EDWARD KATS & ASSOCIATES 511 South Maria Avenue
Redondo Beach, CA 90277 (310) 344-0081
MODEL: 737-400 DOCUMENT NO.: EAK-15-507-DT REVISION: NC DATE: 11-02-2015
Prepared By: Edward Kats Date: 11-02-2015
Checked By: Ricardo Fernandez Date: 11-02-2015
Approved By: Edward Kats Date: 11-02-2015
DAMAGE TOLERANCE EVALUATION
FUSELAGE ANTENNAS INSTALLATION
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
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CHECKED BY
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SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
LIST OF ACTIVE PAGES
ADDED PAGES
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i NC ii NC iii NC iv NC
1-68 NC A1-A70 NC
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SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
REVISION RECORD
REVISION SYMBOL
DATE
APPROVAL
NC Initial Release 11/02/15 E. Kats
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DOCUMENT NO.EAK-15-507-DT
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REF. DWG. NO.
EDWARD KATS & ASSOCIATES
TABLE OF CONTENTS SECTION / TITLE PAGE Title Page ......................................................................................................... - List of Active Pages .................................................................................................. i Revisions Record ...................................................................................................... ii Table of Contents .................................................................................................... iii References .............................................................................................................. iv 1.0 Introduction ....................................................................................................... 1 1.1 Summary of Results ................................................................................. 1 2.0 Antennae Installation ........................................................................................ 2
2.1 Damage Tolerance Evaluation ................................................................. 9 2.1.1 Fastener Load Definition and Durability Analysis ...................... 9
3.0 TCAS Antenna Installation ................................................................................ 10 3.1 Transponder Antenna Installation ............................................................ 24 3.2 GPS Antenna Installation (original skin .................................................... 39
4.0 Residual Strength Evaluation ............................................................................ 58 5.0 Inspection Requirements .................................................................................. 59
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Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
REFERENCES
1 T. Swift FAA-AIR-90-01 “Repairs to Damage Tolerant Aircraft.”, Structural Integrity of Aging Airplanes, Springer Verlag Berlin Heidelberg, 1991
2 EO1668 Cargo Door Surround Skin - Existing Antenna Relocation, Outside STC with Dual GPS Configuration, dated 08/14/2014
3 FAR 25.571 “Federal Aviation Regulations, Part 25 - Airworthiness Standards: Transport Category Airplanes.”
4 WL-TR-94-4054 “Damage Tolerance Design Handbook”
5 D. J. Hagemaier “Maintenance Engineering Plan, Nondestructive Inspection”
6 R. J. Roark &
W. C. Young
“Formulas for Stress and Strain”, Fifth edition
7 D. P. Rooke &
D. J. Cartwright
“Compendium of Stress Intensity Factors”
8 D6-82669 Supplemental Structural Inspection Document Models 737-
300/400/500 Airplanes
9 2799 SUBSTANTIATION OF AEI BOEING 737-300, -400
TRANSPONDER, GPS AND TCAS ANTENNA INSTALLATION, RevC, Dated 4/25/2013
10 R-816, revision J Supplemental Structural Inspection Document For Boeing Model
737-400 Airplane With Cargo Conversion Modification
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DOCUMENT NO.EAK-15-507-DT
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CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
1.0 INTRODUCTION This report presents the damage tolerance evaluation of 1. TCAS Antenna Doubler, FS370 between S-2L and S-1 3” Hole w/ external doubler (.080 2024-T3), external mounting plate 2. ATC L-band Antenna Doubler, FS427 between S-2L and S-1 (Ref AMM 34-53-11) 1” Hole w/ external doubler (.080 2024-T3), internal mounting plate. 3. GPS 1 Antenna, FS500D+5.0 between S-2R and S-1, GPS 2 Antenna, FS500D+15.0 between S-1 and S-2L, 2” Hole with external doubler (.081 2024-T3), and internal mounting plate on AEI 737-400 aircraft. Installation of the repair is performed per Engineering Order 1670A (Reference 2). Static Strength of these installations is evaluated under separate cover. Certification basis of 737-400 aircraft is has been brought up to the damage tolerance requirements by virtue of Supplemental Structural Inspection Document (SSID) release. In addition, it is a requirement to perform damage tolerance assessment of the repairs to the pressure shell of the aircraft 1.1 SUMMARY OF RESULTS The results of the damage tolerance evaluation presented in this report show that damage tolerance requirements are met and there are supplemental inspections in addition to existing fuselage inspections.
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Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
2.0 ANTENNAE INSTALLATION Antennae are relocated due to the cargo conversion of the aircraft performed per STC ST01827LA As A part of the main cargo door installation, the existing aircraft skin from FS360 to FS540 and from S-2R to S-22L is repalced with new 0.080 inch thick 2024-T3 Clad skins, installed per AEI drawing AE6203. Antennae had to be relocated as shown below.
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Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
REVISION
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R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
REVISION
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R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
REVISION
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11/02/15 DATE
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R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
REVISION
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R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
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PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
REVISION
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R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
2.1 DAMAGE TOLERANCE EVALUATION 2.1.1 FASTENER LOAD DEFINITION & DURABILITY ANALYSIS
In general, any structural modification or repair to an airframe can substantially degrade
durability and damage tolerance characteristics unless extreme care in design detail is taken. In case there is a doubler installed on the skin, there will be load transfer out of the skin into the doubler due to strain compatibility between the two pieces. The highest fastener loads, induced from the skin into the doubler, typically will occur at the first row of attachments between the skin and a doubler.
This phenomenon can be illustrated as follows: The gross stress in the skin is unchanged in a presence of a doubler, however now bearing
stress in the hole is introduced which will degrade both fatigue life and crack propagation life. The higher the ratio of bearing stress to gross stress is, the lower fatigue life will be. The fastener loads in a doubler to skin attachments are typically determined through a displacement compatibility analysis.
It can be stated that under the same loading a skin-doubler structural configuration with the highest bearing stress to gross stress ratio will be the most critical from the durability and damage tolerance viewpoint. Tom Swift presents results of the compatibility analysis for several types of skin-doubler combinations in his article “Repairs to Damage Tolerant Aircraft” (Reference 1).
bypass stress
bearing stress
gross stress
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SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
3.0 TCAS ANTENNA INSTALLATION
REVISION
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Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
The TCAS antenna is located on the top just left of the centerline between FS 360.0 and FS 380.0. The external doubler reinforces the 3.00" diameter hole drilled in the fuselage skin for the antenna connector. The doubler is .080 inch thick 2024-T3 clad aluminum. The .036 inch thick fuselage bonded skin was replaced by .080 inch thick 2024-T3 aluminum to accommodate the installation of a cargo door. The Antenna and doubler attach to this new .080 inch thick 2024-T3 skin. The doubler is riveted to the skin with NAS1097AD6 rivets
Stress for this location are obtained from Reference 9
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Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
It needs to be pointed out that limit stress for pressure only (condition 1) includes 1.33 factor that is not required for damage tolerance evaluations. Therefore hoghes stress is for condition 6 (Down Bending + Pressure) in the longitudinal direction Stress = 8909 psi (limt) For this analysis conservatively limit load is utilized for GAG once per flight load Stress = 8.909 ksi, R=0.0 GAG cycle LIMIT = 8.909 ksi .
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CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
CRACK GROWTH ANALYSIS
Critical flaw Location C=0.05 inch
Crack Path
Fuselage skin (0.160 inch)
Rivet hole
Initial Flaw (0.050 inch) Through flaw
Adjacent hole
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SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
The critical location would be at the first row of attachments between fuselage skin and splice doubler. The doubler is attached to the aircraft skin by 0.186 inch diameter aluminum rivets NAS1097AD6 Two stages of crack growth are considered STAGE I Crack growing from the hole and linking with the adjacent hole. The correction for the crack growing toward the adjacent holes is derived from Rooke & Cartwright (Reference 6).
Fastener pitch = 1.00 inches D=0.186 inch First attachment load per 1 ksi gross stress = 21 lbs (skin/doubler configuration) (Ref. 1, Figure 7) (3/16 inch diameter aluminum fastener data). Total first attachment load = (8.909)(21)(1.00) Total first attachment load = 187 lbs Bearing Stress = 187 / (0.186*0.080) Bearing Stress = 12.573 ksi Total crack length possible in Stage I is (1.00-.186) = 0.814 inch
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R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
STAGE II Continuing damage crack growth of initial crack, following linkup. The secondary 0.005 inch flaw will be grown during stage I crack growth and added to the initial crack size of Stage II.
Fastener pitch = 1.00 inches AFGROW 5.01.06.17 crack propagation program is used for crack growth analysis. Crack growth model utilized in this analysis : Non-Interaction Equation/Table : NASGRO Equation Retardation is not used for purposes of this analysis. The stress relieving effects of the stiffeners are ignored in this analysis Results of crack growth analysis for crack growth are presented in appendix A. da/dN data is obtained from the NASGRO material database Fastener spacing is 1.00 inch bypass = ((8.909-12.573(0.186/1.00)) = 6.57 ksi total = (6.57 + 12.573(0.186/1.00)) = 8.909 ksi (AFGROW required parameter) Bearing stress fraction = (12.573)/8.909 = 1.411 bypass stress fraction = (6.57/8.909) = 0.737
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R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
STAGE I Beta correction for the flaw growing toward the adjacent hole (Reference 8, Fig 110)
Crack length c Beta 0.005 1.01 0.10 1.012 0.20 1.04 0.30 1.06 0.40 1.07 0.60 1.10 0.70 1.13 0.814 1.19
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Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
REVISION
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R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
STAGE I Crack growth Crack starts from the 0.05 inch flaw and links up with the adjacent hole at 910600 flights STAGE II Crack growth Crack starts from the total length of 1.46 inch (Half length of 0.73 inch) flaw and becomes unstable at flights At this point it would be considered an overall failure (Conservative, since crack arresting capability of the frames is ignored) Total life = 987341 flights (crack growth)
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R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Stage I Crack Growth Title: 737 TCAS Antenna Stage I
Spectrum title: Constant amplitude loading
2020 <‐‐‐ crack geometry code: Single Through Crack at Hole ‐ Standard Solution
Cycles C Length Beta C Sb. Spectrum
Pass Life
0 0.005 3.278313 1 1 0
108000 0.025027 2.170056 1081 1081 108000
167400 0.045033 1.668841 1675 1675 167400
224400 0.065068 1.405154 2245 2245 224400
282100 0.085097 1.212113 2822 2822 282100
339100 0.105108 1.104672 3392 3392 339100
394300 0.125143 1.016084 3944 3944 394300
446300 0.145152 0.96065 4464 4464 446300
494600 0.165166 0.929554 4947 4947 494600
539200 0.18519 0.887378 5393 5393 539200
580400 0.205225 0.86195 5805 5805 580400
618500 0.225245 0.837489 6186 6186 618500
653900 0.245259 0.826378 6540 6540 653900
686900 0.265262 0.806015 6870 6870 686900
717400 0.285262 0.787507 7175 7175 717400
746100 0.305335 0.778943 7462 7462 746100
772800 0.325381 0.769976 7729 7729 772800
797800 0.345386 0.761329 7979 7979 797800
821500 0.365469 0.74536 8216 8216 821500
843800 0.385512 0.738023 8439 8439 843800
864800 0.405533 0.731091 8649 8649 864800
884600 0.42554 0.725167 8847 8847 884600
903300 0.445595 0.71993 9034 9034 903300
920900 0.465629 0.715051 9210 9210 920900
937600 0.48574 0.715051 9377 9377 937600
953400 0.505856 0.710522 9535 9535 953400
968300 0.525928 0.706331 9684 9684 968300
982400 0.546021 0.70277 9825 9825 982400
995700 0.566061 0.699558 9958 9958 995700
1008400 0.586168 0.699558 10085 10085 1008400
1020400 0.606211 0.696686 10205 10205 1020400
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SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
1031800 0.626335 0.696313 10319 10319 1031800
1042500 0.646339 0.696313 10426 10426 1042500
1052600 0.666374 0.697024 10527 10527 1052600
1062200 0.686535 0.697024 10623 10623 1062200
1071200 0.706616 0.69833 10713 10713 1071200
1079700 0.726727 0.70307 10798 10798 1079700
1087600 0.746761 0.70307 10877 10877 1087600
1095000 0.766799 0.710257 10951 10951 1095000
1101900 0.786816 0.710257 11020 11020 1101900
1108400 0.807012 0.718066 11085 11085 1108400
1110600 0.814196 0.718066 11107 11107 1110600
Stage II Crack Growth Title: 737 TCAS Antenna Stage II
Spectrum title: Constant amplitude loading
2010 <‐‐‐ crack geometry code: Internal Through Crack ‐ Standard Solution
Cycles C Length Beta C Sb. Spectrum
Pass Total Life
0 0.73 1.000789 1 1 910600
5200 0.780307 1.000872 53 53 915800
9800 0.830435 1.000962 99 99 920400
14000 0.88168 1.001063 141 141 924600
17700 0.931921 1.001173 178 178 928300
21100 0.983 1.001433 212 212 931700
24200 1.034325 1.001581 243 243 934800
27000 1.085169 1.001747 271 271 937600
29600 1.136749 1.001747 297 297 940200
32000 1.188611 1.001931 321 321 942600
34200 1.240215 1.002137 343 343 944800
36200 1.290933 1.002357 363 363 946800
38100 1.342882 1.0026 382 382 948700
39900 1.395886 1.002869 400 400 950500
41500 1.446463 1.002869 416 416 952100
43000 1.497163 1.003166 431 431 953600
44400 1.547642 1.003494 445 445 955000
45800 1.601499 1.003494 459 459 956400
47100 1.654855 1.003873 472 472 957700
48300 1.707232 1.004293 484 484 958900
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SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
49400 1.758171 1.004293 495 495 960000
50500 1.812145 1.004757 506 506 961100
51500 1.864096 1.004757 516 516 962100
52500 1.919066 1.005269 526 526 963100
53400 1.97131 1.005269 535 535 964000
54300 2.026484 1.005832 544 544 964900
55100 2.078111 1.006447 552 552 965700
55900 2.132488 1.006447 560 560 966500
56700 2.189724 1.007117 568 568 967300
57400 2.242444 1.007117 575 575 968000
58100 2.297706 1.007898 582 582 968700
58800 2.355886 1.007898 589 589 969400
59400 2.40811 1.007898 595 595 970000
60000 2.462822 1.008749 601 601 970600
60600 2.52008 1.008749 607 607 971200
61200 2.580187 1.009673 613 613 971800
61700 2.632562 1.009673 618 618 972300
62200 2.687147 1.010754 623 623 972800
62700 2.74424 1.010754 628 628 973300
63200 2.803818 1.010754 633 633 973800
63700 2.866291 1.011929 638 638 974300
64100 2.918376 1.011929 642 642 974700
64500 2.97248 1.013191 646 646 975100
64900 3.028872 1.013191 650 650 975500
65300 3.087483 1.013191 654 654 975900
65700 3.148639 1.014676 658 658 976300
66100 3.212518 1.014676 662 662 976700
66500 3.279113 1.016271 666 666 977100
66800 3.331296 1.016271 669 669 977400
67100 3.385223 1.016271 672 672 977700
67400 3.440988 1.016271 675 675 978000
67700 3.498997 1.018162 678 678 978300
68000 3.559237 1.018162 681 681 978600
68300 3.621685 1.018162 684 684 978900
68600 3.686841 1.020189 687 687 979200
68900 3.754704 1.020189 690 690 979500
69200 3.825259 1.022324 693 693 979800
69500 3.899349 1.022324 696 696 980100
69700 3.950463 1.022324 698 698 980300
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Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
69900 4.003029 1.022324 700 700 980500
70100 4.057406 1.024861 702 702 980700
70300 4.113696 1.024861 704 704 980900
70500 4.171695 1.024861 706 706 981100
70700 4.23149 1.027509 708 708 981300
70900 4.293878 1.027509 710 710 981500
71100 4.358303 1.027509 712 712 981700
71300 4.424879 1.027509 714 714 981900
71500 4.494202 1.030676 716 716 982100
71700 4.566455 1.030676 718 718 982300
71900 4.64133 1.030676 720 720 982500
72100 4.718988 1.034534 722 722 982700
72300 4.800987 1.034534 724 724 982900
72500 4.886258 1.034534 726 726 983100
72700 4.975024 1.03859 728 728 983300
72900 5.069226 1.03859 730 730 983500
73100 5.167607 1.03859 732 732 983700
73200 5.218464 1.03859 733 733 983800
73300 5.270491 1.043595 734 734 983900
73400 5.324943 1.043595 735 735 984000
73500 5.380723 1.043595 736 736 984100
73600 5.437887 1.043595 737 737 984200
73700 5.496494 1.043595 738 738 984300
73800 5.55661 1.048787 739 739 984400
73900 5.619781 1.048787 740 740 984500
74000 5.684686 1.048787 741 741 984600
74100 5.751412 1.048787 742 742 984700
74200 5.820047 1.048787 743 743 984800
74300 5.890689 1.055294 744 744 984900
74400 5.965684 1.055294 745 745 985000
74500 6.043055 1.055294 746 746 985100
74600 6.122939 1.055294 747 747 985200
74700 6.205482 1.061883 748 748 985300
74800 6.29357 1.061883 749 749 985400
74900 6.384866 1.061883 750 750 985500
75000 6.479587 1.061883 751 751 985600
75100 6.577969 1.070281 752 752 985700
75200 6.684576 1.070281 753 753 985800
75300 6.795802 1.070281 754 754 985900
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R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
75400 6.912021 1.078397 755 755 986000
75500 7.038746 1.078397 756 756 986100
75600 7.171941 1.078397 757 757 986200
75700 7.312241 1.088891 758 758 986300
75800 7.468775 1.088891 759 759 986400
75900 7.635178 1.088891 760 760 986500
76000 7.812694 1.103277 761 761 986600
76100 8.018662 1.103277 762 762 986700
76200 8.24205 1.11683 763 763 986800
76300 8.506348 1.11683 764 764 986900
76400 8.800479 1.136292 765 765 987000
76500 9.177075 1.136292 766 766 987100
76600 9.62057 1.169114 767 767 987200
76669 10.10825 1.191365 767 767 987269
76700 10.46958 1.191365 768 768 987300
76735 10.99536 1.238035 768 768 987335
76741 11.56773 1.273146 768 768 987341
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
24
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
3.1 TRANSPONDER ANTENNA INSTALLATION
External Doubler (2024-T3, t = .080")
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
25
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
The Transponder antenna weighs 4 oz and is mounted to the top just left of the centerline with 4, #10-32 screws between FS 420.0 and FS 440.0. The external doubler reinforces the 1.00" diameter hole drilled in the fuselage skin for the antenna connector. The doubler is .080 inch thick 2024-T3 clad aluminum. The doubler is riveted to the skin with NAS1097AD6 rivets. Stress for this location are obtained from Reference 9.
