ML20050C963
| ML20050C963 | |
| Person / Time | |
|---|---|
| Site: | Sequoyah  |
| Issue date: | 10/23/1978 |
| From: | AMERICAN ENVIRONMENTS CO. |
| To: | |
| Shared Package | |
| ML20050C841 | List:
|
| References | |
| RTR-NUREG-0588, RTR-NUREG-588 IEB-79-01B, IEB-79-1B, STR-060578-1, STR-60578-1, NUDOCS 8204090455 | |
| Download: ML20050C963 (67) | |
Text
{{#Wiki_filter:r_ YALVE AND FLOW CONTROL EQUIPMENT SPECIALISTS
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7 POWER PLANT, OIL & GAS INDUSTRY & INDUSTRIAL SERVICE 6M t ~MM ATWOOD6MORRILLCO INC. I ossionens Ano uanuractuasas since isoo 285 CANAL STREET SALEM. MASSACHUSETTS c1970 617 744-5690 TELEX 94 0299 TWX 710 34 I May 27, 1980
, Tennessee Valley Authority I 400 Commerce Avenue W100216 Knoxville, Tennessee 37902 l
i r Attention: Mr. Robert Poole i
Dear Mr. Poole:
Per your request of our Mr. A. J. McKay, enclosed is a copy of our Valve Actuator Qualification Test Report, #201-39500. b If you require further infonnation, please do not hesitate to contact us. Yours truly, ATWOOD & MORRILL CO., INC. ka - "@ .h . Nancy D. Peck, l Secretary to Mr. A. J. McKay, Manager, Engineering Services ndp Enclosure cc: A. H. Webber
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- INTRODUCTION
(,) . The purpose of this test program was to generically qualify the Atwood & Morrill pneumatically operated safety-related MSI valve
' actuator assembly to the requirements of IEEE Standards 323, 344 and 382.
The test specimen was a 26" BWR MSI valve actuator assembly consisting of a production cover, attached yoke rods, springs, spring plates, Chicago Fluid Power 20" diameter pneumatic cylinder with hydraulic speed control system, special test stem, packing gland follower, NAMCO EA 740-20100 limit switches and a Chicago Fluid Power subplate mounted air control system using 3/4" NPT and 1%" NPT solenoid valves. The test program involved the following test phases which were performed by American Environments Company: g,/ 1. Mechanical Life Test (Normal Service)
- 2. Radiation Soak Test (Normal and Abnormal Service)
- 3. Thermo Cyclic Aging Test (Normal Service)
- 4. , Seismic Qualification Test (Abnormal Service)
- a. Resonant Frequency Search
- b. Dynamic Shake Table Test i
- c. Static Bend Test
- 5. Abnormal Ambient Simulation (Abnormal Service)
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'RESULTS km/ + The test results presented in American Environments' Test Report No. STR-060578-1, included in this Report as Appendix A, satisfactorily meet the requirements of IEEE Standards 323, 344 and 344 subject to f
the following anomalies. In the thermo cyclic aging test, Section 6.0 of the Report, temperatures in excess of the low temperature range were noted at cycle numbers 17 and 34. This was traced to periodic calibration of the Standardization cell in the test chamber. The calibration was done prior to cycle 1 and during cycles 17 and 34 and were due to the heating and refrigeration systems acting simultaneously. Since the subsequent cycles were within the required temperature range, the readout and results were effected only during these cycles. Therefore, this anomaly was segregated and did not alter the test. In addition, two extra cycles were run within the proper temperature range. In the resonant frequency search, Section 7.0 of the Report, resonant frequencies below 33 Hz were noted in the limit switch-junction box assemblies. Therefore, these assemblies were considered as non-rigid structures and were subjected to further testing. The results of the dynamic shake table test of the limit switch-junction box assemblies, Section 8.2 of the Report, showed no evidence of physical damage, switch continuity / discontinuity, or malfunction. - At the completion of the static seismic test, Section 9.0 of t:4e Report, air leakage in excess of the Atwood & Morrill specified maximum allow-able rate was noted. This leakage was traced to the 1/8" NPT connection
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'RESULTS ( continued )
() - between the 90 elbow tube fitting and the solenoid exhaust stack adaptor, CFP, Part No's. 6 and 19 on drawing number CFP-167-C.
- Examination of'the connection revealed cross-threading. Both the elbow fitting and the adaptor were replaced and the connection was sealed with hydraulic sealant. Air leakage was again measured and found to be within Specification limits. As this anomaly is attributed to a manufacturing error, Chicago Fluid Power was notified immediately and appropriate corrective action has been taken.
At the completion of the abnormal environment (LOCA) simulation air leakage in excess of Atwood & Morrill's specified maximum rate was recorded, Section 10.0 of the Report. Examination of the unit revealed a defective valve seat in the four-way valve. A portion of the seat was erroded resulting in excessive leakage. The erroded portion was about 5/8" long along the lip. All of the remaining air valve seats
- were examined and no degradation was noted. Therefore, this anomaly is attributed to a defect in a specific piece of material and is not a generic material inadequacy.
CONCLUSIONS The test results presented in American Environments' Test Report, No. STR-060578-1 verify that the Atwood & Morrill main steam isolation valve actuator assembly successfully completed all phases of the test program.
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I q APPENDIX A AMERICAN ENVIRONMENTS COMPANY TEST REPORT f
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- s. .4 AMFRICAN ENVIRONMENTS COMPAtJY INC., P.O. BOX 222 KINGS PARK, NEW YORK 11754(516) 752 0989
. helping to provide Safe Nuclear Power.
NUCLEAR QUALIFICATION TEST REPORT ON MSIV AIR SPRING ACTUATOR FOR ATWOOD MORRILL COMPANY, INC. SALEM, MASSACHUSETTES a NUMBER BY DATE
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STR-060578-1 AMERICAN ENVIRONMENTS COMPANY 10/23/78 PREPARED BY: _ , y --------------------------------------- -------------- . .---- QUALITY ASSURANCE BY.
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APPROVAL CERTIFICATION .
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BY: ,, CUSTOMER REVIEW BY: (Aggi)
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V' _ STR-0G0578-1 PAGE 1 OF 63 PAGES [i - - _ _ _ _ _ _ _ _ _ _ _ _ _
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STR-060578-1
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PAGE PARAGRAPH
. 2 ADMINISTRATIVE DATA 3
1.0 TEST APPARATUS 5
2.0 DESCRIPTION
OF TEST SPECIMEN 5 3.0 METHOD OF TEST 5 y 3.1 TEST SEQUENCE 5 3.2 TEST SETUP 6 3.3 MECHANICAL LIFE TEST METHOD 7 3.4 RADIATION SOAK TEST METHOD 8
,. 3.5 THERMO CYCLIC AGING TEST METHOD 10
- l 3.6 RESONANT SEARCH TEST METHOD 11 3.7 DYNAMIC SHAKE TABLE TEST METHOD 12 3.8 STATIC SEISMIC SIMULATION TEST METHOD 13 3.9 ABNORMAL ENVIRONMENT (LOCA) TEST METHOD 14 TEST RESULTS 14 4.0 MECHANICAL LIFE TEST RESULTS 15 5.0 RADIATION SOAK TEST RESULTS 15 6.0 THERMO CYCLIC AGING TEST RESULTS 16
%./ 7.0 RESONANT SEARCH TEST RESULTS 27 8.0 DYNAMIC SHAKE TABLE TEST RESULTS 45 9.0 STATIC SEISMIC TEST RESULTS 46 10.0 ABNORMAL ENVIRONMENT (LOCA) TEST RESULTS 47 11.0
SUMMARY
OF OPERATING CONDITION 47 12.0 RECOMMENDATIONS 47
13.0 CONCLUSION
S 48 APPENDIX A - CERTIFICATIONS 49 TYPICAL TEMPERATURE RECORDING 50 IRRADIATION CERTIFICATE 51 APPENDIX B - FIGURES FIGURE l-TilERMO CYCLIC AGING 'AND MECHANICAL 52 LIFE TEST SETUP 53 FIGURE 2-STATIC SEISMIC SIMULATION TEST SETUP 54 FIGURE 3-DYNAMIC SilAKE TABLE INPUT CURVE 55 FIGURE 4-ABNORMAL ENVIRONMENT TEST SETUP 56 FIGURE 5-ABNORMAL ENVIRONMENT TEMPERATURE CURVE 57 APPENDIX C - PIIOTOGRAPHS 58 STATIC SEISMIC SIMULATION 59 4; RESONANT SEARCH ss * - - 60 . . _ _ _ DYNAMIC SilAKE TABLE TEST 63 ABNORMAL ENVIRONMENT (LOCA) PAGE i
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ll V'! sl ADMINISTRATIVE DATA PAGE 2 l DATE: 23 October 1978 4 PURPOSE OF TEST: To determine the e f f ects of Nuclea r Quali fica tion Testing on the physical and operational characteristics of the
' submitted test specimen. '4 MANUPACTURER: Atwood Morrill Company, Inc.
285 Canal Street Salem, Massachusettes 01970
.)
MANUFACTURER TYPE AND See paragraph 2.O for a SERIAL NUMBER: description of the test specimen. i:
*e V ' One (1) only.
QUANTITY OF ITEMS TESTED: DISPOSITION OF TEST Returned to client. SPECIMEN: EQUIPMENT: Uncla ssi fied . REPORT:
- Unclassified.
AMERICAN ENVIRONMENTS COMPANY, TEST CONDUCTED BY: INC. Division of: East-West Technology 119 Cabot Street ~ West Babylon, N.Y. 11704 ADSTRACT: It is the function o f American Environments Company , Inc., as an im pa r ti a l testing agency in performing this test, to 5:_- ._ subject the test specimen to qualification environments as y . . . . . - . .. .- -.--: -r- specifled in the detailed test specifications. STR-060578-1
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STR-060578-1 lj
- u. u TEST APPARATUS
1.0 DESCRIPTION
OF TEST APPARATUS: 1.1 Func tion Genera tor , Model No. 202A Serial No. 11638, manufactured by Hewlett-Packa rd. Calibration Due : 30 December 1978. 1.2 DC Servo Controllers (2), Model No. 828300, Serial Nos. 193 and 432 manufactured.by Moog, Inc. Calibration not required. 1.3 Actuator, Model No. DN-65, Serial No. 70552,
- manufactured by Miller Fluid Power Company. .
Calibration no t required. 1.4 Servo Valves (3), Model No. 72-103, Serial Nos. 68, 110 and 228, manufactured by Moog , Inc. Ca lib ra tio n not required. 1.5 Hydraulic Power Pack , Model No. 180/3000-5606, Serial No. 1, manufactured by Ea s t-West Technology Corp.
" Calibration no t required.
V Linear Displacement Potentiometer, Model No. 1.6 Rp-04-01-01-1, Serial No. 2662, manufactured by Calibrated immediately Pacific Scientific Company. prior to test. 1.7 Signal Amplifiers (2) Model No. 6 0 7 -RMG -3 A , Serial Nos. 135 and 155, manuf actured by Unhol tz-Di c ke . Calibration Due: 26 January 1979. 1.8 Accelerometers (4) , Model No. 2215, Serial Nos. 4702, 9663, 7952, and 8412, manufactured by Endevco. Calibration Due: 28 December 1978. 1.9 Oscilloscope, Model No. 564, Serial No. 000846, manuf ac tur ed by Tektronix. Ca lib ra tio n Due: 30 September 1978. -
. 1.10 Power Supply (2), Model No. 3564, Serial Nos. 893 &
' 896, manufactured by SCR Division Maxon Electronics. Calibration not required. 1.11 Strain Gauge Signal Conditioners (2), Model No. 601B, Serial Nos. 10896 & 10897, manufactured by Daytronic Corporation. Calibrated immediately prior to use, v Z-J 1.12 Timer, Model No. S-1-34-60, Serial No. manu f ac tur ed by Standard Electric Time Corp. Calibration due: 10 October 1978 L
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- STR-060578-1 j
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y- u. TEST APPARATUS CONTINUED l.0 DESCRIPTION OF TEST APPARATUS (CON'T): 1.13 controller, Model No. 2T500, Serial No. 63A18654, 9.c.nuf actured by Bri stolCorpo ration. Cal ~ibration Due : 1 September 1978. 1.14 Sling Psycrometer, Model No. 30-110, Serial No. 4413, manuf ac tured by Taylor Instruments Corporation. Calibration Due: 19 July 1979. 1.15 Contact Monitor ing Unit , Model No. CD-HPB 43, Serial No. 003, manuf ac tur ed by Ea s t-We s t Technology Corporation. Calibration Due: 28 February 1979. 8
- 1.16 Temperature sa fety Unit , Model No. J, Serial No.
5509246, manufactured by West Instruments
' Corporation. Calibration not required.
