Bsi bs 3a 125 to 3a 132, 3a 136 to 3a 143, 3a 147 to 3a 168, 3a 180, 3a 181, 3a 186, 3a 187, 3a 192, 3a 193, 3a 200, 3a 201, 2a 213 to 2a 216 1981 + a1 2013

Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BRITISH STANDARD AEROSPACE SERIES Specification for Stiffnuts (Unified threads) for aircraft ICS 49.030.30 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 Incorporating +A1:2013 Corrigendum No and No Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 216:1981+A1:2013 BS 2870, Rolled copper and copper alloys Sheet, strip and foil BS 2874, Copper and copper alloys Rods and sections (other than forging stock) BS 3488, Technical anhydrous lanolin A 102, Steel bolts (Unified hexagons and Unified threads) for aircraft A 104, Corrosion-resisting steel bolts (Unified hexagons and Unified threads) for aircraft A 169, Aluminium alloy bolts (Unified hexagons and Unified threads) for aircraft B 11, Brass bars suitable to be brazed or silver soldered L 80, Sheet and strip of aluminium-21/4 per cent magnesium alloy (soft-0) L 81, Sheet and strip of aluminium-21/4 per cent magnesium alloy (three-quarter hard-H6) L 163, Specification for sheet and strip of aluminium-coated aluminium-copper-magnesium-silicon-manganese alloy (solution treated, cold worked for flattening and aged at room temperature) (Cu 4.4, Mg 0.5, Si 0.8, Mn 0.8) L 168, Specification for bars and extruded sections of aluminium-copper-magnesium-silicon-manganese alloy (solution treated and artificially aged) (not exceeding 200 mm diameter or minor sectional dimension) S 80, Specification for high chromium-nickel corrosion-resisting steel billets, bars, forgings and parts (880–1 080 MPa; limiting ruling section 100 mm) S 92, Carbon-manganese steel (suitable for welding) S 95, 11/2 per cent nickel-chromium-molybdenum steel S 112, Semi-free cutting carbon steel, bright bars for machining (primarily intended for the manufacture of nuts) S 113, “40” carbon steel bright bars for machining (primarily intended for the manufacture of nuts) S 114, Manganese-molybeenum steel S 117, per cent chromium steel S 137, Specification for high chromium-nickel corrosion-resisting steel bright bars (free machining) (880–1 080 MPa; limiting ruling section 70 mm) S 154, 21/2 per cent nickel-chromium-molybdenum steel billets, bars, forgings and parts (880–1 080 MPa: limiting ruling section 150 mm) S 510, Carbon steel sheet and strip (430–540 MN/m2) (suitable for welding) S 511, Deep drawing carbon steel sheet and strip (280–400 MN/m2) (suitable for welding) S 526, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (titanium stabilized: 54 hbar) S 527, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (niobium stabilized: 54 hbar) Amendments/corrigenda issued since publication b) Ministry of Defence specifications AD 114, requirements, qualification Amd No.DesignDate Commentsapproval tests and acceptance test for AGS 2000 series stiffnuts (BA and BSF threads)2) C1 February 2010 DEF 151, Anodizing of aluminium and aluminium alloys DEF PX-1, dyed and undyed C2 2331, Protective February 2010 DEF STAN, 03-8 Electro-deposition of tin A1 May 2013 See Foreword This British Standard, having been prepared under the direction of the Aerospace Standards Committee, was published under the authority of the Executive Board and comes into effect on 30 June 1981 © The British Standards Institution 2013 Published by BSI Standards Limited 2013 Draft for comment 13/30275817 DC ISBN 978 580 81451 iv 2) Referred to in foreword only © BSI 2010 Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A213 201, to 2A 216:1981 3A200, 193,3A 3A201, 200,2A 3A 193, 3A to2A 2A213 216:1981+A1:2013 Contents DEF STAN, 03-9 Electro-deposition of silver Page Foreword iii DTD 10, High nickel copper alloy sheets and strips Section General requirements DTD 417, Lubricating oil, aircraft controls: anti-freezing DTDScope 904, Cadmium plating c) Society Definitions of British Aerospace Companies (SBAC) publication 3) RS 732, Design and dimensions Manufacturers