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Plans (24) tN- ;Wm usocittu, Inc, ENGINEERING 2007 ur 8 IJILD u ilt RD 1 --ok G D /SION STRUCTURAL CALCULATIONS PROJECT: •TC Building - Tigard . PROJECT No.: A07042 DATE: December 05, 2007 PERMIT SUBMITTAL olgolezt 4 , 4 9 PRar v• N / PaXis C044-6 + a 2 A' 11,2.2 C ity of:Tigard it Apo rliv-d Plans G. B *kit- Date C1 '$* v°4 is • .9 17. s z,Vt R. A* EXPIRES: 12/31/07 1 PFITICE COPY 4875 SW Griffith Drive I Suite 300 I Beaverton, OR I 97005 503.620.3030 I tel 503.620.55 I fax www.aaieng.-com • g = (I R 2-5) (a ( I A-) t ( ) ( 7 4) NZ) •= 3. ►t w12.x35 d = � ; o3 F -( •< 3 $a - o 53,- F (sr3 }�. 3• Z 2, 1 3 ksi < s t o IL (s) (0 (3, 2- t C- _ /C (5 _ ) ^ 3. S ( • t k S � rt • : 3 ,s (4 s ~ >�• ) 2. 3� < ( C o G k f PaIIovj = ( 4)(Z)(•)*ig ) °I > 3 °jam ° � • A AI I afghan associates, inc. A_ 'rG 5 tD , _ 7/� Ape By: AKA Date:,DE (' 2407 ENGINEERING �f /� 6 0- X4675 SW Griffith Drive !Suite 300 1 Beaverton, OR 1 97005 Project No.: T t v 7 I 503.620.3030 1 tot 503.620.5539 t fax I www.aaieng.com Sheet: / of: . ITEM 4 5 w� @ 97p. 3 DI. = /8 �s f SL 25 7orAL 5 /s/"/ / . Lc 4D C -g/D 3 _ /1.0 i< S NEST 4, /3 of rfk L C c., r oof DL _ ()(/0.5/z) = o.o9s /- ���.� +?.�)� l4.oK Aoor .:L !4J (z5)00f`'/`2) 0.13 K// Q _ ���I,4=1.9.�K. i 0.5 L = 23 . LoND co 4 /ATiDA , 4SGE 7- OS /z.4 , 3.2 EQ .5,4, 1 S 5. 0.0.1-6•14S1s) b+ + t 0 .7 oQE ) .SDs = o• �3 09D-t-0.7 E = ).o9b PE o 6_ 0.,91.-6.105 Sks)bt�-!"V 0.525S2. t o L i- 0.753 /.07b .t o.SZ5-(2-._5) +0 _ /.07D1 - 0.7 5 1 °/ OE • i -a X 8. (0.c SDS)1)1- CL -12-0 oK By zNisPE-c710ti WIZx35 SEISMIC LOAD = (19.6)0,40 = 0•57a )< /, 5 0 �E.AD Lo�D 1 -D9 (0,95) = 0,/03 lc/ Pry, a. _ Q 5 7 2 (Z3),.._ 13.Z K K.P (i)(►Z)( /.c _ ;5 </a- �r 0. = 5,¢65 (5 23,Z5" ks? = 13.2— = 0,& k5i w = 0.03 GL A 10 3(P2� AA' afghan associates, inc. �G L 7)(!y — "FIG A gh By: Date: 40V, z.007 ENGINEERING Project No.: A 07D 42- 4875 SW Griffith Drive I Suite 300 I Beaverton, OR 97005 . 503.620.3030 I tel 503.620.5539 I fax www.aaieng.com Sheet: L/57 of I T EM - c 2 Mwtoc 0•/ (Z3 ) t 0.527 ( /z) _ /z. 9 — � �b = 0. ( = 30 KS I (7p Fl.f4N6, 4 �` = ( = 3.4 IK S i S 45.6 0,0,3 3.� 0. /4 <I -c _> c) le-- 30 — Lo y coms. G oh EY I4s ?E.cT10N _ 3. I- Z 7� E7 � --ter � k Ga , Z � 0 .40 z i r� ( Pi) (�o) S EE. LC) P' GaH g , 5 (z) i(c) As ( D,44(Z) = o , �� �v A s (ra & AAI afghan associates, inc. A TC L b _.._ 7 A . R n By AS A Date: 1•10V• wd 7 ENGINEERING Aso 4875 SW Griffith Drive Suite 300 I Beaverton, OR � 97005 Project NO.: 503.620.3030 I tel 503.620.5539 I fax www.aaieng.com Sheet: 1— 1 5A of: I ITM #4 CrcoM L/322 WA-LL Lc 4 1 b = 1 4. I (0, 83) = 11.'75 k @ WALL 11.75 - 0.07 / (25. 33 = /0.0 /( 1- 4(y6.0= /4..0 LOAD GOMf3. ) A5cE 1_0S I2.4,3.Z ,i1C. 5, 6 4 8 gc,?. 4 S c=� 8`( INSP5 CT)D1-1 E Q . S 0 .3 (1,0 Sys D 0,7 -0 D.7(2.5) Q _ 4 • 7 ( 2 . 