for further testing under the hypothetical accident conditions prior to package profiling. There was no significant change in the radiation profile of the test specimen after all testing including the 1.2 m (4 ft) drop test (See Section 5).

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-24 2.6.8 Corner Drop This test is not applicable, as the transport package does not transport fissile material, nor is the exterior of the transport package made from either fiberboard or wood.

2.6.9 Compression or Stacking Test Plan 84 Report (Section 2.12) documents that the two test specimens (TP84(A) and TP84(B)) were subjected to a combined compressive load of 649 lbs (294 kg) for a period of 24 hours2.777778e-4 days 0.00667 hours 3.968254e-5 weeks 9.132e-6 months (See Figure 2.6.C). This load exceeded five times the maximum transport package weight of 60 lbs (27 kg). This load was also greater than 13 kPa (2 lb/in2) multiplied by the vertically projected area of the transport package.

Following the test, no damage to the specimens was observed . Radiation profiles performed at the conclusion of the all testing showed no significant increase in radiation levels. The Model 865 package maintained its structural integrity and shielding effectiveness and demonstrated that the packages comply with the requirements of this section.

CQl!lpr~-ivc L-ud600lbs (Y11NIMUM)

Figure 2.6.C - Model 865 Compression Test Orientation 2.6.10 Penetration Test Plan 84 Report (Section 2.12) documents that the two test specimens (TP84(A) and TP84(B)) were subjected to the penetration test. Radiation profiles performed after all testing showed no significant increase in radiation levels. The Model 865 package maintained its structural integrity and shielding effectiveness and demonstrated that the packages comply with the requirements of this section .

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-25 2.6.10.1 Cover Bolt Impact The intent of this orientation was to challenge the shipping cover by trying to damage one of the cover bolts. If the bolt is weakened or broken by the impact of the penetration bar the cover may become easier to displace in the following tests. Specimen TP84(A) was rigidly supported so that the penetration bar could be arranged to impact a bolt in such a way as to induce maximum shear stress in the bolt. Testing for this orientation (shown in Figure 2.6.D) was performed on test specimen TP84(A).

The penetration bar impacted the specimen twice to achieve the intended impact point. Damage to the package was limited to a small witness mark on the bolt. No significant damage occurred to the specimen.

Guide Tube Penetration Bar Impact Point Cover Bolt

<J L\

Figure 2.6.D - Model 865 TP84{A) Penetration Test Orientation

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-26 2.6.10.2 Shell Impact The intent of this orientation was to challenge the target impact to the beam port of the package weldment. Penetration of the package weldment might increase the external dose rate above regulatory limits.

Specimen TP84(8) was placed on its handle and supported in this position so that the beam port faced upwards. Testing for this orientation (shown in Figure 2.6.E) was performed on test specimen TP84(8).

The penetration bar impacted the specimen as intended leaving an indentation at the point of impact. No significant damage occurred to the specimen.