identification monograms for aerospace fasteners Material and manufacture This publication does not purport to include all the necessary provisions of a Freedom from defects contract Users are responsible for its correct application Protective coating finish Compliance with a British Standard does cannot confer immunity Screw threads from legal obligations Squareness of face of thread Identification and marking Section Inspection and testing 10 Qualification approval 11 Production batch acceptance 12 Inspection of samples 13 Testing of samples 14 Test bolts 15 Torque test 16 Bolt tolerance test 17 Endurance test 18 Torsional strength test (anchor nuts and stripnuts) 19 Thrust test (anchor nuts) 20 High temperature test 21 Low temperature test 22 Pressure test for cap nuts Appendix A Equipment for testing stiffnuts 21 Figure — Marking on hexagon stiffnuts Figure — Marking on stripnuts Figure — Marking on corrosion-resisting steel hexagon nuts Figure — Marking on corrosion-resisting steel anchor nuts Figure — Identification of brass or bronze hexagon nut Figure — Squareness gauge 22 Figure — Torque-testing machine 24 Figure — Thrust-testing machine 26 Table — Tolerance on squareness Table — Unscrewing torque Table — Torsional strength (anchor nuts and stripnuts) and thrust test loads (anchor nuts) Table — Materials for stiffnuts (Unified threads) for aircraft 10 Summary pagestypes and British Standard numbers, with Table — of Stiffnut temperature 11 This documentclassification comprises a front cover, an inside front cover, pages i to vi, pages and a backand cover Table16to—31 Dimensions part references of ordinary and thinstandard hexagon has stiffnuts 125 to(see A 132, A 180 and A and 181)may have had 12 This been (A updated copyright date) Table — Dimensions andThis partwill references of hexagon amendments incorporated be indicated in the amendment table on the cap nuts (Acover 213 and A 214) 13 inside front Table — Dimensions and part references of ordinary and thin double-lug fixed anchor nuts (A 136 to A 143, A 186 and A 187) 14 3) Obtainable from the Society of British Aerospace Companies, 29 King Street, St James’s, London, SW1 © BSI BSI 2010 © The 2010 British Standards Institution 2013 vi Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 216:1981+A1:2013 BS 2870, Rolled copper and copper alloys Sheet, strip and foil Page BS 2874, Copper and and copper alloys Rods and sections (other Table — Dimensions part references of double-lug fixed than forging stock).cap nuts (A 215 and A 216) anchor 15 BS 3488, Technical anhydrous lanolin Table 10 — Dimensions and part references of ordinary and thin double-lug floating (A 147and to AUnified 156, A threads) 192 and A 16 A 102, Steel bolts anchor (Unifiednuts hexagons for193) aircraft Table 11Corrosion-resisting — Dimensions and steel part bolts references of ordinary A 104, (Unified hexagonsand andthin Unified threads) single-lug fixed anchor nuts (A 157 to A 164, A 200 and A 201) 18 for aircraft Table 12 — Dimensions and part references of ordinary and A 169, Aluminium alloy bolts (Unified hexagons and Unified threads) for thin stripnuts (A 165 to A 168) 19 aircraft Table 13 — Calibration of spring balances for torque and B 11, Brass bars suitable to be brazed or silver soldered torsional strength tests 23 L 80, Sheet and strip of aluminium-21/4 per cent magnesium alloy (soft-0) Table 14 — Dimensions for high limit and low limit test bolts 25 L 81,15 Sheet and strip of aluminium-2 /4 per cent magnesium Table — Acceptance gauge for ordinary and thin double-lugalloy (three-quarter hard-H6) fixed anchor nuts (see Table 8) 27 L 163, forgauge sheetfor and strip of aluminium-coated Table 16Specification — Acceptance attachment plates for ordinary aluminium-copper-magnesium-silicon-manganese alloy (solution treated, cold and thin double-lug floating anchor nuts (see Table 10) 28 worked forAcceptance flattening and aged room temperature) Table 17 — gauge forat ordinary and thin nut and baseplate (Cu 4.4, Mg 0.5, 0.8, Mn 