prEN_13001_3_1_2010
Description
EUROPEAN STANDARDNORME EUROPÉENNE DRAFT prEN 13001-3-1 EUROPÄISCHE NORM July 2010 ICS 53.020.20 English Version Cranes - General Design - Part 3-1: Limit States and proof competence of steel structure Appareils de levage à charge suspendue - Conception générale - Partie 3-1: Etats limites et vérification d'aptitude des structures en acier Krane - Konstruktion allgemein - Teil 3-1: Grenzzustände und Sicherheitsnachweis von Stahltragwerken This draft European Standard is submitted to CEN members for second enquiry. It has been drawn up by the Technical Committee CEN/TC 147. If this draft becomes a European Standard, CEN members are bound to comply with the CEN/CENELEC Internal Regulations which stipulate the conditions for giving this European Standard the status of a national standard without any alteration. This draft European Standard was established by CEN in three official versions (English, French, German). A version in any other language made by translation under the responsibility of a CEN member into its own language and notified to the CEN Management Centre has the same status as the official versions. CEN members are the national standards bodies of Austria, Belgium, Bulgaria, Croatia, Cyprus, Czech Republic, Denmark, Estonia, Finland, France, Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland and United Kingdom. Recipients of this draft are invited to submit, with their comments, notification of any relevant patent rights of which they are aware and to provide supporting documentation. Warning : This document is not a European Standard. It is distributed for review and comments. It is subject to change without notice and shall not be referred to as a European Standard. EUROPEAN COMMITTEE FOR STANDARDIZATION COMITÉ EUROPÉEN DE NORMALISATION EUROPÄISCHES KOMITEE FÜR NORMUNG Management Centre: Avenue Marnix 17, B-1000 Brussels © 2010 CEN All rights of exploitation in any form and by any means reserved worldwide for CEN national Members. Ref. No. prEN 13001-3-1:2010: E prEN 13001-3-1:2010 (E) Contents Page Foreword ..............................................................................................................................................................4 Introduction .........................................................................................................................................................5 1 Scope ......................................................................................................................................................5 2 Normative references ............................................................................................................................5 3 Terms and definitions ...........................................................................................................................7 4 4.1 4.2 4.2.1 4.2.2 4.3 4.3.1 4.3.2 4.3.3 4.3.4 4.3.5 4.4 4.5 4.6 General ................................................................................................................................................. 10 Documentation .................................................................................................................................... 10 Materials for structural members ...................................................................................................... 11 Grades and qualities .......................................................................................................................... 11 Impact toughness ............................................................................................................................... 13 Bolted connections............................................................................................................................. 14 Bolt materials ...................................................................................................................................... 14 General ................................................................................................................................................. 14 Shear and bearing connections ........................................................................................................ 15 Friction grip type (slip resistant) connections ................................................................................ 15 Connections loaded in tension ......................................................................................................... 15 Pinned connections ............................................................................................................................ 15 Welded connections ........................................................................................................................... 15 Proof of competence for structural members and connections .................................................... 16 5 5.1 5.2 5.2.1 5.2.2 5.2.3 5.2.4 5.2.5 5.3 5.3.1 5.3.2 5.3.3 5.3.4 Proof of static strength ...................................................................................................................... 16 General ................................................................................................................................................. 16 Limit design stresses and forces ...................................................................................................... 17 General ................................................................................................................................................. 17 Limit design stress in structural members ...................................................................................... 17 Limit design forces in bolted connections ...................................................................................... 18 Limit design forces in pinned connections ..................................................................................... 26 Limit design stresses in welded connections ................................................................................. 30 Execution of the proof ........................................................................................................................ 32 Proof for structural members ............................................................................................................ 32 Proof for bolted connections............................................................................................................. 32 Proof for pinned connections............................................................................................................ 33 Proof for welded connections ........................................................................................................... 33 6 6.1 6.2 6.2.1 6.2.2 6.2.3 6.3 6.3.1 6.3.2 6.3.3 6.3.4 6.4 6.5 6.5.1 6.5.2 6.5.3 Proof of fatigue strength .................................................................................................................... 34 General ................................................................................................................................................. 34 Limit design stresses ......................................................................................................................... 35 Characteristic fatigue strength.......................................................................................................... 35 Weld quality ......................................................................................................................................... 37 Requirements for fatigue testing ...................................................................................................... 38 Stress histories ................................................................................................................................... 38 General ................................................................................................................................................. 38 Frequency of occurence of stress cycles ........................................................................................ 39 Stress history parameter ................................................................................................................... 39 Stress history classes S .................................................................................................................... 40 Execution of the proof ........................................................................................................................ 41 Determination of the limit design stress range ............................................................................... 42 Applicable methods ............................................................................................................................ 42 Direct use of stress history parameter ............................................................................................. 42 Use of class S...................................................................................................................................... 42 2 prEN 13001-3-1:2010 (E) 6.5.4 Independent concurrent normal and/or shear stresses .................................................................. 44 7 Proof of static strength of hollow section girder joints .................................................................. 44 8 8.1 8.2 8.2.1 8.2.2 8.3 8.3.1 8.3.2 Proof of elastic stability ...................................................................................................................... 44 General ................................................................................................................................................. 44 Lateral buckling of members loaded in compression ..................................................................... 45 Critical buckling load .......................................................................................................................... 45 Limit compressive design force ........................................................................................................ 46 Buckling of plate fields subjected to compressive and shear stresses ........................................ 48 General ................................................................................................................................................. 48 Limit design stress with respect to longitudinal stress σ x ............................................................ 49 8.3.3 Limit design stress with respect to transverse stress σ y .............................................................. 51 8.3.4 8.4 8.4.1 8.4.2 Limit design stress with respect to shear stress τ ......................................................................... 53 Execution of the proof ........................................................................................................................ 54 Members loaded in compression ...................................................................................................... 54 Plate fields ............................................................................................................................................ 54 Annex A (informative) Limit design shear force Fv,Rd per fit bolt and per shear plane for multiple shear plane connections .................................................................................................................... 56 Annex B (informative) Preloaded bolts ........................................................................................................... 57 Annex C (normative) Design weld stress σW,Sd and τW,Sd ............................................................................. 59 C.1 Butt joint ............................................................................................................................................... 59 C.2 Fillet weld ............................................................................................................................................. 60 C.3 T-joint with full and partial penetration ............................................................................................. 61 C.4 Effective distribution length under concentrated load .................................................................... 61 Annex D (normative) Values of slope constant m and characteristic fatigue strength ∆σc, ∆τc.............. 63 Annex E (normative) Calculated values of limit design stress range ∆σRd ................................................. 82 Annex F (informative) Evaluation of stress cycles (example) ..................................................................... 84 Annex G (informative) Calculation of stiffnesses for connections loaded in tension ............................... 86 Annex H (informative) Hollow Sections ......................................................................................................... 89 Annex I (informative) Selection of a suitable set of crane standards for a given application ............... 101 Annex ZA (informative) Relationship between this European Standard and the Essential Requirements of EU Directive 98/37/EC .......................................................................................... 102 Annex ZB (informative) Relationship between this European Standard and the Essential Requirements of EU Directive 2006/42/EC ...................................................................................... 103 Bibliography .................................................................................................................................................... 104 Selection of literature that contains information about Hot Spot Stress Method: .................................. 104 3 F. Annexes A. B. D and E are normative. and supports essential requirements of EU Directive(s). see informative Annex ZA and ZB. 4 . This document has been prepared under a mandate given to CEN by the European Commission and the European Free Trade Association. the secretariat of which is held by BSI. For relationship with EU Directive(s). which is an integral part of this document. G. This document is currently submitted to the second CEN Enquiry. The other parts are as follows: Part 1: General principles and requirements Part 2: Load actions Part 3-2: Limit states and proof of competence of wire ropes in reeving systems Part 3-3: Limit states and proof of competence of wheel/rail contacts Part 3-4: Limit states and proof of competence of machinery Part 3-5: Limit states and proof of competence of forged hooks Annexes C. H and I are informative. CEN shall not be held responsible for identifying any or all such patent rights.prEN 13001-3-1:2010 (E) Foreword This document (prEN 13001-3-1:2010) has been prepared by Technical Committee CEN/TC 147 “Cranes Safety”. Attention is drawn to the possibility that some of the elements of this document may be the subject of patent rights. This European Standard is one Part of EN 13001 Cranes – General Design. hazardous situations and events are covered are indicated in the scope of this standard. Eurocode 3: Design of steel structures – Part 1-8: Design of joints EN 10045-1:1989. as amended. For undated references. requirements and methods to prevent mechanical hazards of cranes by design and theoretical verification. Metallic materials. For dated references. This European Standard is not applicable to cranes which are manufactured before the date of its publication as EN and serves as reference base for the European Standards for particular crane types (see Annex I). The machinery concerned and the extent to which hazards. only the edition cited applies. Charpy impact test — Part 1: Test method EN 10025-1:2004. This standard also establishes interfaces between the user (purchaser) and the designer. the latest edition of the referenced document (including any amendments) applies. the provisions of this type C standard take precedence over the provisions of the other standards. Hot rolled products of structural steels — Part 1: General technical delivery conditions 5 . EN 1990:2002. bulging). This European Standard is a type C standard as stated in EN ISO 12100-1. ultimate. c) Elastic instability of the crane or its parts (buckling. fatigue). for machines that have been designed and built according to the provisions of this type C standard. Clauses 4 to 8 of this standard are necessary to reduce or eliminate risks associated with the following hazards: a) Exceeding the limits of strength (yield. The following is a list of significant hazardous situations and hazardous events that could result in risks to persons during intended use and reasonably foreseeable misuse. b) Exceeding temperature limits of material or components. as well as between the designer and the component manufacturer. When provisions of this type C standard are different from those which are stated in type A or B standards. Eurocode — Basis of structural design EN 1993-1-8:2005. NOTE Specific requirements for particular types of crane are given in the appropriate European Standard for the particular crane type. in order to form a basis for selecting cranes and components.prEN 13001-3-1:2010 (E) Introduction This European Standard has been prepared to be a harmonized standard to provide one means for the mechanical design and theoretical verification of cranes to conform with the essential health and safety requirements of the Machinery Directive. NOTE 2 EN 13001-3-1 deals only with limit state method in accordance with EN 13001-1. Normative references The following referenced documents are indispensable for the application of this document. 