5 ) 0 = 20.4 k (.2 1. 2 ANGLE 27./ TE,ls /O AJ A S - Z 0.95in 2 o 6(30 Trz i- C,x ‘D x 3 /8 A au _ 4i' ANC -,LE IN c.��► -ip, 7= P= 2-0, z 5' 3/� 6,3? - 5)4 r I . Fk0 M TA-r3c,E 7 6 L _ 03.2+2 2, g 2 0 I< Z o i 4 Z -- R�BA� A _ (Z0 �I 2 2 S (Ra&) (0700,9 (Go) = D.toS�� S E_E- Cc r1 . 5 Tit (2) #G A = 0, ci¢(z) Z o, g fn --_ o IL AA afghan associates, inc. r TC $ I_T G, - -r 6.7 Q r) B AR Ak Date: ti f C Z007 • ENGINEERING AD 76e-1 ? 4875 SW Griffith Drive I Suite 300 I Beaverton. OR 1 97005 Project NO.: �+ 503.620.3030 I tel 503.620.5539 I fax www.aaieng.corn Sheet: MS of: 17 M #2-1 FR-0 cM s>< - /e— r FD/s — F 18 1307 5 D /c s `o2E55v2E c 3 4-(5,75 t04 7S-t /• 0) _ F Ps /;M /G = • 1 = q,4 6.5) = 3 97 #1 63•11FgoM . 0 . FTa l - TOTAL s re. 397 t aS5(7, A) +/35.- / ( . F WALL) 7074 -L MOM .NT d 2_55 (2t5__)( C fi 397 (3 -9+ 1 -0) +135 - 2•5) 53.5 F7 — -# 62/67 /A/A -L CA-LCS TOTAL SH6-1< = 32.5(6 ) t 13 5 -- 337, S( _ 2 S D O ( / _ /487 /4 —� c L o - TOTAL MOMENT 135 t 63.2S - 3 2.5(6.5)(3• ; SS) �Z8 Fr —a� > 535 Fr --# (Na t_oaD ci_LI e pF f T6-, Fac orc) TDTA<L Mom eki T I :;5`6,.5) t 397(4-9) t z 5.S(6. 5/) ( ( 3) 4620 Fr_ # o2t67NAL G41-cS. - To TA - L MOMI7 Zb FT —# > AGO 2-0 FT o f ' NO taa � A C rofc) ALL o7HEE? WA-t.LS og 13• StJspsc.TIO4 ;® AA I afghan associates, inc. T C F) — T/67/1 By: A 4: Date: Z4D7 ENGINEERING A � 7 � ` � 4875 SW Griffith Drive I Suite 300 � Beaverton, OR 97005 Project No.: 503.620.3030 I tel 503.620.5539 I fax www.aaieng.com Sheet:_ I of: 3 27EM #'2I RE- 7 /4/klit / 1//A- GL C? 724 L OS ll E • T5_ q.10-4 = 9.�F(6. ti GI c ite. SL-Ae _. 4.1 'f' . I / , CZ 3 4 0.95) 1 , l i $• 67 1 3.85 . 3Sb fsr A (co Ka IT /D 4 1 (kw seismic) SirD /A/C, z - 2 "iI (7 — 3.5b (%) 90 pis - 5/ = 3 . 83 ( 6 .5)( 1 fO) c 29 2.8 C i 7s7( 84 z )(/ 770 - c Z = s.6 ( sp ) = .7S4 tt- 4,44e 4 R, 441g(.35)= /557 C5_ /55 _ 1 73 > x `• a &A MOT = 07 1 ( ✓ 2:4-11-\) _ 255,T-# /> 3 / M _ 2.cf 2.1 (3.08) 770(0.E3) 7$(=Pc) : /;-. F ' P. S. it,p > 1.C" ,> ©) .- AA I afghan associates. inc. A . ts Lac- - ? I C, A g. b B A ' 4 Date: 1)I - G Z 007 ENGINEERING Project No.: � -- 4875 Sw Griffith Drive I Suite 300 I Beaverton, OR 1 97005 _f �► 503.620.3030Ite1 503.620.5539 I fax www.aaieng.com Sheet: G'"' of: J • Cc�I`lDI e (W E/s N9 /c—`) I rz - /5.a7 rs / / - /S >1.10 0.7 A HOT : r-85 - 44g(4.14 t o) S/57 Fr- # s. _ //534 = Z 2. 1. WF��L. l2�li� / lop df LTG / E t I. M a( 4, 14+x) = 4 (44t)(int -r / ( , 95/ j( C% ) S-. 6 r — K Mu = 5 (/2/ q) = 76 .'h — /< g - z — 6 %6 ( ML/ Asia ( S6zs — (00 Arc __ C/;)( / c ? As -- 337,7. 4 a f 3 l' f i I r a .; .. .5 _ c. f 1Y1 /� p #5 @ 4 : -t' 0,c. AA! afghan associates, inc. 4TC B L1)rn — By: Date: 2 c 2M7 ENGINEERING �704Z 4875 SW Griffith Drive I Suite 300 I Beaverton, OR 1 97005 Project No.: 503.620.3030 I tel 503.620.5539 I fax www.aaieng.com Sheet: of: ITEM It 2 '. • 5H- R-iewf -I-I S 0.) c-, 1?