0.8) subassemblies for Si double-lug floating anchor nuts L 168, Specification for bars(see andTable extruded (see Table 10) and stripnuts 12) sections of 29 aluminium-copper-magnesium-silicon-manganese alloy (solution treated and Table 18 — Acceptance gauge for ordinary and thin single-lug artificially (notTable exceeding fixed anchor aged) nuts (see 11) 200 mm diameter or minor sectional 30 dimension) Table 19 — Acceptance gauge for attachment strips for ordinary S 80, Specification forTable high chromium-nickel corrosion-resisting steel billets,31 and thin stripnuts (see 12) bars, forgings and parts (880–1 080 MPa; limiting ruling section 100 mm) S 92, Carbon-manganese steel (suitable for welding) S 95, 11/2 per cent nickel-chromium-molybdenum steel S 112, Semi-free cutting carbon steel, bright bars for machining (primarily intended for the manufacture of nuts) S 113, “40” carbon steel bright bars for machining (primarily intended for the manufacture of nuts) S 114, Manganese-molybeenum steel S 117, per cent chromium steel S 137, Specification for high chromium-nickel corrosion-resisting steel bright bars (free machining) (880–1 080 MPa; limiting ruling section 70 mm) S 154, 21/2 per cent nickel-chromium-molybdenum steel billets, bars, forgings and parts (880–1 080 MPa: limiting ruling section 150 mm) S 510, Carbon steel sheet and strip (430–540 MN/m2) (suitable for welding) S 511, Deep drawing carbon steel sheet and strip (280–400 MN/m2) (suitable for welding) S 526, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (titanium stabilized: 54 hbar) S 527, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (niobium stabilized: 54 hbar) b) Ministry of Defence specifications AD 114, Design requirements, qualification approval tests and acceptance test for AGS 2000 series stiffnuts (BA and BSF threads)2) DEF 151, Anodizing of aluminium and aluminium alloys DEF 2331, Protective PX-1, dyed and undyed DEF STAN, 03-8 Electro-deposition of tin 2) iv ii Referred to in foreword only © BSI BSI 2010 2010 © © The British Standards Institution 2013 John Devaney, British Licensed StandardsCopy: Institution, Mr John 27/07/2012 Devaney, 10:58, British Uncontrolled Standards Institution, Copy, (c) The 27/07/2012 British Standards 10:58, Uncontrolled Institution 2012 Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 193,3A 3A213 201, to 2A 216:1981 3A200, 3A201, 200,2A 3A 193, 3A to2A 2A213 216:1981+A1:2013 Foreword DEF STAN, 03-9 Electro-deposition of silver This British Standard is published BSI Standards licence Self-retaining nuts were first introduced toand the strips BritishLimited, aircraft under industry during DTD 10, High nickel copper alloy by sheets from1930’s The British Standards the They were widelyInstitution adopted and soon constituted a large proportion of DTD 417, Lubricating oil, aircraft controls: anti-freezing the nuts used in aircraft BS 3A 125 to 3A 132, 3A construction 136 to 3A 143, 3A 147 to 3A 168, 3A 180, 3A 181, 3A DTD 904, 186, 3A 187, Cadmium 3A 192, 3Aplating 193, 200,were 3A 201, 2A 213 216:1981+A1:2013 Being proprietary articles, the3A nuts required by to the2Aairworthiness 3)168, 3A 180, c) SocietyBS British Companies (SBAC) publication supersedes 3A 125 Aerospace to 3Aand 132,approval 3A 136 to 143, 3A 147 to 3A authorities toofundergo test by3A the Royal Aircraft Establishment, 1) 3ARS 181, 3A 186, 3A 187, 3A 192, 3A 193, 3A 200, 3A 201, 2A 213 2A 216:1981, , AD 114, setting out the Farnborough, who in 1942 published a specification 732, Manufacturers identification monograms for aerospacetofasteners which is withdrawn design and test requirements The term “stiffnut” was chosen as 143, the most suitable BS 3A 125 to 3A 132, 3A 136 to 3A 3A 147 This publication does not purport to include all the necessary provisions of a to descriptive name for generic use Text introduced or altered by Amendment No.181, is indicated the187, text by 3A 168, 3A 180, 3A 3A 186,in3A 3Atags 192, contract Users are responsible for its correct application  