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
26
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
It needs to be pointed out that limit stress for pressure only (condition 1) includes 1.33 factor that is not required for damage tolerance evaluations. Therefore hoghes stress is for condition 6 (Down Bending + Pressure) in the longitudinal direction Stress = 9315 psi (limt) For this analysis conservatively limit load is utilized for GAG once per flight load Stress = 9.315 ksi, R=0.0 GAG cycle
LIMIT = 9.315 ksi .
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
27
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
CRACK GROWTH ANALYSIS
Critical flaw Location C=0.05 inch
Crack Path
Fuselage skin (0.160 inch)
Rivet hole
Initial Flaw (0.050 inch) Through flaw
Adjacent hole
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
28
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
The critical location would be at the first row of attachments between fuselage skin and splice doubler. The doubler is attached to the aircraft skin by 0.186 inch diameter aluminum rivets NAS1097AD6 Two stages of crack growth are considered STAGE I Crack growing from the hole and linking with the adjacent hole. The correction for the crack growing toward the adjacent holes is derived from Rooke & Cartwright (Reference 6).
Fastener pitch = 1.00 inches D=0.186 inch First attachment load per 1 ksi gross stress = 21 lbs (skin/doubler configuration) (Ref. 1, Figure 7) (3/16 inch diameter aluminum fastener data). Total first attachment load = (9.315)(21)(1.00) Total first attachment load = 187 lbs Bearing Stress = 195 / (0.186*0.080) Bearing Stress = 13.146 ksi Total crack length possible in Stage I is (1.00-.186) = 0.814 inch
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
29
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
STAGE II Continuing damage crack growth of initial crack, following linkup. The secondary 0.005 inch flaw will be grown during stage I crack growth and added to the initial crack size of Stage II.
Fastener pitch = 1.00 inches AFGROW 5.01.06.17 crack propagation program is used for crack growth analysis. Crack growth model utilized in this analysis : Non-Interaction Equation/Table : NASGRO Equation Retardation is not used for purposes of this analysis. The stress relieving effects of the stiffeners are ignored in this analysis Results of crack growth analysis for crack growth are presented in appendix A. da/dN data is obtained from the NASGRO material database Fastener spacing is 1.00 inch
bypass = ((9.315-13.146(0.186/1.00)) = 6.869 ksi
total = (6.869 + 13.146(0.186/1.00)) = 9.315 ksi (AFGROW required parameter) Bearing stress fraction = (13.146)/9.315 = 1.411 bypass stress fraction = (6.869/9.315) = 0.737
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
30
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
STAGE I Beta correction for the flaw growing toward the adjacent hole (Reference 8, Fig 110)
Crack length c Beta 0.005 1.01 0.10 1.012 0.20 1.04 0.30 1.06 0.40 1.07 0.60 1.10 0.70 1.13 0.814 1.19
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
31
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
32
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
STAGE I Crack growth Crack starts from the 0.05 inch flaw and links up with the adjacent hole at 776900 flights STAGE II Crack growth Crack starts from the total length of 1.47 inch (Half length of 0.735 inch) flaw and becomes unstable at flights At this point it would be considered an overall failure (Conservative, since crack arresting capability of the frames is ignored) Total life = 840871 flights (crack growth)
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
33
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Stage I Crack Growth Title: 737 Transponder Antenna Stage I
Spectrum title: Constant amplitude loading
2020 <‐‐‐ crack geometry code: Single Through Crack at Hole ‐ Standard Solution
Cycles C Length Beta C Sb. Spectrum
Pass Life
0 0.005 3.278313 1 1 0
90100 0.025002 2.166665 902 902 90100
140100 0.04502 1.664313 1402 1402 140100
188100 0.065055 1.401263 1882 1882 188100
236600 0.085091 1.20856 2367 2367 236600
284600 0.105108 1.101489 2847 2847 284600
331000 0.125149 1.013459 3311 3311 331000
374800 0.145164 0.958558 3749 3749 374800
415600 0.165195 0.927569 4157 4157 415600
453100 0.185212 0.885617 4532 4532 453100
487900 0.205267 0.860274 4880 4880 487900
520100 0.225322 0.835958 5202 5202 520100
550100 0.245359 0.824956 5502 5502 550100
578000 0.265417 0.804647 5781 5781 578000
603800 0.285422 0.795229 6039 6039 603800
628000 0.305476 0.777716 6281 6281 628000
650600 0.325519 0.768725 6507 6507 650600
671800 0.345555 0.76015 6719 6719 671800
691800 0.365638 0.751971 6919 6919 691800
710700 0.385731 0.736961 7108 7108 710700
728500 0.405776 0.730174 7286 7286 728500
745300 0.42583 0.72435 7454 7454 745300
761100 0.445848 0.719145 7612 7612 761100
776100 0.465965 0.719145 7762 7762 776100
790200 0.485994 0.714314 7903 7903 790200
803600 0.506147 0.709844 8037 8037 803600
816200 0.526194 0.705753 8163 8163 816200
828100 0.546213 0.702265 8282 8282 828100
839400 0.566261 0.702265 8395 8395 839400
850200 0.58643 0.699099 8503 8503 850200
860400 0.606543 0.696271 8605 8605 860400
870100 0.626703 0.696271 8702 8702 870100
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
34
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
879200 0.646778 0.696391 8793 8793 879200
887800 0.666897 0.697197 8879 8879 887800
895900 0.686979 0.697197 8960 8960 895900
903600 0.707233 0.698569 9037 9037 903600
910900 0.727518 0.704173 9110 9110 910900
917600 0.747685 0.704173 9177 9177 917600
923900 0.767753 0.711453 9240 9240 923900
929800 0.788083 0.711453 9299 9299 929800
935300 0.808187 0.719376 9354 9354 935300
936900 0.814389 0.719376 9370 9370 936900
Stage II Crack Growth Title: 737 Transponder Antenna Stage II
Spectrum title: Constant amplitude loading
2010 <‐‐‐ crack geometry code: Internal Through Crack ‐ Standard Solution
Cycles C Length Beta C Sb. Spectrum
Pass Total Life
0 0.735 1.0008 1 1 776900
4400 0.785801 1.000884 45 45 781300
8300 0.836561 1.000978 84 84 785200
11800 0.887564 1.001079 119 119 788700
14900 0.937805 1.001192 150 150 791800
17700 0.987953 1.001318 178 178 794600
20300 1.039214 1.001458 204 204 797200
22700 1.091153 1.001614 228 228 799600
24900 1.143234 1.001781 250 250 801800
26900 1.194812 1.001965 270 270 803800
28700 1.245139 1.002167 288 288 805600
30400 1.296498 1.002401 305 305 807300
32000 1.348651 1.002661 321 321 808900
33500 1.401314 1.002661 336 336 810400
34900 1.454151 1.002948 350 350 811800
36200 1.506752 1.003265 363 363 813100
37400 1.558657 1.003613 375 375 814300
38500 1.609393 1.003613 386 386 815400
39600 1.663425 1.003994 397 397 816500
40600 1.715694 1.003994 407 407 817500
41600 1.7713 1.00441 417 417 818500
42500 1.824431 1.004893 426 426 819400
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
35
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
43400 1.880818 1.004893 435 435 820300
44200 1.933907 1.005421 443 443 821100
45000 1.990049 1.005421 451 451 821900
45700 2.041929 1.005995 458 458 822600
46400 2.096556 1.005995 465 465 823300
47100 2.154235 1.006666 472 472 824000
47700 2.206254 1.006666 478 478 824600
48300 2.260915 1.007395 484 484 825200
48900 2.318376 1.007395 490 490 825800
49400 2.368615 1.008181 495 495 826300
49900 2.42113 1.008181 500 500 826800
50400 2.476061 1.009103 505 505 827300
50900 2.533712 1.009103 510 510 827800
51400 2.594119 1.010097 515 515 828300
51800 2.644775 1.010097 519 519 828700
52200 2.697466 1.010097 523 523 829100
52600 2.752444 1.011155 527 527 829500
53000 2.809867 1.011155 531 531 829900
53400 2.869782 1.012396 535 535 830300
53800 2.932684 1.012396 539 539 830700
54200 2.998478 1.012396 543 543 831100
54500 3.050037 1.013711 546 546 831400
54800 3.103554 1.013711 549 549 831700
55100 3.15905 1.013711 552 552 832000
55400 3.216894 1.015262 555 555 832300
55700 3.277116 1.015262 558 558 832600
56000 3.339741 1.016892 561 561 832900
56300 3.405376 1.016892 564 564 833200
56600 3.473786 1.016892 567 567 833500
56900 3.545359 1.018825 570 570 833800
57200 3.620545 1.018825 573 573 834100
57400 3.672587 1.018825 575 575 834300
57600 3.726484 1.020835 577 577 834500
57800 3.782344 1.020835 579 579 834700
58000 3.840038 1.020835 581 581 834900
58200 3.899665 1.023229 583 583 835100
58400 3.961975 1.023229 585 585 835300
58600 4.026492 1.023229 587 587 835500
58800 4.09335 1.023229 589 589 835700
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
36
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
59000 4.163132 1.026127 591 591 835900
59200 4.236049 1.026127 593 593 836100
59400 4.311855 1.026127 595 595 836300
59600 4.391276 1.029147 597 597 836500
59800 4.474599 1.029147 599 599 836700
60000 4.561566 1.029147 601 601 836900
60200 4.653211 1.032833 603 603 837100
60400 4.749955 1.032833 605 605 837300
60500 4.800081 1.032833 606 606 837400
60600 4.851441 1.0366 607 607 837500
60700 4.904988 1.0366 608 608 837600
60800 4.959927 1.0366 609 609 837700
60900 5.016322 1.0366 610 610 837800
61000 5.074239 1.0366 611 611 837900
61100 5.13375 1.041235 612 612 838000
61200 5.196248 1.041235 613 613 838100
61300 5.260583 1.041235 614 614 838200
61400 5.32685 1.041235 615 615 838300
61500 5.395151 1.045815 616 616 838400
61600 5.467123 1.045815 617 617 838500
61700 5.541469 1.045815 618 618 838600
61800 5.618329 1.045815 619 619 838700
61900 5.697858 1.051478 620 620 838800
62000 5.782482 1.051478 621 621 838900
62100 5.87031 1.051478 622 622 839000
62200 5.961564 1.051478 623 623 839100
62300 6.056488 1.058707 624 624 839200
62400 6.158937 1.058707 625 625 839300
62500 6.265982 1.058707 626 626 839400
62600 6.378011 1.06569 627 627 839500
62700 6.499689 1.06569 628 628 839600
62800 6.627775 1.06569 629 629 839700
62900 6.762918 1.074704 630 630 839800
63000 6.912819 1.074704 631 631 839900
63100 7.072407 1.074704 632 632 840000
63200 7.242925 1.087011 633 633 840100
63300 7.438865 1.087011 634 634 840200
63400 7.65157 1.098485 635 635 840300
63500 7.900369 1.098485 636 636 840400
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
37
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
63600 8.177061 1.114703 637 637 840500
63700 8.523175 1.114703 638 638 840600
63800 8.927815 1.141042 639 639 840700
63875 9.377425 1.158814 639 639 840775
63900 9.603247 1.158814 640 640 840800
63947 10.09259 1.190616 640 640 840847
63968 10.59887 1.216108 640 640 840868
63971 11.28335 1.25516 640 640 840871
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
38
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
3.2 GPS ANTENNA INSTALLATION (GPS 1 & 2)
Installations are the same performed in different fuselage bays.
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
39
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
40
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
The GPS antenna weighs less than a pound and is mounted to the top just right and left of the centerline with 4, #10-32 screws. The external doubler reinforces the 2.0" diameter hole drilled in the fuselage skin for the antenna connector for the 737-400 aircraft. The doubler is .080 inch thick 2024-T3 clad aluminum. The doubler is riveted to the skin with NAS1097AD6 rivets. Stress for this location are obtained from Reference 9 (Element 11033 and 11034)
GPS 1 & 2 antennae Location
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
41
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
AEI 737‐400 Converted Freighter
Fuselage Skin Panel Stresses, Bet. S‐2L to S‐2R
OUTPUT SET 1 ‐ Pressure Only 17.3 psi
Elem PRINCIPAL STRESSES (ZERO SHEAR)
ID FIBRE DIST NORMAL‐X NORMAL‐Y SHEAR‐XY ANGLE MAJOR MINOR VON MISES
40 BOT ‐0.09 5002 5777 5467 47.03 10870 ‐92 10916
TOP 0.09 4648 5553 5572 47.32 10691 ‐490 10944
71 BOT ‐0.09 9764 9269 ‐5073 ‐43.60 14595 4438 12959
TOP 0.09 9271 8665 ‐5309 ‐43.37 14285 3650 12855
10622 BOT ‐0.02 25802 14455 635 3.19 25837 14420 22426
TOP 0.02 25639 14168 616 3.07 25672 14135 22271
10623 BOT ‐0.02 16741 11049 433 4.33 16774 11016 14762
TOP 0.02 16660 10797 371 3.60 16683 10774 14651
10628 BOT ‐0.02 26744 15098 ‐1107 ‐5.38 26849 14994 23305
TOP 0.02 26628 15023 ‐1201 ‐5.85 26751 14900 23217
10629 BOT ‐0.02 21863 13148 ‐2299 ‐13.91 22433 12579 19475
TOP 0.02 21851 13032 ‐2347 ‐14.01 22437 12446 19470
11031 BOT ‐0.02 26045 15740 ‐751 ‐4.15 26100 15685 22756
TOP 0.02 26020 15698 ‐762 ‐4.20 26076 15642 22732
11032 BOT ‐0.02 25935 16841 ‐878 ‐5.46 26019 16757 22843
TOP 0.02 25908 16791 ‐889 ‐5.52 25994 16705 22814
11033 BOT ‐0.02 26584 18108 ‐987 ‐6.55 26697 17995 23583
TOP 0.02 26575 18072 ‐982 ‐6.50 26687 17960 23568
11034 BOT ‐0.02 26583 19167 ‐822 ‐6.25 26673 19077 23802
TOP 0.02 26593 19131 ‐813 ‐6.15 26681 19043 23800
11035 BOT ‐0.02 26844 20067 ‐113 ‐0.96 26846 20065 24179
TOP 0.02 26892 20096 ‐116 ‐0.98 26894 20094 24221
11105 BOT ‐0.02 26459 14774 ‐75 ‐0.37 26460 14774 22967
TOP 0.02 26461 14859 ‐120 ‐0.59 26462 14858 22975
11106 BOT ‐0.02 27310 16267 ‐1211 ‐6.19 27442 16136 23887
TOP 0.02 27361 16428 ‐1244 ‐6.41 27500 16288 23951
11107 BOT ‐0.02 24604 17531 ‐1646 ‐12.48 24968 17167 22124
TOP 0.02 24646 17729 ‐1691 ‐13.03 25037 17338 22212
11108 BOT ‐0.02 24408 19598 ‐1492 ‐15.90 24833 19173 22542
TOP 0.02 24536 19882 ‐1526 ‐16.63 24991 19427 22726
11109 BOT ‐0.02 22874 20914 ‐887 ‐21.08 23216 20572 22013
TOP 0.02 23012 21135 ‐900 ‐21.90 23373 20773 22188
70642 BOT ‐0.04 4777 8623 2194 65.62 9618 3782 8393
TOP 0.04 4675 8267 2187 64.70 9301 3640 8118
70643 BOT ‐0.04 11478 5899 ‐3411 ‐25.36 13095 4282 11564
TOP 0.04 11489 5817 ‐3434 ‐25.22 13106 4200 11592
70644 BOT ‐0.09 9287 10384 ‐1662 ‐54.13 11586 8085 10292
TOP 0.09 9052 9984 ‐2146 ‐51.13 11715 7322 10250
70657 BOT ‐0.04 8280 8187 ‐1143 ‐43.83 9378 7089 8468
TOP 0.04 7963 7628 ‐1189 ‐40.99 8996 6596 8068
70658 BOT ‐0.04 7009 7571 ‐3340 ‐47.40 10642 3938 9319
TOP 0.04 6461 7027 ‐3327 ‐47.43 10083 3405 8884
70659 BOT ‐0.04 7300 8254 ‐5360 ‐47.54 13158 2396 12139
TOP 0.04 7099 7960 ‐5434 ‐47.26 12980 2079 12076
70660 BOT ‐0.09 4507 8768 ‐3089 ‐62.30 10390 2885 9290
TOP 0.09 4160 8578 ‐3195 ‐62.33 10254 2485 9265
70661 BOT ‐0.09 4110 6044 5755 49.77 10913 ‐759 11312
TOP 0.09 4024 6150 5865 50.14 11047 ‐874 11509
70686 BOT ‐0.04 13486 10025 ‐2491 ‐27.61 14789 8722 12876
TOP 0.04 13305 9608 ‐2634 ‐27.47 14674 8238 12740
70687 BOT ‐0.04 12085 10388 ‐3876 ‐38.83 15204 7269 13172
TOP 0.04 11703 9684 ‐3885 ‐37.72 14707 6679 12755
70688 BOT ‐0.04 10765 12776 ‐4998 ‐50.69 16869 6672 14715
TOP 0.04 10593 12237 ‐4778 ‐49.88 16263 6567 14171
70689 BOT ‐0.04 7068 11633 ‐4109 ‐59.53 14051 4651 12398
TOP 0.04 6817 11418 ‐3875 ‐60.35 13624 4611 12002
70690 BOT ‐0.04 6799 9145 5012 51.59 13119 2824 11959
TOP 0.04 6553 9058 5055 51.96 13014 2597 11929
Note: NORMAL‐X ‐ Hoop Stress (psi)
NORMAL‐Y ‐ Axial Stress (psi)
SHEAR‐XY ‐ Shear Stress (psi)
ELEMENT STRESSES
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
42
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
AEI 737‐400 Converted Freighter
Fuselage Skin Panel Stresses, Bet. S‐2L to S‐2R
OUTPUT SET 2 ‐ Down Bending
Elem PRINCIPAL STRESSES (ZERO SHEAR)
ID FIBRE DIST NORMAL‐X NORMAL‐Y SHEAR‐XY ANGLE MAJOR MINOR VON MISES
40 BOT ‐0.09 ‐1476 4213 3354 65.15 5766 ‐3029 7738
TOP 0.09 ‐1614 4360 3718 64.39 6142 ‐3396 8374
71 BOT ‐0.09 2159 7662 ‐4939 ‐59.56 10564 ‐743 10954
TOP 0.09 2294 8246 ‐5079 ‐60.18 11156 ‐617 11477
10622 BOT ‐0.02 1021 14222 943 85.93 14289 954 13837
TOP 0.02 966 14212 938 85.97 14279 900 13851
10623 BOT ‐0.02 2106 13879 ‐1085 ‐84.78 13978 2007 13090
TOP 0.02 2082 13892 ‐1088 ‐84.78 13992 1983 13113
10628 BOT ‐0.02 1292 14579 3143 77.34 15285 586 15000
TOP 0.02 1223 14573 3157 77.34 15282 514 15032
10629 BOT ‐0.02 1807 15648 ‐1074 ‐85.59 15731 1724 14944
TOP 0.02 1775 15670 ‐1071 ‐85.62 15752 1693 14978
11031 BOT ‐0.02 1175 18857 160 89.48 18859 1174 18300