I 1.17 Digital Thermometer, Model No. 2166AT, Serial No. 836002, ma nuf a c tur ed by Omega Engineering Corporation. Calibration Due: 19 December 1978.
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- 1.18 Environmental Test Chamber, Model No. 27TR-120350, Serial No. EXT 023 2962A, manuf ac tured by Tenny
< Engineering Corporation. Calibration not required.
1.19 Dry Bulb Temperature Recorder / Controller, Model 947966, No. Y152P15-P-273-III-91-(L), Serial No. manufactured by Honeywell-Brown Incorporated. Calibra tion Due: 24 August 1978. 1.20 Wet Bulb Tempera ture Recorder / Controller, Model No. 15 2 P-P-2 73-III-91 (L ) , Serial No. 947968, manufactured l by Honeywell-Brown Incorporated. Calibration Due: 24 August 1978. 1.21 LOCA Test Chamber , Model No. 174, Serial No. 010, manufactured by AECO/ Ea s t-We s t Technology Corporation. Calibration immediately prior to use. - l 1.22 Flo wme te r , Model No. RMA-2-SSV, Serial No. 115, manu f ac tured by Dwyer Instruments, Incorporated. Calibrated immediately prior to use. I 1.23 Lo a d cell,Model No. 1220 FX, Serial No. 988, manuf actured by Interface Incorporated. Ca l i b ra t i o n due: 14 March 1980 y j c.-- _ .. _u . . _ . .
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2.0 DESCRIPTION
OF TEST SPECIMEN: 9' The test specimen, MAIN STEAM ISOLATION VALVE ACTUATOR ASSEMBLY, consisted of a production cover, attached yoke rods, [ springs, spring plates, pneumati- cylinder, hyd raulic speed control system, special stem, packing, gland follower, limit switches and air control assemblies containing all wiring and terminal strips. The total specimen weight was approximately 6000 pounds as mounted on a 45 degree inclined fix tur e . j,
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u q 3.0 METHOD OF TEST: h The following test procedures were employed during the f' qualification testing of the test specimen. All testing wa s performed with the specimen's stem inclined 45 degrees from the
}i horizontal unless otherwise stated.
d 3.1 TEST SEQUENCE: 1 U The test sequence, as stated below, was followed for the execution of the qualification program: y 3.1.1 Mechanical Li fe Test 3.1.2 Radiation Soak Test
,", 3.1.3 Thermo Cyclic Aging Test 3.1.4 Resonant Frequency Search 3.1.5 Dynamic Shake Table Test 3.1.6 Static Bend Test 3.1.7 Abno rmal Ambient Simulation (L.O.C.A.)
3.2 TEST SET-UP: Testing was per formed on the test specimen a s described in pa rag raph 2.0. The test specimen was mounted on a test fixture with eighteen (18) 2 1/4 inch-80N studs and nuts of A-540, Grade B23, C1. 5 material. The test fixture was designed such that the test specimen was oriented with it's stem axis at a 45 degree incline to the horizontal. This is the normal _ in-service orientation of the test specimen. The solenoid valves and limit switches were wired to a power source, and the air supply was piped into the mani fold. A load cell wa s located in the stem receptacle (ie. between the stem and the r ig id f ix t u r e) to record the actuator thrust a t the bottom of it's stroke. ~ v Temperature sensors-were located on the outside of the
. hydraulic speed control cylinder and on the bottom spring plate for the thorno cycling test. The sensor located on the
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. STR-060578-1 PAGE 6
/ 7 v,, - u 3.2 TEST SET-UP CONTINUED hydraulic speed control cylinder was used fo r the mechanical life test. An electric timer, used for measuring the closing / opening time, was wired to the open and closed position switches and solenoid control valve circuits. The wiring was so a rranged tha t the timer started when the solenoid control valves we r e d e-ene rgi zed and stopped when the closed position swi tch was actua ted by the bottom spring plate (when it reached
- it's closed posi tion) . The time recorded was f o r the major portion of the stem's travel. Due to overtravel of the closed position switch the entire stroke was not timed by this method.
To compensa te fo r this discrepa ncy the measured time was multiplied by the ra io of the total stroke divided by the - distance travelled during the measured time to yield the final closing time. The co r rected values a re given throughout this r epo r t .
, The a i r supply to the test specimen wa s filtered to a minimum of 50 microns, oil free and dried to a dew point of -40 d eg re es F. Air inlet pressure was maintained within the range of 90 psig to 100 psig. The power source to the solenoid valves and limit switches was nominally 115 volts A.C., 60 Hz, single phase.
V Test pa rame ter s recorded during the test sequence were compa red to the following limits: OUTPUT T!! RUST (a t the bottom of the stroke) - 28000 pounds minimum CLOSING TIME (corrected value) - 3 to 5 seconds OPENING TIME (corrected value) - 6.5 to 19.5 seconds PNEUMATIC SYSTEM LEAKAGE (valve open or closed) .5 SCFH maximum 3.3 MECIIANICAL LIFE TEST The Mechanical Li f e Test is intended to demonstrate the adequacy of the mechanical componets of the test specimen when subjected to conditions of accelerated wea r. The test specimen is expected to experience 120 cycles per year for a period of 40 years (4800 test cycles) . The,120 cycles per year are comprised of 96 excercising cycles and 24 o pe ra ting cycles . This test simulates the ope ra ting conditions of the actua tor - when in actual service. In addition to the instrumentation previously mentioned in the test set-up, the test specimen's ambient humidity was maintained at a value of not less than S5t R . II . . The specimen's hydra ulic oil temperature wa s moni to red and not allowed to exceed 350 deg rees F. v I 3.3.1 The test specimen wa s subjected to a to ta l of 4800 actuation cycles consisting of 960 operating cycles and 3840 exercising cycles. One (1) ope rating cycle was f rom the full
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STR-060578-1 PAGE 7 g . l
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w h 3.3 MECHANICAL LIFE TEST CONTINUED P h' open position to the full closed position and returned to the g full open positon. One (1) exercising cycle is from the full open position to 90% of the full open position a nd return to j the full open position. 1 3.3.2 Normal hands on maintenance was allowed (but not L performed) at intervals of every 120 actua tor cycles. E The re fo re , testing was conducted in forty (40) intervals of 120
,0 actuator cycles each (total 4800 Cycles) . The 120 actua tor ' cycles were comprised of 24 operating cycles and 96 exercising q,; cycles, i.
f; 3.3.3 The first 39 test intervals (4680 cycles) were performed as follows:
- 1) 20 operating cycles
- 2) 96 exercising cycles
- 3) 4 operating cycles lll l 120 cycles total Prior to the fortieth test interval all the non-metallic
- j. 3.3.4 i components were replaced by Atwood & Morrill's designated y representitives. Handling assistance was provided by AECO's T technical sta f f .
i. [, 3.3.5 The .following data was recorded every fourth (4th) test
; interval (480 cycles): ,) 1) OUTPUT THRUST (28,000 pounds min.)
- 2) CLOSING TIME (3 to 5 seconds) 1 3) OPENING TIME (G.5 to 19.5 seconds E 4) PNEUMATIC LEAKAGE (0.5 SCFH maximum)
' 5) OIL TEMPERATfjRE (350 deg rees max.) ! 6) AMBIENT TEMPERATURE f
- 7) HUMIDITY (55% R.H. min.)
i 3.4 RADIATION SOAK TEST
! The Radiation Soak Test was intended to demonstrate the . acceptability of non-metallic actua tor assembly components when -- ; subjected to Gamma radiation. The non-metallic components of ; the test specimen uere subjected to an accumulated air equivalent dose of 17.4 M Rads. This dose wa s representative l of the expected life dose under normal conditions (7.4 M i
Ra d s . ) , plus a one-time po s t ul a ted accident condition dose
. (10.0 M Rads.).
U 3.4.l' The ~ radiation soak test wa s pe r fo rmed on the valve operator, plus a special receptacle containing the valve pa c k i ng .
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STR-060578-1 PAGE 8
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~ w 3.4 RADIATION SOAK TEST CONTINUED I
3.4.2 Dosimetry was performed using an integrating Dosimeters and a timer was used to record the exposure time. All instruments were calibrated and their calibration is traceable 4 to the NBS. d G 3.4.3 The test specimen's operating pa rameters , a s d esc ribed in paragraph 3.2 herein, were measured be fore and a f ter exposure to the radiation, - y 5 3.4.4 The valve operator and special receptacle were placed in The air
- ! a Garma radiation field in a horizontal orientation.
" equivalent dose rate as measured at the specimen's centerline
- . was approximately 0.5 M Rads, per hour.
3.4.5 The valve operator and special receptacle were ro ta ted in order 180 degrees at approximately half the integrated dose,
- to achieve best dose uniformity.
3.4.6 The irradiation was conducted in air at ambient temperature, barometric pressure and relative humidity prevalent at the test sight.
,t 3.5 THERMO CYCLIC AGING TEST:
The Thermo Cyclic Aging Test was intended to demonstrate
- the acceptability of the test specimen when subjected to the elevated temperatures thermo cycles and operational cycles a t normally experienced in the containment o f a Boiling Water Reac to r .
The required 612 actua tor cycles at 225 +/- 15 degrees F
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were distributed throughout the 40 the rmo cycles, (15 ac ua tor cycles per thermo cycle) . 3.5.1 Instrumentation was installed as described in pa rag ra ph 3.2 herein. A recorder was used to continuously monitor and record the temperature of the bottom spring pla te of the test
' specimen.
3.5.2 The test specimen was installed in an environmental test chamber capable o f generating temperature transients between 70
+/- 15 deg rees F and 225 +/- 15 deg rees Fat a rate of 65 +/-
35 degrees F per hour. The test specimen was installed in the chamber utilizing the 45 deg ree inclined fixture. J .-
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STR-060578-1 PAGE 9
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3.5 TilEIU40 CYCLIC AGING TEST CONTINUED 3.5.3 The test specimen was subjected to a to tal o f 4 0 thermo
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cycles from 70 +/- 15 d eg rees F to 225 +/- 15 d eg rees F and return to 70 +/- 15 deg rees F a t a ra te of 65 +/- 3 5 deg rees F per hour. Tem pe ra t ur e wa s m ea s u r ed a nd recorded from the surface of the bottom spring plate. 3.5.4 On each of the first 39 thermo cycles, when the tem pe ra t u r e of the bottom spring plate reached 225 +/- 15 degrees F, the test specinen was subjected to two (2) ope ra ting o cycles followed by twelve (121 exercising cycles and then followed by a single operating cycle for a total of fifteen (15) actuation cycles. One operating cycle is from the full open to the full closed to the full open position. One exercising cycle is from the full open position to 90% of the full open position and return to the full open position. 3.5.5 Test da ta as described in pa rag ra ph 3.2 (ie., output V thrust, opening and closing times and pneumatic leakage) was accumulated during the last operating cycle ofThe every o pe fourth ra ting thermo cycle (every 60 actuator cycle s) .
- characteristics were to be maintained within the specified limits.
3.5.6 Upon completion of thirtynine (39) thermo cycles, 585 act ua to r cycles (458 ex e rc i sing cycles and 117 operating cycles) , the last thermo cycle was pe rfo rmed in accordance with pa rag ra ph 3.5.7 herin. 3.5.7 When the surface temperature of the bottom spring plate reached 225 +/- 15 deg rees F the test specimen was subjected This to 7 exercising cycles followed by 20 operating cycles. completed a total of 612 actuator cycles (475 exercising cycles and 137 ope ra ting cycles) . Test data a s de fined in pa rag ra ph
- 3. 2 he re in wa s recorded on every fif th (5 t h) operating cycle.
The operating characteristics were to be maintained within the __ speci fied limits. 3.5.8 Normal hands on maintenance was allowed (but not required) at the completion o f every the rno cycle. V
*6 STR-060578-1 PAGE 10 in Q. u 3.6 RESONANT FREQUENCY SEARCH:
The Resonant Frequency sea rch wa s pe r formed on the test specimen a s mo unted in the 45 degree test fixture (see pa rag ra ph 3. 2) . The specimen and fixture were mounted to the table of the seismic vibration simulator utilizing (32) 1/2 inch g rade 8 cap sc rews , flat wa shers a nd lock washers. This set-up r e pre s e n ted the normal in-service installation and orientation of the test specimen. 3.6.1 Five (5) uniaxia) accelerometers we re installed on the test specimen and the seismic table . One (1) control acceleromete r wa s installed in the direction of the input motion and cne control accelerometer was located in an of f axis direction in order to facilitate the evlauation of any possible specimen / fixture / table resonances. Three monitor accelerometers were mounted to the test specimen. Ea c h resonace observed, if any, was scruntinized for a spec im en/ fi x tur e/ table characteristid. All resonances determined to be specimen / fixture / table originated were noted on the test data and ignored as a specimen originated
. resonance. The actual location the accelerometers may be found V in the TEST RESULTS section of this report.