-1D D • D)57. O F . Lt47. (SvJ PLALIE WALL) &ET v EEI./ 5H /Z P'A -u5 7 A L wt. _ (I Z) (i$)( 3G,7 + 3(22)) + 50002. ?5) = 101.3 S5-1S. FoRLF = 101 (.081) _ 8.2)G SEF_ LPrT CA-1...C.. / wA - LL w l • DTH /. TO LA/,4LL W -LL G 12'(g) rzoaF(k) L3 6.0 36,Z 5.0 1,,6 L¢ 3.33 - 7 , - 7 2 . ■ n - G, 0, L- lo ap . 67 4-I1.4 4.0 • 2 • ( SHEF ZWAL.L L• 6114' 5 l RooP I) WkU Inl+. 7. ( = 12 -gK j. Co r ._. 2 ) 1/1/A - 4/1-- En.)-L. . _ ( 2 � 1., 14 - 3 K r. . - vvA L 4) { . -Ff`om _ ("1g)(q +11) 12)t 5D(20)+ / �'wau + Iz � i.rc-i� , • i �TE-L B ERM bt u. 5 . l5 (9)(12) + 15(8)(25) : S - 5 1p 4.3k FTC-, k)-1. ,- (:5)(I)(.I .$)02- = 5,4 K 1.41( _ 3.0 K . C A ; c 1,1 t)1) 2 5 5"K t . 4 1 7 4 - . - 1 4 . 4 1c 'MCAT I4(?- x,3$) 1`4 C13,1)t 3` (!'1a ) gl,; FT 1C 13:33 1'1 re , o, ,+ 1r:. .6.�_I. �7, -r-K 2S.S - ow- //2. -K 4 � 3 @5, c.o�Dz) I v -- M07 1•c( 23,30 +1.4(1(4.1) t x , (1 % 101 F7 -1( A MR = 0. (Co) .4- 4,(4.67 -K 2.”fT_ K- o- 444 44.6 c91L P�zE5.ur _, c.,�,D z.) T 1= 6 , 9 �� 1 6 ) = 3. - ‹ et4k M; , = 1 x71 + 4, 3 (1 3 -) 10'7 1c T K. C 107 z 2.43 13/6 z 1 ZF�r - 2-- S r►- ,o.. - - 2.71 - k s F > 2..C.:77 ks ( -. c../.04/E_ F 7c TO 13 3( •5)( /2 - 2 (�� 2.43 ' AA afghan associates, inc. )47e- 81_1)61- T/ A / ) 2) _,.-E C. By: Ag A D a te :AM 2'00 7 ENGINEERING • xx .r 4875 SW Grffil Dive ve I Suite 300 I Beaverton, OR 1 97005 Project No.: T o70 �r Z 503.620.3030 1 tel 503.620.5539 1 fax /� www.aeieng.com Sheet: PD/2 of: 1TE M 1. fTG, w (3) (►)(o./s) (/_ = s ss M= 107 PT -K z_'P 0,5 as) 6 1\44 = o7 / / 4 43,1 -4 _ Z ►vI _ 4(45,4) = z- l <sf < z- �7 k sF (.3)(3(/3- 2( )) AA! alghan associates, inc. ATE L)G - T /G A{z.D By: A'.M Date: 2007 ENGINEERING 4875 SW Griffith Drive I Suite 300 I Beaverton, OR t 97005 Project ND.: 503.620.3030 I tel 503.620.5539 I fax /� /� www.aaieng.com Sheet: of: ITEM * 2 51ArtwA -u.. L. 647 rTt,, IJ . =(3) (1)(•IS) = S�?K rtnl�r= 5 P iz-oK 1) k LL LAA. = l0, 107 (-Ss) ( 2 ,7.. z•I IG ►. pw,eu, I �,Z z) WALL W6 = -o (70 (2�. 63) _ 5.5 )A �• (' i A wmu. r2oM _ `'7b) (t( +51(1 =►n,01 LIt.JTEIL $FA• • LIN 7 ( -^— 4 • 6K -- Dr— M•�, ,I 3 13.3 1 _ _ puN t10‘9K ,, T� 2 (22 3)-t-I 7(13. - 3) =1woFr I3.3, MR 0,9 L (2 t 14 Z t 1 a,9)((e,(, - 7/7.'t 3,5 (5)' _ 91 FT - K - `I � 2.9 K 3 3 4 o, .I 61 () S �. s; coklb z • I` o-r r Z.1 (23•.1) t- 1.43(14.7 + 4(1433) 12E5 F7 —K MP' o,9 i.14- 5,'7)(6, 3,5(01 29(3) Z2o 1--- Sol L 'P 2C �� � IZ� SolL$ t,J.. = (2.3) (1 C. II) (I2•(o1) = 4,3K @ c • M 12£5 —I. 6 (0?) 2.9(3'33) s 1 35 P ° o 9 (39, 2 1-4.5) 3914 e: /35739 3...410 > B/6 - 1 ` "�� = z• +'kcc 4(^3° 5.0 > 2.1-0 ksF --a kJ Cob 3(3) (I 2.007— (S 0} A-14c1 E FTC, TO /3• (7 . f 2.0 M /2.61 C3 FROM E /CN s (DE) SOILS = 4,3 15 -v - 4.