TOP 0.02 1085 18837 173 89.44 18839 1083 18321
11032 BOT ‐0.02 1146 20252 ‐648 ‐88.06 20274 1124 19736
TOP 0.02 1061 20242 ‐637 ‐88.10 20263 1040 19763
11033 BOT ‐0.02 1022 21456 ‐1059 ‐87.04 21510 967 21044
TOP 0.02 959 21453 ‐1050 ‐87.07 21506 906 21068
11034 BOT ‐0.02 1057 22221 ‐922 ‐87.51 22261 1017 21770
TOP 0.02 1023 22221 ‐918 ‐87.53 22260 983 21785
11035 BOT ‐0.02 1203 22256 ‐546 ‐88.51 22270 1189 21700
TOP 0.02 1200 22273 ‐553 ‐88.50 22288 1185 21719
11105 BOT ‐0.02 1121 16475 519 88.07 16493 1103 15970
TOP 0.02 1035 16454 530 88.03 16472 1017 15988
11106 BOT ‐0.02 1354 18680 ‐1481 ‐85.15 18805 1228 18222
TOP 0.02 1279 18659 ‐1477 ‐85.18 18784 1154 18234
11107 BOT ‐0.02 1761 21522 ‐1892 ‐84.58 21702 1582 20956
TOP 0.02 1705 21523 ‐1893 ‐84.59 21702 1526 20981
11108 BOT ‐0.02 1950 22966 ‐1496 ‐85.95 23072 1844 22207
TOP 0.02 1943 23005 ‐1498 ‐85.95 23111 1837 22250
11109 BOT ‐0.02 1720 22873 ‐1011 ‐87.27 22922 1672 22133
TOP 0.02 1750 22909 ‐1007 ‐87.28 22957 1702 22155
70642 BOT ‐0.04 9740 1330 3014 17.81 10709 361 10532
TOP 0.04 9852 1309 3028 17.67 10816 345 10648
70643 BOT ‐0.04 2755 9465 ‐3213 ‐68.12 10755 1465 10103
TOP 0.04 2798 9607 ‐3241 ‐68.20 10903 1502 10235
70644 BOT ‐0.09 2333 9658 ‐5326 ‐62.26 12460 ‐468 12700
TOP 0.09 2401 10052 ‐5565 ‐62.25 12980 ‐526 13251
70657 BOT ‐0.04 1399 12708 ‐1829 ‐81.04 12997 1111 12479
TOP 0.04 1338 12791 ‐1823 ‐81.17 13074 1055 12580
70658 BOT ‐0.04 1246 12132 ‐3121 ‐75.08 12963 414 12761
TOP 0.04 1203 12260 ‐3114 ‐75.31 13076 386 12888
70659 BOT ‐0.04 837 11167 ‐3027 ‐74.81 11988 15 11980
TOP 0.04 848 11295 ‐3061 ‐74.82 12125 17 12117
70660 BOT ‐0.09 ‐356 8900 ‐594 ‐86.34 8938 ‐394 9142
TOP 0.09 ‐230 9197 ‐576 ‐86.51 9232 ‐265 9367
70661 BOT ‐0.09 262 4972 3342 62.59 6705 ‐1472 7550
TOP 0.09 349 5203 3537 62.23 7066 ‐1514 7932
70686 BOT ‐0.04 733 13672 ‐1449 ‐83.69 13833 572 13555
TOP 0.04 644 13662 ‐1471 ‐83.63 13826 480 13592
70687 BOT ‐0.04 187 13336 ‐1689 ‐82.80 13550 ‐26 13563
TOP 0.04 86 13248 ‐1706 ‐82.73 13465 ‐132 13532
70688 BOT ‐0.04 ‐71 14270 ‐1395 ‐84.50 14405 ‐205 14509
TOP 0.04 ‐60 14285 ‐1363 ‐84.62 14414 ‐189 14509
70689 BOT ‐0.04 ‐417 11338 ‐767 ‐86.28 11388 ‐467 11629
TOP 0.04 ‐338 11475 ‐725 ‐86.50 11519 ‐383 11715
70690 BOT ‐0.04 134 7412 3116 69.72 8564 ‐1018 9115
TOP 0.04 233 7526 3147 69.60 8696 ‐937 9200
Note: NORMAL‐X ‐ Hoop Stress (psi)
NORMAL‐Y ‐ Axial Stress (psi)
SHEAR‐XY ‐ Shear Stress (psi)
ELEMENT STRESSES
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
43
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
44
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
45
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Pressure case Operational pressure is 7.85 psi Taking stress levels from element 11034 Longitudinal stress level = (7.85/17.3)(19167) = 8697 psi Hoop stress level = (7.85/17.3)( 26593) = 12067 psi Down Bending case (2.5 G limit) Taking 1.5 G conservatively as GAG stress level Longitudinal stress level = (1.5/2.5)(22221) = 13332 psi Hoop stress level = (1.5/2.5)(1057) = 484 psi Typical GAG load case is (1P+1.5G)(longitudinal direction) σ = (8697+ 13332) = 22029 psi (longitudinal load case) Typical GAG load case (1.15P +1.0 G)(Hoop direction) σ = (12087*1.15+484) = 14384 psi (longitudinal load case) σ = 22.029 ksi (longitudinal load case)
LIMIT = (8697+22221) = 30.918 ksi
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
46
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
For this analysis (1.5G +1.0P)is utilized for GAG once per flight load Stress = 22.029 ksi, R=0.0 GAG cycle
LIMIT = 30.918 ksi Skin thickness is 0.040 inch
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
47
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
CRACK GROWTH ANALYSIS
Critical flaw Location C=0.05 inch
Crack Path
Fuselage skin (0.036 inch)
Rivet hole
Initial Flaw (0.050 inch) Through flaw
Adjacent hole
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
48
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
The critical location would be at the first row of attachments between fuselage skin and splice doubler. The doubler is attached to the aircraft skin by 0.186 inch diameter aluminum rivets NAS1097AD6 Two stages of crack growth are considered STAGE I Crack growing from the hole and linking with the adjacent hole. The correction for the crack growing toward the adjacent holes is derived from Rooke & Cartwright (Reference 6).
Fastener pitch = 1.00 inches D=0.186 inch First attachment load per 1 ksi gross stress = 14 lbs (skin/doubler configuration) (Ref. 1, Figure 7) (3/16 inch diameter aluminum fastener data). Total first attachment load = (22.029)(14)(1.00) Total first attachment load = 308 lbs Bearing Stress = 308 / (0.186*0.040) Bearing Stress = 41.452 ksi Total crack length possible in Stage I is (1.00-.186) = 0.814 inch
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
49
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
STAGE II Continuing damage crack growth of initial crack, following linkup. The secondary 0.005 inch flaw will be grown during stage I crack growth and added to the initial crack size of Stage II.
Fastener pitch = 1.00 inches AFGROW 5.01.06.17 crack propagation program is used for crack growth analysis. Crack growth model utilized in this analysis : Non-Interaction Equation/Table : NASGRO Equation Retardation is not used for purposes of this analysis. The stress relieving effects of the stiffeners are ignored in this analysis Results of crack growth analysis for crack growth are presented in appendix A. da/dN data is obtained from the NASGRO material database Fastener spacing is 1.00 inch
bypass = ((22.029-41.452(0.186/1.00)) = 14.319 ksi
total = (14.319 + 41.452(0.186/1.00)) = 22.029 ksi (AFGROW required parameter) Bearing stress fraction = 41.452)/22.029 = 1.882 bypass stress fraction = (14.319/22.029) = 0.65
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
50
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
STAGE I Beta correction for the flaw growing toward the adjacent hole (Reference 8, Fig 110)
Crack length c Beta 0.005 1.01 0.10 1.012 0.20 1.04 0.30 1.06 0.40 1.07 0.60 1.10 0.70 1.13 0.814 1.19
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
51
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
52
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
STAGE I Crack growth Crack starts from the 0.05 inch flaw and links up with the adjacent hole at 32500 flights STAGE II Crack growth Not used At this point it would be considered an overall failure (Conservative, since crack arresting capability of the frames is ignored) Total life = 32500 flights (crack growth)
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
53
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Stage I Crack Growth Title: 737 GPS Antenna Stage I 500D location
Spectrum title: Constant amplitude loading
2020 <‐‐‐ crack geometry code: Single Through Crack at Hole ‐ Standard Solution
Cycles C Length Beta C Sb. Spectrum
Pass Life
0 0.05 1.717043 1 1 0
800 0.061036 1.568872 9 9 800
1600 0.072082 1.41812 17 17 1600
2400 0.08268 1.338474 25 25 2400
3200 0.093183 1.248782 33 33 3200
4000 0.103453 1.182051 41 41 4000
4800 0.113771 1.120921 49 49 4800
5600 0.124113 1.090701 57 57 5600
6400 0.134434 1.036946 65 65 6400
7200 0.144897 1.009545 73 73 7200
8000 0.155573 0.964306 81 81 8000
8800 0.166288 0.943989 89 89 8800
9600 0.177344 0.923079 97 97 9600
10400 0.188718 0.904766 105 105 10400
11100 0.198963 0.887648 112 112 11100
11800 0.209492 0.871375 119 119 11800
12500 0.220304 0.855656 126 126 12500
13200 0.231408 0.840905 133 133 13200
13900 0.242881 0.82503 140 140 13900
14500 0.253025 0.810185 146 146 14500
15100 0.26336 0.810185 152 152 15100
15700 0.27391 0.796277 158 158 15700
16300 0.284811 0.78377 164 164 16300
16900 0.296084 0.772189 170 170 16900
17500 0.307647 0.772189 176 176 17500
18100 0.319493 0.760573 182 182 18100
18600 0.329693 0.749177 187 187 18600
19100 0.340143 0.749177 192 192 19100
19600 0.35075 0.738395 197 197 19600
20100 0.361748 0.728234 202 202 20100
20600 0.37292 0.728234 207 207 20600
21100 0.384406 0.718761 212 212 21100
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
54
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
21600 0.396326 0.718761 217 217 21600
22100 0.408419 0.708638 222 222 22100
22500 0.41849 0.708638 226 226 22500
22900 0.428665 0.699798 230 230 22900
23300 0.439184 0.699798 234 234 23300
23700 0.449956 0.691631 238 238 23700
24100 0.46098 0.691631 242 242 24100
24500 0.472401 0.683933 246 246 24500
24900 0.483985 0.683933 250 250 24900
25300 0.496113 0.676687 254 254 25300
25700 0.508317 0.676687 258 258 25700
26100 0.521099 0.671047 262 262 26100
26500 0.534075 0.671047 266 266 26500
26800 0.544214 0.671047 269 269 26800
27100 0.554511 0.665719 272 272 27100
27400 0.565073 0.665719 275 275 27400
27700 0.576022 0.660703 278 278 27700
28000 0.587055 0.660703 281 281 28000
28300 0.598494 0.660703 284 284 28300
28600 0.610269 0.656579 287 287 28600
28900 0.622295 0.656579 290 290 28900
29200 0.63478 0.656579 293 293 29200
29500 0.647695 0.655497 296 296 29500
29800 0.66109 0.655497 299 299 29800
30100 0.675024 0.654895 302 302 30100
30400 0.689478 0.654895 305 305 30400
30700 0.704536 0.654895 308 308 30700
30900 0.714965 0.656088 310 310 30900
31100 0.725733 0.656088 312 312 31100
31300 0.736816 0.656088 314 314 31300
31500 0.74823 0.661489 316 316 31500
31700 0.760371 0.661489 318 318 31700
31900 0.772897 0.661489 320 320 31900
32100 0.785829 0.667269 322 322 32100
32300 0.799651 0.667269 324 324 32300
32500 0.813952 0.667269 326 326 32500
32600 0.821291 0.667269 327 327 32600
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
55
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Stage II Crack Growth NOT USED
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
56
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
4.0 RESIDUAL STRENGTH EVALUATION For the pressurized cabins of aircraft certificated to Amendment 96, FAR 25.571 requires that the residual strength evaluation must show that the remaining structure is able to withstand loads corresponding to the following conditions: (i) The normal operating differential pressure combined with the expected external aerodynamic pressures applied simultaneously with the flight loading conditions specified in paragraphs (b)(1) through (4) of FAR 25.571, if they have significant effect. (ii) The expected external aerodynamic pressures in 1 g flight combined with a cabin differential pressure equal to 1.15 times the normal operating differential pressure without any other load. Condition (i) typically takes precedence for modifications located on the top of the fuselage, since the tensile fuselage bending stresses are significant. Condition (ii) takes precedence for modifications located on the bottom of the fuselage since the fuselage bending stresses are compressive. The critical crack lengths for the modification are calculated for the fastener holes. The apparent fracture toughness, Kf, of 0.050" thick clad 2024-T3 material, 153 ksiin, was taken from the material database of the Federal Aviation Administration's RAPID v2.1 aircraft repair design and analysis program. The database provides fracture toughness data for a sheet thickness ranging from 0.010" to 0.090". The most critical installation is GPS antenna and it is used for residual strength evaluation Fresidual =( KIC)/((beta)(3.14*c)) 0.5
GPS ANTENNA 1 & 2 INSTALLATION) At 32500 flights crack half length reaches 0.814 inch Fresidual =(153)/{(0.667)(3.14*0.814)} 0.5
Fresidual =143 ksi LIMIT = 30.918 ksi (Axial direction, principal)
LIMIT < Fresidual Therefore it can be stated that crack growth life of this detail is conservatively assumed to be 32500 Flight cycles.
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
57
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
5.0 INSPECTION REQUIREMENTS
The crack growth was calculated using iterative techniques. The critical location initial flaw was assumed to be a 0.05" through crack at the edge of a circular hole, growing perpendicular to the applied load. The threshold inspection interval is defined as the number of aircraft landings permitted from the time of installation before the first inspection must be conducted. The recurring inspection interval is defined as the number of landings allowed between subsequent inspections.
GPS antenna analysis is utilized for all three (3) Door surround doubler antenna installations, since it has the shortest life.
Crack growth life is long
Detailed visual Inspection is utilized.
Detailed visual inspection detectable flaw size = 1.00 inch (Reference 5)
Crack is detectable following link-up
Life from the point of crack link-up (for GPS Antenna) is 42122 flight cycles
GPS antenna location installed on the original fuselage skin
Doublers are installed externally and internally and critical crack length is relatively short. Therefore, NDI inspections are required.
High Frequency Eddy Current Inspection is utilized.
HFEC inspection detectable flaw size = 0.300 inch (conservative)
Crack reaches detectable size at 17500 flight cycles
N threshold =12000 landings (Supported by crack growth analysis)(Since installation)
This is conservative, since following inspectionwas performed during antenna installation. Accomplish HFEC inspection at all existing fastener holes common to the subject area per 737NDT Manual, Part 6, 51-00-00, Procedure 16 (0.03inch notch) to verify crack free structure
Repeat inspection is calculated as total crack growth life with number flights when crack becomes detectable subtracted and then divided by a scatter factor.
Inspection interval = (32500-17500)/2 = 7500 flight-cycles (Supported by crack growth)
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
58
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Upper skin splice is inspected under requirements of F-31(Reference 10)
Addition of extra fasteners rows will reduce bearing stress level in the first row of attachments betwwen the existing skin and splice. Therefore, existion inspections are sufficient
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
59
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
60
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
61
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Therefore, following inspections are utilized for the antenna locations on the door surround doubler
Inspection threshold = 30,000 flight cycles
Repeat interval = 20,000 flight cycles
Inspection Method is detailed visual
Different inspections are utilized for the GPS antenna location on the original fusealge skin
Inspection threshold = 12,000 flight cycles
Repeat interval = 7,500 flight cycles
Inspection Method is HFEC
Note: Antenna has to be removed for inspection
Note: Inspections have to be performed by the qualified NDI specialist
Note: Inspection requirements have to be added to the aircraft ICA’s ALI portion
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
62
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Inspection requirements are for 737 antenna relocation installations
Inspection Intervals (Landings)
Detectable Crack
DOOR SURROUND DOUBLER INSTALLATIONS
Threshold Recurring Length (in) Detailed visual
TCAS Antenna 30000 20000 1.00 Transponder Antenna 30000 20000 1.00 ORIGINAL SKIN INSTALLATION
HFEC
GPS antenna 1 & 2 12000 7500 0.3 INSPECTION PROGRAM Perform additional inspection of the antenna installations INSPECTION METHOD
Inspect fuselage skin in the antenna installation area, doubler fastener holes, anrenna penetration hole and antenna attachment holes area, using detailed visual inspection techniques or HFEC inspection technique, according to the intervals outlined in the table above. For the fastener holes, the inspector should look for cracks on the surfaces of the skin and doubler around the fastener holes.
