ML17318A507
| ML17318A507 | |
| Person / Time | |
|---|---|
| Site: | Cook  |
| Issue date: | 12/18/1979 |
| From: | Dolan J INDIANA MICHIGAN POWER CO. (FORMERLY INDIANA & MICHIG |
| To: | Harold Denton Office of Nuclear Reactor Regulation |
| Shared Package | |
| ML17318A508 | List: |
| References | |
| AEP:NRC:00001A, AEP:NRC:1A, NUDOCS 7912200509 | |
| Download: ML17318A507 (120) | |
Text
DYNAMIC EVALUATION TEST PROGRAM ON A SAFETY INJECTION SYSTEM PANEL, AN AUXILIARY RELAY PANELS AND A HOT SHUTDOWN PANEL
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FOR AMERICAN ELECTRIC POWER SERVICE CORPORATION TWO BROADWAY NEW YORK, NEW YORK 10004
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SEISMIC SIMULATION Test Report REPORT NO. 44560 1 WYLE JOB NO. 0 CUSTOMER Ref p2p64 25p 9N r p6 P. 0. NO.
PAGE 1 OF PAGE REPORT l,o November 19, 1979
,'jl SPECIFICATION (S) in Section 7.0 yp CUSTOMER American Electric Power Service Co oration ADDRESS Two Broadway, New York, New York 10004 2p TEST SPECIMEN A Safety injection System Panel, an Auxiliary Relay Panel, and a Hot Shutdown Panel 3.0 MANUFACTURER Harlo Corporation 4.0
SUMMARY
A Safety Xnjection System Panel, an Auxiliary Relay Panel, and a Hot Shutdown Panel, described in Paragraph 5.1r hereinafter called the specimens, were subjected to a dynamic evaluation test as required by the American Electric Power Service Corporatior (AEPSC) Purchase Order Number 02064-250-9N, Ref. 06, and Wyle Laboratories'est Plan 541/1735-1/DK, dated April 21, 1979, Revision C.
The dynamic characteristics were determined by providing a force input to the specimens with a small exciter specifically designed for modal-type testing.
The testing was performed at the Donald C. Cook Nuclear Power Plant, Unit No. 2, located in Bridgman, IyIichigan. The specimens were tested in their actual in-service configurations over the period of October 31, 1979, through November 4, 1979.
Ala. Professional Eng. wyte shall htho no aataaty for damages ot any kind to person or property. <net txang spacistor oonseqoential damages. restrt rfom wyte s prodding trio senieos coreredby this repork STATE OF ALABAMA Reg. No. 6363 COUNTY OF MADISON PREPARED BY James W. Foreman being duly sworn,
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AP VED BY deposes and says: The information contained in this report is the result ol complete and carefull c n ucte tests andisto the best o hisknowledgetrueandcorrectin all resp WYLE Q.A.
SUBSC BED sworn to before me this day of ,19 ell Notary P blic ln and for the State of Alabam at large.
SCIENTIFIC SERVICES AND SYSTEMS GROUP My Commission expires HUNTSVILLE, ALABAMA
PAGE NO.
WYLE LAIBGRAlQRIKS SCIENTlRC SERVICES ANO SYSTEMS GROUP REPORT NO.
4.0
SUMMARY
(Continued)
Figures 1, 2 and 3 show the node points, excitation points, and accelerometer locations. r Photograph 1 shows the typical test setup.
Photographs 2 through 4 show the accelerometer; locations for a typical test.
Appendix I contains the Inertance Plots fromithe resonance searches.
Appendix II contains the mode shape data, mode shapes, and damping decay plots.
Appendix III contains the Instrumentation Log Sheets and the Instru-mentation Equipment. List,.
Appendix IV contains Nyle Laboratories'est>'Plan 541/1735-1/DK, dated April 21, 1979, Revision C.
PAGE NO.
Vl/YlE LAJBCRNQ$5ES 44560-1 SMHTIRC SEAVICES ANO SYSTEMS GROUP REPORT NO.
5.0 TEST REQUIREMENTS 5.1 Specimen Descri tion and Mounting The following specimens shall be subjected to a dynamic evaluation test:
Specimen Approximate Size No. Description L x W x H Safety Injection System Panel 138" x 96" x 96" Auxiliary Relay Panel 122" x 24" x 96" Hot Shutdown Panel 144" x 72" x 96" The specimens shall be mounted in their actual in-service configurations.
5.2 Excitation A force input shall be provided by a small, lightweight, armature exciter specifically designed for modal-type testing. A force trans-ducer shall be used at the attachment point to measure force input.
The force input shall be applied to the specimens in each of the two (2) horizontal axes.
The force input shall be applied at two (2) locations as follows:
Floor-mounted cabinets The force input shall be applied near the top of the cabinet and also approximately 24" from the floor.
Floor- and ceiling-mounted cabinets - The force input shall be applied approximately 60" from the floor and also approxi-mately 24" from the floor.
5.3 Resonance Search A sine sweep from approximately 1 Hz to 35 Hz using approximately 5 pounds force input shall be performed to identify major resonances for each test configuration. The sweep rate shall be no greater than one octave per minute. Inertance (g/lb input) plots from the resonance search tests shall be provided.
In addition to the sweeps, resonant frequencies shall be verified by observing force and accelerometer output Lissajous figures on an oscilloscope. The frequencies where force and acceleration are 90 degrees out-of-phase, indicating a resonant condition, shall be recorded in the test log.
PAGE NQ.
SAQX UNOHAlZRIES REPQRT NQ. 44560 1 SCIEIITIRC SERVICES ANO SYSTEMS GROUP 5.0 TEST REQU1REMENTS (Continued 5.4 Mode Sha es and Dam in For each test configuration, mode shapes and damping values shall be determined at the primary resonant frequencies.
Mode shapes shall be determined by tuning in the resonant frequency and using accelerometer probing methods at predetermined locations to describe the relative motion. The mapping shall be performed using two (2) accelerometers (one biaxial). Phase shall be determined from an oscilloscope Lissajous display.