(K �Z•1o7�� : m AAI afghan associates, inc. L 1- h — 776 A RI) B A Ji' A Date: it Pfz 'v o7 ENGINEERING Project No.: A -7 04 - Z— 4875 SW Griffith Drive I Suite 300 1 Beaverton, OR 1 97005 503.620.3030 1 tel 503.620.5539 1 fax w Sheet: FD/3 w.aaieng.com of: ITEM # 2.7 Er= 0.9 ((.Z. 14.2 +3.5 t10-94 Z-91-2.0 +4.() = 39 .9K •e 135- L3.3a 39.1 arc = 4 (39% _ _ 2.5 )NSF <2..67 k s f (3)(3X13 z(3. AAI afghan associates, inc. A TC L 17C� - "r icsikg By: Date: t4O V- 21)0 7 ENGINEERING Project No.: AD7o4{ -Z 4875 SW Griffith Drive 1 Suite 300 1 Beaverton, OR 1 97005 _ 503.620.3030 1 tel 503.620.5539 1 fax y '� www.aaieng.com Sheet: of: i fr1# - CFS Version 5.0.2 Section: Section 2.sct Chemelle Stark • Panel 1.5x3.5x2 @6 -20 Gage AAI Engineering, Inc. Rev. Date: 12/5/2007 8:42:23 AM By: Chemelle Stark Section Inputs Material: A653 SS Grade 33 No strength increase from cold work of forming. Modulus of Elasticity, E 29500 ksi" Yield Strength, Fy 33 ksi Tensile Strength, Fu 45 ksi Warping Constant Override, Cw 0'in ^6 Torsion Constant Override, J 0 in ^4 Panel, Thickness 0.0346 in (20 Gage) Placement of Part from Origin: X to center of gravity 0 in Y to center of gravity 0 in Centerline dimensions, Open shape Length Angle Radius Web k Hole Size Distance (in) (deg) (in) Coef. (in) (in) 1 1.7500 75.000 0.076400 None 0.000 0.0000 0.8750 2 3.5000 0.000 0.076400 Single 0.000 0.0000 1.7500 3 1.5529 - 75.000 0.076400 Deck 0.000 0.0000 0.7765 4 1.6962 0.000 0.076400 None 0.000 0.0000 0.8481 5 1.5529 75.000 0.076400 Deck 0.000 0.0000 0.7765 6 3.5000 0.000 0.076400 Single 0.000 0.0000 1.7500 7 1.5529 - 75.000 0.076400 Deck 0.000 0.0000 0.7765 8 1.6962 0.000 0.076400 None 0.000 0.0000 0.8481 9 1.5529 75.000 0.076400 Deck 0.000 0.0000 0.7765 10 3.5000 0.000 0.076400 Single 0.000 0.0000 1.7500 11 1.5529 - 75.000 0.076400 Deck 0.000 0.0000 0.7765 12 1.7500 0.000 0.076400 None 0.000 0.0000 0.8750 �L Z 'PsF S L = ZS ('sF L - s 0 @ Cn l2- ID L 1 1 , 1 E '7 Ccom LO�r GOMFj, ( A-LT. 6�SIG) + - r E /i-4 13A slc ,d D t D,7 g f f c 0 $T2Ess; W1 D L/FT = ZDcS 7- -6, z•s FT-4 14O.6.3ItT- = 1• < 11 -K. M ar l = 2 5(9. DA ="/ .I FT -# / (0'• 450 )C i .4) z o (� K smoor c15/ vr_/6/A/a -c, 6-a-c. 6.5) / of I TE M #.32_ CFS Version 5.0.2 Section: Section 2.sct Chemelle Stark Panel 1.5x3.5x2 @6 -20 Gage AAI Engineering, Inc. Rev. Date: 12/5/2007 8:42:23 AM By: Chemelle Stark Member Check - 2004 North American Specification - US (ASD) Design Parameters: Lx 5.0000 ft Ly 5.0000 ft Lt 5.0000 ft Kx 1.0000 Ky 1.0000 Kt 1.0000 Cbx 1.0000 Cby 1.0000 ex 0.0000 in Cmx 1.0000 Cmy 1.0000 ey 0.0000 in Braced Flange: None Moment Reduction, R: 0.0000 Loads: P Mx Vy My Vx (k) (k -in) (k) (k -in) (k) Entered 0.6300 1.690 • 0.1125 0.000 0.0000 Applied 0.6300 1.690 0.1125 0.000 0.0000 Strength 5.1432 5.707 2.9140 32.159 3.2147 • Effective section properties at applied loads: Ae 0.86238 in ^2 Ixe 0.345 in ^4 Iye 24.080 in ^4 Sxe(t) 0.5619 