Guide Tube Penetration Bar Impact Point: Beam Port

~~~":: :mm

~~

<]

LI Figure 2.6.E - Model 865 TP84(B) Penetration Test Orientation 2.6.11 Summary Based on the physical tests performed on the Model 865 test packages it is concluded that the Model 865 transport package meets the Normal Conditions of Transport requirements. The post-test radiation profile showed no significant increase in radiation levels.

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-27 The Model 865 was tested for compliance to Type A and Type B requirements with the inclusion of stainless steel spacers surrounding the actuator head retaining bolts. These spacers are included on some units to prevent damage to the bolts during normal field use, however, some units are not fitted with spacers and they are optional for the package.

Although the spacers do provide some protection to the bolts and would minimally strengthen the entire actuator assembly, the use of these spacers would have no effect on the outcome of the previous Type A and Type B testing performed under Test Plan 84. The device's ability to pass, specifically the drop testing, is independent of the sleeves or the bolts.

During testing, the source rod broke at the 0.170 diameter section. This break disconnected the forward part of the source rod containing the source capsule from the section within and attached to the actuator assembly. The forward part of the source rod was still contained within the device by the locking mechanism which is welded to the device housing and not dependent on the integrity of the actuator assembly bolts. The locking mechanism remained undamaged throughout the testing.

Even if the entire actuator assembly sheared off, the source would not move and would remain shielded. As such, any alterations, such as the addition or absence of sleeves over the bolts will not degrade the device's ability to maintain containment and shielding of the source. Final profiling of the device after Type A and Type B testing indicated a maximum dose at 1 meter of 0. 7 mR/hr.

Removal of the actuator assembly and the additional shielding it provides would not substantially increase this dose rate at 1 meter and would still be well below the limit of 1,000 mR/hr specified by the regulations.

2.7 Hypothetical Accident Conditions Sections 2.7.1 through 2.7. 7 summarize evaluations and testing for the hypothetical accident conditions of transport tests. Section 2.7.1 .5 and Table 2.7.A summarize the results of this testing.

Two (2) test specimens were used to conduct the hypothetical accident tests. Testing was performed after the test specimens had undergone the testing in Section 2.6 for Normal Conditions of transport. Justification for drop test orientations and test conditions are contained in Test Plan & Test Plan Report 84 (Section. 2.12).

2.7.1 FreeDrop Justification for all test unit drop orientations are included in Test Plan 84 (Section 2.12).

2.7.1.1 End Drop This orientation was used for Test Specimen TP84(A) and the orientation is shown in Figure 2.7.A . The test specimen impact point was intended to be flat on the top of the lid. This specimen was dropped twice to try and achieve this orientation. It was observed that due to the center of gravity

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-28 on the device, the package tended to rotate slightly during the drop and therefore a flat drop on the top end of the package could not be achieved since the package would naturally rotate during a drop of this height preventing impact onto the flat top of the lid.

Regardless, this unit was dropped twice from a distance of 9 m (30 ft) and it was determined that the combined damage to the unit in the two 9 m (30 ft) drops was more extensive than would occur in a single flat end drop. The cumulative damage caused a local buckling of the shipping cover and slight deformation of two of the cover bolts. There was no other significant damage to the test specimen.

<J

<J Figure 2.7.A - Model 865 (TP84(A)) 9 m Drop Test Orientation - End Drop 2.7.1.2 Side Drop This orientation was used for Test Specimen TP84(B) and the orientation is shown in Figure 2.7.B. Impact was made on the left side of the package in an attempt to break the lock mechanism. The test specimen impacted as intended and caused a slight flattening of the package weldment along the line of impact.

There were no other signs of damage to the specimen.

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-29

<J

<J Figure 2.7.B - Model 865 (TP84(A)) 9 m Drop Test Orientation - Side Drop 2.7.1.3 Corner Drop The corner drop was not specifically performed, however the results of the end drop described in Section 2.7.1.1 indicate that this drop orientation would not have produced greater damage than was seen in specimen TP84(A).

2.7.1.4 Oblique Drops The oblique drop was not performed. In an oblique drop, the energy generated at impact would be distributed across the initial and secondary impact surfaces causing deformation in either the cover/actuator guard or the folded feet of the unit. This type of impact will produce less force at the initial impact location and the force from the secondary impact will cause secondary deformations without contributing to damage which could result in container failure.

Unlike the End and Side drops described in Sections 2. 7 .1.1 and 2. 7 .1.2, an oblique drop is less likely to cause a container failure by the mechanisms identified in Test Plan 84 (Section 2.12.1). These included fracture or penetration of the package weldment, displacement of the shield within the weldment and distortion or fracture of the source, or removal/damage of the shipping cover and simultaneous failure of the locking pin and actuator assembly.

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-30 2.7.1.5 Summary of Results See Table 2.7.A for additional test unit results summary. In all cases, radiation profiles performed at the conclusion of all testing showed no significant increase in radiation levels for the test units and demonstrated that the Model 865 package complies with the requirements of this section.

2.7.2 Crush Not applicable. This package is not used for the Type B transport of normal form radioactive material.

2.7.3 Puncture Justification for all test unit puncture orientations are included in Test Plan 84 Report (Section 2.12). Following the 9 meter (30 foot) free drop, the test specimens were subjected to the puncture test, in accordance with Test Plan 84 (Section 2 .12).

Justification for all test unit puncture orientations are included in Test Plan & Test Plan Report 84 (Section 2.12). Results are summarized in the Sections 2.7.3 .1 and 2.7.3.2.

The puncture bar was a 6 inch diameter x 12 inch long, mild steel solid bar attached to a 12 inch x 12 inch x 1/2 inch thick mild steel base. The bar was attached to the base with a1/4 inch circumferential fillet weld. The puncture bar was attached to the drop test pad steel plate by four stainless steel bolts.

2.7.3.1 Side Puncture Drop Test Specimen TP84(B) was dropped three times onto the puncture billet.

The first drop orientation was onto the beam port. During the first drop the test unit rotated after hitting the legs such that the beam port did not strike the puncture billet. The second drop test was performed to achieve impact onto the beam port and was successful. The test specimen was dropped a third time impacting the lock assembly location side of the 865 with its cover and actuator guard still attached. Following all three drop tests, the device was complete with no broken or missing parts.

2.7.3.2 Oblique Puncture Drop Test Specimen TP84(A) impacted the puncture bar to continue the damage inflicted on the specimen by the 9 m (30 foot) drop test and to continue to challenge the cover bolts (see Figure 2.7 .C). The unit hit as intended, hitting the cover bolt and causing a secondary impact on the shell and leg of the package. This caused some deformation of the leg, but the unit was fully intact after the impact with no broken or missing external parts. Further examination after all testing found the source rod was fractured at the base of the thread which joins the source rod to the actuator assembly, however, the source rod remained secured in the locked position indicating no movement of the source throughout the test sequence. The lock assembly was not damaged and was operational.

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-31 Figure 2. 7 .C - Model 865 (TP84(A)) Puncture Test Orientation Cover Bolts of the Package 2.7.3.3 End Puncture Drop Based on the damage observed on TP84(A) after the end drop orientation , further testing in this orientation was determined to be less likely to produce damage to the package which could result in breach of the weldment or shielding failure. An end drop of the 865 was therefore not performed as the drop orientations described in 2. 7 .3.1 and 2. 7 .3.2 were determined to be most detrimental to evaluation of the package design.

2.7.3.4 Summary of Results See Table 2.7.A for additional test unit results summary. A more detailed summary is given in Test Plan 84 Report (Section 2.12). The package weldments remained intact showing no signs of tearing or fracturing. The shell weldment was only minimally deformed in one specimen and the deformation was insufficient to allow movement of the shield or source.

In all cases, radiation profiles performed at the conclusion of the puncture testing showed no significant increase in radiation levels for the test units and demonstrated that the 865 package complies with the requirements of this section.

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-32 2.7.4 Thermal Compliance for this requirement was assessed (see Sections 2.7.4.1 through 2.7.4.3).

The assessment demonstrates that the thermal test would not be sufficient to weaken the package and cause its failure under the final profile criteria.

Review of the condition of the test specimens after the drop tests suggests the fire test would have no effect on the resulting radiation measurements if the thermal test was performed. This is justified based on the condition of the test specimens after the drop tests and the properties of the materials used to secure and shield the source within the specimens. Without oxidation of the shield the shielding integrity of the package is maintained and it will meet the requirements of 10 CFR 71 .73(c)(4).

Consideration of the principle materials of manufacture and the melting points indicate that the 865 would not fail causing shield integrity to be impaired. Additionally, the structure of the device is such that the degradation of mechanical properties of the materials of construction will not have a detrimental effect on the stability of the device under temperature.

In addition to assessments contained in Section 3.5, calculations were performed to determine the ability of the Model 865 to pass the fire test which are described in the following paragraphs. Further the finite element analysis (FEA) in Section 2.12 concluded there would be no significant thermal stresses generated during the thermal test.

Containment failure cause may only be contemplated by a build-up of pressure within the assemblies that contain a trapped volume of air. The package weldment is such an assembly being predominately a stainless steel welded construction that is maintained air tight by the use of rubber seals. However, the brass source tube is silver soldered in position and at a temperature of 607°C (880 K) the silver solder will melt, along with the seals, and the trapped gases will vent.

2.7.4.1 Projector Weldment under Pressure Loading Induced by the Fire Test Assuming the weldment was assembled at 1 bar atmospheric pressure and 20°c (293 K), the internal gas pressure inside the weldment will be (880 K/293 K)x1 bar= 3 bar just before the venting process begins.

From reference 1, ,I 3.5.1.2 (see Section 2.7.4.2 for reference), the minimum thickness of the cylinder under internal pressure is given by:

e = pDJ(2f + p) where p = design pressure Do = outside diameter of weldment

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-33 f = nominal design stress From reference 2 (see Section 2.7.4.2 for reference) , the 0.1 % proof stress for grade 304 stainless steel at 600°C is 123 N/mm 2 and from reference 1, page 2/40 note (c), f = 0.1 % proof stress/1.35.

Therefore, f = 123 Nmm/1.35 mm

= 91 N/mm 2 (13.2 ksi)

Therefore e = (3 bar - 1 bar) x 10-1 x 127 mm

((2x91 Nmm 2)+(3 bar -1 bar)) x 10-1

= 0.139 mm The nominal thickness of beam port = 1.46 mm, therefore the weldment will not fail due to pressures generated during the thermal test.

2. 7.4.2 Welded End Plates The upper shield collar has the narrowest section of the two end plates. The collar has a through hole directly on its center line. Reference 1, para 3.5.5.2 indicates that where an opening exists, the thickness of the end plate should be reinforced dependent upon plate and hole diameters and hole position.

Consideration of the Model 865 design shows that the collar is reinforced over a much larger diameter than that of the through hole by the actuator base sub-assembly which is welded to the collar. The effect of the central through hole is thus mitigated. In this design, the weakest section occurs where the collar meets the projector weldment and the collar can be considered as a flat end where the following analysis is applicable.

From Reference 1, para 3.5.5.2, the minimum thickness of the end plate is given by:

e = CD J[ii71, where D is the mean diameter of the cylinder weldment p/f = (3 bar - 1 bar) x 10-1 91 Nmm 2

= 0.0022 ecylo = pD/2f

= (3 bar- 1 bar) x 10-1 x (127 mm - 3.048 mm)

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-34 2 x 91 Nmm 2

= 0.136 mm ecyl = 1.46 mm ecyt/ecy10 = 10.7 C = 0.56 from reference 1, Figure 3.5-33.

Thus, e = 0.56 x 123.952 mm x (2 x 10- 1 /91 Nmm 2)

= 3.25 mm < minimum thickness of end plate (i.e. 4.3 mm), therefore the weldment will not fail due to pressures generated during the thermal test.

. 1 .. 4.3 [0.17"] Min.

Figura 2. 7 .D - Section Through Projector Weldment

References:

1. BS 5500:1997 Issue 1, January 1997. Specification for Unfired Fusion welded pressure vessels.

2. High-Temperature Properties of Stainless Steel for Building Structures. Journal of Structural Engineering/April 1998/399. By Y.Sakumoto, T.Nakazato, and A.Matsuzaki.

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-35

2. 7.4.3 Thermal Analysis Summary Damage to the outer containment was not sufficient to increase oxygen ingress to the shield or build up pressure within the assembly (See Sections 2.7.4.1 and 2.7.4.2). Prior to reaching the thermal test temperature, the container will be vented to the atmosphere relieving any internal generation or expansion of gases created by the elevated temperatures.

Because no damage occurred during the Hypothetical Accident Conditions of Transport Tests that could result in oxidation of the DU shield, thermal testing was not performed on any of the 865 test specimens. Specifically, there were no openings in the container that could result in oxidation of the DU shield.

Damage incurred during the drop testing (4 foot, 30 foot and puncture) was minimal, consisting of insignificant deformation of the weldments, actuator block and cover. There were no holes or tears in the cylinder weldment to allow air to circulate through the package. None of the damage significantly increased, or created new, pathways for the ingress of oxygen .

Without the possibility of gross shield oxidation, and subsequent shield degradation, failure under the thermal test conditions would require mechanical degradation of the packages' support structure. The Model 865 support structure is of welded stainless steel construction which will prevent shield movement.

The internal support structure for the test specimen shields was intact and fully functional. The internal support structure consists of the shield, cylinder weldment, and welded endplates. The source was undamaged and secured in the shielded position. The source assembly consists of the source capsule and source rod secured by the actuator assembly.

Since there were no openings in the Model 865 that could result in oxidation of the DU shield. Without oxidation of the shield, the shielding integrity of the cask is maintained and the package will meet the requirements of 10 CFR 71.73(c)(4).

A finite element analysis (FEA) was performed to evaluate the 865's performance under stress of the thermal test since the weldment was not breached during the other destructive pre-testing. A copy of this FEA is included in Section 2.12. Results of this analysis showed the ability of the 865 package to maintain its structural integrity relative to any thermal expansion that occurs during the thermal test. The 865 is determined to pass the requirements of the hypothetical accident thermal event.

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-36

2. 7.4.4 Summary of Pressures and Temperatures See Tables 3.1.A and 3.1.B for summary tables of temperature and maximum pressure related to the Model 865 package. During the thermal test, the brass source tube which is silver soldered in position and the rubber seals will melt at a temperature of approximately 607°C (880 K). At this point any trapped gases in the Model 865 container will be vented to atmosphere. As such , no pressure will build up in the unit under Hypothetical Accident conditions.

2. 7.4.5 Differential Thermal Expansion A FEA was performed to evaluate the 865's performance under stress of the thermal test. A copy of this FEA is included in Section 2.12. Results of this analysis showed the ability of the 865 package to maintain its structural integrity during any expansion caused during the thermal test. As shown in the FEA, (Section 2.12), thermal expansion does not have a significant effect on the Model 865 package.

2. 7.4.6 Stress Calculations As was noted in Sections 2.7.4.5 and the FEA in 2.12, thermal differentials will have no detrimental effect on the package.

2. 7.4. 7 Comparison of Allowable Stresses All stresses calculated in Section 2.7.4 are well below strengths for the materials of construction. Further, the Model 865 package was demonstrated to pass both the Normal and Hypothetical Accident Conditions of transport. It is therefore concluded that the Model 865 package will satisfy the performance requirements specified by the regulations.

2.7 .5 Immersion - Fissile Material Not applicable. This package is not used for transport of Type B quantities of fissile material.

2.7.6 Immersion - All Packages The Model 865 transport package materials are impervious to water and would not be affected by this test. On 7 October 1983, a prototype Model 865 was subjected to a water immersion pressurization test. The Model 865 was fitted with an adapter attached to the source position indicator and two electrical switches used to indicate the source assembly position. The Model 865 was installed in a pressure chamber and the pneumatic fittings of the package were attached to the actuation air supply. The electrical switches were connected to the source assembly position indication system.

The pressure chamber was filled to within 100 mm (4 inches) of the top with sea water.

A supply of argon was connected to the pressure chamber. The internal pressure in the chamber was monitored with a pressure gauge. The pressure in the chamber was increased to 2.49 MPa (360 psi). At this pressure, the package was actuated for a total

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-37 of 1,020 complete expose and retract cycles. The package remained in this pressure environment (equivalent to 244 meters or 800 feet below sea level) for more than two hours.

At the conclusion of the test, the package operated satisfactorily. The package was disassembled and examined. There was no evidence of any water ingress during the test. A shielding efficiency test performed subsequent to the test demonstrated that this water immersion pressure condition did not reduce the shielding efficiency of the package.

The primary containment system in the model 865 package is a special form source, which meets the ISO 2919-2012 requirements for Class 3 pressure testing. Therefore the 865 could withstand the immersion test as Class 3 is in excess of the required 150 kPa (21.7 lb ft/in 2)

The primary containment system in this package is a special form source, which minimally meets the ANSI N43.6 and ISO 2919 requirements for Class 3 pressure testing. Therefore, the Model 865 could withstand the immersion test criteria since the Class 3 pressure test requirements are in excess of the required 150 kPa (21.7 lb ft/in 2).

2.7.7 Deep Water Immersion Test (for Type B Packages Containing More than 10 5 A2)

Not applicable. This package does not transport normal form radioactive material in quantities exceeding 105 A2.

2.7.8 Summary of Damage Table 2.7.A summarizes the results of the Normal Conditions of Transport and Hypothetical Accident testing performed on the Model 865, in the sequence that the tests were completed.

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-38 Table 2.7.A: Summary of Damages During Test Plan 84 Test S ecimen Test Dama e Observed at Test Site TP84(A) sn 51 Compression Units TP84(A) & TP84(B) tested together.

59.8 lb (27.1 kg) Combined Load 649 lbs. No damage.

Penetration Penetration drop repeated twice since Bar first attempt did not impact where intended. Impact Mark. No other visible damage.

4-foot free No significant damage.

drop 30-foot free Drop repeated twice since the unit rotated drop while falling during the first attempt and did not impact where intended. Damage induced caused two of the cover bolts on the impact side to deform slightly and the protective cover to buckle slightly.

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-39 Test S ecimen Test Dama e Observed at Test Site Puncture Witness mark on impact bolt. Secondary drop impact marks on the shell and leg of package. Some deformation of the leg occurred.

Post Test NA

Protective Lid remained securely in Inspection place.

Actuator bolts bent slightly beneath lid but lock was undamaged, source secured.

Source rod fractured at the base of the thread joining the rod to the actuator assembly, but the source remained secured with no significant change in source position.

No significant change in radiation rofi le.

TP80(B) Compression Units TP84(A) & TP84(B) tested together.

60.2 lb (27.3 kg) Combined Load 649 lbs. No damage.

Penetration Impact Mark. No other visible damage.

Bar 4-foot free No significant damage.

drop

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-40 Test S ecimen Test Dama e Observed at Test Site 30-foot free Slight flattening of the package along the drop line of impact.

Puncture The package was dropped twice in this drop orientation since it rotated on the first Orientation 1 attempt and did not impact where intended. Impact mark.

Puncture Impact mark.

drop Orientation 2 Post Drop NA

Protective Lid remained securely in Test place.

Inspection

Some of the fixing bolts and location holes in cover showed indications of strain.

Actuator and hold down bolts distorted

Witness mark on actuator base.

Lock assembly intact and undamaged, source secured.

No change in source position.

No significant change in radiation rofile.

Based on the results and assessments for the test specimens addressed in Test Plan 84 Report (see Section 2.12), it is concluded that the Model 865 transport package maintains structural integrity and shielding effectiveness during Hypothetical Accident Conditions and Normal Conditions of Transport.

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-41 2.8 d .. ')1 of P utornur or Packages with Large Quantities of Radioactivity Not applicable. This package is not used for transport of plutonium or normal form radioactive material. This package is also not used for transport of special form material in quantities~ 3,000 A1.

2.9 Accident Conditions for F1ss1le Material Packages for Air Transport Not Applicable. This package is not used for transport of Type B quantities of fissile material.

2.10 Special Form The Model 865 transport package is designed for use with a special form source capsule contained in the source rod assembly. All special form sources transported in the Model 865 will meet a minimum ANSI N43.6 and ISO 2919 Classification of 3 for pressure testing .

The source capsules transported in this container are approved under a U.S. Department of Transportation special form certification USA/0179/S-96 (see 2.1 2), or other applicable special from certifications. Details of encapsulation as well as chemical and physical form of the radioactive material will comply with specifications approved under the applicable special form certificate.

Based on performance testing, any source capsule that has been tested and achieved special form classification from a Competent Authority and also has achieved an ANSI/ISO Pressure Classification rating of 3 can be safely transported in the Model 865 package so long as the source capsule can be properly inserted into the source rod assembly and properly locates the source capsule within the package radiation shielding. Therefore, any compatible source capsule meeting these criteria should be approved for transport without requirement of amendment to the Type B(U) certification .

2.11 Fuel Rods Not applicable. This package is not used for transport of fuel rods.

2.12 Appendices 2.12 .1 Test Plan 84 Rev 1 (March 1999) 2.12.2 Test Plan 84 Report Minus Appendix A (March 2000) 2.12.3 Model 865 Finite Element Analysis (June 2000) 2.12.4 USDOT Special Form Certificate USA/0179/S-96 Revision 13

Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-42 2.12 .1 Test Plan 84 Rev 1 (March 1999)

SPENT Fl.EL ffiOJECT CFFICE 3014158555 P.02 UNITED STATES NUCLEAR REGULATORY COMMISSION WASMINQTmt, D.C_ 211151il!i ~

March 16, 1999 Mr. William M. McDanlel, Fadlity Manager ASA Technology, QSA Inc.

-40 North Avenue Burlington, MA 01803

Dear Mr. McDaniel:

This is to acknowledge receipt of your plan No. 84, Revision 1, dated March 12, 1999, for testing the Model No. 865 package. This plan was submitted In response to our Confirmatory Action L8ttar No. 97-7-005, datad June 10, 1997.

We have reviewed your teat plan and round it to be acceptable.

If you have any questions regarding this matter, please contact me at (301)-415-8510.

Sincerely,

6_!f!tt;!--

Paclcage Certification Section Spent Fuel Projed. Office Offioe of Nuclear Material Safety and Safeguards cc= 71-9187

I

TEST PLAN NO. 84, Revision 1 TEST TITLE:

MODEL 865 UNDER WATER PROJECTOR PRODUCT MODEL:

MODEL 865 ORIGINATED BY: DATE:

Gravatom (see attached cover sheet)

ENGINEERING APPROVAL* DATE:

'J.. M,9a- 4o/

QUALITY ASSURANCE : DATE:

~ /2 /11/4, 'l'I REGULATORY APPROVAL: DATE: JJ M; 71 COMMENTS:

ENGINEERING APPROVAL: DATE:

QUALITY ASSURANCE APPROVAL: DATE:

REGULATORY APPROVAL: DATE:

SEN,-INEL

TESTPLAN84

..MODEL :865 .

UNDERWATER PROJECTOR March 1999

Issue 1 Prepared For M. TREMBLAY AEAT/QSA Prepared By: Date giii~OLDEN ~~

Checked By: Date G.M.BATES GESL Approved By: Date P.E.CULLUM GESL 28r'.ll*6868!7t0 : 'ON 3NOHd W0.Ltl()t:f~8 : WO;:!.:l

SENTINEL Issue 1_ Test Plan 84 AEAT/QSA March 1999*

Burlington, Massachusetts Page i Contents SECTION 1 INTRODUCTION ;..... ~ .................................................................................... 1 SECTION 2 TRANSPORT PACKAGE DESCRIPTION .................................................... 2 SECTION 3 REGULATORY.COMPLIANCE .................................................................~ .. 5 SECTION 4 DISCUSSION ON SYSTEM FAILURE MODES OF INTEREST ........ ~ .......... 7 4.1 General ...................................................................._................. ;...... ;................................................................ 7 4.2 Nonnal and Accident Conditions ofTransport ..... :................. :........................................................................ 7 SECTION 5 ASSESSMENT OF PACKAGE CONFORMANCE ....................................... 8 5.1 Regulatory Requirements ............. :................................................................................................................... 8 5.1.1 Normal Conditions of Transport Tests (71.43(£))*.................. :...................................................................... 8 5.1.2 Hypothetical Accident Conditions (71.Sl(a)) ............................................................................................... 8 5.2 Test Package Contents .............................................. :...................................................................................... 8 SECTION 6 CONSTRUCTION.AND CONDITION OF TEST SPECIMENS ...................... 9 SECTION 7 MATERIAL AND EQUIPMENT LIST ..........................................................: 10 SECTION 8 TEST PROCEDURE ....... ;.. *...........................-..................................... :........ 11 8.1 General ............................... ;......................... :........ :.. ;.............. :...................................................................... 11 8.2 Roles and Responsibilities ............. .'............................................................................................................... 12 8.3 Test Specimen Preparation and Inspection .................................................................................................... I 3 8.4 Summary of Test Schedule ., ........................................................... ,., ...................................................... ,;*..... *14.

8.5 COMPRESSION TEST (10 CFR 71. 71(C)(9)) .....................................................:... 16 8.5.l Compression Test Set-up ...................................... :.................................................................................... 16 8.5.2 Specimens TP84(A) and TP84(B) Orientation for Compression Test.. .......................: .............................. 17 8.5.3 Compression Test Assessment .............................................. **:******* ............................................................. 18 8.6 PENETRATION TEST (10 CFR 71.71(C)(10)) ........... ;............................................. 18 8.6.1 Penetration Test Set-up ........................................... *...................... :............................................................ 18 8.6.2 Specimen TP84(A) Orientation for Penetration Test ............. ;.............................................................. :...... 19 8.6.3 Specimen TP84(B) Orientation for Penetration Test ....................................................................... :.......... 20 8.6.4 Penetration Test Assessment ................... ,............................. :..................................................................... 21

SENTINEL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page ii 8.7 1.2M (4 FOOT) FREE DROP TEST (10 CFR 71.71(C)(7)) ...................................... 22 8.7.1 1.2m (4 foot) Free Drop Test Set-up ........................................................................................................... 22 8.7.2 Specimen TP84(A) Orientation for 1.2m (4 foot) Free Drop Test... ................................................... ;...... 23 8.7.3 Specimen TP84(B) Orientation for 1.2m (4 foot) Free Drop Test. ............................................................ 24 8.7.4 1.2m (4 foot) Drop Test Assessment ......................................................................................................... 25 8.8 INTERMEDIATE TEST INSPECTION ...................................................................... 25 8.9 9M (30 FOOT) FREE DROP TEST (10 CFR71.73(C)(1)) ...................................., ... 26 8.9.1 9m (30 foot) Free Drop Test'Set-up .............................. :............................................................................. 26 8.9.2 Specimen TP84(A) Orientation for the 9m (30 foot) Drop Test... ............................................................. 27 8.9.3 Specimen TP84(B) Orientation for the 9m (30 foot) Drop Test... ............................................................. 28 8.9.4 9m (30 foot) Free Drop Test Assessment .................................................................................................. 29 8.10 PUNCTURE TEST (10 CFR71.73(C)(3)) ................ ;............................................. 30 8.10.1 Puncture Test Set-up ................................................................................................................................ 30 8.10.2 Specimen TP84(A) Orientation for Puncture Test l ................................................................................. 31 8.10.3 Specimen TP84(B) Orientation for Puncture Test 2 .......... ,..................................................................... 32 8.10.4 Specimen TP84(B) Orientation for Puncture Test 3 ................................................................................ 33 8.10.5 Puncture Test Assessment ......................................................................................................................... 33 8.11 FINAL TEST INSPECTION ................................................................................-.... 34 SECTION 9 WORKSHEETS .. :......................................................................................... 35 APPENDIX A ....................... ~ ........................................................Drawing R86590 Rev.A

SENTINEL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page iii List of Figures Fig. 2.1 Schematic of the Model 865. Underwater Projector Fig. 8.5.2.1 Specimens TP84(A) arid TP84(B) Orientation for the Compression Test Fig. 8.6.2.1 Specimen TP84(A) Orientation for the Penetration Test Fig. 8.6.3.2 Specimen TP84(B) Orientation for the Penetration Test Fig. 8.7.2.1 Specimen TP84(A) Orientation for the l.2m-(4 foot) Drop Test Fig. 8.7.3.1 Specimen TP84(B) Orientation for the 1.2m (4 foot) Free Drop Test Fig. 8.9.2.1 Specimen TP84(A) Orientation for the 9m (30 foot) Drop Test Fig. 8.9.3.1 Specimen TP84(B) Orientation for the 9m (30 foot) Drop Test Fig. 8.10.2.1 Specimen TP84(A) Orientation for Puncture Test 1 Fig. 8.10.3.1 Specimen TP84(B) Orientation for Puncture Test 2 Fig. 8.10.4.1 Specimen TP84(B) Orientation for Puncture ~est 3

SENTINEL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 1 of46 AEAT/QSA Test Plan No. 84 Section 1 Introduction This document describes the mechanical test plan for the Model 865 Projector to meet NRC requirements for Type B(U) packages as described in the Code of Federal Regulations, 10 CPR Part 71, revised as of January 1, 1997. The test plan also covers the criteria stated in the IAEA Regulations for the Safe Transport of Radioactive Material, Safety Series No.6 1985 Edition, (As Amended 1990).

The Model -865 is currently approved for *use under Certificate of Compliance 9187 ..

This document describes the test package specification, testing equipment, testing scenario, justifies the package orientations for the different test specimens and provides test worksheets to record key steps in the testing sequence.

SENTINEL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 2 of46 Section 2 Transport Package Description The Model 865 -Underwater Projector (Figure 2.1) consists of the following major components:

Nickel plated tungsten source rod and capsule holder enclosed in a depleted-uranium shield

1/8 11 thick stainless steel projector weldment

Actuator cylinder ct 1/8" thick stainless steel shipping cover

2 stainless steel housing supports

1/16" thick stainless steel actuator guard

Stainless steel handle

Stainless steel lock assembly The shield assembly consists of a 3/8" nominal outside diameter brass source tube around which is cast the depleted uranium shield. The so~ce tube is closed at one end by a silver soldered brass end cap and sealed against water ingress at the actuator by means of a buna-N rubber O-ring rated for operation at temperatures between -40°F and +125°F. Two machined brass support rings are pressed onto the depleted uranium shield. The brass rings locate into a rabbeted stainless steel plate at each end of the shield. The plates are welded to the ends of a stainless steel cylinder and the whole forms the projector weldment.

The source is manoeuvred by the pneumatically controlled actuator assembly which is fixed to the projector weldment with four 5/16"-18x5" long hex head stainless steel bolts. The source is made fail safe by means of a return spring should the pneumatic control system fail.

The source rod is inserted into the source tube ..Radial clearance between the source tube and rod allows a slip fit to facilitate assembly and free movement of the source rod in operation. A locking pin secures the source rod and source within the shielding when not in use. The lock is key operated and the locking pin is manually activated. The source is contained in a Special Form capsule.

The lock and actuator assemblies are protected by a 1/8" thick stainless steel shipping cover which is fixed to the projector weldment and actuator guard weldment with four M6x12mrn long hexagon head stainless steel bolts.

The depleted-uranium shield provides the primary radiation protection for the Model 865 underwater projector. The shield accomplishes this by limiting the transmission of gamma

SENTINEL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 3 of46 radiationi to a dose rate of 200 mR/hr (2 mSv/hr) at the package surface and limiting the dose rate to 10 mRJhr (0. MSv/hr) at one meter from the surface of the package.

The gross weight of the Model 865 is approximately 59 lbs.

SENTINEL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 4 of46 Source Rod Projector Weldment Handle Depleted Uranium Shield Lower Shield Collar Upper Brass Support Ring Lower Brass Support Ring S/Steel Shi in Cover Pneumatic Actuator "A"

Source Capsule Actuator Weldment (Guard)

CofG 311 SIDE SECTION Lock Assembly Projector Weldment Support Leg 127

.I VIEW "A" FIGURE 2.1: MODEL 865 UNDERWATER PROJECTOR

SENTINEL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 5 of46 Section 3 Regulatory Compliance The purpose of this plan, which was developed in accordance with AEAT/QSA SOP-E005, is to ensure that the Model 865 underwater projector complies with the Type B(U) transport package test requirements of 10 CFR 71 and the IAEA'Safety Series No.6.

The tests for Normal Conditions of Transport (10 CFR 71.71) to be performed are the compression test, penetration test and 1.2m (4 foot}(four foot) free drop test.

The water spray preconditioning of the package is not performed as the Model 865 underwater projector is constructed of waterproof materials throughout. The water spray would not contribute to any degradation in structural integrity.

The Hypothetical Accident Tests (10 CFR 71.73) to be performed are the 9m (30 foot) free drop test and the puncture test.

The crush test (10 CFR 71.73(c)(2)) will not be performed because the radioactive contents are qualified as Special-Form radioactive material.

The thermal test of 10 CFR 71.73(c)(4) has been excluded from the series of tests following an appraisal of the package design and materials used in its production. The main components of the package and their respective melting points ai-e listed below:

Material. Melting Point.

Stainless steel 1390°c 2534°F Depleted uranium 1Bs 0 c 2075°F*

Copper 1083°C 1981°F No components apart from the O-ring seals will degrade at temperatures of 800°C, the thermal test temperature.

The depleted uranium shield is surrounded by a small closed volume of air. Testing of the package under normal and hypothetical accident conditions of transport are not expected to cause a breach of this sealed containment. Subject to damage assessment post hypothetical accident conditions there will be no mechanism for a free supply of oxygen to reach the shield and thereby cause it to bum. During a fire test limited oxidation* only will occur due to the small volume of oxygen present following assembly of the package and melting of the rubber O-rings and silver solder which seals the brass end cap onto the source tube.