Damping values shall be calculated from oscillograph decay recordings of accelerometer signals taken by quickly turning off the exciter while exciting the unit at the resonant frequency. A decay curve shall be developed from the oscillograph recordings and the damping shall be determined by the following formula:
C/C c
= X 2nn log e X n
where C/C = Damping c
Number of Cycles X
0 Amplitude of Cycle "o" X
n Amplitude of Cycle "n" Additionally, the bandwidth method shall be used to determine the specimen damping.
5.5 Instrumentation 5.5.1 Excitation Control Exciter force input shall be measured and controlled by a force trans-ducer at the exciter attachment to the specimens.
PAGE NO IVY'ABQRAlZ%5ES- 44560-1 SCIENTIFIC SERVICES AND SYSTEMS GROUP REPORT NO 5.0 TEST REQUIREMENTS (Continued) 5.5.2 S ecimen Res onse Six (6) response accelerometers (three biaxial locations) shall be located on each specimen under test. The biaxial locations shall be (1) the driving point, (2) the center of the cabinet face, and (3) approximately 18" from the floor.
Frequency response test accelerometer and force data shall be recorded on FM tape.
Inertance plots from the resonance search tests shall be presented in the test report.
PAGE NO.
WVLE lAlBCRA'1KNRIEB REPORT NO. SCIENlPIC SERVICES AND SYSTEMS GROUP 6.0 TEST PROCEDURES AND RESULTS 6.1 S ecimen Mountin The specimens were mounted in their actual in-service configurations.
6.2 Excitation 6.2.1 A force input was provided by a small, lightweight, armature exciter specifically designed for modal-type testing. A force transducer was used at the attachment point to measure force input. The force input was applied to the specimens in each of the two (2) horizontal axes.
The force input was applied at two (2) locations as follows:
Floor-mounted cabinets (Specimens 2 and 3) The force input was applied near the top of the cabinet and also approximately 24" from the floor.
Floor- and ceiling-mounted cabinets (Specimen 1) The force input was applied approximately 60" from the floor and also approximately 24" from the floor.
The excitation points are shown in Figures 1, 2 and 3.
6.3 Resonance Search Procedures A sine sweep from approximately 1 Hz to 35 Hz using approximately 5 pounds force input was performed to identify major resonances for each test configuration. The sweep rate was one octave per minute.
Zn addition to the sweeps, resonant frequencies were verified by observing force and accelerometer output Lissajous figures on an oscilloscope. The frequencies where force and acceleration were 90 degrees out-of-phase, indicating a resonant condition, were recorded in the test log.
6.3.1 Resonance Search Results Xnertance (acceleration divided by force versus frequency) plots are contained in Appendix Z.
No resonant frequencies were found below 35 Hz during the testing of the Safety Enjection System Panel (Specimen 1) .
PAGE NO.
NY)LE LABOI&lZSIES SCIEHTIPIC SERVICES AND SYSTEMS GROUP REPORT NO.
6.0 TEST PROCEDURES AND RESULTS (Continued) 6.3.1 Resonance Search Results (Continued)
Resonant frequencies found during the testing of the Auxiliary Relay Panel (Specimen 2) and the Hot Shutdown Panel (Specimen 3) were:
~secimen Axa.s Fre uenc (Hz)
Front-to-Back 11.2, 18.2, 33.3 Side-to-Side None below 33 Hz Front-to-Backs 16.1, 22.9, 24.4 Side-to-Side 22.3 6.4 Mode Sha e and Dam in Procedures For each test configuration, mode shapes and damping values were determined at the primary resonant frequencies.
Mode shapes were determined by tuning in the resonant frequency and using accelerometer probing methods at predetermined locations to describe the relative motion. The mapping was performed using two (2) accelerometers (one biaxial). Phase was determined from an oscilloscope Lissajous display.
Damping values were calculated from oscillograph decay recordings of accelerometer signals taken by quickly turning off the exciter while exciting the unit at the resonant frequency. A decay curve was developed from the oscillograph recordings and the damping was determined by the following formula:
PAGE NO.
VAflLE ULBQRA1ZNIES REPORT NO. SCIEHTIRC SERVICES AND SYSTEMS GROUP 6.0 TEST PROCEDURES AND RESULTS (Continued) 6.4 Mode Sha e and Dam in Procedures (Continued)
C/C c =
2mn log e X
X n
where C/C c = Damping n = Number of Cycles X
0
= Amplitude of Cycle "o" X
n
= Amplitude of Cycle "n" Additionally, the bandwidth method was used to determine the specimen damping using the following formula:
Damping Factor = f2 - f1 2 f n
where: f and f are frequencies at. which Q=Qo and Q 0
= Resonant Magnification Factor at fn fn = Resonant Frequency.
PAGE NQ.
1M'ABQRAKNIES 44560"1 SCIENTIRC SERVICES AND SYSTEMS GROUP REPQRT NQ.
6.0 TEST PROCEDURES AND RESULTS (Continued) 6.4.1 Mode Sha e and Dam in Results Appendix II contains the mode shape data, mode shapes and damping decay curves for Specimens 2 and 3.
The damping values for Specimens 2 and 3, as determined from the damping decay curves and bandwidth method, are:
Specimen Frequency Dam in (0 critical)
No. (Hz) ~Za Deca Bandwidth F-B 11.2 1.9 2.6 18.2 4.7 6.5 F-B 33.3 3.2 4' F-B 16.1 3.2 3.8 F-B 22.9 3.0 3.8 F-B 24.4 3.3 3.2 S-S 22.3 3.3 5.6 6.5 Instrumentation Procedures 6.5.1 Excitation Control Procedures Exciter force input was measured and controlled by a force transducer at the exciter attachment to the specimens.
6.5.2 S ecimen Res onse Procedures Six (6) response accelerometers (three biaxial locations) were located on each specimen under test. The baxial locations were (1) the driving point, (2) the center of the cabinet face, and ('3) approximately 18" from the floor. Accelerometer locations are shown in Figures 1, 2 and 3.
Frequency response test acceleroemter. and force data were recorded on FM tape.
6.5.2.1 S ecimen Res nse Results Appendix I contains the Inertance Plots obtained from the. specimen response accelerometers.
PAGE NO.