Minor editorial changes are not tagged The specification AD 114 was the first step towards stiffnuts, 3A 193, 3A 200, 3A 201,standardization 2A 213 to 2Aof216:1981 Compliance with a general Britishrequirements Standard does conferperformance immunity and specified certain andcannot the minimum CAUTION BS A 125, A 126, A 127, A 128, A 136, A 137, A 138, A 139, A 147, from legalin obligations acceptable respect of retaining properties Manufacture, however, was to A 148, A 149, A 150, A 151, A 152, A 157, A 158,A 159, A 160, A 165, A 166, proprietary approved the RAEasand nuts were knownwhich to users their A 213 and Adrawings 215 stiffnuts haveby cadmium a plating material hasby been proprietary names and part numbers This continued until 1947, when drawings restricted and / or banned for use in many countries owing to environmental and were issued in theThey Society of British Companies Limited AGSofficials series health concerns should not be Aerospace used in new product designs Local providing common part numbers to which nuts of any make could be supplied; should be consulted about any concerns on using cadmium plated parts maximum envelope dimensions were specified and also other features affecting Self-retaining nuts from werethe firstuser’s introduced the British industry interchangeability point oftoview, but theaircraft nuts were still during the 1930’s They were widely adopted and soon constituted a large proportion of manufactured and inspected to the makers’ drawings At a later date, too, the nuts usedtesting in aircraft construction performance of production quantities was introduced to ensure that the frictional properties were maintained at or above the of AD 114, which Being proprietary articles, the nuts were required by standard the airworthiness had covered only the type testing of prototype nuts when submitted for approval authorities to undergo test and approval by the Royal Aircraft Establishment, 1) , AD 114, setting outBritish the Farnborough, who in 1942 published a specification With the opportunity afforded by the advent of the Unified screw thread, design and test requirements The term “stiffnut” was chosen as the most suitable Standards A 125 to A 168 were published in 1954 to fulfil the functions descriptive name for generic use the AGS drawings, production test schedules previously performed by AD 114, and, to a large extent, the manufacturers’ The AGS drawings were The specification AD 114 was the first stepdrawings towards standardization of stiffnuts, devised around a number of existing products and could not, therefore, supply a and specified certain general requirements and the minimum performance precise definition, but it has been possible in the new series of nuts to coordinate acceptable in respect of retaining properties Manufacture, however, was to developmentdrawings with theapproved preparation of the British Standards, resulting in by a much proprietary by the RAE and nuts were known to users their fuller specification Thepart aim numbers throughout hascontinued been to define and dimension the proprietary names and This until 1947, when drawings product completely so thatof the standards are adequate for manufacture were issued in the Society British Aerospace Companies Limited AGSand series inspection,common except for the friction to element, which defined the be space it may providing part numbers which nuts ofisany makeby could supplied; occupy andenvelope the performance which it has to attain Stiffnuts these maximum dimensions were specified and also othersupplied featuresto affecting British Standards will bepoint interchangeable, onenuts makewere withstill another, interchangeability fromtherefore the user’s of view, but the within the specified limiting conditions (e.g drawings of temperature, etc.).date, too, manufactured and inspected to the makers’ At a later performance of production quantities up wastointroduced to ensure that the This revision testing brings these British Standards date, notably