The shield is completely encased and secured within a stainless steel weldment. Severe disruption of the weldment must occur for the shield to be displaced with relation to the .

source. In additio11, the source capsule is held witl!in the shield by a rod which is secured mechanically by a plunger lock and a spring located within the actuator. Both mechanisms must be removed to.allow the rod to become free and the source to move out of the shield. As neither of these events are likely, as shown through experimental testing and. analysis, the shield will not move relative to the source during thermal testing.

SENTINEL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 6 of46 In the event that either of these catastrophic events occur during testing, the requirement for a thermal test will be re-assessed.

SENTINEL -Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 7 of46 Section 4 . Discuss.ion o.n.System FaUure Mod~s of Interest 4.1 General The .tests in this plan focus on damaging those components of the package which could cause dispiacenient of the source from it_s stol,"ed position within the depleted uranium shield and which affect the integrity of the shield -itself.

4.2 Normal and Accident Conditions of Tran&port The modes of failure under normal. and accJdent conditions which could lead to .

elevated dose rates include the following:

4.2.1 Fracture or penetrntion of the projector weldment.

4.2.2 Displacement of the shi~ld within the projector weldment and distortion oi fracture of the sourc_e: .

4:2.3 Removal or partiai removal of the shipping cover and simultaneous failure of the*

locking pin and 11ctuator assembly:

The test conditions specified in this Test Plan are intendeffto challenge the. ability .of the Model 865 package with respect to these failure modes.

The orientations shown in Figures 8,7.2.1 and 8.9.2.1 are intended to challenge the shipping cover, actuator cover and cover bolts. If the covers can be removed in the drop test damage may be caused to.. the actuator assembly and locking pin either directly or in the*subsequent puncture test. (failure mode 4.2.2 & 4.2.3}

The orientations shown in.Figures 8.7.3.1 and 8.9.3.1 are intended to challenge the locking ~echanism and projector weldment (failure mode 42.1 & 4.2.3).

Additionally, test4J.g in these orientations will challenge the fixture and position of the shield and source.(failure mode 4.2.2):

SENTINEL 'Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Mass~husetts Page 8 of46

Section 5 Assessment ~of _Package. Conformance 5.1 . Regulatory Requirements 5.1.1 Normal Conditions of Transport Tests (71.43(i))

There should be no loss* or dispersal of radioactiye contents, no significant increase in external sqrface radiation levels and no substantial reduction. in the effectiveness of the. packaging.

5.1.2 Hypothetical Accident Conditic;ms (71.;;t(~))

There should be no es~ape ~f radioa~tive materials greater than A2 in one*we~k and no*

external d,qse rate greater tharrl Rem/hr (10 mSv/hr) at Im from the external surface with tlie maximum radioactive contents which the package is designed to carry.

5.2 Test Package Cc,ntents a

The Model 865 underwater projector is designed to *carry Special Form Source.

Containme_nt of the radioactive source _is tested at manufacture. The source capsule design has been . certified by the US. DOT in accordance. witli the performance requirements for. Special Form as spe¢ified in 49 CPR.

This test plan th~refore does not discuss/;pecify tests of the containmenf of the radioactive source. The pmpose .of. the* tests is to demonstrate that the. shielding remains effective within the limits specified by the regulations. .

A simulated source will be used during testing of the package. The radiation .levels post test-will be ni~nitored by replacing the simulated source with an active source.

SENTINEL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 9 of46 Section 6 Construction and Condition of T~st Specimens Two test specimens built to drawing 86590 *Rev.A and the AEAT/QSA Quality Assurance, Program are to be tested. They are to be designated :fP84(A) and TP84(B). The weight *of the test units will be a minimum of 59 lbs.. .

The Model 865 .is constructed principally from: _Type 304 stainless ste~l, which is not.

susceptible to en:1l?rittlement aHow te111peratures. Additionally, the effect of the difference

. between 38°C (100.4°F) aµd ambient, nominally 20°C (68°F), on the mechanical properties is insignificant. Therefore, the testing will .be perfortned qnder ambient temperature conditions ..

SENTINEL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 10 of46 Section 7 Material and Equipm~nt List The test worksheets in Section 9 list the equipment to the specifications required by .10 CPR 71 and all other necessary equipment and measuring instrum~nts needed to perforn+ the tests.

Additional materials and equipment ma:v be used to facilitate the tests.

SENTJNEL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 11 of46 Section 8 Test Proced.ure 8.1 General * ..

Two units_ are to be tested in the sequence presented below. Each test has been designed to check the* integrity of various components of the package. An assessment of transport integrity of the package can be made, based on the cumulative effect of the .tests performed on the package.

Since these. unit~ may experience* rough* handling prior* to transportation and q.uring normal use; the specimens will be subjected to normal conditions of transport test~ in sequence with the hypothetical accident tests. *

The tests have the.following sequences:

Test sequence 1. (Specimen TP84(A))

Normal Conditions of Transporl: Tests. *

1. Test specimen preparation and inspection

2. -Compression test (10 CFR 71.71(c)(9))

3. Penetration test (10 CFR 71.71(c)(10)

4. 1.2in (4 foot) free drop test(10 CFR. 71.?l(c)(7))

5.

First, intermediate test inspection Hypothetical Accident Conditions Tests.

5. 9m (30 foot) free drop test qo CFR 71.73(c)(l)) *

6. Puncture test {10CFR 71.73(c)(3)) *

7.

Final test inspection and evaluation for thermal test.

SENTINEL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 12 of 46' Test sequence 2. (Specimen TP84(B))

Normal Conditions Tests.

I. Test specimen preparation and inspection

2. Compression test (10 CFR 71.7l(c)(9))

3. Penetration test (10 CFR 71.7l(c)(l0))

4. 1.2m (4 foot) free drop test (10 CFR 7L71(c)(7))

5. First, intermediate test inspection Hypothetical Accident Conditions Tests.

6. 9m (30 foot) free drop test (10 CPR 71.73(c)(l))

7. Puncture test (10 CFR71.73(c)(3))

8. Final test inspection and evaluation for thermal test.

8.2 Roles and Responsibilities The responsibilities of the groups identified in this plan are:

Engineering executes the tests according to the test plan and summarises the test results. Engineering also provides technical input to assist Regulatory Affairs and Quality Assurance as needed.

Regulatory Affairs monitors the tests and reviews test reports for compliance with regulatory requirements.

Quality Assurance oversees test execution and test report generation to assure compliance with the AEAT Quality Assurance Programme.

Engineering, Regulatory Affairs and Quality Assurance are jointly responsible for assessing test and specimen conditions relative to 10 CPR 71.

Quality Control is responsible for measuring and recording test and specimen data throughout the test cycle.

SENTINEL Issue I Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 13 of46 8.3 Test Specimen Preparation and Inspection Use Checklist 1: Specimen Preparation and Inspection.

To prepare the test units:

1. Manufacture two standard Model 865 underwater projectors. Clearly and indelibly mark the packages Test Specimen TP84(A) and TP84(B).

2. Measure and record the weight*of each package.

3. Inspect the test units and documentation to ensure that:

All fabrication and inspection records are documented in accordance with the AEAT Quality Assurance Programme.

The test units comply with the requirements of Drawing R86590, Rev.A.

4. Perform .and record the radiation profile in accordance with AEAT/QSA Work Instruction WI-Q09.

5. Engineering, Regulatory Affairs and Quality Assurance will jointly verify that the test specimens comply with Drawing R86590 Rev. A, and the AEAT/QSA Quality Assurance Programme.

6. Prepare the packages for transport in accordance with the operating manual.

SENTINEL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 14 of46 8.4 Summary of Test Schedule Normal Conditions Para. S ecimen Compression. 71.71(c)(9) TP84(A)

TP84(B)

. ,:\

Penetration 1. 71.7l(c)(10) TP84(A)

Target one cover bolt

)*

Penetration 2. 7l.71(c)(l0) TP84(B)

Target the center of the beam port.

1.2m (4 foot) 71.71(c)(7) TP84(A)

Drop 1.

Target the end of the shipping cover.

1.2m (4 foot) 71.71(c)(7) TP84(B)

Drop 2.

Target the_ lock.

SENTINEL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 15 of46 Accident **

Conditions Parat S eciinen

9rn (30 foot) 71.73(c)(l) TP84(A)

Drop 1.

Target the end of

the shipping cover. ~

9rn (30 foot) 71.73(c)(l) TP84.(B)

~

Drop2.

Target the lock.

. ) </

Puncture .1. 71".73(c)(3) TP84(A)

Target one cover**

bolt.

Puncture 2. 71.73(c)(3) ~P84(B)

Target the beam port.

. Puncture 3 71.73(c)(3) _ TP84(B).

Target the lock.

SENTINEL Issue 1 Test Plan 84 AEAT/QSA- March 1999 Burlington, Massachusetts

Page 16 of 46*
8.5'. Compression Test (10 CFR 71.71(c)(9))
The first test carried out .on both specim~s *is the compression test of 10 CFR
71.7l(c)(9).' This requires a package to be subjected for a *period of 24 hours2.777778e-4 days 0.00667 hours 3.968254e-5 weeks 9.132e-6 months to a compressive load appl~ed uniformly to the top and bottom of the package in the position ii:r which the package would normally be transported. The compressive load must be the. greater .of the followirig:
I. The equivalent of 5 times the weight of the package= 5x59 lbs=,, 295 lbs or IL The equivalent of 13kPa (2 .1bf/in2) multiplied by the vertically projected area of the package= (5"x12.25")x2::, 122.5 lbs. . .
Use Checklist 2:_ Compression Test to ensure that the test sequence is followed. Date and initial all action items and record required data.
NOTE: The worksheets identify steps which must be witnessed by Engineering, Regulato,ry Affairs and Quality Assurance. *
8.5.1 Compression Test Set-up This test requires tha,t the compressiye 'load. is applied to the package in the position in which the package would normally be transported.
To facilitate appllcation of a compressive load, the two specimens are to be placed side by side with a suitable. platf<,mn pla~ed on top of their. handles. As the.
compressive load will be shared between the two specimens it needs to be increased*
by *a factor of two. This will ensure. that -each specimen is subjected to the load required in 10 CPR 71.71(c)(9). **
NOTE: Because each test is designed to add to damage inflicted on a specific component or assembly in' the proceeding test, it is important that each specimen maintain its identity throughout the battery of'tests and that the set-up instructions specific to*:
the specimen _are strictly followed. *
To prepare a specimen f°.r the_compression test:
1. Position specimens accordingto theorientation described below.
2. Record the overall dimensions of the packages pre-test.
SENTINEL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 17 of 46.
3. Position the load platform onto the specimens and apply the test load of the equivalent of at least five times the mass of both protectors combined (greater than 590 lbs).
4.
Record appHed load and photograph the test set-up.
5. Record the overall dimensions of the packages post test.
6. After 24 houts remove the load. Record the damage and take a photographic record.
8.5.2 Specimens TP84(A) and TP84(B) Orientation for Compression Test No specific orientation of the package for transportation is recommended therefore, after examin.atiori of the package shape and method of carrying, the following orientation is considered representative of a probable transportation position ..
Specimens TP84(A) and TP84(B) are placed side by side on their housing supports so.
that their handles are at the top. A support platform is placed across the handles, the load being applied on:top of this frame (figure 8.5.2.1).
Compressive Load 600 lbs Approx.
<]
Figure 8.5.2.1: Specimens TP84(A) an:d TP84(B) Orientation for the Compression Test
SENTINEL Issue 1. Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 18 of46 8.5.3 Compression Test Assessment Upon completion of the test, Engineering, Regulatory Affairs and Quality Assurance team members wHljointly take the following actions:
Review tI:ie test execution to ensure that the test was performed in accordance with 10 CFR 71.71.
Make a preliminary evaluation of each specimen relative to the requirements of 10.
CFR 71.
Assess.the damage to each specimen to decide whether testing is to continue.
8.6 Penetration Test (10 CFR 71.71(c)(10))
The second test carried out on specimen TP84(B) is the .penetration .test as described in 10 CFR 71.71(c)(l0), in which a penetration bar is dropped from a height of Im (40") to impact a specified point on the package. The bar is dropped through a guide tube.
Use Checklist 3: Penetration Test to ensure, that the test sequence is followe~i: Date and initial all action items and record required data.
NOTE: The wo~ksheets identify steps which mustbe witnessed by Engineering, Regulatory Affairs and Quality Assurance.
8.6.1 Penetration Test Set-up There is a specific orientation for the specimen so that the penetration bar is aimed at the component or assembly of interest.
NOTE: Because each test is designed to add to d~mage i;eflicted on a specific component in or assembly the proceeding test, it is. important that each specimen *maintain its identity throughout the battery of tests and that the set-up instructions specific to the specimen are strictly followed.
SENTINEL Issue l' Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 19 of46 To prepare a specimen for the penetration test:
1. Place the specimen on the drop surface and position it according.to the specimen-
. specific. orientation described be_low. *
2. Position the guide tube directly above the specified point of impact, and raise the penetration bar lm (40") abov_e the target. Photograph the test set-up.
3. Measure and record the ambient temperature.
4.
Start the video recorder.
5. Drop the test bar. Record damage and take a photographic record.
8.6.2 Specimen TP84(A) Orientation for Penetration Test The penetration. target for Specimen TP84(A) is a shipping cover bolt. If the bolt is weakened or broken by the impact of the penetration bar the cover may become easier to displace _in the following tests.
SpecimenTP84(A) is rigidly supported-so that the penetration bar can be arranged to impact a bolt in such a way as to induce maximum shear stress in the bolt (figure 8.6.2.1):
Penetration Bar Impact Point: Cover Bolt
<J Ll
<J Ll 4
Figure 8.6.2.1 :Specimen TP84(A) Orientation for*the Penetration Test
SENTINEL Issue 1 Test Plan 84*
AEAT/QSA March 1999 Burlington, Massachusetts Page 20 of46 8.6.3 Specimen TP84(B) Orientation for Penetration Test The_ penetration target for Specimen TP84(B). is the beain port in. _the projector weldment. Penetration of the projector weldment might increase the external dose rate above regulato1y limits.
Specimen TP84(B} is placed on its handle and supported in this position so that the beam port faces upwards as shown. The guide tube and penetration bar are arranged such that the impact point is above the beam port (figure 8.6.3.2) .
. ~~:r:~;
Poootr"'ioo 80< .
II II I 11
.I Impact Point: Beam Port I -------
<J L'.l LI Figure 8.6.3.2:Specimen TP84(B) Orientation for.the Penetration Test
SENTINEL Issue 1 Test Plan 84
AEAT/QSA March f999 Burlington, Massachusetts Page 21 of 46 8.6.4 Penetration Test Assessment Upon completion of the test, Engineering, Regulatory Affairs and Quality Assuranct: team members will jointly take the following actions:
Review the test execution to ensure that the test was performed in accordance with 10 CFR 71.71. .
Make a preliminary evaluation of the* specimen relative to the requirements of 10 CFR 71. . .
Assess the dan:age to the specimen to decide whether testing of that specimen is to continue..
Evaluate the. condition of the specimen* to determine what changes, if a:ny, are necessary in package orientation for *the L2m (4.foot) drop to achieve maximum damage.*
SENTINEL Issue I Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 22 of 46 8.7 1.2m (4 foot)Free Drop Test(10 CFR 71.71(c)(7))
The next Normal Transport Conditions test is the 1.2m (4 foot) (four-foot) drop test as described in 10 CFR 7l.7l(c)(7). This drop compounds any. damage caused by the compression test and the penetration test.
Use Checklist 4: 1.2m (4 foot) Drop Test to-ensure that the test sequence is-followed.
Date and initial all action items and record required data on the worksheet.
NOTE: Th_e worksheet identifies those steps which must be witnessed by Engineering, Regulatory Affairs and Quality Assurance.
8.7.1 1.2m (4 foot) Free Drop Test Set-up In this test, the package is released from a height of 1.2m (4 foot) and* lands on the steel drop surface. There is a specific orientation for the specimen so that the package lands on the component or assembly of interest.
NOTE: Because each test is designed to _add to damage inflicted on a specific*
component or assembly in-the preceding test, it is important that each specimen maintains its ideniity throughout the battery oftests and that the set-up instructions specific to the specimen are strictly followed.
To set up a package for the 1.2m (4 foot) drop test:
1. -Place the specimen on the drop surface arid position it according to the specimen-*
specific orientation described below. Ensure the center of gravity ofth,e package is directly over the impact point. ..
2. The lifting mechanism/system shall be arranged such that the center of gravity marker for each package is as shown in either Figure 8.7.2.1 or Figure 8.7.3.l (unless orientation is changed by assessment).
3. Measure and record the ambient_tempe~ature.
4. Raise the package so that the impact target is 1.2m (4 foot) above the drop surface.
5. Photograph the set-up.
6. Start the video recorder.
SENTINEL Issue I Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 23 of46
7. Drop the package. Record the damage to the package and take a photographic record.
8.7.2 Specimen TP84(A) Orientation for 1.2m (4 foot) Free Drop Test The 1.2m (4 foot) drop test set-up for Specimen TP84(A) is shown in Figure 8.7.2.1.
The object of the drop is to cause deformation or removal of the shipping cover and actuator guard and apply a shear load to the fixing bolts.
The specimen will be dropped in an axial direction onto its top end. It is important to position test specimen TP84(A) so that its center of gravity is directly above the impact point.
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<J Figure 8. 7.2.1 :Specimen TP84(A) Orientation for the 1.2m (4 foot) Drop Test
SENTINEL Issue 1 AEAT/QSA Test Plan 84 Burlington, Massachusetts March 1999 Page 24 of46 8.7.3 Specimen TP84(B) Orientation for 1.2m (4 foot) Free Drop Test The projector will strike the drop surface on its left (lock) side. The object of the test is to cause damage to the locking mechanism and projector weldment which in conjunction with previous tests or following tests may cause the source to be moved from the shielded position.
<J
<J Figure 8.7.3.1:Specimen TP84(B) Orientation for the 1.2m (4 foot) Free Drop Test
SENTINEL Issue I Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 25 of 46 8.7.4 1.2m (4 foot) Drop Test Assessment Upon completion of the test, Engineering, Regulatory Affairs and Quality Assurance team members will jointly take the following actions:
Review the test execution to ensure that the test was performed in accordance with 10 CFR 71.71.
Assess the damage to the specimen.
Evaluate the condition of the specimens to determine whether the testing is to proceed further.
8.8 Intermediate Test Inspection An intermediate test inspection after the 1.2m (4 foot) drop tests will be performed on each specimen.
1. Measure and record any damage to each test specimen.
Engineering, Regulatory Affairs and Quality Assurance team members will make a final assessment of the test specimen and jointly determine whether the specimen meets the requirements of 10 CFR 71.71 set out in section 5, para. 5.1.1.
SENTINEL Issue l Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 26 of 46 8.9 9m (30 foot) Free Drop Test (10 CFR 71.73(c)(1))
The first Hypothetical Accident Test is the 9m (30 foot) free drop test as described in IO CFR 71.73(c)(l).
Use Checklist 5: 9m (30 foot) Drop Test to ensure that the test sequence is followed.
Date and initial all action items, and record required data on the worksheet.
NOTE: The worksheet identifies those steps which must be witnessed by Engineering, Regulatory Affairs and Quality Assurance.
Figure 8.9.2.1 and Figure 8.9.3.1 illustrate the anticipated orientations for the two test units.
8.9.1 9m (30 foot) Free Drop Test Set-up In this test, the package is released from a height of 9m (30 foot) and lands on the steel drop surface. There is a specific orientation for the specimen so that the package lands on the component or assembly of interest.
NOTE: Because each test is designed to add to damage inflicted on a specific component or assembly in the preceding test, it is important that each specimen maintains its identity throughout the battery of tests and that the set-up instructions specific to the specimen are strictly followed.
To set up a package for the 9m (30 foot) drop test:
1. Place each specimen on the drop surface and position it according to the specimen-specific orientation described below.
2. The lifting mechanism/system shall be arranged such that the center of gravity is as shown in Figure 8.9.2.1 or Figure 8.9.3.1. Ensure the center of gravity of the package is directly over the impact point.
3. Raise the package so that the impact target is 9m (30 foot) above the drop surface.
4. Measure and record the ambient temperature.
5. Photograph the set-up.
SENTINEL Issue l Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 27 of 46
6. Start the video recorder.
7. Drop the package.
8. Record the damage to the package and take a photographic record.
8.9.2 Specimen TP84(A) Orientation for the 9m (30 foot) Drop Test Figure 8.9.2.1 shows the package orientation for Specimen TP84(A). The obj ect of the drop is to cause deformation or removal of the shipping cover and actuator guard and apply a shear load to the fixing bolts.
The specimen will be dropped in an axial direction onto its top end. It is important to position test specimen TP84(A) so that its center of gravity is directly above the impact point.
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Figure 8.9.2. l :Specimen TP84(A) Orientation for the 9m (30 foot) Drop Test
SENTINEL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 28 of 46 I
I 8.9.3 Specimen TP84(B) Orientation for the 9m (30 foot) Drop Test I I
I Figure 8.9.3.1 shows the package orientation for Specimen TP84(B). The projector I will strike the drop surface on its left (lock) side. The object of the test is to cause I damage to the locking mechanism which in conjunction with previous tests or I following tests may cause the source to be moved from the shielded position. I
1 I
I I
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<J Figure 8.9.3.1 : Specimen TP84(B) Orientation for the 9m (30 foot) Drop Test
SENTINEL Issue I AEAT/QSA Test Plan 84 March 1999 Burlington, Massachusetts Page 29 of 46 8.9.4 9m (30 foot) Free Drop Test Assessment Upon completion of each test, Engineering, Regulatory Affairs and Quality Assurance team members will jointly take the following actions:
Review the test execution to ensure that each test was performed in accordance with 10 CFR 71.
Make a preliminary evaluation of the specimens relative to the requirements of I 0 CPR 71.
Assess the damage to each specimen to decide whether testing of that specimen is to continue.
Evaluate the condition of each specimen to determine what changes, if any, are necessary in package orientation in the puncture test to achieve maximum damage.
SENTINEL Issue I Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 30 of 46 8.10 Puncture Test (10 CFR 71.73(c)(3))
The 9m (30 foot) free drop test is followed by the puncture test of 10 CFR 71.73(c)(3), in which a package is dropped from a height of lm (40") onto the puncture billet.
The billet is to be bolted to the drop surface used in the drop tests.
Use Checklist 6: Puncture Test to ensure that the test sequence is followed. Date and initial all action items and record required data on the worksheet.
NOTE: The worksheet identifies those steps which must be witnessed by Engineering, Regulatory Affairs and Quality Assurance.
8.10.1 Puncture Test Set-up A specific orientation has been identified for each specimen so that the package lands on the component or assembly of interest. However, the final orientations may be determined based on the assessment of the damage caused by the 9 m (30 foot) drops.
NOTE: Because each test is designed to add to damage inflicted on a specific component or assembly in the preceding test, it is important that each specimen maintain its identity throughout the battery of tests and that the set-up instructions specific to the specimen are strictly followed.
This test uses the 12" high puncture billet. The billet meets the minimum height (8")
required in 10 CFR 71.73(c)(3). The specimen has no projections or overhanging members longer than 12" which could act as impact absorbers, thus allowing the billet to cause the maximum damage to the specimen.
To set up a package for the puncture test:
1. Measure and record the ambient temperature.
2. Position it according to the specimen-specific orientation shown in figures 8.10.2.1, 8.10.3.1. and 8.10.3.2, or as determined following previous testing.
3. Check the alignment of the center of gravity with the targeted point of impact.
4. Raise the package so that there is 1m (40") between the impact point on the package and the top of the puncture billet.
SENTINEL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 31 of 46
5. Photograph the set-up.
6. Start the video recorder.
7. Drop the package.
8. Record the damage to the package and take a photographic record.
Figures 8.10.2.1, 8.10.3.1 and 8.10.3.2 illustrate the puncture test package orientations for Specimens TP84(A) and TP84(B), respectively.
8.10.2 Specimen TP84(A) Orientation for Puncture Test 1 The objective of this drop orientation (Figure 8.10.2.1) is to continue the damage inflicted on the specimen by the 9m (30 foot) drop test and to continue to challenge the cover bolts.
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Figure 8.10.2.1:Specimen TP84(A) Orientation for Puncture Test 1
SENTINEL Issue I Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 32 of 46 8.10.3 Specimen TP84(B) Orientation for Puncture Test 2 The objective of this drop orientation (Figure 8.10.3 .1) is to fracture, penetrate or distort the projector weldment in the vicinity of the beam port. The target is the center of the beam port.
Figure 8.10.3 .1:Specimen TP84(B) Orientation for Puncture Test 2
SENTINEL Issue I Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 33 of 46 8.10.4 Specimen TP84(B) Orientation for Puncture Test 3 The objective of this drop orientation (Figure 8.10.4.1) is to target the lock assembly adding to the damage caused in the 9 m (30 foot) drop.
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Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-43 2.12.2 Test Plan 84 Report Minus Appendix A (March 2000)
QSA -
TEST PLAN NO. 84, Revision 1 TEST PLAN COVER SHEET TEST TITLE:
MODEL 865 UNDERWATER PROJECTOR PRODUCT MODEL:
MODEL 865 ORIGINATED BY: DATE:
Gravatom (see attached cover sheet)
TEST PLAN REVIEW ENGINEERING APPROVAL* DATE:
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QUALITY ASSURANCE APPROVAL: DATE:
~~111. I{- /2 /tftlr 'I 'I REGULATORY APPROVAL: c"'cv DATE: ,J M I r1 COMMENTS:
TEST RESULTS REVIEW ENGIN EERING APPROVAL: -~ / , ~
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QUALITY ASSURANCE APPROVAL: DATE:
24/IIA~ 00 REGULA TORY APPROV Ac . , DATE:
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Test Report 84 AEA Technology QSA, Inc. March 2000 Burlington, MA Page i ofii TABLE OF CONTENTS
1. INTRODUCTION .............................................................................................. 1
2. REGULATORY REQUIREMENTS ................................................................... 1
3. TEST UNIT DESCRIPTION AND CONFORMANCE ........................................ 1
4. NORMAL CONDITIONS OF TRANSPORT TEST RESULTS .......................... 2 4.1 Compression Test ................................................................................................................................ 2 4.2 Penetration Test .................................................................................................................................. 3 4.3 1.2 m (4 foot) Free Drop Test ............................................................................................................. 5 4.4 Intermediate Test Inspection ............................................................................................................. 5
5. ACCIDENT CONDITIONS OF TRANSPORT TEST RES ULTS ....................... 6 5.1 9 m (30 foot) Free Drop Test .............................................................................................................. 6 5.2 Puncture Test ....................................................................................................................................... 9
6. POST TEST DISASSEMBLY AND INSPECTION .......................................... 12 6.1 Test Unit TP84(A) ............................................................................................................................. 12 6.2 Test Unit TP84(B) ............................................................................................................................. 13
7. CONCLUSION ................................................................................................ 14 APPENDIX A.................................................................. CALIBRATION RECORDS APPENDIX B ......................................... MANUFACTURING ROUTE CARDS AND RADIATION PROFILE DATA SHEETS APPENDIX C....................................... TEST CHECKLISTS AND DATA SHEETS T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
Test Report 84 AEA Technology QSA, Inc. March 2000 Burlington, MA Page ii ofii TABLE OF FIGURES Figure 1 :Compression test set-up ..................................................................................... 2 Figure 2:Test specimen TP84(A) penetration test set-up ............................................... 3 Figure 3:Penetration damage to cover bolt on TP84(A) ................................................ 3 Figure 4:Test specimen TP84(B) penetration test set-up ...............................................4 Figure 5:Penetration damage to TP84(B) beam port .................................................... .4 Figure 6:Test specimen TP84(A) 4 foot drop set-up ....................................................... 5 Figure 7:Test specimen TP84(B) drop test set-up ........................................................... 5 Figure 8:Test specimen TP84(A) 30 foot drop set-up for first attempt ........................ 6 Figure 9:Buckling of top cover of TP84(A) after first 30 foot drop attempt ................ 6 Figure 10:Test specimen TP84(A) 30 foot drop set-up for second attempt ...**....**....*.. 7 Figure 11:Damage to TP84(A) following second 30 foot drop attempt ........................ 7 Figure 12:Test specimen TP84(B) 30 foot drop set-up .............................*..................... 8 Figure 13:Puncture test set-up for TP84(A) .................................................................... 9 Figure 14:Puncture test damage to TP84(A) ................................................................... 9 Figure 15:Puncture test set-up for TP84(B) drop 1 ...................................................... 10 Figure 16:Puncture test damage to TP84(B) following drop 1 ............*....................... 10 Figure 17 :Puncture test set-up for TP84(B) drop 2 ...................................................... 11 Figure 18:Puncture test damage to TP84(B) following drop 2 .................................... 11 Figure 19:Damage to TP84(A) actuator assembly ........................................................ 12 Figure 20:Brittle failure of TP84(A) source rod ........................................................... 13 Figure 21:Damage to TP84(B) actuator assembly ........................................................ 13 T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
Test Report 84 AEA Technology QSA, Inc. March2000 Burlington, MA Page 1 of 14
1. INTRODUCTION This report describes the results of the tests performed on two Model 865 test specimens between the 1st and l 71h of March 1999 in support of the application for renewal of the existing Type B(U) certificate of compliance, number 9187. The tests were completed in accordance with Test Plan 84 which is approved by the Nuclear Regulatory Commission (NRC).
2. REGULATORY REQUIREMENTS Test Plan 84 describes the test unit, testing sequence, test unit orientations and testing conditions designated to challenge the Model 865 against the normal conditions of transport requirements of 10 CFR 71.71(c)(7),(9) and (10), and the accident conditions of transport requirements of 10 CFR 71.73(c)(l) and (3). Each test specimen was initially subjected to normal conditions of transport tests followed by accident conditions of transport tests, although this is not a specific requirement of the regulations.
The tests are assessed against the Type B package requirements of 10 CFR 71.5l(a)(l) and (2),
repeated below for reference:
71.51 Additional requirements for Type B packages (a) Except as provided in 71.52, a Type B package, in addition to satisfying the requirements o/ 71.41 through 71 .47, must be designed, constructed, and prepared/or shipment so that under the tests specified in:
(1) Section 71. 71 ("Normal conditions of transport ") , there would be no loss or dispersal of radioactive contents-as demonstrated to a sensitivity of 1U6 A2 per hour, no significant increase in external surface radiation levels, and no substantial reduction in the effectiveness of the packaging; and (2) Section 71. 73 ("Hypothetical accident conditions "), there would be no escape of krypton-85 exceeding 10A 2 in 1 week, no escape of other radioactive material exceeding a total amount A 2 in 1 week, and no external radiation dose rate exceeding 10 mSv/h (1 rem/h) at lm (40 in) from the external surface of the package.
3. TEST UNIT DESCRIPTION AND CONFORMANCE TP84 Checklist 1: Specimen Preparation and Inspection Two Model 865 test units were produced in accordance with Section 8.3 of Test Plan 84. Both test units exceeded the minimum weight of 59 lbs specified in Section 6 of Test Plan 84. The units, described fully in the test plan, are almost entirely constructed of stainless steel with a depleted uranium shield and are not subject to brittle fracture at low temperatures. Further, the temperature difference between ambient and 100°F is insignificant with respect to these materials.
As such, the units were tested at ambient.
T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
Test Report 84 AEA Technology QSA, Inc. March2000 Burlington, MA Page 2 of 14
4. NORMAL CONDITIONS OF TRANSPORT TEST RESULTS 4.1 Compression Test TP84 Equipment list 1: Compression Test Equipment TP84 Checklist 2: Compression Test Test units TP84(A) and TP84(B) were subjected to a combined compression test as per Section 8.5 of Test Plan 84. Checklist 2 records the test data and results. A total of 649 lbs. was applied to the two (2) units. The recorded dimensions, 1-4, were measured from the top of the loading platform to the concrete test surface, and are defined as shown in figure 1.
Figure 1:Compression test set-up No visible damage was reported following the test and the testing sequence was continued.
T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
Test Report 84 AEA Technology QSA, Inc. March2000 Burlington, MA Page 3 of 14 4.2 Penetration Test TP84 Equipment list 2: Penetration Test Equipment TP84 Checklist 3: Penetration Test Test units TP84(A) and TP84(B) were subjected to the penetration tests (bar dropped from 40")
per Section 8.6 of Test Plan 84. Test data and results were recorded on checklist 3 together with one data sheet for each test specimen. It was reported on the data sheet relating to test specimen TP84(A) that the first test had to be repeated because the penetration bar struck the package foot instead of the target cover bolt. Subsequent tests were performed successfully with a guide tube.
The penetration test set-up and results required by Test Plan 84 are shown in the figures below.
Figure 2:Test specimen TP84(A) penetration test set-up Test specimen TP84(A) was securely fixed to a block mounted to the test figure such that the penetration bar was able to strike the cover bolt and exert the maximum stress in the bolt. The bolt head was struck on the second attem t cau in a witness mark as shown in figure 3 below.
Figure 3:Penetration damage to cover bolt on TP84(A)
T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
Test Report 84 AEA Technology QSA, Inc. March 2000 Burlington, MA Page 4 of 14 The second penetration test was intended to challenge the thinner shell around the beam port of the projector weldment. Figure 4 (Specimen TP84(B)) shows that the test was set up such that the penetration bar would strike the center of the beam port causing maximum damage.
Figure 4:Test specimen TP84(B) penetration test set-up Figure 5 shows the indentation caused by the impact of the penetration bar. Both test specimens were impacted as intended and were assessed following the test. The damage was not considered sufficient to warrant suspension of the test sequence .
Figure 5:Penetration damage to TP84(B) beam port T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
Test Report 84 AEA Technology QSA, Inc. Marcb2000 Burlington, MA Page 5 of 14 4.3 1.2 m (4 foot) Free Drop Test TP84 Equipment list 3: 1.2m (4 foot) Drop Equipment List TP84 Checklist 4: 1.2m (4 foot) Free Drop Test units TP84(A) and TP84(B) were subjected to the 1.2m (4 foot) free drop tests per Section 8.7 of Test Plan 84. The drop test orientation for each package is shown in figures 6 and 7 below.
TP84(A) was dropped to impact on the top of the cover protecting the actuator mechanism.
TP84(B) was impacted on the side next to the lock. Both specimens impacted correctly.
Figure 6:Test specimen TP84(A) 4 foot drop test set-up Figure 7:Test specimen TP84(B) 4 foot drop test set-up No significant damage was caused by either of these drops as recorded in the associated test data sheets.
4.4 Intermediate Test Inspection A visual intermediate test inspection was performed and the damage caused in the normal conditions tests was considered negligible (i.e. no profile was performed). It was agreed by Engineering, Regulatory and QA that the hypothetical accident conditions tests would be performed immediately following the normal testing sequence without additional inspections.
T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
Test Report 84 AEA Technology QSA, Inc.
March2000 Burlington, MA Page 6 of 14
5. ACCIDENT CONDITIONS OF TRANSPORT TEST RESULTS 5.1 9 m (30 foot) Free Drop Test TP84 Equipment list 4: 9m (30 foot) Drop Equipment List TP84 Checklist 5: 9m (JO foot) Drop Test units TP84(A) and TP84(B) were subjected to the 9m (30 foot) free drop tests per Section 8.9 of Test Plan 84. Test unit TP84(A) was dropped flat onto the top cover. This drop was difficult due to the center of gravity of the Model 865 tending to rotate the package onto the base from this height. Two attempts were made on this specimen to achieve this flat drop.
Figure 8:Test sp ecimen TP84(A) 30 foot drop set-up for first attempt Figure 8 shows the test set up for the first attempt at the test drop for TP84(A). The unit was observed to rotate and strike the target cover causing local buckling as shown in figure 9. Two of the cover bolts on the impact side were slightly deformed.