%IRK. LABORAllQRIEB REPORT NO. SClEHTlRC SERVICES ANO SYSTEMS GROUP 7.0 7.1 American Electric Power Service: Corporation Purchase Order Number 02064-250-9N, Ref. 06.
7.2 ale Laboratories'est Plan 541/1735-1/DK, dated April 21, 1979, Revision C.
Page No. 11 Report No. 44560-1 2 lo 28 28~ 3'3" 3o AccEM 1V.'S,l55 I
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8f D'Rwv e Qec,E4S 9FBp 355 2S FIGURE 2. AUXILIARYRELAY PANEL - NODE POINTS, EXCITATION POINTS AND ACCELEROMETER LOCATIONS
Page No.
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\l I t 0 PHOTOGRAPH 1 TYPICAL TEST SETUP (AUXILIARY RELAY PANEL SHOWN)
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PHOTOGRAPH 2 AUXILIARY RELAY PANEL ACCELEROMETER LOCATIONS 1 FRONT-TO-BACK 2 SIDE-TO-SIDE
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PHOTOGRAPH 3 AUXILIARY RELAY PANEL ACCELEROMETER LOCATIONS 2 FRONT-TO-BACK 2 SIDE-TO-SIDE
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Page No. 18 Report No. 44560-1 This page intentionally left blank.
PAGE NO. 19 lhlYLE UKORAlMtES SQEHTI8C SEA VICES AND SYSTEhlS OAOUP REPORT NO.
APPENDIX I INERTANCE PLOTS RUN DRIVE NO. SPECIMEN AXIS POINT Safety Injection System Panel Front-to-Back Safety Injection System Panel Front-to-Back Safety Injection System Panel Side-to-Side Auxiliary Relay Panel Front-to-Back Auxiliary Relay Panel Front-to-Back 10 Auxiliary Relay Panel Side-to-Side Hot Shutdown Panel Front-to-Back 15 Hot Shutdown Panel Front-to-Back 17 Hot Shutdown Panel Side-to-Side
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AXIS ACCEL NO. M1M~ FORCE INPUT
Page No. 44 Report No. 44560-l
~ ~
FULL SCALE IMERTAMCE 0.001 0 0.01 g .01 0 1.0 0 10 I I ~ ~ ~ I ~ ~
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10 9
8
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AXIS ACCEL NO. +~2 ~ FORCE INPUT TEST RUN NO.
Page No. 45 Report No. 44560-1 FULL SCALE INEATANCE 0.001 CI 0.01 I .01 C3 1.0 El 10 9
8
~ I ~ I ~
10 9
8 7
~ I 3 + 6 6 7 8 0 2 "
3 6 6 6 7 8 910 2 3 6 6 6 7 8 910 100 1000 Frequency (Hz)
AXIS ACCEL NQ. I++ ~ PQRCE INPUT TEST RUN NO.
Page No. 46 Repgm No. 44560 FULL SCALE INEATANCE 0.001 E3 0.01 gl .01 0 1.0 C3 10 I ~
3 10 9
8 7 ~ ~
I I I~ I I I a . ~ 6 e 6
~'2 D).
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8 0
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AXIS ACCEL NO. ~~K~ FORCE INPUT TEST RUN NO.
& - ~
~ ~
Page No. 47 Report: No. 44560-1 FULL SCALE INEATANCE 0.001 Cl 0.01 0 .01 C3 1.0 Q 10 9
8 7
10 9
8 7 ~ I O) 2 0)
O C
ID C
01 10 9
8 U
Q ol Zg I- 0 II I9
() )c Je
~ I 3 4 2 ' 4 5 4 7 8 910 2 3 4 0 8 7 8 910 I
100 1000 Frequency (Hz)
AXIS ACCEL NO. ~M~ FORCE INPUT TEST RUN NO.
Page No. 48 Report No. 44560-1 FULL SCALE INEATANCE 0.001 D 0.01 gf .01 D, 1.0 D 10
~ ~
10 9
I ~
- 0) 2 0)
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10
~ I Ql 10 9
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+n V
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2 3 6 6 6 7 8 910 2 3 6 6 6 7 8 910 6 8 6 7 8 910 10 100 1000 Frequency (Mz)
AXIS ACCEL NO. &~8 ~ FORCE INPUT TEST RUN NO.
Page No. 49 F ~
Report No. 44560-1 FULL SCALE INERTANCE 0.001 0 0.01 gl .01 C3 1.0 0 10 9
8 7
10 9
8 7
OT 2 0)
O G) 0)
C 10 9
8
'2 n 3:g I v IX 0
<<n 19 p
Jn
)C 7 8 91 3 h 8 d 7 8 910 2 3 4 8 8 7 8 910 100 ~ 1000 F quency (Hz)
AXIS ACCEL NO. ~+~ ~ FORCE INPUT TEST RUN NO.
Page No. 50 Report No. 44560-1 ~ I FULL SCALE IhlERTANCE 0.001 Cl 0.01 IP, .01 C3 1.0 0 10
~ ~
~ i I ~
3 10 9
8 7
~ I J5 O1 2 01 O
(0 C
0) 10 9
8 V I ~ I 3 v 6 1 v L0 Ox Js 3 4 6 6 7 8 910 2 3 4 6 6 7 8 910 3 4 8 6 7 8 910 10 100 1000 Frequency (Hz)
AXIS ACCEL NO. 229 4 FORCE INPUT TEST RUN NO. 0
~ ~
I Page No., 51 ReL3ort No, .44560-1 FULL SCALE INEATAMCE 0.001 c3 0.01 3I 1.0 C3 10 9
8 7
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10 J3 CD 2 01 O
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C 10 9
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Sn 2 3 7 8 910 2 3 6 6 6 7 8 910 3 4 6 6 7 8 910 10 100 1000 Frequency (Hz)
AXIS ACCEL NO. I w FORCE INPUT
/0 55'EST RUN NO.
Page No. 52 ~ ~
,...Reoozt ..No. 44560-1 FULL SCALE INERTANCE 0.001 0 0.01 8 .01 0 1.0 0 10 9
8
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7 10 I ~
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~ I 2 3 4 6 6 7 8 910 2 3 6 6 6 7 8 910 3 6 0 6 7 8 910 10 100 1000 Frequency (Hz)
AXIS ACCEL NO. ~ FORCE INPUT TEST RUN NO.