MAINTENANCE MANUAL SUPPLEMENT GUIDELINES A maintenance manual supplement should be created that describes in detail the locations to be examined and the inspection procedure to be followed. The inspection intervals contained within the maintenance manual supplement may be aligned with the existing aircraft maintenance program, provided the following conditions are met: (1) The maintenance check for the aircraft occurs before the threshold inspection interval indicated by the analysis in this report. (2) Subsequent maintenance checks for the aircraft occur before the recurring inspection interval indicated by the analysis in this report. If the maintenance checks for the aircraft exceed the threshold or recurring inspection intervals specified in this report, then the inspection intervals specified within this report apply. Inspection area is presented on the next page
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
63
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
TCAS ANTENNA INSPECTION AREA & METHOD
Detailed Visual Inspection Area
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
64
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
TRANSPONDER ANTENNA
INSPECTION AREA & METHOD
Detailed Visual Inspection Area
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
65
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
GPS ANTENNA 1 &2
INSPECTION AREA & METHOD
HFEC Inspection Area. Additionally inspection fuselage skin Chem-milled step area around the periphery of skin bay with antenna installation
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A1
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
APPENDIX A REFERENCE MATERIAL
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A2
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A3
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A4
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
TCAS ANTENNA CRACK GROWTH PHASE I
AFGROW 5.1.6.17 **English Units [ Length(in), Stress(Ksi), Temperature(F) ] Crack Growth Model and Spectrum Information Title: 737 TCAS Antenna Stage I Load: Axial Stress Fraction: 0.737, Bending Stress Fraction: 0, Bearing Stress Fraction: 1.411 Crack Model: 2020 - Single Through Crack at Hole - Standard Solution Initial surface crack length (c): 0.0050 Thickness : 0.080 Width : 20.000 Hole Diameter: 0.156 Young's Modulus =10600 Poisson's Ratio =0.33 Coeff. of Thermal Expan. =1.29e-005 No crack growth retardation is being considered Determine Stress State automatically (2 = Plane stress, 6 = Plane strain) The stress intensity factors are being modified for a non-uniform stress field as follows: C Stress Beta Correction --------------------------------------- 0.0050000 1.0000 1.010000 0.1000000 1.0000 1.012000 0.2000000 1.0000 1.040000 0.3000000 1.0000 1.060000 0.4000000 1.0000 1.070000 0.6000000 1.0000 1.100000 0.7000000 1.0000 1.130000 0.8140000 1.0000 1.190000 No K-Solution Filters The Forman-Newman-de Koning- Henriksen (NASGRO) crack growth relation is being used For Reff < 0.0, Delta K = Kmax
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A5
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Material: 1000-9000 series aluminum, 2024-T3 Al, [ Clad; plt & sht; L-T ] Plane strain fracture toughness: 33 Plane stress fracture toughness: 66 Effective fracture toughness for surface/elliptically shaped crack: 46 Fit parameters (KC versus Thickness Equation): Ak= 1, Bk=1 Yield stress: 53 Lower 'R' value boundary: -0.3 Upper 'R' value boundary: 0.7 Exponents in NASGRO Equation: n=3.284, p=0.5, q=1 Paris crack growth rate constant: 8.29e-009 Threshold stress intensity factor range at R = 0: 2.9 Threshold coefficient: 1.5 Plane stress/strain constraint factor: 1.5 Ratio of the maximum applied stress to the flow stress: 0.3 Failure is based on the current load in the applied spectrum Vroman integration at 5% crack length **Spectrum Information Constant amplitude loading Spectrum multiplication factor: 8.909 SPL: 0 The spectrum will be repeated up to 999999 times Total Cycles: 100 Levels: 1 Subspectra: 1 Max Value: 1 Min Value: 0 No Spectrum Filters Critical Crack Length is Based on the Maximum Spectrum Stress Critical crack size in 'C' direction=9.15333, Stress State=2 (Based on Kmax criteria) Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.005 3.2783 3.2783 0.0000 0.0000 3.6605e+000 6.5711e-008 Max stress = 8.909000 R = 0.00 0 Cycles Constant amp.: 1 Pass: 1 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.025027 2.1701 2.1701 0.0000 0.0000 5.4210e+000 3.0813e-007
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A6
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Max stress = 8.909000 R = 0.00 108000 Cycles Constant amp.: 1081 Pass: 1081 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.045033 1.6688 1.6688 0.0000 0.0000 5.5922e+000 3.4557e-007 Max stress = 8.909000 R = 0.00 167400 Cycles Constant amp.: 1675 Pass: 1675 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.065068 1.4052 1.4052 0.0000 0.0000 5.6600e+000 3.6123e-007 Max stress = 8.909000 R = 0.00 224400 Cycles Constant amp.: 2245 Pass: 2245 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.085097 1.2121 1.2121 0.0000 0.0000 5.5835e+000 3.4209e-007 Max stress = 8.909000 R = 0.00 282100 Cycles Constant amp.: 2822 Pass: 2822 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.10511 1.1047 1.1047 0.0000 0.0000 5.6553e+000 3.5927e-007 Max stress = 8.909000 R = 0.00 339100 Cycles Constant amp.: 3392 Pass: 3392 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.12514 1.0161 1.0161 0.0000 0.0000 5.6759e+000 3.6419e-007 Max stress = 8.909000 R = 0.00 394300 Cycles Constant amp.: 3944 Pass: 3944 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.14515 0.9606 0.9606 0.0000 0.0000 5.7794e+000 3.9051e-007 Max stress = 8.909000 R = 0.00 446300 Cycles Constant amp.: 4464 Pass: 4464 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A7
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
C 0.16517 0.9296 0.9296 0.0000 0.0000 5.9654e+000 4.4125e-007 Max stress = 8.909000 R = 0.00 494600 Cycles Constant amp.: 4947 Pass: 4947 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.18519 0.8874 0.8874 0.0000 0.0000 6.0301e+000 4.5984e-007 Max stress = 8.909000 R = 0.00 539200 Cycles Constant amp.: 5393 Pass: 5393 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.20523 0.8620 0.8620 0.0000 0.0000 6.1660e+000 5.0080e-007 Max stress = 8.909000 R = 0.00 580400 Cycles Constant amp.: 5805 Pass: 5805 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.22524 0.8375 0.8375 0.0000 0.0000 6.2764e+000 5.3588e-007 Max stress = 8.909000 R = 0.00 618500 Cycles Constant amp.: 6186 Pass: 6186 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.24526 0.8264 0.8264 0.0000 0.0000 6.4624e+000 5.9884e-007 Max stress = 8.909000 R = 0.00 653900 Cycles Constant amp.: 6540 Pass: 6540 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.26526 0.8060 0.8060 0.0000 0.0000 6.5552e+000 6.3205e-007 Max stress = 8.909000 R = 0.00 686900 Cycles Constant amp.: 6870 Pass: 6870 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.28526 0.7875 0.7875 0.0000 0.0000 6.6417e+000 6.6417e-007 Max stress = 8.909000 R = 0.00 717400 Cycles Constant amp.: 7175 Pass: 7175
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A8
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.30533 0.7789 0.7789 0.0000 0.0000 6.7967e+000 7.2456e-007 Max stress = 8.909000 R = 0.00 746100 Cycles Constant amp.: 7462 Pass: 7462 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.32538 0.7700 0.7700 0.0000 0.0000 6.9355e+000 7.8182e-007 Max stress = 8.909000 R = 0.00 772800 Cycles Constant amp.: 7729 Pass: 7729 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.34539 0.7613 0.7613 0.0000 0.0000 7.0653e+000 8.3815e-007 Max stress = 8.909000 R = 0.00 797800 Cycles Constant amp.: 7979 Pass: 7979 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.36547 0.7454 0.7454 0.0000 0.0000 7.1153e+000 8.6060e-007 Max stress = 8.909000 R = 0.00 821500 Cycles Constant amp.: 8216 Pass: 8216 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.38551 0.7380 0.7380 0.0000 0.0000 7.2359e+000 9.1646e-007 Max stress = 8.909000 R = 0.00 843800 Cycles Constant amp.: 8439 Pass: 8439 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.40553 0.7311 0.7311 0.0000 0.0000 7.3517e+000 9.7246e-007 Max stress = 8.909000 R = 0.00 864800 Cycles Constant amp.: 8649 Pass: 8649 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.42554 0.7252 0.7252 0.0000 0.0000 7.4699e+000 1.0320e-006 Max stress = 8.909000 R = 0.00
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A9
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
884600 Cycles Constant amp.: 8847 Pass: 8847 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.44559 0.7199 0.7199 0.0000 0.0000 7.5886e+000 1.0945e-006 Max stress = 8.909000 R = 0.00 903300 Cycles Constant amp.: 9034 Pass: 9034 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.46563 0.7151 0.7151 0.0000 0.0000 7.7048e+000 1.1581e-006 Max stress = 8.909000 R = 0.00 920900 Cycles Constant amp.: 9210 Pass: 9210 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.48574 0.7151 0.7151 0.0000 0.0000 7.8694e+000 1.2527e-006 Max stress = 8.909000 R = 0.00 937600 Cycles Constant amp.: 9377 Pass: 9377 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.50586 0.7105 0.7105 0.0000 0.0000 7.9799e+000 1.3191e-006 Max stress = 8.909000 R = 0.00 953400 Cycles Constant amp.: 9535 Pass: 9535 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.52593 0.7063 0.7063 0.0000 0.0000 8.0886e+000 1.3870e-006 Max stress = 8.909000 R = 0.00 968300 Cycles Constant amp.: 9684 Pass: 9684 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.54602 0.7028 0.7028 0.0000 0.0000 8.2002e+000 1.4590e-006 Max stress = 8.909000 R = 0.00 982400 Cycles Constant amp.: 9825 Pass: 9825 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.56606 0.6996 0.6996 0.0000 0.0000 8.3111e+000 1.5334e-006
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A10
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Max stress = 8.909000 R = 0.00 995700 Cycles Constant amp.: 9958 Pass: 9958 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.58617 0.6996 0.6996 0.0000 0.0000 8.4574e+000 1.6354e-006 Max stress = 8.909000 R = 0.00 1008400 Cycles Constant amp.: 10085 Pass: 10085 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.60621 0.6967 0.6967 0.0000 0.0000 8.5655e+000 1.7139e-006 Max stress = 8.909000 R = 0.00 1020400 Cycles Constant amp.: 10205 Pass: 10205 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.62633 0.6963 0.6963 0.0000 0.0000 8.7019e+000 1.8166e-006 Max stress = 8.909000 R = 0.00 1031800 Cycles Constant amp.: 10319 Pass: 10319 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.64634 0.6963 0.6963 0.0000 0.0000 8.8397e+000 1.9249e-006 Max stress = 8.909000 R = 0.00 1042500 Cycles Constant amp.: 10426 Pass: 10426 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.66637 0.6970 0.6970 0.0000 0.0000 8.9849e+000 2.0439e-006 Max stress = 8.909000 R = 0.00 1052600 Cycles Constant amp.: 10527 Pass: 10527 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.68654 0.6970 0.6970 0.0000 0.0000 9.1198e+000 2.1590e-006 Max stress = 8.909000 R = 0.00 1062200 Cycles Constant amp.: 10623 Pass: 10623 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A11
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
C 0.70662 0.6983 0.6983 0.0000 0.0000 9.2695e+000 2.2922e-006 Max stress = 8.909000 R = 0.00 1071200 Cycles Constant amp.: 10713 Pass: 10713 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.72673 0.7031 0.7031 0.0000 0.0000 9.4643e+000 2.4742e-006 Max stress = 8.909000 R = 0.00 1079700 Cycles Constant amp.: 10798 Pass: 10798 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.74676 0.7031 0.7031 0.0000 0.0000 9.5939e+000 2.6009e-006 Max stress = 8.909000 R = 0.00 1087600 Cycles Constant amp.: 10877 Pass: 10877 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.7668 0.7103 0.7103 0.0000 0.0000 9.8211e+000 2.8342e-006 Max stress = 8.909000 R = 0.00 1095000 Cycles Constant amp.: 10951 Pass: 10951 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.78682 0.7103 0.7103 0.0000 0.0000 9.9485e+000 2.9714e-006 Max stress = 8.909000 R = 0.00 1101900 Cycles Constant amp.: 11020 Pass: 11020 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.80701 0.7181 0.7181 0.0000 0.0000 1.0186e+001 3.2400e-006 Max stress = 8.909000 R = 0.00 1108400 Cycles Constant amp.: 11085 Pass: 11085 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.8142 0.7181 0.7181 0.0000 0.0000 1.0231e+001 3.2930e-006 Max stress = 8.909000 R = 0.00 1110600 Cycles Constant amp.: 11107 Pass: 11107
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A12
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Stress State in 'C' direction (PSC): 6 Crack length exceeded stop value - run time : 0 hour(s) 0 minute(s) 0 second(s)
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A13
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
TCAS ANTENNA
CRACK GROWTH PHASEII
AFGROW 5.1.6.17 **English Units [ Length(in), Stress(Ksi), Temperature(F) ] Crack Growth Model and Spectrum Information Title: 737 TCAS Antenna Stage II Load: Axial Stress Fraction: 1, Bending Stress Fraction: 0, Bearing Stress Fraction: 0 Crack Model: 2010 - Internal Through Crack - Standard Solution Initial surface crack length (c): 0.7300 Thickness : 0.080 Width : 40.000 Young's Modulus =10600 Poisson's Ratio =0.33 Coeff. of Thermal Expan. =1.29e-005 No crack growth retardation is being considered Determine Stress State automatically (2 = Plane stress, 6 = Plane strain) No K-Solution Filters The Forman-Newman-de Koning- Henriksen (NASGRO) crack growth relation is being used For Reff < 0.0, Delta K = Kmax Material: 1000-9000 series aluminum, 2024-T3 Al, [ Clad; plt & sht; L-T ] Plane strain fracture toughness: 33 Plane stress fracture toughness: 66 Effective fracture toughness for surface/elliptically shaped crack: 46 Fit parameters (KC versus Thickness Equation): Ak= 1, Bk=1 Yield stress: 53 Lower 'R' value boundary: -0.3 Upper 'R' value boundary: 0.7 Exponents in NASGRO Equation: n=3.284, p=0.5, q=1 Paris crack growth rate constant: 8.29e-009 Threshold stress intensity factor range at R = 0: 2.9 Threshold coefficient: 1.5 Plane stress/strain constraint factor: 1.5
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A14
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Ratio of the maximum applied stress to the flow stress: 0.3 Failure is based on the current load in the applied spectrum Vroman integration at 5% crack length **Spectrum Information Constant amplitude loading Spectrum multiplication factor: 8.909 SPL: 0 The spectrum will be repeated up to 999999 times Total Cycles: 100 Levels: 1 Subspectra: 1 Max Value: 1 Min Value: 0 No Spectrum Filters Critical Crack Length is Based on the Maximum Spectrum Stress Critical crack size in 'C' direction=11.1898, Stress State=2 (Based on Kmax criteria) Critical crack size in 'C' direction=15.9137, Stress State=2 (Based on Net Section Yield criteria) Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.73 1.0008 1.0008 0.0000 0.0000 1.3502e+001 9.1086e-006 Max stress = 8.909000 R = 0.00 0 Cycles Constant amp.: 1 Pass: 1 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.78031 1.0009 1.0009 0.0000 0.0000 1.3961e+001 1.0300e-005 Max stress = 8.909000 R = 0.00 5200 Cycles Constant amp.: 53 Pass: 53 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.83043 1.0010 1.0010 0.0000 0.0000 1.4404e+001 1.1557e-005 Max stress = 8.909000 R = 0.00 9800 Cycles Constant amp.: 99 Pass: 99 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A15
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
C 0.88168 1.0011 1.0011 0.0000 0.0000 1.4843e+001 1.2913e-005 Max stress = 8.909000 R = 0.00 14000 Cycles Constant amp.: 141 Pass: 141 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.93192 1.0012 1.0012 0.0000 0.0000 1.5262e+001 1.4313e-005 Max stress = 8.909000 R = 0.00 17700 Cycles Constant amp.: 178 Pass: 178 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.983 1.0014 1.0014 0.0000 0.0000 1.5678e+001 1.5816e-005 Max stress = 8.909000 R = 0.00 21100 Cycles Constant amp.: 212 Pass: 212 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.0343 1.0016 1.0016 0.0000 0.0000 1.6085e+001 1.7393e-005 Max stress = 8.909000 R = 0.00 24200 Cycles Constant amp.: 243 Pass: 243 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.0852 1.0017 1.0017 0.0000 0.0000 1.6478e+001 1.9029e-005 Max stress = 8.909000 R = 0.00 27000 Cycles Constant amp.: 271 Pass: 271 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.1367 1.0017 1.0017 0.0000 0.0000 1.6865e+001 2.0750e-005 Max stress = 8.909000 R = 0.00 29600 Cycles Constant amp.: 297 Pass: 297 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.1886 1.0019 1.0019 0.0000 0.0000 1.7249e+001 2.2569e-005 Max stress = 8.909000 R = 0.00 32000 Cycles Constant amp.: 321 Pass: 321
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A16
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.2402 1.0021 1.0021 0.0000 0.0000 1.7623e+001 2.4457e-005 Max stress = 8.909000 R = 0.00 34200 Cycles Constant amp.: 343 Pass: 343 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.2909 1.0024 1.0024 0.0000 0.0000 1.7984e+001 2.6389e-005 Max stress = 8.909000 R = 0.00 36200 Cycles Constant amp.: 363 Pass: 363 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.3429 1.0026 1.0026 0.0000 0.0000 1.8346e+001 2.8447e-005 Max stress = 8.909000 R = 0.00 38100 Cycles Constant amp.: 382 Pass: 382 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.3959 1.0029 1.0029 0.0000 0.0000 1.8710e+001 3.0630e-005 Max stress = 8.909000 R = 0.00 39900 Cycles Constant amp.: 400 Pass: 400 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.4465 1.0029 1.0029 0.0000 0.0000 1.9046e+001 3.2760e-005 Max stress = 8.909000 R = 0.00 41500 Cycles Constant amp.: 416 Pass: 416 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.4972 1.0032 1.0032 0.0000 0.0000 1.9383e+001 3.5006e-005 Max stress = 8.909000 R = 0.00 43000 Cycles Constant amp.: 431 Pass: 431 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.5476 1.0035 1.0035 0.0000 0.0000 1.9713e+001 3.7325e-005 Max stress = 8.909000 R = 0.00