1 Scope This European Standard is to be used together with EN 13001 – 1 and EN 13001 – 2 and as such they specify general conditions. Mechanical properties of fasteners made of carbon steel and alloy steel — Part 1: Bolts. Thermal cutting — Classification of thermal cuts — Geometrical specification and quality tolerances (ISO 9013:2002) EN ISO 12100-1:2003. general principles for design — Part 1: Basic terminology. Welding — Multilingual terms for welded joints with illustrations (ISO 17659:2002) 6 . Delivery requirements for surface conditions of hot-rolles steel plates. Hot rolled products of structural steels — Part 2: Technical delivery conditions for non-alloy structural steels EN 10025-3:2004. including Technical Corrigendum 1:2006)) EN ISO 9013:2002. screws and studs (ISO/DIS 898-1:2006) EN ISO 5817:2008. Hot rolled products of structural steels — Part 3: Technical delivery conditions for normalized/normalized rolled weldable fine grain structural steels EN 10025-4:2004. wide flats and sections – Part 1: General requirements EN 10163-2:2004. nickel. Delivery requirements for surface conditions of hot-rolles steel plates. Hot-rolled flat products made of high yield strength steels for cold forming — Part 1: General delivery conditions EN 10149-2:1995.prEN 13001-3-1:2010 (E) EN 10025-2:2004. general principles for design — Part 2: Technical principles (ISO 12100-2:2003) EN ISO 17659:2004. Cranes — General Design — Part 1: General principles and requirements EN 13001-2. Cranes — General Design — Part 2: Load actions EN 20273:1991. titanium and their alloys (beam welding excluded) — Quality levels for imperfections (ISO 5817:2003. corrected version 2005. methodology (ISO 12100-1:2003) EN ISO 12100-2:2003.Tolerances on dimensions. Welding — Fusion-welded joints in steel. Hot rolled steel plates 3 mm thick or above . Fasteners — Clearance holes for bolts and screws (ISO 273:1979) prEN ISO 898-1:2006. Hot rolled products of structural steels — Part 4: Technical delivery conditions for thermomechanical rolled weldable fine grain structural steels EN 10025-6:2004. Steel products with improved deformation properties perpendicular to the surface of the product — Technical delivery conditions EN 13001-1. Safety of machinery — Basic concepts. Delivery requirements for surface conditions of hot-rolles steel plates. wide flats and sections – Part 2: Plate and wide flats EN 10163-3:2004. shape and mass EN 10149-1:1995. Hot-rolled flat products made of high yield strength steels for cold forming — Part 2: Delivery conditions for thermomechanically rolled steels EN 10149-3:1995. wide flats and sections – Part 3: Sections EN 10164:2004. Safety of machinery — Basic concepts. Hot rolled products of structural steels — Part 6: Technical delivery conditions for flat products of high yield strength structural steels in the quenched and tempered condition EN 10029:1991. Hot-rolled flat products made of high yield strength steels for cold forming — Part 3: Delivery conditions for normalized or normalized rolled steels EN 10163-1:2004. Rd limit design tensile force in bolt 7 . Rd limit design slip force per bolt and friction interface Ft. pin) do diameter of hole e 1. the terms and definitions given in EN ISO 12100-1 and EN ISO 12100-2 and the basic list of definitions as provided in EN 1990-1 apply. Di outer. Sd. inner diameter of hollow pin d diameter (shank of bolt. Rd Fb. Cranes — Vocabulary — Part 1: General 3 Terms and definitions 3. 3.τ limit design force for shear stresses Fe external force (on bolted connection) Fb. abbreviations Description A cross section An net cross section AS stress area of a bolt a length of plate ar relevant weld thickness b width of plate c edge stress ratio factor (buckling) Do.2 Symbols and abbreviations The symbols and abbreviations used in this Part of the EN 13001 are given in Table 1. Sd limit design bearing force design bearing force Fcs. For the definitions of loads.σ limit design force for normal stresses FRd. ISO system of limits and fits — Part 2: Tables of standard tolerance grades and limit deviations for holes and shafts ISO 4306-1:2007.prEN 13001-3-1:2010 (E) ISO 286-2:1990. Table 1 — Symbols and abbreviations Symbols. e 2 edge distances Fb tensile force in bolt Fd limit force FK characteristic value (force) Fp preloading force in bolt FRd. Clause 6 of ISO 4306-1:1990 applies. d design preloading force Fcr reduction in compression force due to external tension Fs. Rd limit design tensile force Fp. Fbi.1 Terms and definitions For the purposes of this European Standard. p 2 8 Description probability of survival distances between bolt centers Q mass of the maximum hoist load q impact toughness parameter .τ acting normal/shear force f maximum imperfection fd limit stress fK characteristic value (stress) fRd limit design stress fu ultimate strength of material fub ultimate strength of bolts fw. abbreviations Fv. Rd limit design weld stress fy yield stress of material fyb yield stress of bolts fyk yield stress (minimum value) of base material or member fyp yield stress of pins Gt mass of the moving crane parts during a representative working cycle H distance between weld and contact area of acting load kσ. kτ buckling factors Kb stiffness of bolt Kc stiffness of flanges K* specific spectrum ratio factor km stress spectrum factor based on m of the detail under consideration K3 stress spectrum factor based on m = 3 lm gauge length lr relevant weld length lW weld length MRd limit design bending moment MSd design bending moment m slope constant of log ∆σ/log N-curve NC notch class Nref reference number of cycles min σ.prEN 13001-3-1:2010 (E) Table 1 – (continued) Symbols. max σ extreme values of stresses PS p 1. Rd limit design shear force per bolt/pin and shear plane Fv. Sd design shear force per bolt/pin and shear plane Fσ. abbreviations Rd r Description design resistance radius of wheel Sd design stresses or forces s(m) stress history parameter T Temperature t Thickness Wel elastic section modulus α side ratio (plate field buckling) α cross section parameter (lateral buckling) αb characteristic factor for bearing connection αL load introduction factor (buckling) αw characteristic factor for limit weld stress γm general resistance factor γMf fatigue strength specific resistance factor γp partial safety factor γR resulting resistance factor γS specific resistance factor γRb resulting resistance factor of bolt γsb specific resistance factor of bolt γRm resulting resistance factor of members γsm specific resistance factor of members γRp resulting resistance factor of pins γsp specific resistance factor of pins γRs resulting resistance factor of slip-resistance connection γss specific resistance factor of slip-resistance connection γRc resulting resistance factor for tension on section with holes γst specific resistance factor for tension on section with holes γRw resulting resistance factor of welding connection γsw specific resistance factor of welding connection δp elongation from preloading φ2 dynamic factor κ dispersion angle (wheel pressure) κ. κy. κx. κτ λ reduction factors (buckling) width of contact area in weld direction 9 .prEN 13001-3-1:2010 (E) Table 1 – (continued) Symbols. and tests when applicable. λτ Ψ 4 4. weld quality classes. materials of connecting elements. material grades and qualities.1 limit design stress range for k* = 1 ∆τRd permissible (limit) stress range (shear) ∆σSd design stress range (normal) ∆τSd design stress range (shear) General Documentation The documentation of the proof of competence shall include: design assumptions including calculation models. applicable loads and load combinations. 10 .prEN 13001-3-1:2010 (E) Table 1 – (continued) Symbols. abbreviations λx.1 Description non-dimensional plate slenderness (buckling) edge stress ratio (buckling) ∆F b additional force ∆δ additional elongation µ slip factor ν relative total number of stress cycles (normalized) νD ratio of diameters ∆σc characteristic value of stress range (normal stress) ∆τc characteristic value of stress range (shear stress) σe reference stress (buckling) σSd design stress (normal) τSd design stress (shear) σw. Sd design weld stress (shear) ∆σRd permissible (limit) stress range (normal) ∆σRd. λy. in accordance with EN ISO 5817. relevant limit states results of the proof of competence calculation. Sd design weld stress (normal) τw. 2. weldability shall be demonstrated. Weldable fine grain structural steels in conditions: normalized (N) EN 10025-3. This standard gives a preferred selection. Table 2 shows specific values for the nominal value of strength fu. Grades and qualities other than those mentioned in the above standards and in Table 2 may be used if the mechanical properties and the chemical composition are specified and conform to a relevant European Standard. normal 2 N/mm fRdτ. If necessary. fy and limit design stress fRd (see 5. Table 2 — Specific values of steels for structural members Steel Standard S235 EN 10025-2 S275 Thickness t mm Nominal strength fy yield 2 N/mm fu ultimate 2 N/mm Limit design stress (γRm=1.1 Grades and qualities European Standards specify materials and specific values. High yield strength steels for cold forming in conditions: thermomechanical (M) EN 10149-2. B or C of EN 10029 shall be specified for the plates to allow the use of nominal values of plate thicknesses in the proof calculations.1) fRdσ. steel according to following European Standards should be used: Non-alloy structural steels EN 10025-2.2 Materials for structural members 4.2). For structural members.prEN 13001-3-1:2010 (E) 4. The values given are applicable for temperatures up to 150°C. Tolerance class A. normalized (N) EN 10149-3. Otherwise the minimum value of thickness shall be used. High yield strength structural steels in the quenched and tempered condition EN 10025-6. thermomechanical (M) EN 10025-4. For more information see the specific European Standard. shear 2 N/mm t ≤ 16 235 214 123 16 < t ≤ 40 225 205 118 40 < t ≤ 100 215 195 113 100 < t ≤ 150 195 177 102 340 t ≤ 16 275 250 144 16 < t ≤ 40 265 241 139 40 < t ≤ 63 255 232 134 430 63 < t ≤ 80 245 223 129 80 < t ≤ 100 235 214 123 100 < t ≤ 150 225 205 118 11 . 1) fRdσ.prEN 13001-3-1:2010 (E) Table 2 – (continued) Steel S355 S355 Standard EN 10025-2 EN 10025-3 (N) EN 10025-4 (M) S420 S460 S460 S500 S550 S620 EN 10025-6 S690 Nominal strength fy yield 2 N/mm fu ultimate 2 N/mm Limit design stress (γRm=1. shear 2 N/mm t ≤ 16 355 323 186 16 < t ≤ 40 345 314 181 40 < t ≤ 63 335 305 176 63 < t ≤ 80 325 296 171 80 < t ≤ 100 315 287 166 100 < t ≤ 150 295 268 155 t < 16 355 323 186 16 < t ≤ 40 345 314 181 40 < t ≤ 63 335 305 176 63 < t ≤ 80 (N) 325 295 171 80 < t ≤ 100 (N) 315 286 165 100 < t ≤ 150 (N) 295 268 155 t < 16 420 382 220 16 < t ≤ 40 400 364 210 40 < t ≤ 63 390 355 205 63 < t ≤ 80 (N) 370 336 194 80 < t ≤ 100 (N) 360 327 189 100 < t ≤ 150 (N) 340 309 178 490 450 500 t < 16 460 418 241 16 < t ≤ 40 440 400 231 40 < t ≤ 63 430 391 226 63 < t ≤ 80 (N) 410 373 215 80 < t ≤ 100 (N) 400 364 210 418 241 3 < t ≤ 50 460 50 < t ≤ 100 440 3 < t ≤ 50 500 50 < t ≤ 100 480 3 < t ≤ 50 550 50 < t ≤ 100 530 530 550 590 640 400 231 455 262 436 252 500 289 482 278 564 325 527 304 3 < t ≤ 50 620 50 < t ≤ 100 580 3 < t ≤ 50 690 770 627 362 50 < t ≤ 100 650 760 591 341 467 700 3 < t ≤ 50 890 940 809 50 < t ≤ 100 830 880 755 436 3 < t ≤ 50 960 980 873 504 S315 315 390 286 165 S355 355 430 323 186 420 480 382 220 460 520 418 241 550 455 262 600 500 289 S890 S960 S420 S460 (M) EN 10149–2 (M) S500 (M) EN 10149-3 (N) S550 (M) 12 Thickness t mm all t 500 550 . normal 2 N/mm fRdτ. 2 Thickness t mm Limit design stress (γRm=1. Table 4 gives the required steel quality and impact energy/test temperature in dependence of Σqi.prEN 13001-3-1:2010 (E) Table 2 – (continued) Steel Standard S600 (M) S650 (M) EN 10149–2 (M) S700 (M) EN 10149-3 (N) 4. Table 3 gives the impact toughness parameters qi for various influences. the sum of impact toughness parameters qi shall be taken into account.8 h 4 Stress concentration and notch class ∆σc 2 (N/mm ) (see Annex D and Annex H) qi 0≤T 0 -10 ≤ T < 0 1 -20 ≤ T < -10 2 -30 ≤ T < -20 3 -40 ≤ T < -30 4 -50 ≤ T < -40 6 fy ≤ 300 0 300 < fy ≤ 460 1 460 < fy ≤ 700 2 700 <fy ≤ 1000 3 1000 <fy ≤ 1300 4 t ≤ 10 0 10 < t ≤ 20 1 20 < t ≤ 40 2 40 < t ≤ 60 3 60 < t ≤ 80 4 80 < t ≤ 100 5 100 < t ≤ 125 6 125 < t ≤ 150 7 ∆σc > 125 0 80 < ∆σc ≤ 125 1 56< ∆σc ≤ 80 2 40≤ ∆σc ≤ 56 3 13 . if an impact energy/temperature is tested in accordance with EN 10045-1 and specified.8 1. Table 3 — Impact toughness parameters qi Influence i 1 Operating temperature T (°C) 2 2 Yield stress fy (N/mm ) 3 Material thickness t (mm) Equivalent thickness t for solid bars: d b b for < 1.8 : t = t= 1.1) Nominal strength fy yield N/mm2 fu ultimate N/mm2 fRdσσ. normal N/mm2 fRdττ. Grades and qualities of steel other than mentioned in Table 4 may be used. shear N/mm2 all t 600 650 545 315 t≤8 650 591 341 t>8 630 573 331 t≤8 700 636 367 t>8 680 618 357 700 750 Impact toughness When selecting grade and quality of the steel for tensile members.2. 9 or 12.9.2 General For the purpose of this standard bolted connections are connections between members and/or components utilizing bolts. MC NC.1 a) a) May be used if the impact toughness is at least 27 J at – 40°C. 4.9 in accordance with prEN ISO 898-1 shall be used. caused by vibrations or fluctuations in loading) causes deleterious changes in geometry bolts shall be tightened to avoid slippage sufficiently or the joint surfaces shall be secured against rotation (e. 14 . tested in accordance with EN 10045-1 and specified . g. Technical requirements can be found in EN ISO 15330.3. 10.3 4. MC a) 4.3. for the property classes (bolt grades) 10. EN ISO 4042 and ISO 9587.9 12. Bolted connections Bolt materials For bolted connections bolts of the property classes (bolt grades) 4.6.8. by using multiple bolts).8 10.9 f yb (N/mm2) 240 300 640 900 1 080 fub (N/mm2) 400 500 800 1 000 1 200 NOTE The designer should ask the bolt supplier to demonstrate compliance with the requirements regarding the protection against hydrogen brittleness.6 5. Where slippage (e.6 8. In general bolted connections are tensioned wrench tight.prEN 13001-3-1:2010 (E) Table 4 — Impact toughness requirement and corresponding steel quality for ∑qi ∑ qi ≤ 5 6 ≤ ∑ qi ≤ 8 9 ≤ ∑qi ≤ 11 12 ≤ ∑qi ≤ 14 Impact energy/ test temperature requirement 27 J / +20°C 27 J / 0°C 27 J / -20°C 27 J / -40°C EN 10025-2 JR J0 J2 EN 10025-3 N N N NL EN 10025-4 M M M ML EN 10025-6 Q Q Q QL EN 10149-1 NC. Table 5 shows nominal values of the strengths: Table 5 — Property classes (bolt grades) Property class (Bolt grade) 4. MC NC.g.6. 5.9 and 12. 8. 9 or 12. high strength bolts of property classes (bolt grades) 8.3 Shear and bearing connections For the purpose of this standard shear and bearing connections are those connections where the loads act perpendicular to the bolt axis and cause shear and bearing stresses in the bolts and bearing stresses in the connected parts.prEN 13001-3-1:2010 (E) 4. 15 .5 Welded connections For the purposes of this standard welded connections are joints between members and/or components which utilize fusion welding processes. 10.3. i. consideration shall be given to the stiffness of the connected parts. and where high strength bolts of property classes (bolt grades) 8.8. 4. and where clearance between bolt and hole shall conform to ISO 286-2 tolerances h13 and H11 or closer. 10.9 are used and tightened by a controlled method to a specified preloading state.9 or 12. in other cases wider clearances in accordance with EN 20273 may be used. in addition to standard holes oversized and slotted holes may be used. Clearance between pin and hole shall be in accordance with ISO 286-2 tolerances h13 and H13 or closer. they do not apply to connections made only as a convenient means of attachment.8. 4. when bolts are exposed to load reversal or where slippage may cause deleterious changes in geometry. NOTE 4. In case of loads with changing directions closer tolerances shall be applied. In order to inhibit local out-of-plane distortion (dishing). bolts shall be tightened by a controlled method to a specified preloading state.5 Connections loaded in tension For the purpose of this standard connections loaded in tension are those connections where the loads act in the direction of the bolt axis and cause axial stresses in the bolts. the surface condition of the contact surfaces shall be specified and taken into account accordingly. special surface treatment of the contact surfaces is not needed. Only round pins are considered.4 Bolts in tension that are not preloaded are treated as structural members. and where connected parts are 3 mm or larger in thickness.4 Friction grip type (slip resistant) connections For the purpose of this standard friction grip connections are those connections where the loads are transmitted by friction between the joint surfaces. 