Page No. 53 Report No. 44560<<1 FULL SCALE IlUEATAMCE 0.001 0 0.01 8 .01 0 1.0 0 10 9
8 7 I ~
10 9
8 7
it i 1D
< ~
i 6 7 8 910 2 3 8 6 6 7 8 910 3 4 6 6 7 8 910 10 100 1000 Frequency (Hz)
AXIS ACCEL NQ. aMi ~ FORCE INPUT TEST RUN NQ.
Page No. 54 Report No. 44560-1 FULL SCALE INEATANCE 0.001 0 0.01 @ .01 Q 1.0 0 10 9
8 7 ~ I 10 9
I ~ ~ I ~ I ~ ~ ~
~ ~ ~ ~
OI 2 0)
CJ O'F IQ I
ID 10 9
8 0 7 ~ I 6
I v L II I9 p >C I
I I I I 2 3 4 4 6 7 8 910 2 3 4 4 6 7 8 910 3 4 4 6 7 8 910 10 100 1000 Frequency (Hz)
AXIS ACCEL NQ. ~4 'ORCE INPUT TEST RUN NO.
Page No. 55
~ ~
Report No. 44560-1 FULL SCALE INERTANCE 0.001 0 0.01 J8, .01 0 1.0 0 10 I I ~ ~ I ~
10 9
8 7
O1 2 0)
O C ~ i (0
~~ r1 g) 10 9
8 7 ~ I gn 6 3
I- u cu
<<n I9 0+
Jn 3 0 2 ' 4 8 6 7 8 910 3 6 8 6 7 8 910 10 100 1000 Frequency (Hz)
AXIS ACCEL NO. > ~~ ~ FORCE INPUT
Page No. 56 Report No. 44560-1 FULL SCALE INEATANCE 0.001 0 0.01 gf, .01 0 1.0 0 10 I ~ ~ ~
I I ~ ~ I II~
10 9
8
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'1 3 6 S 6 78910 2 3 6 6 6 7 8 910 3 ' 6 6 7 8 910 10 100 1000 Frequency (Hz)
AXIS ACCEL NO. ~+9 t FORCE INPUT
~/
Page No. 57 Report No. 4456p-y FULL SCALE INERTANCE 0.001 0 0.01+ .01 0 1.0 CI 10 9
8 10
\ ~
O) 2 CI O
C IQ I
(0 C
10 9
8 3
2 3 8 8 8 7 8 910 2 3 4 0 8 7 8 910 IO 100 1000 I
P Frequency (Hz)
AXIS ACCEL NO. ~E~ +'ORCE INPUT
Page No. 58 Report No. 44560-1 FULL SCALE IMEATAIMCE 0.001 0 =
0.01 6 .01 0 1.0 0 10 9
8
~ ~ ~ \
7 I ~
~ ~ ~ ~
10 9
8 I ~
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8 0
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I I I 2 3 8 8 8 7 8 910 3 S 8 8 7 8 910 3 4 8 8 7 8 910 10 100 1000 Frequency (Hz)
AXIS i (>
f ACCEL NO. ~ '~ ~ FORCE INPUT TEST RUN NO.
Page No. 59.
Report No. 44560-1, FULL SCALE INERTANCE 0.001 C3 0.01 g .01 C3 1.0 0 10 9
8 6
10 C) 9 07 O
(0 C
Cl C
10 9
8 0 7 ~ I g ul 6 i"
I v 0 8
<n pX JA I
I I I I
'J 9 0 8 6 8 6 7 8 910 8 6 8 6 r 8 910 100 1000 Frequency IHz)
AXIS 8
~~~ 'ORCE ACCEL NO.
~i INPUT
Page No. 60 ~ ~
Resort No. 44560-1 FULL SCAI.E INEATANCE 0.001 P 0.01 0 .01 C3 1.0 P 10 9
8 7
10 9
8 7
"O) 3
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- ia'AC 10 9
8 0 7 ~ ~
QO 6
0.'II 6 I9 A p >C I
I I I I I I 3 6 6 6 7 8 910 3 ' 6 6 6 7 8 910 3 3 6 6 6 7 8 910 10 100 1000 Frequency (Hz)
AXIS ACCEL NO. ~@ ~ FORCE INPUT TEST RUN NO.
Page No.. 61 Report: No. 44560-1.
FULL SCALE IMEATAMCE 0.001 Cl 0.01 g .01 Cl 1.0 C3 10 I ~ ~ I 10 II ~
93 ~ I I ~ I ~ ~
- 0) 2 o
4J ~ I
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10 9
8
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~n 19 0<
J 91 2
1 I 9 1 I ~ I I I 9 9th 2 3 4 d d 7 d 910
~9II I I 100 1000 Frequency (Hz)
AXIS ACCEL NO. ~<~ + FORCE INPUT TEST RUN NO.
Page No. 62 I
RepoM No. 44560-1
~
FULL SCALE IhlEAYANCE 0.001 0 0.01 g .01 0 1.0 CJ 10
~ I I 10 9
8
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5 S3 O) 2
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19 n
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4 5 IS 7 8 910 2 3 4 5 5 7 8 910 10 100 1000 Frequency (Hz)
AXIS ACCEL NO. l4 w FORCE INPUT
Page No. 63 Report, No. 44560-g FULL SCALE INEAYAMCE 0.001 0 0.01 5( .01 C3 1.0 0 10 9
8 10 9
8 7
O) 2 O
10 C
- '-a Ql 10 9
8 0 7 aa Q al 3:g 6 I-v L'U 8
~n 0
pAnac 3
Ld 6 7 9 'lP 2 =
3 6 8 6 7 8 910 4 6 6 7 8 910 100 1000 Frequency (Hz)
AXIS ACCEL NO. l >~ a FORCE INPUT
Page No. 64 I
Report No. 44560-1 ~
FVLL SCALE IMEATAMCE 0.001 C3 0.01 8 .01 0 . 1.0 Cl 10 9
8 7
~
' ~
10
~ I J3 O) 2 0)
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I L"I1V 5 4
I9 R 0JN )c I
I I I 2 3 6 5 6 7 8 910 6 5 6 7 8 910 6 5 5 7 8 910 10 100 1000 Frequency (Hz)
AXIS ACCEL NO. ca i~~ ~ FORCE INPUT TEST RUN NO.