Figure 9:Buckling of top cover of TP84(A) after first 30 foot drop attempt T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
Test Report 84 AEA Technology QSA, Inc. March2000 Burlington, MA Page 7 of 14 Because of the oblique impact in the first drop test of TP84(A) it was decided to attempt an additional drop on the same specimen. The set up for the second attempt is shown in figure I 0 below.
Figure 10:Test specimen TP84(A) 30 foot drop set-up for second attempt The second attempt on test specimen TP84(A) resulted in similar rotation and impact orientation to drop one. Consequently, the buckling damage caused by the first drop was exacerbated, however, no further damage was observed to the cover bolts. The post test damage is shown in figure 11.
Figure 11:Damage to TP84(A) following second 30 foot drop attempt Following the second attempt an assessment was done by engineering, regulatory and QA. It was decided that a true flat drop would be extremely difficult to achieve. Furthermore, the cumulative effects of the 30 foot drop tests carried out on test specimen TP84(A) were considered to be worse than a single flat drop as originally planned. o significant damage was evident so the test sequence for TP84(A) was continued.
Test specimen TP84(B) was dropped onto the left side in order to attempt to break the lock assembly. The test set up is shown in figure 12.
T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
Test Report 84 AEA Technology QSA, Inc. March 2000 Burlington, MA Page 8 of 14 Figure 12:Test specimen TP84(B) 30 foot drop set-up The test unit impacted as intended and struck the drop surface flat on the left side causing slight flattening of the unit along the line of impact. The planned test sequence for TP84(B) was continued.
T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
Test Report 84 AEA Technology QSA, Inc. March2000 Burlington, MA Page 9 of 14 5.2 Puncture Test TP84 Equipment list 5: Puncture Test Equipment TP84 Checklist 6: Puncture Test Test units TP84(A) and TP84(B) were subjected to the 4 foot puncture tests as per Section 8.10 of Test Plan 84. The test set up for specimen TP84(A) is shown in figure 13.
Figure 13:Puncture test set-up/or TP84(A)
The target for this test (TP84(A)) was a cover bolt. The bolt head was hit during the primary impact. There were secondary impacts on the shell and leg of the unit. There was some deformation of the leg as shown in figure 14.
Figure 14:Puncture test damage to TP84(A)
T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
Test Report 84 AEA Technology QSA, Inc. March2000 Burlington, MA Page IO of 14 Following the puncture test to TP84(A) the device was still fully intact with no broken or missing parts evident externally.
Specimen TP84(B) was dropped three times onto the puncture billet. Figure 15 shows the set up for the first drop which was intended to target the beam port.
Figure 15:Puncture test set-up for TP84(B) drop 1 The test data sheet describes how in the primary impact the test unit rotated after hitting the legs such that the target beam port did not strike the puncture billet. The test was repeated successfully. The damage to TP84(B) is shown in figure 16.
Figure 16:Puncture test damage to TP84(B) following drop 1 T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
Test Report 84 AEA Technology QSA, Inc. March 2000 Burlington, MA Page 11 of 14 TP84(B) was deemed fit to continue with the testing sequence following puncture drop 1. The test set up for puncture drop 2 is shown in figure 17.
Figure 17:Puncture test set-up/or TP84(B) drop 2 The target for drop 2 was again the lock assembly. The test data sheet indicates that the unit hit the specified point and that no further damage was caused to the device, see figure 18.
Figure I 8:Puncture test damage to TP84(B) following drop 2 Following the puncture tests performed on TP84(B) the device was complete with no broken or missing parts.
T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
Test Report 84 AEA Technology QSA, Inc. March2000 Burlington, MA Page 12 of 14
6. POST TEST DISASSEMBLY AND INSPECTION
6. 1 Test Unit TP84(A)
The test data sheet describes the post-test examination performed on TP84(A). This unit was dropped twice from 30 feet suffering compounded damage. Both covers were removed with all fixing bolts in good condition showing no indication of strain. After removal of the shipping and actuator cover it was evident, by the presence of a witness mark on the inside of the cover, that the actuator cover had struck the actuator assembly, bending the actuator holding down bolts, see figure 19.
Figure 19:Damage to TP84(A) actuator assembly The actuator assembly was removed. The source rod was found to be fractured at the base of the thread which joins the source rod to the actuator assembly, see figure 20. The source rod remained secure in the locked position indicating no movement of the source throughout the test sequence. The lock assembly was not damaged and was operational.
T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
Test Report 84 AEA Technology QSA, Inc. March2000 Burlington, MA Page 13 of 14 Figure 20:Brittle failure of TP84(A) source rod Test unit TP84(A) was reassembled with an active source for final profiling. The profile sheet shows a maximum intensity of 0.5 mR/hr at 1 m from the package surface, well below the limit of 1 R/hr specified by the regulations. Additionally, there was no significant increase in radiation levels anywhere on the device, indicating that the normal condition testing had no effect on those levels.
6.2 Test Unit TP84(B)
The test data sheet describes the post-test examination performed on TP84(B). This unit was subjected to three puncture tests suffering compounded damage. Both the shipping and actuator covers were removed. Some of the fixing bolts and their corresponding location holes in the cover showed indications of strain. After removal of the shipping and actuator covers it was evident that the actuator assembly and hold down bolts were distorted, see fi ure 21 .
Figure 21 :Damage to TP84(B) actuator assembly T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
Test Report 84 AEA Technology QSA, Inc. March 2000 Burlington, MA Page 14 of 14 Figure 21 shows the actuator assembly leaning towards the left side on which the lock is located.
The distortion of the outer casing caused by the 30 foot drop onto this side was minimal, implying that high deceleration forces were exerted on the actuator assembly and shield. The inertia of the actuator assembly, tending to cause rotation of the actuator, may have been responsible for applying tensile loads to the bolts and causing bending of the top plate. A witness mark was visible on the actuator base which may have been due to the rotation of the actuator assembly.
The device was connected to a Pressure Control Unit and the actuator piston was moved to the expose position, coming to rest when the source rod was stopped by the locking pin, indicating that the actuator was still connected to the source rod. The lock assembly was intact and operational. When the device was unlocked the piston operated correctly. The device was then re-locked. The actuator was removed revealing the source rod which was locked in position, implying that the source was secure. Final profiling of TP84(B) shows a peak intensity of 0.7 mR/hr at 1 m from the package surface, well below the limit of 1 R/hr specified by the regulations. Additionally, there was no significant increase in radiation levels anywhere on the device, indicating that the normal condition testing had no effect on those levels.
7. CONCLUSION Both test specimens TP84(A) and TP84(B) have been subjected to the normal and accident tests specified in the approved Test Plan 84. The test results described in this report show that the test specimens conformed to the Type B requirements of 10 CFR 71 .
The projector weldment remained intact showing no signs of tearing or fracture . As such, there was no direct flame path to the depleted uranium shield so oxidation of the shield during a fire test could not occur. In addition, the shell was only minimally deformed in one specimen, and not to an extent as to allow movement of the shield or source which would have resulted in increased radiation levels. Therefore, the assessment by Engineering, Regulatory and QA determined that it was not necessary to perform the thermal test on either specimen.
T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
APPENDIX A CALIBRATION RECORDS T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
APPENDIXB MANUFACTURING ROUTE CARDS AND RADIATION PROFILE DATA SHEETS T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
865 TYPE B TESTING PACKAGE FABRICATION
SUMMARY
SIN 51, 52, 57 The Type B package verification testing is to be performed using existing Model 865 devices. A brief overview of the fabrication history and supporting documentation is provided below.
The Model 865 transport packages were fabricated in 1996. (The basis for the current QA program was implemented in 1992.) The following fabrication records have been compiled for each of the Model 865 test packages.
Overall Assembly:
- Route Card Inspection Record
- Original Profile Data Sheets
- Current Profile Data Sheets
- " A" Subassemblies and Components:
- Weldment Assembly Route Card and Inspection Record
- Housing Weldment Inspection Record and Material Certificate of Conformance DU Shield Inspection Record and Material Certificate of Conformance Source Rod and Capsule Holder Assembly Route Card and Inspection Record Source Rod Inspection Record and Material Certificate of Conformance Source Cap Holder Inspection Record and Material Certificate of Conformance
- Roll Pin Inspection Record, Purchase Order and Material Certificate of Conformance Based on a review of these fabrication records and visual inspection of the packages, it is concluded that the test packages have been fabricated in accordance with the applicable QA Program requirements and that the packages comply with the test plan requirements.
. f' SENJINEL I
~
QCL# :55 :3 ROUTE CARD PAGE 1 Of 2 I s5 /lSrber I l '-~" COMPLETE LOT !U.a TOTAL IXl QTY: Ir' LOT NO: !UA...
SPLIT LOT !U.a RTE. CD. QTY: _l_ SUB-LOT NO: ML.A CM: A PART NUMBER DESCRIPTION !ORAi.JiNG NUMBER !REVISION I.IJORK ORDER NUMBER 86501 'Projector Uelanent D 86501
\.e, Mo7~Pl/o OPER OPERATION 11,Mae.Ull'W) ,,~epu-S:ci ,OIDt>
SEQUENCE DEPARTMENT DESCRIPTION BY DATE STATUS REFERENCE ' COMMENTS Hach & Assy Item 3&4 )J) j; '
1-,,qv.:s . :n, 0010 MS NIA SOP - P024 Upper & lower Shield Support Ring 0020 QC J nspect Items 3&4
-r
I 19 "'o-f Ace D 86501 Verify Tight Fit on Shield 0030 MS Asseri>le 9)(('{_) 5'.4-uJl. NIA SOP*P024 IS""
0040- QC Inspect AOA At":,., SOP*P024 Verify Aligr111ent of Scribe Mark IA.,A
94' 0050 HS \leld PTltl (,AuJ'(, N/A SOP* P024 Item 8 to 2 & Item 6 to 2 t!'.IOS~ NI~ 1 ... 'lt\A f? ......... *,- 1),ro <t-Av114b till A- ~~Po?..\/ wtlJi ~. ~ o.Ji, fl't:8<t ~
- (#
0060 QC Inspect Ueld' nm A. ** 9~ I>< '.t ...--J- D 86501 !ten 8 to..l.,,t. l_,t~6- ~o, z;t~":.,
&M~ /.JI' -f~ , ( JJ.1r:.1.b ~,: APB I
t/AutJ 'if, Au D'6v?OJ I '
0070 , MS Ueld "Pl<~ ,a ' A"~"' N/'- D 86501 ltem 7 to 2 0080 QC Inspect \leld
~ l,iJ.1-t'-
/f Cr.;_ D 86501 Item 7 to 2 0090 HS Hechine )Dt f I, NI'- D U501 Note 7 & 8
,.-~
0100 QC Inspect // SOP*0015 NU(l, 5~,..-1-:" LY/
-* CHECKLIST I
CHECKLJST CHECKLIST SOP-STEP DESCRIPTION INITIALS SOP*STEP t>ESCRIPTION INITIALS SOP*STEP DESCRIPTION INITIAlS
!4IA Install Item 9 Bronze J,K<E Bearing (Note 3)
NIA .030 + /- .005 ,l)"',"
~ - ./')
ENGINEERING:__.'l_f(~,y 1-Gt,tfft((. ~(. REGULATOAY:H ,.__.,\,./..,...2 j, ::>., t'Y\~,,.J1 {,., MATERIALS:*~
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PROOUCTION: / ~J1)... - -:- 1.J,7/"f,t P'6 CUAt I TY ASSURANCi ;- /j. hhh Oh h _ J:t. n.l> qt, V IISSUE NUMBER: 3 9/94 R1
CONFIGURATION DESCRIPTION OF DISPOSITION INDIV/DATE INSP/DATE PART NUMBER DESCRIPTION CH SERIAL/ INITIALS DATE HO. HONCONfORMAIICE LOT 110.
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I If) Q
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. h ff11.)()R 'i rm 1~v;c, :~~,-twc. 86502 Housing \Jeldment A t.~ '1'1b<.-I
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I CHANGE VERIFICATION PART HUMBER DESCRIPTION REV ECO IHDIV!OUAL VER! FIED
<;;../.,._<tJ I ,~~~riz>'r \Q ~.. u,,....""+ lT 2,//..~ NIA- ~-
9/94 R1 Date: \ I '.:?'ef? cqk
SEN11NEL ROUTE CARO
,5 PAGE 2 Of 2 N0:4
~,
jSERlAL NUMBER I
~
QC LOT#_ _ _ COMPLETE LOT TOTAL \JO QTY: LOT SPLIT LOT RTE . CO. QTY: _l SUB*LOT NO: A>ll!'
CH: A i PART NUMBER DESCR IPTION IDRAIIING NUMBER IRtlSION !WORK ORDER NUMBER 86501
PROJECTOR IIELDHENT 0 86501 ~ H (}7{,.f t./0
\
OPER oPERATION OI ,, Ser qp SEQUENCE DEPARTMENT DESCRIPTION BY DATE STATUS REFERENCE COMMENTS 011 0 QA QA Review e,-r .
JJ ~r.9b N/A SOP-0025 0120 IC Stock Room N/A SOP -H002
JH 1:zse~1 I,
CHECKLIST CHECKLIST CHECKLIST SOP- STEP DESCRI PTION INIT IALS SOP-STEP DESCRIPTION INITIALS SOP-STEP DESCRIPTION INIT IALS I
/}
ENGI NEERI NG:
~-. tY~ u "'H n. REGULATORY: 1
-f{._),./,...;:?;-_, *:lJ fY'v~ f.* MATERIALS;,,#~4 J. ~?t..,J!j" PROOUCTJON: /(_u, ~ ~ ? £ QUALITY ASSURANCE:- /',,. -r:,__"':,...'tt./Jhr, J,!J. 'maJ> 9~ IISSUE NIJHBER: 3
__ , Lil Ji/~.,
b\tt llOUTcCARO $CR.IA.':- HUo.cnJic.
I\.M cllS I (AM S0~2,1 6'1 CORrORATION _L_ COMrLCTC LOT TOTAL WO QTY: /1.. LOT HO: N/A 'I rs- ~(;
SrLtTLOT R.TC...CO . QTY : t.\~ SU0 -LOTNO: N/A fM. ..
~
I l"ART NUM0l!R. 1oesc1urTION OR.AWING l'IUMBl!R
~OR.It ORDl!ll
,c. .:;3~71:~Fi,..~(,
86504 Source Rod & Cansule Holder Ass'II ARh'iOt. C ()
oreR Ol"l!llATION sea oerT Dl!SCRll'TIOl'I BY CATI! STATUS lll!PE!Rl!NCI! COMMl!NTS
,1)7 l,J.P:.i*fJ; 0010 ~ Fir,c:r- Pi.,..... NIA 11.0'-,r:,r,,/, n..J;,..,..,. F; ....... Pi-~ -
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0020 ~ First Pc InspectL 1Y, J V 7M;b IJ//_ t,/36504
,.,,e, fYl"VI MC.' u..-r..:- A. "' -1.
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~ er. Final Insoectlon I I , 8~* Ac<- 00P...IY)l5 & ~ ~...IY)1 "\
00.50 QA Review k1{ft* lfZ~11i JJ/4 OOP-q>25 rrff'I Tr <! -1. D- ~,JI- ~
[c,c"P} G, IYA
, Q"P.:.MY\?
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CHl!CCUST CHl!CCLIST Cffl!CltUST sor. JO~*
fN1TIALs 0 1c1umo*
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Threads n.~ ....
eNGINl!l?.RIN(i : ,,a_ ~ '!r/d"-'f'/ REGULATORY: ~ ~1~2.J >>J,AA<, '>'( MATERiALS:~
_.I ~/f1'HIL if/
P'RODUCTIOH : " J f ' ~ ~3/l'i!I q;~LITY ASSURANCE: /t:f~* ~ I Zl:/U~f' ,ssue. Nui.caeR. : 2 R.EVISiON I
NONCONPORMANCBS COHPIOURATIOH OO SCA IP l l OK 0 1HOIIT ION I* 0 1V/0 A Tl I* I I/DA Tl 011c-.1n 1O1< cw , IHI ALA. OT *O . I H1 ll4LI D~ TI g~Cl'i"-3 v~.)
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)23,::.........;~,:?'q;......4-86_504-86504-2 1 _ _--+--------+---+_.e.J;l!.~~"4~=----f Source Rod Source Qin Holder A
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7-o:..:;-re, lw,,Hf',-..1 D- 11 o:_ A 'j( -1.t t - ' yr"" ~' o .: 7' '>t
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\.---i----- ------+----- - ---1-- ----1f---- - - - ---f-- -- -- - - - -- -+--+---1-- - +'- - -
A. 1 "'111 0 *" 1 CA A£V1£W £ 0 DY : . . .:;t_~_~_,7(;p/,-J!-..;....--------
SENJINEL SHIELDING PROFILE AND INSPECTION FORM Model: {o Serial Number: ~, Radionuclide: I 2 Max.Capacity: 2~ 0 Ci I Shield Data I i~ld Heat#: I Mass of Shield: Lbs. Lot#:
~ Initial Profile Source Model : ~' -2 C", Source SN: Activity: Ci Survey Inst. : ~ ~
SN: Date Cal.: Date Due:
Observed ~ction Surface Intensity mR/hr r Adjusted Intensity mR/hr Top 1.61 ~ N/ /J-Right I 2f.... Capac Correction Front Factor :
l,?L Left
~
\ '?_L ~
Rear \.7 '=,. ~
Bottom I.Z~ ~
Inspector : Date : NCR# : ~
Final Prof ile Source Model: 8bS 2D Source SN: Q31l Activity : 231,) Ci Mass of Device: Lbs.
Survey lnst .: AtJ Jt>l")R"?i'"T I
SN: ~~3~2~0:Z Date Cal. : 8'4.1: 18 Date Due : 8~2' Observed Intensity mR/hr Adjusted Intensity mR/hr Surface At Surface Corr. At One Surface Factor Meter At Surface At One Meter Top *.3 23 l,Di 2.5" .3 Right g_s- I, Z.'"- _c; 110 .s Front Left
~.( I. 7t... *b Capacity Correction Factor: l, 03. IJO -~
~T'\ I.Zb . _,:; I CL.I . .<::"
Rear 7/\ 1,2b -~ 11 .~
Bottom Inspector:
1./ 5_ /,i'C:.
A,,/;12 - A'?
.s Date : 8 fr1a.r-ch 'i.. 2 5'~
NCR# : NIA
-~
~
omments:_ _ __ __ _ _ _ ~_ __ _ _ _ _ __ _ _ __ __ _ __ _ _ _ 016-1/1 J"'A mersham QSA
?e.oPtt-£.- oe.t~J~~J.
( F,,A- f"'( /lti ,!> il"V1)v~~ ......... .,_-i~
tl. 1/2 ,,
4 .
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..40 North A venue
.Burlington, MA O 1803 SHIELDING PROFILE AND INSPECTION FORM Model No . : f>k$" Serial No .: -r-j Rad ionuc lide Tr J'l2. Max. Capacity 2':tO Ci INCOMING SHIELD INSPECTION L.c.+'ffL9b\1.,-I Shield 1.0. No. 3$:313- I Source Tube Clear of Obstructions_/112C,. ......,...___ _ __ _
Mass.*of Shield '-If. 4.S' \k, Hot Top Dimensio n Measured ( _., lA'-'-------
H.....
Visual Inspection. ,PW Tube Cut in Fixtu re___.N.,_,(..._
t3,___ _ _ _ ~ -i::---__,...,,.
Inspector Signature ,M?f3r D ate 24":l;,.....,1 96 NCR No._ _.L/'-....
(IJ A:C) .11ei3 'J:Kil1 'f6
~ 2---Zs____
SHIELDING -EFFICIENCY TEST INCOMING SHIELD ASSEMBLY Source Model No. : 8(S20 Source Serial No.: (J). 7 D Activity_,.../'"--~---b____. It, Survey lnstrument:fpt<! U -J.7R Serial No. : 1-13P Date Cat ~At~q & Due_>_:f _1.t_,_/4_,_y_9,...'1__
OBSERVED INTENSITY mR/hr ADJUSTED INTENSITY mR/hr AT SURFACE AT SURFACE COMECTION SURFACE FACTOR TOP C, UY'\ TOP 6 RIGHT 9o t. 7.b CAPACfTY CORAECTION RIGHT /1/ 7 FRONT FACTOR FRONT J t;O 1,71,... It.. '-I LEFT qo ,. ? /,., LEFT l'-17 REAR ~o I .3 REAR J L/ 7 I.ZJ.,
BOTTOM lJO BOTTOM qp--.,
r*,,J l~
3 :5,,L.'( '"
Inspector' s Signature Atr1/2d Date 3 -:Ivl f ft 6 NCR NO "-"J~hl7. .'lf
. .____~ _
i FrNAL DEVICE INSPECTION i Guide Tube Connection Functions Properly Proper Identification/labels Attached ~
Lock Functions Properly Painted Surfaces Not Damaged "_L Selector Ring Functions Properly Fasteners Installed Properly r_
Control Unit Connects Properly Source Travels Properly Source Stores Properly Total Mass of Device ,,,,a Proper Continuity - "E" Machines Only N.)A ti;;. .
Rear Plate Serial No . _.a.; Na.&.f"--'A'---- - - - -
NCR No. : Nit Date lnspected._.__/'IL--"':C....."""""'f~7"--- - - -
SHIELDING EFFICIENCY TEST FINAL DEVllE ASSEMBLY Source Model No.: ~~S~() Source Serial No.: 0 '2.jS"'
Survey lnstrument:A'I\Pt>R::z.1,Serial No.: ~"3"'2-':16 I Date Cal. '- r --, ::z Due lo Ayri \ '17
(
OBSERVED IN'TENSlTY mR/hr ADJUSTED INTENSITY mR/hr AT SURFACE ATONE SURFACE ATONE SURFACE COMECTION METER METER FACTOR TOP £b 1,67 ( .-!l TOP 73 <. 7 RIGHT 'fS 12\, * -~ CN'ACITY COMECTION FACTO!'\
RIGHT 155" .2 FRONT 1\0 l,2(o ,7 FRONT ,~p., /,0 LEFT A< t,?l.. {.. LEFT I 4, (,, -B REAR BOTTOM
~<
Q; 1,26-. .
l,ZS-
. t.
<-5 REAR BOTTOM It.//_
~~
-~
Inspector's Signature._ _ _ _....JIYui
~~~"".::a.,. lqzz._/J ___Oate "2 1 Ft.1> 'l 7
NCR NO ._ _c.H.J.. /LI A_ _ __
I QCL#
(,, 7 0*.;(yJIZll5 a, FJ..17 ROUTE CARD \SERIAL NUMBER I
.~ S"I CK:A COIPLETE LOT:
SPLIT LOT: N/A N/A TOTAL W OTY:
RTE. CO. QTY: ' t.
LOT NO:
SUB-LOT NO:
N/A N/A PART NUHBER TEN 865 DESCRIPT!(lll '
TVJ>e 8 Underwater Projector IDRA\IING NUMBER D86500 /~I-,
'REVISION IMK ORDER NUMBER
.e-F/r lJ7,~?~
OPER OPERATION ~( I "I fJ.> I,' ") } '
SEQUENCE DEPARTMENT l>ESCRIPTIDN BY DATE STATUS REfEAENCE ta4MENTS 0010 Any Assentlle N/A SOP-P022 '
o1A f?_j:.,_ '}J 0020 Assy/or. underwater Leakage SOP-P022 Notify QC
.. &.fuictional Test
-:r .
/J 'J°'1N G17 A-o<.- (Includes 100 PSI Pressure _T estJ 0030 As*y C?iPlet* Assetrbly N/A SOP-P022 rtr7A 1111,;;._ '77
"}~JV 0040 QC '.
Ffnil Jnspectfon 7 ~
SOP-0015 1
. *-.* *\ .
I -
0050 RL ; *~ Verification * .YA- #k N/A N/A ~l"!/:'!f~_7_7 J/k,
' : f~~~b,.,
0060 QC '; . Final Profile Jr!X , ,:;J.17 A~ WJ*Q08
/JC.L#t/i' "? l/
0070 QA QA Review
~ f?h,1olJ? ~/A SOP-0025 1c * . .. ...... Stock- ROCIID . .... - . 0.c .-. - .
<<t fQ' &if 0080 j , , ~- - SOP-"002
. ~ ! .
CilEIXI.IST . CHEC:nlST CHEO::UST SOP-STEP DESCRIPTION .. INITIALS SOP-STEP DESCRIPTiON
. .. . J~_l!l~S SOP-STEP DESCRIPTION . JNrTJALS I
~
\
\
ENGINEERING:~ -~ _
~ ~, MM,'IJ. REGULATORY:-~(
rJ~.L,,..R_g '1_-, ~ / , , MATERIALS:~.v'l~ ~-'
- ..,_ YC PROOUCTION:/(V ~cP,.'}h.,.c..f>(J QUALITY ASSURANCE: . {!,, ~-,..or-, n Jq /)'YJM_ 9 b .,. 1issu~ NUHBER: 3 9/94 Rl
CONF IC\JRATION OESCRlPTlON OF DlSPOSlTlON lNOI V/DATE CH SER IAL/ INI TIALS DATE I!
tNSP/OATE l'>ARY NUNa&a OECCR t PTI ON
NO, NONCONFORHANCE
',_ . I. . .... ~ -* ...~ I I
. i LOT NO.
I .
I
' i I i :865~1 i i ;ll'roJector \lellinent; A IA/ l{l1A 13.X,,.. 77.
' .' ,r; I /(r7A ./(J.~77
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~
I
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i*
CHANGE VE~IFICATION ..
. t , **
f>ART NUMaER OESCRll'>TIOH REV ECO tNOIVIOUAL VERIFIED
- . i r~ F
' f~£o~ : ~ J 11 I
9/94 R_1
CA evlew: _ _ _ _ _ _ _ _ _ _ _ _ __ Date: _ _ _ _ __
i i
P"-"r, e. ~-
SEN'TINEL Otl-,,,lt' nr,r SHIELDING PROFILE AND INSPECTION FORM Model* R(o5' Serial Number* S I Radionuclide* J: R. l'\ 2 Max Capacity
2 L..J.0 Ci I Shie ld Data I Sh1/4ld Heat#: I Mass of Shield: Lbs . Lot II:
~ Initial Profile Source Model: ~ ? c'\ Source SN : Activity : Ci Survey Inst.: ~ S~ N.* Date Cal. : Date Due :
Ob served ~ction Surface Intensity mR/hr C Adjusted Intensity mR/hr Top 1,61 ~ N/A Right I ?_ (,..
~ct;on Front Facto I, 7 l..
~
Left \. 7 L ~
Rear ,, \,7 b ~
Bottom
,. z' ~
Inspector: Date: NCR II : ~
Final Profile Source Model: ~~S ?..b Source SN: e"J',323 Activity : 2.",f6 ,1 Ci Mass of Device: Lbs.
Survey Inst.: ~NI eDB:Z.' I SN: .5.m 32 2 !t~ 2 Date Cal.: ~~+/-'l.!. Date Due : S. ,,,...,..,_f.<J:_
Observed Intensity mR/hr Adjusted Intensity mR/hr Surface At Surface Corr. At One Surface Factor Meter At Surface At One Meter Top zo l,D7 , 2. s2- I 2.
Right ~c' I' '2."- 1-~ /('\(o - ~~
Front
'1rl I 7L He: Capacity Correction I l Z. * .!>
Factor: *Tl Left 75 1.7b .s 'Fl * !:, --
Rear 71'\ 1,2b. ,S- 'b1 IS" Bottom '-I<. l.7C:::. .'-/ S6 . t(
Inspector : 1~'.:?._-< ,1"'1 Date: 1C\ v'V\,,.,.,.. I....9"'1 NCR# : ~ /,ii J OU~* l / 1
'omments:
,,.Amersham QSA
865 TYPE B TESTING PACKAGE FABRICATION
SUMMARY
SIN 51, S2, 57 The Type B package verification testing is to be performed using existing Model 865 devices. A brief overview of the fabrication history and supporting documentation is provided below.
The Model 865 transport packages were fabricated in 1996. (The basis for the current QA program was implemented in 1992.) The following fabrication records have been compiled for each of the Model 865 test packages.
- Overall Assembly:
- Route Card
- Inspection Record Original Profile Data Sheets Current Profile Data Sheets
- "A" Subassemblies and Components:
- Weldment Assembly Route Card and Inspection Record Housing Weldment Inspection Record and Material Certificate of Conformance
- DU Shield Inspection Record and Material Certificate of Conformance Source Rod and Capsule Holder Assembly Route Card and Inspection Record Source Rod Inspection Record and Material Certificate of Conformance Source Cap Holder Inspection Record and Material Certificate of Conformance Roll Pin Inspection Record, Purchase Order and Material Certificate of Conformance Based on a review of these fabrication records and visual inspection of the packages, it is concluded that the test packages have been fabricated in accordance with the applicable QA Program requirements and that the packages comply with the test plan requirements.
SEN1 1NEL SHIELDING PROFILE AND INSPECTION FORM Serial Number* S2.. Radionuclide* J:R.l'\. 2 Max Capacity* 2. L.J(} Ci I Shield Data I l ~ d Heat#: I Mass of Shield: Lbs. Lot#:
~ Initial Profile Source Model: ~ :::> c'\ Source SN: Activity: Ci Survey Inst .: ~N: Date Cal .: Date Due:
Observed ~tion Surface Intensity mR/hr Fae Adjusted Intensity mR/hr Top 1,Dl ~ N/A Right I 2t... ~c,;on Front Factor.
1,?L
~
Left
\
2l>> I'---.__
Rear l.7 C-. ~
Bottom J.Zc:;' ~
Inspector: Date: NCR#: ~
Final Profile Source Model : 8toS 2D Source SN: t"l3iZ3 Activity : g~.~ Ci Mass of Device: Lbs .
I Survey Inst. : dN EDRZ.1 T SN: 5m,322~~Z. Date Cal. : f.l,CJ;:+/-1.e Date Due: 6.. ,"},,,,-J-f_',:.
Observed Intensity mR/hr Adjusted Intensity mR/hr Surface At Surface Corr. At One Surface Factor Meter At Surface At One Meter 1,TJe, ,~.,'fl Top Z5
L./ ~ 2i.
l,Ci ' L/
Right ~ I,? C.. I ~ /OG.
.~*"Vth/r7 Front Capacity Correction 1ofl.~
110 I 71- ' "J I '37 '=i-¢7
7 Factor: *9~
Left 'Jl) ,6 ,/;
1.7b t\ 2-Rear I.,{)
l,2t -~ 1nr, .b Bottom Sb I."? c:: .s 47 .5 Inspector : I I Jo .?.._ __J Date: IC\ 'IV\,,..-,..\--.99 NCR#: q/ IA
,., aIll , 11 I
'omments: _ _ __ _ __ _ __ __ _ _ __ __ _ _ __ __ _ _ _ _ _ _ _~ ~ - - - - -
,..Amersham QSA
, ;;mersna,n co,porauon 40 North A venue I Ii Burlington, M A 0 18 0 3 SHIELDING PROFILE AND INSPECTI ON FORM .
Model No .: f1/4S: Serial No. : _fz_ Rad ionuclide :Ct 1'l 2. M ax . Cap acity Shi eld 1.0. No. 3 ~- 3 \ 3-2... Sou rce Tube Clear of Obstruc t ions..-ne'.?> .-.-....
_ __ _ _ _
M ass -of Shield_ __Li"-L"-..__b"'--<l.,..1.._____Hot Top Dimension Measured { l .........
H...,.!A Visua\ \nspectkm.___[)0'3=-=-- - -- Tuoe Cut in Fb(.t m e_.N...,}f,L-A. .__ _ _ _ __ _ __ _
~ ,'t'- ( u/OC J Inspector Signature_ _ __..,._,#12f2-~=_j};,::::;;... _ _ _ Da t e 26::fuo.t_U NCR No. r 1 /,1: .t..J'-122.
~ I SHIELDING EFFI CIENCY TEST INCOMING SH IELD ASSE MBLY Source Model No .: 6 {,S-20 Source Serial No. : o J.. 7 D Activit y_-"-/_rlO__,,' -& ~ - -
) Survey lnstrument:fd b8* 1 ?I Serial No. : L~ 1 1~ D ate Cal. 7/)/J 1~ Due 5 .J1.,L;1 4- It, OBSERVED INTENSllY mR/hr ADJUSTED INTENSITY mR/hr AT SURFACE AT SURFACE CORRECTION SURf-ACE FACTOR TOP :;- U Y'\ T OP 7 RIGHT io l ,?l-.. CAPACITY CORRECTION RlGHT 13 I FRONT FACTOR
/ IJ1J 1,7 1... FRONT lb 4 LEFT ? () l, ?I,.,. LEFT 14 7.
REAR ~o l.'2.C... REAR
'3 '
e>J rfi BOTTOM ~{) ~ t -'-f BOTTOM
~ 3 SvJ.y 11?
I Inspector' s Signature 1rl71,r Date-3 :::G,17 9,4 NCR NO. l,l/ tt
"* (
FINAL DEVICE INSPECTION Guide Tube Connection Functions Properly Proper Identification/Labels Attached l!fl'!l_
Lock Functions Properly Painted Surfaces Not Damaged ~
Selector Ring Functions Properly Fasteners Installed Properly Jllil:;
Control Unit Connects Properly Proper Continuity - "E" Machines Only .t::DA Source Travels Properly Total Mass of Device ,o, 2 /1>,
Source Stores Properly Rear Plate Serial No._.:..: NCLJIA'-'--- - - --
NCR No .: JJIA I Date lnspected_za___,/i.._....b._2-17--------
SHIELDING EFFICIENCY TEST FINAL DEVICE ASSEMBLY Source Model No.: ~~ '.S<::>.() Source Serial No.: 0'2,95 Activity 117,Q ct'
Survey lnstrument:A~2JTSerial No.: £m,:392,:Wl Date Cal. 6 Z-:-i.:
~1 Due t, ~r:J\'17 _
f'(i!G~~"l.7 1
OBSERVED INTENSITY mR/hr ADJUSTED INTENSITY rnR/hr AT SURFACE ATONE SURFACE ATONE SURFACE CORRECTION METE!\ - MITER FACTOR TOP /,J') 1,67 <.5' TOP S7 (, 7 RIGHT 96 I. 2\:, (.
CAPACrTY CORRECTION RIGHT l~S- .g FACTOR FRONT ~10 i-2ln. .7 FRONT 187 'j LEFT Qr""") 1.?l- ' I- LEFT 1'3.b .g REAR R< -* 1,?t... * .l REAR ',., _c;- ,-~
BOTTOM -'-t~ ,.~- <,5° BOTTOM 7,b (.. 7 Inspector's Signature _ _ _ _..._/1@' ..............
-;1/2--'-i'L9'
= - - -Date eL> fil97 NCR NO. _ _~JJ'+-'_/ tr~---
SEN1 1NEL SHIELDING PROFILE AND INSPECTION FORM Model* 8{o5 Serial Number* S 2. Radionuclide* J:Rlq2 Max Capacity* 2 L.JO Ci I Shield Data I
~ I d Heat#: I Mass of Shield : Lbs . Lot#:
~ Initial Prof ile Source Model:~ c:::' ::>.r-. Source SN: A c tivi ty : Ci Survey Inst.: ~ ...... SN : Date Cal .: Date Due:
Observed ~orrection Surface Intensity mR/hr ctor Adjusted Intensity m R/hr Top Right l,61~
I 7 l...
'---- JJ /Ir
~ Y Correction Front Fact
1,7/,...
left
\ '?_L ~
Rear \. 7 h. ~
Bottom I. 2 S" ~
Inspector: Date: NCR# : ~
Final Prof ile ~
Source Model: ~bS' 2D Source SN: Q~::Zl Activity : 23L, J Ci Mass of Device : Lbs.
Survey lnst. : A '-' Jj) r-. i:l-:>,, SN : ~~3~26!02 Date Cal.: BOt.+-1.8. Date Due : 8~~
Observed Intensi ty mR/ hr Adjusted Intensity mR/hr Surface At Surface Corr . At One Surface Factor Meter At Surface At One Meter Top 2.Z-- 1,0r . :3. Z.8 . ....,
Right 7,:;- I, 2..&-. .s 97 -~-
Front
~5 I. 7l.. .:::: Capaci ty Correct ion
.5 Left
'35' L?'- *S-Factor: Lr o 3
~L/ ._s-Rear l,..._, 1,2h .< 7q_ . _..._......
Bottom
~c ,*.7 C: . S" -~tg, .5 Inspector: /Y)~<kA 0/ Date: g /Y)o.rc b. ~ 2 NCR II : N/,1
{/ 0 16-1/1
~o m m ent s:
,,.Amersham QSA
. *: ... ?eo~~ oe.t~J~~J.
... . 'f;.1. ' . *. ( f,,,lt.- rv "" ,5 ~ ~""?r 'f-,...,h---"'!~
1 *! . . .
_ I ,* "'
. t*-,.
s_.5 ,00*,: *).: _,.
,,, SENJINEL ........
F I i
! OCL# ' t, ~ S '/,.,,.rz,& U ~ j 7 CARD . !SERIAL NUMBER I I 5?,
COHPLETE LOT: N/A TOTAL UC QTY: _ _,.,..*_ _ LOT NO: N/A SPLIT LOT: N/A RTE. CD. OTY: __1____ SUB-LOT NO: N/A CH:A
,\IOI!~ ORDER NUMBER PART NUMBER TEN 865 OPER DESCRIPTION
Type B Underwater Projector OPERATION I DRAIJING NUKBER D86soo / flu.-,
"t. 11 IREVISlON
.e f /F
/.l~vqi IM/J7 l:>P--3b SEQUENCE OEPARTKENT DESCRIPTION BY DATE STATUS REFERENCE COHHENTS 0010 Assy Asseni>le SOP*P022 ltr1A 0020 Assy/QC Underwater Leakage SOP*P022 Notify QC
, & fWlet1ona\ lest 0030 Assy toq>lete Asseirbly N/A SOP-P022 IKrJA 1/1/;r...., 11 0040 nnat Inspection SOP-0015
/. I J.
0050 IL ~_put ~erificatfon _,,VA,- -,,P,k N/A ; I/A 0060 QC final PMf ile \11-008 0070 QA Q Rewlev N/A SOP-0025 0080 Stoel: R~ (~ hl 11 NIA " * , . SOP*H002 .
CHECXLIST CHEtnlST CHECXLIST SOP-STEP DESCRIPTION INITIALS SOP-STEP DESCRIPTION INITIALS SOP-STEP DESCRIPTION INITIALS EN~INEERING: JI, ~ _ .. l:,~ ft!# ?J. REGULATORY: ~( ,..!/LJ?tb .2-i ~ { , , ~TERIALS:~ .CA. ,rr... ~C PROOUCTION:Jf~ ~'J'-7°h-.'P-o QUALITY ASSURANCE: e 1:_... hnh n ,q* rmiv-;_ q b ., Tissue NUMBER: 3 9/94 R1
COIIFIGURATION DESCRIPTION OF DlSPOSlTIOH INOIV/DATE
INSPiOATE PART NUMBER DESCRIPTION ' CH SERIAL/ INITIALS DATE NO. NONCONFORMANCE , LOT NO
I Projector Melcinent A IJ(r1/I Kr1A I
I 11-----1----------1------'----~----4----~1------.f-----------i---+----+-----+----i I 11----..._J~---------+------4-----4--------1,~-----1----------1-----+-----+-----+----i, I
I
' i i
~ -
I CHANGE VERIFICATION
~. ., -~:, ..
PART !!VHBER OESCR IPTION REV ECO INDIVIDUAL VERIFIED I 9/94 R1 QA Re-vi w: _ _ _ _ _ _ _ _ _ _ _ _ __ Date: _ _ _ _ __
SENJINEL ROUTE CARD PAGE t OF 2
I s~ria l NUllb<?r I ocu='iJDS ~
I '5"~
1~<<:rW * *COMPLE TE LOT ill TOTAL 110 QTY:
, I~ LOT NO: !IL.A_ f CM: A SPLIT LOT 1iUi RTE. CD. OTY: SUB*LOT NO: ill
. I t
PART NUMBER DESCRIP TI ON IORA\II NG NUMBE R !REVI SION !\IORK ORDER NUMBER 86501 Projector Weldment 0 !6501 G M.oll,8va OPER OPERATION SEQUENCE DEPARTMENT 0010 HS Mach DE SCR IPTI ON
&Assy Item 3&4 BY l...)I
i ,
DATE
") [,./f
'l /..
STATUS N/ ~
REFERENCE SOP
P024 Upper COMMENTS
& lower Shield Suppor t Ring 0020 QC Inspec t I tems 3&4 u 5,._,,,,-u O 86501 Verify Tight Fi t on Shield
~
I
~
0030 HS Asseri>l e 'ft. N/A SOP*P024
'PR~ J Oc,-
0040 QC Inspect I SOP*P024 Verify Aligrvnent of Scribe Mark
/JliP. /), 9£. VE' 0050 lleld ()~r'ft N/A SOP* P024 I t em 8 to 2 & Item 6 to 2 HS
.Ptt: ft I 0060 QC Inspect lleld 2 I> 86501 l ten 8 to 2 & Item 6 to 2
~ h,,,,+. J/. Ac/"
0070 MS lleld P f?T!> i ()cT t/C:, ti/A D 86501 Item 7 to 2 0080 QC Inspect Ueld D 86501 Item 7 to 2
/fl?/?) ~?{. ALI'° 0090 MS Mach ine ,!) T \'". v~, N/A D 86501 Note 7 & 8 7 .f,
--:; .-,Loe,1"5(,,
&Q.~ ~ ZD L.J 0100 QC Inspect 12 n ,ACC. SOP*Q015
,IIVZ/3 CHECKLI ST Dd"'J" *-*
CHECKLIST CHEtKL IST SOP
STEP DESCR IPTI ON INlT IALS SOP*STEP DESCRIPTION INITIALS SOP*STEP DESCRIPT ION INITI ALS N/A Install Item 9 Bronze ~~ '
Beari ng (Note 3)
N/A .030 + /* .005 ~,
ENGINEERING: _,Jc{/fl.--... ?~ /J--./fl f J, RE GULAT ORY: ~(:..<_ -~__,t?,b ~ , J.J At MATERIALS: l,l Ul~ 11 :>~'\ ~
1, s suE NUMB ER: 4 ~
V PRODUCT ION : ) ~~fi>_
- j..J./Ltz...1/1. QUALi H ASSURANCE: /I -:fun-,... on,.._
1 '> ~ O J..J. r. C\ t, r
u 9/94 R1
=-
DESCRIPTION Of 01 SPOSIT ION INOIV/OATE lNSP/DATE PART NUMBER DESCRIPTlOH CM SERIAL/ INITIALS DATE HO . NOHCOHFORHANCE LOT NO.
a /
(D Of'!R. ~e:-.~ di,...,,,.., 86502 Housing Wel~nt A 9'~-:Z l ">* {
,~1?7*/
m'B 1-c,c..-. "fj t\.-. . t. 27.D J:::t L~i 86501
3 DU Sh ield A H1. :S.1'3/J-~ V/\1'3 J-ocf q&
k..+uli~ I L.c.clJ..S~ ..J. 20 ~
Don,,,,c..,'fX- . Z. 2 7
-/vi~ -
N cit! Gt:I..J,..7f\ '-f I \
VO I (')- ,,,,., <~iu tit) ,; ri.M ft .
/1.~ ,c; ()cfH CHANGE VERIFICATION PART NUMBER DESCRIPTION REV ECO INDIVIDUAL VERIFIED I
, 9/94 RI Date: I b QC,1 qp
SEN11NEL . ..
QC LOT#~ COMPLETE LOT SPLIT LOT i l~r~
ROUTE CARO TOTAL 110 QTY:
RTE . CO. QTY: l
,s LOT NO:
PAGE 2 OF 2 J).,-
SUB - LOT NO :
~h
!SERIAL NUMBER I ..f~
I CM: A PART NUMBER DESCRIPTION IDRA\IING NUMBER !REVISION !\/ORK ORDER NUMBER 86501 PROJECTOR \IELDMENT D 86501 G /'1d7tKLft, OPER OPERATION SEQUENCE DEPARTMENT DESCRIPTION BY DATE STATUS REFERENCE COMMENTS 0110 OA SOP*Q025 QA Review e:( ,~ Oc:rqr, N/A 0120 IC Stock Room .:rH- /"f!,bC-T1tb N/A SOP
H002 CHECKLIST CHECKLIST CHECKLIST SOP-STEP DcSCRlPllON INITIALS SOP-STEP DESCRIPTION INITIALS SOP*STEP DESCRIPTION INITIALS
,., /7 ENGINEERING: ~ - 4 } " ~ ?l.lf-t'f)f> REGULATORY: ~ ( ..),d~,/4 ;).,:ii) q ,GL, MATERIALS: ()_ , ct);;,. a:? Av'\~(.
PRODUCTION: IC.ft) ~ ~- v- -
i.~ ,d_ C .tvlALITY ASSURANCE:
~ (!. +-ehJ\.11"1 h :, !::,_
IL.J...d Gt i. j Issue NUMBER: 4v V
'1c:, ,1 C *it... *)
IAMt!RS((AM blit ltOUTt! CARO SCRIAL HUMIIJI(.
S0~2,1 6'1 CORrORATION _L COMtLCTC LOT TOTAL WO QTY: 1,5" I.OTHO: N/A tf 5- ,; <j St LIT LOT RTI!.. CO. QTY: I..\ c:; SUD-LOT NO: N/A n.( A I sc
!"ART NUM0CR 101!.SCRlrTION ORAWIHG NUMBER REV' L,:.OllC OllOl!:R 86504 _ _ Source Rod & Can=le Holder Ass" AN-,~ . c:i 7{;. s-*1, <)
orcll Ol"EllATION /;(.
seo oerr O1!:SCllll'"rlON BY OATC STATUS lll!:Pl!:Rl!NCI!: COMMENTS li ~ -*~(,
/)1 NJ:i*1t, 0010 MC:: F;,......,- Pi-~ IJJA APJ-,<;N,. i 0.. H *-- Fi rc;t- Pi oro t-n * "f'
/ :---....
0020 ~ First Pc 1nspectL 1yJ V 1M"fb :/),N _ Mb~
Ml Al/A .
nn'1n UC u..-1.i~ JI. "'.. _ ... ~qv.
0040 Final Insoection i ~! £>.&5r A<<:.L 0:
- ~..JY)15&~ ~-Nl1 l 0050 Qi\ Review kl\1T lft~t?. Ptfl \
&P-(p25 rvv.r. Tr. ~t-nrl, o~ l,>>- cy -*
ot: *iG,
. ~- ... -.-.--:
1.VA Processing CHl!CCUST CHl!:CCLIST CHl!CCUST JOf"* so,- &or-fMfnA** lfffflAU b * ...c..,rno* n r oasc,ttl"TION JT r tMtTIALS o**ClltrTtON I
,f 'f Note 3 - Drill LT~-
. n..---
Threads ~
~
fl. .£. ~~I~~ -iy ,~p,9/l,?'/
1!:NGIHl!:l?lllHC: A 3-J(i'-'r'/ lll!:GUI.ATOllY : :>-:>-},'-A<, MATERiALS:~ -
rROQUCTION : 7 f ~ ~ 3 ; 9 ~ / ~~l.lTY ASSU~ANCI?: /t:l~~ - i!l:IW~j' I,ssuE NUMBER: 2 REVISiOH I
/10/'ICO/'i!ORMAHCSS COHPIOVRATIOH HO . ODjCJ'-1"1101'f OIJPOIITIO" t* l)IV/OATI IMH/OAT I fld,T PfUM'lll OIIC~ll'TION CW* IHIA~i',.OT *o . ll'lllALI O~TI
\ b MM 'Jl. 7S r,.,t ... 1141> t>~/'\~'- A.-1 << 7i:v:Jl32:f 86504-1 Source Rod A ci!L l'\C C"
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I
APPENDIXC TEST CHECKLISTS AND DATA SHEETS T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
AEAT/QSA February I999 Burlington, Massachusetts Page 36 of47 Checklist 1: Specimen Preparation and Inspection Step TP84(A) TP84(B)
I
1. Total package weight (lb.).
59.B lb
2. Are all fabrication and inspection records documented in accordance with the AEAT Q.A. Programme?
3. Does the test unit comply with the requirements of Drawing R86590 Rev. A. 16@ 2i1, ye$@_26?'
4. Has the radiation profile been recorded in 1e.@~s "fe.7@ -z.s accordance with AEAT/QSA Work J:tlJ Fe..B Instruments WI-Q09? r,, 9,
5. Is the package prepared for transport?
1/~ ~
Steps 1 through 5 witnessed and verified by; Print Name Signature Date Engineering:
Regulatory Affairs:
Q.A.:
(j)r~ ~..e tJ '--* f),
d vc.~~,-~
P- o.:.,J e ca,,c).. s a, i]J roS,,,,J..v .:..,,.,1.d ,.,. J p.o.<J Cl $ ! ~ ~ c;;bv t.Le- lo~e ,o1/2 .
hJ ~ Ci51l$~d w, 1h frv~pLHl./t\ .JoJ- assess,n t 1-11.or'lf v111 ~
AEAT/QSA February 1999 Burlington, Massachusetts Page 37 of 47 Equipment List 1: Compression Test Equipment Description Enter the Model and Attach Inspection Serial Number Report or Calibration Certificate Compression Test Loading Plate.
Test Weights.
Test Surface.
Record any additional tools used to facilitate the test and attach the appropriate inspection report or calibration certificate Print Name Date
AEAT/QSA February 1999 Burlington, Massachusetts Page 38 of47 Checklist 2: Compression Test Test Location:
1J u ~ l ,o11 r lo~ , ~ ~
Step Specimen TP84(A) Specimen TP84(B)
I. Position the specimens as shown in the referenced Figure 8.5.2. l
,figure .
2. Record the ambient temperature:
)/a C
3. Record applied load.
4. Note the instrument used for the temperature measurement:
5. Measure and record each specimens overall dimensions pre-test.
6. Place the weights onto the loading platfonn and leave for 24 hours2.777778e-4 days 0.00667 hours 3.968254e-5 weeks 9.132e-6 months .
7. Mea_sure and record each specimens overall dimensions post-test.
8. Record damage to the test specimen on a separate sheet and attach.
Test Witnessed by: Signature: Print Name Date Regulatory
) /1 (;.'{ f .
Quality Assuranc
&~ ({/f',\fJf5SL(A {t5+, /at{d IA..1 i ~
i:;i.s la11 tied* l/J?1 I ; fa_ (b 'I (
c:r- 1 J.,,
11 i ~
b..,.,, _, ;:
/
SENTINEL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 39 of46 Equipment List 2: Penetration Test Equipment Description Enter the Model and Attach Inspection Serial Number Report or Calibration Certificate Penetration Bar.
~ SEE Atff'lc.+l cazr r,0129 REVB Drop Surface.
, 1012 '2.. l?c'I/B, Record any additional tools used to facilitate the test and attach the appropriate inspection report or calibration certificate OMthA 7H[Rft10M6Tl!ER... l\'?OOft- Hrt *-Z.. I HH 2/ l=N&-/2- Et-{&- lZ..
l1-*U~21VlOC0L,\)c...G 5 T'- G- -K-Zf)*~ ~I Signature Print Name Date
}:)GJ.).JL~
Completed by:
Checked by:
'1),-.ve" A..J~< S 11 M~f'" 9,
~""""1 w. H 7'tJlllf'/ kl . /{urlt. l7Hl41' "1'
SENTINEL Issue I Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 40 of 46 Checklist 3: Penetration Test Test Location: (i, , - - ~ .NI A-Step Specimen TP84'8) A Specimen TP84(B) s SI s:~ s:L I. Position the specimen as shown in the referenced figure. Figure 8.6.2.1
2. Inspect the orientation set-up and verify the bar height.
3. Record the ambient temperature: a II c... 150 e
4. Note the instrument used for the temperature measurement:
5. Start the video recorder.
6. Release the penetration bar. Check to ensure that the penetration bar hit the specified area.
7. Record damage to the test specimen on a separate sheet and attach.
8. Engineering, Regulatory Affairs and Quality Assurance ma lim inary assessment o IO CFR 71 .
Record the assessment on a separate sheet and attach. Determine what changes, if any, are necessary in package orientation for the 1.2m (4 foot) drop test to achieve maximum damage.
Test witnessed by: Signature: Print Name Date Quality Assurance:
7),J,J,
AEAT/QSA February 1999 Burlington, Massachusetts Test Plan 84 Data Sheet Test Unit ModeVSerial No.: ~t~ SAJ SJ Specimen/Test: 1P31/ (A )/ftJ;Jerl(,lfr/tJN 7cS, Test Date: m MM. 'It'?_ !_est Time: / /: ~ ,Ir'/ Test Plan Step No. :
Describe drop orientation and drop height:
1'~1t~,:f;-;. ~ e Atl- J,tt,~ P~"1 fl-pt (),-/ n, u-,t/'fL- &,.-T - <<~ dltt.,~,rv Pll/L f , ~ d.l. :J. /
Describe impact {location, rotation, etc.):
p~",._,,,, '3,ht. w-h iJ,,_,.,/1;,<1'0 ~ ~.r. -/P IJ4,P ,-,, ssd>tJ uJ"'ch'- &,1.,T
~,,..,A"])IJ.,-,/J w-9-s MFII'*- w,'f'H fi#411'11 n,,~;:;, il,.7i)n ,F <,1,110li'Tl-'IJ~- ~? 19-dJ,.,,r:
~/Jlhr 1'11 "'.J'; BIM. .-vM ~s $' '* ~ 1 ,- UtlJk;r ('1,uvr - Jj/J./f. HIT, ] ) , ~~ 'r "'"""""
u;i,tc,,-n_ ~1,,T.
DSfcribe on-site inspection (damage, broken parts, etc.):
~1~~ M,ta.H t;?A/ 8.>>T 1-/~. ~If/() tJ'n-lPL /Mt'1l1~&-
11!-()A..,,I- w, r-,.,,;m ~ , - , "IV I- 11'6 ¥ J:n/Jtk-Jr fl~-?°' -A/,1 dn.tn- tf.J lh-1;1#-r/P,r On-site assessment:
'4?~ l#i,,.,r WLT1-t ~ ~ T Sl?,Jutl)vt::& ~ i)JCJ~g/VJ l~/2.he-~egulatory: l7M41L'/'f ,
1sassembly and inspection:
.If/A-Describe any change in source position:
/1/#
Describe results of radiography:
vi+
Completed by: Date:
AEAT/QSA February 1999 Burlington, Massachusetts Test Plan 84 Data Sheet Test Unit ModeVSerial No.: S SAJ 52 Specimen/fest: 7P PBJi::71UT?a,J 'JF5r Test Date:/ n#"l Test Time: I/ : ql-hr? Test Plan Step No.:
Describe drop orientation and drop height:
- Pe-~,,.,,~ f&ht..- }14J/J v/\/ 8~"')'}-n PJ~ /7&,M "'~ p-**
-M;7ll: 6'41"'<, n,, 4 r u ~ TD ~~- >Mlh/ltr c?~Arl p~r - 8vi7'rlr? c:N~
7>t~c-d' " A,d~? ~ ~.vr - iJ,9A. SY-" ;'/-4,vc~MIi-er P111N?"'
Describe impact (location, rotation, etc.):
XrtNJer J),ll..t'-...,;,-~ '-( Q/V 8~19-M PhLr !=tfYt-- Pi;,. B. ~ 3. .l..
Describe on-site inspection (damage, broken parts, etc.):
Z v ~".v t>r- Sli'l>M p;.,ir "'7:P,,,l'Aer PV(/VT - N'4> 0 71-1,1>-t.
Oltr>A-oeT On-site assessment:
C (j/V'"TI /t/t,(e..,, W.:I:TI-/ p"~ ,eg- &'~ "'~ ~ - ~ L )
O#-tt}M"l9--711)/VS .
jl//J-Describe any change in source position:
,flt Describe results of radiography