with regard to frictional properties were maintained at and or above the standard of ADstandards 114, which the qualification approval requirements the references to other had the typethe testing of prototype nuts whenin submitted for approval Thiscovered revisiononly supersedes previous edition published 1958, which is With the opportunity therefore withdrawn afforded by the advent of the Unified screw thread, British Standards A 125 make to A 168 were published in 1954 to of fulfil functions These standards reference to the latest issues thethe following previously performed by AD 114, the AGS drawings, production test schedules a) to British Standards and, a large extent, the manufacturers’ drawings The AGS drawings were BS 919, Screwa gauge limits and tolerances Part 1: Gauges for screwsupply threads devised around number of existing products—and could not, therefore, a of Unified form.but it has been possible in the new series of nuts to coordinate precise definition, development with the preparation of the British /4 in andin a much BS 1580, Unified screw threads — Parts & 2:Standards, Diameters resulting fuller specification The aim throughout has been to define and dimension the larger — Part 3: Diameters below /4 in Summary of pagesso that the standards are adequate for manufacture and product completely inspection, except for the friction element, defined bypages the space it may This document comprises a front cover, an which inside is front cover, i to vi, occupy the performance which it has to attain Stiffnuts supplied to these pages 1and to 31 and a back cover British Standards will therefore be interchangeable, one make with another, This standard has been updated (see copyright date) and may have had within the specified limiting conditions (e.g of temperature, etc.) amendments incorporated This will be indicated in the amendment table on the This brings these British Standards up to date, notably with regard to insiderevision front cover the qualification approval requirements and the references to other standards This revision supersedes the previous edition published in 1958, which is therefore withdrawn 3) Obtainable from the Society of British Aerospace Companies, 29 King Street, St James’s, 1) Now issued by the Ministry of Defence, Assistant Directorate of Standardization (Air) These make reference to the latest issues of the following London,standards SW1 a) British Standards iii v © © BSI The 2010 British Standards Institution BS2013 919, Screw gauge limits and tolerances — Part 1: Gauges for screw threadsiii of Unified form BS 1580, Unified screw threads — Parts & 2: Diameters 1/ in and Foreword Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c)2012 The British Standards Institution 2012 opy: :Copy: Mr.Mr John Mr John Devaney, John Devaney, Devaney, British British British Standards Standards Standards Institution, Institution, Institution, 27/07/2012 27/07/2012 27/07/2012 10:58, 10:58, 10:58, Uncontrolled Uncontrolled Uncontrolled Copy, Copy, Copy, (c) (c) The (c) The British The British British Standards Standards Standards Institution Institution Institution 2012 2012 precise definition, but it has been possible in the new series of nuts to coordinate development with the preparation of the British Standards, resulting in a much BS 3A 125 to 3A 132,fuller 3A 136 to 3A 143, 3A throughout 147 to has been to define and dimension the specification The aim product so that standards are adequate for manufacture and 3A 168, 3A 180, 3A 181, 3A completely 186, 3A 187, 3Athe192, inspection, except for 216:1981 the friction element, which is defined by the space it may 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981+A1:2013 occupy and the performance which it has to attain Stiffnuts supplied to these British Standards will therefore be interchangeable, one make with another, within the specified limiting conditions (e.g of temperature, etc.) This revision brings these British Standards up to date, notably with regard to the qualification