3.6.2 The test specimen was evaluated for specimen originated
, resonances in both the full open and full closed positions.
3.6.3 The test specimen wa s subjected to a slow sine sweep (approxima tely one-octave per minute) in the f requency range of 1 to 50 Hz. Tne sine sweep was stopped a t each in teg ral test frequency, in the range of 1 to 50 Hz, for a period of approximately 40 seconds in order to accumulate response data. 3.6.4 The input acceleration was approximately 0.3 g applied to each orthogonal direction. 3.6.5 The first test axis was in the vertical direction, the second test axis wa s in the horizontal direction (along the stem's direction) and the last test axis was horizontal (across the stem's direction) this wa s accomplished by rotating the _ specimen and test fixture 90 deg rees (about the vertical) on the seismic table. This input sequence was not in accordance with the test procedure but wa s determined to be acceptable in light of the convenience of the test set-up. 3.6.6 A specimen originated structural resonance wa s de fined as an amplification (output g/ input g) of 3 times or g reater.
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- STR-060578-1 PAGE 11 v- -
a 3.7 DYNAMIC SilAKE TABLE TEST ( ABNORMAL SERVICE) : The test specimen's limit swi tch assemblies and air manifold assembly components were subjected to a dynamic seismic simulation test to demonstrate their ability to operate under dynamic seismic loads.
" The specimens (each in turn) were mounted to a test fixture with actual fasteners used in service. The specimen and fixture were then mounted to the seismic table simulating normal in-service mounting and orientation.
The specimen was then subjected to seismic dwell tests, at , each integer f requency, in the range of 1 to 35 Hz. The input o motion wa s continuous-sine in wave f orm and was applied for a minimum uninterrupted period of thirty (30) seconds each. The input motion wa s in accordance with figure 3. The input was applied to the horizontal and vertical axes simultaneously, in-pha se , a nd a t a n a ngl e o f 34 d eg rees from the horizontal. Each dwell was repea ted with the inputs simultaneous but 180 deg rees out-o f-pha se (ie., specimen and fixture rota ted 180 deg rees about the vertical on the seismic table). Three (3) y response accelerometers, located on the specimen, were recorded at each f requency. Upon completion o f dwell testing in the first biaxial pair, the specimen and fixture we re rota ted 90 deg rees about the vertical resulting in the second biaxial pair. The above dwell tests were then repeated in their entirety for the second biaxial pair. There were a total of four (4) test input motion orientations as follows:
- 1) Vertical and horizontal inputs in-phase; equi pment in the first horizontal axis.
- 2) Vertical and ho ri zon tal inputs 180 deg.
o u t-o f-pha se ; equipment in the first horizontal axis. Equipment and fixture rota ted 90 deg rees about the ~ vertical on the seismic test table.
- 3) Vertical and horizontal inputs in-phase; equi pment in the second horizontal axis. inputs 180 deg.
- 4) Vertical and horizontal out-of-phase; equipment in the second horizontal axis.
Dwell testing wa s re pea ted for the above input v-a motion o rientations.
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. STR-060578-1 PAGE 12 y.g/ -
I. 3.7 DYNAMIC SIIAKE TABLE TEST CONTINUED The following measurements we re ta ken d uring' the dynamic seismic simulation test. Air fianifold Specimen
- Accelerometer readings.
- Air leakage, as measured from the air make-up line.
- Ope ra tion of the air valves at each integer frequency.
. Limit Switch Assemblies
- Accelerometer readings.
- Switch continuity /non-continuity.
- Switch operation a f ter each integer frequency.
Following the dynamic seismic simulation testa the air manifold and limit switch assembly were re-installed on the actuator. The actuator was then tested for air leakage utilizing a flow meter in the air make-up line. This test was y per formed a t room ambient conditions with the specimen in the full open and full closed positions. No maintenance was performed on the specimen during this test. 3.8 STATIC SEISMIC SIMULATION TEST ( ABNORMAL SERVICE) : The test specimen wa s subjected to a static seismic loading test to demonstrate it's ability to operate under seismic loads. The specimen and loading system were mounted to a restraining fixture with the specimen's stem inclined at an angle of 45 deg rees from the horizontal (see figure 4) . The specimen was then subjected to a series of five side loads of 46080 pounds. These load s. spa nned the required "g" load through the c .g . of the actua tor in both the valve open and valve closed positions. The load was applied along a line - of 45 degrees from the horizontal and extending from the centerline of the upper spring retaine r flang e downwa rd. The specimen wa s o p e ra't ed a minimum o f once per load increment (5 times to ta l) from full open to full closed and returned to full open. v
- 46080 pounds is the load synonymous with 14.4g x 3200 pounds resultant:
loading.
. 4 STR-060578-1 PAGE 13
[
'M V v]
3.8 STATIC SEISMIC SIMULATION TEST CONTINUED The specimen's output fo rce , closing time, opening time and the applied load were recorded for each of the load increments. Upon completion o f the static seismic loading test the specimen was tested for air leakage util.izing a flow meter in the ai r ma ke-up line. This test was per fo rmed a t room ambient conditions with the specimen in the full open and full closed positions. No maintenance was performed on the specimen during the test.
; 3.9 ABNORMAL ENVIRONMENT TEST (LOCA):
The test specimen was subjected to an aonormal environment test (LOCA) to demonstrate it's ability to operate during a postulated loss of coolant accident. The test specimen was installed in an auto-clav e test chamber and the specimen / chamber combination inclined at an angle of 45 deg rees f rom the ho r i zo n ta l (see figure 4 ) . Tne y specimen wa s then subjected to the abnormal environment test profile as shown in figure 5. During the first hour (while a t the extreme temperature and pressure) of the test profile the specimen was cycled once every ten (10) minutes. The specimen was then maintained in the fully extended position for the remainder of the test. The specimen's output force, closing time and opening time were recorded, for in f o rma tion purpo ses , wh ile the ac tua to r wa s cycled. The specimen's air leakage was monitored, during the open a nd closed positions, with a flow meter in the ai r ma ke-up line. The chamber's a tmo s ph e r i c conditions ( tem pe ra ture , pressure and hum id i ty) , as a pplicable , were continuously monitored and periodically recorded during the test profile. ,_ Upon completion of the abnormal environment test the specimen's output force, closing time a nd opening time were recorded when the specimen wa s o pe ra ted with normal air pressure. The output force with spring only extension wa s measured and air leakage was measured with the specimen in the f ull open and full closed positions utilizing a flow meter in V the air make-up line. These tests were per fo rmed a t room ambient conditions During the entire test period, no maintenance wa s performed on the test specimen.
e -. 2
/ STR-060578-1 PAGE 14 . . . . J (wI '
TEST RESULTS
.' 4.0 MECHANICAL LIFE TEST The following data wa s obse rved and recorded during the progress of the Mechanical Li fe Test :
Note: The values given below a re in; Load in KIPS, Time in seconds, and leakage in SCFH. ACTUATOR OUTPUT STROKE TIME PNEUM LEAK CYCLE NO. OIL TEMP AMB TEMP REL HUM LOAD OPEN CLOSE OPEN CLOSE 350F MAX DEGREES F PERCENT BASELINE 42.1 10.26 3.93 0 480 0 70 DEG F 68 DEG F 70% - 42.2 10.28 4.08 0 0 86 DEG F 69 DEG F
'960 42.1 10.27 3.99 0 66%
1440 0 97 DEG F 70 DEG F 65% 41.8 10.40 3.97 0 0 80 DEG F 1920 68 DEG F 62% 41.8 10.46 3.94 0 0 85 DEG F 68 DEG F "2400 41.8 10.15 4.12 0 62% 2880 0 96 DEG F 69 DEG F 64% 41.8 10.26 4.08 0 0 72 DEG F 3360 41.8 10.28 69 DEG F 62% 3.97~ 0 0 93 DEG F 69 DEG F 3840 41.8 10.26 4.02 0 61%
>4320 0 98 DEG F 69 DEG F 64%
41.8 10.31 4.02 0 0 103 DEG F
.680 41.8 10.14 69 DEG F 63%
4.08 0 0 89 DEG F 69 DEG F 65% V
". At this point in the program the test was halted in order to replace the pneuma tic seals.
The three (3) solenoid coils were also replaced due to a noise eminating from the pneumatic. control sub-system. This noise was first noticed during actua tor cycle number 4 672. ACTUATOR OUTPUT STROKE TIME PNEUM LEAK CYCLE NO. OIL TEMP AMB TEMP REL HUM LOAD OPEN CLOSE OPEN CLOSE 350F MAX DEGREES F PERCENT 4797 41.8 10.24 4.04 0 4798 0 79 DEG F 68 DEG F 58% 41.8 10.12 4.02 0 0 80 DEG F 68 DEG F 4799 58% 41.8 10.09 3.96 0 0 80 DEG F 68 DEG F 4800 41.8 10.14 58% 3.99 0 0 81 DEG F 68 DEG F 58% There was no evidence o f malf unction , d eg reda tion o f performance or physical damage noted as a result of this test. Seal and solenoid replacement are considered to be normal maintenance procedures.
+ .
*b
.. J STR-060578-1 PAGE 15
- TEST RESULTS 5.0 RADIATION SOAK TEST The Radiation Soak Test was performed by:
Radiation Technology, Inc. Lake Denmark Road Rockaway, New Jersey 07'866 The Pre and Post Test data was accumulated by AECO personnel and is as follows: Post-Test
Pre-Test Runi Run2 OUTPUT LOAD (KIPS): 41.8 41.8 41.4 STROKE TIME (SEC.):
Close 3.97 4.08 4.08 Open 10.28 10.59 10.57 PNEUMATIC LEAKAGE (SCFH): 0 0 0
%=/ Close Open 0 .0 0 OIL TEMPERATURE 69 60 60 (DEG . F) :
AMBIENT TEMPERATURE 69 60 60 (DEG.F): There wa s no evidence o f mal f unc t io n , d eg rada tio n of performance or physical damage observed as a result of the The Irradiation Processing Ce rtifica tion stress o f this test. may be seen in appendix A of this report. 6.0 THERMO CYCLIC AGING TEST: The following data wa s obse rved a nd recorded during the -- prog ress o f the Thermo Cyclic Aging ' Test (Note the values given below are; Load in KIPS, Time in Seconds and Leakage in SCFH): t
\w i
I ( -_ -
STR-060578-1 PAGE 15A y
/ 1
- TEST RESULTS k) 9 A-{_]}
6.0 T!!ERMO CYCLIC AGING TEST - TEMPERATURE EXTREMES TEMPERATURES (DEGREES PAllRENIIEIT) LOW TEMP HIGH TEMP CYCLE A LOW TEMP HIGH TEMP CYCLE # 65 210 21 60 224 1 225 j 2 75 75 223 221 22 23 62 63 224
;. 3 75 220 24 55 222 4
63 221 25 70 225
'i 5 64 220 26 60 210 6
75 221 27 75 226 [ 7 8 55 216 28 70 224 75 224 29 70 223 9 66 211 30 74 220 10 222
" 11 65 211 31 75 70 221 32 75 212 " 12 218 13 80 225 33 73 75 215 34 93 215 14 73 223 35 80 213 " 15 212 16 60 223 36 75 g ,f 226 37 75 220 - 17 90 75 225 38 85 222 18 70 220 39 75 221 19 73 225 40 70 222 20 l
O I
%) ._
W6% M -
r
~
STR-060578-1 PAGE 16 Qfi
- ss TEST RESULTS 6.0 THERMO CYCLIC AGING TEST CONTINUED ACTUATOR OUTPUT STROKE TIME PNEUM. LEAKAGE OIL TEMP. AMB. TEMP.