Completed by: Date: /? M A, -,q
SENTINEL Issue I Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 41 of 46 Equipment List 3: 1.2m (4 foot) Drop Equipment List Description Enter the Model and Attach Inspection Serial Number Report or Calibration Certificate Drop Surface.
I 10/22. kVB ~ ~ ~"'~
Record any additional tools used to facilitate the test and attach the appropriate inspection report or calibration certificate
$EE ~m,c...
0/Yll:&A 7 i i ~ IIH 21 EJ/Cr l:,Nu--1'2. (~ C.&ta:r O~t&A 1~E:RMClooDL£' S Tc. - &G- -f(-20-3', ~
Signature Print Name Date Completed by:(
\)~. ,n ( .~ ~ live ArJ,-)1!> \i MM"~
Verified by:
~ ... _,.
~A} . ,d.....--,.
.. ~ 7::>(,;,,,~, "'* /(u,lz. /7 /1161' '19
SENTINEL Issue I Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 42 of46 Checklist 4: 1.2m (4 foot) Free Drop Test Location C .,~~ ,h'A-Step Specimen TP84(A) Specimen TP84(B)
SIii SI SN SJ..
I. Measure and record the ambient temperature ( 0 C).
0
/3 c:...
2. Note the instrument used:
3. Attach the test specimen to the release mechanism.
4. Lift and orientate the test specimen as shown in the Figure 8.7.3. l referenced figure for the specimen.
5. Inspect the orientation set-up and verify the drop height.
6. Photograph the set-up in at least two perpendicular planes.
7. Begin video recording of the test so that impact is recorded .
8. Release the test specimen.
9. Record the damage to the test specimen on a separate sheet and attach.
I0. Engineering, Regulatory Affairs and Quality Assurance m reliminary assessment ive to IO CFR
71. Record the assessment on a separate sheet and attach. Determine what changes, if any, are necessary in package orientation for the 9m (30 foot) free drop test to achieve maximum damage.
Test witnessed by: Signature Print Name Date Quality Assurance:
-;x).J,,I. ~
AEAT/QSA February 1999 Burlington, Massachusetts Test Plan 84 Data Sheet Describe drop orientation and drop height:
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~~ HA, "" f,,I) - 14,., ,r 11-fov P1:1-u I)/',, si oe-Describe on-site inspection (damage, broken parts, etc.):
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- /Vp 0AM~6&-
On-site assessment:
4,,.;ru,/l,;tl{ _lltr( r-H p, mv,,,'££) ~ T Slrae4r,v~- ,t,.,o {)f</~N'5 Engineering:
Describe any Describe any change in source position:
//A Describe results of radiography:
t1/J Completed by