approval requirements and the references to other standards BS 2870, Rolled copper and copper alloys Sheet, strip and foil This revision supersedes the previous edition published in 1958, which is BS 2874,withdrawn Copper and copper alloys Rods and sections (other than forging therefore stock) These standards make reference to the latest issues of the following 3488, anhydrous lanolin BS 3A 125 to 3A 132,BS 3A 136Technical to 3A 143, 3A 147 to a) British Standards A3A 102, Steel bolts (Unified and Unified threads) for aircraft BS 3A 125 3A3A 132, 136 to 3A 143, 3A 147 totolerances 3A 168, 3A to 180, 181, 186, 3A 187,limits 3Ahexagons 192, BS3A 919-1: Screw gauge limits and Part1:1:Gauges Specification forthreads gauges 919, Screw gauge and tolerances —–Part for screw A 104, Corrosion-resisting steel bolts (Unified hexagons and Unified threads) 3A 168, 3A 180, 3A 181, 3A 186, 187, 192, BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to for screw threads of unified form of Unified form 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 for aircraft diameters ¼ in 3A 193, 201, 2A 213 to 216:1981 168, 3A 200, 180, 3A 181, 186, 3A2A 187, 3A 192,—Part BS3A 1580-1: Unified screw threads 1: 1Screw threads with /4 in and 1580, Unified screw threads Parts & 2: Diameters A 169, Aluminium alloy bolts (Unified hexagons and Unified threads) for and larger larger Part Diameters below /4 in 3A 193, 3A 200, 3A 201, 2A — 213 to3:2A 216:1981 aircraft BS 1580-3: Unified screw threads - Part 3: Screw threads with diameters Bbelow 11, Brass suitable to be brazed or silver soldered ¼ in bars – Requirements 1/ per cent magnesium alloy (soft-0) LBS 80,2870, SheetRolled and strip of aluminium-2 copper and copper alloys Sheet, strip and foil © BSI 2010 iv LBS 81,2870, SheetRolled and strip aluminium-2 /4 perand centsections magnesium alloy copper and copper Sheet, strip and foil BS 2874, Copper andofcopper alloys.alloys Rods (other than forging (three-quarter hard-H6) 2870, Copper Rolled copper and copper Sheet, strip and foil stock) BS 2874, and copper alloys.alloys Rods and sections (other than forging Lstock) 163, Specification for sheet and strip of aluminium-coated BS 2874, Copper and copper alloys Rods and sections (other than forging 3488, Technical anhydrous lanolin aluminium-copper-magnesium-silicon-manganese alloy (solution treated, cold stock) BS 3488, Technical anhydrous lanolin A Steel bolts (Unified hexagons andwith Unified threads) for aircraft BS102, EN 2133: Cadmium plating of steels specified tensile strength worked for flattening and aged at room temperature) ≤ 1450 MPa, copper, copper alloys and nickel alloys BS 3488, Technical anhydrous lanolin A 102, Steel bolts (Unified hexagons and Unified threads) for aircraft A 104, steelAssistant bolts (Unified hexagons and Unified threads) 1) (Cu 4.4, Corrosion-resisting Mg 0.5,Ministry Si 0.8,ofMn 0.8) Now issued by the Defence, Directorate of Standardization (Air) 102, Steel bolts (Unified steel hexagons Unified threads) forUnified aircraft for104, aircraft A Corrosion-resisting boltsand (Unified hexagons and threads) L 168, Specification for bars and extruded sections of for aircraft A 104, steel bolts (Unified hexagons and Unified threads) 169, Corrosion-resisting Aluminium alloy bolts (Unified hexagons and Unified threads) for aluminium-copper-magnesium-silicon-manganese alloy (solution treated and iii for aircraft aircraft A 169, Aluminium alloy bolts (Unified hexagons and Unified threads) artificially aged) (not exceeding 200 mm diameter or minor sectional for aircraft A Aluminium alloy bolts hexagons and Unified threads) for B 169, 11, Brass bars suitable to be(Unified brazed or silver soldered dimension) aircraft 11,Specification Brass and barsstrip suitable tochromium-nickel be brazed1/or silver soldered per cent magnesium alloy (soft-0) L80, 80, Sheet aluminium-2 SB for of high corrosion-resisting steel billets, 1/orper B 11, Brass bars suitable to be brazed soldered L 80, Sheet and strip of aluminium-2 