OPEN CLOSE OPEN CLOSE 350F MAX. DEGREES F
~ CYCLE NO. LOAD i '
41.9 10.7 3.97 0 0 64 deg.F 64 deg.F Base line - - 65 deg.F 60 - - 1 42.8 10.8 3.68 0 0 221 deg.F 220 deg.F 60 - - 69 deg.F
'.:' .l 120 - - -
216 deg.F 120 41.9 10.77 3.78 0 0 218 deg.F
- - - 71 deg .F 180 - - -
10.80 3.73 0 0 222 deg.F 221 deg.F
.. 180 41.8
- - 67 deg.F
,, 240 - - -
223 deg.F 240 41.8 11.40 3.78 0 0 225 deg.F
- - - 70 deg.F 300 - - -
225 deg.F 10.75 3.75 0 0 226 deg.F
;, 300 41.9
- - - 68 deg.F 360 - - -
41.9 10.82 3.78 0 0 223 deg.F 222 deg.F
\=/
360 - - - 71 deg.F i 420 - - - 224 deg.F 420 42.1 10.68 3.76 0 0 225 deg.F
- - - 73 deg .F r a 480 - - -
212 deg.F 10.52 3.97 0 0 213 deg.F 480 41.9
- - - 71 deg.F 540 - -
212 deg.F 42.1 10.95 3.69 0 0 213 deg.F 540 - - - 71 deg.F
- 597 - -
221 deg.F 10.87 3.68 0 0 221 deg.F j 597 41.2
- - - 73 deg.F l 602 - - -
222 deg.F 10.96 3.74 0 0 223 deg.F 602 41.3
- - - 72 deg.F 607 - -
222 deg.F 11.02 3.79 0 0 222 deg.F 607 41.5
- - - 70 deg .F 612 - -
223 deg.F 10.98 3.65 0 0 225 deg.F 612 41.3 1 The re was no evidence of malf unction , d eg rada tio n of f per formance or physical damage observed as a result of the I stress of this test. A typical temperature recording of the bottom spring plate may be seen in appendix A of this report. 7.0 RESONANT FREQUENCY SEARCli: The followi ng da ta wa s obse rved and recorded during the progress of the Resonant Frequency Sea rch Test: l l l
/J STR-060578-1 PAGE 17
,, /
g,; - -
' TEST RESULTS
- 4 7.1 VERTICAL AXIS:
, _ _- Accelerometer Loca tions:
Input- 1) Control Vertical
- 2) Control Horizontal Outputs- 3) On Junction Box Vertical
- 4) On Air Cylinder Upper Flange Vertical
,, 5) On Top of the Hydraulic
.! Cylinder Vertical The following data was taken during the resonance search in the vertical axis. Any resonances not specifically
- ~ - determined to be specimen originated were noted as specimen / fixture / table resonances but were ignored as specimen
- produced, g,j Resonances were observed on the junction box in the vertical direction. A resonance at 20 Hz (amplification factor 3.2) and 40 Hz (amplification f a c to r 19.7) were located with the valve in the closed position. A resonance at 41 Hz (ampli f ica tion' f ac to r 6.7) wa s loca ted with the valve in the open position.
VERTICAL AXIS (Valve Closed) : FREQUENCY INPUT (g) OUTPUTS (g) 2 3 4 5
- (Hz) 1 1 0.1 n/a 0.1 0.1 0.1 2 0.2 n/a 0.2 0.2 0.2 3 0.2 n/a 0.2 0.2 0.2 4 0.2 n/a 0.2 0.2 0.2 5 0.2 n/a 0.2 0.2 0.2 6 0.2 n/a 0.2 0.2 0.2 -
7 0.2 n/a 0.2 0.2 0.2 8 0.2 n/a 0.24 0.23 0.25 9 0.2 0.05 0.27 0.27 0.32 10 0.3 0.08 0.35 0.35 0.42 11 0.3 0.05 0.32 0.33 0.35 12 0.3 n/a 0.3 0.3 0.3 13 0.3 n/a 0.3 0.3 0.3 s_j 14 0.3 n/a O '. 3 0.3 0.3 15 0.3 n/a 0.3 0.3 0.3 16 0.3 0.05 0.42 0.39 0.39 17 0.3 0.05 0.41 0.41 0.42
e
) PAGE 18 STR-060578-1
/
V "] TEST RESULTS 7.1 VERTICAL AXIS CONTINUED: VERTICAL AXIS (Valve Closed): FREQUENCY INPUT (g) OUTPUTS (g) 1 2 3 4 5
, (H z) 18 0.3 0.05 0.47 0.46 0.49 19 0.3 0.06 0.5 0.5 0.6 20* 0.3 0.07 0.95 0.51 0.59 21 0.3 0.05 0.28 0.35 0.49
. 22 0.3 0.05 0.46 0.22 0.19 23 0.3 n/a 0.3 0.3 0.3 24 0.3 n/a 0.3 0.3 0.3 25 0.3 n/a 0.3 0.3 0.3 26 0.3 n/a 0.3 0.3 0.3 27 0.3 n/a 0.3 0.3 0.3 28 0.3 n/a 0.3 0.3 0.3 29 U.3 0.05 0.52 0.3 0.3 30 0.3 0.05 0.3 0.3 0.3
.31 0.3 n/a 0.3 0.3 0.3
. bw/ ~
32 0.3 n/a 0.3 0.3 0.3 33 0.3 0.05 0.52 0.3 0.3 34 0.3 n/a 0.3 0.3 0.3 35 0.3 n/a 0.3 0.3 0.3 36 0.3 0.05 0.8 0.3 0.3 37 0.3 0.08 1.1 0.3 0.3 38 0.3 0.08 1.5 0.3 0.3 39 0.3 0.08 3.0 0.41 0.43 40* 0.3 0.08 5.9 0.38 0.38 41 0.3 0.05 2.0 0.3 0.3 42 0.3 n/a 0.3 0.3 0.3 i 43 0.3 n/a 0.3 0.3 0.3 44 0.3 n/a 0.3 0.3 0.3 45 0.3 0.05 0.5 0.3 0.3 46 0.3 n/a 0.3 0.3 0.3 47 0.3 n/a 0.3 0.3 0.3 48 0.3 n/a 0.3 0.3 0.3 -- 49 0.3 n/a 0.3 0.3 0.3
' 50 0.3 n/a 0.3 0.3 0.3 *
- Significant Resonances observed.
Y : :.*
'," - 3 - C. . .
L. .
w -_. ~ . - -.--- - STR-060570-1 PAGE 19
)
l j TEST RESULTS Q- s. i . 7.1 VERTICAL AXIS CONTINUED:
. VERTICAL AXIS (Valve Opened) :
a INPUT (g) OUTPUTS (g) FREQUENCY 4 5 1 2 3 (Hz) of 1 0.1 n/a 0.1 0.1 0.1
" 0.2 n/a 0.2 0.2 0.2 2
0.2 n/a 0.2 0.2 0.2 8 3 0.2 n/a 0.2 0.2 0.2 4
.g 0.2 n/a 0.2 0.2 0.2 t- 5 0.2 n/a 0.2 0.2 0.2 M 6 0.2 n/a 0.2 0.2 0.2 7
0.2 n/a 0.2 0.2 0.2 8 0.2 n/a 0.2 0.2 0.2 9 0.3 n/a 0.3 0.3 0.3 10 0.3 0.3 n/a 0.3 0.3 11 0.3 n/a 0.3 0.3 0.3 12 0.3 0.3 n/a 0.3 0.3 13 0.3 0.3 n/a 0.3 0.3 g,g 14 0.3 0.3 n/a 0.3 0.3 15 16 0.3 0.05 0.4 0.4 0.4 0.3 0.05 0.52 0.52 0.53
,. . 17 0.75 0.3 0.05 0.6 0.61 18 0.81 0.3 0.06 0.5 0.6 19 0.58 0.3 0.05 0.3 0.4 20 0.3 21 0.3 n/a 0.28 0.3 0.3 n/a 0.3 0.3 0.3 22 0.3 0.3 n/a 0.3 0.3 23 0.3 0.3 n/a 0.3 0.3 24 0.3 0.3 n/a 0.3 0.3 25 0.3 0.3 n/a 0.3 0.3 26 0.3 0.3 n/a 0.3 0.3 27 0.3 0.3 n/a 0.3 0.3 28 0.3 0.3 n/a 0.3 0.3 29 0.3 0.3 n/a 0.3 0.3 30 0.3 0.3 n/a 0.3 0.3
31 0.3 0.3 n/a 0.3 0.3 32 0.3 0.3 n/a 0.3 0.3 33 0.3 0.3 n/a 0.3 0.3 34 0.3 0.3 n/a 0.3 0.3 35 0.3 0.3 n/a 0.3 0.3 36 0.3 0.3 0.05 0.7 0.3 37 0.3 0.3 0.3 0.08 0.9 38 0.3 0.3 c;j 39 0.3 0.08 0.9 0.08 1.2 0.3 0.33 40 0.3 0.3 0.05 2.0 0.3 0.3 41*
l STR-060578-1 PAGE 20
, l
. . . I V TEST RESULTS
]
7.1 VERTICAL AXIS CONTINUED: VERTICAL AXIS (Valve Opened) : INPUT (g) OUTPUTS (g) FREQUENCY 4 5 2 3-
.. (!!z) 1 0.3 0.05 1.5 0.3 0.3 42 0.3 0.3 0.05 1.2 0.3 43 0.3 0.3 n/a 0.9 0.3 44 0.3 0.3 n/a 0.5 0.3 .
45 46 0.3 n/a 0.46 0.3 0.3 0.3 n/a 0.4 0.3 0.3 47 0.3 0.3 n/a 0.3 0.3 48 0.3 0.3 n/a 0.3 0.3 49 50 0.3 n/a 0.3 0.3 0.3
- Significant Resonances observed.
7.2 HORIZONTAL AXIS (Along the Stem): V Accelerometer Locations: Input- 1) Control Horizontal
- 2) Control Vertical Outputs- 3) On Junction Box Horizontal
- 4) On Air cylinder Upper Flange Horizontal
- 5) On Top of the Hydraulic Cylinder Horizontal The following data was taken during the resonance sea rch in the horizontal axis. Any resonances not specifically determined to be specimen o r ig ina t ed were noted as specimen / fixture / table resonances but were ignored as specimen ,_
produced. Resonances were observed on the junction box in the horizontal direction. A r e so'na nc e a t 9 11 : (am pli fic a t ion f ac to r 4.5), 20 Hz (amplification factor 10) and 28 !!: (amplification f actor 7) were located with the valve in the A re sona nc e at 40 Hz closed and opened positions.
%./ (amplification f actor 9.2) was located on top o f the hyd ra ul ic cylinder with the valve in the closed position. A resonance a t 36 11 2 ( am pl i f i c a t io n f a c to r 9.6) was located on to p o f the hydraulic cylinder with the valve in the o t)ened posi tion .
PAGE 21
' ! STR-060578-1 Q,' %..
7.2 HORIZONTAL AXIS CONTINUED llORIZONTAL AXIS (Along the stem Valve opened): FREQUENCY INPUT (g) OUTPUTS (g) (!!z) 1 2 3 4 5 1 0.2 n/a 0 .'2 0.2 0.2 2 0.2 n/a 0.2 0.2 0.2 3 0.2 n/a 0.2 0.2 0.2 4 0.2 n/a 0.2 0.2 0.2 5 0.2 n/a 0.2 0.2 0.2 i 6 0.2 n/a 0.2 0.2 0.2
- 7 0.2 n/a 0.2 0.2 0.2 8 0.2 n/a 0.2 0.2 0.2 9* 0.2 0.05 0.9 0.22 0.32 10 0.3 0.05 0.61 0.3 0.3 11 0.3 0.05 0.38 0.3 0.3 12 0.3 n/a 0.3 0.3 0.3 13 0.3 n/a 0.3 0.3 0.3 14 0.3 n/a 0.3 0.3 0.3 15 0.3 n/a 0.3 0.3 0.3
%=/ 16 0.3 n/a 0.3 0.3 0.3 17 0.2 0.05 0.38 0.2 0.2 18 0.2 0.05 0.6 0.2 0.2 0.06 19 0.2 0.74 0.2 0.2 20* 0.2 0,08 2.0 0.3 0.36 21 0.2 0.05 1.2 0.2 0.2 22 0.2 0.05 0.7 0.2 0.2 23 0.3 n/a 0.38 0.3 0.3 f 24 0.3 n/a 0.3 0.3 0.3 25 0.3 n/a 0.3 0.3 0.3 26 0.3 0.05 0.63 0.3 0.3 27 0.3 0.06 0.98 0.3 0.3 28* 0.3 0.07 2.1 0.38 0.39 29 0.3 0.05 1.1 0.3 0.3 30 0.3 0.05 0.65 0.3 0.3 31 0.3 n/a 0.3 0.3 0.3 32 0.2 n/a 0.2 0.2 0.2
33 0.2 n/a 0.2 0.2 0.2 34 0.2 n/a 0.2 0.2 0.2 35 0.2 0.07 0.2 0.25 0.6 36* 0.2 0.09 0.2 0.28 0.96 37 0.2 0.05 0.2 0.23 0.55 38 0.2 0.05 0.2 0.2 0.4 39 0.2 n/a 0.2 0.2 0.2
, AO: : - 0 .- 2 m/a 0.2 0.2 0.2 bf ,r ..... _.. .. . --
_-.m -
e
~~:] PAGE 22 STR-060578-1
/
ll 4/' -[]~) 7.2 HORIZONTAL AXIS CONTINUED HORIZONTAL AXIS (Along the stem Valve Opened): INPUT (g) OUTPUTS (g) FREQUENCY 1 2 3 4 5 (!! z) 0.2 n/a 0.2 0.2 0.2
., 41 0.2 n/a 0.2 0.2 0.2 42 0.2 n/a 0.2 0.2 0.2 43 0.2 n/a 0.2 0.2 0.2 44 45 0.2 n/a 0.2 0.2 0.2 -
0.2 n/a 0.2 0.2 0.2 46 47 0.2 n/a 0.2 0.2 0.2 0.2 n/a 0.2 0.2 0.2 48 0.2 n/a 0.2 0.2 0.2 49 0.2 n/a 0.2 0.2 0.2 50
- Significant Resonances observed.