Date: I?
AEAT/QSA February 1999 Burlington, Massachusetts Test Plan 84 Data Sheet Test Unit Model/Serial No.: S, '52 Specimen/fest: TP8 Test ~ate:/ M_ "? Test Time: / .2.. i ~ Test Plan Step No. :
Describe drop orientation and drop height:
Describe impact (location, rotation, etc.):
~
Des~ribe on-si:e inspection (damage, broken parts, etc.):
5,1,ur t,.ffi'lvlN't!i c."vM Hr i'tJ1N'r ;Jj: ~ -"hT l 1.e. ;)r-£.t)G-it') - ~
(}7J,,i£:tt,,. j) /}n 19-6f On-site assessment:
disassembly and inspection:
Descri# ;;? change in source position:
Describe results of radiography:
Completed by: Date: I? f1
SENTIN EL Issue 1 Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 43 of46 Equipment List 4: 9m (30 foot) Drop Equipment List Description Enter the Model and Attach Inspection Serial Number Report or Calibration Certificate Thennometer 0,416,A H# 21 ENti-llJ- lfNfrlZ,. ~/).~
Record any additional tools used to facilitate the test and attach the appropriate inspection report or calibration certificate St£ ~,,-Alt'i WmfYJD~o t£ ofVllsA S TC... *e-G-K - 2.0*.3'. ~
Signature Print Name Date
/'"\
Completed by: ',.- Uw( l£i' DN At.J.UI > (7 MAR..~,
Verified by:
~~ - ~ 7JQ,,,,~, ;,;.l(ud z l7 >'Me 'I?
SENTINEL Issue l Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 43 of46 Equipment List 4: 9m (30/oot) Drop Equipment List Description Enter the Model and Attach Inspection Serial Number Report or Calibration Certificate Thennometer o,4t6A HH 21 EN/s-1~ *N"*l'l,. ~" ~~
Record any additional tools used to facilitate the test and attach the appropriate inspection report or calibration certificate SE:£ ~n-AC.t-1
/J)p}2fYJl',G,l)l)t£ otvltsA STL*e-G-t'- -2.0-3'. UP" Signature Print Name Date
/"'I J)
~
Completed by: ...---- (
'- JJfJ1 A DNG At.JAJI~ (1 MA~~j Verified by:
~~-~ 7,]o,,tl J,J,l(urlz. 17111:/e 'I?
SENTlNEL Issue I Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 44 of46 Checklist 5: 9m (30 foot) Drop Test Location: u/' ~t.a..,...c,...-
4 L .A.A A Step Specimen TP84(A) Specimen TP84(B)
SN S"I NS";J..
I. Measure and record the ambient temperature ( 0 C) 13°c. ;@11~
Note the instrument used:
&ty& tNtr-/1,
2. Attach the test specimen to the release mechanism.
3. Lift and orientate the test specimen as shown in the Figure 8.9.3.1 referenced figure for the specimen.
4. Inspect the orientation set-up and verify the drop height.
5. Photograph the set-up in at least two perpendicular planes.
6. Begin video recording of the test so that impact is recorde
7. Release the test specimen
8. Pause the video recorder. Ensure that the point of impact and the orientation speci achieved and recorded. Ci> ., ..
A A,.
nd attach .
10. Engineering, Regulatory Affairs and Quality Assurance make a preliminary asses m 7 1. Record the assessment on a separate sheet and attach. Detennine what changes, if any, are necessary in package orientation for the puncture test to achieve maximum damage. (b )
Test witnessed by (Signature) Print Name Engineering:
Regulatory A Quality Assurance:
'Z>, J.J.
AEAT/QSA February I 999 Burlington, Massachusetts Test Plan 84 Data Sheet Test Date: /? Mhtt- Test Time: I ~ 1.- ~ o Test Plan Step No. :
Describe drop orientation and drop height:
-D,a..,IJ . r"'...,- Q/'V 1'ot' F'lt.4M io ~ , - ~ e. 'f. .;2..1 Describe impact (location, rotation, etc.):
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~/'f~ ~~ ~ ~ l Describe on-site inspection (damage, broken parts, etc.):
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disassembly and inspection:
Describe any change in source position:
/Vii Describe results of radiography:
ft Completed by: Date: 11") 1'1,/!JtL
AEAT/QSA February 1999 Burlington, Massachusetts Test Plan 84 Data Sheet Specimen/fest:
Test Plan Step No.:
Describe dJ:op orientation and drop height:
DP.()P F1..AT ~"' Lt>Ch s ,r,F rA.*/JI Describe impact (location, rotation, etc.):
X M/>IJ'-T pelt F i G "f At ~. &f, 3. I Describe on-site inspection (damage, broken parts, etc.):
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C<,J/1(77Nt,UT WI.,.,_,, f1,.4NN4JJ Tli"&T .sn"eNa:' ~ IJAI/TAl'"f",,..,.f()IV Describe an post-test disassembly and inspection.
Describe any change in source position:
jVh-Describe results of radiography:
111/J-Completed by: Date: /
SENTINEL Issue I Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 45 of46 Equipment List 5: Puncture Test Equipment Description Enter the Model and Attach Inspection Serial Number Report or Calibration Certificate Puncture Billet.
,1011') Set:~
Thermometer OMcl:IA U 1-1 *'i C N~'-['Z -Ji Record any additional tools used to facilitate the test and attach the appropriate inspection report or calibration certificate
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SENTINEL Issue I Test Plan 84 AEAT/QSA March 1999 Burlington, Massachusetts Page 46 of 46 Checklist 6: Puncture Test Test Location: SPociMen Pu"'-to -re 5 r nJ
2. )<. Fl6<>(t£ 8 . lC ,3. i (2~ =2T$r Step Specimen TP84(A) Specimen TP84(8)
I. Measure and record the ambient temperature ( 0 C).
p 13 c_
2. Note the instrument used :
3. Attach the test specimen to the release mechanism
4. Lift and orientate the test specimen as shown in the Figure 8.10.2.1
~
referenced figure for the specimen.
5. Inspect the orientation set-up and verify the drop height.
6. Photograph the set-up in at least two perpendicular planes.
7. Begin video recording of test so that the impact is recorded.
8. Release the test specimen.
9. Pause the video recorder. Ensure that the point of impact and orientation specified in the plan have been achieved and recorded.
10. Record damage to test specimen on a separate sheet and attach.
11 . Device Profile Complete.
l------------------+----------,t"F----,..;-----1#~~
t::::~
12. Engineering, Regulatory Affairs and Quality Assurance make a preliminary assessment relative to IOCFR 71.
Record the assessment on a separate sheet and attach.
Test witnessed by: Signature Date f
Q~ity Assurance:
~
AEAT/QSA February 1999 Burlington, Massachusetts Test Plan 84 Data Sheet Specimen/fest: PtlAJtTVRe Test Plan Step No.:
Describe drop orientation and drop height:
"Dl.11P o.i /:ut111,ruu 8.o~ ~ - 4 '.
Describe impact (location, rotation, etc.):
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Describe on-site inspection (damage, broken parts, etc.):
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Describe any change in source ~sition: _
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:P*vull l t ~ l 6 1 , ~ V N?l1" Jf(,FGJ.-<<*A-~.
Completed by: Date: /'l n~
AEAT/QSA February 1999 Burlington, Massachusetts Test Plan 84 Data Sheet OR.vP.:1.
Test Unit ModeVSerial No.: f/6~ S Specimen/Test: 7P Test Date: /f} /1/J,(t. ~ Test Time: Test Plan Step No. :
Describe drop orientation and drop height:
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pt?rl., f;Gu/ul' 8. lD,3,/
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disassembly and inspection:
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Describe results of radiography:
ff Completed by: Date: / 7 M6({. 1
AEAT/QSA February 1999 Burlington, Massachusetts Test Plan 84 Data Sheet Specimen/Test: iP 03 pH,.,,~*-- 0/l"P ~
Test Plan Step No.: fl , p, ~ -=
Describe drop orientation and drop height:
J}µ~ t:?tv Pt,t-,1,TAA-e 8~ - F'-'W' of\/ L ,t,,1-t, - ~
Describe impact (location, rotation, etc.): :\
Jwy,,,.,c/-- DIV /,,&,ft { per Fp~ l/.1(). ~I.J Describe on-site inspection (damage, broken parts, etc.):
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. . f'l 11-.17 Engmeenng:M. 1,,~~._,, Regulatory: QA: :r,.w.
Describe any ost-tes sassembly and inspection.
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Describe anv change in source position:
- So1ttt,:;,Y ,t.-,o /rrSt,,"'M/$t, r \ ~ ,,.,,, ~tf "-.:,~ l'P(,;,p,v Describe results of radiography:
- Oi:V11,e A,..o,(),/1Jtpi,4"f ,;v-,r A,a,,.,11,n - /V~
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. Completed by: Date: / r; /7~ ~
APPENDIXD TEST PHOTOGRAPHS T:\REGULATE\Old Regulate\WP\WORD\Type B\865\TP 84 865\TP84 report Final.DOC
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 2-44 2.12.3 Model 865 Fin ite Element Analysis (June 2000)
MPR Associates, Inc.
mMPR 320 King Street Alexandria, VA 22314 CALCULATION TITLE PAGE Client AEA Technology QSA, Inc. Page 1 of 46 (Attachments 1, 2)
Project Task No.
Type B Projector Qualification 420-0001-004-0 Title Calculation No.
Model 865 Finite Element Analysis 420-004-AAB-1 Preparer / Date Checker/ Date Reviewer & Approver/Date Rev. No.
0 Anindya Baral Edward Bird Nick Marrone 7-28-00 7-28-00 7-28-00 QUALITY ASSURANCE DOCUMENT IThis document has been prepared, checked and reviewed/approved in accordance with the Quality Assurance requirements of 10CFR50, Appendix B, as specified in the MPR Quality Assurance Manual.
MPA QAA Form: QA-3.1-1, Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 RECORD OF REVISIONS Calculati9n No. Prepared By Checked By Page: 2 420-004-AAB-1 Revision: 0 Revision Affected Pages Description 0 All Initial Issue Note: The revision number found on each individual page of the calculation carries the revision level of the calculation in effect at the time that page was last revised.
MPR QA FOfm: OA*3.1*2, Rev. 0
MPA Associates, Inc.
MPR 320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 3 420-004-AAB-1 Revision: 0 CONTENTS Section Page 1.0 Purpose 4 2.0 Summary of Results 4 3.0 Approach 4 4.0 Finite Element Model 5 4.1 Geometry 5 4.2 Material Properties 6 4.3 Thermal Boundary Conditions 6 4.4 Structural Boundary Conditions 7 5.0 Results 8 5.1 Thermal 8 5.2 Stress 8 6.0 References 9 - Geometric Keypoint Coordinates 37 - Material Property Listing 42 I
I MPR QA Form: OA-3.1-3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 4 420-004-AAB- l Revision: 0 1.0 PURPOSE The purpose of this calculation is to document a fmite element analysis of the AEA Technology Model 865 Projector for the thermal requirements of 10CFR7 l.73.4. The Model 865 Type B Projector is designed for radiographic inspections. The projector is shown on Figures 1 and 2.
10CFR71. 73 specifies hypothetical accident conditions for which the projector must be designed. The thermal accident conditions include immersion in a 1475°F fire for 30 minutes. The acceptance criterion for the test is that there is not a significant increase in radiation levels external to the package following a hypothetical accident. For this calculation, the acceptance criterion is considered to be met if the calculated strains in the stainless steel components which contain the depleted uranium shield are less than the strain corresponding to the material ultimate strength at the test temperature.
2.0
SUMMARY
OF RESULTS Figure 3 shows contours of the stress intensity profile in the projector at 3 minutes, the time of maximum stress during the transient. The maximum stress intensity is 28 ksi. Figure 4 shows contours of total strain at 3 minutes. The maximum strain is less than 3%. This strain is considerably less than the strain at failure (40 to 50%) for stainless steel at a temperature of 147 5°F.
An additional elastic-plastic stress pass was made at a time of 30 minutes to confirm that there is sufficient material strength at the highest temperatures to react the primary pressure loads. The maximum calculated total strain at 30 minutes is less than 1%.
3.0 APPROACH A three-dimensional finite element model of the projector was developed with the ANSYS computer program (Reference 1). The projector components included in the model are:
Projector Weldment
Shield
Upper and Lower Shield Collars
Upper and Lower Shield Support Rings
Handle
Housing Support Legs MPA QA Form: QA-3.1-3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 5 420-004-AAB-1 Revision: o
Actuator Assembly Components, including:
- Actuator Base
- Actuator Body Weldment
- Actuator F1ange
- Actuator Guard
Shipping Cover
Source Tube
Source Rod and Capsule Holder Half (180 degrees) of the projector was modeled based on geometric and loading symmetry.
A three-part sequential analysis technique was used. In the first part of the analysis, a thermal transient analysis was performed to calculate temperature profiles within the projector as a result of immersion in a fire. Radiation and convective heat transfer modes were considered. In the second part of the analysis, stresses in the projector components due to the calculated temperature profiles were detennined on an elastic basis at several times during the transient. In the third part of the analysis, at the time of maximum elastic stress due to temperature, a final analysis was pe1formed with elastic-plastic material properties.
The effects of bounding internal pressure were included in the final analysis.
4.0 FINITE ELEMENT MODEL 4.1 Geometry One half of the transport package is modeled. Figures 5 through 8 show the finite element model components. Dimensions for the model are from References 2 through 22. Figures 9, 10 and 11 show key-point numbers for a cross section of the model. Keypoint coordinates for the cross sections are listed in Attachment l to this calculation.
The model is meshed with hexahedral (SOLID70 for thermal; SOLID45 for structural) and tetrahedral elements (SOLID87 for thermal; SOLID92 for structural). A surface effect element (SURF152) is used on the outside of the model to facilitate the application of the thermal boundary conditions.
The transport package includes thin brass shield support rings that separate the depleted uranium from the stainless steel. These rings are modeled explicitly and are assumed to completely fill the gap between the depleted uranium shield and the upper/lower shield collars. Perfect thermal contact is assumed MPR QA Form: QA-3.1*3. Rev. 0
MPR Associates, Inc.
mMPR 320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 6 420-004-AAB-1 Revision: O between the stainless steel on one side and the depleted uranium on the other. Structurally, these rings provide little mechanical resistance due to the low strength of brass at high temperature.
4.2 Material Properties The projector weldment (including the upper and lower shield collars), housing handle, housing support, actuator assembly (including the actuator base, actuator body weldment, and the actuator tlange),
shipping cover, and the actuator guard are constructed from 304 stainless steel. Depleted uranium is used for the shield. Thin brass shield support rings are used between the stainless steel and uranium. The entire source rod/capsule holder assembly is modeled as tungsten. A brass tube separates the tungsten source rod from the depleted uranium shield. Material properties for these four materials from References 23 through 26 are used in the model and are listed in Attachment 2 to this calculation. The properties are temperature dependent for all but brass.
The mechanical strength of the brass at elevated temperature is assumed to be negligible. Accordingly.
the elastic modulus for this material was set to 1000 psi.
Elastic-plastic material properties for the stainless steel components were used for the final analysis runs.
Bi-linear stress strain curves as a function of temperature were input. The yield stress values used are shown in Table 4-1. A tangent modulus (slope of the stress strain curve in the plastic region) of 5x105 psi was used for each curve.
Table 4-1 Yield Stress Values for 304 Stainless Steel (Reference 17) 100 29.01 300 22.39 600 18.27 900 16.21 1200 14.20 1500 9.50 4.3 Thermal Boundary Conditions Thermal boundary conditions representing immersion in a fire at 1475°F were applied to the finite element model on all exterior surfaces. These surfaces include the outer surfaces of the housing and shipping cover. The bottom of the lower shield collar was also heated (i.e., the projector is assumed to be MPR QA Form: OA-3.1-3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 7 420-004-AAB-1 ~ Revision: O suspended in the fire). The symmetry plane of the model was represented by a no heat flow condition (i.e., insulated).
Radiation and convection heat transfer modes were included to account for heat flow from the fire to the projector. For radiation, the outer surfaces of the projector were conservatively assumed to be black bodies; absorbing all radiation. An absorptivity/emissivity of 1.0 was assumed for the exterior surfaces.
A form factor of 1.0 for the exterior surfaces was assumed indicating the cask is fully engulfed by the fire.
Based on a review of typical fossil-fired furnace design coefficients, a heat transfer coefficient of 20 BTU/hr-ft2-°F was assumed on the exterior surfaces for convection. The shield, brass source tube, and the source rod/capsule holder assembly were assumed to be in perfect thennal contact with each other.
Heat tlow across the air gaps inside the projector was also considered. The AUX12 radiation matrix generator within ANSYS was used to generate matrices of form factors (view factors) between the radiating internal surfaces of the projector. The hidden-line algorithm in AUX 12 was used to calculate the form factors. This algorithm determines which elements are "visible" to every other element (a "target" element is visible to a viewing" element if their normals point toward each other and there are no blocking elements). Each radiating or viewing" element is enclosed in a unit hemisphere. All "target" or receiving elements are projected onto the hemisphere. To calculate the form factor, a predetermined number of rays (20 in the present analysis) are projected from the viewing element to the hemisphere. Thus, the form factor is the ratio of the number of rays incident on the projected surface to the number of rays emitted by the viewing element. The radiation matrices were then used as superelements (MATRIX50) in the thermal analysis. Convective heat transfer in the confined space within the projector was assumed to be negligible.
4.4 Structural Boundary Conditions Structural boundary conditions were applied to the projector finite element model to determine thermal expansion stresses and stresses due to internal pressure. Thermal expansion stresses result from differential thermal expansion of the projector components.
Pressure stresses result from the air inside the projector weldment heating up and expanding (according to the ideal gas law). It was conservatively assumed in this analysis that the projector weldment is pressurized, Le., it is assumed that the air in the projector weldment is not vented through the projector label plate rivet holes. The shipping cover is not air-tight and the volume within the cover is not pressurized. This approach results in the maximum differential pressure across the upper shield collar.
Internal pressures were applied in the final elastic-plastic analyses. The bounding value of the applied pressure is determined as follows:
MPR QA Form: QA-3.1-3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 8 420-004-AAB-l Revision: O P2 = T2 Pt = <1 475 + 460) 15 = 55 si Tt (70+460) p Displacements are constrained at the plane of symmetry in the direction normal to the plane of symmetry (y direction), along a vertical line through the origin in the x direction , and at a single node on the bottom of the lower shield collar in the z direction.
5.0 RESULTS 5.1 Thermal Figures 12 through 16 show temperature profiles in the projector at selected times during the temperature transient. At three minutes into the transient (Figure 13) the exterior surfaces of the shipping cover and the housing have heated up to nearly 1300°F. The handle and the housing support have heated up to nearly 1475°F. However, the inside of the projector is still relatively cool. By 30 minutes, the projector has nearly reached an equilibrium temperature of 1475°F.
5.2 Stress Figures 17 through 23 show contours of stress intensity in the projector at selected times during the temperature transient. These stresses were calculated with elastic material properties and do not include pressure loads. This phase of the analysis was used to identify the time of maximum thermal stress. The maximum thermal stress intensity occurs at 3 minutes and is located in the projector weldment shell near the sharp comer of the lock cut-out.
As shown in Figure 19, high stresses occur at the connection between the projector weldment shell and the upper shield collar. This is due to the expansion of the projector weldment shell which is restrained by the cooler upper shield collar. The maximum calculated elastic stress of 273 ksi occurs at the sharp comer of the lock cut-out due to stress concentration effects. This maximum stress would not occur in the projector weldment subjected to the specified thermal conditions because the stainless steel shell material would yield and relieve the stress. These thermal expansion stresses are secondary and the maximum stress intensity does not occur in the material that forms the containment boundary around the depleted uranium shield.
To obtain a more realistic picture of the stress and strain condition in the projector, the stress pass was repeated at the time of maximum elastic thermal stress, 3 minutes, with elastic-plastic material properties.
Pressure loads were included in this stress pass. Figures 3 and 4 show contours of stress intensity and total (elastic+ plastic) strain. The maximum stress is reduced from 273 ksi to 28 ksi due to yielding in the material. The maximum calculated strain of less than 3% occurs near the lock cut-out in the projector MPR QA Form: QA-3.1-3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 9 420-004-AAB-l Revision: O shell which is also the location of maximum elastic stress intensity. The beam window in the projector shell, where the shell thickness reduces from 0.12" to 0.06", experiences a maximum strain of less than 2%. Material testing shows that 304 stainless steel at 1475°F will not rupture until the strain reaches 40 to 50% (Reference 27). Consequently, a strain of less than 3% is judged to be acceptable.
An elastic-plastic stress pass was made at a time of 30 minutes to confirm that there is sufficient material strength at the highest temperatures to react the primary pressure loads. Figure 24 shows that the stress results are bounded by the stresses at 3 minutes. The maximum calculated total strain at 30 minutes is less than 1%.
An additional elastic stress pass was made with the containment boundary subject to an internal pressure load of 55 psi and a uniform temperature of 70°F to evaluate the effect of the pressure load alone on the containment boundary. The beam window with a reduced shell thickness of 0.06" was a location of particular interest. As seen in Figure 26, the maximum elastic stress intensity of 5 ksi occurs due to stress concentration at the connection between the actuator and the upper shield collar. The beam window experiences a stress intensity of less than 4 ksi. These stresses are judged to be acceptable.
6.0 REFERENCES
1. ANSYS Finite Element Analysis Computer Program, Version 5.6 installed on a Sun Ultra 2 workstcl.tion running the Sola1is 7 operating system. The ANSYS installation verification is documented in QA-56-1
2. AEA Drawing No. 86500, Type B Underwater Projector, Rev. F
3. AEA Drawing No. 86500-14, Model 865 Outline Dimension, Rev. A
4. AEA Drawing No. 86501, Projector Weldment, Rev. G
5. AEA Drawing No. 86502, Housing Weldment, Rev. J
6. AEA Drawing No. 86501-6, Shield Collar, Lower, Rev. D
7. AEA Drawing No. 86502-3, Shield Collar, Upper, Rev. C
8. AEA Drawing No. 86501-1, Shield Support Ring, Lower, Rev. B
9. AEA Drawing No. 86501-2, Shield Support Ring, Upper, Rev. B
10. AEA Drawing No. 86502-1, Housing Support, Rev. C
11. AEA Drawing No. 86502-2, Handle, Rev. B
12. AEA Drawing No. 86505, Actuator Base Sub-Assembly, Rev. C
13. AEA Drawing No. 86505-1, Actuator Base, Rev. C MPR QA Form: OA-3.1-3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 10 420-004-AAB-1 Revision: O
14. AEA Drawing No. 86500-5, Actuator Flange, Rev. G
15. AEA Drawing No. 86500-3, Actuator Body Weldment, Rev. C
16. AEA Drawing No. 86500-8, Shipping Cover, Rev. D
17. AEA Drawing No. 86500-12, Actuator Guard, Rev. F
18. AEA Drawing No. 86501-3, Shield, Rev. G
19. AEA Drawing No. 86505-2, Source Tube, Rev. B
20. AEA Drawing No. 86504, Source Rod and Capsule Holder Assembly, Rev. D
21. AEA Drawing No. 86504-1, Source Rod, Rev. G
22. AEA Drawing No. 86504-2, Source Capsule Holder, Rev. B
23. Marchbanks, M.F., Moen, RA., and Irvin, J.E., Nuclear Systems Materials Handbook, Part I -
Structural Materials, Group 1 - High Alloy Steels, Section 2 - 304 SS Annealed, Revision 8, 1976.
24. Rohsenhow, W.M., Hartnett, J.P., and Cho, Y.I. (Eds.), Handbook of Heat Transfer, Third Edition, McGraw-Hill (Properties for Tungsten and Uranium obtained from Chapter 2 - Thermophysical Properties).
25. Metals Handbook, Volume 2, Tenth Edition, 1990.
26. Tungsten (W) thermal expansion coefficient from Matweb, Online Materials Information Resource, http://www.matweb.com.
27. Aerospace Structural Metals Handbook, 1991 Edition.
MPR QA Form: OA*3.1*3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 11 420-004-AAB-1 Revision: 0 Figure 1 Isometric View of Model 865 Type B Projector MPR QA Form: QA-3.1-3. Rev. 0
MPR Associates, Inc.
MPR 320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 12 420-004-AAB-1 Revision: 0 Source Rod Projector W eldment Handle Depicted Uranium Shield Upper Brass Support Ring Lower Bras.s Support Ring S/S tecl Shi in Cover Pneumatic Actuator "A"
Source Capsule Actuator Weldment (Guard)
Coro 311 SIDE SECTION Lock Assembly Projector Wcldruent Support Leg I 127 p I
VIEW "A" Figure 2 Model 865 Type B Projector Schematic MPR QA Form: OA-3.1-3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 13 420-004-AAB-1 Revision: 0 1 ANSYS 5.6 JUL 26 2000 14:47:29 PLOT NO. 1 NODAL SOLUTION TIME=180 SINT (AVG }
DMX =.125676 SMN =13.084 SMX =27837
- 13.084
- 3105
- 6196
- 9288
- 12379 D 15471 CJ 18562 21654
- 24745 27837 Model 865 - Plastic Analysis Figure 3 Model 865 Stress Intensity Profile at 3 Minutes MPR QA Form: OA-3.1*3. Rev. 0
MPR Associates, Inc.
mMPR 320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 14 420-004-AAB-l Revision: O 1 ANSYS 5.6 JOL 26 2000 14:48: 51 PLOT NO. 1 NODAL SOLUTION TIME=180 EPTOINT ( AVG)
DMX = . 125676 SMN = . 929E-06 SMX =.023452
- .929E-06
- .002607
.005212
. 007818
. 010424
. 013029
.015635
. 018241
.020847
. 023452 Model 865 - Plasti c Analysis Figure 4 Model 865 Strain Intensity Profile at 3 Minutes MPR QA Form: OA*3.1*3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 15 420-004-AAB-1 Revision: O 1 I\N Model 865 Figure 5 Model 865 Finite Element Model MPR QA Form: OA*3.1*3. Rev. O
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 16 420-004-AAB-1 Revision: O 1 J\N ~
Model 865 Figure 6 Model 865 Finite Element Model - Projector Weldment (includes the Upper and Lower Shield Collars),
Housing Support, Handle, Actuator Assembly (includes Actuator Base, Actuator Body Weldment, and Actuator Flange), Actuator Guard, and Shipping Cover.
MPR QA Form: QA-3.1-3, Rev. O
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 17 420-004-AAB- l Revision: O 1 J\N Model 865 Figure 7 Model 865 Finite Element Model - Shield MPR OA Form: OA-3.1-3. Rev. 0
MPR Associates, Inc.
~MPR 320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 18 420-004-AAB-1 Revision: O 1 J\N Model 865 Figures Model 865 Finite Element Model - Source Rod/Capsule Holder Assembly and Source Tube MPR QA Form: OA-3.1-3. Rev. O
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 19 420-004-AAB-1 Revision: 0 1 J\N Model 865 Figure 9 Geometric Keypoints - Projector Weldment, Handle, Housing Support, Actuator Assembly, Actuator Guard, and Shipping Cover MPR QA Form: QA-3.1*3. Rev. 0
MPR Associates, Inc.
(+JMPR 320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 20 420-004-AAB-l Revision: O 1
20D02 33 34 14 17 AN 23 31 10 1
08 99 5
Model 865 Figure 10 Geometric Keypoints - Shield MPR QA Form: OA-3.1*3. Rev. O
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 21 420-004-AAB- 1 Revision: O 1 J\N fF l:E4i4 2l4i3 Model 865 Figure 11 Geometric Keypoints - Source Rod/Capsule Holder and Source Tube MPA QA Form: OA-3.1*3, Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 22 420-004-AAB-1 Revision: 0 1 ANSYS 5.6 JUL 25 2000 1 4:54:29 PLOT NO. 1 NODAL SOLUTION TIME=l TEMP (AVG)
RSYS=0 PowerGraphics EFACET=l AVRES=Mat SMN =67.457 SMX al475 0
100 200 300 400 500 600 700 800 D 900 1000 D
1100 D 1200 D 1300 1400 1500 Model 865 Figure 12 Temperature Profile at 1 Second MPR QA Form: QA-3.1*3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 23 420-004-AAB-1 Revision: O 1 ANSYS 5.6 JUL 26 2000 15:12:57 PLOT NO. 1 NODAL SOLUTION TIME=180 TEMP (AVG)
RSYS=O PowerGraphics EFACET=l AVRES=Mat SMN =122 .111 SMX =1475
- ~00
- 200
- 300
- 400
- 500
- 600
- 700
- 800
- 900 c:J B
CJ 1000 1100 1200 1300
- 1400 1500 Model 865 Figure 13 Temperature Profile at 3 Minutes MPR QA Form: OA-3.1-3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 24 420-004-AAB-l Revision: 0 l ANSYS 5.6 JUL 25 2000 14:58:17 PLOT NO. 1 NODAL SOLUTION TIME=600 TEMP (AVG)
RSYS=O PowerGraphics EFACET=l AVRES=Mat SMN =839.087 SMX =1475 0
100 200 300 400 500 600 700 800 900 D 1000 D
CJ 1100 CJ 1200 1300 1400 1500 Model 865 Figure 14 Temperature Profile at 10 Minutes MPR QA Form: QA-3.1-3. Rev. O
MPR Associates, Inc.
mMPR 320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 25 420-004-AAB-1 Revision: O 1 ANSYS 5.6 JUL 25 2000 15:00:18 PLOT NO. 1 NODAL SOLUTION TIME=1200 TEMP {AVG)
RSYS=0 PowerGraphics EFACET=l AVRES=Mat SMN =1330 SMX =1475
- ~00
- 200
- 300
- 400
- 500
- 600
- ?00 800 900 C J 1000 1100 CJ 1200 D 1300 1400 1500 Model 865 Figure 15 Temperature Profile at 20 Minutes MPR QA Form: OA-3.1*3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 26 420-004-AAB-1 Revision: 0 1 ANSYS 5.6 JUL 25 2000 15:01:40 PLOT NO. 1 NODAL SOLUTION TIME=1800 TEMP (AVG)
RSYS=0 PowerGraphics EFACET=l AVRES=Mat SMN =1440 SMX =1475 0
100 200 300 400 500 600
- 700 800 900 CJ 1000 CJ 1100 D 1200 D 1300 1400 1500 Model 865 Figure 16 Temperature Profile at 30 Minutes MPR QA Form: QA-3,1*3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 27 420-004-AAB-1 Revision: O 1 ANSYS 5.6 JUL 28 2000 09:47:50 PLOT NO. 1 NODAL SOLUTION TIME=60 SINT (AVG)
DMX = .081938 SMN =.176204 SMX =214828
- .176204 23870 47740 71609 95479 119349 143219 167088 190958 214828 Model 865 - Structural Analysis Figure 17 Stress Intensity Profile at 1 Minute MPR QA Form: QA-3.1*3. Rev. O
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 28 420-004-AAB-1 Revision: 0 1 ANSYS 5.6 JUL 28 2000 09:50:44 PLOT NO. 1 NODAL SOLUTION TIME=l20 SINT (AVG)
DMX =.106745 SMN =. 791185 SMX =270532
- .791185 30060 60119 90178 120237 150296 180355 210414
- 240473 270532 Model 865 - Structural Analysis Figure 18 Stress Intensity Profile at 2 Minutes MPR QA Form: QA-3.1*3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 29 420-004-AAB-1 Revision: O 1 ANSYS 5.6 JUL 28 2000 09:53:22 PLOT NO. 1 NODAL SOLUTION TIME=180 SINT (AVG)
DMX ... 121544 SMN =1 . 593 SMX =2 72885
- 1.593
- 30322 60642 90963 121283
-~ 151603 181924 iij 212244
- 242564 272885 Model 865 - Structural Analysis Figure 19 Stress Intensity Profile at 3 Minutes MPA QA Form: QA-3.1-3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 30 420-004-AAB-1 Revision: 0 1 ANSYS 5.6 JUL 28 2000 09:56:09 PLOT NO . l NODAL SOLUTION TIME=300 SINT (AVG)
OMX =.138767 SMN =3.045 SMX =233420
- 3.045
- 25938 51873 77809 103744 129679 155614 181549 207485 233420 Model 865 - Structural Analysis Figure 20 Stress Intensity Profile at 5 Minutes MPR QA F01m: OA-3.1-3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 31 420-004-AAB-1 Revision: O 1 ANSYS 5.6 JUL 28 2000 09:59:15 PLOT NO. 1 NODAL SOLUTION TIME=600 SINT (AVG)
OMX =.164027 SMN =2.503 SMX =117368
- 2.503
- 13043 26084 39124 52165 65206 78246 91287
- 104328 117368 Model 865 - Structural Analysis Figure 21 Stress Intensity Profile at 10 Minutes MPR OA Form: QA-3.1-3. Rev. 0
MPR Associates, Inc.
[+]MPR 320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 32 420-004-AAB-l Revision: O 1 ANSYS 5 . 6 JUL 28 2000 10:01:35 PLOT NO . 1 NODAL SOLUTION TIME==1200 SINT (AVG)
DMX ==.184387 SMN ==. 776372 SMX :::28305
- .776372
- 3146 6291
- 9435 12580
- 15725 D 10070 D 22015
- 25160
- 28305 Model 865 - Structural Analysis Figure 22 Stress Intensity Profile at 20 Minutes MPR QA Form: QA-3.1-3. Rev. 0
MPR Associates, Inc.
[+]MPR 320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 33 420-004-AAB-1 Revision : O 1 ANSYS 5.6 JUL 28 2000 10:03:22 PLOT NO. 1 NODAL SOLUTION TIME=1800 SINT (AVG)
DMX =.188076 SMN =.27036 SMX =17636
- .27036 1960 3919 5879 7838 9798 11757 13717
- 15676 17636 Model 865 - Structural Analys i s Figure 23 Stress Intensity Profile at 30 Minutes MPR QA Fofm: QA-3.1-3. R&Y. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 34 420-004-AAB-1 Revision: O 1 ANSYS 5.6 JUL 26 2000 14:51:14 PLOT NO. 1 NODAL SOLUTION TIME=l800 SINT (AVG)
DMX =.185228 SMN =.083159 SMX =11579
- .083159
- 1287 2573 3860 5146 6433 7719 9006
- 10292 11579 Model 865 - Plastic Analysis Figure 24 Stress Intensity Profile at 30 Minutes - Elastic Plastic MPR QA Form: QA-3.1-3. R6\f. 0
MPR Associates, Inc.
320 King S1reet Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 35 420-004-AAB- l Revision: 0 1 ANSYS 5.6 JUL 26 2000 14:52:50 PLOT NO. 1 NODAL SOLUTION TIME=1800 EPTOINT (AVG)
DMX =.185228 SMN =.595E-08 SMX =.002685
.595E-08
.298E-03
.597E-03
.895E-03
.001194
.001492 D .00179 CJ .002089
.002387
.002685 Model 865 - Plastic Anal ysis Figure 25 Strain Profile at 30 Minutes - Elastic Plastic MPR QA Form: OA-3. 1-3. Rev. O
MPA Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 36 420-004-AAB-1 Revision: 0 1 ANSYS 5.6 JUL 28 2000 14:01:56 PLOT NO. 1 NODAL SOLUTION STEP=l SUB =1 TIME=l SINT ( AVG }
OMX =.001253 SMN =.004945 SMX =4750
- .004945
- 527.776
- 1056 1583 2111 2639 3167 3694
- 4222 4750 Model 865 - Pressure Analysis Figure 26 Stress Intensity Profile due to Pressure Load - Elastic MPR QA Form: QA-3.1-3. Rev. O
MPR Associates, Inc.
MPR 320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 37 420-004-AAB- 1 Revision: 0 ATTACHMENT 1 Geometric Keypoint Coordinates MPA QA Form: QA-3.1-3. Rev. 0
MPR Associates, Inc.
mMPR 320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 38 420-004-AAB-1 Revision: 0 LIST ALL SELECTED KEYPOINTS. DSYS= 0
ANSYS - ENGINEERING ANALYSIS SYSTEM RELEASE 5 . 6 ANSYS/Multiphysics 00040197 VERSION=SOLARIS64 16 : 22:33 JUL 25 , 2000 CP= 22 . 960 Model 865 NO. X,Y,Z LOCATION KESIZE NODE ELEM MAT REAL TYP ESYS l 2 . 50 0. 0. 0. 11286 0 0 0 0 0 2 2 . 38 0. 0. o. 10243 0 0 0 0 0 3 -2. 38 0.291E-15 0. o. 1 0244 0 0 0 0 0 4 - 2.50 0.306E-15 o. 0. 11373 0 0 0 0 0 5 2 . 50 0. 7 . 12 o. 43199 0 0 0 0 0 6 - 2.50 0 . 306.E-15 7 .12 0. 43161 0 0 0 0 0 7 - 2 . 38 0 . 291E- 15 7.12 0. 42835 0 0 0 0 0 8 2 . 38 0. 7 . 12 0. 42575 0 0 0 0 0 9 2.50 o. 6 . 56 o. 11323 0 0 0 0 0 10 2 . 38 0. 6.56 o. 11215 0 0 0 0 0 11 - 2. 38 0 . 291E-15 6.56 0. 11184 0 0 0 0 0 12 -2.50 0 . 306E- 15 6.56 o. 1 1 504 0 0 0 0 0 13 2 . 50 0. 4 . 22 0. 11287 0 0 0 0 0 14 2.44 o. 4 . 22 0. 11309 0 0 0 0 0 15 2.00 1 . 40 4 . 22 o. 13193 0 0 0 0 0 16 2.05 1.43 4.22 0. 11556 0 0 0 0 0 17 2.50 0. 6 . 22 o. 11321 0 0 0 0 0 18 2.05 1.43 6.22 0. 11548 0 0 0 0 0 19 2 . 00 1.40 6 . 22 0. 13217 0 0 0 0 0 20 2.44 0. 6 . 22 0. 11311 0 0 0 0 0 NO . X,Y , Z LOCATION KESIZE NODE ELEM MAT REAL TYP ESYS 21 1. 69 0. 5.94 0. 6115 0 0 0 0 0 22 o. 0. 0.435E-01 o. 8799 0 0 0 0 0 23 1.50 0. 0.435E-Ol 0. 9320 0 0 0 0 0 24 2.38 o. 6.19 0. 6349 0 0 0 0 0 25 - 2 .38 0.291E-15 6.19 0. 6556 0 0 0 0 0 26 1 . 56 0. 5 . 94 o. 5 0 0 0 0 0 27 0 . 750 o. 6 . 13 o. 319 0 0 0 0 0 28 - 0 . 7S0 0 . 918E-16 6.13 0. 400 0 0 0 0 0 29 -0 . 280 2.48 7.12 0. 43187 0 0 0 0 0 30 -0.280 2.36 7 . 12 o. 43882 0 0 0 0 0 31 - 0 . 280 2,36 6 . 56 0. 10230 0 0 0 0 0 32 -0 . 280 2 , 48 6 , 56 0. 10231 0 0 0 0 0 33 0 . 720 2.39 7.12 o. 43189 0 0 0 0 0 34 0.720 2 .27 7 . 12 0. 44154 0 0 0 0 0 35 0 . 720 2.39 6 . 56 0. 11531 0 0 0 0 0 36 o. 720 2 . 27 6.56 0. 11211 0 0 0 0 0 37 -0.280 2.36 6 . 41 0. 10235 0 0 0 0 0 38 - 0 . 280 2 . 48 6.41 o. 10233 0 0 0 0 0 39 0.720 2 . 39 6 . 41 0. 11525 0 0 0 0 0 40 0.720 2 .27 6 . 41 o. 11205 0 0 0 0 0 NO . X, 'i,Z LOCATION KESIZE NODE ELEM MAT REAL TYP ESYS 41 o. 750 0. 6. 31 0. 9987 0 0 0 0 0 42 2.38 0. 6.31 0. 9629 0 0 0 0 0 43 - 2 . 38 0 . 291E- 15 6.31 0. 9649 0 0 0 0 0 44 - 1. 50 0 . 184E- 15 0.4352-01 0. 9321 0 0 0 0 0 45 1.50 o. 6 . 31 o. 9575 0 0 0 0 0 46 - 1. 50 0.1848-15 6 . 31 0. 9565 0 0 0 0 0 47 - 1.56 0 . 1928-15 5.94 o. 50 0 0 0 0 0 48 - 1.50 0 . 2228-15 6 .1 9 o. 6494 0 0 0 0 0 49 1 . 50 0. 6 . 19 o. 6353 0 0 0 0 0 so 1 .50 0. 0. 263 0. 8247 0 0 0 0 0 51 l. 56 0. 6.13 0. 6360 0 0 0 0 0 MPR QA Form: QA-3.1*3. Rev. 0
MPR Associates, Inc.
mMPR 320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 39 420-004-AAB-1 Revision: O 52 - 1. 56 0.192E- 15 6.13 0. 6386 0 0 0 0 0 53 -1 . 69 0.207E-15 5.94 o. 6117 0 0 0 0 0 54 - 1.50 0.222E-15 6.13 0. 401 0 0 0 0 0 55 l. 50 0. 6, 13 o. 310 0 0 0 0 0 56 -0.750 0.918E-16 6.31 o. 9985 0 0 0 0 0 57 1.69 0. 6 . 10 0. 6185 0 0 0 0 0 58 0.750 0. 6.19 o. 7892 0 0 0 0 0 59 - 0.750 0.222E-15 6.19 0. 7890 0 0 0 0 0 60 - 1.69 0. 207E-15 6.10 0. 6186 0 0 0 0 0 NO . X, Y,Z LOCATION KESIZE NODE BLEM MAT REAL TYP BSYS 61 -1.56 0.1928- 15 6.10 o. 59 0 0 0 0 0 62 1.56 0. 6 , 10 0. 14 0 0 0 0 0 63 - 1 . 50 0.184E- 15 0 . 263 0. 83 94 0 0 0 0 0 64 o. 0. 0 . 263 o. 77 0 0 0 0 0 65 o. 0. 0.292 o. 87 0 0 0 0 0 66 1.25 0. 0 . 435E-01 o. 8800 0 0 0 0 0 67 - 1.25 O.l53E-15 0.4358- 01 0. 8808 0 0 0 0 0 68 1.25 0. 0.263 o. 95 0 0 0 0 0 69 - 1 .25 0 . 153E- 15 0.263 0. 199 0 0 0 0 0 70 1 . 25 0. 0 . 292 0. 96 0 0 0 0 0 71 2. 38 0. 0 . 169 o. 8161 0 0 0 0 0 72 1.31 0. 0.169 0. 9167 0 0 0 0 0 73 - 1.31 0 . 1618- 15 0.169 0. 9169 0 0 0 0 0 74 -2 . 38 0.291E-1 5 0.169 o. 8159 0 0 0 0 0 75 2.38 0. 0 . 543 0. 7287 0 0 0 0 0 76 - 2.38 0 . 2918- 15 0 . 543 o. 7307 0 0 0 0 0 77 - 1.31 0.161E-15 0.543 o. 471 0 0 0 0 0 78 1.31 0. 0.543 o. 439 0 0 0 0 0 79 2 . 38 0. 0 . 292 o. 7016 0 0 0 0 0 80 1.31 0. 0.292 o. 447 0 0 0 0 0 NO. X,Y,Z LOCATION KESIZE NODE ELEM MAT REAL TYP ESYS 81 -1.31 0.1618- 15 0.292 o. 463 0 0 0 0 0 82 -2. 38 0.2918-15 0.292 o. 7022 0 0 0 0 0 83 -1. 25 0 . 1538- 15 0.292 o. 251 0 0 0 0 0 84 1. 25 o. 1 . 76 o. 929 0 0 0 0 0 85 - 1.25 0.1538- 15 1. 76 o. 969 0 0 0 0 0 86 0 . 750 0. 4.83 o. 534 0 0 0 0 0 87 1.31 0. 0 . 263 0. 8245 0 0 0 0 0 88 -1.3 1 0 . 1618- 15 0.263 o. 8396 0 0 0 0 0 89 1.50 0. 0.169 0. 8249 0 0 0 0 0 90 -1 .50 0.1848-15 0 . 169 o. 8275 0 0 0 0 0 91 0.189 0. 2 . 47 o. 2917 0 0 0 0 0 92 1.50 0. 3 . 70 o. 2260 0 0 0 0 0 93 -1 . 50 0 . 1848-15 3 . 70 o. 2261 0 0 0 0 0 94 1.25 0. 0 . 543 o. 455 0 0 0 0 0 95 -1.25 0 . 1538-15 0 . 543 0. 479 0 0 0 0 0 96 o. 0. 0.54 3 0. 1 513 0 0 0 0 0 97 o. o. 0 . 792 o. 866 0 0 0 0 0 98 1.25 0. 0. 792 o. 867 0 0 0 0 0 99 -1.25 0.1538- 15 0.792 o. 873 0 0 0 0 0 100 -0.189 0.231E-16 2 . 47 o. 2915 0 0 0 0 0 NO . X, Y, Z LOCATION KESIZ8 NODE ELEM MAT REAL TYP BSYS 101 0 . 1398-16 0 . 189 2 . 47 0. 2914 0 0 0 0 0 102 1.50 0. 6.10 0. 23 0 0 0 0 0 103 - 1 . 50 0.1848-15 6.10 0. 68 0 0 0 0 0 104 1.50 0. 4 . 63 o. 4307 0 0 0 0 0 105 0. o. 1. 76 o. 93 3 0 0 0 0 0 106 0.750 0. 3.70 o. 1954 0 0 0 0 0 107 -0 . 7 50 0 . 918E-16 3,70 o. 1950 0 0 0 0 0 108 2.22 0. 1.76 o. 1180 0 0 0 0 0 109 -2 . 22 0.2728-15 1 .76 0. 1174 0 0 0 0 0 110 2.22 0. 3 . 70 0. 2369 0 0 0 0 0 111 - 0.750 0.918E-1 6 6.10 0. 37 3 0 0 0 0 0 MPR QA Form: QA-3.1-3. Rev. 0