I
~ ~
Page No. 65 Report. No. 44560-1 FULL SCALE I N EATANC E 0.001 C3 0.01+ .01 C3 1.0 Cl 10 9
8 9
10
~ I JD Ol 2 07 O
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C 10 9
8 Q Qn 2
I v 0
<n CI )c 4 An 3
2 3 4 ~ 8 910 ilj g 3 4 8 6 7 8 910 3 4 8 8 3 8 910 100 1000 requency (Hz AXIS IICCEL NO. ~+ 'ORCE INPLIT TEST RUN NO.
Page No. 66 ~ ~
Report No. 44S60-1 FULL SCALE INEATANCE 0.001 0 0.01 tS, .01 0 1.0 0 10 9
8 7
~ ~ ~ I ~
~ \ ~ I I~
10 9
8 7
~f2 QI'I ID "<<,
I 10 9
8 0 7 ~ ~ I~
gn 6 Lg 8
~n I9 Jn 6 6 6 7 8 910 8 6 6 6 7 8 910 3 6 6 6 7 8 910 10 100 1000 Frequency (Hz)
AXIS ACCEL NO. REM~ FORCE INPUT TEST RUN NO.
~ ~
Page No.
No. 4456p<<l 67'eport FULL SCALE INERTANCE 0.001 CJ 0.0 .01 Cj 1.0 0
'10
~ i I ~ I
~ ~
10
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10 9
8 0 7 ~ I ~ ~ I I 6
L'0 d
<<n 19 pJn )C 4 de 7 8 910 2 3 h 6 d 7 8 910 2 3 6 6 6 7 8 910 1 0 100 1000 Frequency (Hz)
AXIS ACCEL NO. ~M ~ FORCE INPUT TEST RUN NO.
Page No. 68 ~ '
Re
.P os No. 44560-1 FULL SCALE INERTANC E 0.001 0 0.01 Q .01 Cl 1.0 0 10 9
8 7
~ ~
10 9
8
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7 ~ I O1 2 01 O
C (0 be 1- IE ID 10 9
8 V ~ I 7 ~ I gn z
O'U 6
<<n 0
Ox Jn I ~ ~ I 6 6 6 7 8 910 2 3 6 6 6 7 8 910 100 1000 Frequency (Hz)
AXIS ACCEL NO. ~+> ~ FORCE INPUT TEST RUN NO.
d Page No. 69 Report, No. 44560-1 FULL SCALE IIMERTANCE 0.001 Cj 0.01, .01 Cj 1.0 Cj 10 9
8 7
10 9
8 7
dd 6
6 Zl
- 0) 9 0)
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10 C
0)
C 10 9
8 0
g dd X
I V C dd 17 0 dc J dd 6 6 6 7 8 910 6 6 6 7 8 910 3 6 6 6 7 8 910 10 100 1000 Frequency (Hz)
AXIS ACCEL NO. I ~~ 'ORCE INPUT TEST RUN NO.
Page No. 70
~ ~
Report No. 44560-1 FULL SCALE INERTANCE 0.001 0 0.01 gl..01 0 1.0 C3 10
~ I I ~
10 9
8 7 ~ I i6 "d
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C IF (0.
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CC0 6
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6 6 6 7 8 910 3 6 6 ~ 6 7 8 910 100 1000 Frequency (Hz)
AXIS ACCEL NQ. ~>I ~ FORCE INPUT TEST RUN NO.
Page No. 73.
Mport No. 445l70-g FULL SCALE INERTANCE 0.001 0 0.01 j2f, .01 El 1.0 0 10 9
8 7
10 9
8 7
SD O) 2 0)
O (0
C 0)
C 10 9
8 Q vl gN I-V CU IE n
pX Jn 9 10 2 3 6 6 6 7 8 910 3 6 6 6 7 8 910 10 100 1000 Frequency (Hz)
AXIS ACCEL NO. ~~~ ~ FORCE INPUT TEST RUN NQ.
page No. 72 Re P ort No. 44560-1 FULL SCALE INERTANCE 0.001 C} 0.01 g .01 E3 1.0 Cl 10
~ ~
~ I ~ I r ~ I 10 9
8 7
6 r
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8 0
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~ I I I r
I r ~ 2 ' 8 6 6 1 8 910 6 6 7 8 910 p
f 100 1000 Q]( 4(5QJ Frequency (Hz)
AXIS ACCEL NO ~Pi w FORCE INPUT
~r
Page No. 73 Report No. 44560-1 FVLL SCALE INERTANCE 0.001 0 0.01 'g .01 0 1.0 CI 10
\ ~
10 I I 1 II t ~
I ~ I i 0 tt 8
7
~ t t t ZN i" 0 II 8
IS Q )C J tI 3
t ~
~ t tII'jtt'I $ 3 4 8 8 7 8 910 100 3 4 0 d 7 8 910 1000 Frequency (Hz)
AXIS ACCEL NO. " t FORCE INPUT TEST RUN NO.
Page No. 74 Report No. 44560-1 This page intentionally left blank.