4. e.3. All pins shall be furnished with retaining means to prevent the pins from becoming displaced from the hole. The requirements herein apply to pinned connections designed to carry loads.3. Pinned connections For the purpose of this standard pinned connections are connections that do not constrain rotation between connected parts..9 shall be used. sliding of friction-grip connections. such distributions can. In general. The proof shall be carried out for structural members and connections whilst taking into account the most unfavourable load effects from the load combinations A. load carrying welds shall be at least of quality level C. Terms for welded joints are as given in EN ISO 17659.. This applies specifically to the normal stress parallel to the axis of the weld which is accommodated by the base material. The use of the theory of plasticity for calculation of ultimate load bearing capacity is not considered acceptable within the terms of this standard. 5 Proof of static strength 5. B or C in accordance with EN 13001-2 and applying the resistances according to 5. in general. load combinations and partial safety factors in accordance with EN 13001-2. In the following clauses.1 General A proof of static strength by calculation is intended to prevent excessive deformations due to yielding of the material. be considered uniform. Quality level D may be applied only in joints where local failure of the weld will not result in failure of the structure or falling of loads. 4. proof of fatigue strength according to 6. proof of strength of hollow section girder joints in accordance with clause 7. and appropriate methods of non-destructive testing shall be used to verify compliance with quality level requirements. 16 . Dynamic factors given in EN 13001-2 are used to produce equivalent static loads to simulate dynamic effects. The following proofs for structural members and connections shall be demonstrated: proof of static strength in accordance with clause 5. Residual stresses and stresses not participating in the transfer of forces need not to be considered in the design of weld subjected to static actions. elastic instability (see 8) and fracture of structural members or connections. proof of elastic stability in accordance with clause 8.2. the design resistances Rd are represented as limit stresses f d or limit forces Fd .6 Proof of competence for structural members and connections The object of the proof of competence is to demonstrate that the design stresses or forces S d do not exceed the design resistances Rd : Sd ≤ Rd The design stresses or forces (1) Sd shall be determined by applying the relevant loads.prEN 13001-3-1:2010 (E) Quality levels of EN ISO 5817 shall be applied . Although the distribution of stresses along the length of the weld may be non-uniform. γ R ) or Limit design forces FRd = function ( Fk . such as finite element analysis. stresses calculated using traditional elastic strength of materials theory.2. 5. When alternative methods of stress calculation are used.1 (see EN 13001-2) is the specific resistance factor applicable to specific structural components as given in the clauses below fRd NOTE 5. e.2 and FRd are equivalent to R /γm in EN 13001-1.prEN 13001-3-1:2010 (E) This standard is based on nominal stresses. column fy ) is the specific resistance factor for material as follows: For non-rolled material 17 . Limit design stress in structural members fRd . i. used for the design of structural members. using those stresses for the proof given in this standard may yield inordinately conservative results. shall be calculated from: The limit design stress fRdσ = fRdτ = f yk γ Rm f yk γ Rm 3 for normal stresses (3) for shear stresses (4) γ Rm = γ m ×γ sm with where f yk γ sm is the minimum value of the yield stress of the material (see Table 2.2 Limit design stresses and forces 5.1 General The limit design stresses and forces shall be calculated from: Limit design stresses fRd = function ( fk . γ R ) (2) where fk or Fk are characteristic values (or nominal values) γR is the total resistance factor γm is the general resistance factor γs γ R = γ m ×γ s γ m = 1.2. 16 for material in quality class Z15 in accordance with EN 10164 γ sm = 1.0 for plate thicknesses less than 15mm or material in quality classes Z25 or Z35 in accordance with EN 10164 γ sm = 1.0 for stresses in the plane of rolling γ sm = 1.0 For rolled materials (e.50 without quality classification of through-thickness property Key Figure shows a tensile load perpendicular to plane of rolling where 1 is the direction of the plane of rolling 2 is the direction of stress/load Figure 1 — Tensile load perpendicular to plane of rolling 5.prEN 13001-3-1:2010 (E) γ sm = 1. g. plates and profiles): γ sm = 1.0 for compressive and shear stresses For tensile stresses perpendicular to the plane of rolling (see Figure 1): Material shall be suitable for carrying perpendicular loads and be free of lamellar defects.3.2. Only the unthreaded part of the shank is considered effective in the bearing calculations.2.3 Limit design forces in bolted connections 5.1 Shear and bearing connections General The resistance of a connection shall be taken as the least value of the limit forces of the individual connection elements.1.1 5. In addition to the bearing capacity of the connection elements other limit conditions at the most stressed sections shall be verified using the resistance factor of the base material.2.3. γ sm = 1. 18 . 2 Bolt shear The limit design shear force Fv.1. Rd per bolt shall be calculated from: Fb.Rd per bolt and for each shear plane shall be calculated from: f yb × A Fv.0 × d 0 p2 ≥ 3. 5.3.3 Bearing on bolts and connected parts The limit design bearing force Fb .3.2.5 × d 0 (7) and with the following recommendations for the plate e2 ≥ 1.Rd = (5) γ Rb × 3 γ Rb = γ m × γ sb with where f yb is the yield stress (nominal value) of the bolt material (see Table 5) A is the cross-sectional area of the bolt shank at the shear plane γ sb is the specific resistance factor for bolted connections γ sb = 1.Rd = fy × d × t γ Rb (6) γ Rb = γ m × γ sb with With the requirement e1 ≥ 1.1.3 for single shear plane connections See Annex A for limit design shear forces of selected bolt sizes.0 for multiple shear plane connections γ sb = 1.prEN 13001-3-1:2010 (E) 5.5 × d 0 p1 ≥ 3.0 × d 0 where fub is the ultimate strength (nominal value) of the bolt (Table 5) 19 .2. .1. Fcs.Rd = f y × An γ Rc with γ Rc = γ m × γ st where 20 (8) .Rd . . on the net cross-section shall be calculated from: Fcs. .4 Tension in connected parts The limit design tensile force per connected member with respect to yielding.9 for single shear plane connections p1 p 2 e1 e 2 . are distances used in Equation (2) Arrow shows the direction of force Figure 2 — Illustration for Equation (7) 5. .3.prEN 13001-3-1:2010 (E) fu is the ultimate strength (nominal value) of the basic material (Table 2) fy is the minimum value of yield stresses of the basic materials and bolt (Table 2) d is the shank diameter of the bolt d0 is the diameter of the hole t is the thickness of the connected part in contact with the unthreaded part of the bolt γ sb is the specific resistance factor for bolt connections γ sb = 0.7 for multiple shear plane connections γ sb = 0.2. are distances (see Figure 2) Key p1 p 2 e1 e 2 . Rd per bolt and per friction interface shall be calculated from: Fs.50 for surfaces blasted with steel grit or sand and metallized with a product based on zinc µ = 0. no unevenness µ = 0.3.2. The applied preloading force shall be greater than or equal to the design preloading force.50 for surfaces blasted metallic bright with steel grit or sand.25 for surfaces cleaned and treated with etch primer µ = 0.d − Fcr ) (9) γ Rs γ Rs = γ m × γ ss where µ is the friction coefficient µ = 0.20 for surfaces cleaned of loose rust.d is the design preloading force Fcr is the reduction in the compression force due to external tension on connection (for simplification Fcr = Fe may be used).2 5. For friction grip type connections the limit design slip force Fs.40 for surfaces hot dip galvanized and lightly blasted µ = 0. γ ss is the specific resistance factor for friction grip type connections (see Table 6) 21 .Rd = with µ × ( Fp.prEN 13001-3-1:2010 (E) An is the net cross-sectional area at bolt or pin holes (see Figure 2) γ st is the specific resistance factor for tension on sections with holes γ st = 1.30 for surfaces cleaned metallic bright by wire brushing µ = 0.50 for surfaces blasted with steel grit or sand and aluminized µ = 0. oil and dirt (minimum requirement) Fp.40 for surfaces blasted with steel grit or sand and alkali-zinc-silicate coating of 50 µm to 80 µm thickness µ = 0.2 Friction grip type connections The resistance of a connection shall be determined by summing the limit forces of the individual connecting elements. depending upon the joint construction.7 × f yb × As .3 Connections loaded in tension This clause specifies the limit state for a bolt in the connection. see Figure 3.25 times the diameter of the bolt. The connected parts and their welds shall be calculated with the general rules for structural members.2.2 gives limit design slip forces using the specific resistance factor value γ ss = 1. In order to reduce pressure under bolt or nut appropriate washers shall be used. Table B. see Figure 4.14 1. The proof calculation shall be done for the bolt under maximum external force in a connection. where f yb is the yield stress (nominal value) of the bolt material (Table 5) As is the stress area of the bolt (Table B. the effect of different load paths of the external compression force. shall be taken into account.00 1. Long slotted hole: length of hole is larger than 1.63 a Holes with clearances in accordance with the medium series of EN 20273:1991.3. Proof of competence calculations of a preloaded connection shall take into account the stiffness of the bolt and the connected parts. In addition to that.prEN 13001-3-1:2010 (E) Table 6 — Specific resistance factor γss for friction grip connections Type of holes Effect of connection slippage Standard a holes b Oversized and shortc slotted holes Longslotte d holes Longslotte d holes c d a hazard is created 1. leverage).14 and a design preloading force of Fp.25 times the diameter of the bolt.d = 0. 5.34 1.63 2. with due consideration to the force distribution in a multi-bolt connection and the prying effects (i. c Slotted holes with slots perpendicular to the direction of force. e.00 a hazard is not created 1. Short slotted hole: length of hole is smaller than or equal to 1. b Holes with clearances in accordance with the coarse series of EN 20273:1991.2).41 1. d Slotted holes with slots parallel to the direction of force. where the preload in the bolt is considered as one loading component. 22 .14 1. a symmetric loading with the bolt in the middle is assumed in the figure.t Fe. Figure 4 — Load path alternatives for the external compression force Two separate design limits shall be considered for the external tensile bolt force: 23 .c Bolt elongation due to preloading External tensile force External compression force ∆δt Additional elongation.t Additional force in bolt. due to external compression force Kb Stiffness of bolt Kc Stiffness of connected parts Figure 3 — Force-elongation-diagram a) External compression force does not interfere with the compression zone under the bolt b) External compression force is transferred through the compression zone under the bolt For simplicity. due to external tensile force ∆Fb.c Additional force in bolt.prEN 13001-3-1:2010 (E) Key Fp Preloading force in bolt δp Fe. due to external tensile force Tensile force in bolt Fb ∆Fb. min is the minimum value of the preload.Rd = Fy / γ Rb − Fp.d 24 is the nominal value of the design preload. Φ is the stiffness ratio factor of the connection.Rd . see also Annex G. For connections loaded in tension it shall be proven that the external tensile design force in the bolt Fe. see Annex G. fyb is the yield stress of the bolt material. The limit design tensile force per bolt for the opening criteria of the connection is calculated from: Ft2. Equation (11).91 NOTE: A load introduction factor αL may be taken into account when calculating the factor Φ. d where Fp. (12) (13) .max is the maximum value of the preload.2.Rd or Ft2.3. As is the stress area of the threaded part of the bolt.prEN 13001-3-1:2010 (E) 1) the resulting bolt force from the external force and the maximum design preload shall not exceed the bolt yield load.d and Fp. see also 5. Equation (10) 2) the connection shall not open (gap) under the resulting bolt force from the external force and the minimum design preload.max = (1 + s ) × Fp. The variation of preload due to scatter is taken into account by the maximum and minimum values of the preload as follows: Fp. γ sb is the specific resistance factor for connections loaded in tension. Fp. does not exceed either of the two limit design forces Ft1.Rd = Fp.max Φ (10) with Φ = Kb Kb + K c and γ Rb = γ m × γ sb and Fy = f yb × As where Fy is the bolt yield force.min (11) γ Rb ⋅ (1− Φ ) where Fp. The limit design tensile force per bolt for the bolt yield criteria is calculated from: Ft1.min = (1 − s ) × Fp. γ sb = 0.t . 5.7 Fy Methods.1 for information on tightening torques. The additional force in bolt ∆Fb shall be used in the proof of fatigue strength of the bolt in accordance with clause 6. force in bolt or elongation is measured.Sd F + v. Sd is the external tensile force per bolt 25 . For the calculation of the additional force in bolt. see Figure 4.d value shall not exceed the values given in Table 7.09 controlled tightening. Otherwise.c ) (14) where ∆Fb is the additional force in bolt Φ is the stiffness ratio factor Fe.3. any value for the preload may be chosen for a particular connection. the nominal preload is the residual preload achieved after a possible loss of the applied preload during the tensioning operation. This shall be omitted (i. rotation angle or tightening torque is measured s = 0.c is the external compression force.2. t is the external tensile force Fe.max is the maximum value of the preload. t + Fe. s = 0.4 Bearing type connections loaded in combined shear and tension When bolts in a bearing type connection are subjected to both tensile and shear forces.Sd ≤ 1 F F t. where only direct tension is applied to the bolt 0. the applied forces shall be limited as follows: 2 2 Ft. the load path of the external compression force shall be considered. where the bolt is subjected to torque 0. s is the preload scatter. Fe. In a general format the additional force in bolt is calculated as follows: ∆Fb = Φ × (Fe. where the external compression force does not interfere with the compression zone under the bolt. Fp. case a) in Figure 4. Table 7 — Upper limits of preload levels according to method of preloading Type of preloading method Upper limit of preload level Methods.9 Fy NOTE For direct tensioning method. e.23 controlled tightening. The nominal value of the design preload Fp.c is set to zero in the equation) in cases.min is the minimum value of the preload.prEN 13001-3-1:2010 (E) Fp. See Table B.Rd v.Rd (15) where Ft. prEN 13001-3-1:2010 (E) Ft,Rd is the limit tensile force per bolt (see 5.2.3.3) Fv,Sd is the design shear force per bolt per shear plane Fv,Rd is the limit shear force per bolt per shear plane (see 5.2.3.1.2) 5.2.4 Limit design forces in pinned connections 5.2.4.1 Pins, limit design bending moment The limit design bending moment is calculated from M Rd = Wel × f yp (16) γ Rp with γ Rp = γ m × γ sp where Wel is the elastic section modulus of the pin f yp is the yield stress (minimum value) of the pin material γ sp is the specific resistance factor for pinned connections bending moment 5.2.4.2 γ sp = 1,0 Pins, limit design shear force The limit design shear force per shear plane for pins is calculated from Fv,Rd = A × f yp 1 × u 3 × γ Rp (17) with γ Rp = γ m × γ sp where u 26 is the shape factor u= 4 3 for solid pins u= 4 1 + vD + vD 2 × 3 1 + vD 2 for hollow pins Di , DO where νD = Di is the inner diameter of pin Do is the outer diameter of pin prEN 13001-3-1:2010 (E) A is the cross-sectional area of the pin γ sp is the specific resistance factor for shear force in pinned connections γ sp = 1,0 for multiple shear plane connections γ sp = 1,3 for single shear plane connections 5.2.4.3 Pins and connected parts, limit design bearing force The limit design bearing force is calculated from Fb,Rd = αb × d × t × fy (18) γ Rp with γ Rp = γ m × γ sp where f yp α b =Min f y 1,0 fy is the yield stress (minimum value) of the material of the connected parts f yp is the yield stress (minimum value) of the pin material d is the diameter of the pin t is the lesser value of the thicknesses of the connected parts, i. e. γ sp is the specific resistance factor for the bearing force in pinned connections γ sp = 0,6 t1 + t 2 or t 3 in Figure 5 when connected parts in multiple shear plane connections are held firmly together by retaining means such as external nuts on the pin ends γ sp = 0,9 for single shear plane connections or when connected parts in multiple shear plane connections are not held firmly together 27 prEN 13001-3-1:2010 (E) Figure 5 — Pinned connections In case of significant movement between the pin and the bearing surface, consideration should be given to reducing the limit bearing force in order to reduce wear. In case of reversing load consideration should be given to the avoidance of plastic deformation. 