HORIZONTAL AXIS (Along the stem valve Closed): V INPUT (g) OUTPUTS (g) FREQUENCY 4 5 1 2 3 (H z) 0.2 n/a 0.2 0.2 0.2 1 0.2 n/a 0.2 0.2 0.2 2 0.2 n/a 0.2 0.2 0.2 3 0.2 n/a 0.2 0.2 0.2 4 0.2 n/a 0.2 0.2 0.2 5 6 0.2 n/a 0.2 0.2 0.2 0.2 n/a 0.2 0.2 0.2 7 0.2 n/a 0.2 0.2 0.2 8 9* 0.2 0.05 0.86 0.24 0.37 0.3 0.05 0.58 0.3 0.3 10 0.3 0.05 0.31 0.3 0.3 11 0.3 n/a 0.3 0.3 0.3 12 0.3 n/a 0.3 0.3 0.3 13 0.3 n/a 0.3 0.3 0.3 -- 14 0.3' n/a 0.3 0.3 0.3 15 0.3 n/a 0.3 0.3 0.3 , 16 17 0.2 n/a 0.27 0.2 0.2 18 0.2 0.05 0.53 0.22 0.2 19 0.2 0.05 0.76 0.23 0.2 0.06 2.1 0.3 0.33 20* 0.2 0.05 0.9 0.2 0.2 21 0.2 ss '22 0.2 0.05 0.73 0.2 0.2 s
~' hm
,' STR-060578-1 PAGE 23 g/ s TEST RESULTS 7.3 HORIZONTAL AXIS CONTINUED HORIZONTAL AXIS (Along the stem Valve Closed):
FREQUENCY INPUT (g) OUTPUTS (g) (Hz) 1 2 3 4 5 23 0.3 n/a 0.35 0.3 0.3
'! 24 0.3 n/a 0.3 0.3 0.3 25 0.3 n/a 0.3 0.3 0.3 26 0.3 n/a 0.53 0.3 0.3 .. 27 0.3 0.05 0.89 0.3 0.3 ,, 28* 0.3 0.06 1.9 0.35 0.37 .. 29 0.3 0.05 0.95 0.3 0.3 5 30 0.3 0.05 0.57 0.3 0.3 31 0.3 n/a 0.3 0.3 0.3 32 0.2 n/a 0.2 0.2 0.2 d
33 0.2 n/a 0.2 0.2 0.2 34 0.2 n/a 0.2 0.2 0.2 35 0.2 n/a 0.2 0.2 0.2 36 0.2 n/a 0.2 0.2 0.2 n/a
. 37 0.2 0.2 0.2 0.2 38 0.2 0.05 0.2 0.2 0.43 g ,j 0.2 0.2 0.55 39 0.2 0.06 40* 0.2 0.08 0.2 0.27 1.8 41 0.2 0.06 0.2 0.23 1.2 42 0.2 0.05 0.2 0.21 0.5 43 0.2 0.05 0.2 0.2 0.2 44 0.2 n/a 0.2 0.2 0.2 45 0.2 n/a 0.2 0.2 0.2 46 0.2 n/a 0.2 0.2 0.2 47 0.2 n/a 0.2 0.2 0.2 48 0.2 n/a 0.2 0.2 0.2 49 0.2 n/a 0.2 0.2 0.2 50 0.2 n/a 0.2 0.2 0.2 1
i
- Significant Resonances observed.
l HORIZONTAL AXIS (Across the Stem) : l Accelerometer Locations: l Input- 1) Control Horizontal
- 2) Control Vertical Outputs- 3) On Jur.c tion Box Ho ri zontal
- 4) On Air Cylinder Upper Flange !!o rizontal
,j
- 5) On Top o f the flydra ulic
! Cylinder !!o ri zontal l l
?
d STR-060578-1 PAGE 24 TEST RESULTS Q %
7.3 HORIZONTAL AXIS CONTINUED HORIZONTAL AXIS (Across the stem Valve Closed): The following da ta wa s taken during the resonance search in the horizontal axis. Any resonance.s not specifically determined to be specimen originated were noted as g-specimen / fixture / table resonances but were ignored as specimen produced. l Resonances were obse rved on the junction box in the horizontal direction. A resonance at 12 Hz (amplification facto r 3.7) , and 25 Hz (amplification factor 4.3) were located with the valve in the closed and opened positions. A resonance d at 40 Hz (amplification factor 4.8) wa s located on top o f the J hydra ulic cylinder with the valve in the closed position. A resonance a t 36 Hz (ampli f ic a tio n f a c to r 5.5) wa s loca ted on top of the hyd ra ulic cylinder with the valve in the opened position. HORIZONTAL AXIS (Across the stem Valve Closed): INPUT (g) OUTPUTS (g)
, FREQUENCY 5 1 2 3 4 (H z) 0.2 n/a 0.2 0.2 0.2 1
0.2 n/a 0.2 0.2 0.2 2 0.2 n/a 0.2 0.2 0.2 3
, 4 0.2 n/a 0.2 0.2 0.2 0.2 n/a 0.2 0.2 0.2 5
0.2 n/a 0.2 0.2 0.2 6 0.2 n/a 0.2 0.2 0.2 7 8 0.2 n/a 0.2 0.2 0.2 0.2 n/a 0.2 0.2 0.2 9 0.3 0.05 0.43 0.3 0.3 10 11 0.3 0.05 0.51 0.33 0.3 12* 0.3 0.05 1.1 0.37 0.3 ~~ 13 0.3 0.05 0.55 0.31 0.3 0.3 n/a 0.3 0.3 0.3 14 0.3 n/a 0.3 0.3 0.3 15 0.3 n/a 0.3 0.3 0.3 16 0.2 n/a 0.2 0.2 0.2 17 0.2 n/a 0.2 0.2 0.2 18 0.2 n/a 0.2 0.2 0.2 19 0.2 n/a ;
.- , 0.2 0.2 0.2 20 .
0.2 n/a 0.2 0.2 0.2 21 _.
~
0.2 n/a - - 0.2 0.2 0.2 22 0.3 0.3 n/a 0.3 0.3 23 . - . . . ~ _ - - . - ~ ,
PAGE 25
.' STR-060578-1 0
l k,)- \- TEST RESULTS N
! 7.3 HORIZONTAL AXIS CONTINUED HORIZONTAL AXIS (Across the stem Valve Closed):
FREQUENCY INPUT (g) OUTPUTS (g) 1 2 3 4 5 (H z)
.! 24 0.3 0.05 0.56 0.32 0.3 25* 0.3 0.05 1.7 0.35 0.3 5 0.3 q 26 0.3 0.06 0.59 0.3 27 0.3 0.05 0.39 0.3 0.3 28 0.3 0.05 0.3 0.3 0.3 29 0.3 n/a 0.3 0.3 0.3 9 0.3 3 30 0.3 n/a 0.3 0.3 d 31 0.3 n/a 0.3 0.3 0.3 32 0.2 n/a 0.2 0.2 0.2 33 0.2 n/a 0.2 0.2 0.2 9 34 0.2 n/a 0.2 0.2 0.2 3 35 0.2 n/a 0.2 0.2 0.2 36 0.2 n/a 0.2 0.2 0.2
. 37 0.2 n/a 0.2 0.2 0.2
' 0.2 0.35
- 38 0.2 0.05 0.2 39 0.2 0.06 0.2 0.2 0.65 g ,j 0.08 0.58 0.29 1.1 40* 0.2
, 41 0.2 0.06 0.41 0.26 0.7 42 0.2 0.05 0.2 0.2 0.4 43 0.2 0.05 0.2 0.2 0.2 44 0.2 n/a 0.2 0.2 0.2 45 0.2 n/a 0.2 0.2 0.2 46 0.2 n/a 0.2 0.2 0.2 47 0.2 n/a 0.2 0.2 0.2 l 0.2 1 48 0.2 n/a 0.2 0.2 0.2 n/a 0.2 0.2 0.2 49 50 0.2 n/a 0.2 0.2 0.2 l
- Significant Resonances observed.
HORIZONTAL AXIS (Across the stem Valve Opened): INPUT (g) OUTPUTS (g) _ FREQUENCY 1 2 3 4 5 (H z) 0.2 n/a 0.2 0.2 0.2 l 1 2 0.2 n/a 0.2 0.2 0.2 0.2 n/a 0.2 0.2 0.2 3 4 0.2 n/a 0.2 0.2 0.2 l 0.2 n/a 0.2 0.2 0.2 5 0.2 n/a 0.2 0.2 0.2 , ,l 6-i < mw
w .- _, . - STR-060578-1 PAGE 26
. A
/ TEST RESULTS
/ '] -
%dl -
7.3 IlORIZONTAL AXIS CONTINUED
' HORIZONTAL AXIS (Across the stem valve opened):
INPUT (g) OUTPUTS (g) FREQUENCY 2 3 4 5 (liz) 1 7 0.2 n/a 0.2 0.2 0.2 8 0.2 n/a 0.2 0.2 0.2 9 0.2 n/a 0.2 0.2 0.2
" 10 0.3 0.05 0.33 0.3 0.3 11 0.3 0.05 0.45 0.3 0.3 12* 0.3 0.05 0.89 0.35 0.3 13 0.3 0.05 0.37 0.3 0.3 14 0.3 n/a 0.3 0.3 0.3 15 0.3 n/a 0.3 0.3 0.3 16 0.3 n/a 0.3 0.3 0.3 17 0.2 n/a 0.2 0.2 0.2 18 0.2 n/a 0.2 0.2 0.2 19 0.2 n/a 0.2 0.2 0.2 20 0.2 n/a 0.2 0.2 0.2 21 0.2 n/a 0.2 0.2 0.2 22 0.2 n/a 0.2 0.2 0.2 23 0.3 n/a 0.3 0.3 0.3 g,j 24 0.3 0.05 0.56 0.32 0.3 25* 0.3 0.05 0.96 0.33 0.3 26 0.3 0.05 0.47 0.3 0.3 27 0.3 0.05 0.31 0.3 0.3 28 0.3 0.05 0.3 0.3 0.3 29 0.3 n/a 0.3 0.3 0.3 30 0.3 n/a 0.3 0.3 0.3 31 0.3 n/a 0.3 0.3 0.3 32 0.2 n/a 0.2 0.2 0.2 33 0.2 n/a 0.2 0.2 0.2 34 0.2 0.05 0.2 0.26 0.39 35 0.2 0.06 0.2 0.27 0.77 36* 0.2 0.09 0.27 0.35 0.95 37 0.2 0.06 0.21 0.25 0.66 38 0.2 0.05 0.2 0.2 0.35 0.2 n/a 0.2 0.2 0.27 39 40 0.2 n/a 0.2 0.2 0.2
0.2 n/a 0.2 0.2 0.2 41 42 0.2 n/a 0.2 0.2 0.2 0.2 n/a 0.2 0.2 0.2 43 44 0.2 n/a 0.2 0.2 0.2 0.2 n/a 0.2 0.2 0.2 45 46 0.2 n/a 0.2 0.2 0.2 0.2 n/a 0.2 0.2 0.2 47 48 0.2 n/a 0.2 0.2 0.2
'# n/a 0.2 0.2 0.2 49 0.2 50 0.2 n/a 0.2 0.2 0.2
- Significant Resonances observed.
- ~ . _ -- ~
s o e
< _J STR-060578-1 PAGE 27 j/
/*l
' TEST RESULTS 8.0 DYNAMIC S!!AF'E TABLE TEST The following da ta was taken during the Dynamic Shake Table test.*
8.1 AIR MANIFOLD ASSEMBLY . i
" BIAXIAL PAIR NO. 1 The following da ta wa s taken during the dwell testing in
' the longitudinal in-phase biaxial direction.
8 Accelerometer Locations: INPUT: 1) Vector Control, loca ted on the table a t 34 degrees. OUTPUTS: 2) On the base of the manifold, horizontal.
- 3) on the side of the control box, vertical.
%./
- 4) On the top o f the control box cover, vector 34 degrees.
- There was no evidence of physical damage, pneumatic lea kage o r malf unctions obse rved. The air valves operated normally during and a f ter each integer f requency.