PAGE NO. 75 WYLE LABGRATQRES SCIEIITIPIC SERVICES ANO SYSTEMS GROUP REPORT NO. 44560-APPENDXX ZI MODE SHAPE DATA, MODE SHAPES AND DAMPlNG DECAY CURVES
Page No. 76 Report No. 44560-1 DATA SHEET SPECDKN A vx a. l A R ++LAY AXIS F'RoN'To -~Ace. DRXVE PT FREQUENCY '1'1' l'H'8 ' ' '
NooK lN L 'LI4 B c g,o $ $ Asks g gooR
@lath BER, READ (sl Q Haec )~( Nu&BEL
+ 22. ao
+ 2c)o
+ Zo
+ 72o 2o + 3' + 1l 21 2l+
23 gOO 37
+ 2'to + P 3 ~
+ 81o
+ l9o
+ 7o
+ ago llo 3o
+ lS-S.
q 3lo 7l e Ross 'D gis gzAu iuc Moss BE Wu L.rt'Pu S> Eb9
Page No. 77 Report No. 44560-1 DATA SHEET SPECZJKN A Uwl )-l'A&9 RE,l A'f VAasE,K DATE l1) R/79 AXZS F ~@AT - Yo - 9 Ac.t DRIVE PT PRZqUENCy ~
18; ~ 14 +
~
NooK la )-i)4 E CAY $$ t4OOE lk ).>F6 QK)) e)ec CRnSC AX)s W
<use ER RE>o ru g 8%Ass )ups NuMBER RPAQ)t4C-
+ 3C) 20
+LO
'39
+ 1 l)=)
t 7p
+ 200 70 + JZ5
+/C C' ROSS A Xls SEA 'b)as)s-N)u)-Y'lP) l 9n
Page No. 78 Report No. 44560-1 DATA SHEET SPECIMEN 4 U <l4 lAR< Rgl Ag P~P'l DATE lh 1~l79 AXIS From -~-SAc.x. DRIVE PT l rREOUENn >3 8 H+
NooK lN Lll4 Q Cf<$ $ Mr ag f4008 la@ L>86 CRo5$ Axes +
hlv th MA, RED+ ivy, 8'BAg )el~ hluMBKR, P KA'oiaac 9 EAOst4C gz) l 7O
&9o 20 q ~o
+ 'PK
+ t9o 23 + 7b
+ 2o
+ 110
+3o
-4 5 So (HER
-2.9o
- 42.0 +7c
Page No. 79 Report No. 44560-1 DATA SHEET SPECXm HoT SHOrea~d Y-p ~Ki DATE hh $ 7'f AXXS PAo~r -Vo PREOUENCV -t4';> Ha.
'RZVE PT NObE, 1N LL< Q. C ko SS AaiS W gooK 1H L-at4E cRass Axts nlvMR EA. H,RAb ru ~ a%Ay )N+ hLu&BKL P,KAbsHQ RPAb tt46.
+ 2o L7 lho I "t2.
I So + ~S
+ go I52 CRoS~ Ax)s R~'biuG- &us T'E' vt.7l PL l~b BY o. I
Page No. 80 Report, No. 44560-1 DATA SHEET SPECIMEN Ho'T ZHU7~4 "+hA4V i ' DATE 11 1'3179 mIS F R~ ->o haec. DRIVE PT t
' 2 2.'94 t' ' '
FREQUENCY Ho+K lN l S4+ cross f4Oe R 1 s4 l.lHQ Cross Axe hl~MSKR, RFee )up 8%A~ ~A+ %UMBRA P"EAase~ 9 PAO inlC l3o 27 32.0 l 32. + 13o 5 /5 3 oQ - 7M
+ 95
+ /We f C7
. u.z + ZoO +10
<~os'Xmas RV.A0yLc H v m P t.-l EO c &9
Page No. 81 Repoxt No. 44S60-1 DATA SHEET SPECIMEN HOT 8 A~~M'MS' ATE L l(3'/a g AXIS %Anat - Tb - BAc<
FREQUENCY'2k '
'RIVE PT 1 NouG, 1N I lH+ C go fs Aswg QouK lk Lat46 CRoSC Axles
<VMSEA, g9AD tel Q R%AD ~45. NURSER P.QAbs H6 SEA'0 lhl4 3g
+ lo + I 2,5 -2Q l7 ~
+ 125 +70 loo + 2oo -5$
lo[ t 250 12o +3O 8 135 l2l +1QS
+ Z,to% 12m + ec 1 + l Oo
- g. 1 0 lZZ, +aM
, +i<5 V$
SZ + l 7 o
+ Z.LO
+ 11C)
+ 17m + to
+ ZZ~ + Wo
~ 9'W
~ 1-gS- w MS'
+ g05 /47O
+28c C, g~g +yg g~Q fiO(i ~'MENT M Mua.Vi P~> Fb 8Y 0 "t
Page No. 82 Report No. 44560-1 DATA SHEET SPECIMEN 8~7 + H>W~el +'A~K'l DATE ll /Q 7 I AXIS + aber -~ S ihB DRIVE PT 3 rRZOUENCV 2 l;3. HZ NooK 'l N L ll4 Q, CROSS Rr wg goo 6 1l4 LIH9 C Ro5$ Ax L$
hlVKSEA, BRAD lsl Q RV.Ap ~A~ Nu trt BE% P Kepler 9 PA& ic44 lj' l l5 a io
+ 2<5 o
+ 75 LSo l '7o 21 l<o l 4o
Page No. 83 Report No. 44560-1 MODE SHAPE AUXILIARY RELAY PANEL FRONT-TO-BACK AXIS 11.1 Hz
Page No. 84 Report No. 44560-1 MODE SHAPE AUXlLlARY RELAY PANEL FRONT-TO-BACK AXIS 18.2 Hz 3
1 1
1
page No. 85 Report Noo 44>6O MODE SHAPE AUXELEARY RELAY PANEL FRONT-TO-BACK AXIS 33.3 Hz I
I I
7l I I 'I I I
83 ) /
t I
I 7o .