5.2.4.4 Connected parts, limit design force with respect to shear The limit design force in a failure mode, where a piece of material is torn out, shall be based upon shear stress in a critical section. In general, a uniform shear stress distribution throughout the section is assumed. The limit design shear force is calculated as follows: Fv, Rd = As × f y γm ⋅ 3 (19) with As = (s1 + s2 ) × t in general and As = 2 × s × t for a symmetric construction as in Figure 6 a) and c), where fy As is the yield stress of the material of the structural member in question is the shear area of the tear-out section s,s1,s2 are shear lengths of the tear-out section. For constructions in accordance with Figure 6 the tearout section is A-A and shear lengths are determined through a 40 degree rule as indicated. t 28 is the thickness of the member. ratio between the maximum stress and the average stress in the section. The limit design force for the construction in accordance with Figure 6 a) is determined as follows: Fv.4. The clearance between the hole and the pin are assumed to conform ISO 286-2 tolerances H11/h11 or closer.2. Stress concentration due to geometry of the pin hole shall be considered. γ sp is the specific resistance factor for tension at pinned connections.5 Connected parts. k is the stress concentration factor.95 k where f y is the yield stress of the material of the structural member in question. limit design force with respect to tensile stress Design shall be based upon the maximum tensile stress at inner surface of the pin hole. In case of a larger clearance. i. the stress concentration factor k is taken from the Figure 7. Rd = 2×b×t × fy k × γ m × γ sp (20) with γ sp = 0. higher values of k shall be used.5 ≤ b/d ≤1 (see Figure 6). 29 .e.prEN 13001-3-1:2010 (E) Figure 6 — Connected parts 5.For a construction with the geometric proportions as 1≤ c/b ≤2 and 0. However. the weld quality.Rd = 30 α w × f uw γm (22) . the type of the weld. Depending on the equation number given in Table 8.2. the type of stress evaluated in accordance with Annex C.prEN 13001-3-1:2010 (E) Figure 7 — Stress concentration factors for a specific type of pinned connection NOTE Tensile loads or tensile parts of reversing loads only need to be considered within this clause.5 Limit design stresses in welded connections The limit design weld stress f w.Rd used for the design of a welded connection depends on: the base material to be welded and the weld material used.2.4.Rd = α w × f yk γm (21) or by f w. 5.Rd shall be calculated either by: f w. reversing load situations may require additional considerations where this may result in unacceptable plastic deformations or affect functionality of the connection (see 5.3). the limit design weld stress f w. 80 0.93 All welds.54 0. a undermatching weld material Tension or compression 22 0. provided the welds are proportioned to accommodate the shear forces developed between those parts. However. the type of stress and the material is the minimum value of the yield strength of the connected member under consideration fuw is the ultimate tensile strength of the weld material (all weld metal) Table 8 — Factor for limit weld stress Direction of stress Stress normal to the weld direction Stress parallel to the weld direction The values of Type of weld Type of stress Equation number αw f yk < 960 f yk ≥ 960 N/mm² N/mm² Full penetration weld. matching a weld material Tension or compression 21 0. e.0 0.93 Compression 21 1.65 All welds.80 Compression 22 0. matching weld material Shear 21 0. matching weld material Shear 21 0.50 α w are valid for welds in quality classes B and C of EN ISO 5817.56 0.0 0.0 0.55 Full penetration welds. matching weld material Tension 21 1.50 0.65 Partial penetration weld.60 0.prEN 13001-3-1:2010 (E) where αw f yk is a factor given in Table 8 in dependence on the type of weld. 31 .. Undermatching weld material: weld material with strength properties less than those of connected members a Note : An asymmetric weld is not recommended.70 0. undermatching weld materials Tension 22 0.50 0. undermatching weld material Shear 22 0.80 Partial penetration weld.93 Full penetration weld. the proof shall be made for each member separately.80 0. may be designed without regard to normal stress parallel to the axis of the weld.54 All welds Tension or Compression 21 1. flange-to-web connections. The welds joining parts of built-up members. In case of connected members from different materials.g.56 All welds. undermatching weld material Shear 22 0.70 0.50 Partial penetration weld. undermatching weld material Shear 22 0. if used connected members shall be supported so as to avoid the effect of load eccentricity on the weld. 2. Fv.2 Proof for bolted connections For each mode of failure of a connection it shall be proven for the most highly loaded member that: FSd ≤ FRd (25) where FSd is the design force of the element.1 Proof for structural members For the structural member to be designed it shall be proven that: σ Sd ≤ fRdσ and τ Sd ≤ fRd τ (23) where σ Sd.Rd limit design shear force Fb.2. y Spatial states of stresses may be reduced to the most unfavourable plane state of stress. x 2 σ + Sd. Fe.3.τ Sd are the design stresses. x f Rdσ. fRdσ . In case von Mises is used.t FRd NOTE 32 for connections loaded in tension (see 5.Rd limit design slip force Ft. i. e.2. x + Sd f Rdσ. The von Mises equivalent stress may be used as the design stress instead.3.2. y f Rdτ 2 ≤1 (24) where indicate the orthogonal directions of stress components.3. x. y σ τ − Sd. x × f Rdσ . 5.3) is the limit design force in accordance with clause 5. y f Rdσ. . y 2 × σ Sd. g. In case of plane states of stresses when von Mises stresses are not used it shall additionally be proven that: σ Sd. fRdσ is the limit design stress.Rd limit design bearing force Fs. fRdτ are the corresponding limit design stresses in accordance with clause 5.3.3 Execution of the proof 5. e.Rd limit design tensile force Care should be taken in apportioning the total load into individual components of the connection. depending on the type of connection.prEN 13001-3-1:2010 (E) 5. depending on the type of the connection. Sd .3 Proof for pinned connections For pins.2.Sd ≤ Fv.prEN 13001-3-1:2010 (E) 5.Sd f w.Sd.3.Sd is the design value of the shear force in the pin Fv.Sd.Sd ≤ Fb. σ w.4.2.sd and τ w.Sd is the most unfavourable design value of the bearing force in the joining plate i of the pin connection Fb.4 Proof for welded connections For the weld to be designed it shall be proven that: σ w.Rd (28) where τ w.4 Fv.2.2. σ w. y ) in welded connections it shall additionally be proven that: 33 .2 Fbi.Rd is the limit design bearing force in accordance with clause 5.4 NOTE In multi – pin connections care should be taken in apportioning the total load into individual components of the connection.Sd ≤ f w.Rd are the design weld stresses (see Annex C) is the corresponding limit design weld stress in accordance with clause 5. it shall be proven that: M Sd ≤ M Rd Fv.3.5 In case of plane states of stresses (with orthogonal stress components τ w. l ⋅ Fb3 4 M Sd = (27) where is the distance between Fb 1 and Fb2 l is the sum of Fb1 and Fb2 (see Figure 5) Fb3 5.x .Rd where M Sd is the design value of the bending moment in the pin M Rd is the limit design bending moment in accordance with clause 5.Rd (26) Fbi.Rd is the limit design shear force in accordance with clause 5. As a conservative assumption in the absence of a more detailed analysis the following equation may be used.Sd. σ w. The constructional details in Annex D and Annex H contain the influences illustrated in the figures and thus the characteristic fatigue strength values include the effects of: local stress concentrations due to the shape of the joint and the weld geometry. Where the design stress always is purely compressive in a uniaxial stress state.Sd.Sd σ − w. y τ w.Rd.prEN 13001-3-1:2010 (E) σ w. the welding process and post-weld improvement procedures. as presented in EN 13001-1. x f w. y 6 6. Proof of fatigue strength General A proof of fatigue strength is intended to prevent risk of failure due to formation and propagation of critical cracks in structural members or connections under cyclic loading. residual stresses. setting all partial safety factors γp = 1. multiplied by the dynamic factors φi . In general. metallurgical conditions. A nominal stress is a stress in the base material adjacent to a potential crack location. and applying the resistances (i. y 2 2 × σ w. y f w.Sd. the proof shall be executed by applying the load combinations A in accordance with EN 13001-2. The bibliography gives information on literature about Hot Spot Stress Method. e.1 + f w.1 indicate the orthogonal directions of stress components. The effect of other geometric stress concentrations than those listed above (global stress concentrations) shall be included in the nominal stress by means of relevant stress concentration factors. size and shape of acceptable discontinuities.3). calculated in accordance with simple elastic strength of materials theory.2.Sd. x × f w. limit design stresses) according to 6. excluding local stress concentration effects. The stresses are calculated in accordance with the nominal stress concept. In this standard Palmgren-Miner's rule of cumulative damage is reflected by use of the stress history parameters (see Clause 6.Rd (29) where x. and hence crack propagation cannot occur. y f w. the stress direction.Rd. Mean-stress influence. in structures in as-welded condition (without stress relieving) can be considered but is negligible.Rd. the effective stress range to be used in the fatigue 34 . In non-welded details or stress relieved welded details. x ≤ 1. a proof of fatigue strength is not required. This document deals only with the nominal stress method. in some cases. In some applications a load from load combinations B (occasional loads) can occur frequently enough to require inclusion in the fatigue assessment.Sd. Therefore the stress history parameter s is independent of the mean-stress and the fatigue strength is based on the stress range only. NOTE This standard does not use other methods like Hot Spot Stress Method. x 2 σ + w.Rd. For the execution of the proof of fatigue strength the cumulative damages caused by variable stress cycles shall be calculated. The stresses from these occasional loads shall be handled in the same way as those from the regular loads. 1 Limit design stresses Characteristic fatigue strength The limit design stress of a constructional detail is characterized by the value of ∆σ c . 35 .2.0 1. 6.05 1. Table 9 — Fatigue strength specific resistance factor gmf γ mf Accessibility Fail-safe components Non fail-safe components without hazards persons for with hazards for persons Accessible joint detail 1. Non „fail-safe“ structural components are those where local failure of one component leads rapidly to failure of the structure or falling of loads. see Figure 8.prEN 13001-3-1:2010 (E) assessment may be determined by adding the tensile portion of the stress range and 60 % of the compressive portion of the stress range or by special investigation (see 6.20 Joint detail with poor accessibility 1. such that the local failure of one component does not result in failure of the structure or falling of loads.5). ∆σ c represents the fatigue strength at 2 ×106 cycles under constant stress range loading and with a probability of survival equal to Ps = 97. The fatigue strength specific resistance factor γ mf (given in Table 9) is used to account for the uncertainty of fatigue strength values and the possible consequences of fatigue damage.10 1.25 „Fail-safe“ structural components are those with reduced consequences of failure.7 % (mean value minus two standard deviations obtained by normal distribution and single sided test).2 6.15 1. the characteristic fatigue strength. The curves have slopes of −1/ m in the log/log representation. Figure 8 — Illustration of ∆σ -N curve and ∆σc In the first column of Annex E the values of ∆σ c are arranged in a sequence of notch classes (NC) and with the constant ratio of 1. For shear stresses ∆σ c is replaced by ∆τ c .prEN 13001-3-1:2010 (E) Key a) b) principle simplification using one value for m (see EN 13001-1) 1 Constant stress range fatigue limit m is the slope constant of the fatigue strength curve. NOTE This standard is based on the use of stress history parameter s which requires the use of the one slope simplification of the log ∆σ − log N curve as shown in Figure 8 b).125 between the classes. . The values of characteristic fatigue strength ∆σ c or ∆τ c and the related slope constants m of the log ∆σ − log N curve are given in Annex D (normative) and Annex H (informative) for: Table D.1: 36 Basic material of structural members. remelting by TIG.1: Values of slope constant m of the log ∆σ − log N -curve and limit design stress range ∆σ c for connections and joints of hollow section girders. 6. . 100 % NDT.) the basic notch class to decrease the resistance according to Annex D. The requirements in addition to those of level B given hereafter define quality level B*. plasma welding or by needle peening.1 NC. Table H. remelting by TIG. plasma welding or by needle peening so that any undercut and slag inclusions are removed. sum of lengths of concavities of weld less than 5 % of the total length of the weld. both surfaces machined or flush ground down to plate surface. Table D. Quality classes B. The given values apply for the defined basic conditions. For deviating conditions an appropriate notch class (NC) shall be selected one or more notch classes above (+ 1 NC. For parallel and lap joints: transition angle of the weld to the plate surface shall not exceed 25°. + 2NC. For the purpose of this standard an additional quality level B* can be used.2: Elements of non-welded connections.prEN 13001-3-1:2010 (E) Table D... All other joints: full penetration..3: Welded members.2 Weld quality ∆σ c -values in Annex D and Annex H depend on the quality level of the weld.2: Values of slope constant m of the log ∆σ − log N -curve and limit design stress range ∆σ c for lattice type connections of hollow section girders. plasma welding or by needle peening. For butt welds: full penetration without initial (start and stop) points. C. * Additional requirements for quality level B : For the purpose of this standard 100 % NDT (non destructive testing) means inspection of the whole length of the weld with an appropriate method to ensure that the specified quality requirements are met.2. grinding in stress direction. transition angle of the weld to the web surface shall not exceed 25°. 37 . eccentricity of the joining plates less than 5 % of the greater thickness of the two plates. 100 % NDT. The effects of several deviating conditions shall be added up. the weld toe post-treated by grinding. . D shall be in accordance with EN ISO 5817. Table H. the weld toe post-treated by grinding. In Annex H class C is assumed.2 NC. ..) to increase the resistance or below (. remelting by TIG. Lower quality than level D shall not be used. the weld toe post-treated by grinding. 4 at least one stress range level that results in a mean number of stress cycles to failure of less than 2x10 cycles shall be used.5x10 6 and 2. Using the established rules of metal fatigue the large number of variable magnitude stress cycles are condensed to one or two parameters. 6. test specimen produced under workshop conditions.1 5 Stress histories General The stress history is a numerical presentation of all stress variations that are significant for fatigue.5x10 cycles shall be used.3 Requirements for fatigue testing Details not given in Annex D and Annex H or consideration of mean stress influence require special investigation into ∆σ c and m by tests. 38 . 6. the stress cycles shall be completely in the tensile range.prEN 13001-3-1:2010 (E) 100 % NDT. at least one stress range level that results in a mean number of stress cycles to failure between 1. a stress range level that results in a mean number of stress cycles to failure of less than 1x10 cycles shall be used. 6 A simplified method for the determination of m and ∆σ c may be used: m shall be set to m = 3.3 6. Requirements for determination of m and ∆σ c are: ∆σ c shall be determined from numbers of cycles based on mean value minus two standard deviations in a log–log presentation. in both cases simulating the specified crane use.2. Stress histories shall be determined either through stress calculations or measurements. at least 7 tests per stress range level. Requirements for such tests are: test specimen in actual size (1:1).3. eccentricity less than 10 % of the greater thickness of the two plates. If TIG dressing is used as a post treatment of the potential crack initialization zone of a welded joint in order to increase the fatigue strength. welds of quality class C for design purposes may be upgraded to quality class B for any joint configuration. Stress histories shall be represented in terms of maximum stress amplitudes and frequencies of occurrence of stress amplitudes. 