MPR Associates, Inc.
MPR 320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 40 420-004-AAB- l Revision: 0 112 0 . 750 o. 6.10 0. 322 0 0 0 0 0 113 0 . 189 0. 4.98 0. 631 0 0 0 0 0 114 1.50 0. 5.94 0. 24 0 0 0 0 0 115 - 1. 50 0.184E-15 5.94 0. 41 0 0 0 0 0 116 -2.22 0.2728-15 3.70 o. 2390 0 0 0 0 0 117 1.50 o. 5.81 o. 4216 0 0 0 0 0 118 0 . 189 o. 6 . 10 0. 2648 0 0 0 0 0 119 0 . 139E-16 0 . 189 6.10 0. 2646 0 0 0 0 0 120 -0.189 0 . 231E-16 6.10 0. 2644 0 0 0 0 0 NO. X,Y,Z LOCATION KESIZE NODE ELEM MAT REAL TYP ESYS 121 0.750 o. 5.61 0. 494 0 0 0 0 0 122 1 . 50 0. 4.42 o. 2285 0 0 0 0 0 123 - 1. 50 0 . 184E-15 4 . 42 0. 2281 0 0 0 0 0 124 0.189 0. 5.46 0. 492 0 0 0 0 0 125 -0 . 750 0. 4.42 0. 510 0 0 0 0 0 126 0.750 0. 4. 42 0. 536 0 0 0 0 0 127 0.750 0. 5 . 94 o. 519 0 0 0 0 0 128 -0.750 o. 5.94 0. 511 0 0 0 0 0 129 0 . 189 0. 3 . 70 o. 1918 0 0 0 0 0 130 -0.189 0.231E- 16 3 . 70 0. 1914 0 0 0 0 0 131 -0 . 1 89 o. 4 . 42 0. 600 0 0 0 0 0 132 0.189 0. 4.42 0. 604 0 0 0 0 0 133 -0 . 189 0. 5 . 94 o. 650 0 0 0 0 0 134 0 . 189 o. 5 . 94 0. 658 0 0 0 0 0 135 0. o. 2 . 47 0. 2919 0 0 0 0 0 136 1.50 0 . 163E- Ol 4 . 63 0. 4323 0 0 0 0 0 137 1.30 0 . 750 4.68 0. 4325 0 0 0 0 0 138 1.50 0.163E-01 5.81 0. 4217 0 0 0 0 0 139 1.30 o. 750 5 . 76 0. 4219 0 0 0 0 0 140 0.650 0.375 4.86 0. 530 0 0 0 0 0 NO . X,Y,Z LOCATION KESIZE NODE ELEM MAT REAL TYP ESYS 141 0.163 0.943E- Ol 4 . 99 0. 663 0 0 0 0 0 142 0.650 0.375 5.58 o. 487 0 0 0 0 0 143 0.163 0 . 943E-01 5. 4 5 0. 488 0 0 0 0 0 144 2 . 20 0. 6.56 o. 27602 0 0 0 0 0 145 - 2.20 0 . 269E-15 6.56 o. 27969 0 0 0 0 0 146 2.38 0. 7.69 0. 35619 0 0 0 0 0 147 -2.38 0.291E-15 7. 69 0. 35620 0 0 0 0 0 148 - 2 . 20 0 . 269E-15 7 . 69 0. 28422 0 0 0 0 0 149 2 . 20 0. 7. 69 o. 28449 0 0 0 0 0 150 2 . 20 0. 7 . 12 o. 27620 0 0 0 0 0 151 - 2.20 0.269E-15 7.12 0. 27991 0 0 0 0 0 152 2 . 50 0. 7 . 69 0. 32320 0 0 0 0 0 153 - 2.50 0 . 306E-15 7.69 0. 32318 0 0 0 0 0 154 2 . 62 o. 6 . 56 0. 44400 0 0 0 0 0 155 1.50 o. 11.8 0. 26425 0 0 0 0 0 156 2.25 0. 6.56 0. 27706 0 0 0 0 0 157 - 1. 50 0 . 184E-15 11.8 0. 26483 0 0 0 0 0 158 0 . 111E-15 1.50 11 . 8 0. 26467 0 0 0 0 0 159 -2.25 0.276E-15 6 . 56 0. 28143 0 0 0 0 0 160 2 . 25 o. 12.0 0. 31929 0 0 0 0 0 NO . X,Y,Z LOCATION KESIZE NODE ELEM MAT REAL TYP ESYS 161 -2 . 25 0 . 276E-15 12.0 0. 31927 0 0 0 0 0 162 -2 . 20 0 . 269E- 15 12.0 o. 26545 0 0 0 0 0 163 2 . 20 0. 12 . 0 0. 2643 2 0 0 0 0 0 164 2.25 o. 11.8 0. 29555 0 0 0 0 0 165 -2.25 0.276E-15 11.8 o. 29553 0 0 0 0 0 166 1. 50 0. 11.9 0. 26227 0 0 0 0 0 167 0 . lllE- 15 1.50 11. 9 o. 26228 0 0 0 0 0 168 2 . 20 0. 11.8 o. 26426 0 0 0 0 0 169 - 2 . 20 0 . 222E-15 11 . 8 0. 26539 0 0 0 0 0 170 2.25 0. 7 . 12 0. 27704 0 0 0 0 0 171 -2 . 25 0 . 222E-15 7.12 0. 28091 0 0 0 0 0 MPA QA Form: OA-3.1-3. Rev. 0
MPR Associates, Inc.
MPR 320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 41 420-004-AAB-1 Revision: O 1 72 2 . 25 o. 7 . 69 o. 29424 0 0 0 0 0 173 -2.25 0.222E- 15 7 .69 0. 29422 0 0 0 0 0 174 - 1.50 0.184E-15 11.9 0. 26244 0 0 0 0 0 175 -2 . 62 0 . 321E-15 6.56 0. 44409 0 0 0 0 0 176 0.845 2 . 03 6.56 0. 27579 0 0 0 0 0 177 0.845 2 . 03 7.12 0. 27586 0 0 0 0 0 178 0. 845 2 . 09 6 . 56 o. 27580 0 0 0 0 0 179 0 . 84 5 2.09 7 . 12 0. 27582 0 0 0 0 0 180 - 0. 4 05 2.16 6 . 56 0. 27953 0 0 0 0 0 NO . X,Y , Z LOCATION KESIZE NODE ELEM MAT REAL TYP ESYS 181 -0 . 4 05 2.16 7 . 12 0. 27946 0 0 0 0 0 182 - 0.405 2.21 6 . 56 0. 27949 0 0 0 0 0 183 - 0.405 2 . 21 7.12 0. 27947 0 0 0 0 0 184 0 . 8 4 5 2 . 22 6.56 0. 11213 0 0 0 0 0 185 0.845 2.22 7.12 0. 42559 0 0 0 0 0 186 - 0. 4 05 2 . 35 6.56 o. 11186 0 0 0 0 0 187 -0 . 4 05 2 . 35 7.12 0. 42818 0 0 0 0 0 188 0 . 8 4 5 2.35 7.12 0. 43197 0 0 0 0 0 189 -0.405 2. 4 7 7.12 o. 43163 0 0 0 0 0 190 0 . 845 2.22 7.56 0. 44925 0 0 0 0 0 191 0.845 2 . 35 7 . 56 0. 43306 0 0 0 0 0 192 - 0 . 405 2.35 7.56 0. 44895 0 0 0 0 0 193 - 0.405 2.47 7 . 56 0. 43310 0 0 0 0 0 194 0.8 4 5 2.09 7.56 o. 34912 0 0 0 0 0 195 -0. 4 05 2 . 21 7 . 56 0. 34717 0 0 0 0 0 196 0.8 4 5 2.03 7.56 0. 34743 0 0 0 0 0 197 - 0. 4 05 2.16 7.56 0. 34718 0 0 0 0 0 198 2 . 62 0. 8.06 o. 32437 0 0 0 0 0 199 - 2.62 0.321E- 15 8.06 o. 32577 0 0 0 0 0 200 -2 . 25 0.536E-16 7 . 81 o. 29528 0 0 0 0 0 NO. X,Y,Z LOCATION KESIZE NODE ELEM MAT REAL TYP ESYS 201 - 2.50 0.306E- 15 8 . 06 o. 32457 0 0 0 0 0 202 0 . 500 o. 12.0 0. 26189 0 0 0 0 0 203 0. 27 8E-16 0 . 500 12.0 o. 26183 0 0 0 0 0 204 -0.500 0 . 612E- 16 12 . 0 0. 26180 0 0 0 0 0 205 2 . 50 o. 8 . 06 o. 32441 0 0 0 0 0 206 - 0.500 0 . 296E-15 11.9 0. 26181 0 0 0 0 0 207 0.500 0 . 518E-15 11.9 o. 26195 0 0 0 0 0 208 -2.25 0.536E- 16 11. 7 o. 28384 0 0 0 0 0 209 2 . 62 o. 7 . 12 0. 43104 0 0 0 0 0 210 -2 . 62 0 . 321E-15 7.12 o. 43105 0 0 0 0 0 211 -2.20 0.222E-15 1 1.7 0. 28394 0 0 0 0 0 212 -2 . 20 0 . 222E- 15 7.81 0. 28423 0 0 0 0 0 213 - 2. 07 0. 875 8.69 0. 29530 0 0 0 0 0 214 - 2.02 0.875 8.69 o. 28425 0 0 0 0 0 215 -2 . 07 0 .875 10 . 8 o. 28381 0 0 0 0 0 216 -2 . 02 0.875 10.8 o. 28382 0 0 0 0 0 217 -1 . 44 1.00 6.31 0. 9692 0 0 0 0 0 218 - 1. 44 o. 6 . 31 0. 10079 0 0 0 0 0 219 -2 . 38 0 . 291E-15 12 . 2 0. 33311 0 0 0 0 0 220 2.38 0. 12 . 2 0. 33313 0 0 0 0 0 NO . X,Y,Z LOCATION KESIZE NODE ELEM MAT REAL TYP ESYS 221 2.62 o. 7.69 0. 32261 0 0 0 0 0 222 - 2.62 0.321E-l5 7 . 69 0. 32262 0 0 0 0 0 223 0. 0. 12.l 0. 32855 0 0 0 0 0 22 4 2.50 0. 12 . 1 0. 34327 0 0 0 0 0 225 -2 . 50 0 . 306E-15 12.1 o. 34325 0 0 0 0 0 226 2.50 0. 12.2 o. 34441 0 0 0 0 0 227 -2.50 0 . 306E-15 12.2 0. 34449 0 0 0 0 0 228 o. o. 12 . 2 0. 33421 0 0 0 0 0 229 2.38 0. 12.1 0. 32856 0 0 0 0 0 230 -2 . 38 0.222E- 15 12 . 1 o. 32872 0 0 0 0 0 231 1.00 1.00 6.31 0. 10036 0 0 0 0 0 MPR QA Form: OA*3.1*3. Rev. 0
MPR Associates, Inc.
MPR 320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 42 420-004-AAB-1 Revision: 0 232 1.00 o. 6.31 o. 10019 0 0 0 0 0 233 0.875 o. 7.0 4 o. 39568 0 0 0 0 0 234 1.00 0. 7.04 0. 39562 0 0 0 0 0 235 1.00 1.00 7 . 04 0. 39611 0 0 0 0 0 MPR QA Form: OA-3.1*3. Rev. 0
MPR Associates, Inc.
mMPR 320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 43 420-004-AAB-1 Revision: O ATTACHMENT 2 Material Property Listing MPR QA Form: QA-3.1-3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 44 420-004-AAB-1 Revision: 0 LIST MATERIALS 1 TO 4 BY 1 PROPERTY= ALL PROPERTY TABLE EX MAT= 1 NUM. POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70 . 000 0 , 28120E+08 200.00 0 . 27620E+08 300 . 00 0 . 27160E+08 400.00 0.26640E+08 500.00 0,26070E+08 600 . 00 0.25440E+08 700.00 0.24770E+08 800 . 00 0 . 24060E+08 900 . 00 0 . 23310E+08 1000 . 0 0 . 22530E+08 1100.0 0.21720E+08 1200 . 0 0.20890E+08 1300 . 0 0.20030E+08 1400.0 0 . 19170E+08 1500 . 0 0.18300E+08 1600.0 0 . 17420E+08 1700.0 0 . 16540E+08 PROPERTY TABLE NUXY MAT= 1 NUM. POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70.000 0 . 26390 200.00 0.27110 300 . 00 0 . 27610 400 . 00 0.28080 500.00 0.28510 600 . 00 0 . 28920 700.00 0.29310 800.00 0 . 29700 900 . 00 0 . 30080 1000 . 0 0 . 30460 1100 . 0 0.30860 1200 . 0 0.31270 1300.0 0 . 31710 1400.0 0 . 32170 1500. 0 0 . 32680 1600.0 0.33240 1700.0 0 . 33840 PROPERTY TABLE ALPX MAT= 1 NUM. POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70.000 0 . 84810E-05 200.00 0.87860E-05 300.00 0 . 89980E- 05 400 . 00 0 . 91930E-05 500.00 0.93710E-05 600.00 0.95340E- 05 700 . 00 0 . 968408-05 800.00 0.98230E-05 900 . 00 0 . 99510E-05 1000.0 0 . 10070E-04 1100 . 0 0 . 10180E-04 1200 . 0 0 . 10290E- 04 1300.0 0.10390E-04 1400 . 0 0.10490E-04 1500.0 0.10590E-04 1600.0 0 . 10690E- 04 1700.0 0.10790B- 04 PROPERTY TABLE DENS MAT= 1 NUM. POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70.000 0 . 29020 200.00 0 . 28900 30 0. 00 0.28800 400 . 00 0 . 28710 500.00 0 . 28620 600.00 0 . 28530 700.00 0 . 28430 800 . 00 0 . 28340 900.00 0 . 28250 1000 . 0 0 . 28150 1100 . 0 0 . 28060 1200.0 0 . 27970 1300 . 0 0 . 27880 1400.0 0 . 27780 1500.0 0.27690 1600 . 0 0 . 27600 1700 . 0 0 . 27500 PROPERTY TABLE KXX MAT= 1 NUM. POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70 , 000 0 . 19840E-03 200 . 00 0.21520E-03 300.00 0 . 22750E-03 400.00 0 . 23950E- 03 500 . 00 0 . 25110E-03 600.00 0 .26240E-03 700.00 0.27330E-03 800 . 00 0.28400E-03 900.00 0 . 29450E-03 1000 . 0 0 . 30480E-03 1100.0 0 , 31490E- 03 1200 . 0 0.32480E-03 1300 . 0 0.33470E- 03 1400.0 0.3 4450E-03 1500.0 0 . 35430E-03 1600 . 0 0 . 36410E-03 1700.0 0.373908-03 PROPERTY TABLE C MAT= 1 NUM . POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70.000 0.11410 200 . 00 0 . 12020 300 . 00 0.124 10 400.00 0.12740 500.00 0 .13020 600 . 00 0 . 13260 700 . 00 0.13470 800.00 0 . 13640 900.00 0 .13800 1000 . 0 0 . 13950 1100.0 0 . 14100 1200. 0 0.14260 1300.0 0 . 14430 1400.0 0 , 14620 1500 . 0 0 . 14850 1600.0 0.15110 1700 . 0 0.15420 PROPERTY TABLE EMIS MAT= 1 NUM . POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70.000 1.0000 200.00 1. 0000 300 . 00 1. 0000 40 0 .00 1.0000 500.00 l.0000 600.00 1.0000 700.00 1. 0000 800 , 00 1 .0000 900.00 l. 0000 1000.0 1 . 0000 1100.0 1. 0000 1200 . 0 l.0000 1300.0 1 . 0000 1400.0 1. 0000 1500 . 0 1. 0000 1600.0 1. 0000 1700.0 1. 0000 MPR OA Form: OA-3. 1-3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 45 420-004-AAB- 1 Revision: O PROPERTY TABLE REFT MAT= 1 NUM. POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70 . 000 70.000 200.00 70.000 300.00 70.000 400 . 00 70 . 000 500 . 00 70 . 000 600 . 00 70.000 700.00 70.000 800.00 70 . 000 900 . 00 70.000 1000.0 70.000 1100.0 70.000 1200 . 0 70 . 000 1300.0 70.000 1400.0 70.000 1500 . 0 70.000 1600.0 70 . 000 1700 . 0 70. 000 PROPERTY TABLE EX MAT= 2 NUM . POINTS= 12 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 77 . 000 0 . 29500E,.08 212.00 0 . 26100E,.08 392 . 00 0.22200E,.08 572.00 0 . 18600E,.08 752. 00 0.14300E,.08 932 . 00 0 . 10100E+08 1112 . 0 0 . 57800E+07 1220.0 0.33700E+07 1231.0 0. 57800E+07 1292.0 0.50600E+07 1429 . 0 0.83900E+06 1472 . 0 0.83900E+06 PROPERTY TABLE NUXY MAT= 2 NUM. POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70.000 0 . 22000 200 . 00 0.22000 300 . 00 0 . 22000 400 . 00 0.22000 500.00 0.22000 600.00 0 . 22000 700.00 0.22000 800 . 00 0.22000 900 . 00 0.22000 1000.0 0 . 22000 1100.0 0 . 22000 1200.0 0.22000 1300 . 0 0 . 22000 1400.0 0 . 22000 1500 . 0 0 . 22000 1600.0 0.22000 1700.0 0.22000 PROPERTY TABLE ALPX MAT= 2 NUM. POINTS= 5 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 77.000 0 . 66700E-05 1161.0 0 . 15600E- 04 1341.0 0 . 15600E-04 1656 . 0 O. lllOOE-04 2061 . 0 O. lllOOE-04 PROPERTY TABLE DENS MAT= 2 NUM . POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70 . 000 0.68910 200.00 0.68680 300.00 0.68500 400 . 00 0.68320 500.00 0 . 68130 600.00 0.67920 700.00 0.67690 800.00 0.67460 900.00 0.67210 1000 . 0 0 . 66930 1100 . 0 0.66490 1200 . 0 0 . 66050 1300.0 0 . 65600 1400.0 0.65220 1500 . 0 0 . 64860 1600 . 0 0 . 64520 1700 . 0 0 . 64160 PROPERTY TABLE KXX MAT= 2 NUM . POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70 . 000 0 . 35710E-03 200.00 0 . 40210E- 03 300.00 0 . 41600E- 03 400.00 0 . 43340E- 03 500.00 0.45130E-03 600.00 0.47010E- 03 700 . 00 0 . 49320E-03 800.00 0.51780E-03 900 . 00 0 . 54180E-03 1000 . 0 0.56120E-03 1100.0 0.56110E-03 1200.0 0.60400E-03 1300 . 0 0 . 60370E-03 1400.0 0 . 60390E-03 1500 . 0 0.60450E-03 1600.0 0 . 60490E-03 1700.0 0 . 60530E-03 PROPERTY TABLE C MAT= 2 NUM. POINTS,. 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70 . 000 0.27900E-01 200.00 0.29100E- 01 300 . 00 0 . 30100E-01 400.00 0 . 31500E-01 500 . 00 0 . 32900E-01 600 . 00 0.34300E-01 700.00 0.36200E- 01 800 . 00 0.38100E- Ol 900 . 00 0 . 40000E-01 1000.0 0 . 41600E-01 1100 . 0 0.41900E-Ol 1200.0 0. 42100E- Ol 1300.0 0.42400E-01 1400 . 0 0.42700E-Ol 1500 . 0 0 . 42900E- 01 1600.0 0.43200E-Ol 1700.0 0.43500E-01 PROPERTY TABLE EMIS MAT= 2 NUM. POINTS;: 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70.000 1.0000 200.00 1.0000 300 . 00 1.0000 400 . 00 1.0000 500.00 1 . 0000 600 . 00 1 . 0000 700.00 1.0000 800.00 1.0000 900.00 1. 0000 1000.0 1 . 0000 1100.0 1.0000 1200 . 0 1.0000 1300.0 1.0000 1400 . 0 1 . 0000 1500.0 1.0000 1600 . 0 1 . 0000 1700 . 0 1. 0000 MPR QA Form: QA-3. i -3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 46 420-004-AAB-1 Revision: 0 PROPERTY TABLE REFT MAT= 2 NUM. POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70.000 70.000 200.00 70 . 000 300 . 00 70.000 400 . 00 70.000 500.00 70 . 000 600.00 70.000 700.00 70.000 800.00 70.000 900.00 70.000 1000 . 0 70 . 000 1100 . 0 70 . 000 1200.0 70.000 1300.0 70 . 000 1400.0 70.000 1500.0 70.000 1600.0 70.000 1700 . 0 70 . 000 PROPERTY TABLE EX MAT: 3 NUM. POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70.000 1000 . 0 200.00 1000 . 0 300.00 1000 . 0 400.00 1000.0 500.00 1000.0 600 . 00 1000.0 700.00 1000 . 0 800.00 1000.0 900 . 00 1000.0 1000 . 0 1000 . 0 1100 . 0 1000 . 0 1200.0 1000 . 0 1300.0 1000.0 1400 . 0 1000 . 0 1500.0 1000.0 1600.0 1000.0 1700 . 0 1000.0 PROPERTY TABLE NUXY MAT= 3 NUM. POINTS: 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70 . 000 0.3 000 200.00 0 . 30000 300.00 0 . 30000 400.00 0 . 3 000 500.00 0.30000 600.00 0 . 30000 700 . 00 0 . 30000 800 . 00 0 . 30000 900 . 00 0.30000 1000.0 0 . 30000 1100.0 0.30000 1200.0 0 . 30000 1300 . 0 0 . 30000 1400.0 0 . 30000 1 500 . 0 0.30000 1600 . 0 0 . 30000 1700.0 0.30000 PROPERTY TABLE ALPX MAT= 3 NUM. POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70.000 0 . 11300E- 04 200 . 00 0 . ll300E-04 300 . 00 O. ll300E-04 400.00 O. ll300E-04 500.00 O. ll300E-04 600 . 00 O. ll300E-04 700.00 0 . 11300E- 04 800 . 00 0 . l1300E- 04 900 . 00 O. ll300E- 04 1000.0 0 . ll300E-04 1100.0 O.ll300E-04 1200 . 0 O. ll300E-04 1300.0 O.ll300E-04 1400 . 0 O.ll300E-04 1500 . 0 O.ll300B- 04 1600.0 O. ll300E-04 1700.0 0.11300E-04 PROPERTY TABLE DENS MAT: 3 NUM. POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70.000 0.30600 200.00 0 . 30600 300 . 00 0.30600 400.00 0 . 30600 500.00 0 . 30600 600.00 0 . 30600 700 . 00 0.30600 800.00 0 . 30600 900 . 00 0.30600 1000.0 0.30600 1100.0 0 . 30600 1200 . 0 0.30600 1300.0 0.30600 1400.0 0 . 30600 1500 . 0 0.30600 1600.0 0.30600 1700 . 0 0. 30600 PROPERTY TABLE KXX MAT: 3 NUM. POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70.000 0.15509E-02 200 . 00 0.15509E-02 300 . 00 0 . 15509E-02 400,00 0.15509E- 02 500.00 0 . 15509E-02 600.00 0.15509E-02 700.00 0.15509E-02 800 . 00 0 . 15509B- 02 900 . 00 0.15509E-02 1000 . 0 0.15509E-02 1100.0 0 . 15509E-02 1200 . 0 0.15509E-02 1300 . 0 0 . 15509E- 02 1400 . 0 0 . 15509E-02 1 500 . 0 0 . 15509B- 02 1600.0 0 . 15509B-02 1700.0 0 . 15509E-02 PROPERTY TABLE C MAT: 3 NUM. POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70 . 000 0 . 90000E- 01 200 . 00 0 . 90000B-01 300 . 00 0.90000B - 01 400 , 00 0 . 90000E-01 500.00 0 . 90000E-Ol 600 . 00 0 . 90000B-01 700.00 0.90000B-Ol 800.00 0 . 90000E- 01 900 . 00 0.90000B-01 1000.0 0.90000E-Ol 1100.0 0 . 90000B-01 1200 , 0 0.90000E-Ol 1300,0 0.90000E- 01 1400.0 0.90000E- 01 1500 . 0 0 . 90000E- Ol 1600 . 0 0.90000E-Ol 1700 . 0 0.90000E-0 1 PROPERTY TABLE EMIS MAT= 3 NUM , POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA MPR QA Form: OA-3.1*3. Rev. 0
MPR Associates, Inc.
320 King Street Alexandria, VA 22314 Calculation No. Prepared By Checked By Page: 47 420-004-AAB-1 Revision: 0 70.000 1. 0000 200.00 l.0000 300.00 1.0000 400.00 1.0000 500.00 1.0000 600.00 l . 0000 700 . 00 1.0000 800.00 1. 0000 900.00 1.0000 1000.0 1.0000 1100 . 0 1.0000 1200.0 1. 0000 1300. 0 1. 0000 1400.0 1.0000 1500.0 1. 0000 1600.0 l.0000 1700.0 1.0000 PROPERTY TABLE REFT MAT= 3 NUM. POINTS= 17 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 70.000 70 . 000 200.00 70.000 300.00 70.000 400.00 70.000 500.00 70.000 600.00 70.000 700.00 70.000 800.00 70 . 000 900 . 00 70.000 1000.0 70.000 1100.0 70 . 000 1200 . 0 70.000 1300.0 70 . 000 1400.0 70.000 1500.0 70 .0 00 1600 . 0 70 . 000 1700.0 70.000 PROPERTY TABLE EX MAT= 4 NUM. POINTS= 4 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 32 . 000 0.59470E+08 752 . 00 0 . 57430E+08 1472.0 0 . 54820E+08 2192 . 0 0.51920E+08 PROPERTY TABLE NUXY MAT= 4 NUM. POINTS= 4 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 32.000 0.28000 752 . 00 0.28300 1472.0 0 .287 50 2192.0 0.29500 PROPERTY TABLE ALPX MAT= 4 NUM . POINTS= 4 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 32.000 0.244448-05 752 . 00 0 . 244448-05 1472.0 0 . 244448-05 2192.0 0.244448-05 PROPERTY TABLE DENS MAT= 4 NUM . POINTS= 7 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 80.330 0 . 69620 260.33 0.69510 440 .33 0 . 69440 620.33 0.69330 980 . 33 0.69110 1340.3 0.68930 1700.3 0 . 68710 PROPERTY TABLE KXX MAT= 4 NUM. POINTS= 7 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 32.000 0,22243E-02 212.00 0 . 20221E-02 932 . 00 0.16021E-02 1832 . 0 0 .1 32218-02 2732.0 0.15243E- 02 3632 . 0 0 .18199E-02 4352.0 0.19599E-02 PROPERTY TABLE C MAT= 4 NUM . POINTS= 6 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 80.330 0.32200E-Ol 260.33 0.32720E-Ol 440,33 0.33190E-Ol 620 . 33 0.33440E-01 980.33 0.34390E-01 1340 . 3 0.35350E-01 PROPERTY TABLE EMIS MAT= 4 NUM. POINTS= 4 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 32.000 1.0000 752.00 1.0000 1472.0 1. 0000 2192 . 0 1.0000 PROPERTY TABLE REFT MAT= 4 NUM. POINTS= 4 TEMPERATURE DATA TEMPERATURE DATA TEMPERATURE DATA 32.000 70.000 752.00 70.000 1472.0 70 . 000 2192.0 70.000 MPR QA Form: QA-3.1-3. Rev. 0
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc.
April 2023 - Revision 14 8 urli ngton, Massachusetts Page 2-45 2.12.4 USDOT Special Form Certificate USA/0179/S-96 Revision 13
East Building, PHH-23 1200 New Jersey Ave, SE Washington , D.C . 20590 U.S. Department IAEA CERTIFICATE OF COMPETENT AUTHORITY of Transportation SPECIAL FORM RADIOACTIVE MATERIALS Pipeline and CERTIFICATE USA/0179/S-96, REVISION 13 Hazardous Materials Safety Administration This certifies that the source described has been demonstrated to meet the regulatory requirements for special form radioactive material as prescribed in the regulations of the International Atomic Energy Agency 1 and the United States of America 2 for the transport of radioactive material.
1. Source Identification - QSA Global, Inc. Series 900 Iridium Capsule.
2. Source Description - Cylindrical single encapsulation made of Type 304 or Type 304L stainless steel and tungsten inert gas or laser welded. Approximate exterior dimensions are 5. 2 mm ( 0. 205 in.) in diameter and 15.5 mm (0.611 in.) in length. Inside dimensions vary, but minimum wall thickness is 0. 71 mm ( 0. 028 in.) . Construction shall be in accordance with attached QSA Global, Inc. Drawing No.
900 CAP, Rev. C. Source capsules utilizing Type 304 stainless steel must be manufactured after the date of this certificate.
3. Radioactive Contents No more than 8.88 TBq (240.0 Ci) of Iridium-192 in solid, metallic form.
4. Management System Activities Records of Management System activities required by Paragraph 306 of the IAEA regulations shall be maintained and made available to the authorized officials for at least three years after the last shipment authorized by this certificate. Consignors in the United States exporting shipments under this certificate shall satisfy the requirements of Subpart H of 10 CFR 71.
5. Expiration Date This certificate expires on March 31, 2025.
Previous editions which have not reached their expiration date may continue to be used.
1 "Regulations for the Safe Transport of Radioactive Material, 2012 Edition, No. SSR-6" published by the International Atomic Energy Agency (IAEA),
Vienna, Austria.
2 Title 49, Code of Federal Regulations, Parts 100-199, United States of America.
- - - - - -- - - - - - - ~
(- 2 -)
CERTIFICATE USA/0179/S-96, REVISION 13 This certificate is issued in accordance with paragraph(s) 804 of the IAEA Regulations and Section 173 . 476 of Title 49 of the Code of Federal Regulations , in response to the January 10 , 2020 petition by QSA Gl obal ,
Inc ., Burlington , MA , and in consideration of other information on file in this Office .
Certified By :
March 04 , 2020 William Schoonover (DATE)
Associate Administrator for Hazardous Materials Safety Revision 13 - Issued to authorize the manufacture of source capsules from Type 304 stainless steel and to extend the expiration date .
TUNGSTEN INERT GAS OR LASER WELDED
(/).205
.155
- - - - - .507 - - -
- - - - - - .611 - - - -
NOTES:
1. INTERNAL VOID VOLUME TO BE 0.010 ml OR GREATER
£ 2. MATERIAL: 304 OR 304L STAINLESS STEEL
3. INNER CAVITY DIMENSIONS MAY VARY. METALLIC SPAC ERS, SPRINGS AND GUARDS WHICH SECURE AND/OR LOCATE THE RADIOACTIVE MATERIAL WITH IN THE CAPSULE MAY BE USED
4. MINIMUM WALL THICKNESS TO BE 0.028
£ 5. TOLERANCES: FRACTIONS +/- 1/8 x.x +/- 0.12 UNLESS OTHERWISE SPECIFIED:
x.xx +/- 0.06 ALL DIMENSIONS ARE INCHES, TOLERANCE +/-l / 16 x.xxx +/- 0.020 QSAGLOBAL. DESCRIPTIVE DRAWING 40 NORTH AVE, BURLINGTON, MA 01803 ERF # TITLE 900 SERIES CAPSULE REV 4088 C
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington , Massachusetts Page 3-1 Section 3 - THERMAL EVALUATION 31 Description of Thermal Desigr The Model 865 transport package is a completely passive thermal device having no mechanical cooling system or relief valves. Cooling of the transport package is through free convection and radiation. There are no specific cooling or insulating design features . Pressure relief of the container is not necessary since, during the thermal test, the construction is no longer air tight and will allow negligible venting to the atmosphere based on the amount of trapped air within the package available for venting during the thermal test.
The containment system for the Model 865 transport package is the radioactive source capsule referred to in Section 4.1. The maximum output activity for this package is 240 Ci of lr- 192. Accounting for source absorption, this equals a maximum content activity of 552 Ci of lr-192. The corresponding decay heat generation rate for the content activity is approximately 4.8 Watts (See Table 1.2.A). The maximum decay heat has been adjusted to account for the content activity of the source. Actual content to output activity varies based on the capsule configuration as well as variations in isotope self-absorption. A factor of 2.3 was used for lr-192 to convert output activity to content activity as this factor reflects the worst case variation for lr-192 sources transported in this package. The thermal evaluations are based on the decay energy of lr-192.
3.1.1 Design Features The Model 865 package is described in Section 1. The container uses depleted uranium shielding. The depleted uranium is fully enclosed in the welded steel structure and endplates which are attached by welding. This construction prevents oxidation by severely limiting oxygen from reaching the depleted uranium shield.
3.1.2 Decay Heat of Contents From Table 1.2.A , a maximum of 4.8 Watts of decay energy is available to be absorbed by the package.
3.1 .3 Summary Tables of Temperatures Table 3.1.A: Summary Table of Temperatures Temperature Model 865 Package Comments Condition t--------
lnsolation (38°C in full _su_n~-----------~-~----+-S_e_ct_io_n_3_.4_.1_.1 _ __,
Decay Heatino (38°C i_n_sh_a_d_e..__ _ _ _ _ _ _ _4_4_ °C__._1_1_1°_F..____ _ _ _s_e_ct_io_n_3_.4_.1_.2_-----1 Fire Test During 800°C 1,472°F Post-Fire (Maximum T_em_p,_e_ra_t_ur_e_ _ ___.__ _ __8_0_0°-'C_,_1"-,4_7_2_°F_,__ ___._ _ _ _ _ ___,
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 3-2 3.1.4 Summary Tables of Maximum Pressures The Model 865 container is an air tight construction unless subjected to the thermal test conditions under 10 CFR 71 .73(c)(4). Evaluation of the container pressures under the thermal test is included in Section 3.4.2.
Any pressure generated within the special form source is significantly below that which would be generated during the Hypothetical Accident Conditions thermal test, which is shown in Section 2.7.4 to result in no loss of structural integrity or containment.
Table 3.1.B: Summary Table of Maximum Pressures Normal Conditions Fire Conditions Package 62.9°C (145.2°F) 800°C (1 ,472°F) Comments Configuration Pressure Develo ed Pressure Develo ed Model 865 0 psig O psig None 32 Material Properties and Component Spec1f1cat1ons 3.2.1 Material Properties Table 3.2.A lists the relevant thermal properties of the important materials in the transport package. The sources referred to in the last column are listed below the table.
Table 3.2.A: Thermal Properties of Principal Transport Package Materials Material Density Melting/Combustion Thermal Source (g/cm 3) Temperature Expansion 1 (um/mK)
Depleted 1, 13s 0 c 18.6 12 Reference #1 Uranium (2,075°F) 900-1 ,025°C Brass 8.3- 8.75 18.7 -21 .2 Reference #1 (1 ,652-1,877°F)
Stainless Steel-1,400-1,450°C Type 304 7.9 17 Reference #1 Type 303 (2,552-2 ,642°F) 3,410°c Tungsten 19.3 4.6 Reference #2 (6, 170°F) 980-1,050°C Bronze 7.7 - 8.89 6.4-21.2 Reference #1 (1,796-1,922°F) 1NOTE: The thermal expansion of the materials in this table are temperature dependent.
Operating temperature range of nitrile rubber 'O' rings is -40°F to +125°F.
Resource references :
1. Metals Handbook. American Society for Metals, 8th Edition.
2. Metals Handbook Desk Edition. American Society for Metals.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington , Massachusetts Page 3-3 3.2 .2 Component Specifications All components are specified and described on the descriptive drawings included in Appendix 1.3.
3.3 General Considerations 3.3.1 Evaluation by Analysis Evaluations by analysis are described in the section they apply to in this Safety Analysis Report or when applicable in the Test Plan contained in Appendix 2.12.
3 .3.2 Evaluation by Test Evaluations by direct testing are documented in the Test Plan contained in Appendix 2.1 2 or are described in the section they apply to in this Safety Analysis Report.
3.4 Thermal Evaluation Under Normal Conditions of Transport 3.4.1 Heat and Cold 3.4.1.1 lnsolation and Decay Heat This analysis determines the maximum surface temperature produced by solar heating of the Model 865 transport package loaded at maximum activity in accordance with 10 CFR 71. 71 (c)(1) and Table 13 of IAEA TS-R-1 and Table 12 of SSR-6. This will be compared to the Normal Transport test conditions temperature range to determine which is the most onerous for thermal stress considerations.
The model consists of taking a steady state heat balance over the surface of the transport package. The following design analysis calculates the steady state surface temperature of a cylindrical package subjected to insolation and self-heat. The analysis is based on recognized heat transfer theory and specifically, that the total heat input due to the self-heat of the radioactive contents and the insolation energy absorbed must balance the heat loss due to convection and emitted radiation from the package surface.
+
L 0 Figure 3.4.A - Model of Cylindrical Package for Heat Analysis
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 3-4 In order to assure conservatism , the following assumptions are made:
Basic Input Parameters:
Max Content Activity , A= 552 Ci of lr-192 (240 Ci x 2.3 for self absorption)
The surface finish of the package is light silvery stainless steel Length of Package, L = 0.311 m Diameter of Package, = 0.127 m o-a Stefan-Boltzmann constant, cr = 5.669 x 1 W/m 2 K4 By Kirchhoff's Law Emissivity, E = Absorptivity, a= 0.44 (Ref: Heat Transmission, 3rd Edition - McAdams)
Ambient Temperature, TA= 311 K Area of cylinder ends, AcE = 0.025 m2 Total Area of curved surfaces, Acs = 0.124 m 2 Decay Heat Input Oor = 4.8 W
The transport package is assumed to undergo free radiative heat transfer from the top and sides. The transport package is assumed to undergo free convective heat transfer and radiative heat transfer from the top, bottom, and sides.
To maximize the temperature of the stainless steel cylinder surface temperature, the inside transport package faces are considered perfectly insulated so there is no conduction into the transport package. In use, the inside transport package will act as a heat sink during daylight hours and a heat source during the night, but this will be ignored for this calculation.
The transport package is approximated as a right cylinder with dimensions, 5 inches (0.127 m) in diameter and 12 1/4 inches (0.311 m) long (approximation of the solid length of the cylinder).
The surfaces of the transport package are assumed to be solid. The faces are considered to be sufficiently thin so that no temperature gradients exist in the faces .
The worst case decay heat load (4.8 Watts) is added to the solar heat input load (see assumptions in Section 1.2.2).
The following heat calculations are based on the steady-state equilibrium relationship between the heat gained by the package and the heat lost.
Heat Input, QIN = Heat Output, Oour in the steady-state QIN = Solar Heat Input + Decay Heat Oour = Heat loss by Radiation and Convection O1E = Heat input due to insolation falling on ends O1c = Heat input due to insolation on curved surfaces, Solar Heat Input = a(O1E + O1c), where a is the absorptivity
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 3-5 The solar heat input is the combined solar heating of the top horizontal surface and the vertical side surface. The insolation data, provided in 10 CFR 71 .71(c)(1), is found in Table 3.4.A Table 3.4.A: lnsolation Data Surface lnsolation for a 12 hour1.388889e-4 days 0.00333 hours 1.984127e-5 weeks 4.566e-6 months period (g-cal/cm 2 or W/m 2 )
Horizontal base None Other horizontal flat surfaces 800 Non-horizontal flat surfaces 200 Curved surfaces 400 Practically all solid materials used in engineering are opaque to thermal radiation (even glass is only transparent to a fairly narrow range of wavelengths), and thermal radiation is in fact either reflected or absorbed within a very shallow depth of matter. Thus, for solids it is possible to neglect transmissivity and write:
reflectivity, p + absorptivity, a. = 1 i.e., the sum of the radiation reflected and absorbed by the material is equal to the total incident energy. Since the reflected energy does not contribute to the heat energy contained within the system, or package, it is not necessary to consider it in the analysis. However, the absorptivity of the material is the fraction of the total incident energy entering the system, which in this case is the heat input due to insolation.
Heat input due to insolation falling on ends, 01E = 200 W/m 2 xAcE = 5 W Heat input due to insolation on curved surfaces, 01c = 400 W/m 2 xAcs =49.6 W In the case of a cylindrical package standing on the ground, the top surface can radiate freely to the surroundings assumed to be effectively at ambient temperature. For the vertical surface, the upper 90° of azimuth can radiate freely to the surrounding air in the same way as the top surfaces. However, some radiation emitted in the lower 90° will be intercepted by the ground and vice versa. Owing to the complex nature of radiation interchange, and allowing for this asymmetrical characteristic, a geometrical factor g is assumed in the following analysis.
For curved surfaces, gc = 0.5 For vertical surfaces, gs = 0.5
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 3-6 Radiation heat transfer from curved surfaces, Radiation heat transfer from end surface, Heat transfer by convection is complex as it represents a dynamic process involving fluid flow. Newton introduced a quantity known as the "heat transfer coefficient" represented by the symbol, h. From Newton's Law of cooling due to heat loss by convection :
Oc = hA[Tv.r TA]
Consider the curved surface of the cylinder:
Cylindrical Surface Convection, 0cc = HcAcs[Tv.r TA]
Where the free convection coefficient, He = 1.32{(1/tj>) 114 (Tv.r TA) 114} (Ref 1)
Therefore, 0cc = 0.18(Tv-rTA) 1*25 Considering the vertical surfaces of the cylinder:
Vertical End Surface Convection, OcE = HsAcE{Tv.r TA}
Where the free convection coefficient, Hs = 1.42{( 1/tj>) 114 (Tv.r TA) 114} (Ref. 1)
Therefore, OcE = 0.227 (Tv.rTA) 1*25 Total Heat Input, Q,N = a.(Q,E + O,c) + Oor = 28.8 W Total Heat Output, Oour = (0Rc + QRE) + (0cc + OcE) 28.8 W = 1.45x 10*9 {Tw4 - (311)4} + 3.12x 1o- 10{Tw4 - (311)4} + 0.407(T w- (311)) 1*25 28.8 W = 1.76x 10*9{Tw4 - (311)4} + 0.407(Tw- (311)) 1*25 Iteration of this relationship yields a maximum wall temperature (T w) of 62 .9°C (145.2°F). This temperature would constitute the most onerous Normal Transport thermal condition. Based on the package materials of construction, this temperature will not be sufficient to adversely affect the package containment or shielding integrity. As such the package complies with the requirements of this section.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 3-7
References:
1. Engineering Thermodynamics, Work & Heat Transfer - 4th Edition. , Rogers
& Mayhew.
2. Heat Transmission, 3rd Edition - McAdams.
3.4.1.2 Still Air (shaded) Decay Heating This analysis calculates the maximum surface temperature of the Model 865 package in the shade (i.e., no insolation effects), assuming an ambient temperature of 38°C (100°F), per 10 CFR 71.43(g) .
The same assumptions from Section 3.4.1.1 are used . To assure conservatism, the following additional assumptions are made:
a. The entire decay heat (4.8 W) is deposited in the exterior surfaces of the package.
b. The interior of the package is perfectly insulated and heat transfer occurs only from the exterior surface to the environment.
c. The only heat transfer mechanism is free convection.
Using these assumptions, the maximum wall temperature T w is found using:
T w = (q/hA) + TA Where:
q = 4.8 W (heat deposited per unit time on the package surface) h = 5 W/m 2 K (free convection heat transfer coefficient for air)
(Reference Fundamentals of Heat and Mass Transfer, F.P.
lncropera, 4 th Edition, 1996)
A= 0.149 m2 (surface area of the package)
TA = 3, 11 °K (ambient air temperature of 38°C)
Solving for T w produces a maximum wall temperature (T w) of 44°C (111 °F). It is demonstrated that the package surface temperature will not exceed the limit of 50°C (122°F) allowed by 10 CFR 71.43(g) and IAEA TS-R-1 ,I 617 and SSR-6 ,I 619.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 3-8 3.4.1.3 Cold Effected Materials There are no components of the Model 865 that have increased susceptibility to failure by any mechanism at ambient temperatures of -40°C. Though the tungsten source rod can exhibit brittle tendencies, the reduction in temperature will not adversely affect the relative brittleness of the tungsten rod , therefore the package complies with the requirements of this section.
All materials exhibit some contraction due to lower temperatures. However, in this limited temperature range, the Model 865 was not adversely affected as all specimens passed the Normal and Hypothetical Accident drop, puncture and compression testing and maintained their structural integrity and shielding efficiency.
3.4.1.4 Model 865 Type B(U) Source Capsule Thermal Analysis This analysis demonstrates that the pressure inside the Model 865 source capsule, when subjected to the Hypothetical Accident Conditions of Transport thermal test, does not exceed the pressure which corresponds to the minimum yield strength at the thermal test temperature.
The source capsules used in the 865 are all special form tested and approved.
The thermal test for special form capsules involves heating the capsules at 800°C for at least 10 minutes and allowing the capsules to cool afterwards. Test capsules are tested for leak tightness after this test and must pass intact in order to achieve special form status.
Special form capsules are also brought up to the 800°C temperature and allowed to cool prior to integrity testing. The FEA demonstrated that the Model 865 will withstand the stresses induced by the thermal test and the special form capsules also demonstrate their ability to retain integrity at 800°C. Therefore, it is concluded that the container and contents meet the requirements of this section.
3.4.2 Temperatures Resulting in Maximum Thermal Stresses The temperature and pressure variations described in Sections 3.4.1 and 3.4.3 will not adversely affect the transport package during normal transport since the melting temperatures of all safety critical components are well above these temperatures and the package will experience no pressures sufficient to cause package failure. It is therefore concluded that the Model 865 transport package will maintain its structural integrity and shielding effectiveness under the normal transport thermal stress conditions.
3.4.3 Maximum Normal Operating Pressure Under normal conditions of transport, the maximum normal operating pressure (MNOP) is determined by the maximum heating of the shield encasement chamber from decay heat and insolation data given in 71.71 (c)(1 ). Table 3.1a gives the maximum normal conditions of transport temperature as 62.9°C (145.2°F). The shield encasement is
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 3-9 made at atmospheric pressure (15 psia) and room temperature (25°C or 77°F). Based on the ideal gas law for constant volume, the maximum normal operating pressure developed in the shield encasement is 18 psia or 3 psig. This pressure is insignificant to the Model 865 shield encasement structural integrity as demonstrated by the external pressure tests reaching 360 psig described in Section 2.6.4.
During the hypothetical accident condition fire test, the silver solder in the brass source tube assembly melts at about 600°C (1 , 112°F). When the silver solder melts, the heated air in the encasement will vent out through the source tube and then through the melted seals of the source actuator assembly. No pressure will buildup in the package under the Hypothetical Accident conditions. Containers will exhibit a pressure differential of O psi as they are vented to the atmosphere with no means for creating a pressure differential.
No other contributing gas sources are present.