I
/ I I
I I I
I I I I I
I / I
/ I I
/
I I
/ 8I I
/ I
/ I
/
I I
go
Page No. 86 Report No. 44560-1 NODE SHAPE HOT SHUTDOWN PANEL FRONT-TO-BACK AXXS 16.1 Hz ISZ le
Page No. 87 Report No. 44S60-1 MODE SHAPE HOT SHUTDOWN PANEL FRONT-TO-BACK AXlS 22.9 Hz 5+
~5'0
Page No. 88 Report, No. 44560-1 HODE SHAPE HOT SHUTDOWN PANEL FRONT-TO-BACK AggS 24.4 Hz PANEL FRONT
Page No. 89 Report, No. 44560-1 MODE SHAPE HOT SHUTDOWN PANEL SIDE-TO-SIDE AXIS 2l.3 Hz
/ \ g,/
/
PANEL FRONT
Page No. 90 Report, No. 44560-1 DECAY CURVE AUXILIARY RELAY PANEL RUN 6 FRONT-TO-BACK AXIS 11>>2 Hz
~ ~ ~ ~
I~
III 0 Z II O"I>> Z El II 1I I=O II IZ r 0 II Y 0gl4II II Y
IY II 5 II I ~ I 0 2 3 6 7 n Number of Cycles
Page No. 91
~ ~
Report No. 44560-1 DECAY CURVE AUXILIARY RELAY PANEL RUN 7 FRONT-TO-BACK AXIS 18.2 Hz
~ ~
I~ I ~
I I I t I II
~ I 6
Z V 0
0 tt w tt 4 6 Za tt I=0 4 4x tt 0 tt ~
4 ggV V tt IV V Ct tt I ~
0 5 6 n - Number of Cycles
Page No. 92 Report No. 44560-1
~ ~
1 DECAY CURVE AUXILIARY RELAY PANEL RUN 8 FRONT-TO-BACK AXXS 33.3 Hz l~ I I~ ~ ~ ~ ~ ~ f~ ~ ~
e I f4 qe Fl 4
~ I
- f. W'I
- 0) 4
~ Il g
lA;n I
n 0 X II 0
0n S
Xo l o 4
'n O,
4 II ~nI 0 n 4 0 fl g II II E II I'4 Cl II 0 3 4 n - Number of Cycles
Page No. 93 Report No. 44560-1 DECAY CURVE HOT SHUTDOWN PANEL RUN 13 FRONT-TO-BACK AXXS 16.1 Hz I ~
~ ~ ~ )
~ I
~ ~ I ~ ~ ~ I~ I I ~ I ) ~ I I~ ~ II ~ ) I I I~ ~ ~
~ I 5
4J I I II dJ
~
e (9))
)" 3) 6 0
V 6
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pg ttI)t IV V Cl tt N
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~ ~ ~ ~ I I ~ I~
I ~ ~ ~ ~ I I ~ ~ I I
~ I I ~
I II I I
~ I I~
0 1 2 3 4 5 6 7 n Number of Cycles
Page No. 94 Report No. 44560-1 DECAY CURVE HOT SHUTDOWN PANEL RUN 14 FRONT-TO-BACK AXIS 22.9 Hz
<<l 4 I0 a IA 'a V
Q( 1 a
X 0
ue E>
Xa bo't L
0 )Ca Q
V XI Ia V 4I 4
~ II 0 2 3 5 6 7 n - Number of Cycles
Page No. 95 Report, No. 44560-1 DECAY CURVE HOT SHUTDOWN PANEL RUN 12 FRONT-TO-.BACK'XIS 24.4 Hz
~ I l~ I ~ I I ~
I~ I~
l (
Xa 0
0 ll 0
II
~I 5
I=O 4 w
g IC II a Q
g Isl IC II XI w"
4I II II ~
~ l
\ \
I I ~ I
~ ~ I ~
~ I 2 3 . 4 n - Number of Cycles
Page No. 96 Report No. 44560-1 DECAY CURVE HOT SHUTDOWN PANEL RUN 18 SIDE-TO-SIDE AXIS 22.3 Hz
~ I I I~
I ~
I ~
~ I Cl 4
~ y lO a Q V 6
+ 0 Z Q o-~
0 Vl U Ol gg l4 Lo L+ J 4
+)c 00 a 9 Q gy 4 J V
~V Q !4 N
X OI 2 3 4 n Number of Cycles
97 PAGE NO.
QIYLE LABORA1URES SCIENTIPIC SERVICES AHO SYSTEMS GROUP REPORT NO.
APPENDIX III INSTRUMENTATION LOG SHEETS AND INSTRUMENTATION EQUIPMENT SHEETS
W 322 WYLE LABORATORIES GF gl
. INSTRUMENTATION LOG SHEET 0 Eb JOB NO. LOG PAGE NO. > OF~ 0 0
M CUSTOMER ~ <RPf/Ar/) TEST ENGINEE (Include Run Number, Part Changes, Shift Changes ED I
DATE TIME REMARKS and all other pertinent data)
-7
W 322 WYI.E lABORATORIES INSTRUMENTATION I.OG SHEET JOB NO. 0 I.OG PAGE NO. + OF CUSTOMER PCS< zn k'c/c lo ~ P/~ ~) TEST ENGINEER (Include Run Number, Part Changes, Shift Changes DATE TIME REMARKS and all other pertinent data)
Q, 0 cA dC1' lD W ul 0 0 0
0 Ql C)
I
ib Q.
W 322 WYLE LABORATORIES
'.,INSTRUMENTATION LOG SHEET 0 lD JOB NO. LOG PAGE NO. OF~ 0
> C)0 CUSTOMER 0Mb+ H/A~8) TEST ENGINEER (Include Run Number, Part Changes, Shift Changes
~~ Sf'~ oI DATE TIME REMARKS and all other pertinent data)
W 322 JOB NO.
CUSTOMER e>Pr<~)
WYLE LABORATORIES INSTRUMENTATION I.OG SHEET LOG PAGE NO.
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109 PAGE NO.
lhNlE LAIBGRATUREB 44560 1 SCIEHTIEIC SERVICES AHD SYSTEMS GROUP REPORT NO.
APPENDIX ZV TEST PLAN
Page No. 110 Report, No. 44560-1 TEST PROCEDURE 541/1735-1/DK TEST PROCEDURE NO.
SCIENTIFIC SERVICES ANO SYSTEMS GROUP DATEJ April 21, 1979 P. O. BOX 1008 ~ HUNTSVILLE,ALABAMA35807 TWX (810) 725.2225 ~ TELEPHONE 12051 807~11 Revision C BASIC TEST PLAN FOR IN-SITU VIBRATION TESTING OF VARIOUS CONTROL PANELS FOR THE DETERMINATION OF SYSTEM NATURAL FREQUENCIES FOR INDIANA AND MICHIGAN POWER COMPANY FOR THE DONALD C. COOK NUCLEAR POWER PLANT, UNIT NO. 2 APPROVED BY: APPROVED BY FOR: PROJECT MANAGER:
'PPROVED BY: APPROVED BY FOR: QUALITYENGINEER:
APPROVED BY: PREPARED BY FOR: PROJECT ENGINEER:
REVISIONS FORM 1054-1 Rev. 4/74 REV. NO. DATE PAGES AFFECTED BY APP'L. DESCRIPTION OF CHAJJGES B-B-79 All GF Revised entire test lan er Customer request.