3 Stress history parameter Stress history parameter s is calculated as follows. stress histories are expressed as single-parameter representations of frequencies of occurrence of stress ranges by using methods such as the hysteresis counting method (Rainflow or Reservoir method) with the influence of mean stress neglected. m is the slope constant of the log ∆σ − log N -curve of the component under consideration. ∆σ i is the stress range.3. ∆σˆ the maximum stress range. Stress history parameter sm has a specific value for each structural detail. Nt = ∑ ni is the total number of occurrences of stress ranges during the design life of the crane.2 Frequency of occurence of stress cycles For the proof of fatigue strength.prEN 13001-3-1:2010 (E) 6. i N ref = 2 × 10 6 is the reference number of cycles. 6. σ o is the lower extreme value of a stress range. The value is related to crane duty and decisively depends on: 39 . km is the stress spectrum factor dependant on m. Each of the stress ranges is sufficiently described by its upper and lower extreme value. based on a one-parameter presentation of stress histories during the design life of the crane: sm = ν × km (31) where km = ν = m ni ∆σ i ∆σˆ × Nt i ∑ Nt N ref (32) (33) where ν is the relative total number of occurrences of stress ranges.3. ni is the number of occurrences of stress range i . ∆σ is the stress range. ∆σ = σ u − σ b (30) where σ u is the upper extreme value of a stress range. 000 S9 2. Proof of competence for fatigue may be omitted for structural members in cases.002 < s3 ≤ 0.008 < s3 ≤ 0.063 < s3 ≤ 0.125 < s3 ≤ 0. Stress histories characterized by the same value of sm may be assumed to be equivalent in respect to the damage in similar materials.063 S4 0. details or components. the most severe class occurring within the structure shall be used. The classification is based upon m = 3 and is specified in the Table 10 and illustrated in the Figure 9.008 S1 0.3. Stress history classes S Members of crane structures may be arranged into classes S of the stress history parameter sm. For thermally stress relieved or non-welded structural members the compressive portion of the stress range may be reduced to 60 %.000 < s3 ≤ 2.250 S6 0. the value of stress history parameter s3 shall be taken in accordance with the Table 11. NOTE 6.004 S0 0.001 < s3 ≤ 0.004 < s3 ≤ 0.500 < s3 ≤ 1.000 The classes S01 and S02 do not exist in EN 13001-1 but may be used. where the value of the stress 2 history parameter is lower than 0.032 S3 0. luffing etc). Where a class S is referred to in the proof of fatigue strength of a member.002 S01 0.000 < s3 ≤ 4.125 S5 0.016 S2 0. the effect of the crane motions on stress variations (traverse.016 < s3 ≤ 0.001 and the yield stress is 500 N/mm or lower.prEN 13001-3-1:2010 (E) the number of working cycles. crane configuration.4 An example for the determination of stress histories by simulation is given in an Annex F. the net load spectrum.000 S8 1.500 S7 0. Where a single stress history class S is used for the calculation of the whole structure. . slewing. Table 10 — Classes S of stress history parameter s3 NOTE 40 Class Stress history parameter S02 0.032 < s3 ≤ 0.250 < s3 ≤ 0. independent of the slope constant m of the relevant log ∆σ / log N -curve.3.3. ∆σ Rd is the limit design stress range 41 . 6.4 Execution of the proof For the detail under consideration it shall be proven that: ∆σ Sd ≤ ∆σ Rd (34) ∆σ Sd = max σ − min σ (35) where ∆σ Sd is the maximum range of design stresses. minσ are the extreme values of design stresses (compression stresses with negative sign).prEN 13001-3-1:2010 (E) Key 1 fatigue assessment might not be required k 3 is the stress spectrum factor based on m = 3 ν is the relative total number of occurrences of stress range Figure 9 — Illustration of the classification of stress history parameter s for A given stress history falls into specific class S . maxσ. the same value that is used for ∆σˆ in 6. The diagonal lines for the class limits represent the k 3 to ν relationship for s = constant in a log/log scale diagram. 5.004 0.3.25 0.5. For each stress component σ x .2 Direct use of stress history parameter The limit design stress range shall be calculated from: ∆σ Rd = ∆σ c (36) γ mf × m sm where ∆σ Rd is the limit design stress range ∆σ c is the characteristic fatigue strength (see Annex D and Annex H) m is the slope constant of the log ∆σ − log N curve (see Annex D and Annex H) γ mf is the fatigue strength specific resistance factor (see Table 9) sm is the stress history parameter 6.0 2.3 Use of class S 6.008 0.5 Determination of the limit design stress range 6.5 1.016 0.063 0. Table 11 — Values of s3 for stress history classes S Class s3 NOTE 42 S02 S01 S0 S1 S2 S3 S4 S5 S6 S7 S8 S9 0. 6.125 0. In case of non welded details. the simplified determination of the limit design stress range is dependent on the (negative inverse) slope constant m of the log ∆σ –log N-curve.prEN 13001-3-1:2010 (E) Shear stresses τ are treated similarly.3.1 Applicable methods The limit design stress ranges ∆σ Rd for the detail under consideration shall be determined either by direct use of stress history parameter sm or by simplified method based on the use of class S .5.0 4. only the maximum principal stress range may be used.002 0. 6.032 0.3.0 Values of stress history parameter s3 shown above are the upper limit values of ranges shown in Table 10. .y indicate the orthogonal directions of stresses).1 Slope constant m When the detail under consideration is related to a class S according to 6.5. σ y and τ the proof shall be executed separately (where x. or if the plane of the maximum principal stress does not change significantly in the course of a loading event.5. 6.2 Slope constant m = 3 Values of stress history parameter s corresponding to individual stress history classes S are selected according to Table 11. if the normal and shear stresses induced by the same loading event vary simultaneously. 5.1 = ∆σ c γ mf × m s3 k k*=m 3 ≥ 1 km (38) (39) (40) where ∆σ Rd is the limit design stress range σ Rd.1 is the limit design stress range for k* = 1 k* is the specific spectrum ratio factor ∆σ c .25 Annex E gives the values of ∆σ Rd 6. the limit design stress range is dependent on the class S and the stress spectrum factor km (see 4. The limit design stress range ∆σ Rd shall be calculated from: ∆σ Rd = ∆σ Rd.4 of EN 13001-1). Slope constant m ≠ 3 If the slope constant m of the log ∆σ − log N curve is not equal to 3. s3 is the classified stress history parameter (see Table 11). γ mf is the fatigue strength specific resistance factor (see Table 9). ∆σ c is the characteristic fatigue strength of details with m = 3 (see Annex D). m are the characteristic values of stress range and the respective inverse slope of the log ∆σ .4.prEN 13001-3-1:2010 (E) The limit design stress range shall be calculated from: ∆σ Rd = ∆σ c γ mf × 3 s3 (37) where For ∆σ Rd is the limit design stress range.3.3 in dependence on the class S and ∆σ c .log N-curve (see Annex D and Annex H) s3 is the classified stress history parameter (see Table 11) γ mf is the fatigue strength specific resistance factor (see Table 9) k3 is the stress spectrum factor based on m = 3 km is the stress spectrum factor based on m of the detail under consideration 43 . γ mf = 1.1 × k * ∆σ Rd. x ∆σ c.25 and m = 5.1 may then be used as limit design stress range. if not otherwise given in Clause 8 of EN 13001-3. The value of k* may be calculated for k3 and km from the stress spectrum estimated by experience.1 Proof of elastic stability General The proof of elastic stability is made to prove that ideally straight structural members or components will not lose their stability due to lateral deformation caused solely by compressive forces or compressive stresses.1.5. x mx γ mf × ∆σ Sd. 44 .5. ∆τ c are the characteristic fatigue strengths γ mf is the fatigue strength specific resistance factor (see Table 9) sm is the stress history parameter m is the slope constant of log ∆σ − log N curve x. ∆τ Sd are the calculated maximum ranges of design stresses ∆σ c . This chapter covers global buckling of members under compression and local buckling of plate fields subjected to compressive stresses. y + mf ∆τ c mτ ⋅ smτ ≤ 1. 6. x + ∆σ c.prEN 13001-3-1:2010 (E) k 3 and km For shall be based on the same stress spectrum that is derived either from calculation or simulation γ mf = 1. and ∆σ Rd. Annex E gives the values of ∆σ Rd.1 in dependence on the class S and ∆σ c .4 k* = 1 covers the most unfavourable stress spectra for cases with m > 3 and sm < 1.4). Simplified method for slope constants m ≠ 3 6.0 (41) where 7 ∆σ Sd . or in combination with bending moments caused by initial geometric imperfections.4 Independent concurrent normal and/or shear stresses In addition to the separate proof for σ and τ (see 6. y my γ × ∆τ Sd × sm. shall be nd assessed by the theory of 2 order as part of the proof of static strength. the action of independently varying ranges of normal and shear stresses shall be considered by: γ mf × ∆σ Sd. 8 8. Deformations due to compressive forces or compressive stresses in combination with externally applied bending moments.y indicate the orthogonal directions of normal stresses τ indicates the respective shear stress Proof of static strength of hollow section girder joints The proof shall be executed in accordance with Clause 7 of EN 1993-1-8:2005. y × sm.3. Lateral buckling of members loaded in compression 8. I is the moment of inertia of the member in the plane of the figure. Euler case no 1 2 3 4 5 π2 ×E×I π2 ×E×I 2. ki = N E × Ii (42) where: x is the longitudinal coordinate. y is the lateral coordinate in the weakest direction of the member.2.prEN 13001-3-1:2010 (E) NOTE 8. E is the elastic modulus. L is the length of the member. which has the general solution: y = Ai × cos( ki × x ) + Bi × sin( ki × x ) + Ci × x + Di . Table 12 — Critical buckling load Nk for Euler’s buckling cases. For other boundary conditions or for members consisting of several parts i.2 Further information may be found in the bibliography. For members with constant cross section. 45 . Nk is given in Table 12 for a selection of boundary conditions. or system of differential equations.05 × π 2 × E × I 4×π 2 × E × I π2 ×E×I 4 × L2 L2 L2 L2 L2 Boundary conditions Nk E is the elastic modulus. also known as Euler’s buckling cases. of the elastic deflection curve in its deformed state.1 Critical buckling load The critical buckling load Nk is the smallest bifurcation load according to elastic theory. with different cross sections. Nk may be computed from the differential equation. Ai. The reduction factor κ is computed from the slenderness λ. The critical buckling load Nk is found as the smallest positive value N that satisfies Equation (42). which is given by: λ= f yk × A (44) Nk where: Nk is the critical buckling load according to 8.1. 46 ] (45) . the parameter α is given in Table 13. N is the compressive force. or system of Equations (42).2: κ = 1. Bi.0: κ= 1 2 2 ξ + ξ −λ [ ξ = 0.2) + λ2 1 λ × (λ + α ) Depending of the type of cross section. Ci.2 < λ ≤ 3. the reduction factor κ is given by: λ ≤ 0.0: κ= λ > 3.2 Limit compressive design force The limit compressive design force NRd for the member or its considered part is computed from the critical buckling load Nk by: NRd = κ × f yk × A (43) γm where: κ is a reduction factor. Depending on the value of λ and the cross section parameter α. fyk is the compressive yield stress.2. 8. when solved with the appropriate boundary conditions applied.prEN 13001-3-1:2010 (E) Ii is the moment of inertia of part i in the weakest direction of the member.0 0. Di are constants to be found by applying appropriate boundary conditions.2.5 × 1 + α × (λ − 0. A is the cross section area of the member. t ≤ 40 mm h b > 1.3 4 L 250 0. The smallest resulting value of NRd shall be used.3 4 L 250 0. t ≤ 80 mm 5 mm 0.prEN 13001-3-1:2010 (E) Table 13 — Parameter α and acceptable bow imperfections for various cross sections.2 1 0.4 9 0.2 1 0.4 9 0.4 9 0.7 6 0.1 3 0.2 shall be applied to all parts of the member. Buckling about axis Type of cross section 1 2 Hollow sections α Acceptable maximum bow imperfectio n L 300 0.2 1 hy t y < 30 4 Acceptable maximum bow imperfectio n f y ≥ 460 N 2 y− y z−z Welded box sections Rolled sections α N mm2 Hot rolled Thick welds and 3 f y < 460 y− y z−z y− y z−z t > 80 mm y− y z−z ti ≤ 40 mm y− y z−z ti > 40 mm y− y z−z Welded I sections 0.2.4 9 L 200 NOTE : L is the length of the member In case of a member with varying cross section.4 9 L 200 hz t z < 30 h b > 1.2.2.2. the equations in 8.2 1 0. L.4 9 0.4 9 0.3 4 L / 250 y− y z−z 0. and in addition it shall be conform to the following: 47 .7 6 L 200 0.3 4 0. 40 mm < t ≤ 80 mm h b ≤ 1.3 4 0.3 4 0.4 9 L 200 L 350 L 350 L 300 L 300 l 250 l 200 L 200 L 150 Channels.4 9 0. T and solid sections y− y z−z 0.3 4 L / 250 y− y z−z 0.1 3 L 350 Cold formed y− y z−z 0.3 4 0.1 3 0.4 9 L 200 0.7 6 L 300 L 250 L 250 L 200 L 150 L 250 L 200 L 200 L 150 0. where b ≤ 2a lm = 2a. there is no instability resulting from the interaction between the local buckling of the plate field and the global buckling of the member containing it. It is assumed that: geometric imperfections of the plate are less than the maximum values shown in Table 14. such case is not covered by this standard.prEN 13001-3-1:2010 (E) NRd ≤ Nk 1.3.e. buckling strength of stiffeners is greater than that of the plate field).3 Buckling of plate fields subjected to compressive and shear stresses 8. stiffeners are designed with sufficient stiffness and strength to allow the required buckling resistance of the plate to be developed (i. Table 14 — Maximum allowable imperfection f for plates and stiffeners 1 2 4 3 l f = m 250 1 General lm = 2b.1 General Plate fields are unstiffened plates that are supported only along their edges or plate panels between stiffeners. where b > 2a f = a 400 . where a > 2b Unstiffened plates 2 3 48 lm = a. where a ≤ 2b Subject to transverse compression Longitudinal stiffeners in plates with longitudinal stiffening l f = m 250 lm = b.2 × γ m (46) NOTE Special consideration should be given to members with thin-walled cross sections which are susceptible to local buckling and possible reduction in their limit compressive design force NRd 8. the plate field is supported along its edges as shown in Table 15. from wheel load. fyk is the minimum yield stress of the plate material.4) applied on one side only.(e.(continued) 4 f Transverse stiffeners in plates with longitudinal and transverse stiffening f = a 400 f = b 400 shall be measured in the perpendicular plane.Rd. x = κ x × f yk γm (47) where: κx is a reduction factor according to Equation (48). Figure 10 shows a plate field with dimensions a and b (side ratio α = a/b).g.Rd. see Annex C. Figure 10 — Stresses applied to plate field Limit design stress with respect to longitudinal stress σ x 8. It is subjected to longitudinal stress varying between σ x (maximum compressive stress) and ψ . coexistent shear stress τ and with coexistent transverse stress σ y . The reduction factor κ is given by: 49 . lm is the gauge length.σ x along its end edges.3.prEN 13001-3-1:2010 (E) Table 14 .x is calculated from: f b.2 The limit design compressive stress fb. 50 .22 = c× − < 1.prEN 13001-3-1:2010 (E) κx κx 1 0. ν is the Poisson’s ratio of the plate.673 (48) c ≤ 1. t is the plate thickness. relative to the maximum compressive stress.12 ×ψ .673 for λ x ≤ 0. The non-dimensional plate slenderness λx is given by: λx = f yk (49) kσ × σ e where: σe is a reference stress according to Equation (50). the side ratio α and the edge support conditions of the plate field.0 λ2x λx = 1.25 − 0. Table 15 gives values for the buckling factor kσ for plate fields supported along both transverse and longitudinal edges (Case 1) and plate fields supported along both transverse edges but only along one longitudinal edge (Case 2).0 with c = 1. The reference stress σe is given by: σe = π2×E t × 2 12 × (1 − υ ) b 2 (50) where: Ε is the elastic modulus of the plate. kσ is a buckling factor given in Table 14. for λ x > 0.25 where: λx is a non-dimensional plate slenderness according to Equation (49). b is the width of the plate field. The buckling factor kσ depends on the edge stress ratio ψ. ψ is the edge stress ratio of the plate. 78ψ 2 1.0 for rows 3 to 6 and α < 0.57 6 0 > ψ > −1 7.07ψ 2 7 ψ = −1 23.05 ψ + 0.81 − 6. see bibliography.3 Limit design stress with respect to transverse stress σ y The limit design transversal normal stress shall be calculated from: f b.0 .3.578 ψ + 1.1ψ 2 0.21ψ + 0.8 0.85 8 ψ < −1 5.07ψ 2 For Case 1 the values and equations for buckling factors kσ given in Table 14 for plate fields supported along all four edges can give overly conservative results for plate fields with α < 1.70 0.21ψ + 0.8 0. Rd . Further information regarding alternative values for short plate fields can be found in additional references.66 for row 7.07ψ 2 2 0. For NOTE Case 2 the results can be overly conservative for plate fields with α < 2.57 − 0.43 8.21ψ + 0. y = κ y . 