READ MEAuthor:R. AbbottTotal Report Pages:4Page TitleSubSubSubFigTableRunning CountsTotal Sheet Pages:1Check: Report:AA-SM-003NoNoTitleTitleTitleNoNoTotal Title No:0Date:20/10/2013Revision:IRTotal Sub No:0Section Number:Sheet NameIMPORTANT INFORMATIONTotal Sub No:0Report Title:STANDARD SPREADSHEET METHODTotal Sub No:0Section:Total Fig No:0Total Table No:0Author:R. AbbottDocument Number:AA-SM-003Check: Revision Level :IR1Date:20/10/2013Page:1 of 41Title:STANDARD SPREADSHEET METHODIMPORTANT INFORMATION

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T-ClipsAuthor:R. AbbottTotal Report Pages:4Page TitleSubSubSubFigTableRunning CountsTotal Sheet Pages:2Check: Report:AA-SM-003NoNoTitleTitleTitleNoNoTotal Title No:0Date:20/10/2013Revision:IRTotal Sub No:0Section Number:Sheet NameTENSION CLIP - EXTRUDED 'T'1Total Sub No:0Report Title:STANDARD SPREADSHEET METHODTotal Sub No:0Section:Total Fig No:0Total Table No:0Author:R. AbbottDocument Number:AA-SM-003Check: Revision Level :IR1Date:20/10/2013Page:2 of 42Title:STANDARD SPREADSHEET METHOD TENSION CLIP - EXTRUDED 'T'

Extruded 7075 T-Section ClipsRef Niu, Airframe Stress Analysis and Sizing.Figure 9.10.9 is digitized using straight line functions, this will produce conservative results, if a negative margin is created using this method the source material should be consultedtb/rPall/Dvert0.250.51.001.5002.0000000.000.0000.000t =0.18in, End Pad Thickness0.251407.30-1407.308.008.809.2009.750D =0.25in, Fastener Diameter0.51408.00e =0.7in, Fastener Offset11408.80r =0.18in, Fillet Radius1.51409.200.250.30.40.50.60.721409.750000000t / (e - r / 2 - D / 2) 0.64.35.056.357.558.659.7=0.18 / (0.7 - 0.18 / 2 - 0.25 / 2) 0.3711340206tb/Dtb/(e-r/2+D/2)vert=0.37
Abbott Aerospace: Abbott Aerospace:Do not delete0.250.64.3t / D 0.30.65.05=0.18 / 0.25 0.720.40.66.35=0.700.50.67.55The value of t/D has been set to 0.7 as the calculated value exceeds 0.7, this is conservative.
Abbott Aerospace: Abbott Aerospace:Do not delete0.60.68.650.70.69.7t / r =0.18 / 0.18 1=1.00tb/Dtb/(e-r/2+D/2)verttb/rPall/Dvert
Abbott Aerospace: Abbott Aerospace:Do not delete0.250.64.30.251407.300.30.65.050.51408.000.40.66.3511408.800.50.67.551.51409.200.60.68.6521409.750.70.69.7

6.07583505158.5435

16.386726751399.56304877590.3700.376.0760.006.0760.006.076-99.566.076-99.560

99.56Alllowable load per 1in length (4D) of T-section =(99.56 0.25) 1000 P =6222.7lb
Abbott Aerospace: Abbott Aerospace:Do not Delete

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Formed L-ClipsAuthor:R. AbbottTotal Report Pages:4Page TitleSubSubSubFigTableRunning CountsTotal Sheet Pages:3Check: Report:AA-SM-003NoNoTitleTitleTitleNoNoTotal Title No:0Date:20/10/2013Revision:IRTotal Sub No:0Section Number:Sheet NameTENSION CLIPS - 'L' SECTION FORMED CLIP2Total Sub No:0Report Title:STANDARD SPREADSHEET METHODTotal Sub No:0Section:Total Fig No:0Total Table No:0Author:R. AbbottDocument Number:AA-SM-003Check: Revision Level :IR1Date:20/10/2013Page:3 of 43Title:STANDARD SPREADSHEET METHOD TENSION CLIPS - 'L' SECTION FORMED CLIP

Ref Niu, Airframe Stress Analysis and Sizing Fig 9.10.4Allowable Load per 1in of clip length0.10.080.0710.050.0320.10.080.0710.050.032Applied Load, P =200lb000.10.1Fastener Tension Load 2P = 400lb0.20.20.30.0710.050.30.0710.05Material =20240.4675.0430.0337.0165.070.00.6227.2111.2227.20.4950.0580.0465.0233.0105.01325.0162.8325.00.5550.0350.4274.6134.457.00.7189.792.9189.70.5800.0475.0390.0195.488.10.7275.0137.8275.0e =0.6in0.6455.0289.9227.2111.247.20.6700.0400.0325.0162.870.0t =0.071in0.7380.0242.1189.792.939.4227.1629629630.7590.0340.0275.0137.857.03250.8330.0210.2164.880.734.20.8510.0295.0234.0117.247.0Allowable Load =227.2lb/in0.9290.0184.7144.870.930.10.9445.0260.0206.297.040.0Clip Length =2.50in1265.0168.8132.364.827.51385.0235.1186.485.038.3Total Allowable Load =2.5 227.16 1.1245.0156.1122.359.925.41.1345.0215.0170.575.033.8=567.91lb1.2227.0144.6113.355.523.51.2310.0200.0158.670.031.5