in ^3 Sye(l) 2.7420 in ^3 Sxe(b) 0.3137 in ^3 Sye(r) 2.5783 in ^3 Interaction Equations NAS Eq. C5.2.1 -1 (P, Mx, My) 0.122 + 0.309 + 0.000 7'0.431 <= 1.0 \, NAS Eq. C5.2.1 -2 (P, Mx, My) 0.095 + 0.296 + 0.000 F 0.391 <= 1.0 NAS Eq. C3.3.1 -1 (Mx, Vy) Sqrt(0.088 + 0.001),' 0.299 <= 1.0 r NAS Eq. C3.3.1 -1 (My, Vx) Sqrt(0.000 + 0.000)= 0.000 <= 1.0 Panel element 2 w/t exceeds 60. Edge stiffener D/w exceeds 0.8. Calculation Details - 2004 North American Specification - US (ASD) Axial Load Eccentricity, P =0.63 k Effective width calculations for part 1: Panel Element 1: Unstiffened, w= 1.6781 in f1= 0.73054 ksi, f2= 0.73054 ksi y, =1 NAS Eq. B3.2 -1 k =0.43 NAS Eq. B3.2 -3 . X= 0.3872 NAS Eq. B2.1 -4 X <0.673 (fully effective) NAS Eq. B2.1 -1 Elements 2 to 10: NAS Section B5.1 - Multiple Intermediate Stiffeners bo= 15.356 in, bp= 3.3562 in kloc =83.74 NAS Eq. B5.1.2-1 0= 9.8998 NAS Eq. B5.1.2 -3 kd= 107.25 NAS Eq. B5.1.2-2 R =0.5 NAS Eq. B5.1 -8 k= 53.625 NAS Eq. B5.1 -6 f1= 0.73054 ksi Fcr= 7.2586 ksi NAS Eq. B5.1 -5 X =0.31724 NAS Eq. B5.1 -4 p =1 (fully effective) NAS Eq. B5.1 -2 Element 12: Unstiffened, w= 1.6781 in f1=0.73054 ksi, f2= 0.73054 ksi W =1 NAS Eq. B3.2 -1 k =0.43 NAS Eq. B3.2 -3 X= 0.3872 NAS Eq. B2.1 -4 Z F ITEMi3Z CFS Version 5.0.2 Section: Section 2.sct Chemelle Stark Panel 1.5x3.5x2 @6 -20 Gage AAI Engineering, Inc. Rev. Date: 12/5/2007 8:42:23 AM By: Chemelle Stark /,. <0.673 (fully effective) NAS Eq. B2.1 -1 Element 11: Check for lip stiffener reduction S= 257.22 NAS Eq. B4 -1 w/t < 0.328S (no lip reduction) Element 11: Stiffened, w= 1.4091 in f1= 0.73054 ksi, f2= 0.73054 ksi 4f=1 NAS Eq. B2.3 -1 k =4 NAS Eq. B2.3 -8 X=0.1066 NAS Eq. B2.1 -4 p =1 NAS Eq. B2.1 -3 be= 1.4091 in NAS Eq. B2.1 -2 b1= 0.70456 in NAS Eq. B2.3 -9 b2= 0.70456 in NAS Eq. B2.3 -10 b1 +b2 > compression width (fully effective) Center of gravity shift: x =0 in, y =0 in Initial eccentricity: x =0 in, y =0-in Specified eccentricity: x =0 in, y =0 in Overall eccentricity: x =0 in, y =0 in Additional moments: My =O k -in, Mx =0 k -in Axial Compression Strength (KL /r)x= 94.91, (KL /r)y= 11.355 ax= 32.322 ksi NAS C3.1.2.1 -6 ay= 2258.3 ksi NAS C3.1.2.1 -7 at= 36.536 ksi NAS C3.1.2.1 -8 Fe =31.41 ksi Fy =33 ksi %c =1.025 NAS C4 -4 Fn= 21.259 ksi NAS C4 -2 Effective width calculations for part 1: Panel Element 1: Unstiffened, w= 1.6781 in f1= 21.259 ksi, f2= 21.259 ksi y, =1 NAS Eq. B3.2 -1 k =0.43 NAS Eq. B3.2 -3 X= 2.0887 NAS Eq. B2.1 -4 p= 0.42833 NAS Eq. B2.1 -3 b= 0.71879 in (ineffective width = 0.95932 in) NAS Eq. B2.1 -2 Elements 2 to 10: NAS Section B5.1 - Multiple Intermediate Stiffeners bo= 15.356 in, bp= 3.3562 in kloc =83.74 NAS Eq. B5.1.2-1 (3= 9:8998 NAS Eq. B5.1.2-3 kd= 107.25 NAS Eq. B5.1.2-2 R =0.5 _ NAS Eq. B5.1 -8 k= 53.625 NAS Eq. B5.1 -6 f1= 21.259 ksi Fcr= 7.2586 ksi NAS Eq. B5.1 -5 