The following data was ta ken during the performance of j dwell testing in biaxial pair number 1. FREQUENCY INPUT (g) OUTPUTS (g) 2 3 4 (Hz) 1 L 1 1.4 1.2 1.0 1.4 l 2.6 1.9 2.9 i 2 2.9 3 4.3 3.6 3.4 4.6 ( 4 5.8 5.2 4.2 6.2 l 5 7.2 6.0 4.6 7.6 -- ( ! 6 8.6 7.2 5.3 8.1 7 10.0 8.9 6.0 10.2 8 11.5 10.0 7.1 11.9 9 13.0 12.2 8.8 14.6 l ' 10 14.4 12.7 9.4 15.0 11 14.4 12.8 10.5 16.5
- 12 14.4 - 14.6 10.6 17.2 ks/ e 13 _14.4 . 16.7 10.9 18.6 14 14.4 14.5 11.4 18.8
- The input of 14.4g is the resultant of the specified horizontal and vertical acceleration of 12g and Og respectively.
s PAGE 28 [ STR-060578-1
" ' TEST RESULTS
. 8.0 DYNAMIC SHAKE TABLE TEST CONTINUED
- AIR MANIFOLD (BIAXIAL PAIR NO. 1)
INPUT (g) OUTPUTS (g) FREQUENCY 3 4 1 2 (H z) 14.4 12.8 11.7 18.7
- 15 14.4 12.8 10.3 16.5 " 16 17 14.4 12.8 10.2 16.4 14.4 13.2 10.9 16.0 18 15.8 14.4 12.5 11.0 19 14.4 13.8 10.8 16.2 20 14.4 10.6 .'. 21 14.4 14.4 11.8 12.5 10.1 14.8 22 14.4 12.6 9.9 15.2 23 15.1 24 14.4 12.7 10.0 , 9.9 14.8 25 14.4 12.7 .; 9.9 14.9 26 14.4 12.3 14.4 12.2 10.1 14.9 27 15.5 28 14.4 12.5 9.9 14.4 12.4 9.5 15.2 29 15.6 14.4 12.4 9.5
\=/ 30 12.3 9.1 15.3 31 14.4 14.4 12.3 9.1 15.5 32 33 14.4 12.3 9.1 14.9 14.4 12.3 9.1 14.9 34 35 14.4 12.3 9.1 14.6 BIAXIAL PAIR NO. 2 The following da ta wa s taken during the dwell testing in the transverse in-phase biaxial direction. Accelerometer Locations: INPUT: 1) Vector Control, loca ted on the table at 34 deg rees. OUTPUTS: 2) On the base of the manifold, -~ ho ri zon ta l .
- 3) on the side of the control box, vertical.
- 4) on the top o f the control box cover , vec tor 34 deg rees.
There was no. evidence of physical. damage, pneumatic h/ leakage or malfunctions observed. T,he a i r y,alve s o pe ra ted normally during and a f ter each integer frequency. o
. , _J STR-060578-1 PAGE 29 v ,J/r
'- l TEST RESULTS ks/
i 8.0 DYNAMIC S!!AKE TABLE TEST CONTINUED AIR MANIPOLD (BIAXIAL PAIR NO. 2) The following data was taken during the performance of dwell testing in biaxial pair number 2. , d FREQUENCY INPUT (g) OUTPUTS (g) (Hz) 1 2 3 4 1 1.4 1.2 .7 1.2 2 2.9 2.5 1.5 2.6
' 4.0 2.7 4.9 3 4.3 0 4 5.8 5.3 4.0 6.5 5 7.2 6.4 4.8 7.7 6 8.6 7.2 5.3 8.7
' 7 10.0 9.4 7.1 11.2 8 11.5 10.8 7.5 12.4 9 13.0 11.7 8.2 13.6 10 14.4 12.3 8.5 14.4 11 14.4 14.3 9.7 16.4 g,/ 12 14.4 16.1 10.5 17.8 13 14.4 16.7 10.7 17.8 14 14.4 20.6 12.6 20.0
, 15 14.4 17.7 12.6 20.8 16 '14.4 16.5 11.7 19.9 17 14.4 15.7 10.2 18.4 18 14.4 14.1 9.2 16.8 19 14.4 13.4 9.2 15.6 20 14.4 12.7 9.1 15.0 21 14.4 12.6 9.1 14.7 22 14.4 12.5 9.0 14.7 23 14.4 12.6 8.9 14.7 24 14.4 12.6 8.9 14.6 l 25 14.4 12.2 9.0 14.6 26 14.4 12.3 8.9 14.7 27 14.4 12.4 8.8 14.8 28 14.4 12.4 8.8 14.8 29 14.4 12.5 8.9 14.8 -
, 30 14.4 12.7 8.9 14.9 31 14.4 12.8 9.0 15.3 32 14.4 12.9 9.1 15.5 33 14.4 12.5 9.1 15.7 34 14.4 12.3 8.9 15.0 35 14.4 12.3 8.9 15.0 7
. . ~. - _ - . - - . . . . . . . - -_
/ "~ STR-060578-1 PAGE 30 t -
\_ .' TEST RESULTS 4,/
i 8.0 DYNAMIC SifAKE TABLE TEST CONTINUED AIR MANIFOLD (BIAXIAL PAIR NO. 3) The following data was taken during the dwell testing in the longitudinal out-of-phase biaxial direction. Accelerometer Locations: . INPUT: 1) Vector Control, loca ted on the table at 34 degrees. OUTPUTS: 2) On the base of the manifold,
' hori zon tal .
i
- 3) On the side of the control box, vertical.
- 4) On the top of the control box cover, vector 34 degrees.
There was no evidence of physical damage, pneumatic leakage or malf unctions observed. The ai r valves operated normally during and af ter each integer frequency.
"# The following data was taken during the per formance of dwell testing in biaxial pair number 3.
IN PUT (g) OUTPUTS (g) FREQUENCY 3 4 1 2 (H z) 1 1.4 1.3 1.0 1.5 2.6 1.8 2.8 2 2.9 3 4.3 3.6 3.5 4.7 5.1 4.0 6.1 4 5.8 7.2 6.0 4.7 7.5 5 8,6 7.1 5.4 8.1 6 7 10 9.0 6.1 10.4 10.2 7.1 12.1 8 11.5 13 12.2 8.9 14.6 9 14.4 12.6 9.3 15.1 10 17.1 14.4 12.8 10.8 11 17.1
~~
14.4 14.8 10.9 12 13 14.4 17.9 11.6 18.7 14 14.4 15.4 11.5 18.7 15 14.4 13.1 11.5 18.8 12.8 10.2 16.4 16 14.4 12.9 10.9 16.1 17 14.4 16.0 14.4 12.6 10.9 18 19 14.4 13.9 10.7 16.2 j
s _ e b STR-060578-1 PAGE 31 km/
'- TEST RESULTS 8.0 DYNAMIC S!!AKE TABLE TEST CONTINUED AIR MANIPOLD (BIAXIAL PAIR NO. 3)
FREQUENCY INPUT (g) OUTPUTS (g) 2 3 4 (liz) 1 20 14.4 11.9 10.7 15.2 21 14.4 12.5 10.1 14.5 22 14.4 12.5 9.6 15.0 23 14.4 12.6 10.0 15.1 24 14.4 12.7 9.9 15.0 i 25 14.4 12.8 9.9 15.1 26 14.4 12.3 9.7 14.8 27 14.4 12.3 10.0 14.9 28 14.4 12.4 9.8 15.5 29 14.4 12.5 9.8 15.2 30 14.4 12.4 9.4 15.6 31 14.4 12.4 9.2 15.3 32 14.4 12.3 9.2 15.5 33 14.4 12.3 9.2 14.9 34 14.4 12.3 9.2 14.8
%./ 12.3 9.2 14.6 35 14.4
' BIAXIAL PAIR NO. 4 The following data was taken during the dwell testing in the transverse out-of-phase biaxial direction.
Accelerome ter Loca tions : INPUT: 1) Vector Control, loca ted on the table a t 34 deg rees. OUTPUTS: 2) On the base of the manifold, ho ri zon tal .
- 3) On the side of the control box, vertical.
- 4) On the top o f the control --
box cover , vec tor 34 degrees. There wa s no evidence of physical damage, pneumatic lea kage o r malf unctions o b s e~ rv e d . The ai r valves opera ted normally during and a f ter each integer frequency.
.- The following data wa s ta ke n d u r i.ng the. per fo rmance of V;/ dwell testing in biaxial pair number 4.
"~
1 STR-060578-1 PAGE 32
/
/ \
1 h -] TEST RESULTS 8.0 DYNAMIC S!!AKE TABLE TEST CONTINUED AIR MANIFOLD (BIAXIAL PAIR NO. 4)
, FREQUENCY INPUT (g) OUTPUTS (g)
(Hz) 1 2 3 4 1 1.4 1.2 .8 1.3 2 2.9 2.4 1.6 2.6 - 3 4.3 4.0 2.7 4.8
- 4 5.8 5.2 3.9 6.5 5 7.2 6.4 4.6 7.8 6 8.6 7.1 5.3 8.7 7 10.0 9.4 7.1 11.8 8 11.5 10.8 7.7 12.5 9 13.0 11.7 8.2 13.6 10 14.4 12.5 8.5 14.5 11 14.4 14.0 9.9 16.6 g,/ 12 14.4 15.1 10.6 17.9 13 14.4 16.1 11.2 17.9 14 14.4 20.2 13.2 20.1 15 14.4 17.9 12.5 21.0 16 14.4 16.6 11.8 19.8 17 14.4 16.2 10.4 18.8 18 14.4 14.9 9.4 16.9 19 14.4 13.6 9.5 16.8 20 14.4 13.1 9.1 14.8 21 14.4 12.7 9.1 14.8 22 14.4 12.6 9.2 14.8 23 14.4 12.6 9.1 14.7 24 14.4 12.7 9.1 14.6 25 14.4 12.3 9.1 14.6 26 14.4 12.3 9.1 14.7 27 14.4 12.4 8.8 14.7 28 14.4 12.5 8.9 14.8 29 14.4 12.5 8.9 14.9 -
30 14.4' 12.7 8.9 15.1 31 14.4 12.8 9.1 15.3 32 14.4 12.9 9.2 15.5 33 14.4 12.8 9.2 15.4 34 14.4 12.6 9.1 15.1 35 14.4 12.5 9.0 14.8 p 4 s - -:. . - -
- =.
' e -m. . . _ : mM _
I STR-060578-1
,. PAGE 33 g,
TEST RESULTS U. 8.0 DYNAMIC SIIAKE TABLE TEST CONTINUED 8.2 LIMIT SWITCil (TIIREE SWITCII ASSEMBLY) BIAXIAL PAIR NO. 1 The following da ta in-phasewas ta ken during the dwell testing in the longitudinal
." biaxial direction.
d e Accelerometer Locations: INPUT:
;1,'
' 1) Vector Control, loca ted on
.i the tabic a t 34 deg rees.
OUTPUTS:
- 2) on the side of the
- i. enclosure, hori zon tal .
- 3) On the side of enclosure, vertical. the
- 4) On the top of the enclosure, L vector 34 degrees.
. There was no evidence of physical continuity / discontinuity, or malf unctions observed. damage, switch U assembly operated normally a f ter each integer frequency The swi tch The following da ta wa s dwell testing in biaxial pair number 1.ta ken during the performance of FREQUENCY INPUT (g)
Ulz) 1 OUTPUTS (g) 2 3 4 1 1.4 2 2.9 1.6 1.8 1.7 3 4.3 3.2 3.1 4.1 4 5.8 4.5 4.3 5.1 5 7.2 6.5 6.7 7.4 6 8.6 11.3 11.7 11.9 7 10.0 13.5 13.7 14.8 8 11.5 .12.5 13.5 14.3 9 13.0 15.9 14.1 30.2 10 14.4 14.9 13.8 14.9 11 14.4 17.6 14.9 14.8 12 14.4 18.1 14.4 14.0 13 14.4 21.3 14.4 14.5 14 14.4 22.6 14.4 16.3 24.8 11.9 16.3 .. .a. .. ... . - - - . . .... .