cent magnesium alloy (soft-0) bars, forgings and parts (880–1 080 MPa; limiting ruling section 100 mm) silver L 81, Sheet and strip of aluminium-2 /4 per cent magnesium alloy 80,Carbon-manganese SL 92, steel (suitable1/4for 81, Sheet and strip of aluminium-2 perwelding) cent magnesium alloy (soft-0) (three-quarter hard-H6) 1 (three-quarter hard-H6) L 81, Sheet and strip of aluminium-2 / per cent steel magnesium alloy S 95, /Specification 163, for sheet and strip4of aluminium-coated per cent nickel-chromium-molybdenum (three-quarter hard-H6) aluminium-copper-magnesium-silicon-manganese (solution treated, cold 163,Semi-free Specification for carbon sheet and strip of aluminium-coated SL 112, cutting steel, bright bars foralloy machining (primarily worked for and aged at strip room of temperature) aluminium-copper-magnesium-silicon-manganese alloy (solution treated, cold L 163, Specification for sheet and aluminium-coated intended forflattening the manufacture of nuts) (Cu 4.4,for Mgflattening 0.5, Si 0.8, Mnaged 0.8).at room temperature) worked and alloy (solution treated, cold Saluminium-copper-magnesium-silicon-manganese 113, “40” carbon steel bright bars for machining (primarily intended for the (Cu 4.4, Mg 0.5, Si 0.8, Mn 0.8) worked for flattening and aged at room temperature) L 168, Specification for bars and extruded sections of manufacture of nuts) (Cu 4.4,Specification Mg 0.5, Si 0.8, aluminium-copper-magnesium-silicon-manganese L 168, for Mn bars0.8) and extruded sections alloy of (solution treated and S 114, Manganese-molybeenum steel artificially aged) (notfor exceeding mm diameter sectional aluminium-copper-magnesium-silicon-manganese alloy (solution treated and L 168, Specification bars and200 extruded sectionsor ofminor Sartificially 117, per aged) cent chromium steel.200 mm diameter or dimension) (not exceeding minor sectional aluminium-copper-magnesium-silicon-manganese alloy (solution treated and Sdimension) Specification forexceeding high chromium-nickel chromium-nickel corrosion-resisting steel billets, bright artificially aged) (not 200 mm diameter or minor sectional S137, 80, Specification for high corrosion-resisting steel bars machining) 080080 MPa; limiting ruling section 70 steel mm) dimension) bars, forgings and parts (880–1 MPa; limiting ruling section 100 mm) S 80,(free Specification for(880–1 high chromium-nickel corrosion-resisting billets, andnickel-chromium-molybdenum parts (880–1 080 MPa; ruling section 100 mm) steel billets, bars, forgings Sbars, 21/2 per cent S154, 80, Specification for high chromium-nickel corrosion-resisting steel billets, 92, forgings Carbon-manganese steel (suitable forlimiting welding) and parts (880–1 080 MPa: limiting ruling section 150 mm) bars, forgings and parts (880–1 080 MPa; limiting ruling section 100 mm) S 92, Carbon-manganese steel (suitable for welding) S 95, /2 per cent nickel-chromium-molybdenum steel 2) (suitable for welding) 1/ per cent SS510, Carbon steelnickel-chromium-molybdenum sheet and (430–540 MN/m 92, Carbon-manganese steelstrip (suitable for welding) S 95, 112,1 Semi-free cutting carbon steel, bright bars steel for machining (primarily 2) (suitable 1/ per SS 511, drawing carbon steel sheetbright and strip MN/m(primarily centmanufacture nickel-chromium-molybdenum steel 95, intended of steel, nuts) 112,1Deep Semi-free cutting carbon bars(280–400 for machining for the for welding) intended forcarbon the manufacture ofbars nuts) S 112, cutting carbon steel, bars for machining (primarily 113, Semi-free “40” steel bright forbright machining (primarily intended for the SS 526, Softened 18/10 chromium-nickel steelintended sheet andfor strip intended forcarbon the manufacture nuts) manufacture of nuts) 113, “40” steel brightofbars forcorrosion-resisting machining (primarily the (titanium stabilized: 54 hbar) manufacture of nuts) S 113, carbon steel bright bars for machining (primarily intended for the 114, “40” Manganese-molybeenum steel SS 527, Softened chromium-nickel corrosion-resisting