2,= 1.7114 NAS Eq. B5.1 -4 p= 0.50921 NAS Eq. B5.1 -3 be= 10.078 in NAS Eq. B5.1 -1 Element 12: Unstiffened, w= 1.6781 in f1= 21.259 ksi, f2= 21.259 ksi 4, =1 NAS Eq. B3.2 -1 k =0.43 NAS Eq. B3.2 -3 3 0 F • 1 I TI»1 31 . CFS Version 5.0.2 Section: Section 2.sct Chemelle Stark Panel 1.5x3.5x2 @6 -20 Gage AA! Engineering, Inc. Rev. Date: 12/5/2007 8:42:23 AM By: Chemelle Stark • k= 2.0887 NAS Eq. B2.1 -4 p= 0.42833 NAS Eq. B2.1 -3 b= 0.71879 in (ineffective width = 0.95932 in) NAS Eq. B2.1 -2 Element 11: Check for lip stiffener reduction S= 47.682 NAS Eq. B4 -1 la= 8.328e -5 in ^4 NAS Eq. B4.2 -10 Is= 0.012713 in "4 > la (no lip reduction) k =0.43 NAS Table B4.2 Element 11: Partially stiffened, w= 1.4091 in f= 21.259 ksi, k =0.43 X= 1.7539 NAS Eq. B2.1 -4 p= 0.49863 NAS Eq. B2.1 -3 b= 0.70263 in (ineffective width = 0.70648 in) NAS Eq. B2.1 -2 b1= 0.35132 in, b2= 0.35132 in Ae= 0.43547 in ^2 Pn= 9.2577 k NAS C4 -1 Oc =1.8, 4c =0.85 Flexural Strength about X -axis 6y= 2258.3 ksi NAS C3.1.2.1 -7 6t= 36.536 ksi NAS C3.1.2.1 -8 Ctf =1 NAS C3.1.2.1 -10 Fy =33 ksi Fe =17584 ksi NAS C3.1.2.1 -5 Fc =33 ksi Not subject to lateral - torsional buckling - same as fully braced strength Flexural Strength about Y -axis 6x= 32.322 ksi NAS C3.1.2.1 -6 6t= 36.536 ksi NAS C3.1.2.1 -8 Ctf =1 NAS C3.1.2.1 -10 Fy =33 ksi • Fe =65.43 ksi NAS C3.1.2.1 -5 Fc =31.53 ksi NAS C3.1.2.1 -2 Effective width calculations for part 1: Panel Element 1: No compressive stress (fully effective) Element 2: No compressive stress (fully effective) Element 3: No compressive stress (fully effective) Element 4: No compressive stress (fully effective) Element 5: No compressive stress (fully effective) Element 6: Stiffened, w= 3.3562 in f1= 6.4751 ksi, f2 =- 3.7498 ksi w= 0.57911 NAS Eq. B2.3 -1 k= 15.034 NAS Eq. B2.3 -2 X= 0.38992 NAS Eq. B2.1 -4 p =1 NAS Eq. B2.1 -3 be= 3.3562 in NAS Eq. B2.1 -2 ho =3.5 in, bo= 1.5529 in, ho /bo= 2.2538 b1= 0.93772 in NAS Eq. B2.3 -3 b2= 1.6781 in NAS Eq. B2.3 -4 Compression width = 2.1254 in b14-b2 > compression width (fully effective) Element 7: Stiffened, w= 1.4091 in f1 =7.862 ksi, f2= 6.7509 ksi Is I TEM 43 CFS Version 5.0.2 Section: Section 2.sct Chemelle Stark Panel 1.5x3.5x2 @6 -20 Gage AAI Engineering, Inc. Rev. Date: 12/5/2007 8:42:23 AM By: Chemelle Stark yr= 0.85867 NAS Eq. B2.3 -1 k= 4.2883 NAS Eq. B2.3 -8 X= 0.33775 NAS Eq. B2.1 -4 p =1 NAS Eq. B2.1 -3 be= 1.4091 in NAS Eq. B2.1 -2 b1= 0.65806 in NAS Eq. B2.3 -9 b2= 0.75106 in NAS Eq. B2.3 -10 b1 +b2 > compression width (fully effective) Element 8: Stiffened, w= 1.5524 in f1= 12.867 ksi, f2= 8.1377 ksi yr= 0.63244 NAS Eq. B2.3 -1 k= 4.8344 NAS Eq. B2.3 -8 k=0.44832 NAS Eq. B2.1 -4 p =1 NAS Eq. B2.1 -3 be= 1.5524 in NAS Eq. B2.1 -2 b1= 0.65568 in NAS Eq. B2.3 -9 b2= 0.89668 in NAS Eq. B2.3 -10 b1 +b2 > compression width (fully effective) Element 9: Stiffened, w= 1.4091 in f1= 14.254 ksi, f2= 13.143 ksi yi =0.92205 NAS Eq. B2.3 -1 k= 4.1568 NAS Eq. B2.3 -8 ?.