3.5 Thermal Evaluation Under Hypothetical Accident Conditions 3 .5.1 Initial Conditions The thermal test was not performed. Rather, an assessment was performed to demonstrate that the thermal test would not create sufficient additional damage to the package that would cause it to fail final profile criteria.
Consideration of the principle materials of manufacture and their melting points indicates that they would not fail and shielding integrity would not be significantly degraded. (See Table 2.2.A).
The initial conditions used in the thermal evaluation of the Model 865 were based on the physical condition of the Test Specimens as summarized in Table 2.7.A. The Model 865, including the special form capsule, is assumed to reach the thermal test temperature of 800°C (1,472°F). At this temperature the nitrile rubber 'O' rings will have melted and charred. The resulting gases will have escaped the transport package through the space left by the melted gaskets/seals.
The nitrile rubber 'O' rings on the Model 865 will be destroyed when subjected to the Hypothetical Accident Conditions of Transport thermal test conditions. The other package materials, however, are suitable for use at 800°C (1,472°F) (see Table 3.2.1 .a).
The depleted uranium, which is susceptible to oxidation, is enclosed within stainless steel and would not be exposed to oxygen. The transport package will undergo no loss of structural integrity or shielding. The pressures generated have been demonstrated in the Finite Element Analysis in Section 2.12 to be less than the yield strength of the material and will not adversely affect the package integrity.
Damage incurred during the drop testing (4 foot, 30 foot and puncture) was insufficient to create any new, significant pathways for the ingress of oxygen. Oxygen ingress has been shown empirically to be the primary contributing factor in the oxidation of depleted uranium shields during thermal testing (see Section 2.7.4.).
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 3-10 3.5.2 Fire Test Conditions Not applicable.
3.5.3 Maximum Temperatures and Pressure See Sections 3.1.3 and 3.1.4. No pressures generated in the package during the thermal test will adversely impact the package integrity or containment.
3.5.4 Temperatures Resulting in Maximum Thermal Stresses The temperature and pressure variations described in Sections 3.4.1 and 3.4.3 will not adversely affect the transport package during normal transport since the melting temperatures of all safety critical components are well above these temperatures and the package will experience no pressures sufficient to cause package failure. This assumption was further supported by the finite element analysis, contained in Section 2.12. It is therefore concluded that the Model 865 transport package will maintain its structural integrity and shielding effectiveness under the hypothetical accident condition transport thermal stress conditions.
3.5.5 Fuel/Cladding Temperatures for Spent Nuclear Fuel Not applicable. This package is not used for transport of spent nuclear fuel.
3.5.6 Accident Conditions for Fissile Material Packages for Air Transport Not applicable. This package is not used for transport of Type B quantities of fissile material.
3.6 Appendix Not applicable.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 4-1 Section 4 - CONTAINMENT 4.1 Description of the Containment System The containment system consists of the Model 865 transport package and the radioactive source capsule. This source capsule shall be qualified as Special Form radioactive material under 49 CFR 173 and IAEA TS-R-1 and SSR-6 and shall meet a minimum ANSI N43.6 - 2007 Pressure Classification of 3.
4.1.1 Special Requirements for Damaged Spent Nuclear Fuel Not applicable. This package is not used for the transport of spent nuclear fuel.
4.2 Containment Under Normal Conditions of Transport As demonstrated in the Test Plan 84 Report (Section 2.12), and supported by assessments when applicable, performance of the normal conditions of transport testing caused no breach of the source capsules contained in the package. Since the source capsules are the primary containment of the radioactive contents and no release from the source capsules occurred, the Model 865 package meet the requirements of this section . The normal conditions of transport criteria listed in 10 CFR 71 .71 will result in no loss of transport package containment as prescribed in 10 CFR 71 .51 (a)(1). This conclusion is based on information presented in Sections 2 and 3.
4.3 Containment Under Hypothetical Accident Condition The hypothetical accident conditions outlined in 10 CFR 71 .73 will result in no loss of transport package containment. This conclusion is based on information presented in Section 2.7 and Section 3.4 and as demonstrated in the Test Plan 84 Report (Section 2.12). As supported by assessments when applicable, performance of the hypothetical accident conditions of transport testing resulted in rad iation levels at one meter from the surface of the package that did not exceed 1 R/hr. The Model 865 package therefore meets the requirements of this section. Further, Sections 2.7 and 3.5 show that the transport package meets the containment requirements of 10 CFR 71.51 (a)(2).
4.4 Leakage Rate Tests for Type B Packages The primary containment for the radioactive material in the Model 865 Transport Packages is the radioactive source capsule. All source capsules authorized for Type B transport in the Model 865 are certified as special form radioactive material under 10 CFR Part 71, 49 CFR Part 173 and IAEA TS-R-1 and SSR-6. After manufacture, and again once every six months thereafter prior to transport, the source capsules are leak tested in accordance with ISO 9978:2020(E) (or more recent editions) to ensure that containment of the source does not allow release of more than 0.005 µCi of radioactive material. These fabrication and periodic tests ensure that contamination release from the package does not exceed the regulatory limits.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 4-2
Reference:
ISO 9978: 2020(E) - Radiation Protection - Sealed Radioactive Sources -
Leakage Test Methods.
4.5 Appendix Not applicable.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 5-1 Section 5 - SHIELDING EVALUATION 5.1 Description of Shielding Design 5.1.1 Design Features The principal shielding in the Model 865 transport package is the depleted uranium shield assembly and a small amount of tungsten in the source rod assembly. The shielding is described in drawings contained in Section 1.3.
5.1.2 Summary Table of Maximum Radiation Levels The tables in this Section include radiation profile data obtained from the 865 packages that were tested to the Normal and Hypothetical Accident Conditions of Transport under Test Plan 84 Report (see Section 2.12). Figure 5.1 .A shows the profile orientations for the surveys documented in this section. All reported dose rates are the highest measured for the location noted and survey measurements were corrected to the maximum package capacity.
Rear Bottom Right Front Figure 5.1.A - Profile Orientation for the Model 865
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 5-2 Table 5.1.A: Model 865 Test Unit TP84(A) After Transport Testing Summary Table of External Radiation Levels Extrapolated to Capacity of 240 Ci lr-192 (Non-Exclusive Use)
Normal Conditions Package Surface mSv/h (mrem/hr) 1 Meter from Package Surface mSv/h of Transport (mrem/h)
Radiation Top Side Bottom Top Side Bottom Gamma 0.32 (32) 1.12 (112) 0.56 (56) 0.002 (0.2) 0.005 (0.5) 0 .004 (0.4)
Neutron NA NA NA NA NA NA Total 0.32 (32} 1.12 (112} 0.56 (56} 0 .002 (0.2) 0.005 (0.5} 0 .004 (0.4}
10 CFR 71 .47(a) or 2 (200) 2 (200) 2 (200) 0.1 (10) 0.1 (10) 0.1 (10)
§525 & 526 of TS-R-1 and §527 & 528 of SSR-6 Limits Hypothetical Accident Conditions Gamma 0.002 (0.2) 0.005 (0.5) 0 .004 (0.4)
Neutron NA NA NA Total 0 .002 (0.2) 0 .005 (0.5) 0 .004 (0.4) 10 CFR 71.51 (a)(2) or Paragraph 656(b)(ii)(I) of TS-R-1 and 10 (1000) 10 (1000) 10 (1000)
SSR-6 Limit 1
Table results are extrapolated to the device capacity and incorporate surface correction factors.
2The maximum transport index based on the mrem per hour readings at one meter from the surface of the package was 0.8. All packages accepted and released for shipment under this Model designation will have a Transport Index less than or equal to 10.
Table 5.1 .B : Model 865 Test Unit TP84(B) After Transport Testing Summary Table of External Radiation Levels Extrapolated to Capacity of 240 Ci lr-192 (Non-Exclusive Use)
Normal Conditions Package Surface mSv/h (mrem/hr) 1 Meter from Package Surface mSv/h of Transport (mrem/h}
Radiation Top Side Bottom Top Side Bottom Gamma 0 .26 (26) 1.37 (137) 0.62 (62) 0.004 (0.4) 0.007 (0.7) 0.005 (0.5)
Neutron NA NA NA NA NA NA Total 0.26 (26) 1.37 (137) 0.62 (62) 0.004 (0.4) 0.007 (0.7) 0.005 (0.5) 10 CFR 71.47(a) or 2 (200) 2 (200) 2 (200) 0.1 (10) 0 .1 (10) 0.1 (10)
§525 & 526 of TS-R-1 and §527 & 528 of SSR-6 Limits Hypothetical Accident Conditions Gamma 0 .004 (0.4) 0 .007 (0.7) 0.005 (0.5)
Neutron NA NA NA Total 0 .004 (0.4) 0 .007 (0.7) 0 .005 (0.5) 10 CFR 71.51 (a)(2) or Paragraph 656(b)(ii)(I) of TS-R-1 and 10 (1000) 10 (1000) 10 (1000)
SSR-6 Limit 1Table results are extrapolated to the device capacity and incorporate surface correction factors.
2The maximum transport index based on the mrem per hour readings at one meter from the surface of the package was 0.8. All packages accepted and released for shipment under this Model designation will have a Transport Index less than or equal to 10.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington , Massachusetts Page 5-3 Table 5.1 .C: Model 865 Test Unit TP84(8) After Transport Testing I Package (or Freight Container} Surface 2 Meters from Outer Vehicle Surface mSv/h (mrem/h mSv/h (mrem/h Normal Conditions Top Side Bottom Top Side Bottom of Transport Gamma 0.26 (26) 1.37 (137) 0.62 (62) <0.004 (0.4) <0.007 <0.005 (0.7) (0.5)
Neutron NA NA NA NA NA NA Total 0.26 (26) 1.37 (137) 0.62 (62) <0.004 (0.4) <0.007 <0.005 (0.7) (0.5) 10 CFR 71.47(b) or 10 (1000) 2 10 (1000) 2 10 (1000) 2 0.1 (10) 0 .1 (10) 0.1 (10)
§569 of TS-R-1 and
§573 SSR-6 Limits Vehicle Surface mSv/h (mrem/h) Occupied Position mSv/h (mrem/hr)
Gamma < 0.26 (26) < 1.37 < 0.62 (62) S 0.02 (2) 3
{137)
Neutron NA NA NA NA Total < 0.26 (26) < 1.37 < 0.62 (62) s 0.02 (2) 3
{137) 10 CFR 71.47(b) or 2 (200) 2 (200) 2 (200) 0 .02 (2)
§569 of TS-R-1 and
§573 SSR-6 Limits Hypothetical Accident Conditions 1 Meter from Package Surface mSv/h (mrem/hr)
Gamma 0.004 (0.4) 0.007 (0.7) 0.005 (0.5)
Neutron NA NA NA Total 0.004 (0.4) 0.007 (0.7) 0.005 (0.5) 10 CFR 71 .51 (a}(2) or §657(b)(ii) of TS-R-1 and 10 (1000) 10 (1000) 10 (1000)
§659(b)(ii) SSR-6 Limits 1For packages transported by roadway, railway and sea.
2 For packages in closed vehicles, otherwise, 2 mSv/h (200 mrem/h}.
3 Confirmed at time of vehicle loading prior to shipment.
4 Table results are extrapolated to the device capacity and incorporate surface correction factors.
5 Results provided for Test Unit TPB4(B) as this unit was the worst case tested specimen.
52 Source Specificat'on 5.2.1 Gamma Source The gamma sources allowed for transport in the Model 865 transport package are specified in Sections 1.2.2 and 2.10.
5.2.2 Neutron Source Not applicable. The Model 865 transport package is not used for the transportation of neutron emitting sources.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 5-4 5.3 Shielding Model 5.3.1 Configuration of Source and Shielding A shielding model was not used to justify acceptance of this package. Shielding justification was based on direct measurement.
5.3.2 Material Properties Not applicable. A shielding model was not used in the justification for this package.
Shielding justification was based on direct measurement.
5.4 Shielding Evaluation 5.4.1 Methods Shielding justification was based on direct measurement. All packages are profiled prior to final acceptance and shipment. This profile takes into account the maximum capacity of the package. Any package not meeting the required dose rates is rejected.
5.4.2 Input and Output Data Radiation measurements included in this Section were adjusted to the maximum activity capacity for the package (e.g., activity correction factor) and the surface measurements were also adjusted to correct for off-set of the survey meter probe from the true surface of the package.
Activity correction factors (CFA) were obtained by using the following relationship:
{update equation details to reflect package activity limits}
MaximumPackageActivityCapacity (Ac)
CF=---------------
A Actual Pro fileActivity (Ap)
ForExample, if Ap = 230 Ci and Ac = 240 Ci, then 240 Ci CFA = 230 Ci= 1.04 Therefore, all original surface and 1 meter profile measurements would be multiplied by a factor of 1.04 for a package profiled using 230 Ci and a package capacity of 240 Ci.
Radiation measurements at the surface of the container were also adjusted to compensate for the off-set of the survey meter probe from the true surface of the package.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 5-5 Surface correction factors (SCF) were obtained by using the following relationship:
SCF = dd1 2
where d 1 and d 2 are determined as shown in Figure 5.4. A.
For Example, if d 1 = 9 inches and d 2 = 9.5 inches, then 9.5 inches SCF = . h 9 me es
= 1.06 Therefore, in the example shown, all original surface profile measurements located along the side of the package shown in Figure 5.4.A would also be multiplied by a factor of 1.06 to account for surface correction of the detector to the package. Different SCF's would be calculated for the any dimension of the container where the minimum distance from the center of the activity to the center of the radiation probe is different.
d1 = distance from activity center to surface of container.
d2 = distance from activity center to surface of container plus radius of the survey meter probe.
Figure 5.4.A - Sample Surface Correction Factor Distance Criteria The radiation profile data showed no increase in radiation dose after testing beyond normal measurement variations. All test specimens met the regulatory requirements.
5.4.3 Flux-to-Dose-Rate Conversion Not applicable. Flux rates were not used to convert to dose rates in any shielding evaluations.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 5-6 5.4.4 External Radiation Levels Radiation surveys for all 865 configurations showed maximum surface and 1 meter radiation levels from the transport packages within regulatory limits. Radiation surveys of 865 transport packages after undergoing normal and accident condition transport testing were also well within the regulatory limits.
Profiles performed with the Model 865, with and without the actuator assembly components that are typically secured to the actuator base, demonstrate that the package dose rate compliance is not dependent on the presence of a majority of the actuator assembly components under normal and hypothetical accident conditions.
These components are important to the operation of the Model 865 as a radiography device but are not important to the source containment or package integrity of the Model 865 as a transport package.
5.5 Appendix 5.5.1 Assessment of Model 865 for Actuator Assembly Component Importance
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 5-7 5.5.1 Assessment of Model 865 for Actuator Assembly Component Importance The following is an engineering assessment to justify the classification of certain Model 865 actuator parts as "optional". The scope of the justification is specific to the source actuator assembly shown on sheet 5 of 7 of drawing R86590 Revision K (and subsequent revisions).
A radiation profile inspection was performed on a Model 865 serial number 32, built with all actuator parts removed (reference TMI 954), but the actuator guard and cover installed in place. The profile results showed all measurements within compliance limits except for one very small spot about 0.25 inches in diameter on the shipping cover at the top center surface and at 1-meter in a direct line from this same spot. The surface measurement at this location was 214 mrem/hr and the 1-meter from the surface measurement was 4 mrem/hr.
214 mR/hr ALL ACTUATOR PARTS ALL OPTIONAL REMOVED PER TMI #954 PARTS REMOVED Figure 5.5.A - Inspected Configuration Figure 5.5. B - Compliant Configuration The high dose measurement at this spot is a result of scatter radiation emitting from the clearance gap between the source rod and shield source channel. With the actuator piston in place, the dose at this same location on the package (center of the cover) is below the compliance limits of 200 mrem/hr at the surface and 10 mrem/hr at 1-meter from the surface.
The stainless steel actuator piston is 4 inches long and covers the clearance gap between the source rod and shield source channel. The 4-inch piston material provides 8 half value layers of shielding to sufficiently lower the dose well below the compliance limit.
Based on the radiation profile and shielding assessment of the actuator piston, the actuator piston and other items needed to keep it in place during transport are deemed important to safety (ITS) and are not optional. The other ITS items include the actuator body, the actuator flange and the actuator bolts. The short distance between the bolts and the actuator guard during transport prevents the bolts from being removed , and keep the piston in place in the event the thread locker and/or lock wire are not present or were to fail. The actuator guard is also an important to safety item and required for transport. Since the actuator guard is in place for transport, the thread locker and the lock wire are both optional.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 5-8 Other optional actuator assembly items from drawing R86590 sheet 5 include; the source engage plate, the adapter mount, the sleeve spacer, all seals, the three screws, the end stop, adapter, filter, fitting, spring, and set screw. All these optional items do not contribute to shielding, piston restraint, and/or source securement necessary to ensure compliance of the Model 865 package for transport. As such, these items can be absent without adversely affecting the radiological safety of the Model 865 Type-8 package and detailed specifications for these items is not necessary to ensure package conformance under 10 CFR part 71 and in accordance with guidance from NUREG-CR-5502.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 6-1 Section 6 - CRITICALITY EVALUATION All parts of this section are not applicable. The Model 865 transport package is not used for shipment of Type B quantities of fissile material.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 7-1 Section 7 - Package Operations Operation of the Model 865 transport package must be in accordance with the operating instructions supplied with the transport package, per 10 CFR 71.87 and 71.89.
7.1 Package Loading 7.1.1 Preparation for Loading The Model 865 transport package must be loaded and closed in accordance with procedures that, at a minimum, include the requirements specified in this section.
Shipment of Type B quantities of radioactive material are authorized for sources specified in Section 7.1.1.1. Maintenance and inspection of the 865 packaging is in accordance with the requirements specified in Section 7.1.1.2.
7 .1 .1 .1 Authorized Package Contents Ta bl e 7 1 A . Mod e I 865 Pac kaae Inf ormaf I0n Nuclide Form Maximum Maximum DU Weight Maximum Weight Capacity 1 lr-192 Special Form 240 Ci 42 lbs (19 kg) 60 lbs (27 kg)
Sources 1 Maximum Activity for lr-192 is defined as output Curies as required in ANSI N432 and 10 CFR 34.20 and in line with TS-R-1, SSR-6, USNRC 10 CFR 71 and USDOT 49 CFR 173.
7.1.1.2 Packaging Maintenance and Inspection Prior to Loading NOTE: If the device is used in an environment that would be conducive to the creation of crevice corrosion (i.e. salt water splash zone, oil rig work, etc.), the device should be rinsed after use with clean water to remove any residue which could contribute to corrosion.
a. Ensure all markings are legible and labels are securely fastened to the container.
b. Inspect the container for signs of significant degradation. Ensure that the housing integrity is secure and does not have any significant dents, cracks or any type or rust.
c. Ensure all bolts and hardware are present and there is no visible signs of damage to hardware heads. After removal of the cover, examine the external surfaces of the cover bolts for any signs of fatigue cracking.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 7-2 Note: A visual examination of the actuator guard bolts and the source actuator assembly bolts for thread condition is performed by QSA Global, Inc. at the time of source changing/replacement as this device requires the use of a shielded cell and specially designed tools to access and remove the sealed source. Removal of this hardware should not be performed by general users of the device/transport package. While empty, annual servicing and inspection of the package hardware is performed on the Model 865 device by QSA Global, Inc.
The bolts/fasteners must be replaced prior to further transport, if they are no longer fit for use (e.g., threads stripped, unable to fully thread, signs of cracking, etc).
d. If the container fails any of the inspections in steps 7.1.1.2.a-c, remove the container from use until it can be brought into compliance with the Type B certificate.
7.1 .2 Loading of Contents NOTE: These loading operations apply to "dry" loading only. The Model 865 package is NOT approved for wet loading.
NOTE: All removal and installation of radioactive material contained within the Model 865 must be performed in a shielded cell/enclosure capable of holding the maximum isotope capacity of this container. This can only be performed by persons specifically authorized under an NRC or agreement state license.
All necessary safety precautions and regulations must be observed to ensure safe transfer of the radioactive material.
7 .1.2.1 Prior to transportation, ensure the package and its contents meet the following requirements:
a. The contents are authorized for use in the package.
b. The package condition has been inspected in accordance with Section 7.1.1.2.
c. Ensure that the source is secured into place in the storage position in accordance with the following requirements.
Compliance with the following requirements ensures that the source is securely locked in position before shipment.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 7-3
1. Removal and installation of radioactive material contained within the shield container must be performed in a shielded cell/enclosure capable of holding the maximum isotope capacity of the container. Container loading can only be performed by persons specifically authorized under an NRC or Agreement State license (or as otherwise authorized by an International Regulatory Authority). All necessary safety precautions and regulations must be observed to ensure safe transfer of the radioactive material. Source removal or loading should not be attempted by general users of this package and it is recommended that the device be returned to QSA Global Inc. for source loading or unloading.
2. Remove the shipping cover. Unlock the actuator assembly.
Remove the four bolts which secure the actuator assembly to the container body.
3. Using remote handling techniques, remove the actuator assembly from the container body. Load the source assembly into the source rod assembly. Install the source rod into the container and secure the actuator assembly to the container body using the hardware specified on drawings in Section 1.3.
4. Ensure all bolts are present and secured. Assure safety wires are present and intact as noted on the drawings referenced in the Type B certificate.
5. Check that the source position indicator rod is in the down position and the key operated lock is engaged and the key removed, assuring that the source is locked in place in its proper shielded storage position.
6. Install the shipping cover using the bolts specified on drawings in Section 1.3. These bolts should be hand tightened. Attach a tamper indicating seal with an identification mark to two of these bolts.
7.1.3 Preparation for Transport 7.1.3.1 Prior to transport, ensure the following requirements are met:
a. Ensure that all conditions of the certificate of compliance are met.
b. Perform a contamination wipe of the outside surface of the package and ensure removable contamination does not exceed the limit specified in 49 CFR 173.443.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 7-4 C. Survey all exterior surfaces of the package to assure that the radiation level does not exceed 200 mR/hr (2 mSv/hr) at the surface. Measure the radiation level at one meter from all exterior surfaces to assure that the radiation level is less than 10 mR/hr (0.1 mSv/hr).
d. Ship the container according to the procedure for transporting radioactive material as established in 10 CFR 71.5 and 49 CFR 171-178.
NOTE: The US Department of Transportation, in 49 CFR 173.22(c),
requires each shipper of Type B quantities of radioactive material to provide prior notification to the consignee of the dates of shipment and expected arrival.
7.2 Package Unloading 7.2.1 Receipt of Package from Carrier 7.2.1.1 The consignee of a transport package of radioactive material must make arrangements to receive the transport package when it is delivered. If the transport package is to be picked up at the carrier's terminal, 10 CFR 20.1906 requires that this be done expeditiously upon notification of its arrival.
7.2.1.2 Upon receipt of a transport package of radioactive material:
a. Survey the transport package in accordance with the requirements of 10 CFR 20.1906 (or equivalent Agreement State or international regulations).
b. Record the actual radiation levels on the receiving report.
c. If the radiation levels exceed the limits, secure the container in a Restricted Area and notify the appropriate personnel in accordance with 10 CFR 20 or applicable Agreement State regulations.
d. Inspect the outer container for physical damage or leaking. If the package is damaged or leaking or it is suspected that the package may have leaked or been damaged or leaking, or any part of the package is suspected to have leaked or been damaged, restrict access to the package. As soon as possible, contact the Radiation Safety Office to perform a full assessment of the package condition and take necessary follow-up actions.
e. Visually inspect the Model 865 to assure that the seal wire has not been tampered with.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 7-5
f. Record the radioisotope, activity, model number, and serial number of the source and the transport package model number and serial number.
7.2.2.1 Removal of Contents
a. Arrange for the unloading of the package in accordance with the information on drawings in Section 1.3 and the instructions supplied with the package per 10 CFR 71.89.
NOTE: Removal and installation of radioactive material contained within the shield container must be performed in a shielded cell/enclosure capable of holding the maximum isotope capacity of the container. Container loading can only be performed by persons specifically authorized under an NRC or Agreement State license (or as otherwise authorized by an International Regulatory Authority). All necessary safety precautions and regulations must be observed to ensure safe transfer of the radioactive material.
Source removal or loading should not be attempted by general users of this package and it is recommended that the device be returned to QSA Global Inc. for source loading or unloading.
b. Unloading of the package must also be in accordance with applicable licensing provisions for the user's facility related to radioactive material handling.
7.3 Preparation of Empty Package for Transport In the following instructions, an empty transport package refers to a Model 865 transport package without an active source contained within the shielded container. A device returned to the user as "empty" will have been visually confirmed at QSA Global Inc. (or other specifically licensed user) that the radioactive source has been removed and the container is confirmed empty.
7.3 .1. To ship an empty transport package:
7.3.1.1 Assure that the levels of removable radioactive contamination on the outside surface of the transport package does not exceed 4 Bq/cm 2 (when averaged over 300 cm 2 }.
7.3.1.2 After the survey prepare the package depending upon the radiation levels obtained as prescribed in 49 CFR 173.
7.3.1.3 Ship the container according to the procedure for transporting radioactive material as established in 49 CFR 171-178.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 7-6 7.4 Other Operations 7.4.1 Package Transportation By Consignor Persons transporting the Model 865 transport package in their own conveyances should comply with the following:
7.4.1 .1 For a conveyance and equipment used regularly for radioactive material transport, check to determine the level of contamination that may be present on these items. This contamination check is suggested if the package shows signs of damage upon receipt or during transport, or if a leak test on the special form source transported in the package exceeds the allowable limit of 185 Bq (0.005 µCi).
7.4.1.2 If contamination above 4 Bq/cm 2 (0.0001 µCi/cm 2) based on wiping an area of 300 cm 2 is detected on any part of a conveyance or equipment used regularly for radioactive material transport, or if a radiation level exceeding 5 µSv/h (0.5 mR/hr) is detected on any conveyance or equipment surface, then remove the affected item from use until decontaminated or decayed to meets these limits.
7.4.1 .3 Ensure the package is properly blocked and braced prior to transport to prevent movement within the conveyance during transport.
7.4.2 Emergency Response In the event of a transport emergency or accident involving this package, follow the guidance contained in "2020 Emergency Response Guidebook: A guidebook intended for fi rst responders during the initial phase of a transportation incident involving hazardous materials/dangerous goods", or equivalent guidance documentation.
Reference:
"2020 Emergency Response Guidebook: A guidebook intended for first responders during the initial phase of a transporation incident involving hazardous materials/dangerous goods".
r1*
7.5 Not Applicable.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 8-1 Section 8 - ACCEPTANCE TESTS AND MAINTENANCE PROGRAM 8.1 Acceptance Test 8.1.1 Visual Inspections and Measurements 8.1.1.1 Visually inspect each transport package component to be shipped to assure the following:
a. The transport package was assembled properly to the applicable drawing referenced on the Type B transport certificate.
b. Evaluate the transport package for shielding integrity to ensure the transport dose rate requirements are met when the container is loaded to capacity.
c. All fasteners as required by the applicable drawings referenced on the Type B transport certificate are properly installed and secured .
d. The relevant labels are attached , contain the req uired information, and are marked in accordance with 10 CFR 20.1904, 10 CFR 40.13(c)(6)(i) , 10 CFR 34, and 10 CFR 71 or equivalent Agreement State regulations.
8.1.1.2 Visual inspections and measurements will be performed in accordance with QSA Global, lnc.'s USNRC approved Quality Assurance Program No. 0040.
8.1.2 Weld Examinations Weld examinations will be performed in accordance with the applicable drawings requ irements and in accordance with QSA Global, lnc.'s USNRC approved Quality Assurance Program No. 0040.
8 .1 .3 Structural and Pressure Tests Prior to first use as part of a Model 865 Transport Package, container structu ral conformance will be evaluated in accordance with the applicable drawings requirements and in accordance with QSA Global, lnc.'s USNRC approved Quality Assurance Program No. 0040. The containment system is not designed to require increased or decreased operating pressures to maintain containment during transport, therefore pressure tests of package components prior to first use are not required.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington , Massachusetts Page 8-2 8.1.4 Leakage Tests The source capsule (primary containment) is wipe tested for leakage of radioactive contamination upon initial manufacture. The removable contamination must be less than 185 Bq (0.005 µCi). The source capsule will also be subjected to leak tests under ISO 9978:2020(E) (or more recent editions). The source capsule are not used if it fails any of these tests.
8.1 .5 Component and Material Tests Component and material compliance is achieved in accordance with the requirements in QSA Global, lnc.'s USNRC approved Quality Assurance Program No. 0040.
8.1.6 Shie lding Tests The radiation levels at the surface of the transport package and at 1 meter from the surface are measured upon manufacture. This survey is performed in a low background area and involves a slow scan survey of the entire surface area as well as one meter from the surface of the package. This survey is used to identify any significant void volumes or shield porosity which could prevent the finished package from complying with the dose limits in 10 CFR 71.4 7.
The radiation profile survey is made with the radiation detector housing in contact with the surface of the package and then also at one meter from the surface of the container. These radiation levels.when extrapolated to the rated capacity of the transport package, must not exceed 200 mR/hr (2 mSv/hr) at the surface, nor 10 mR/hr (0.1 mSv/hr) at 1 meter from the surface of the transport package.
Failure of this test prevented use of the package as a Type B(U) package.
Rejected packages which do not comply with the construction requirements on the applicable drawings referenced on the Type B certificate, or that do not comply with the radiation profile requirements will not distributed as approved Type B(U) packages.
8.1 .7 Thermal Tests Not applicable. The source content of the Model 865 package has minimal effect on the package surface temperature and therefore no additional testing is necessary to evaluate thermal properties of the packaging.
8.1.8 Miscellaneous Tests Not applicable.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 8-3 8.2 Maintenance Program 8.2.1 Structural and Pressure Tests Not applicable. Material certification, or equivalent dedication process, is obtained for Safety Class A components used in the transport package prior to their initial use. Based on the construction of the design, no additional structural testing during the life of the package is necessary if the container shows no signs of defect when prepared for shipment in accordance with the requirements of Section 7 of the SAR.
The 865 packaging is not designed to require increased or decreased operating pressures to maintain containment during transport, therefore pressure tests of package components prior to individual shipment is not required.
8.2.2 Leakage Tests As described in Section 8.1.4, "Leakage Tests," the radioactive source assembly is leak-tested at manufacture. In addition, the sources are leak tested in accordance with that Section at least once every six months thereafter if being transported to ensure that removable contamination is less than 185 Bq (0.005
µCi).
8.2.3 Component and Material Tests The transport package is inspected for tightness of fasteners, proper seal wires, general condition and fitness for use prior to each use (see Section 7.1.1 ). No additional component or material testing is required prior to shipment. Failure of these inspections will prevent use of the package until the cause of the failure is corrected.
Prior to each use, a radiation survey of the transport package is made to assure that the radiation levels do not exceed 200 mR/hr (2 mSv/hr) at the surface, nor 10 mR/hr (0.1 mSv/hr) at 1 meter from the surface.
8.2.4 Thermal Tests Not applicable. The source content of the Model 865 package has minimal effect on the package surface temperature and therefore no additional testing is necessary to evaluate thermal properties of the packaging prior to shipment.
8.2.5 Miscellaneous Tests Inspections and tests designed for secondary users of this transport package under the general license provisions of 10 CFR 71.17(b) are provided in Section 7 .1 .1.2. In addition to the inspections from Section 7, the following inspection and maintenance of the Model 865 container is recommended at source reloading:
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 8-4 8.2.5.1 Inspect all housing body and actuator base welds for signs of corrosion and/or cracks.
8.2.5.2 If the device is routinely used for underwater radiography, then the projector should be tested by a non-destructive examination (NDE) technique such as dye penetrant at source changes. The NDE should be performed on all external shield container surfaces, particularly under the label. Evidence of pitting, cracking or corrosion indicate the need for repair or scrapping of the component or assembly.
8.2.5.3 Failure of any of the checks in Section 7.1.1.2, 8.2.5.1 or 8.2.5. 2 will prevent use of the package until the cause of the failure is corrected. If correction cannot be made under the approved Type B certificate, the device will be removed from use as a Type B(U) transport container.
8.3 Appendix Not applicable.
Safety Analysis Report for the Model 865 Transport Package QSA Global, Inc. April 2023 - Revision 14 Burlington, Massachusetts Page 9-1 Section 9 - Quality Assurance 9.1 I I ~ ()1 I"+ I All component fabrication (including assembly) is controlled under the QSA Global, Inc.
Quality Assurance program approved by the USNRC (approval number 0040) and ISO 9001.
9.2 r'!:a r-1 I r::1nr-0 Drl"'\r,r ,..., 0 ,., 11r Not applicable. This package is originally submitted for certification in the United States and complies with the criteria in Section 9.1.

ML23125A153

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1.1 INTRODUCTION

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5.1 DESCRIPTION

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69 N/mm 2 Maximum combined stress on weld

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Dear Mr. McDaniel:

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6.0 REFERENCES

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