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A17
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
44400 Cycles Constant amp.: 445 Pass: 445 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.6015 1.0035 1.0035 0.0000 0.0000 2.0053e+001 3.9833e-005 Max stress = 8.909000 R = 0.00 45800 Cycles Constant amp.: 459 Pass: 459 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.6549 1.0039 1.0039 0.0000 0.0000 2.0392e+001 4.2462e-005 Max stress = 8.909000 R = 0.00 47100 Cycles Constant amp.: 472 Pass: 472 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.7072 1.0043 1.0043 0.0000 0.0000 2.0721e+001 4.5138e-005 Max stress = 8.909000 R = 0.00 48300 Cycles Constant amp.: 484 Pass: 484 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.7582 1.0043 1.0043 0.0000 0.0000 2.1028e+001 4.7752e-005 Max stress = 8.909000 R = 0.00 49400 Cycles Constant amp.: 495 Pass: 495 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.8121 1.0048 1.0048 0.0000 0.0000 2.1358e+001 5.0695e-005 Max stress = 8.909000 R = 0.00 50500 Cycles Constant amp.: 506 Pass: 506 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.8641 1.0048 1.0048 0.0000 0.0000 2.1662e+001 5.3528e-005 Max stress = 8.909000 R = 0.00 51500 Cycles Constant amp.: 516 Pass: 516 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.9191 1.0053 1.0053 0.0000 0.0000 2.1990e+001 5.6725e-005
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A18
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Max stress = 8.909000 R = 0.00 52500 Cycles Constant amp.: 526 Pass: 526 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.9713 1.0053 1.0053 0.0000 0.0000 2.2288e+001 5.9749e-005 Max stress = 8.909000 R = 0.00 53400 Cycles Constant amp.: 535 Pass: 535 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.0265 1.0058 1.0058 0.0000 0.0000 2.2610e+001 6.3169e-005 Max stress = 8.909000 R = 0.00 54300 Cycles Constant amp.: 544 Pass: 544 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.0781 1.0064 1.0064 0.0000 0.0000 2.2910e+001 6.6491e-005 Max stress = 8.909000 R = 0.00 55100 Cycles Constant amp.: 552 Pass: 552 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.1325 1.0064 1.0064 0.0000 0.0000 2.3208e+001 6.9922e-005 Max stress = 8.909000 R = 0.00 55900 Cycles Constant amp.: 560 Pass: 560 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.1897 1.0071 1.0071 0.0000 0.0000 2.3533e+001 7.3826e-005 Max stress = 8.909000 R = 0.00 56700 Cycles Constant amp.: 568 Pass: 568 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.2424 1.0071 1.0071 0.0000 0.0000 2.3815e+001 7.7346e-005 Max stress = 8.909000 R = 0.00 57400 Cycles Constant amp.: 575 Pass: 575 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A19
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
C 2.2977 1.0079 1.0079 0.0000 0.0000 2.4125e+001 8.1380e-005 Max stress = 8.909000 R = 0.00 58100 Cycles Constant amp.: 582 Pass: 582 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.3559 1.0079 1.0079 0.0000 0.0000 2.4429e+001 8.5485e-005 Max stress = 8.909000 R = 0.00 58800 Cycles Constant amp.: 589 Pass: 589 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.4081 1.0079 1.0079 0.0000 0.0000 2.4698e+001 8.9265e-005 Max stress = 8.909000 R = 0.00 59400 Cycles Constant amp.: 595 Pass: 595 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.4628 1.0087 1.0087 0.0000 0.0000 2.4998e+001 9.3635e-005 Max stress = 8.909000 R = 0.00 60000 Cycles Constant amp.: 601 Pass: 601 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.5201 1.0087 1.0087 0.0000 0.0000 2.5287e+001 9.8003e-005 Max stress = 8.909000 R = 0.00 60600 Cycles Constant amp.: 607 Pass: 607 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.5802 1.0097 1.0097 0.0000 0.0000 2.5610e+001 1.0308e-004 Max stress = 8.909000 R = 0.00 61200 Cycles Constant amp.: 613 Pass: 613 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.6326 1.0097 1.0097 0.0000 0.0000 2.5869e+001 1.0730e-004 Max stress = 8.909000 R = 0.00 61700 Cycles Constant amp.: 618 Pass: 618
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A20
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.6871 1.0108 1.0108 0.0000 0.0000 2.6163e+001 1.1228e-004 Max stress = 8.909000 R = 0.00 62200 Cycles Constant amp.: 623 Pass: 623 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.7442 1.0108 1.0108 0.0000 0.0000 2.6440e+001 1.1711e-004 Max stress = 8.909000 R = 0.00 62700 Cycles Constant amp.: 628 Pass: 628 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.8038 1.0108 1.0108 0.0000 0.0000 2.6725e+001 1.2229e-004 Max stress = 8.909000 R = 0.00 63200 Cycles Constant amp.: 633 Pass: 633 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.8663 1.0119 1.0119 0.0000 0.0000 2.7053e+001 1.2845e-004 Max stress = 8.909000 R = 0.00 63700 Cycles Constant amp.: 638 Pass: 638 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.9184 1.0119 1.0119 0.0000 0.0000 2.7298e+001 1.3321e-004 Max stress = 8.909000 R = 0.00 64100 Cycles Constant amp.: 642 Pass: 642 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.9725 1.0132 1.0132 0.0000 0.0000 2.7584e+001 1.3898e-004 Max stress = 8.909000 R = 0.00 64500 Cycles Constant amp.: 646 Pass: 646 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.0289 1.0132 1.0132 0.0000 0.0000 2.7844e+001 1.4439e-004 Max stress = 8.909000 R = 0.00
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A21
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
64900 Cycles Constant amp.: 650 Pass: 650 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.0875 1.0132 1.0132 0.0000 0.0000 2.8112e+001 1.5015e-004 Max stress = 8.909000 R = 0.00 65300 Cycles Constant amp.: 654 Pass: 654 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.1486 1.0147 1.0147 0.0000 0.0000 2.8431e+001 1.5725e-004 Max stress = 8.909000 R = 0.00 65700 Cycles Constant amp.: 658 Pass: 658 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.2125 1.0147 1.0147 0.0000 0.0000 2.8718e+001 1.6387e-004 Max stress = 8.909000 R = 0.00 66100 Cycles Constant amp.: 662 Pass: 662 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.2791 1.0163 1.0163 0.0000 0.0000 2.9060e+001 1.7206e-004 Max stress = 8.909000 R = 0.00 66500 Cycles Constant amp.: 666 Pass: 666 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.3313 1.0163 1.0163 0.0000 0.0000 2.9290e+001 1.7777e-004 Max stress = 8.909000 R = 0.00 66800 Cycles Constant amp.: 669 Pass: 669 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.3852 1.0163 1.0163 0.0000 0.0000 2.9526e+001 1.8379e-004 Max stress = 8.909000 R = 0.00 67100 Cycles Constant amp.: 672 Pass: 672 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.441 1.0163 1.0163 0.0000 0.0000 2.9768e+001 1.9014e-004
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A22
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Max stress = 8.909000 R = 0.00 67400 Cycles Constant amp.: 675 Pass: 675 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.499 1.0182 1.0182 0.0000 0.0000 3.0074e+001 1.9842e-004 Max stress = 8.909000 R = 0.00 67700 Cycles Constant amp.: 678 Pass: 678 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.5592 1.0182 1.0182 0.0000 0.0000 3.0332e+001 2.0564e-004 Max stress = 8.909000 R = 0.00 68000 Cycles Constant amp.: 681 Pass: 681 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.6217 1.0182 1.0182 0.0000 0.0000 3.0597e+001 2.1329e-004 Max stress = 8.909000 R = 0.00 68300 Cycles Constant amp.: 684 Pass: 684 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.6868 1.0202 1.0202 0.0000 0.0000 3.0932e+001 2.2332e-004 Max stress = 8.909000 R = 0.00 68600 Cycles Constant amp.: 687 Pass: 687 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.7547 1.0202 1.0202 0.0000 0.0000 3.1216e+001 2.3211e-004 Max stress = 8.909000 R = 0.00 68900 Cycles Constant amp.: 690 Pass: 690 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.8253 1.0223 1.0223 0.0000 0.0000 3.1574e+001 2.4362e-004 Max stress = 8.909000 R = 0.00 69200 Cycles Constant amp.: 693 Pass: 693 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A23
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
C 3.8993 1.0223 1.0223 0.0000 0.0000 3.1878e+001 2.5380e-004 Max stress = 8.909000 R = 0.00 69500 Cycles Constant amp.: 696 Pass: 696 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.9505 1.0223 1.0223 0.0000 0.0000 3.2086e+001 2.6097e-004 Max stress = 8.909000 R = 0.00 69700 Cycles Constant amp.: 698 Pass: 698 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.003 1.0223 1.0223 0.0000 0.0000 3.2299e+001 2.6848e-004 Max stress = 8.909000 R = 0.00 69900 Cycles Constant amp.: 700 Pass: 700 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.0574 1.0249 1.0249 0.0000 0.0000 3.2598e+001 2.7936e-004 Max stress = 8.909000 R = 0.00 70100 Cycles Constant amp.: 702 Pass: 702 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.1137 1.0249 1.0249 0.0000 0.0000 3.2824e+001 2.8781e-004 Max stress = 8.909000 R = 0.00 70300 Cycles Constant amp.: 704 Pass: 704 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.1717 1.0249 1.0249 0.0000 0.0000 3.3054e+001 2.9667e-004 Max stress = 8.909000 R = 0.00 70500 Cycles Constant amp.: 706 Pass: 706 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.2315 1.0275 1.0275 0.0000 0.0000 3.3376e+001 3.0946e-004 Max stress = 8.909000 R = 0.00 70700 Cycles Constant amp.: 708 Pass: 708
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A24
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.2939 1.0275 1.0275 0.0000 0.0000 3.3621e+001 3.1951e-004 Max stress = 8.909000 R = 0.00 70900 Cycles Constant amp.: 710 Pass: 710 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.3583 1.0275 1.0275 0.0000 0.0000 3.3873e+001 3.3012e-004 Max stress = 8.909000 R = 0.00 71100 Cycles Constant amp.: 712 Pass: 712 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.4249 1.0275 1.0275 0.0000 0.0000 3.4130e+001 3.4132e-004 Max stress = 8.909000 R = 0.00 71300 Cycles Constant amp.: 714 Pass: 714 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.4942 1.0307 1.0307 0.0000 0.0000 3.4503e+001 3.5809e-004 Max stress = 8.909000 R = 0.00 71500 Cycles Constant amp.: 716 Pass: 716 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.5665 1.0307 1.0307 0.0000 0.0000 3.4779e+001 3.7100e-004 Max stress = 8.909000 R = 0.00 71700 Cycles Constant amp.: 718 Pass: 718 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.6413 1.0307 1.0307 0.0000 0.0000 3.5063e+001 3.8471e-004 Max stress = 8.909000 R = 0.00 71900 Cycles Constant amp.: 720 Pass: 720 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.719 1.0345 1.0345 0.0000 0.0000 3.5487e+001 4.0604e-004 Max stress = 8.909000 R = 0.00
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A25
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
72100 Cycles Constant amp.: 722 Pass: 722 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.801 1.0345 1.0345 0.0000 0.0000 3.5794e+001 4.2213e-004 Max stress = 8.909000 R = 0.00 72300 Cycles Constant amp.: 724 Pass: 724 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.8863 1.0345 1.0345 0.0000 0.0000 3.6111e+001 4.3931e-004 Max stress = 8.909000 R = 0.00 72500 Cycles Constant amp.: 726 Pass: 726 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.975 1.0386 1.0386 0.0000 0.0000 3.6580e+001 4.6597e-004 Max stress = 8.909000 R = 0.00 72700 Cycles Constant amp.: 728 Pass: 728 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.0692 1.0386 1.0386 0.0000 0.0000 3.6925e+001 4.8649e-004 Max stress = 8.909000 R = 0.00 72900 Cycles Constant amp.: 730 Pass: 730 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.1676 1.0386 1.0386 0.0000 0.0000 3.7281e+001 5.0858e-004 Max stress = 8.909000 R = 0.00 73100 Cycles Constant amp.: 732 Pass: 732 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.2185 1.0386 1.0386 0.0000 0.0000 3.7464e+001 5.2027e-004 Max stress = 8.909000 R = 0.00 73200 Cycles Constant amp.: 733 Pass: 733 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.2705 1.0436 1.0436 0.0000 0.0000 3.7832e+001 5.4452e-004
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A26
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Max stress = 8.909000 R = 0.00 73300 Cycles Constant amp.: 734 Pass: 734 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.3249 1.0436 1.0436 0.0000 0.0000 3.8027e+001 5.5780e-004 Max stress = 8.909000 R = 0.00 73400 Cycles Constant amp.: 735 Pass: 735 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.3807 1.0436 1.0436 0.0000 0.0000 3.8226e+001 5.7164e-004 Max stress = 8.909000 R = 0.00 73500 Cycles Constant amp.: 736 Pass: 736 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.4379 1.0436 1.0436 0.0000 0.0000 3.8428e+001 5.8608e-004 Max stress = 8.909000 R = 0.00 73600 Cycles Constant amp.: 737 Pass: 737 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.4965 1.0436 1.0436 0.0000 0.0000 3.8635e+001 6.0116e-004 Max stress = 8.909000 R = 0.00 73700 Cycles Constant amp.: 738 Pass: 738 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.5566 1.0488 1.0488 0.0000 0.0000 3.9039e+001 6.3171e-004 Max stress = 8.909000 R = 0.00 73800 Cycles Constant amp.: 739 Pass: 739 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.6198 1.0488 1.0488 0.0000 0.0000 3.9260e+001 6.4906e-004 Max stress = 8.909000 R = 0.00 73900 Cycles Constant amp.: 740 Pass: 740 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A27
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
C 5.6847 1.0488 1.0488 0.0000 0.0000 3.9486e+001 6.6725e-004 Max stress = 8.909000 R = 0.00 74000 Cycles Constant amp.: 741 Pass: 741 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.7514 1.0488 1.0488 0.0000 0.0000 3.9717e+001 6.8635e-004 Max stress = 8.909000 R = 0.00 74100 Cycles Constant amp.: 742 Pass: 742 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.82 1.0488 1.0488 0.0000 0.0000 3.9953e+001 7.0642e-004 Max stress = 8.909000 R = 0.00 74200 Cycles Constant amp.: 743 Pass: 743 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.8907 1.0553 1.0553 0.0000 0.0000 4.0445e+001 7.4995e-004 Max stress = 8.909000 R = 0.00 74300 Cycles Constant amp.: 744 Pass: 744 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.9657 1.0553 1.0553 0.0000 0.0000 4.0701e+001 7.7372e-004 Max stress = 8.909000 R = 0.00 74400 Cycles Constant amp.: 745 Pass: 745 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 6.0431 1.0553 1.0553 0.0000 0.0000 4.0964e+001 7.9884e-004 Max stress = 8.909000 R = 0.00 74500 Cycles Constant amp.: 746 Pass: 746 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 6.1229 1.0553 1.0553 0.0000 0.0000 4.1234e+001 8.2543e-004 Max stress = 8.909000 R = 0.00 74600 Cycles Constant amp.: 747 Pass: 747
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A28
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 6.2055 1.0619 1.0619 0.0000 0.0000 4.1770e+001 8.8087e-004 Max stress = 8.909000 R = 0.00 74700 Cycles Constant amp.: 748 Pass: 748 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 6.2936 1.0619 1.0619 0.0000 0.0000 4.2066e+001 9.1297e-004 Max stress = 8.909000 R = 0.00 74800 Cycles Constant amp.: 749 Pass: 749 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 6.3849 1.0619 1.0619 0.0000 0.0000 4.2370e+001 9.4721e-004 Max stress = 8.909000 R = 0.00 74900 Cycles Constant amp.: 750 Pass: 750 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 6.4796 1.0619 1.0619 0.0000 0.0000 4.2683e+001 9.8381e-004 Max stress = 8.909000 R = 0.00 75000 Cycles Constant amp.: 751 Pass: 751 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 6.578 1.0703 1.0703 0.0000 0.0000 4.3346e+001 1.0661e-003 Max stress = 8.909000 R = 0.00 75100 Cycles Constant amp.: 752 Pass: 752 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 6.6846 1.0703 1.0703 0.0000 0.0000 4.3696e+001 1.1123e-003 Max stress = 8.909000 R = 0.00 75200 Cycles Constant amp.: 753 Pass: 753 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 6.7958 1.0703 1.0703 0.0000 0.0000 4.4058e+001 1.1622e-003 Max stress = 8.909000 R = 0.00
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A29
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
75300 Cycles Constant amp.: 754 Pass: 754 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 6.912 1.0784 1.0784 0.0000 0.0000 4.4770e+001 1.2673e-003 Max stress = 8.909000 R = 0.00 75400 Cycles Constant amp.: 755 Pass: 755 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 7.0387 1.0784 1.0784 0.0000 0.0000 4.5178e+001 1.3319e-003 Max stress = 8.909000 R = 0.00 75500 Cycles Constant amp.: 756 Pass: 756 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 7.1719 1.0784 1.0784 0.0000 0.0000 4.5604e+001 1.4030e-003 Max stress = 8.909000 R = 0.00 75600 Cycles Constant amp.: 757 Pass: 757 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 7.3122 1.0889 1.0889 0.0000 0.0000 4.6496e+001 1.5653e-003 Max stress = 8.909000 R = 0.00 75700 Cycles Constant amp.: 758 Pass: 758 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 7.4688 1.0889 1.0889 0.0000 0.0000 4.6991e+001 1.6640e-003 Max stress = 8.909000 R = 0.00 75800 Cycles Constant amp.: 759 Pass: 759 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 7.6352 1.0889 1.0889 0.0000 0.0000 4.7511e+001 1.7752e-003 Max stress = 8.909000 R = 0.00 75900 Cycles Constant amp.: 760 Pass: 760 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 7.8127 1.1033 1.1033 0.0000 0.0000 4.8696e+001 2.0597e-003
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A30