= 0.46191 NAS Eq. B2.1 -4 p =1 NAS Eq. B2.1 -3 be =1.4091 in NAS Eq. B2.1 -2 b1 =0.67813 in NAS Eq. B2.3 -9 b2 =0.73099 in NAS Eq. B2.3 -10 b1 +b2 > compression width (fully effective) Element 10: Stiffened, w= 3.3562 in f1= 24.755 ksi, f2 =14.53 ksi y, =0.58695 NAS Eq. B2.3 -1. k =4.967 NAS Eq. B2.3 -8 2.= 1.3263 NAS Eq. B2.1 -4 p= 0.62889 NAS Eq. B2.1 -3 be= 2.1107 in NAS Eq. B2.1 -2 b1= 0.8747 in NAS Eq. B2.3 -9 b2 =1.236 in NAS Eq. B2.3 -10 Ineffective width = 1.2455 in Element 12: Unstiffened, w= 1.6781 in f1 =31.53 ksi, f2= 26.417 ksi yr =0.83785 NAS Eq. B3.2 -1 k =0.44319 NAS Eq. B3.2 -3 ?.= 2.5056 NAS Eq. B2.1 -4 p= 0.36406 NAS Eq. B2.1 -3 b= 0.61094 in (ineffective width = 1.0672 in) NAS Eq. B2.1 -2 Element 11: Check for lip stiffener reduction S= 42.999 NAS Eq. B4 -1 la= 0.00013572 inA4 NAS Eq. B4.2 -10 Is= 0.012713 inA4 > la (no lip reduction) k =0.43 NAS Table B4.2 Element 11: Partially stiffened, w= 1.4091 in f= 26.142 ksi, k =0.43 X= 1.9449 NAS Eq. B2.1 -4 p =0.456 NAS Eq. B2.1 - b =0.64255 in (ineffective width = 0.76657 in) NAS Eq. B2.1 -2 Of C7 17E'i #3Z CFS Version 5.0.2 Section: Section 2.sct Chemelle Stark Panel 1.5x3.5x2 @6 -20 Gage AA! Engineering, Inc. Rev. Date: 12/5/2007 8:42:23 AM By: Chemelle Stark b1= 0.32128 in, b2= 0.32128 in Center of gravity shift: x =- 1.0098 in Sc= 1.7033 in ^3 Mn= 53.705 k -in NAS C3.1.2.1 -1 f b =1.67, Ob =0.9 • Compression and Bending Interaction ax= 0.95932 NAS C5.2.1 -4 ay= 0.99942 NAS C5.2.1 -5 Effective section at applied loads Effective width calculations for part 1: Panel Element 1: Unstiffened, w= 1.6781 in f1= 3.3131 ksi, f2 =- 4.6352 ksi y=1 .3991 NAS Eq. B3.2 -1 4, >1 (fully effective) NAS Eq. B2.1 -1 Element 2: Check for lip stiffener reduction Element 2: Stiffened, w= 3.3562 in f1= 3.6536 ksi, f2= 3.6536 ksi y, =1 NAS Eq. B2.3 -1 k =4 NAS Eq. B2.3 -8 X=0.56782 NAS Eq. B2.1 -4 p = 1 NAS Eq. B2.1 -3 be= 3.3562 in NAS Eq. B2.1 -2 b1= 1.6781 in NAS Eq. B2.3 -9 b2= 1.6781 in NAS Eq. B2.3 -10 b1 +b2 > compression width (fully effective) Element 3: Stiffened, w= 1.4091 in f1= 3.3131 ksi, f2 =- 3.3611 ksi yr= 1.0145 NAS Eq. B2.3 -1 k =24.38 NAS Eq. B2.3 -2 Z= 0.091955 NAS Eq. B2.1 -4 p =1 NAS Eq. B2.1 -3 be= 1.4091 in . NAS Eq. B2.1 -2 ho= 1.5529 in, bo =3.5 in, hobo= 0.44369 b1= 0.35101 in NAS Eq. B2.3 -3 b2= 0.70456 in NAS Eq. B2.3 -4 Compression width = 0.69948 in b1 +b2 > compression width (fully effective) Element 4: No compressive stress (fully effective) Element 5: Stiffened, w= 1.4091 in f1= 3.3131 ksi, f2 =- 3.3611 ksi yr= 1.0145 NAS Eq. B2.3 -1 k =24.38 NAS Eq. B2.3 -2 ?