~~
t - _ . , _ . ,,sf~~~ ~ ~
- STR-060578-1 PAGE 34 l'
TEST RESULTS
? 'l 3
8.0 DYNAMIC SIIAKE TABLE TEST CONTINUED LIMIT SWITCH (BIAXIAL PAIR NO. 1) FREQUENCY INPUT (g) OUTPUTS (g) h 2 3 4 (Hz) 1 15 14.4 28.3 11.9 14.6 16 14.4 31.7 15.0 16.7 u 17 14.4 46.1 28.8 18.9 (. lj 18 14.4 30.3 27.6 17.5 19 14.4 19.9 28.2 17.0 8 20 14.4 19.0 27.5 16.7 k 21 14.4 9.9 24.2 15.5 -
!! 22 14.4 9.9 26.7 17.2 y 23 14.4 12.5 26.0 18.9
- i. 24 14.4 14.9 28.2 35.1 25 14.4 24.6 43.4 56.5
;, ,:2 6 14.4 24.6 27.7 51.0 '8 27 14.4 15.8 12.5 40.2 28 14.4 16.1 15.8 47.5 r 29 14.4 13.1 18.5 41.3 6 30 14.4 18.2 17.4 27.8 g ,f 31 14.4 15.2 19.4 31.3 32 14.4 21.5 26.2 40.9 6 33 14.4 22.5 30.1 47.2 ,, . 34 14.4 26.3 33.8 47.7 35 14.4 32.8 36.2 56.3 '. BIAXIAL PAIR NO. 2 The following da ta was ta ken during the dwell testing in the transverse in-phase biaxial direction.
Accelerometer Locations: f INPUT: 1) Vector Control, loca ted on the table a t 34 deg rees. OUTPUTS: 2) On the side of the enclosure, horizontal. --
- 3) On the side of the enclosure, vertical.
- 4) On the top o f the enclosure,
'vec to r 34 d eg rees .
There wa s no evidence of physical damage, switch continuity / discontinuity, or malf unctions observed. The switch gj assembly operated normally a f ter each integer frequency.
STR-060578-1 PAGE 35
- )
TEST RESULTS 4=/ s.
. 8.0 DYNAMIC SHAKE TABLE TEST CONTINUED LIMIT SWITCH (BIAXIAL PAIR NO. 2)
The following data was taken during the performance of dwell testing in biaxial pair number 2.
.. FREQUENCY INPUT (g) OUTPUTS (g) 2 3 4
- . (Hz) 1 1 1.4 1.9 1.5 1.6 2 2.9 4.8 3.8 3.9
- 3 4.3 8.3 7.1 8.2 .
4 5.8 10.6 10.1 9.2
' 5 7.2 18.4 13.3 12.5 6 8.6 22.7 14.8 14.5 7 10.0 25.6 15.2 17.8 8 11.5 31.0 21.9 16.0 9 13.0 32.5 15.7 14.9 10 14.4 29.4 21.2 21.2 11 14.4 26.5 22.6 25.1 12 14.4 29.8 15.1 24.0 13 14.4 31.6 14.4 20.8 %./ 16.8 21.7 14 14.4 32.8 15 14.4 36.1 22.5 24.5 16 14.4 33.4 18.0 22.5 14.4 35.9 23.2 23.2 17 14.4 31.0 26.0 27.5 18 14.4 29.1 23.2 23.2 19 20 14.4 27.6 29.4 21.6 21 14.4 22.0 23.0 22.4 14.4 23.5 31.5 24.5 22 14.4 23.5 31.5 27.9 23 14.4 24.7 29.5 24.5 24 25 14.4 35.7 34.8 27.8 l 38.8 26 14.4 41.3 37.7 27 14.4 41.3 36.0 41.5 14.4 49.5 42.5 49.5 28 29 14.4 50.8 46.7 50.8 30 14.4 42.2 35.4 37.6 ,,
14.4 49.5 41.3 39.2 31 f 32 14.4 40.7 34.1 26.1 14.4 29.9 26.6 33.5 33 39.4 14.4 21.0 17.0 34 38.7 l 35 14.4 17.9 19.6 J
s _ i- STR-060578-1 PAGE 36 (y - s,
- TEST RESULTS 8.0 DYNAf1IC SHAKE TABLE TEST CONTINUED LIMIT SWITCII (BIAXIAL PAIR NO. 3)
The following data wa s taken during the dwell testing in the longitudinal out-of-phase biaxial direction. Accelerometer Loca tions : 8 INPUT: 1) Vector Control, loca ted on the table a t 34 deg rees. OUTPUTS: 2) On the side of the enclosure, horizontal.
- 3) On the side of the enclosure, vertical.
- 4) On the top of the enclosure,
., vector 34 degrees.
There was no evidence of physical damage, switch continuity / discontinuity, or malfunctions observed. The switch assembly operated normally a f ter each integer frequency.
\d The following data wa s ta ken during the per fo rmance of dwell testing in biaxial pair number 3.
FREQUENCY INPUT (g) OUTPUTS (g) (Hz) 1 2 3 4 1 1.4 1.6 1.8 1.7 2 2.9 3.2 3.1 4.0 3 4.3 4.4 4.4 5.0 4 5.8 6.7 6.6 7.4 5 7.2 11.2 11.6 11.8 6 8.6 13.3 13.7 14.5 7 10.0 12.4 13.5 14.3 8 11.5 15.9 14.0 30.0 9 13.0 14.9 13.8 15.0 10 14.4 17.5 15.0 14.9 11 14.4 18.8 14.5 14.5 12 14.4 22.6 14.5 14.4 13 14.4 22.6 14.5 15.0 14 14.4 25.1 11.9 16.2 15 14.4 28.6 11.9 15.1 16 14.4 31.9 15.1 16.6 17 14.4 46.2 29.1 18.8 18 14.4 31.1 27.5 17.6 19 14.4 19.8 28.1 17.5 d
STR-060578-1 PAGE 37 4
. )
TEST RESULTS
%wd 8.0 DYNAMIC SilAKE TABLE TEST CONTINUED LIMIT SWITCH (BIAXIAL PAIR NO. 3)
FREQUENCY INPUT (g) OUTPUTS (g) 3 4 (liz) 1 2 20 14.4 19.9 27.8 15.1 21 14.4 10.'4 24.0 14.7 22 14.4 10.2 26.5 17.0 23 14.4 12.8 26.3 19.1 24 14.4 15.1 27.6 -35.5 25 14.4 24.5 43.0 56.0 26 14.4 24.4 28.2 53.1
. 27 14.4 15.9 14.8 42.0 28 14.4 16.5 16.1 49.0 29 14.4 13.5 19.9 42.0 30 14.4 18.4 17.5 28.0 31 14.4 15.1 19.6 31.2 32 14.4 21.4 27.7 42.5 33 14.4 23.0 31.0 47.2 34 14.4 26.2 34.1 48.1 35 14.4 33.0 37.6 55.8 %=/
BIAXIAL PAIR NO. 4
- The following data was taken during the dwell testing in the transverse out-of-phase biaxial direction.
Accelerometer Locations: INPUT: 1) Vector Control, located on the table at 34 deg rees. OUTPUTS: 2) On the side of the enclosure, horizontal.
- 3) On the side of the enclosure, vertical.
- 4) On the top of the enclosure, vector 34 degrees.
There was no evidence of physical damage, switch continuity / discontinuity, or malf unctions observed. The switch assembly operated normally a f ter each integer frequency. The following data was ta ken during the per formance of dwell testing in biaxial pa i r number 4. V w - y w-- -m ; 7 w
~ _ . . . . ~ _ _ . _ _ _ .
. , ~J STR-060578-1 PAGE 38 l s(I
%wd ' '-{I)) _
TEST RESULTS 8.0 DYNAMIC SIIAKE TABLE TEST CONTINUED LIMIT SWITCII (BIAXIAL PAIR NO. 4) FREQUENCY INPUT (g) OUTPUTS (g) 2 3 4 (IIz) 1 l, 1 1.4 1.9 1.5 1.7 2 2.9 4.7 3.5 3.8 3 4.3 8.1 7.2 8.3
. 4 5.8 10.44 10.0 9.0 5 7.2 18.5 13.5 12.4
; 6 8.6 22.0 15.0 14.5 7 10.0 25.5 15.0 17.6 8 11.5 30.1 20.9 16.2 9 13.0 32.2 15.6 14.5 10 14.4 29.5 21.0 22.0 11 14.4 26.4 22.3 25.5 12 14.4 29.0 14.7 23.9 13 14.4 31.0 14.5 21.0 14 14.4 33.4 15.6 21.7
(,/ 15 14.4 36.4 22.4 24.7 16 14.4 33.4 17.6 22.2 17 14.4 35.8 23.0 23.4 18 14.4 31.0 26.0 27.5 29.1 19 '14.4 23.2 23.0 20 14.4 27.5 29.1 22.6 21 14.4 23.5 23.4 20.0 22 14.4 23.0 30.8 25.1 23 14.4 23.0 30.1 26.2 24 14.4 24.7 29.3 24.1 25 14.4 36.0 34.9 28.0 26 14.4 40.3 38.2 39.0 27 14.4 41.1 36.5 40.8 28 14.4 49.0 43.1 46.7 29 14.4 49.7 46.5 50.9 1 30 14.4 43.4 35.5 37.6 31 14.4 49.5 41.4 39.1 32 14.4 41.1 34.3 26.2 -- 33 14.4 30.0 26.5 35.1 34 14.4 21.7 16.9 39.5 35 14.4 18.0 19.2 37.4 V
' d *J STR-060578-1 PAGE 39
>0 s.
TEST RESULTS y, 8.0 DYNAMIC SIIAKE TABLE TEST CONTINUED 8.3 LIMIT SWITCil (t40 SWITCil ASSEMBLY) BIAXIAL PAIR NO. 1 The following data was ta ken during the dwell testing in the longitudinal in-phase biaxial direction. 1 Accelerometer Locations: INPUT: 1) Vector Control, loca ted on the table at 34 deg rees. N OUTPUTS: 2) On the side of the enclosure, horizontal.
- 3) On the side of the enclosure, vertical.
- 4) On the top o f the enclosure, vector 34 degrees.
There wa s no evidence of physical damage, switch continuity / discontinuity, o r malf unctions obse rved. The switch 4./ assembly operated normally a f ter each integer f requency. The following data was ta ken during the per formance of dwell testing in biaxial pair number 1. FREQUENCY INPUT (g) OUTPUTS (g) 2 3 4 (Hz) 1 1 1.4 2.8 1.8 1.5 2 2.9 5.8 3.6 3.0 4.3 11.5 5.7 5.4 3 5.8 15.2 6.3 5.7 4
- 5 7.2 21.2 14.7 13.8 6 8.6 21.4 15.1 14.0 7 10.0 23.0 21.1 18.4 8 11.5 17.2 24.9 11.7 13.0 26.0 23.9 22.6 9
10 14.4 24.2 13.6 13.1 11 14.4 26.0 16.1 16.1 14.4 27.4 13.9 13.0 12 14.4 29.1 11.2 15.6 13 14.4 30.0 13.4 18.6 14 W
STR-060578-1 PAGE 40
)
/':j g,j s
- TEST RESULTS 8.0 DYNAMIC SIIAKE TABLE TEST CONTINUED LIMIT SWITCll (BIAXIAL PAIR NO. 1)
FREQUENCY INPUT (g) OUTPUTS (g) (Hz) 1 2 3 4 15 14.4 39.2 21.7 30.5 16 14.4 44.1 24.9 22.7 17 14.4 48.5 25.0 17.3 18 14.4 50.8 28.2 25.5 19 14.4 51.0 31.8 27.8 20 14.4 40.1 29.5 18.5 21 14.4 22.0 26.0 14.9 22 14.4 18.8 27.5 14.9 23 14.4 16.5 27.5 17.7 24 14.4 15.1 24.5 31.9 25 14.4 14.3 25.7 29.5 26 14.4 19.6 36.6 25.7 27 14.4 38.1 49.8 51.5 28 14.4 21.5 19.2 40.2 29 14.4 19.9 15.6 27.3 30 14.4 15.4 14.9 21.1
%"# 31 14.4 15.4 15.8 17.4 32 14.4 14.5 16.2 15.8 33 14.4 14.4 16.8 14.4 34 14.4 14.4 16.0 14.4 35 14.4 15.6 17.5 14.4 BIAXIAL PAIR NO. 2 l
1 The following data wa s taken during the dwell testing in l the transverse in-phase biaxial direction. ! Accelerometer Locations: INPUT: 1) Vector Control, loca ted on the table at 34 deg rees. 1 OUTPUTS: 2) On the side of the enclosure, horizontal. l of the l
- 3) On the side l
enclosure, vertical.
- 4) On the top o f the enclosure,
( vector 34 degrees. There was no evidence of physical damage, switch continuity / discontinuity, or malfunctions observed. The switch
'# assembly operated normally a f ter each integer frequency.
l
d STR-060578-1
'd,' /I PAGE 41
... TEST RESULTS U. I i
8.0 DYNAMIC S!!AKE TABLE TEST CONTINUED LIMIT SWITCII (BIAXIAL PAIR NO. 2) The following data was ta ken during the performance of dwell testing in biaxial pair number 2.