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Max stress = 8.909000 R = 0.00 76000 Cycles Constant amp.: 761 Pass: 761 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 8.0187 1.1033 1.1033 0.0000 0.0000 4.9333e+001 2.2339e-003 Max stress = 8.909000 R = 0.00 76100 Cycles Constant amp.: 762 Pass: 762 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 8.242 1.1168 1.1168 0.0000 0.0000 5.0630e+001 2.6430e-003 Max stress = 8.909000 R = 0.00 76200 Cycles Constant amp.: 763 Pass: 763 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 8.5063 1.1168 1.1168 0.0000 0.0000 5.1435e+001 2.9413e-003 Max stress = 8.909000 R = 0.00 76300 Cycles Constant amp.: 764 Pass: 764 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 8.8005 1.1363 1.1363 0.0000 0.0000 5.3229e+001 3.7660e-003 Max stress = 8.909000 R = 0.00 76400 Cycles Constant amp.: 765 Pass: 765 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 9.1771 1.1363 1.1363 0.0000 0.0000 5.4356e+001 4.4349e-003 Max stress = 8.909000 R = 0.00 76500 Cycles Constant amp.: 766 Pass: 766 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 9.6206 1.1691 1.1691 0.0000 0.0000 5.7261e+001 7.0678e-003 Max stress = 8.909000 R = 0.00 76600 Cycles Constant amp.: 767 Pass: 767 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A31
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
C 10.108 1.1914 1.1914 0.0000 0.0000 5.9812e+001 1.1656e-002 Max stress = 8.909000 R = 0.00 76669 Cycles Constant amp.: 767 Pass: 767 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 10.47 1.1914 1.1914 0.0000 0.0000 6.0871e+001 1.5022e-002 Max stress = 8.909000 R = 0.00 76700 Cycles Constant amp.: 768 Pass: 768 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 10.995 1.2380 1.2380 0.0000 0.0000 6.4825e+001 9.5395e-002 Max stress = 8.909000 R = 0.00 76735 Cycles Constant amp.: 768 Pass: 768 *********Fracture based on ' Kmax' Criteria (current maximum stress) Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 11.568 1.2731 1.2731 0.0000 0.0000 6.8376e+001 1.0000e-001 Max stress = 8.909000 R = 0.00 76741 Cycles Constant amp.: 768 Pass: 768 Stress State in 'C' direction (PSC): 2 Fracture has occurred - run time : 0 hour(s) 0 minute(s) 1 second(s)
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A32
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
TRANSPONDER ANTENNA CRACK GROWTH PHASE I
AFGROW 5.1.6.17 **English Units [ Length(in), Stress(Ksi), Temperature(F) ] Crack Growth Model and Spectrum Information Title: 737 Transponder Antenna Stage I Load: Axial Stress Fraction: 0.737, Bending Stress Fraction: 0, Bearing Stress Fraction: 1.411 Crack Model: 2020 - Single Through Crack at Hole - Standard Solution Initial surface crack length (c): 0.0050 Thickness : 0.080 Width : 20.000 Hole Diameter: 0.156 Young's Modulus =10600 Poisson's Ratio =0.33 Coeff. of Thermal Expan. =1.29e-005 No crack growth retardation is being considered Determine Stress State automatically (2 = Plane stress, 6 = Plane strain) The stress intensity factors are being modified for a non-uniform stress field as follows: C Stress Beta Correction --------------------------------------- 0.0050000 1.0000 1.010000 0.1000000 1.0000 1.012000 0.2000000 1.0000 1.040000 0.3000000 1.0000 1.060000 0.4000000 1.0000 1.070000 0.6000000 1.0000 1.100000 0.7000000 1.0000 1.130000 0.8140000 1.0000 1.190000 No K-Solution Filters The Forman-Newman-de Koning- Henriksen (NASGRO) crack growth relation is being used For Reff < 0.0, Delta K = Kmax Material: 1000-9000 series aluminum, 2024-T3 Al, [ Clad; plt & sht; L-T ]
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A33
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Plane strain fracture toughness: 33 Plane stress fracture toughness: 66 Effective fracture toughness for surface/elliptically shaped crack: 46 Fit parameters (KC versus Thickness Equation): Ak= 1, Bk=1 Yield stress: 53 Lower 'R' value boundary: -0.3 Upper 'R' value boundary: 0.7 Exponents in NASGRO Equation: n=3.284, p=0.5, q=1 Paris crack growth rate constant: 8.29e-009 Threshold stress intensity factor range at R = 0: 2.9 Threshold coefficient: 1.5 Plane stress/strain constraint factor: 1.5 Ratio of the maximum applied stress to the flow stress: 0.3 Failure is based on the current load in the applied spectrum Vroman integration at 5% crack length **Spectrum Information Constant amplitude loading Spectrum multiplication factor: 9.315 SPL: 0 The spectrum will be repeated up to 999999 times Total Cycles: 100 Levels: 1 Subspectra: 1 Max Value: 1 Min Value: 0 No Spectrum Filters Critical Crack Length is Based on the Maximum Spectrum Stress Critical crack size in 'C' direction=9.07886, Stress State=2 (Based on Kmax criteria) Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.005 3.2783 3.2783 0.0000 0.0000 3.8273e+000 7.9968e-008 Max stress = 9.315000 R = 0.00 0 Cycles Constant amp.: 1 Pass: 1 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.025002 2.1667 2.1667 0.0000 0.0000 5.6564e+000 3.6358e-007 Max stress = 9.315000 R = 0.00 90100 Cycles Constant amp.: 902 Pass: 902
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A34
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.04502 1.6643 1.6643 0.0000 0.0000 5.8303e+000 4.0623e-007 Max stress = 9.315000 R = 0.00 140100 Cycles Constant amp.: 1402 Pass: 1402 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.065055 1.4013 1.4013 0.0000 0.0000 5.9009e+000 4.2452e-007 Max stress = 9.315000 R = 0.00 188100 Cycles Constant amp.: 1882 Pass: 1882 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.085091 1.2086 1.2086 0.0000 0.0000 5.8206e+000 4.0213e-007 Max stress = 9.315000 R = 0.00 236600 Cycles Constant amp.: 2367 Pass: 2367 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.10511 1.1015 1.1015 0.0000 0.0000 5.8960e+000 4.2229e-007 Max stress = 9.315000 R = 0.00 284600 Cycles Constant amp.: 2847 Pass: 2847 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.12515 1.0135 1.0135 0.0000 0.0000 5.9194e+000 4.2857e-007 Max stress = 9.315000 R = 0.00 331000 Cycles Constant amp.: 3311 Pass: 3311 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.14516 0.9586 0.9586 0.0000 0.0000 6.0298e+000 4.6001e-007 Max stress = 9.315000 R = 0.00 374800 Cycles Constant amp.: 3749 Pass: 3749 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.1652 0.9276 0.9276 0.0000 0.0000 6.2245e+000 5.1942e-007
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A35
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Max stress = 9.315000 R = 0.00 415600 Cycles Constant amp.: 4157 Pass: 4157 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.18521 0.8856 0.8856 0.0000 0.0000 6.2927e+000 5.4139e-007 Max stress = 9.315000 R = 0.00 453100 Cycles Constant amp.: 4532 Pass: 4532 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.20527 0.8603 0.8603 0.0000 0.0000 6.4351e+000 5.8942e-007 Max stress = 9.315000 R = 0.00 487900 Cycles Constant amp.: 4880 Pass: 4880 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.22532 0.8360 0.8360 0.0000 0.0000 6.5515e+000 6.3085e-007 Max stress = 9.315000 R = 0.00 520100 Cycles Constant amp.: 5202 Pass: 5202 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.24536 0.8250 0.8250 0.0000 0.0000 6.7467e+000 7.0482e-007 Max stress = 9.315000 R = 0.00 550100 Cycles Constant amp.: 5502 Pass: 5502 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.26542 0.8046 0.8046 0.0000 0.0000 6.8443e+000 7.4396e-007 Max stress = 9.315000 R = 0.00 578000 Cycles Constant amp.: 5781 Pass: 5781 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.28542 0.7952 0.7952 0.0000 0.0000 7.0145e+000 8.1588e-007 Max stress = 9.315000 R = 0.00 603800 Cycles Constant amp.: 6039 Pass: 6039 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A36
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
C 0.30548 0.7777 0.7777 0.0000 0.0000 7.0969e+000 8.5238e-007 Max stress = 9.315000 R = 0.00 628000 Cycles Constant amp.: 6281 Pass: 6281 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.32552 0.7687 0.7687 0.0000 0.0000 7.2413e+000 9.1913e-007 Max stress = 9.315000 R = 0.00 650600 Cycles Constant amp.: 6507 Pass: 6507 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.34555 0.7602 0.7602 0.0000 0.0000 7.3776e+000 9.8542e-007 Max stress = 9.315000 R = 0.00 671800 Cycles Constant amp.: 6719 Pass: 6719 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.36564 0.7520 0.7520 0.0000 0.0000 7.5073e+000 1.0516e-006 Max stress = 9.315000 R = 0.00 691800 Cycles Constant amp.: 6919 Pass: 6919 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.38573 0.7370 0.7370 0.0000 0.0000 7.5569e+000 1.0776e-006 Max stress = 9.315000 R = 0.00 710700 Cycles Constant amp.: 7108 Pass: 7108 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.40578 0.7302 0.7302 0.0000 0.0000 7.6794e+000 1.1441e-006 Max stress = 9.315000 R = 0.00 728500 Cycles Constant amp.: 7286 Pass: 7286 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.42583 0.7244 0.7244 0.0000 0.0000 7.8041e+000 1.2146e-006 Max stress = 9.315000 R = 0.00 745300 Cycles Constant amp.: 7454 Pass: 7454
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A37
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.44585 0.7191 0.7191 0.0000 0.0000 7.9281e+000 1.2877e-006 Max stress = 9.315000 R = 0.00 761100 Cycles Constant amp.: 7612 Pass: 7612 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.46596 0.7191 0.7191 0.0000 0.0000 8.1050e+000 1.3974e-006 Max stress = 9.315000 R = 0.00 776100 Cycles Constant amp.: 7762 Pass: 7762 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.48599 0.7143 0.7143 0.0000 0.0000 8.2217e+000 1.4733e-006 Max stress = 9.315000 R = 0.00 790200 Cycles Constant amp.: 7903 Pass: 7903 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.50615 0.7098 0.7098 0.0000 0.0000 8.3379e+000 1.5518e-006 Max stress = 9.315000 R = 0.00 803600 Cycles Constant amp.: 8037 Pass: 8037 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.52619 0.7058 0.7058 0.0000 0.0000 8.4525e+000 1.6320e-006 Max stress = 9.315000 R = 0.00 816200 Cycles Constant amp.: 8163 Pass: 8163 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.54621 0.7023 0.7023 0.0000 0.0000 8.5692e+000 1.7167e-006 Max stress = 9.315000 R = 0.00 828100 Cycles Constant amp.: 8282 Pass: 8282 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.56626 0.7023 0.7023 0.0000 0.0000 8.7250e+000 1.8346e-006 Max stress = 9.315000 R = 0.00
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A38
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
839400 Cycles Constant amp.: 8395 Pass: 8395 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.58643 0.6991 0.6991 0.0000 0.0000 8.8390e+000 1.9244e-006 Max stress = 9.315000 R = 0.00 850200 Cycles Constant amp.: 8503 Pass: 8503 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.60654 0.6963 0.6963 0.0000 0.0000 8.9530e+000 2.0173e-006 Max stress = 9.315000 R = 0.00 860400 Cycles Constant amp.: 8605 Pass: 8605 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.6267 0.6963 0.6963 0.0000 0.0000 9.1005e+000 2.1424e-006 Max stress = 9.315000 R = 0.00 870100 Cycles Constant amp.: 8702 Pass: 8702 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.64678 0.6964 0.6964 0.0000 0.0000 9.2467e+000 2.2717e-006 Max stress = 9.315000 R = 0.00 879200 Cycles Constant amp.: 8793 Pass: 8793 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.6669 0.6972 0.6972 0.0000 0.0000 9.4003e+000 2.4134e-006 Max stress = 9.315000 R = 0.00 887800 Cycles Constant amp.: 8879 Pass: 8879 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.68698 0.6972 0.6972 0.0000 0.0000 9.5408e+000 2.5485e-006 Max stress = 9.315000 R = 0.00 895900 Cycles Constant amp.: 8960 Pass: 8960 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.70723 0.6986 0.6986 0.0000 0.0000 9.6995e+000 2.7076e-006
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A39
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Max stress = 9.315000 R = 0.00 903600 Cycles Constant amp.: 9037 Pass: 9037 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.72752 0.7042 0.7042 0.0000 0.0000 9.9165e+000 2.9366e-006 Max stress = 9.315000 R = 0.00 910900 Cycles Constant amp.: 9110 Pass: 9110 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.74769 0.7042 0.7042 0.0000 0.0000 1.0053e+001 3.0875e-006 Max stress = 9.315000 R = 0.00 917600 Cycles Constant amp.: 9177 Pass: 9177 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.76775 0.7115 0.7115 0.0000 0.0000 1.0292e+001 3.3656e-006 Max stress = 9.315000 R = 0.00 923900 Cycles Constant amp.: 9240 Pass: 9240 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.78808 0.7115 0.7115 0.0000 0.0000 1.0428e+001 3.5307e-006 Max stress = 9.315000 R = 0.00 929800 Cycles Constant amp.: 9299 Pass: 9299 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.80819 0.7194 0.7194 0.0000 0.0000 1.0677e+001 3.8506e-006 Max stress = 9.315000 R = 0.00 935300 Cycles Constant amp.: 9354 Pass: 9354 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.81439 0.7194 0.7194 0.0000 0.0000 1.0718e+001 3.9049e-006 Max stress = 9.315000 R = 0.00 936900 Cycles Constant amp.: 9370 Pass: 9370 Stress State in 'C' direction (PSC): 5.93829
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A40
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Crack length exceeded stop value - run time : 0 hour(s) 0 minute(s) 1 second(s)
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A41
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
TRANSPONDER ANTENNA CRACK GROWTH PHASE II
AFGROW 5.1.6.17 **English Units [ Length(in), Stress(Ksi), Temperature(F) ] Crack Growth Model and Spectrum Information Title: 737 Transponder Antenna Stage II Load: Axial Stress Fraction: 1, Bending Stress Fraction: 0, Bearing Stress Fraction: 0 Crack Model: 2010 - Internal Through Crack - Standard Solution Initial surface crack length (c): 0.7350 Thickness : 0.080 Width : 40.000 Young's Modulus =10600 Poisson's Ratio =0.33 Coeff. of Thermal Expan. =1.29e-005 No crack growth retardation is being considered Determine Stress State automatically (2 = Plane stress, 6 = Plane strain) No K-Solution Filters The Forman-Newman-de Koning- Henriksen (NASGRO) crack growth relation is being used For Reff < 0.0, Delta K = Kmax Material: 1000-9000 series aluminum, 2024-T3 Al, [ Clad; plt & sht; L-T ] Plane strain fracture toughness: 33 Plane stress fracture toughness: 66 Effective fracture toughness for surface/elliptically shaped crack: 46 Fit parameters (KC versus Thickness Equation): Ak= 1, Bk=1 Yield stress: 53 Lower 'R' value boundary: -0.3 Upper 'R' value boundary: 0.7 Exponents in NASGRO Equation: n=3.284, p=0.5, q=1 Paris crack growth rate constant: 8.29e-009 Threshold stress intensity factor range at R = 0: 2.9 Threshold coefficient: 1.5 Plane stress/strain constraint factor: 1.5 Ratio of the maximum applied stress to the flow stress: 0.3
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A42
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Failure is based on the current load in the applied spectrum Vroman integration at 5% crack length **Spectrum Information Constant amplitude loading Spectrum multiplication factor: 9.315 SPL: 0 The spectrum will be repeated up to 999999 times Total Cycles: 100 Levels: 1 Subspectra: 1 Max Value: 1 Min Value: 0 No Spectrum Filters Critical Crack Length is Based on the Maximum Spectrum Stress Critical crack size in 'C' direction=10.7048, Stress State=2 (Based on Kmax criteria) Critical crack size in 'C' direction=15.7346, Stress State=2 (Based on Net Section Yield criteria) Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.735 1.0008 1.0008 0.0000 0.0000 1.4166e+001 1.0869e-005 Max stress = 9.315000 R = 0.00 0 Cycles Constant amp.: 1 Pass: 1 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.7858 1.0009 1.0009 0.0000 0.0000 1.4649e+001 1.2300e-005 Max stress = 9.315000 R = 0.00 4400 Cycles Constant amp.: 45 Pass: 45 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.83656 1.0010 1.0010 0.0000 0.0000 1.5116e+001 1.3813e-005 Max stress = 9.315000 R = 0.00 8300 Cycles Constant amp.: 84 Pass: 84 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A43
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
C 0.88756 1.0011 1.0011 0.0000 0.0000 1.5571e+001 1.5419e-005 Max stress = 9.315000 R = 0.00 11800 Cycles Constant amp.: 119 Pass: 119 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.9378 1.0012 1.0012 0.0000 0.0000 1.6008e+001 1.7085e-005 Max stress = 9.315000 R = 0.00 14900 Cycles Constant amp.: 150 Pass: 150 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.98795 1.0013 1.0013 0.0000 0.0000 1.6432e+001 1.8833e-005 Max stress = 9.315000 R = 0.00 17700 Cycles Constant amp.: 178 Pass: 178 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.0392 1.0015 1.0015 0.0000 0.0000 1.6856e+001 2.0706e-005 Max stress = 9.315000 R = 0.00 20300 Cycles Constant amp.: 204 Pass: 204 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.0912 1.0016 1.0016 0.0000 0.0000 1.7274e+001 2.2694e-005 Max stress = 9.315000 R = 0.00 22700 Cycles Constant amp.: 228 Pass: 228 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.1432 1.0018 1.0018 0.0000 0.0000 1.7685e+001 2.4780e-005 Max stress = 9.315000 R = 0.00 24900 Cycles Constant amp.: 250 Pass: 250 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.1948 1.0020 1.0020 0.0000 0.0000 1.8083e+001 2.6938e-005 Max stress = 9.315000 R = 0.00 26900 Cycles Constant amp.: 270 Pass: 270
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A44