= 0.091955 NAS Eq. 62.1 -4 p =1 NAS Eq. B2.1 -3 be= 1.4091 in NAS Eq. B2.1 -2 ho= 1.5529 in, bo =3.5 in, hobo= 0.44369 b1= 0.35101 in NAS Eq. B2.3 -3 b2= 0.70456 in NAS Eq. B2.3 -4 Compression width = 0.69948 in b1 +b2 > compression width (fully effective) Element 6: Stiffened, w= 3.3562 in f1= 3.6536 ksi, f2= 3.6536 ksi 6 Cf r 1 7EM # 3Z CFS Version 5.0.2 Section: Section 2.sct Chemelle Stark Panel 1.5x3.5x2 @6 -20 Gage AA! Engineering, Inc. Rev. Date: 12/5/2007 8:42:23 AM By: Chemelle Stark yf =1 NAS Eq. B2.3 -1 k =4 NAS Eq. B2.3 -8 X= 0.56782 NAS Eq. B2.1 -4 p =1 NAS Eq. B2.1 -3 be= 3.3562 in NAS Eq. B2.1 -2 b1= 1.6781 in NAS Eq. B2.3 -9 b2= 1.6781 in NAS Eq. B2.3 -10 b1 +b2 > compression width (fully effective) Element 7: Stiffened, w= 1.4091 in f1= 3.3131 ksi, f2 =- 3.3611 ksi yr= 1.0145 NAS Eq. B2.3 -1 k =24.38 NAS Eq. B2.3 -2 X=0.091955 NAS Eq. B2.1 -4 p =1 NAS Eq. B2.1 -3 be= 1.4091 in NAS Eq. B2.1 -2 ho= 1.5529 in, bo =3.5 in, ho /bo= 0.44369 b1= 0.35101 in NAS Eq. B2.3 -3 b2= 0.70456 in NAS Eq. B2.3 -4 Compression width = 0.69948 in b1 +b2 > compression width (fully effective) Element 8: No compressive stress (fully effective) Element 9: Stiffened, w= 1.4091 in f1= 3.3131 ksi, f2 =- 3.3611 ksi w= 1.0145 NAS. Eq. B2.3 -1 k =24.38 NAS Eq. B2.3 -2 X= 0:091955 NAS Eq. B2.1 -4 p =1 NAS Eq. B2.1 -3 be= 1.4091 in NAS Eq. B2.1 -2 ho= 1.5529 in, bo =3.5 in, ho/bo = 0.44369 b1= 0.35101 in NAS Eq. B2.3 -3 b2=0.70456 in NAS Eq. B2.3 -4 Compression width = 0.69948 in b1 +b2 > compression width (fully effective) Element 10: Stiffened, w= 3.3562 in f1= 3.6536 ksi, f2= 3.6536 ksi W =1 NAS Eq. B2.3 -1 k =4 NAS Eq. B2.3 -8 ).= 0.56782 NAS Eq. B2.1 -4 p =1 NAS Eq. B2.1 -3 be= 3.3562 in NAS Eq. B2.1 -2 b1= 1.6781 in NAS Eq. B2.3 -9 b2= 1.6781 in NAS Eq. B2.3 -10 b1 +b2 > compression width (fully effective) Element 12: No compressive stress (fully effective) Element 11: Stiffened, w= 1.4091 in f1= 3.3131 ksi, f2 =- 3.3611 ksi yf= 1.0145 NAS Eq. B2.3 -1 k =24.38 NAS Eq. B2.3 -2 ?.= 0.091955 NAS Eq. B2.1 -4 p =1 NAS Eq. B2.1 -3 be= 1.4091 in NAS Eq. B2.1 -2* ho= 1.5529 in, bo =3.5 in, ho/bo = 0.44369 b1= 0.35101 in NAS Eq. B2.3 -3 b2= 0.70456 in NAS Eq. B2.3 -4 Compression width = 0.69948 in 7 of °i ITEM * 32. • CFS Version 5.0.2 Section: Section 2.sct Chemelle Stark Panel 1.5x3.5x2 @6 -20 Gage AAI Engineering, Inc. Rev. Date: 12/5/2007 8:42:23 AM By: Chemelle Stark b1 +b2 > compression width (fully effective) c I 176M #3Z 1 )/7 /r 'r I /71Ii ,✓taPDLE G; 0 ,eoo f DECK = 7c ,-;,7(1.. (a) ,q F %7r c. rC E cF / -.: Cv Pr, - c 1. , '1�r e fit G ,S SMC. 4 ` ( 0 3¢6) = Zeg / 2' 71 ( 5. �► = i (' 275) z, . 4' /S)(7e) = 121C ' (b) E;111 /1/z r77ee N6 T r1 OC /vi%77 J' / %r. , °1 <<1a /t/C; ‘;')1:7 1 61, ' (t' f.) _ , l "" , - , y 54 / , � l = o -E /a - c 2 . 2 (0 )(4 !, e— ) ' E i t/ (pc (r /f (f / r"77 Nor /'/fl - (/ /ry . If I Ci-l/!''V • /'6k &cat 7 f V " /5 `' f%` fL zz 1'///(.. 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