, FREQUENCY INPUT (g) OUTPUTS (g)
[' (IIz) 1 '2 3 4 1 1 1.4 2.5 2.5 3.6
,, 2 2.9 3 4.3 6.8 4.4 6.3 b,
11.8 5.7 6.4 4 5.8 16.4 ll 5 7.2 7.7 10.2 6 25.0 13.2 17.2 8.6 29.2 16.8 20.3 7 10.0 20.7 15.9 14.5 it 8 11.5 il 9 13.0 19.2 21.0 15.2 19.2 10.5 22.7 10 14.4 22.5 14.8 14.9 11 14.4 23.4 [ 12 15.9 14.9 14.4 26.0 13.6 17.7 13 14.4 14 14.4 25.0 6.5 9.9
%=/ 15 14.4 29.7 13.8 13.8 31.4 11.9 24.7 16 14.4 38.2 17 22.5 44.2 14.4 45.9 25.4 24.3 18 14.4 19 48.7 26.2 38.0 14.4 48.0 26.3 31.2 20 14.4 40.4 21 29.8 46.1 14.4 29.7 25.1 20.0 22 14.4 23.6 23.5 13.9 23 14.4 23.5 23.4 12.6 24 14.4 18.2 30.6 12.9 i
25 14.4 26 21.7 46.8 48.0 14.4 28.6 25.9 50.0 27 14.4 20.4 15.8 41.0 28 14.4 19.8 10.2 32.0 29 14.4 12.7 15.1 30 27.0 14.4 14.4 22.0 24.2 31 14.4 23.4 32 29.6 29.1 14.4 23.3 35.0 27.6 33 14.4 13.5 22.0 35.0 34 14.4 13.8 16.2 34.0 35 14.4 15.3 9.4 31.1
, , e 9 %
- w L
l STR-060578-1 PAGE 42
)
b
- i i s TEST RESULTS e
. 8.0 DYNAMIC SHAKE TABLE TEST CONTINUED
, LIMIT SWITCH (BIAXIAL PAIR NO. 3)
- The following data was taken during the dwell testing in h the longitudinal out-of-phase biaxial direction.
Accelerometer Locations: , N li INPUT: 1) Vector Control, located on l the table at 34 deg rees.
.i OUTPUTS: 2) On the side of the "
h; enclosure, horizontal.
- 3) On the side of the I': '
enclosure, vertical.
- 4) On the top o f the enclosure, a vector 34 deg rees.
a There was no evidence of physical damage, switch continuity / discontinuity, or malf unctions observed. The switch
;, assembly operated normally a f ter each integer frequency.
\"# The followi ng da ta wa s ta ken during the per formance of dwell testing in biaxial pa i r number 3.
"' FREQUENCY INPUT (g) OUTPUTS (g) 2 3 4 (Hz) 1 1 1.4 2.5 1.6 1.4 - 2 2.9 5.6 3.6 2.8 o 3 4.3 11.0 5.6 5.2 4 5.8 15.1 6.2 5.8 5 7.2 21.1 15.2 13.6 i
6 8.6 21.1 15.2 14.0 7 10.0 22.8 21.1 18.0 8 11.5 17.1 24.6 11.4 9 13.0 ' 25.9 23.0 22.2 10 14.4 24.1 13.9 13.0 11 14.4 25.5 16.0 16.1
. 12 14.4 27.4 13.5 12.6 I
13 14.4 29.0 11.5 15.8 14 14.4 29.8 13.5 18.8 e 15 14.4 39.1 21.7 30.0 16 14.4 43.8 24.6 22.5 17 14.4 48.6 24.9 17.5 18 14.4 49.9 28.1 25.7 19 14.4 50.8 31.4 27.0 j 4
- m-
STR-050578-1 PAGE 43
~
){
'._ TEST RESULTS
%.T -
8.0 DYNAMIC SHAKE TABLE TEST CONTINUED LIMIT SWITCH (BIAXIAL PAIR NO. 3) FREQUENCY INPUT (9) OUTPUTS (g). (Hz) 1 2 3 4 20 14.4 21 40.1 29.2 18.4 14.4 21.4 25.8 14.6 22 14.4 23 18.7 27.6 14.3 14.4 17.1 27.6 16.4 24 14.4 25 14.8 24.4 32.0 14.4 14.4 25.7- 29.5 26 14.4 19.3 27 36.4 25.2
.: 14.4 37.1 44.5 49.4 28 14.4 29 21.2 19.2 39.6 14.4 19.4 15.0 27.1 30 14.4 31 15.4 14.4 20.2 14.4 15.4 15.9 18.2 32 14.4 14.4 33 16.2 15.9 14.4 14.4 16.8 14.7 34 14.4 35 14.7 16.9 14.7 14.4 15.9 17.3 14.6 Nw/
BIAXIAL PAIR NO. 4 The following data wa s taken direction. during the dwell testing in the transverse out-of-phase biaxial Accelerometer Locations: INPUT: 1) Vector Control, loca ted on the tabic a t 34 deg rees. OUTPUTS: 2) On the side of the enclosure, hori zon tal .
- 3) On the side of the enclosure, vertical.
- 4) On the top of the enclosure, vector 34 deg rees.
There wa s no evidence of physical damage, switch j continui ty/di scontinuity, o r malf unctions obse rved. The swi tch assembly opera ted normally a f ter each integer frequency. ' The followi ng da ta was ta ken during the per fo rmance of dwell testing in biaxial pai r number 4. l
%)
\
- STR-060578-1 PAGE 44 l TEST RESULTS hm) ,
%q }
a 8.0 DYNAMIC SilAKE TABLE TEST CONTINUED LIMIT SNITCII (BIAXIAL PAIlt NO. 4). FREQUENCY INPUT (g) OUTPUTS (g) y (liz) 1 2' 3 4 il g 1 1.4 2.4 2.5 3.5 2 2.9 6.9 4.5 6.2 3 4.3 11.7 5.8 6.3 1 4 5.8 16.6 7.6 10.4 5 7.2 25.2 13.2 17.4
} 6 8.6 29.4 16.8 20.3 t- 7 10.0 20.8 16.0 14.1 8 11.5 19.2 20.8 15.2 9 13.0 19.2 10.4 22.4 10 14.4 22.5 14.4 14.4 11 14.4 23.4 16.2 14.4 12 14.4 26.1 13.5 17.1 13 14.4 - :25.2 6.3 9. 0'
%./ 14 14.4 29.7 13.5 13.5 , 15 14.4 31'.5 11.7 24.3 16 14.4 38.7 22.5 45.0
- 17 ,14.4 46.5 25.2 24.3 18 14.4 49.1 26.1 39.6 19 14.4 48.5 26.1 32.4 20 14.4 40.5 29.7 48.6 21 14.4 29.7 25.2 19.8 22 14.4 23.4 23.4 13.5 23 14.4 23.4 23.4 11.7 24 14.4 18.0 30.6 13.5 25 14.4 21.6 46.8 47.7 26 14.4 28.8 25.2 53.1 27 14.4 20.7 14.4: 40.5 28 14.4 19.9 9.9 31.5 29 14.4 12.6 14.4 26.1 30 14.4 14.4 20.7 22.5 31 14.4 23.4 29.7 28.8 -
32 14.4 23.4 36.0 27.0 33 14.4 13.5 22.5 34.2 34 14.4 13.5 16.2 34.2 35 14.4 15.3 9.0 30.6
-J W M JM
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3 STR-060578-1 PAGE 45 Q' u
, TEST RESULTS 9.0' STATIC' SEISMIC SIMULATION
'[he following data wa s obse rved and recorded during the Static ~ Seismic Simulation test. The units for the below listed da.ta are: output load in kips, opening time in seconds, and closing time in seconds.
CYCLE NO. OUTPUT LOAD OPEN TIME CLOSE TIME e
., , BASELINE 40.0 10.16 3.96 1 39.9 10.42 3.85
. 2 39.2 10.58 3.99 3.97 3 39.0 10.65 4 39.2 10.65 3.92
_5 39.2 10.59 4.00 POST
- 39.2 10.35 3.97
- NOTE: Af ter ' completion of the Sta tic Seismic Simula tion wi th ne static load applied to the actua tor.
V At the completion of the Static Seismic test the air leakage was measured with the following results: VALVE OPEN VALVE CLOSED 13.0 SCFH 14.7 SCFH The ai r leakage exceeded the specification limit (.5 SCFH) and was evaluated by Atwood Morrill personnel. The lea kag e wa s traced to the air control manifold and, after evaluation, wa s repa i red by Atwood Morr ill personnel .
- Excluding the air lea kag e noted above there wa s no evidence o f walf unction or damage noted as a result of this test.
=
_en
STR-060578-1 PAGE 46
. L a -
km/ - TEST RESULTS [ 10.0 ABNORMAL ENVIRONMENT (LOCA) The following data wa s obse rved and recorded during the Abnormal Environment test. The units for the below listed data are: output load in kips, opening time in seconds, a nd closing time in seconds. Prior to the initiation of the LOCA test the output load with springs only was recorded at 9.0 kip. CONDITION OUTPUT LOAD OPEN TIME CLOSE TIME
~
BASELINE 40.0 14.1 3.87 CYCLE 1 39.8 14.2 3.74 2 40.0 13.8 3.82 3 39.9 13.9 3.86 4 37.5 14.1 3.84 5 38.0 13.9 3.85 6 38.4 13.6 3.79 POST 36.0 15.6 3.87
\./
NOTE: Measurements were made once every ten minutes during the first hour of the extreme temperature and pressure cycle. At the completion of the LOCA test the output force was recorded with springs only at 9.0 kip. At the completion of the LOCA test the a i r lea kage was measured with the following resul ts : VALVE OPEN VALVE CLOSED 2.0 SCFM 10.0 SCFM The air leakag e exceeded the' specification limit (.5 SCFH) and was evaluated by Atwood Morrill personnel. The -- lea kag e wa s traced'to the air control manifold and, after evaluation, was repaired by Atwood Morrill personnel. Excluding minor rust there was no operational malfunctions or damage to the unit noted as a resul t o f this test. V i
. n ._
O STR-060578-1 PAGE 47
'I h* v' 11.0
SUMMARY
OP OPERATING CONDITION: The test specimen continued to perform within the required limits throughout the test prog ram. Except for the air leakage noted herein there was no evidence of malfunction, deg rada tion of performance or physical damage observed as a result of the stresses o f these tests. The air leakage in excess o f the specification limit after the static seismic simulation and the abnormal environment test did not effect the operation of the actua tor. l 12.0 RECOMMONDATIONS: None, data merely submitted.
13.0 CONCLUSION
S: y It is the function of AMERICAN ENVIRONMENTS COMPANY, INC., to report the test da ta as observed. Final evlauation of the test results shall be accomplished by Atwood & Morrill Compa ny, - Inc. 3 m
4 l e e i j STR-060578-1 PAGE 48
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4 il. APPENDIX A 4
' IRRADIATION CERTIFICATE - }
AND l 4 s TYPICAL TEMPERATURE RECORDING I 9
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,, STR-060578-1 PAGE 49 f.f .
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g TilERMO CYCLIC AGING TEST TYPICAL TEMPERATURE CIIART L *
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' R L l;.iio . T ec k . nto v. l.c. srn-060s78-1 race so
' Lake Denma rk toad Rockaway. New Jersey 07866 Q' (201) 627-2930 1R R A DI ATION PR O CESSING C E R TI FIC A T ION CUSTOMER: AMERICAN ENVIR0f'MENTS COMPANY, INC.
0891 ACCOUNT NO: March 26th thru 27th ,1978 . IRRADIATION DATE: 1 Steam Valve Operating Assembly. PRODUCT DESCRIPTION: DOSE, MEGAR AD: (+ 5%) IRR A D. B AT CH. NO, CUSTOMER LOT MINIMUM M AXIMUM 0891 - 1 N/A 17.4 N/A V l l l l l IRRADIATION MODE: Static Mode using a Cobalt-60 camma source. In air dose rate of 0.5 menarads per
~
hour as measured at assembly center line, for 34 hours 48 minutes. R EM A R KS : 00simeters used - ferrous-cupric which have been directly correlA ted to > NBS dosimetry. _, ,, CE RTIFIED: / - c7 9 .[; . (J
!fobert nuck tey, supervisor-d epotion uperations!. / Martin A. Welt. President DATE: 4/5/78 /
- s. _ _ _ _ . .. _ . . . _ . _ _ _ _
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' ' STR-060578-1 PAGE 51 t
I
't 4
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APPENDIX B I
FIGURES t e l I l . Y l 1 --
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. A STR-060578-1 PAGE~52 Q' u-FIGURE 1 l\m: 4xo Et.icTencest.
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TitERMO CYCLIC AGING AND MECllANICAL LIFE TEST SETUP
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