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.2451 1.0022 1.0022 0.0000 0.0000 1.8463e+001 2.9135e-005 Max stress = 9.315000 R = 0.00 28700 Cycles Constant amp.: 288 Pass: 288 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.2965 1.0024 1.0024 0.0000 0.0000 1.8845e+001 3.1470e-005 Max stress = 9.315000 R = 0.00 30400 Cycles Constant amp.: 305 Pass: 305 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.3487 1.0027 1.0027 0.0000 0.0000 1.9225e+001 3.3939e-005 Max stress = 9.315000 R = 0.00 32000 Cycles Constant amp.: 321 Pass: 321 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.4013 1.0027 1.0027 0.0000 0.0000 1.9597e+001 3.6495e-005 Max stress = 9.315000 R = 0.00 33500 Cycles Constant amp.: 336 Pass: 336 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.4542 1.0029 1.0029 0.0000 0.0000 1.9968e+001 3.9196e-005 Max stress = 9.315000 R = 0.00 34900 Cycles Constant amp.: 350 Pass: 350 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.5068 1.0033 1.0033 0.0000 0.0000 2.0333e+001 4.1991e-005 Max stress = 9.315000 R = 0.00 36200 Cycles Constant amp.: 363 Pass: 363 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.5587 1.0036 1.0036 0.0000 0.0000 2.0687e+001 4.4856e-005 Max stress = 9.315000 R = 0.00
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A45
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
37400 Cycles Constant amp.: 375 Pass: 375 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.6094 1.0036 1.0036 0.0000 0.0000 2.1021e+001 4.7693e-005 Max stress = 9.315000 R = 0.00 38500 Cycles Constant amp.: 386 Pass: 386 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.6634 1.0040 1.0040 0.0000 0.0000 2.1379e+001 5.0888e-005 Max stress = 9.315000 R = 0.00 39600 Cycles Constant amp.: 397 Pass: 397 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.7157 1.0040 1.0040 0.0000 0.0000 2.1712e+001 5.4010e-005 Max stress = 9.315000 R = 0.00 40600 Cycles Constant amp.: 407 Pass: 407 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.7713 1.0044 1.0044 0.0000 0.0000 2.2071e+001 5.7530e-005 Max stress = 9.315000 R = 0.00 41600 Cycles Constant amp.: 417 Pass: 417 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.8244 1.0049 1.0049 0.0000 0.0000 2.2410e+001 6.1029e-005 Max stress = 9.315000 R = 0.00 42500 Cycles Constant amp.: 426 Pass: 426 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.8808 1.0049 1.0049 0.0000 0.0000 2.2754e+001 6.4742e-005 Max stress = 9.315000 R = 0.00 43400 Cycles Constant amp.: 435 Pass: 435 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.9339 1.0054 1.0054 0.0000 0.0000 2.3085e+001 6.8485e-005
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A46
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Max stress = 9.315000 R = 0.00 44200 Cycles Constant amp.: 443 Pass: 443 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 1.99 1.0054 1.0054 0.0000 0.0000 2.3417e+001 7.2417e-005 Max stress = 9.315000 R = 0.00 45000 Cycles Constant amp.: 451 Pass: 451 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.0419 1.0060 1.0060 0.0000 0.0000 2.3734e+001 7.6327e-005 Max stress = 9.315000 R = 0.00 45700 Cycles Constant amp.: 458 Pass: 458 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.0966 1.0060 1.0060 0.0000 0.0000 2.4050e+001 8.0384e-005 Max stress = 9.315000 R = 0.00 46400 Cycles Constant amp.: 465 Pass: 465 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.1542 1.0067 1.0067 0.0000 0.0000 2.4394e+001 8.5015e-005 Max stress = 9.315000 R = 0.00 47100 Cycles Constant amp.: 472 Pass: 472 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.2063 1.0067 1.0067 0.0000 0.0000 2.4687e+001 8.9113e-005 Max stress = 9.315000 R = 0.00 47700 Cycles Constant amp.: 478 Pass: 478 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.2609 1.0074 1.0074 0.0000 0.0000 2.5009e+001 9.3803e-005 Max stress = 9.315000 R = 0.00 48300 Cycles Constant amp.: 484 Pass: 484 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A47
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
C 2.3184 1.0074 1.0074 0.0000 0.0000 2.5325e+001 9.8593e-005 Max stress = 9.315000 R = 0.00 48900 Cycles Constant amp.: 490 Pass: 490 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.3686 1.0082 1.0082 0.0000 0.0000 2.5618e+001 1.0321e-004 Max stress = 9.315000 R = 0.00 49400 Cycles Constant amp.: 495 Pass: 495 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.4211 1.0082 1.0082 0.0000 0.0000 2.5900e+001 1.0783e-004 Max stress = 9.315000 R = 0.00 49900 Cycles Constant amp.: 500 Pass: 500 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.4761 1.0091 1.0091 0.0000 0.0000 2.6216e+001 1.1319e-004 Max stress = 9.315000 R = 0.00 50400 Cycles Constant amp.: 505 Pass: 505 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.5337 1.0091 1.0091 0.0000 0.0000 2.6520e+001 1.1854e-004 Max stress = 9.315000 R = 0.00 50900 Cycles Constant amp.: 510 Pass: 510 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.5941 1.0101 1.0101 0.0000 0.0000 2.6861e+001 1.2480e-004 Max stress = 9.315000 R = 0.00 51400 Cycles Constant amp.: 515 Pass: 515 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.6448 1.0101 1.0101 0.0000 0.0000 2.7122e+001 1.2977e-004 Max stress = 9.315000 R = 0.00 51800 Cycles Constant amp.: 519 Pass: 519
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A48
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.6975 1.0101 1.0101 0.0000 0.0000 2.7390e+001 1.3506e-004 Max stress = 9.315000 R = 0.00 52200 Cycles Constant amp.: 523 Pass: 523 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.7524 1.0112 1.0112 0.0000 0.0000 2.7697e+001 1.4131e-004 Max stress = 9.315000 R = 0.00 52600 Cycles Constant amp.: 527 Pass: 527 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.8099 1.0112 1.0112 0.0000 0.0000 2.7985e+001 1.4739e-004 Max stress = 9.315000 R = 0.00 53000 Cycles Constant amp.: 531 Pass: 531 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.8698 1.0124 1.0124 0.0000 0.0000 2.8316e+001 1.5466e-004 Max stress = 9.315000 R = 0.00 53400 Cycles Constant amp.: 535 Pass: 535 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.9327 1.0124 1.0124 0.0000 0.0000 2.8625e+001 1.6169e-004 Max stress = 9.315000 R = 0.00 53800 Cycles Constant amp.: 539 Pass: 539 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 2.9985 1.0124 1.0124 0.0000 0.0000 2.8944e+001 1.6925e-004 Max stress = 9.315000 R = 0.00 54200 Cycles Constant amp.: 543 Pass: 543 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.05 1.0137 1.0137 0.0000 0.0000 2.9230e+001 1.7626e-004 Max stress = 9.315000 R = 0.00
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A49
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
54500 Cycles Constant amp.: 546 Pass: 546 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.1036 1.0137 1.0137 0.0000 0.0000 2.9485e+001 1.8273e-004 Max stress = 9.315000 R = 0.00 54800 Cycles Constant amp.: 549 Pass: 549 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.1591 1.0137 1.0137 0.0000 0.0000 2.9747e+001 1.8959e-004 Max stress = 9.315000 R = 0.00 55100 Cycles Constant amp.: 552 Pass: 552 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.2169 1.0153 1.0153 0.0000 0.0000 3.0065e+001 1.9816e-004 Max stress = 9.315000 R = 0.00 55400 Cycles Constant amp.: 555 Pass: 555 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.2771 1.0153 1.0153 0.0000 0.0000 3.0345e+001 2.0601e-004 Max stress = 9.315000 R = 0.00 55700 Cycles Constant amp.: 558 Pass: 558 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.3397 1.0169 1.0169 0.0000 0.0000 3.0682e+001 2.1581e-004 Max stress = 9.315000 R = 0.00 56000 Cycles Constant amp.: 561 Pass: 561 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.4054 1.0169 1.0169 0.0000 0.0000 3.0982e+001 2.2486e-004 Max stress = 9.315000 R = 0.00 56300 Cycles Constant amp.: 564 Pass: 564 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.4738 1.0169 1.0169 0.0000 0.0000 3.1292e+001 2.3453e-004
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A50
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Max stress = 9.315000 R = 0.00 56600 Cycles Constant amp.: 567 Pass: 567 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.5454 1.0188 1.0188 0.0000 0.0000 3.1673e+001 2.4691e-004 Max stress = 9.315000 R = 0.00 56900 Cycles Constant amp.: 570 Pass: 570 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.6205 1.0188 1.0188 0.0000 0.0000 3.2007e+001 2.5823e-004 Max stress = 9.315000 R = 0.00 57200 Cycles Constant amp.: 573 Pass: 573 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.6726 1.0188 1.0188 0.0000 0.0000 3.2236e+001 2.6625e-004 Max stress = 9.315000 R = 0.00 57400 Cycles Constant amp.: 575 Pass: 575 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.7265 1.0208 1.0208 0.0000 0.0000 3.2536e+001 2.7707e-004 Max stress = 9.315000 R = 0.00 57600 Cycles Constant amp.: 577 Pass: 577 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.7823 1.0208 1.0208 0.0000 0.0000 3.2779e+001 2.8612e-004 Max stress = 9.315000 R = 0.00 57800 Cycles Constant amp.: 579 Pass: 579 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.84 1.0208 1.0208 0.0000 0.0000 3.3028e+001 2.9566e-004 Max stress = 9.315000 R = 0.00 58000 Cycles Constant amp.: 581 Pass: 581 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A51
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
C 3.8997 1.0232 1.0232 0.0000 0.0000 3.3361e+001 3.0887e-004 Max stress = 9.315000 R = 0.00 58200 Cycles Constant amp.: 583 Pass: 583 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 3.962 1.0232 1.0232 0.0000 0.0000 3.3627e+001 3.1975e-004 Max stress = 9.315000 R = 0.00 58400 Cycles Constant amp.: 585 Pass: 585 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.0265 1.0232 1.0232 0.0000 0.0000 3.3900e+001 3.3128e-004 Max stress = 9.315000 R = 0.00 58600 Cycles Constant amp.: 587 Pass: 587 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.0934 1.0232 1.0232 0.0000 0.0000 3.4180e+001 3.4351e-004 Max stress = 9.315000 R = 0.00 58800 Cycles Constant amp.: 589 Pass: 589 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.1631 1.0261 1.0261 0.0000 0.0000 3.4568e+001 3.6109e-004 Max stress = 9.315000 R = 0.00 59000 Cycles Constant amp.: 591 Pass: 591 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.236 1.0261 1.0261 0.0000 0.0000 3.4869e+001 3.7530e-004 Max stress = 9.315000 R = 0.00 59200 Cycles Constant amp.: 593 Pass: 593 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.3119 1.0261 1.0261 0.0000 0.0000 3.5180e+001 3.9047e-004 Max stress = 9.315000 R = 0.00 59400 Cycles Constant amp.: 595 Pass: 595
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A52
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.3913 1.0291 1.0291 0.0000 0.0000 3.5607e+001 4.1222e-004 Max stress = 9.315000 R = 0.00 59600 Cycles Constant amp.: 597 Pass: 597 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.4746 1.0291 1.0291 0.0000 0.0000 3.5943e+001 4.3011e-004 Max stress = 9.315000 R = 0.00 59800 Cycles Constant amp.: 599 Pass: 599 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.5616 1.0291 1.0291 0.0000 0.0000 3.6290e+001 4.4935e-004 Max stress = 9.315000 R = 0.00 60000 Cycles Constant amp.: 601 Pass: 601 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.6532 1.0328 1.0328 0.0000 0.0000 3.6784e+001 4.7803e-004 Max stress = 9.315000 R = 0.00 60200 Cycles Constant amp.: 603 Pass: 603 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.75 1.0328 1.0328 0.0000 0.0000 3.7165e+001 5.0126e-004 Max stress = 9.315000 R = 0.00 60400 Cycles Constant amp.: 605 Pass: 605 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.8001 1.0328 1.0328 0.0000 0.0000 3.7360e+001 5.1359e-004 Max stress = 9.315000 R = 0.00 60500 Cycles Constant amp.: 606 Pass: 606 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.8514 1.0366 1.0366 0.0000 0.0000 3.7697e+001 5.3547e-004 Max stress = 9.315000 R = 0.00
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A53
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
60600 Cycles Constant amp.: 607 Pass: 607 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.905 1.0366 1.0366 0.0000 0.0000 3.7904e+001 5.4939e-004 Max stress = 9.315000 R = 0.00 60700 Cycles Constant amp.: 608 Pass: 608 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 4.9599 1.0366 1.0366 0.0000 0.0000 3.8116e+001 5.6395e-004 Max stress = 9.315000 R = 0.00 60800 Cycles Constant amp.: 609 Pass: 609 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.0163 1.0366 1.0366 0.0000 0.0000 3.8332e+001 5.7917e-004 Max stress = 9.315000 R = 0.00 60900 Cycles Constant amp.: 610 Pass: 610 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.0742 1.0366 1.0366 0.0000 0.0000 3.8553e+001 5.9511e-004 Max stress = 9.315000 R = 0.00 61000 Cycles Constant amp.: 611 Pass: 611 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.1338 1.0412 1.0412 0.0000 0.0000 3.8951e+001 6.2498e-004 Max stress = 9.315000 R = 0.00 61100 Cycles Constant amp.: 612 Pass: 612 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.1962 1.0412 1.0412 0.0000 0.0000 3.9188e+001 6.4335e-004 Max stress = 9.315000 R = 0.00 61200 Cycles Constant amp.: 613 Pass: 613 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.2606 1.0412 1.0412 0.0000 0.0000 3.9430e+001 6.6267e-004
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A54
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Max stress = 9.315000 R = 0.00 61300 Cycles Constant amp.: 614 Pass: 614 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.3268 1.0412 1.0412 0.0000 0.0000 3.9677e+001 6.8301e-004 Max stress = 9.315000 R = 0.00 61400 Cycles Constant amp.: 615 Pass: 615 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.3952 1.0458 1.0458 0.0000 0.0000 4.0106e+001 7.1971e-004 Max stress = 9.315000 R = 0.00 61500 Cycles Constant amp.: 616 Pass: 616 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.4671 1.0458 1.0458 0.0000 0.0000 4.0373e+001 7.4346e-004 Max stress = 9.315000 R = 0.00 61600 Cycles Constant amp.: 617 Pass: 617 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.5415 1.0458 1.0458 0.0000 0.0000 4.0647e+001 7.6861e-004 Max stress = 9.315000 R = 0.00 61700 Cycles Constant amp.: 618 Pass: 618 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.6183 1.0458 1.0458 0.0000 0.0000 4.0928e+001 7.9529e-004 Max stress = 9.315000 R = 0.00 61800 Cycles Constant amp.: 619 Pass: 619 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.6979 1.0515 1.0515 0.0000 0.0000 4.1439e+001 8.4624e-004 Max stress = 9.315000 R = 0.00 61900 Cycles Constant amp.: 620 Pass: 620 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A55
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
C 5.7825 1.0515 1.0515 0.0000 0.0000 4.1746e+001 8.7828e-004 Max stress = 9.315000 R = 0.00 62000 Cycles Constant amp.: 621 Pass: 621 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.8703 1.0515 1.0515 0.0000 0.0000 4.2062e+001 9.1254e-004 Max stress = 9.315000 R = 0.00 62100 Cycles Constant amp.: 622 Pass: 622 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 5.9616 1.0515 1.0515 0.0000 0.0000 4.2388e+001 9.4925e-004 Max stress = 9.315000 R = 0.00 62200 Cycles Constant amp.: 623 Pass: 623 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 6.0565 1.0587 1.0587 0.0000 0.0000 4.3017e+001 1.0245e-003 Max stress = 9.315000 R = 0.00 62300 Cycles Constant amp.: 624 Pass: 624 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 6.1589 1.0587 1.0587 0.0000 0.0000 4.3380e+001 1.0705e-003 Max stress = 9.315000 R = 0.00 62400 Cycles Constant amp.: 625 Pass: 625 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 6.266 1.0587 1.0587 0.0000 0.0000 4.3755e+001 1.1203e-003 Max stress = 9.315000 R = 0.00 62500 Cycles Constant amp.: 626 Pass: 626 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 6.378 1.0657 1.0657 0.0000 0.0000 4.4436e+001 1.2168e-003 Max stress = 9.315000 R = 0.00 62600 Cycles Constant amp.: 627 Pass: 627
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A56
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 6.4997 1.0657 1.0657 0.0000 0.0000 4.4857e+001 1.2809e-003 Max stress = 9.315000 R = 0.00 62700 Cycles Constant amp.: 628 Pass: 628 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 6.6278 1.0657 1.0657 0.0000 0.0000 4.5297e+001 1.3514e-003 Max stress = 9.315000 R = 0.00 62800 Cycles Constant amp.: 629 Pass: 629 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 6.7629 1.0747 1.0747 0.0000 0.0000 4.6144e+001 1.4990e-003 Max stress = 9.315000 R = 0.00 62900 Cycles Constant amp.: 630 Pass: 630 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 6.9128 1.0747 1.0747 0.0000 0.0000 4.6652e+001 1.5959e-003 Max stress = 9.315000 R = 0.00 63000 Cycles Constant amp.: 631 Pass: 631 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 7.0724 1.0747 1.0747 0.0000 0.0000 4.7188e+001 1.7052e-003 Max stress = 9.315000 R = 0.00 63100 Cycles Constant amp.: 632 Pass: 632 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 7.2429 1.0870 1.0870 0.0000 0.0000 4.8300e+001 1.9594e-003 Max stress = 9.315000 R = 0.00 63200 Cycles Constant amp.: 633 Pass: 633 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 7.4389 1.0870 1.0870 0.0000 0.0000 4.8949e+001 2.1270e-003 Max stress = 9.315000 R = 0.00
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A57
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
63300 Cycles Constant amp.: 634 Pass: 634 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 7.6516 1.0985 1.0985 0.0000 0.0000 5.0168e+001 2.4880e-003 Max stress = 9.315000 R = 0.00 63400 Cycles Constant amp.: 635 Pass: 635 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 7.9004 1.0985 1.0985 0.0000 0.0000 5.0977e+001 2.7669e-003 Max stress = 9.315000 R = 0.00 63500 Cycles Constant amp.: 636 Pass: 636 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 8.1771 1.1147 1.1147 0.0000 0.0000 5.2628e+001 3.4611e-003 Max stress = 9.315000 R = 0.00 63600 Cycles Constant amp.: 637 Pass: 637 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 8.5232 1.1147 1.1147 0.0000 0.0000 5.3730e+001 4.0464e-003 Max stress = 9.315000 R = 0.00 63700 Cycles Constant amp.: 638 Pass: 638 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 8.9278 1.1410 1.1410 0.0000 0.0000 5.6290e+001 5.9948e-003 Max stress = 9.315000 R = 0.00 63800 Cycles Constant amp.: 639 Pass: 639 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 9.3774 1.1588 1.1588 0.0000 0.0000 5.8589e+001 9.0329e-003 Max stress = 9.315000 R = 0.00 63875 Cycles Constant amp.: 639 Pass: 639 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 9.6032 1.1588 1.1588 0.0000 0.0000 5.9290e+001 1.0412e-002