8.57 − 0.9 23. f yk γm (51) 51 .70 − 5ψ + 17.29ψ + 9.98 x (1-ψ) 23.81 1.34 ψ =0 7.prEN 13001-3-1:2010 (E) Table 15 — Buckling factor kσ Case 1 Case 2 Supported along all four edges Supported along both loaded (end) edges and along only one longitudinal edge. 1 Type of support 2 Stress distribution 3 ψ =1 4 1>ψ > 0 5 4 0.57 − 0.2 0. The reduction factor κ y is given by: 1 κ y = 1.22 λ2y κ y = 1. corresponds to a point load) . kσ is a buckling factor determined using figure 10.831 for λ y ≤ 0.0 for λ y > 0.prEN 13001-3-1:2010 (E) κy is a reduction factor according to Equation (52). f yk is the minimum yield stress of the plate material.831 The non-dimensional plate slenderness λy = λ y is given by: f yk kσ × σ e × (52) a c (53) where: 52 σe is a reference stress according to Equation (50). a is the plate field length c is the width over which the transverse load is distributed ( c = 0 .13 × λy − 0. prEN 13001-3-1:2010 (E) Figure 11 — Buckling factor kσ 8.4 Limit design stress with respect to shear stress τ The limit design buckling shear stress is calculated from: f b.τ = κτ .84 for λτ ≥ 0. 3 (56) f yk is the minimum yield strength of the plate material 53 . Rd . f yk (54) 3 .σ e .84 λτ κτ = 1 (55) for λτ < 0.3.γ m where κτ is a reduction factor given by: κτ = 0.84 where λτ = f yk kτ . 4.3.3.3 8. it shall be proven that: τ Sd ≤ f b. y (58) where: σSd.2.2 Plate fields subjected to shear stress For the plate field under consideration. f b. x ≤ f b.4. x and σ Sd. 54 (59) . σSd.2.2 Plate fields 8.τ where: τ Sd is the design value of the shear stress. it shall be proven that: σ Sd. y ≤ f b. Table 16 — Buckling factor kτ kτ α 8.1 Plate fields subjected to longitudinal or transverse compressive stress For the plate field under consideration.prEN 13001-3-1:2010 (E) kτ is a buckling factor calculated (for a plate field supported along all four edges) using equations given in table 16.34 α2 Execution of the proof 8. fb.x .x . NRd is the limit design compressive force according to 8.τ is the limit design shear stress in accordance with 8. 8.1 Members loaded in compression For the member under consideration.2.4 α>1 kτ = 5.2 and 8.Rd.4.Rd.2.34 + α≤1 kτ = 4 + 4 α2 5.4.Rd.Rd.4.Rd. it shall be proven that: N Sd ≤ N Rd (57) where: NSd is the design value of the compressive force. fb.Rd.y are the design values of the compressive stresses σ x or σ y .y are the limit design compressive stresses in accordance with 8.3. Rd . y τ + Sd f b.4. Rd . f b. x × σ Sd .prEN 13001-3-1:2010 (E) 8. y + f b.4.τ e3 ≤1 (60) where e1 = 1 + κ x4 (61) e2 = 1 + κ 4y (62) e3 = 1 + κ x × κ y × κτ2 (63) and with κ x calculated in accordance with 8.3 and κτ in accordance with 8. y e2 σ Sd . apart from a separate proof carried out for each stress component in accordance with 8.2. κ y in accordance with 8.1 and 8.σ Sd . x . ( ) V = κx ×κ y 6 for σ Sd .3. y > 0 V = −1 for σ Sd . y − V × f b.2. x f b.2. x e1 σ Sd . Rd . Rd . y < 0 (64) 55 . x × σ Sd .3. Rd . it shall be additionally proven that: σ Sd .3.2.3 Plate fields subjected to coexistent normal and shear stresses For the plate field subjected to coexistent normal (longitudinal and/or transverse) and shear stresses.4. x .2.4. 9 53.4 333.1 M22 23 52.8 10.8 10.8 253.3 164.3 237.0 349.4 196.Rd per fit bolt and per shear plane for multiple shear plane connections Table A.0 235.4 105.9 291.3 139.9 M20 20 39.6 8.8 59.9 400.2 17.4 M24 24 56.9 278.4 324.2 107.0 Table A.1 4.9 71.2 — Limit design shear force Fv.9 44.4 M16 17 28.4 178.4 64.4 116.9 213.2 M24 25 61.6 97.0 M22 22 47.5 M30 30 89.1 M16 16 25.Rd in the shank per standard bolt and per shear plane for multiple shear plane connections Fv.8 127.5 148.9 231.4 M27 27 72.9 12.Rd kN Bolt Shank diameter Bolt material for γ Rb = 1.3 M27 28 77.1 192.5 94.2 M30 31 95.6 62.6 5.Rd Fit bolt Shank diameter kN Fit bolt material mm for γRb = 1.1 111.8 37.6 67.8 77.9 113.6 179.6 428.2 196.1 90.prEN 13001-3-1:2010 (E) Annex A (informative) Limit design shear force Fv.Rd per fit bolt and per shear plane for multiple shear plane connections Fv.0 206.2 128.6 5.6 256.5 215.7 20.3 31.6 35.9 M12 12 14.6 8.2 151.6 .1 mm 56 4.5 54.2 163.8 75.6 356.2 65.9 M12 13 16.1 — Limit design shear force Fv.9 12.6 M20 21 43.5 49.0 111.7 76.3 270. 1 — Tightening torques in Nm to achieve the maximum allowable preload level 0. 57 .9 M12 86 122 145 M14 136 190 230 M16 210 300 360 M18 290 410 495 M20 410 590 710 M22 560 790 950 M24 710 1 000 1 200 M27 1 040 1 460 1 750 M30 1 410 2 000 2 400 M33 1 910 2 700 3 250 M36 2 460 3 500 4 200 Note A friction coefficient µ = 0.14 is assumed in the calculations of the preceding tightening torques.9 12.7 × Fy Bolt size Bolt material 8.prEN 13001-3-1:2010 (E) Annex B (informative) Preloaded bolts Table B.8 10. 9 53.9 20.9 119 28.7 209 167 126 83.0 21.3 11.8 35.8 36.5 21.6 49.4 205 164 123 82.3 32.30 0.3 15.8 115 92.8 10.8 13.20 M12 84.50 0.6 M27 459 206 289 347 82.6 76.5 M22 303 136 191 229 54.2 60.6 73.40 0.6 56.9 12.4 20.8 47.3 73.9 59.40 0. γss = 1.6 13.7 20.3 57.9 Slip factor : Slip factor : Slip factor : 8.5 61.9 28.2 10.prEN 13001-3-1:2010 (E) Table B.7 70.6 58.0 26.2 36.9 0.0 6.7 8.3 M30 561 251 353 424 100 80.2 28.20 0.2 46.1 50.9 45.9 M18 192 86.6 34.3 8.4 49.9 M16 157 70.2 32.4 12.1 63.1.3 17.9 12.d = 0.7 30.6 28.9 24.6 174 139 105 69.0 121 145 34.9 46.2 88.4 169 135 101 67.7 M36 817 366 515 618 146 117 87.2 16.5 72.3 37.2 74.14 2 Bolt material 58 8.50 0.8 11.3 27.4 91.8 42.2 — Limit design slip force FS.7 23.Rd per bolt and per friction interface using a design preloading force Fp.20 0.1 60.2 39.0 65.4 37.2 M14 115 51.7 15.5 106 85.6 M33 694 311 437 525 124 99.8 25.3 37.1 40.40 0.8 10.3 98.0 22.7 × f yb × As Bolt stress area Design preloading force Fp.5 86.9 12.1 43.1 54.1 12.1 138 111 83.8 53.0 55.3 34.2 35.d in kN AS Bolt material mm Limit design slip force Fs.5 .0 9.9 23.6 23.2 38.4 20.30 0.1 44.30 0.5 16.4 31.7 15.1 63.4 18.50 0.5 M24 353 158 222 267 63.Rd in kN γm = 1.2 M20 245 110 154 185 43.5 25.4 16.1 246 197 148 98.1 17.2 69.5 49.7 27.1 141 113 84.3 29.7 48.9 19. Sd = ar × lr ar × lr (C. the effective weld length lr is given by: lr = lW − 2 × ar (for continuous welds) unless measures are taken to ensure that the whole weld length is effective.Sd C.1).1 — Butt weld The effective weld thickness a r is calculated from: ar ≤ min(t1.Sd and shear weld design stress τ W .Sd = σ W .prEN 13001-3-1:2010 (E) Annex C (normative) Design weld stress σW. ar is the effective weld thickness. In general.t 2 ) for full penetration welds ar = 2 × ai for double sided symmetrical partial penetration welds where ai NOTE is the thickness of either welds Single sided partial penetration butt welds with transverse loads are not covered by this standard. lr is the effective weld length. in which case l r = l W 59 . τ W. Figure C.1) where Fσ is the acting normal force (see Figure C.1 Butt joint Normal weld design stress σ W.Sd and τW. Fτ is the acting shear force (see Figure C.1).Sd are calculated from: Fσ Fτ . τ W.2 — Joint dimensions The effective weld thickness ar is limited to: ar ≤ 0. Sd = ar1 × lr1 + ar2 × lr2 ar1 × lr1 + ar2 × lr2 (C.Sd and τ W . t2 ) . Sd and shear weld design stress τ W. For single sided welds. For the effective weld lengths see C. ari are the effective weld thicknesses (see Figure C. Fτ is the acting shear force (see Figure C.2). t2 thicknesses of the plates. Single sided welds may be used loaded with forces as shown in Figure C.2) where Fσ is the acting normal force (see Figure C. 60 . σ W .2.1.Sd = Fσ Fτ .7 × min( t1.Sd are calculated in an analogous manner using the relevant weld parameters.2). Figure C.1).prEN 13001-3-1:2010 (E) where lW is the weld length (see Figure C. ar is the effective weld thickness. t1 . C. Sd are calculated from: σ W.2). with ari = ai lri are the effective weld lengths.2 Fillet weld Normal weld design stress σ W. Fτ is the acting shear force (see Figure C. Sd and shear weld design stress τ W.prEN 13001-3-1:2010 (E) C.3.4 Effective distribution length under concentrated load For simplification the normal design stresses in the weld and parent material under concentrated load may be calculated using the effective distribution length as follows l r = 2 × hd × tan κ + λ (C.3). Sd are calculated from: Fσ Fτ . τ W. Figure C.3) where Fσ is the acting normal force (see Figure C. Sd and τ W. Sd = σ W. ari are the effective weld thicknesses (see Figure C.4) 61 . C. Sd are calculated in an analogous manner using the relevant weld parameters.3 — Joint dimensions The effective weld thickness ar is limited to: ar ≤ 0. with ari = ai + ahi lri are the effective weld lengths. Single sided welds may be used loaded with forces as shown in Figure C.1. t2 ) .3).7 ⋅ min( t1.3). σ W. For the effective weld lengths see C. Sd = ar1 × lr1 + ar2 × lr2 ar1 × lr1 + ar2 × lr2 (C.3 T-joint with full and partial penetration Normal weld design stress σ W. For single sided welds. κ is the dispersion angle.2 × r with λmax = 50 mm where r is the radius of wheel. For wheels λ may be set to: λ = 0. 62 . κ shall be set to κ ≤ 45° . λ is the length of the contact area. hd is the distance between the section under consideration and contact level of acting load . Figure C. however the values for ∆σ c and ∆τ c in Annex D are based on the calculation presented herein.prEN 13001-3-1:2010 (E) where lr is the effective distribution length .4 — Concentrated load Other calculations for the determination of the design stresses may be used. flat bars.prEN 13001-3-1:2010 (E) Annex D (normative) Values of slope constant m and characteristic fatigue strength ∆σc. ∆σc ∆ τc 2 N/mm Constructional detail Requirements General requirements: m=5 Rolled surfaces No geometrical notch effects (e. rolled profiles under normal stresses - 1.1 140 Independent of fy 140 180 ≤ fy ≤ 220 160 220 < fy ≤ 320 180 320 < fy ≤ 500 - - 200 500 < fy - - - 180 180 ≤ fy ≤ 220 200 220 < fy ≤ 320 225 320 < fy ≤ 500 - 250 500 < fy ≤ 650 - 280 650 < fy ≤ 900 315 900 < fy Surface condition in accordance with EN10163 classes A1 or C1 (repair welding allowed) Surface condition in accordance with EN10163 classes A3 or C3 Surface roughness Rz ≤ 100µm Edges rolled or machined or no free edges Any burrs and flashes removed from rolled edges Surface roughness Rz ≤ 60 µm +1 NC Surface condition in accordance with EN10163 classes A3 or D3 Surface roughness Rz ≤ 20µm Edges machined or no free edges 63 .g.2. Table D.1 — Basic material of structural members Detail No. ∆τc Notch classes (NC) refer to the first column of Annex E (see 6.1). cut outs) Surface roughness values before surface treatment such as shot blasting Plates. flat bars.1 .2 m=5 - General requirements: Rolled surfaces Thermal cut edges No geometrical notch effects (e. g. ∆σc ∆ τc 2 N/mm Constructional detail Requirements - 1. cutouts) Surface roughness values before surface treatment such as shot blasting Edges in plates.prEN 13001-3-1:2010 (E) Table D.Continued Detail No. rolled profiles under normal stresses 140 Independent of fy - 140 180 ≤ fy ≤ 220 - 160 220 < fy ≤ 500 - 64 - 180 500 < fy 160 180 ≤ fy ≤ 220 180 220 < fy ≤ 320 200 320 < fy ≤ 500 225 500 < fy ≤ 650 - 250 650 < fy ≤ 900 - 280 900 < fy - - - Surface condition in accordance with EN10163 classes A1 or C1 (repair welding allowed) Edge quality in accordance with Table 5 Range 3 of EN ISO 9013 Edge quality in accordance with Table 5 Range 3 of EN ISO 9013 Surface condition in accordance with EN10163 classes A3 or C3 Surface roughness Rz ≤ 100µm Mill scale removed before cutting Machine controlled cutting Plate surface roughness Rz ≤60µm and edge quality in accordance with Table 5 Range 2 of EN ISO 9013 +1NC Edge quality in accordance with Table 5 Range 1 of EN ISO 9013 Surface condition in accordance with EN10163 classes A3 or C3 Plate surface roughness Rz ≤20µm Mill scale removed before cutting Machine controlled cutting . ∆σc ∆ τc 2 N/mm Constructional detail Requirements General requirements: Nominal stress calculated for the net cross-section Holes not flame cut.Continued Detail No.1 .3 80 Independent of fy - Holes may be punched 100 180 < fy ≤ 220 - 112 220 < fy ≤ 320 125 320 < fy ≤ 500 140 500 < fy ≤ 650 160 650 < fy Holes machines or thermal cut to a quality in accordance with Table 5 Range 3 of EN ISO 9013 Holes not punched Burr on hole edges removed Rolled surface condition in accordance with EN 10163 classes A3 or C3 Plate surface roughness Rz ≤100µm - - 65 . Bolts may be present as long as these are stressed to no more than 20 % of their strength in shear/ bearing connections or to no more than 100 % of their strength in slipresistant connections m=5 Hole edges in a plate under normal stresses 1.prEN 13001-3-1:2010 (E) Table D. 4 - 90 Independent of fy 90 180 ≤ fy ≤ 220 - 100 220 < fy ≤ 320 - 112 320 < fy ≤ 500 - 125 500 < fy - 66 - 112 180 ≤ fy ≤ 220 - 125 220 < fy ≤ 320 - 140 320 < fy ≤ 500 - 160 500 < fy ≤ 650 180 650 < fy ≤ 900 200 900 < fy Surface condition in accordance with EN10163 classes A1 or C1 (repair welding allowed) Surface condition in accordance with EN10163 classes A3 or C3 Surface roughness Rz ≤ 100µm Edges rolled or machined or no free edges Any burrs and flashes removed from rolled edges Surface roughness Rz ≤ 60 µm +1 NC Surface condition in accordance with EN10163 classes A3 or D3 Surface roughness Rz ≤ 20µm Edges machined or no free edges . flat bars. rolled profiles under shear stress 1. cut outs) Surface roughness values before surface treatment such as shot blasting Plates.Concluded Detail No.1 .g. ∆σc ∆ τc 2 N/mm Constructional detail Requirements - m=5 General requirements: Rolled surfaces No geometrical notch effects (e.prEN 13001-3-1:2010 (E) Table D. 2. not supported Normal stress Fit bolts in double-shear or supported single-shear joints 125 Shear stress (∆τc) 355 Bearing stress (∆σc) m=5 2.prEN 13001-3-1:2010 (E) Table D.3) Pinned connections are considered in the proof of fatigue strength as structural members.2 160 f y ≤ 275 180 275 < f y m=5 180 2.8 or better) 50 Machined thread 63 Rolled thread above M30 71 Rolled thread for M30 or smaller (see 5. using ∆Fb double-shear and supported single-shear Normal stress Perforated parts in shear/bearing connections under normal stresses single-shear joints.3 m=5 125 m=5 2.6 NOTE Nominal stress calculated for the net cross-section Nominal stress calculated for the net cross-section Uniform distribution of stresses is assumed Uniform distribution of stresses is assumed ∆σ calculated for the stress-area of the bolt. 67 .1 Nominal stress calculated for the net cross-section Single-shear Perforated parts in slip-resistant bolted connections under normal stresses 2. ∆σc ∆ τc 2 N/mm Constructional detail Requirements Double shear Supported single-shear (example) The proof of fatigue strength is not required for bolts of friction grip type bolted connections m=5 2.5 Perforated parts in shear/bearing connections under normal stresses Fit bolts in single-shear joints.4 2.2 —Elements of non-welded connections Detail No.3. not supported 100 Shear stress (∆τc) 250 Bearing stress (∆σc) m=3 Threaded bolts loaded in tension (bolt grade 8. prEN 13001-3-1:2010 (E) Table D.3 — Welded members Detail No. ∆σc ∆ τc 2 N/mm Constructional detail Requirements Basic conditions: symmetric plate arrangement fully penetrated weld Components with usual residual stresses Angular misalignment < 1° t1 = t2 or m=3 slope <1:3 Symmetric butt joint, normal stress across the weld 3.1 Special conditions: Components with considerable residual stresses (e. g. joint of components with restraint of shrinkage) -1 NC 140 Butt weld, quality level B* -2 NC 125 Butt weld, quality level B -4 NC 112 Butt weld, quality level C - 4 NC Basic conditions: 3.2 m=3 symmetric plate arrangement fully penetrated weld Components with usual residual stresses Angular misalignment < 1° Special conditions: Symmetric butt joint, normal stress across the weld 80 68 Butt weld on remaining backing, quality level C Components with considerable residual stresses (e. g. joint of components with restraint of shrinkage) -1 NC prEN 13001-3-1:2010 (E) Table D.3 - Continued Detail No. ∆σc ∆ τc 2 N/mm Constructional detail Requirements Basic conditions: fully penetrated weld Supported parallel to butt weld: e < 2⋅t2 + 10mm Supported vertical to butt weld: e < 12⋅t2 Components with usual residual stresses slope ≤ 1:3 m=3 t2 - t1 ≤ 4 mm 3.3 Unsymmetrical supported butt joint, normal stress across the butt weld Special conditions: Components with considerable residual stresses (e. g. joint of components with restraint of shrinkage) -1 NC Influence of slope and thickness t2-t1: thickness 125 Butt weld, quality level B* 112 Butt weld, quality level B 100 Butt weld, quality level C t 2 − t1 slope ≤4 ≤1:3 – ≤1:2 -1NC ≤1:1 -1NC ≤ 10 -1NC -1NC -2NC ≤ 50 -1NC -2NC -2NC >1:1 - -2NC -2NC -3NC -3NC > 50 -2NC -2NC -3NC Basic conditions: fully penetrated weld supported parallel to butt weld: e < 2⋅t2 + 10mm supported vertical to butt weld: e < 12⋅t2 3.4 m=3 components with usual residual stresses Unsymmetrical supported butt joint, normal stress across the butt weld t2 - t1 ≤ 10 mm Special conditions: components with considerable residual stresses (e. g. joint of components with restraint of shrinkage) -1 NC t2 - t1 > 10 mm -1 NC 69 prEN 13001-3-1:2010 (E) Table D.3 - Continued Detail No. ∆σc ∆ τc 2 N/mm Constructional detail 80 Butt weld on remaining backing, quality level C Requirements Basic conditions: fully penetrated weld components with usual residual stresses slope ≤ 1:1 slope in weld or base material t1/t2 > 0,84 m=3 Special conditions: 3.5 components with considerable residual stresses (e. g. joint of components with restraint of shrinkage) Unsymmetrical unsupported butt joint, stress across the butt weld -1 NC -2 NC 100 Butt weld, quality level B* t1/t2 > 0,74 -1 NC 90 Butt weld, quality level B t1/t2 > 0,63 -2 NC 80 Butt weld quality level C t1/t2 > 0,50 -3 NC t1/t2 > 0,40 -4 NC Basic conditions: m=3 3.6 Butt joint with crossing welds, stress across the butt weld 70 125 Butt weld, quality level B* 100 Butt weld, quality level B 90 Butt weld, quality level C components with usual residual stresses 1 NC Cross or T-Joint. symmetric double fillet weld automatic welding. quality level B 100 K-weld.1 NC m=3 3.prEN 13001-3-1:2010 (E) Table D.9 m=3 Cross or T-Joint. no initial points +1 NC welding with restraint of shrinkage -1 NC 71 . quality level C 71 V-weld with full penetration and backing.8 automatic welding. quality level C 80 Intermittent weld. no initial points +1 NC welding with restraint of shrinkage . quality level B 80 K-weld. quality level C Basic conditions: continuous weld Special conditions: m=3 3.7 Normal stress in weld direction 180 Continuous weld.3 . quality level B 140 Continuous weld. normal stress across the weld * 112 K-weld. quality level C Basic conditions: continuous weld Special conditions: 3.Continued Detail No. ∆σc ∆ τc 2 N/mm Constructional detail Requirements Special conditions: no irregularities from startstop-points in quality level C + 1 NC welding with restraint of shrinkage . groove weld. 3 . g. wheel) 72 112 Quality level B 100 Quality level C .prEN 13001-3-1:2010 (E) Table D. Quality level B 71 Stresses in plate at weld toe.11 Full penetration weld (double sided) with transverse compressive load (e. stresses from bending Stress calculated with the applied bending moment and weld joint geometry taken into account 45 Stress in weld throat 80 Stresses in plate at weld toe. Quality level C m=3 3.Continued Detail No. ∆σc ∆ τc 2 N/mm Constructional detail 45 Stress in weld throat 71 Quality level B 63 Quality level C Requirements σ w = F /(2 × a × l ) see Annex C Stress in the loaded plate at weld toe m=3 3.10 T-Joint. wheel). 