MS = 567.91 / (200 1.15) - 1 =1.47

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Extruded L-ClipsAuthor:R. AbbottTotal Report Pages:4Page TitleSubSubSubFigTableRunning CountsTotal Sheet Pages:5Check: Report:AA-SM-003NoNoTitleTitleTitleNoNoTotal Title No:0Date:20/10/2013Revision:IRTotal Sub No:0Section Number:Sheet NameTENSION CLIPS - 'L' SECTION EXTRUDED CLIP3Total Sub No:0Report Title:STANDARD SPREADSHEET METHODTotal Sub No:0Section:Total Fig No:0Total Table No:0Author:R. AbbottDocument Number:AA-SM-003Check: Revision Level :IR1Date:20/10/2013Page:4 of 44Title:STANDARD SPREADSHEET METHOD TENSION CLIPS - 'L' SECTION EXTRUDED CLIP

Allowable Load on the clip

tb =0.15into =0.10in00000000.250.250.31250.31250.3750.37510.050.050.050.050.050.05125160125160125160Fastener Diameter =0.25in0.70.20.1500.70.251.20.070.060.060.060.060.06123456Bolt Material Strength =160ksi0.60.170.150.1750.60.31251.40.080.080.070.080.080.0810.050.050.050.050.050.050.520.150.350.1750.520.3751.60.090.090.090.100.090.0920.140.140.130.130.1150.115Applied Load =1500.0lb0.420.120.421.80.110.110.110.120.110.1130.60.360.250.250.180.180.350.100.1750.3512520.140.140.130.130.120.12420.80.410.380.260.26Basic Fastener Shank Tension Strength =(0.25 / 2) 160 1000 0.280.082.220.1750.281602.20.180.170.150.150.130.1350.670.540.3350.335(Width = 4D)=7854lb0.220.062.2200.222.40.250.210.170.180.150.1560.730.430.432.60.340.250.200.200.160.1670.60.55Tension Strength =2223.4lb2.80.450.300.220.220.170.1780.730030.600.360.250.250.180.19y = 0.0950x3 - 0.3850x2 + 0.5800x - 0.2400y = 0.015000x3 - 0.025000x2 + 0.060000x - 0.000000y = 0.002500x4 - 0.025000x3 + 0.107500x2 - 0.105000x + 0.070000y = 0.0000925926x3 + 0.0117063492x2 + 0.0501851852x - 0.0133333333y = 0.0022222222x3 - 0.0187500000x2 + 0.1147420635x - 0.0514285714y = 0.0015404040x3 - 0.0129383117x2 + 0.1009974747x - 0.0428571429

0.30.70.253.20.790.430.280.270.200.201603.41.020.500.310.300.210.21003.61.290.590.340.320.220.220.30.60.1752.162.002.200.140.183.81.620.690.370.350.240.242.222.202.400.170.2142.000.800.410.380.250.25Ref Airframe Stress Analysis and Sizing, Michael C.Y. Niu, Fig 9.10.6, For Extruded 2024 Clips.002.402.402.600.170.204.22.440.920.450.410.260.27Will give conservative results for 7000 series extrusions.0.30.522.392.202.400.150.184.42.951.060.500.440.280.282.852.803.000.170.184.63.531.210.550.470.300.30002.842.803.000.170.194.84.181.370.610.510.310.310.30.4254.911.550.670.540.330.332.1595.25.721.750.740.580.350.35002.225.46.621.960.830.610.370.370.30.355.67.622.190.920.650.390.392.225.88.712.431.030.690.420.410069.902.701.150.730.440.430.30.286.211.202.991.290.770.470.456.412.613.291.440.810.500.48006.614.133.621.620.850.530.500.30.226.815.773.971.810.900.560.53717.544.342.030.940.600.567.219.444.732.270.990.630.597.421.475.152.551.040.670.627.623.635.602.851.080.710.657.825.946.073.181.130.760.69

Tension Clip Margin of SafetyM.S. = 2223.36 / (1500 1.15) - 1 =0.29

Author:R. AbbottDocument Number:AA-SM-003Check: Revision Level :IR1Date:20/10/2013Page:5 of 45Title:STANDARD SPREADSHEET METHOD TENSION CLIPS - 'L' SECTION EXTRUDED CLIP

Check on Heel-Toe of Bracket and additional fastener tension.(based on Triangular Bearing Distribution)

A =0.625inB =0.5in

Moment at the bolt =0.63 1500 M =937.5inlb

Additional bolt load =M / (2 B / 3) =937.5 / (2 0.5 / 3) Padd =2813lb

Total bolt Tension Load ==1500 + 2812.5 PTOT =4313lb

Maximum Bolt Tension Margin of SafetyM.S. = 7853.98 / (4312.5 1.15) - 1 =0.58

Peak Bearing effect between Flange and Support Structure

Additional bolt load =2813lb

Peak bearing running load =2812.5 / 0.5 2 =11250lb/in

e, effect length of flange =0.5in

Peak Bearing Stress =11250 / 0.5 =22500psi

Minimum Bearing Allowable =129000psi

Peak Bearing Margins of SafetyM.S. = 129000 / (22500 1.15) - 1 =3.99

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tbtoPTOTPallAB BAssumed Centroid of Moment reaction