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A58
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Max stress = 9.315000 R = 0.00 63900 Cycles Constant amp.: 640 Pass: 640 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 10.093 1.1906 1.1906 0.0000 0.0000 6.2450e+001 2.4109e-002 Max stress = 9.315000 R = 0.00 63947 Cycles Constant amp.: 640 Pass: 640 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 10.599 1.2161 1.2161 0.0000 0.0000 6.5367e+001 2.2816e-001 Max stress = 9.315000 R = 0.00 63968 Cycles Constant amp.: 640 Pass: 640 *********Fracture based on ' Kmax' Criteria (current maximum stress) Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 11.283 1.2552 1.2552 0.0000 0.0000 6.9611e+001 1.0000e-001 Max stress = 9.315000 R = 0.00 63971 Cycles Constant amp.: 640 Pass: 640 Stress State in 'C' direction (PSC): 2 Fracture has occurred - run time : 0 hour(s) 0 minute(s) 1 second(s)
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A59
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
GPS ANTENNA 1 & 2
CRACK GROWTH PHASE I
AFGROW 5.1.6.17 **English Units [ Length(in), Stress(Ksi), Temperature(F) ] Crack Growth Model and Spectrum Information Title: 737 GPS Antenna Stage I 500D location Load: Axial Stress Fraction: 0.65, Bending Stress Fraction: 0, Bearing Stress Fraction: 1.882 Crack Model: 2020 - Single Through Crack at Hole - Standard Solution Initial surface crack length (c): 0.0500 Thickness : 0.040 Width : 20.000 Hole Diameter: 0.186 Young's Modulus =10600 Poisson's Ratio =0.33 Coeff. of Thermal Expan. =1.29e-005 No crack growth retardation is being considered Determine Stress State automatically (2 = Plane stress, 6 = Plane strain) The stress intensity factors are being modified for a non-uniform stress field as follows: C Stress Beta Correction --------------------------------------- 0.0050000 1.0000 1.010000 0.1000000 1.0000 1.012000 0.2000000 1.0000 1.040000 0.3000000 1.0000 1.060000 0.4000000 1.0000 1.070000 0.6000000 1.0000 1.100000 0.7000000 1.0000 1.130000 0.8140000 1.0000 1.190000 No K-Solution Filters The Forman-Newman-de Koning- Henriksen (NASGRO) crack growth relation is being used
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A60
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
For Reff < 0.0, Delta K = Kmax Material: 1000-9000 series aluminum, 2024-T3 Al, [ Clad; plt & sht; L-T ] Plane strain fracture toughness: 33 Plane stress fracture toughness: 66 Effective fracture toughness for surface/elliptically shaped crack: 46 Fit parameters (KC versus Thickness Equation): Ak= 1, Bk=1 Yield stress: 53 Lower 'R' value boundary: -0.3 Upper 'R' value boundary: 0.7 Exponents in NASGRO Equation: n=3.284, p=0.5, q=1 Paris crack growth rate constant: 8.29e-009 Threshold stress intensity factor range at R = 0: 2.9 Threshold coefficient: 1.5 Plane stress/strain constraint factor: 1.5 Ratio of the maximum applied stress to the flow stress: 0.3 Failure is based on the current load in the applied spectrum Vroman integration at 5% crack length **Spectrum Information Constant amplitude loading Spectrum multiplication factor: 22.029 SPL: 0 The spectrum will be repeated up to 999999 times Total Cycles: 100 Levels: 1 Subspectra: 1 Max Value: 1 Min Value: 0 No Spectrum Filters Critical Crack Length is Based on the Maximum Spectrum Stress Critical crack size in 'C' direction=5.95814, Stress State=2 (Based on Kmax criteria) Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.05 1.7170 1.7170 0.0000 0.0000 1.4991e+001 1.3409e-005 Max stress = 22.029000 R = 0.00 0 Cycles Constant amp.: 1 Pass: 1 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.061036 1.5689 1.5689 0.0000 0.0000 1.5134e+001 1.3882e-005
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A61
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Max stress = 22.029000 R = 0.00 800 Cycles Constant amp.: 9 Pass: 9 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.072082 1.4181 1.4181 0.0000 0.0000 1.4866e+001 1.2993e-005 Max stress = 22.029000 R = 0.00 1600 Cycles Constant amp.: 17 Pass: 17 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.08268 1.3385 1.3385 0.0000 0.0000 1.5027e+001 1.3519e-005 Max stress = 22.029000 R = 0.00 2400 Cycles Constant amp.: 25 Pass: 25 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.093183 1.2488 1.2488 0.0000 0.0000 1.4884e+001 1.3048e-005 Max stress = 22.029000 R = 0.00 3200 Cycles Constant amp.: 33 Pass: 33 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.10345 1.1821 1.1821 0.0000 0.0000 1.4845e+001 1.2920e-005 Max stress = 22.029000 R = 0.00 4000 Cycles Constant amp.: 41 Pass: 41 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.11377 1.1209 1.1209 0.0000 0.0000 1.4763e+001 1.2656e-005 Max stress = 22.029000 R = 0.00 4800 Cycles Constant amp.: 49 Pass: 49 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.12411 1.0907 1.0907 0.0000 0.0000 1.5003e+001 1.3434e-005 Max stress = 22.029000 R = 0.00 5600 Cycles Constant amp.: 57 Pass: 57 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A62
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
C 0.13443 1.0369 1.0369 0.0000 0.0000 1.4845e+001 1.2918e-005 Max stress = 22.029000 R = 0.00 6400 Cycles Constant amp.: 65 Pass: 65 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.1449 1.0095 1.0095 0.0000 0.0000 1.5005e+001 1.3438e-005 Max stress = 22.029000 R = 0.00 7200 Cycles Constant amp.: 73 Pass: 73 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.15557 0.9643 0.9643 0.0000 0.0000 1.4851e+001 1.2935e-005 Max stress = 22.029000 R = 0.00 8000 Cycles Constant amp.: 81 Pass: 81 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.16629 0.9440 0.9440 0.0000 0.0000 1.5030e+001 1.3522e-005 Max stress = 22.029000 R = 0.00 8800 Cycles Constant amp.: 89 Pass: 89 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.17734 0.9231 0.9231 0.0000 0.0000 1.5178e+001 1.4020e-005 Max stress = 22.029000 R = 0.00 9600 Cycles Constant amp.: 97 Pass: 97 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.18872 0.9048 0.9048 0.0000 0.0000 1.5347e+001 1.4604e-005 Max stress = 22.029000 R = 0.00 10400 Cycles Constant amp.: 105 Pass: 105 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.19896 0.8876 0.8876 0.0000 0.0000 1.5460e+001 1.5006e-005 Max stress = 22.029000 R = 0.00 11100 Cycles Constant amp.: 112 Pass: 112
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A63
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.20949 0.8714 0.8714 0.0000 0.0000 1.5572e+001 1.5416e-005 Max stress = 22.029000 R = 0.00 11800 Cycles Constant amp.: 119 Pass: 119 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.2203 0.8557 0.8557 0.0000 0.0000 1.5681e+001 1.5819e-005 Max stress = 22.029000 R = 0.00 12500 Cycles Constant amp.: 126 Pass: 126 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.23141 0.8409 0.8409 0.0000 0.0000 1.5795e+001 1.6246e-005 Max stress = 22.029000 R = 0.00 13200 Cycles Constant amp.: 133 Pass: 133 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.24288 0.8250 0.8250 0.0000 0.0000 1.5876e+001 1.6559e-005 Max stress = 22.029000 R = 0.00 13900 Cycles Constant amp.: 140 Pass: 140 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.25302 0.8102 0.8102 0.0000 0.0000 1.5912e+001 1.6701e-005 Max stress = 22.029000 R = 0.00 14500 Cycles Constant amp.: 146 Pass: 146 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.26336 0.8102 0.8102 0.0000 0.0000 1.6234e+001 1.7990e-005 Max stress = 22.029000 R = 0.00 15100 Cycles Constant amp.: 152 Pass: 152 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.27391 0.7963 0.7963 0.0000 0.0000 1.6272e+001 1.8146e-005 Max stress = 22.029000 R = 0.00
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A64
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
15700 Cycles Constant amp.: 158 Pass: 158 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.28481 0.7838 0.7838 0.0000 0.0000 1.6332e+001 1.8396e-005 Max stress = 22.029000 R = 0.00 16300 Cycles Constant amp.: 164 Pass: 164 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.29608 0.7722 0.7722 0.0000 0.0000 1.6406e+001 1.8708e-005 Max stress = 22.029000 R = 0.00 16900 Cycles Constant amp.: 170 Pass: 170 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.30765 0.7722 0.7722 0.0000 0.0000 1.6723e+001 2.0092e-005 Max stress = 22.029000 R = 0.00 17500 Cycles Constant amp.: 176 Pass: 176 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.31949 0.7606 0.7606 0.0000 0.0000 1.6786e+001 2.0373e-005 Max stress = 22.029000 R = 0.00 18100 Cycles Constant amp.: 182 Pass: 182 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.32969 0.7492 0.7492 0.0000 0.0000 1.6796e+001 2.0420e-005 Max stress = 22.029000 R = 0.00 18600 Cycles Constant amp.: 187 Pass: 187 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.34014 0.7492 0.7492 0.0000 0.0000 1.7060e+001 2.1644e-005 Max stress = 22.029000 R = 0.00 19100 Cycles Constant amp.: 192 Pass: 192 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.35075 0.7384 0.7384 0.0000 0.0000 1.7075e+001 2.1713e-005
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A65
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Max stress = 22.029000 R = 0.00 19600 Cycles Constant amp.: 197 Pass: 197 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.36175 0.7282 0.7282 0.0000 0.0000 1.7102e+001 2.1842e-005 Max stress = 22.029000 R = 0.00 20100 Cycles Constant amp.: 202 Pass: 202 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.37292 0.7282 0.7282 0.0000 0.0000 1.7364e+001 2.3120e-005 Max stress = 22.029000 R = 0.00 20600 Cycles Constant amp.: 207 Pass: 207 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.38441 0.7188 0.7188 0.0000 0.0000 1.7400e+001 2.3300e-005 Max stress = 22.029000 R = 0.00 21100 Cycles Constant amp.: 212 Pass: 212 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.39633 0.7188 0.7188 0.0000 0.0000 1.7668e+001 2.4671e-005 Max stress = 22.029000 R = 0.00 21600 Cycles Constant amp.: 217 Pass: 217 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.40842 0.7086 0.7086 0.0000 0.0000 1.7683e+001 2.4749e-005 Max stress = 22.029000 R = 0.00 22100 Cycles Constant amp.: 222 Pass: 222 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.41849 0.7086 0.7086 0.0000 0.0000 1.7899e+001 2.5905e-005 Max stress = 22.029000 R = 0.00 22500 Cycles Constant amp.: 226 Pass: 226 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A66
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
C 0.42867 0.6998 0.6998 0.0000 0.0000 1.7890e+001 2.5853e-005 Max stress = 22.029000 R = 0.00 22900 Cycles Constant amp.: 230 Pass: 230 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.43918 0.6998 0.6998 0.0000 0.0000 1.8108e+001 2.7056e-005 Max stress = 22.029000 R = 0.00 23300 Cycles Constant amp.: 234 Pass: 234 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.44996 0.6916 0.6916 0.0000 0.0000 1.8115e+001 2.7095e-005 Max stress = 22.029000 R = 0.00 23700 Cycles Constant amp.: 238 Pass: 238 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.46098 0.6916 0.6916 0.0000 0.0000 1.8335e+001 2.8356e-005 Max stress = 22.029000 R = 0.00 24100 Cycles Constant amp.: 242 Pass: 242 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.4724 0.6839 0.6839 0.0000 0.0000 1.8354e+001 2.8468e-005 Max stress = 22.029000 R = 0.00 24500 Cycles Constant amp.: 246 Pass: 246 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.48398 0.6839 0.6839 0.0000 0.0000 1.8578e+001 2.9796e-005 Max stress = 22.029000 R = 0.00 24900 Cycles Constant amp.: 250 Pass: 250 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.49611 0.6767 0.6767 0.0000 0.0000 1.8610e+001 2.9990e-005 Max stress = 22.029000 R = 0.00 25300 Cycles Constant amp.: 254 Pass: 254
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A67
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.50832 0.6767 0.6767 0.0000 0.0000 1.8838e+001 3.1397e-005 Max stress = 22.029000 R = 0.00 25700 Cycles Constant amp.: 258 Pass: 258 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.5211 0.6710 0.6710 0.0000 0.0000 1.8914e+001 3.1880e-005 Max stress = 22.029000 R = 0.00 26100 Cycles Constant amp.: 262 Pass: 262 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.53408 0.6710 0.6710 0.0000 0.0000 1.9148e+001 3.3397e-005 Max stress = 22.029000 R = 0.00 26500 Cycles Constant amp.: 266 Pass: 266 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.54421 0.6710 0.6710 0.0000 0.0000 1.9329e+001 3.4606e-005 Max stress = 22.029000 R = 0.00 26800 Cycles Constant amp.: 269 Pass: 269 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.55451 0.6657 0.6657 0.0000 0.0000 1.9356e+001 3.4791e-005 Max stress = 22.029000 R = 0.00 27100 Cycles Constant amp.: 272 Pass: 272 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.56507 0.6657 0.6657 0.0000 0.0000 1.9539e+001 3.6057e-005 Max stress = 22.029000 R = 0.00 27400 Cycles Constant amp.: 275 Pass: 275 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.57602 0.6607 0.6607 0.0000 0.0000 1.9579e+001 3.6336e-005 Max stress = 22.029000 R = 0.00
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A68
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
27700 Cycles Constant amp.: 278 Pass: 278 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.58705 0.6607 0.6607 0.0000 0.0000 1.9766e+001 3.7668e-005 Max stress = 22.029000 R = 0.00 28000 Cycles Constant amp.: 281 Pass: 281 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.59849 0.6607 0.6607 0.0000 0.0000 1.9957e+001 3.9075e-005 Max stress = 22.029000 R = 0.00 28300 Cycles Constant amp.: 284 Pass: 284 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.61027 0.6566 0.6566 0.0000 0.0000 2.0027e+001 3.9595e-005 Max stress = 22.029000 R = 0.00 28600 Cycles Constant amp.: 287 Pass: 287 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.6223 0.6566 0.6566 0.0000 0.0000 2.0223e+001 4.1094e-005 Max stress = 22.029000 R = 0.00 28900 Cycles Constant amp.: 290 Pass: 290 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.63478 0.6566 0.6566 0.0000 0.0000 2.0425e+001 4.2679e-005 Max stress = 22.029000 R = 0.00 29200 Cycles Constant amp.: 293 Pass: 293 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.64769 0.6555 0.6555 0.0000 0.0000 2.0598e+001 4.4074e-005 Max stress = 22.029000 R = 0.00 29500 Cycles Constant amp.: 296 Pass: 296 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.66109 0.6555 0.6555 0.0000 0.0000 2.0810e+001 4.5832e-005
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A69
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Max stress = 22.029000 R = 0.00 29800 Cycles Constant amp.: 299 Pass: 299 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.67502 0.6549 0.6549 0.0000 0.0000 2.1009e+001 4.7532e-005 Max stress = 22.029000 R = 0.00 30100 Cycles Constant amp.: 302 Pass: 302 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.68948 0.6549 0.6549 0.0000 0.0000 2.1233e+001 4.9502e-005 Max stress = 22.029000 R = 0.00 30400 Cycles Constant amp.: 305 Pass: 305 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.70454 0.6549 0.6549 0.0000 0.0000 2.1463e+001 5.1600e-005 Max stress = 22.029000 R = 0.00 30700 Cycles Constant amp.: 308 Pass: 308 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.71497 0.6561 0.6561 0.0000 0.0000 2.1661e+001 5.3452e-005 Max stress = 22.029000 R = 0.00 30900 Cycles Constant amp.: 310 Pass: 310 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.72573 0.6561 0.6561 0.0000 0.0000 2.1823e+001 5.5014e-005 Max stress = 22.029000 R = 0.00 31100 Cycles Constant amp.: 312 Pass: 312 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.73682 0.6561 0.6561 0.0000 0.0000 2.1989e+001 5.6646e-005 Max stress = 22.029000 R = 0.00 31300 Cycles Constant amp.: 314 Pass: 314 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A70
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
C 0.74823 0.6615 0.6615 0.0000 0.0000 2.2341e+001 6.0233e-005 Max stress = 22.029000 R = 0.00 31500 Cycles Constant amp.: 316 Pass: 316 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.76037 0.6615 0.6615 0.0000 0.0000 2.2522e+001 6.2140e-005 Max stress = 22.029000 R = 0.00 31700 Cycles Constant amp.: 318 Pass: 318 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.7729 0.6615 0.6615 0.0000 0.0000 2.2707e+001 6.4141e-005 Max stress = 22.029000 R = 0.00 31900 Cycles Constant amp.: 320 Pass: 320 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.78583 0.6673 0.6673 0.0000 0.0000 2.3096e+001 6.8523e-005 Max stress = 22.029000 R = 0.00 32100 Cycles Constant amp.: 322 Pass: 322 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.79965 0.6673 0.6673 0.0000 0.0000 2.3298e+001 7.0891e-005 Max stress = 22.029000 R = 0.00 32300 Cycles Constant amp.: 324 Pass: 324 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.81395 0.6673 0.6673 0.0000 0.0000 2.3506e+001 7.3388e-005 Max stress = 22.029000 R = 0.00 32500 Cycles Constant amp.: 326 Pass: 326 Crack size Beta Tension Beta Compression R(k) R(final) Delta-K D( )/DN C 0.82129 0.6673 0.6673 0.0000 0.0000 2.3611e+001 7.4687e-005 Max stress = 22.029000 R = 0.00 32600 Cycles Constant amp.: 327 Pass: 327
REVISION
NC
DOCUMENT NO.EAK-15-507-DT
PAGE NO.
A71
PREPARED BY E. Kats
11/02/15 DATE
CHECKED BY
R. Fernandez 11/02/15 DATE
SUBJECT:
Damage Tolerance Evaluation Fuselage Antennas Installation
REF. DWG. NO.
EDWARD KATS & ASSOCIATES
Stress State in 'C' direction (PSC): 2 Crack length exceeded stop value - run time : 0 hour(s) 0 minute(s) 1 second(s)