3.14 m=3 p=1mm for t≤6mm p≥ t for t>6mm 4 Partial penetration weld with transverse compressive load (e. wheel). (e.5 ⋅ t ≤ a ≤ 0.prEN 13001-3-1:2010 (E) Table D.Continued Detail No. g.3 . stress calculated in the plate 71 Quality level C 73 .5 ⋅ t ≤ a ≤ 0.13 Quality level C 0. g.7 ⋅ t with a according to Annex C 3. stress calculated in the plate 71 Quality level C 0.7 ⋅ t m=3 Double fillet weld with transverse compressive load. wheel) 80 3. g.12 ∆σc ∆ τc 2 N/mm Constructional detail Requirements m=3 Full penetration weld (with backing) with transverse compressive load (e. 7 × t with a according to Annex C 3.Continued Detail No. g.5 × t ≤ a ≤ 0. stress calculated in the plate 63 Quality level C Basic conditions: quality level C continuous weld distance c between the weld toe and rim of continuous component greater than 10 mm Special conditions: m=3 quality level B NC +2 quality level B NC +1 quality level D NC -1 c < 10 mm NC -1 3.prEN 13001-3-1:2010 (E) Table D. ∆σc ∆ τc 2 N/mm Constructional detail Requirements 0. underslung crab).16 Continuous component with a welded cover plate 74 80 l ≤ 50 mm 71 50 mm < l ≤ 100 mm 63 l > 100 mm * .15 m=3 p=1mm for t ≤ 6mm p≥ t 4 for t > 6mm Partial penetration weld with transverse load (e.3 . 5 tu Continuous component with load carrying flange plate.Continued Detail No.3 . edge weld and end of flank weld in weld quality level B* Basic conditions: 3. stress in continuous component at end of connection 80 Edge weld and end of flank weld in weld quality level B* 75 .17 Continuous component with load carrying flange plate.prEN 13001-3-1:2010 (E) Table D.18 m=3 continuous fillet or groove weld to ≤ 1. edge weld and end of flank weld in weld quality level B* 100 Flange plate with end chamfer ≤ 1:2. stress in continuous component at end of connection 112 Flange plate with end chamfer ≤ 1:3. ∆σc ∆ τc 2 N/mm Constructional detail Requirements Basic conditions: m=3 continuous fillet or groove weld 3. 19 continuous fillet or groove weld Continuous component with load carrying flange plate. ∆σc ∆ τc 2 N/mm Constructional detail Requirements Basic conditions: m=3 3. bL + l ) 3. lap plates 76 .prEN 13001-3-1:2010 (E) Table D.3 . stress in continuous component at end of connection 63 Quality level B 56 Quality level C Basic conditions: stressed area to be calculated from: As = t × lr m=3 lr = min( bm . main plate * 80 Quality level B 71 Quality level B 63 Quality level C m=3 Basic conditions: 3.21 stressed area to be calculated from: As = bL × (tL1 + tL 2 ) 50 Overlapped welded joint.Continued Detail No.32 Overlapped welded joint.20 see also detail 3. 22 Continuous component with longitudinally mounted parts.3 . Parts rounded or chamfered 90 Quality level B* 80 Quality level B 71 Quality level C end welds in a zone of at least 5 t fully penetrated +1 NC Basis conditions: allround fillet weld quality level B. welded to edge R ≥ 150 mm or α ≤ 45° +1 NC R < 50mm or α > 60° -2 NC end welds in a zone of at least 5 t2 fully penetrated with quality level B* +1 NC 77 .prEN 13001-3-1:2010 (E) Table D. α ≤ 60° for quality levels B or C R ≥ 150 mm.23 single fillet weld -1 NC weld quality level D -1 NC Continuous component with parts ending perpendicularly 80 l ≤ 50 mm 71 50 mm < l ≤ 100 mm 63 100 mm < l ≤ 300 mm 56 l > 300 mm Basic conditions: R ≥ 50 mm or α ≤ 60° t2 ≤ t1 butt weld or all-round fillet weld Special conditions: 3.24 m=3 Continuous component with longitudinally mounted parts. C Special conditions: m=3 3. α ≤ 45° for quality level B* groove weld or allround fillet weld Special conditions: 3. ∆σc ∆ τc 2 N/mm Constructional detail Requirements Basic conditions: m=3 R ≥ 50 mm.Continued Detail No. 3 . quality level B* c < 10 mm 100 Double fillet weld.prEN 13001-3-1:2010 (E) Table D.26 plate thickness t > 12 mm (Double fillet welds only) 1 NC Continuous component to which parts are welded transversally 112 Double fillet weld. quality level B 90 Double fillet weld.Continued Detail No. quality level B. quality level C 71 Single fillet weld. ∆σc ∆ τc 2 N/mm Constructional detail 80 Quality level B 71 Quality level C Requirements Basic conditions m=3 c ≥ 10 mm quality level C Special conditions: 3. quality level B. C quality level D instead of C-1 NC -1 NC Basic conditions: plate thickness t ≤ 12 mm c ≥ 10 mm Special conditions: 3.27 m=3 Continuous component to which stiffeners are welded transversally 78 plate thickness t > 12 mm (double fillets only) -1 NC c < 10 mm K-weld instead of double fillet weld +1 NC quality level D instead of C -1 NC -1 NC .25 Continuous component with overlapping parts b ≤ 50 mm and quality level B NC +1 80 b ≤ 50 mm quality level D -1 NC 71 50 mm < b ≤ 100 mm c < 10 mm -1 NC 63 b > 100 mm Basic conditions: m=3 plate thickness t ≤ 12 mm c ≥ 10 mm quality level D not allowed for K-weld Special conditions: 3. C K-weld instead of double fillet weld +1 NC 71 Partial penetration V-weld on remaining backing. 29 R ≥ 50 mm. C 71 Partial penetration V-weld on remaining backing.3 . α ≤ 45° +1 NC end welds in the zone of at least 5 t fully penetrated +2 NC Continuous component with longitudinally mounted parts. C Requirements m=3 3. α ≤ 60° Special conditions: m=3 R ≥ 100 mm. parts through hole 80 Parts rounded or chamfered 79 . quality level B. quality level C 71 Single fillet weld. ∆σc ∆ τc 2 N/mm Constructional detail 112 Double fillet weld.Continued Detail No.28 Continuous component to which transverse parts or stiffeners are welded intermittently 63 Quality level C 50 Quality level D For parts rounded or chamfered: Basic conditions: 3. quality level B 90 Double fillet weld. quality level B. quality level B* 100 Double fillet weld.prEN 13001-3-1:2010 (E) Table D. g. cylindrical tube (case a) 63 Groove weld. normal stresses calculated in the tube Special conditions: 80 Butt weld. cylindrical tube (case b) quality B +1 NC 56 Groove weld.31 Continuous groove weld. rectangular tube (case b) quality B +2 NC 45 Double fillet weld.7 tube thickness flange thickness greater than two times tube thickness (for middle figure) Tubes under axial and bending loads. joint of components with restraint of shrinkage) -1 NC no initial points +1 NC . ∆σc ∆ τc 2 N/mm 56 Constructional detail Requirements Parts ending perpendicularly Basic conditions: m=3 3.30 quality level C groove weld fully penetrated fillet weld thickness a > 0. single or double fillet weld under uniform shear flow 80 112 With full penetration 90 Partial penetration components with considerable residual stresses (e.prEN 13001-3-1:2010 (E) Table D.Continued Detail No.3 . rectangular tube (case c) * Basic conditions: m=5 quality level C components with usual residual stresses Special conditions: 3. cylindrical tube (case c) 40 Double fillet weld. 32 m=5 load is assumed to be transferred by longitudinal welds only Weld in lap joint.Continued Detail No.prEN 13001-3-1:2010 (E) Table D.3 . ∆σc ∆ τc 2 N/mm Constructional detail Requirements Basic conditions: 3. shear with stress concentration 71 Quality level B 63 Quality level C 81 . 9 705.3 504.0 200.0 504.0 254.2 20.6 28.4 448.4 178.0 402.6 56.9 70.0 508.9 113.8 141.8 80.4 20.7 256.5 252.6 160.8 22.8 63 400.6 560.7 72.7 630.0 888.0 101.0 50.8 280 1777.2 71.9 907.0 225 1428.0 158.6 282.0 31.2 224.0 88.7 1133.4 57.2 22.8 141.0 15.6 181.3 567.9 1411.0 203.6 45.2 36 228.5 713.1 1120.8 180 1142.0 201.0 177.1 160.3 44.0 88.0 127.0 403.1 — Details with m = 3 and NC.6 71.0 127.0 1000.4 200 1269.7 25.9 1000.6 181.8 56 355.6 282.3 40.4 44.0 50.7 113.3 25.0 177.6 56.0 100.0 158.9 705.8 284.1 1789.0 317.7 126.7 126.0 114.1 112.7 72.6 160.6 125 793.8 40.25 ∆σRd 2 N/mm 2 S02 S01 S0 S1 S2 S3 S4 S5 S6 S7 S8 S9 355 2254.5 453.8 126.6 90. +1 NC is one line above.7 40 254.1 28 177.0 142.0 158.2 45 285.0 158.4 178.0 57. ∆σc N/mm γ mf = 1.6 82 .4 36.3 90.0 50.7 100.4 360.8 180.0 714.0 79.7 126.2 224.6 80.1 112.0 400.8 284.9 89.9 113.6 80.7 226.0 452.0 100.0 31.0 57.0 201.4 63.0 63.3 51.1 250 1587.0 101.0 225.3 28.6 32.4 64.3 200.3 32.1 720.0 444.9 315 2000.6 28.6 160.0 200.0 400.9 806.1 793.5 252.6 64.7 226.8 357.8 40.4 40.3 128.0 100.6 80.7 36.0 127.0 100.4 100 635.8 180.0 502.2 40.0 79.0 114.0 200.0 500.2 161.4 144.5 50.8 14.5 50.5 252.5 72.0 201.4 1259.1 112.0 31.0 285.0 317.6 71.6 282.2 225.0 225.0 100.7 126.0 635.4 80 508.8 281. -1 NC is one line below.6 20.2 321.3 640.5 252.4 90.9 288.5 352.1 320.9 800.7 568.8 180.1 56.0 317.9 144.1 25 158.4 144.6 140 888.0 28.5 224.0 793.8 141.8 35.1 45.8 35.0 317.8 357.9 70.6 562.5 50.5 80.0 63.8 633.8 141.1 45.2 564.3 90.0 403.7 25.7 630.0 285.3 16.0 100.0 254.4 40.0 201.0 158.4 17.0 25.9 142. Table E.0 251.5 1260.8 80.0 114.1 1587.2 50 317.9 315.8 80.7 226.9 448.5 252.6 360.1 1420.1 35.0 200.7 160 1015.3 90.5 453.0 355.2 142.0 228.0 112 711.0 63.9 1007.0 504.9 18.0 1127.2 161.8 45.1 56.prEN 13001-3-1:2010 (E) Annex E (normative) Calculated values of limit design stress range ∆σRd One row is representing a notch class (NC) for basic conditions.0 355.0 571.0 450.3 128.4 63.8 128.6 400.0 177.3 71 450.1 894.6 64.9 900.2 320.6 89.1 32 203.0 396.9 12.0 142.6 361.6 22.2 112.4 90 571.2 179.0 101. 7 102.3 457.0 63 174.8 160.8 29.6 80 221.9 50.3 125.6 48.9 80.6 225 623.0 29.6 54.2 83 .9 147.7 72.5 295.3 493.8 250 693.6 90 249.4 144.9 113.6 22.4 19.3 224.3 190.8 25.0 156.0 165.0 97.9 294.4 43.4 89.2 445.6 358.4 200 554.6 438.0 73.1 21.7 169.0 114.7 39.4 97.0 168.2 284.8 237.4 109.5 44.3 105.4 111.3 45 124.0 82.2 — Details with m = 5 and NC.9 100.5 64.8 30.7 200.1 91.3 60.9 96.6 47.6 25.3 204.7 38.2 501.0 17.4 210.9 100 277.7 77.4 760. ∆σc N/mm γ mf = 1.0 169.8 135.7 228.5 206.3 286.2 256.9 576.4 36.1 95.1 164.0 34.3 241.6 78.8 151.9 24.1 74.7 199.7 86.1 183.2 58.0 44.1 434.2 129.4 28 77.7 22.8 30.0 27.7 326.8 543.6 94.6 82.5 45.0 25 69.0 280 776.5 270.6 250.0 69.0 84.5 79.8 180.9 159.8 193.8 128.4 155.0 20.7 48.1 28.0 67.1 603.3 398.7 262.9 171.0 50 138.4 149.6 38.8 411.0 219.3 512.3 121.2 77.2 63.2 44.9 65.9 229.0 140 388.5 84.9 125 346.1 182.5 60.1 222.0 62.8 49.5 378.1 43.9 40.5 41.3 135.8 45.9 649.5 289.3 19.4 191.7 136.3 87.4 25.0 55.1 347.9 38.1 242.3 312.2 336.2 56.4 73.3 180 499.1 98.3 661.2 100.2 315 873.2 215.2 117.9 67.9 194.0 31.0 87.1 173.8 318.1 382.5 84.3 97.9 57.1 51.2 102.1 168.7 112.3 71.4 115.5 51.3 40 110.6 301.7 420.1 132.7 430.8 112 310.0 332.3 127.4 15.7 254.0 34.1 472.6 386.6 143.0 111.9 389.8 39.7 105.1 146.3 675.3 36 99.2 109.8 108.0 247.5 217.4 565.4 43.8 34.2 56 155.3 218.25 ∆σRd.5 252.7 303.2 337.7 62.8 32.2 365.1 75.2 139.8 588.7 152.6 67.2 189.4 525.8 118.5 71 196.4 339.2 67.8 33.9 75.8 147.9 178.9 89.0 125.0 128.7 54.8 51.9 745.5 211.5 17.5 482.7 55.2 292.1 121.8 222.0 139.8 86.9 272.3 52.5 42.1 160 443.6 52.1 263.3 50.1 151.2 36.9 59.6 69.4 23.6 58.9 34.5 38.3 27.6 91.6 65.6 76.1 2 N/mm 2 S02 S01 S0 S1 S2 S3 S4 S5 S6 S7 S8 S9 355 984.3 856.prEN 13001-3-1:2010 (E) Table E.2 329.5 194.0 195.5 374.3 235.0 33.6 132.5 57.0 174.6 120.4 66.6 257.3 26.5 278.8 32 88.6 60. The total number of working cycles of a crane during its useful life can be divided into several typical tasks with the numbers of working cycles corresponding to them. Before the sequence of stress peaks occurring during the performance of any task can be evaluated. A task can be characterized by a specific combinations of crane configuration and sequence of intended movements.e. 84 . the corresponding series of loadings has to be determined first. hopper (point 2) and stockpile (points 31 and 32). 1 and 11).1 — Example of load and moment variations due to load movements for tasks on a ship unloader The unloader handles bulk material from ship to hopper or stockpile. position and direction of all loads. the ranges of points to be served are given by the arrangement of the ship (points 12. their direction and position during the use of the crane. the magnitude. as well as on the crane configuration. i.prEN 13001-3-1:2010 (E) Annex F (informative) Evaluation of stress cycles (example) The stress histories at a selected point of the structure depend on the loads. Key A B C System Influence lines for bending at selected point j Influence lines for shear at selected point j D Sequences of movements E Extreme values of bending Mj and shear Qj (φ 2= 1) during sequences of movements Figure F. The complete stress history is obtained by summating the individual stress histories taken from the sequences of movements of all different tasks. underlined when the grab (load lifting attachment) is grounded. moving load from ship (point 11) to hopper (point 2) and moving load from stockpile (point 31) to hopper (point 2).A when load dropped d 11 Lifted T.A j 31 Grounded T The sequences of stresses arising from the bending moment Mj ( σ (t ) = global bending stress) and the shear force Qj ( τ (t ) = global shear stress) can be determined directly from the influence lines. In the encoded description of each task. the point labels are: linked by the sign “+” for working movements (with load) and “-“ for dead movements (without load). i. The description of salient points of the bending moment and shear load variations can be found in Table F. grab). 85 .prEN 13001-3-1:2010 (E) Figure F.1 – Description of salient points in bending moment and shear load variations Point Trolley position Grab position Acting loads a 11 Grounded T b 11 Lifted T. Stress cycles can be identified from the resulting sequences of stress peaks using one of the established stress cycle counting methods. Table F.P and T.1.A e 11 Grounded T f 31 Grounded T g 31 Lifted T.P and T. such as the Rainflow counting method or the Reservoir method.A.e.A when load dropped i 31 Lifted T.A. P for payload.P h 2 Lifted T.A.A.P c 2 Lifted T.1 shows the different sequences of movements of an unloader for two tasks considered. A for lifting attachment. The influence lines (representing the influences of loading and its position) for bending moment Mj and shear force Qj at the selected point j are shown for different loads (T for trolley. 1 — Types of connections loaded in tension The stiffnesses for connections in tension can be calculated as follows: The stiffness of the connected parts is calculated from Kc = E × Aeq lK where Kc is the stiffness (slope) of flanges E is the modulus of elasticity lK is the effective clamped length (including all clamped components) with lK = l1 + l2 86 (G.1) . Figure G.prEN 13001-3-1:2010 (E) Annex G (informative) Calculation of stiffnesses for connections loaded in tension The determination of stiffnesses of elements for the calculation of bolt joints in tension presented in this annex applies in the ideal cases shown in Figure G. Adjacent bolts and/or the way of introduction of external forces into the system have great influence on the additional bolt force and should be considered in actual design.1 assuming no more than 5 contact surfaces in practical joints. 