B-30-79 3 Para. 3.3 Added ". . . in the three coordinate directions."
C 10-12-79 All BGF Revised entire test plan per Customer request.
COPYRIGHT BY WYLE I.ABORATORIES. THE RIGHT TO REPRODUCE, COPY, EXHIBIT, OR OTHERWISE UTILIZE ANY OF THE MATERIAL COJJTAINEO HEREIN WITHOUT THE EXPRESS PRIOR PERMISSION OF WYLE LABORATORIES IS PROHIBITED. THE ACCEPTANCE OF A PURCHASE ORDER IN COIJNECTION WITH THE MATERIAL CONTAINED HEREIN SHALL BE EQUIVALENT TO EXPRESS PRIOR PERMISSION.
Page No. 111 Report No. 44560-1 S 541/1735-1/DK TEST PROCEDURE NO.
PAGE NO.
WYLE LASCRATQRES SCIENTIFIC SERVICES ANO SYSTEMS GROUP Revision C 1.0 SCOPE In-situ vibration testing of control panels containing electromechanical equipment for the purpose of determining the natural frequencies within the frequency range of 1 to 35 Hz shall be the scope of this test. A total of three (3) Panels shall be tested. The Panels are located at the Donald C. Cook Nuclear Power Plant, Unit No. 2, Bridgman, Michigan.
2.0 SPECIMEN MOUNTING The specimens, consisting of a Safety Injection System, a Hot Shutdown Panel and an Auxiliary Relay Panel, shall be mounted in their actual in-use configurations.
3.0 EXCITATION 3.1 Force In ut A force input shall be provided by a small, lightweight, armature exciter specifically designed for modal-type testing. A force trans-ducer shall be used at the attachment point to measure force input.
The force input shall be applied to the specimens in each of the two (2) horizontal axes to excite the specimens. A typical test setup is shown in Figure l.
The force input shall be applied at two (2) locations as follows:
Floor-mounted cabinets - The force input shall be applied near the top of the cabinet and also approximately 24" from the floor.
Floor- and ceiling-mounted cabinets - The force input shall be applied approximately 60" from the floor and also approxi-mately 24" from the floor.
3.2 Resonance Search A sine sweI 5 from approximately 1 Hz to 35 Hz using approximately 5 pounds force input shall be performed to identify major resonances for each test configuration. The sweep rate shall be no greater than one octave per minute. Inertance (g/lb input) plots from the resonance search tests shall be provided. A typical inertance plot is shown in Figure 2.
In addition to the sweeps, resonant frequencies shall be verified by observing force and accelerometer output Lissajous figures on an oscilloscope. The frequencies where force, and acceleration are 90 degrees out-of-phase, indicating a resonant condition, shall be recorded in the test log.
Form I054.2 Rev. 4/74
Page No. 112 Report No. 44560-1 l 541/1755-1/DK TEST PROCEDURE NO.
PAGE NO.
QNLK LAKKNNMfES.
SCIENTIFIC SERVICES ANO SYSTEMS GROUP Revision C 3.3 Mode Sha es and Dam in For each test configuration, mode shapes and damping values shall be determined at the primary resonant frequencies.
Mode shapes shall be determined by tuning in the resonant frequency and using accelerometer probing methods at predetermined locations to describe the relative motion. The mapping shall be performed using two (2) accelerometers (one biaxial) . Phase shall be determined from an oscilloscope Lissajous display. A typical mode shape: is shown in Figure 3.
Damping values shall be calculated from oscillograph decay recordings of accelerometer signals taken by quickly turning off the exciter while exciting the unit. at the resonant fzequency. A decay curve shall be developed from the oscillograph recordings and the damping shall be determined by the following formula:
C/C c
1 2mn log e X
X n
where C/C Damping c
n ,Number of Cycles X
0 m Amplitude of Cycle "o" X
n m Amplitude of Cycle "n" A typical decay curve is shown in Figure 4.
Additionally, the bandwidth method shall be used to determine the specimen damping.
4.0 INSTRUMENTATZON 4.1 Excitation Control Exciter force input shall be measured and controlled by a force trans-ducer at the exciter attachment to the specimens.
Form IC64.2 Rev. 4/74
Page No. 113 Report No. 44560"1 541/1735-1/DK TEST PROCEDURE NO.
PAGE NO.
M(LE lABORAlUREB SCIENTIFIC SERVICES AND SYSTEMS GROUP Revision C 4.2 S ecimen Res onse Six (6) response accelerometers (three biaxial'.locations) shall be located on each specimen under test. The biaxial locations shall be 1) the driving point, 2) the center of the cabinet face, and
- 3) approximately 18" from the floor.
Frequency response test accelerometer and force data shall be recorded on FM tape.
Znertance plots from the resonance search tests shall be presented in the test report.
5.0 BEPQRT Six (6) copies of a certification-type report shall be issued subse-quent to completion of testing. This report shall be signed by a Registered Professional Engineer and shall include inertance plots, natural frequencies, mode shapes, damping, and accelerometer locations.
The report shall also include a list of the test equipment and its calibration.
Form 1054.2 Rev. 4/74
Page No. 114 Report No. 44560-1 Test Procedure No.
541/1735-1/DK Page No. 5 Revision C
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Page No. ll5 Report No. 44560-1 Test Procedure No.
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Page No. 116 Report No. 44560-1 Test Procedure No.
541/1735-1/DK Page No. 7 Revision C UNDEFo~KK Svaucvu e.a D% Ve Wtrt~ STRvc~ a'6 A,FLA'nW AMPLI TUAE Il4pv'T X pouNDs
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I Page No. 117 Report No. 44560-1 II 10.0 tsj DECAY CURVE Test Procedure No.
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