5 × d + = × K b E Ar π × d2 (G.4) π for d W + lK < DA Aeq = π 4 2 × (d W − dh2 ) + π where DA is the diameter of the available cylinder of clamped material dw is the diameter of the contact area under the bolt head Aeq is the equivalent area for calculation dh is the diameter of the hole lK is the effective clamped length The stiffness of the bolt is calculated from 1 1 4 × (l1 + 2 × 0.4 × d ) l2 + 0.prEN 13001-3-1:2010 (E) Aeq is the equivalent area for calculation The calculation of Aeq is in dependence of DA (see Figure G.5) where Kb is the stiffness (slope) of bolt E is the modulus of elasticity l1 is the effective length for tension without thread l2 is the effective length for tension with thread d is the shank diameter Ar is the root area of the bolt 87 .2) for d W ≤ DA ≤ d W + lK : Aeq = π 4 2 × (d W − dh2 ) + 2 lK × d W × d W × ( DA − d W ) × 3 + 1 − 1 2 8 D A (G.1): for DA < d W : Aeq = π 4 × ( DA2 − dh2 ) (G.3) 2 lK × d W × lK × d W × 3 + 1 − 1 (l + d )2 8 W K (G. 1 b) αL = 0.. a) αL = 0. between the bolt end and the connection plane (case b) or close to the connection plane (case c). In cases where the stiffness ratio factor Φ is determined by finite element analysis of the complete joint. 88 .9 . the external load is introduced to the bolt near its end (Figure G.2 — Values for the load introduction factor αL as a function of the connection shape Case a) is typical for bolted connections in cranes..6) where Φ is the stiffness ratio factor Kb is the stiffness of bolt Kc is the stiffness of connected parts αL is the load introduction factor.2. the load introduction factor αL will become an in-built part of the analysis and the value αL = 1 shall be used with the Equation G. see Figure G.3 Figure G. case a). In cases where load introduction cannot be reliably specified.6 c) αL = 0.2. a conservative assumption αL = 1 should be used. This may be considered in calculation of the stiffness ratio factor as follows: Φ = αL × Kb Kb + Kc (G.6.prEN 13001-3-1:2010 (E) According to the shape of the connected parts. More precise values can be found in the literature. or V-weld with weld backing 90 8 < t0 ≤ 25 71 2 < t0 ≤ 8 Requirements The admissible mismatch of the sections due to a change of the plate thickness is ≤ t0/3. In case of a higher mismatch.prEN 13001-3-1:2010 (E) Annex H (informative) Hollow Sections Table H. ∆σc is reduced to 80 % of the given values. but not more than max. 1 without weld backing 89 . No. without backing weld 2 80 2 < t0 ≤ 25 Butt joint with I. especially for a transverse plate butt of rectangular hollow section girders of different dimensions. m = 5 For site welding the given values of ∆σc should be multiplied by the factor 0. ∆σc N/mm 1 90 2 Dimensions mm 2 < t0 ≤ 25 Constructional detail Butt joint with I.1 — Values of inverse slope of ∆σ –N-curve m and limit design stress range ∆σc for connections and joints of hollow sections girders.or V-weld with weld backing 80 8 < t0 ≤ 25 63 2 < t0 ≤ 8 Requirements analogous to No. 2 mm.9. ∆σc N/mm 2 Dimensions mm Constructional detail Requirements Transverse plate butt with semi V-welds (tp ≥ 2 to ) 63 2 < t0 ≤ 25 63 8 < t0 ≤ 25 with weld backing Requirements analogous to No. 1 .prEN 13001-3-1:2010 (E) Table H. 1 3 56 2 < t0 ≤ 8 without weld backing 56 2 < t0 ≤ 25 56 8 < t0 ≤ 25 Transverse plate butt with semi V-welds (tp ≥ 2 to ) with weld backing Requirements analogous to No.1 — Continued No. 1 4 50 2 < t0 ≤ 8 without weld backing Transverse plate butt with semi V-welds (tp ≥ 2 to ) 5 90 45 2 < t0 ≤ 8 Requirements analogous to No. (b > b0) Fillet weld thickness a: for 9 71 6 < t ≤ 12 2 < t0 ≤ 3:a = 2 for 3 ≤ t0 ≤ 25:a ≤ 0.7⋅t0. not bearing transverse loading in y-direction (2 < to ≤ 25). (b > b0) Fillet weld thickness a: for 8 90 2 < t0 ≤ 3:a = 2 6 < t ≤ 12 for 3 ≤ t0 ≤ 25:a ≤ 0. ∆σc N/mm 2 Dimensions mm Constructional detail Requirements Transverse plate butt with semi V-welds (tp ≥ 2 to ) 6 7 40 2 < t0 ≤ 8 80 l ≤ 50 71 50 < l ≤ 100 Fillet weld thickness a = t0 Longitudinally welded outer fin not bearing transverse loading in y-direction (2 < t0 ≤ 25) Fillet weld thickness a: for 2 < t0 ≤ 3:a = 2 for 56 l > 100 100 t≤6 3 ≤ t0 ≤ 25:a = 0. 63 12 < t ≤ 25 but not more than a = 10 91 .7⋅t0.7⋅t0 Transversally welded outer fin with projection. not bearing transverse loading in y-direction (2 < t0 ≤ 25).1 — Continued No. 80 80 but not more than a = 10 12 < t ≤ 25 t≤6 Transversally welded outer fin with projection.prEN 13001-3-1:2010 (E) Table H. 7⋅t0. not bearing transverse loading in y-direction (2 < t0 ≤ 25). 63 100 but not more than a = 10 12 < t ≤ 25 t≤6 Transversally welded outer fin without projections. not bearing transverse loading in y-direction (b. not bearing transverse loading in y-direction (2 < t0 ≤ 25).1 — Continued No.8 b0) Fillet weld thickness a: for 2 < t0 ≤ 3:a = 2 11 90 6 < t ≤ 12 for 3 ≤ t0 ≤ 25:a ≤ 0. ∆σc N/mm 80 2 Dimensions mm t≤6 Constructional detail Transversally welded outer fin without projection.d ≤ b0.prEN 13001-3-1:2010 (E) Table H. 80 but not more than a = 10 6 < t ≤ 12 Welded-on hollow section girder. (b ≤ 0.7⋅t0.8 d0) Requirements Fillet weld thickness a: for 2 < t0 ≤ 3:a = 2 10 71 6 < t ≤ 12 for 3 ≤ t0 ≤ 25:a ≤ 0. (b ≤ 0.d0) 12 92 63 2 < t0 ≤ 8 Fillet weld thickness a = t0 . d)/d0 = 0.d)/d0 = 0. bearing transverse loading F in y-direction (b. (2 < t0 ≤ 8) (b.d)/b0 = 1 Fillet weld thickness 14 12.d ≤ b0).6 t0/t = 1 Welded-on hollow section girder.d)/b0 = 0.1 — Continued No. rounded slot milled at end of tube Fillet weld thickness a = t0 93 .d)/d0 = 1 t0/t ≥ 1 a = t0 (b.6 Single butt strap at chamfered end of tube (d0/t0 < 25) 15 80 Pinched end of tube 2 < t0 ≤ 8 a = 2 t0 Welded double butt strap ((b0.d)/b0 = 0.d0)/t0 < 25) 16 80 2 < t0 ≤ 8 Hot-bended strap.5 40 Requirements t0/t ≥ 1 a = t0 (b.6 t0/t = 1 (b.d)/d0 = 0.d)/b0 = 0.d ≤ d0). (2 < t0 ≤ 8) t0/t = 1 Fillet weld thickness (b. bearing transverse loading F in y-direction (b.prEN 13001-3-1:2010 (E) Table H. ∆σc N/mm 10 36 13 16 50 6 32 2 Dimensions mm t0/t = 1 (b.6 Constructional detail Welded-on hollow section girder.6 t0/t ≥ 1 (b.6 t0/t ≥ 1 (b. (tP ≥ 2. ∆σc N/mm 2 Dimensions mm Constructional detail Requirements Inserted dovetail strap ((b0.7✕tL End face strap (b0/t0 < 25).prEN 13001-3-1:2010 (E) Table H.5 t0) 19 45 Fillet weld thickness for the hollow section girder: a = t0 2 < t0 ≤ 8 for the strap: a = 0.5 t0) 18 56 Fillet weld thickness for the hollow section girder: a = t0 2 < t0 ≤ 8 for the strap: a = 0.d0)/t0 < 25] 20 94 45 2 < t0 ≤ 8 Fillet weld thickness a = t0 .1 — Continued No. (tP ≥ 2.d0)/t0 < 25) 17 71 Fillet weld thickness 2 < t0 ≤ 8 a = t0 End face strap (d0/t0 < 25).7✕tL Inserted rectangular strap [(b0. 1 23 45 8 < a ≤ 14 95 . (ϕ ≥ 90°) 50 8 < t0 ≤ 25 Requirements analogous to No. (ϕ ≥ 90°) Requirements analogous to No. (ϕ ≥ 90°).5 t0) 2<a≤8 Requirements analogous to No. ∆σc N/mm 56 2 Dimensions mm 8 < t0 ≤ 25 Constructional detail Requirements Mitre joint with I. stressed by bending (b0/t0 < 25). 1 21 50 2 < t0 ≤ 8 Mitre joint with I. 1 22 45 2 < t0 ≤ 8 50 Weld thickness a: Mitre joint with transverse plate and fillet welds.prEN 13001-3-1:2010 (E) Table H. stressed by bending (d0/t0 < 25).or V-weld without weld backing.or V.1 — Continued No.weld without weld backing. (tP ≥ 2. stressed by bending (d0/t0 < 25). ∆σc N/mm 45 2 Dimensions mm Weld thickness a: Constructional detail Requirements Mitre joint with transverse plate and fillet welds.1 — Continued No. 1 24 40 45 8 < a ≤ 14 Weld thickness a: Joint of column and transverse girder with fillet welds. (tP ≥ 2.5 t0) 2<a≤8 Requirements analogous to No. stressed by bending (b0/t0 < 25). (ϕ ≥ 90°). stressed by bending (b0/t0 < 25). (b0 ≤ b + 3 r) 2<a≤8 Fillet weld thickness a = t0 where t0 is the existing 25 minimum plate thickness 40 96 8 < a ≤ 14 .prEN 13001-3-1:2010 (E) Table H. d i ) /(b0. d 0 ≤ 120 mm. m = 5 Basic symbols for all items with gap (e ≥ 0) with overlapping (e < 0) Basic requirements for all items Bending in individual members should be included in the calculated nominal stress b0. 97 .5 ≤ e /( h0 .02 (b0. d 0 ) ≤ 0.2 — Values of inverse slope of ∆σ –N-curve m and limit design stress range ∆σc for lattice type connections of hollow section girders. For site welding the given values of ∆σ c should be multiplied by the factor 0. 0.6 ≤ (bi.9. the given values of ∆σ c should be multiplied by the factor f a = 4 120 /(bo . d 0 > 120 mm. d 0 ) / t 0 < 25 . / t i ≥ 1. t 0.prEN 13001-3-1:2010 (E) Table H. d o ) t 0 ≤ 12.5 mm Weld thickness a = min t Incline of the diagonal members: (b0.25 perpendicular to the plane of the lattice work: ≤ 0. d 0 ) ≤ 1 Eccentricity 35° ≤ Θi ≤ 50° in the plane of the lattice work: − 0. d 0 ) Welding under shop conditions. For b0. with overlapping K-T-gusset with direct strut joint 2 t0 / ti = 1 t0 / ti ≥ 2 di / d0 = 0.3 d 0 di / d0 = 0.6 36 71 di / d0 = 1 35 80 0.2 (continued) No .6 36 80 g ≤ 2 / 3 di di / d0 = 1 45 90 0.prEN 13001-3-1:2010 (E) Table H.6 45 80 di / d0 = 1 50 90 b.3 ≤ q / p ≤ 1 N-gusset with direct strut joint b) with gap: 3 t0 / ti = 1 t0 / ti ≥ 2 g ≤ 0.3 d 0 di / d0 = 0. ∆σc (N/mm2) Requirements Intermediate values by straight-line interpolation! K-gussett with direct strut joint a) with gap: 1 t0 / ti = 1 t0 / ti ≥ 2 g ≤ 0.6 18 56 g ≤ 2 / 3 di di / d0 = 1 25 63 0.3 ≤ q / p ≤ 1 t0 / ti = 1 t0 / ti ≥ 2 di / d0 = 0.3 ≤ q / p ≤ 1 t0 / ti = 1 t0 / ti ≥ 2 di / d0 = 0. with overlapping 98 .6 50 80 di / d0 = 1 56 90 a. 6 32 56 bi / b0 = 1 36 63 0.3 b0 t0 / ti = 1 t0 / ti ≥ 2 bi / b0 = 0.6 32 63 bi / b0 = 1 36 71 5 g ≤ 2 / 3bi 0.prEN 13001-3-1:2010 (E) Table H.3 ≤ q / p ≤ 1 with overlapping K-T-gusset with direct strut joint 6 t0 / ti = 1 t0 / ti ≥ 2 bi / b0 = 0. 2 ∆σc (N/mm ) Intermediate values by straight-line interpolation! Requirements T.3 ≤ q / p ≤ 1 99 .2 (continued) No.and X-gusset with direct strut joint 4 t0 / ti = 1 t0 / ti ≥ 2 di / d0 = 0.6 10 16 di / d0 = 1 36 50 60° ≤ Θ ≤ 90° Bending of boom member should be considered! K-gusset with direct strut joint c) with gap: g ≤ 0. with overlapping T.5 bi / b0 = 1 32 40 60° ≤ Θ ≤ 90° Bending of boom member should be considered! 100 .prEN 13001-3-1:2010 (E) Table H.3 b0 7 t0 / ti = 1 t0 / ti ≥ 2 bi / b0 = 0.2 (continued) No.6 29 50 bi / b0 = 1 36 56 g ≤ 2 / 3bi 0. 2 ∆σc (N/mm ) Intermediate values by straight-line interpolation! Requirements N-gusset with direct strut joint d) with gap: g ≤ 0.and X-gusset with direct strut joint 8 t0 / ti = 1 t0 / ti ≥ 2 bi / b0 = 0.3 ≤ q / p ≤ 1 c.6 6 12. 3 Cranes — General design — Part 3.2: Limit states and proof of competence of wire ropes CEN/TS 13001-3.2 Cranes — General design — Part 3.1: Limit states and proof of competence of steel structures CEN/TS 13001-3.5: Limit states and proof of competence of forged hooks EN 13135-1 Cranes — Equipment — Part 1: Electrotechnical equipment EN 13135-2 Cranes — Equipment — Part 2: Non-electrotechnical equipment EN 13557 Cranes — Controls and control stations EN 12077-2 Cranes safety — Requirements for health and safety — Part 2: Limiting and indicating devices EN 13586 Cranes — Access EN 14502-1 Cranes — Equipment for the lifting of persons — Part 1: Suspended baskets EN 14502-2 Cranes — Equipment for the lifting of persons — Part 2: Moveable cabins EN 12644-1 Cranes — Information for use and testing — Part 1: Instructions EN 12644-2 Cranes — Information for use and testing — Part 1: Marking 101 .3: Limit states and proof of competence of wheel / rail contacts CEN/TS 13001-3.1 Cranes — General design — Part 3.prEN 13001-3-1:2010 (E) Annex I (informative) Selection of a suitable set of crane standards for a given application Is there a product standard in the following list that suits the application? EN 13000 Cranes — Mobile cranes EN 14439 Cranes — Tower cranes EN 14985 Cranes — Slewing jib cranes prEN 15011 Cranes — Bridge and gantry cranes EN 13852-1 Cranes — Offshore cranes — Part 1: General purpose offshore cranes EN 13852-2 Cranes — Offshore cranes — Part 2: Floating cranes EN 14492-1 Cranes — Power driven winches and hoists — Part 1: Power driven winches EN 14492-2 Cranes — Power driven winches and hoists — Part 2: Power driven hoists EN 12999 Cranes — Loader cranes EN 13157 Cranes — Safety — Hand powered lifting equipment EN 13155 Cranes — Non-fixed load lifting attachments EN 14238 Cranes — Manually controlled load manipulating devices EN 15056 Cranes — Requirements for container handling spreaders YES NO Use it directly. plus the standards that are referred to Use the following: EN 13001-1 Cranes — General design — Part 1: General principles and requirements EN 13001-2 Cranes — General design — Part 2: Load actions prEN 13001-3.5 Cranes — General design — Part 3. within the limits of the scope of this standard. amended by 98/79/EC. 102 . a presumption of conformity with the relevant Essential Requirements of that Directive and associated EFTA regulations. WARNING — Other requirements and other EU Directives may be applicable to the product(s) falling within the scope of this standard. compliance with the normative clauses of this standard confers. Once this standard is cited in the Official Journal of the European Union under that Directive and has been implemented as a national standard in at least one Member State.prEN 13001-3-1:2010 (E) Annex ZA (informative) Relationship between this European Standard and the Essential Requirements of EU Directive 98/37/EC This European Standard has been prepared under a mandate given to CEN by the European Commission and the European Free Trade Association to provide a means of conforming to Essential Requirements of the New Approach Directive Machinery 98/37/EC. prEN 13001-3-1:2010 (E) Annex ZB (informative) Relationship between this European Standard and the Essential Requirements of EU Directive 2006/42/EC This European Standard has been prepared under a mandate given to CEN by the European Commission and the European Free Trade Association to provide a means of conforming to Essential Requirements of the New Approach Directive Machinery 2006/42/EC. 103 . within the limits of the scope of this standard. WARNING — Other requirements and other EU Directives may be applicable to the product(s) falling within the scope of this standard. compliance with the normative clauses of this standard confers. a presumption of conformity with the relevant Essential Requirements of that Directive and associated EFTA regulations. Once this standard is cited in the Official Journal of the European Union under that Directive and has been implemented as a national standard in at least one Member State. Dutta. Delft University Press. Sedlacek. Heft 75-01 104 . D. M. brazed and soldered joints — Symbolic representation on drawings (ISO 2553:1992) [4] EN ISO 4042:1999. A. van. Contraintes admissibles dans les assemblages soudés. X-L. Designer's guide to the structural hot-spot stress approach. A. J. O.. September 2006 [12] American Petroleum Institute – API RP 2A-WSD: Recommended practice for planning.. S.. Packer. designing and constructing fixed offshore platforms – Working Stress Design.. Yeomans. rapport CETIM.. Document XIII-1804-99 Part 2: Commentary.2000 [13] Romeijn. 2nd edition. ISBN 90-407-1057-0 Selection of literature that contains information about hollow sections: [14] Zhao. 1994.. Techni. L. W. Herion. Wingerde.: Design Guide for structural hollow sections in mechanical applications. 1A4085/1A4087. CIDECT and Verlag TÜV Rheinland. Fasteners — Preloading test for the detection of hydrogen embrittlement — Parallel bearing surface method (ISO 15330:1999) [7] ISO 9587:2007. G. December 1. K.: Design Guide for circular and rectangular hollow section welded joints under fatigue loading. 1995. 1999. and Yeomans. J. Document XV-1035-99 [10] I. Wiss. R. Cologne.. F. Metallic and other inorganic coatings — Pre-treatment of iron or steel to reduce the risk of hydrogen embrittlement [8] IIW International Institute of Welding.Multilingual terms for welded joints with illustrations (ISO 17659:2002). H-P. N. Eurocode 3: Design of steel structures — Part 1-1: General rules and rules for buildings [2] prEN 1993-1-9: Eurocode 3: Design of steel structures — Part 1-9: Fatigue strength of steel structures [3] EN 22553:1994. Fatigue analysis if welded components. Weymand. 1975. Cologne. J. 1999. A. Bericht MPA Stuttgart. Maddox. LIEURADE.. Fricke. S. Welded. Delft. J. 2000. A.J. N. R. HUTHER..: Schwingfestigkeitsverhalten geschweißter Rohrknotenpunkte und Rohrlaschenverbindungen. and Bucak. S. ISBN 3-82490302-4 [16] Zirn. VELLUET. Fasteners — Electroplated coatings (ISO 4042:1999) [5] EN ISO 17659:2004 Welding . Trilingual version [6] EN ISO 15330:1999. Stress and strain concentration factors of welded multiplanar tubular joints. Wardenier. CIDECT and Verlag TÜV Rheinland. June 1999 [9] IIW – XV-E: Recommended Fatigue Design Procedure for Welded Hollow Section Joints Part 1: Recommendations. Packer. Subcommission XV-E-92-244: Recommended Fatigue Design Procedure for Welded Hollow Section Joints.prEN 13001-3-1:2010 (E) Bibliography Selection of literature that contains information about Hot Spot Stress Method: [1] EN 1993-1-1:2005.. Puthli. ISBN 3-8249-0565-5 [15] Wardenier. avril 2000 [11] E. Niemi. “Beulwerte ausgesteifter Rechteckplatten“. : Zum Scheiben und Beulproblem lângsversteifter Stegblechfelder bei örtlicher Lasteinleitung und bei Belastung aus Haupttragwirkung. and Möller. Ernst und Sohn [20] Klöppel.prEN 13001-3-1:2010 (E) Selection of literature that contains information about elastic stability: [17] DIN 18800-2. Part 1. W. “Beulwerte ausgesteifter Rechteckplatten. Stahlbauten — Stabilitätsfälle — Knicken von Stäben und Stabwerken [18] “Eurocode 3 – Design of steel structures”.. K. W. and Scheer. J. W. Ernst und Sohn [21] Protte. Band II“. K.5 : general rules : supplementary rules for planar plated structures without transverse loading (EN 1993-1-5:2007) [19] Klöppel. K.. pages 251-252 105 .Stahlbau 45 (1976).
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