steel sheet and strip manufacture of18/10 nuts) S 114, 117, Manganese-molybeenum per cent chromium steel.steel (niobium stabilized: 54 hbar) 114, Manganese-molybeenum steel S per cent chromium S 117, 137, Specification for highsteel chromium-nickel corrosion-resisting steel bright b)S Ministry of Defence specifications 117, per cent chromium steel bars (free machining) 080 MPa; limiting ruling section 70 steel mm).bright 137, Specification for(880–1 high chromium-nickel corrosion-resisting AD 114, Design requirements, qualification approval tests and acceptance test bars (free 080 MPa; limiting ruling section 70 mm) machining) 137, Specification for(880–1 high chromium-nickel corrosion-resisting steel bright /2 per cent nickel-chromium-molybdenum steel billets, bars, forgings S 154, 2) for AGS 2000 series stiffnuts (BA and BSF threads) bars (free (880–1limiting 080 MPa; limiting ruling section mm) per cent080 nickel-chromium-molybdenum steel billets, 70 bars, forgings S 154, /2machining) and parts (880–1 MPa: ruling section 150 mm) DEF 151, ofMPa: aluminium and aluminium alloys Anodizing and parts (880–1 080 limiting ruling section 150 mm) billets, for bars, forgings 154, Carbon /2 per cent ) (suitable welding) S 510, steelnickel-chromium-molybdenum sheet and strip (430–540 MN/msteel DEF 2331, Protective PX-1, dyed and(430–540 undyed 2) (suitable and parts (880–1 080 MPa: limiting ruling section 150 mm) for welding) S 510, Carbon steel sheet and strip MN/m S 511, Deep drawing carbon steel sheet and strip (280–400 MN/m ) (suitable DEF STAN, Electro-deposition of tin 2) (suitable for2 welding) S 510, Carbon steel sheet andsteel stripsheet (430–540 MN/m for welding) 511, Deep 03-8 drawing carbon and strip (280–400 MN/m ) (suitable 2) (suitable for welding) 511, Softened Deep drawing steel sheet corrosion-resisting and strip (280–400 steel MN/m S 526, 18/10 carbon chromium-nickel sheet and strip for welding) (titanium stabilized: 54 hbar) S 526, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip 2) Referred to in foreword only (titanium stabilized: 54 hbar) 526, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip S 527, (titanium stabilized: 54 hbar) (niobium stabilized: hbar) S 527, Softened 18/1054 chromium-nickel corrosion-resisting steel sheet © and BSIstrip 2010 © The British Standards Institution 2013 (niobium stabilized: 54 hbar) S 527, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip b) Ministry of Defence specifications (niobium stabilized: 54specifications hbar) qualification approval tests and acceptance test b) of Defence ADMinistry 114, Design requirements, Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Licensed Copy:Standards Mr John Institution Devaney, 2012 British Standards Instit ohn d r Copy: John Devaney, Devaney, Mr John British British Devaney, Standards Licensed Licensed Standards British Copy: Institution, Copy: Standards Institution, Mr Mr John John 27/07/2012 Institution, 27/07/2012 Devaney, Devaney, 10:58, 27/07/2012 British British 10:58, Uncontrolled Standards Standards Uncontrolled 10:58,Copy, Institution, Uncontrolled Institution, Copy, (c) The (c) 27/07/2012 27/07/2012 The Copy, British British (c) Standards 10:58, The 10:58, Standards British Uncontrolled Uncontrolled Institution Standards Institution 2012 Copy, Copy, Institution 2012(c) (c) The The 2012 British British Standards Standards Institution Institution 2012 2012 S 113, “40” steel3A bright BS 3A 125 to 3A 132, 3A 136 tocarbon 3A 143, 147bars to for machining (primarily intended for the manufacture of nuts) 3A 168, 3A 180, 3A 181, 3A 186, 3ABS 187, 192, BS 3A3A 125 tosteel 3A 132, 132, 3A 3A 136 136 to to 3A 3A 143, 143, 3A 3A 147 147 to to 3A 125 to 3A S 114, Manganese-molybeenum 3A 193, 3A 200, 3A 201, 2A 213 to 2A3A 216:1981 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 168, steel 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, S 117, per cent chromium 193, 3A213 201, to 2Asteel 216:1981 3A 3A201, 200,2A 3A 193, 3A 200, 3A to2A 2A213 216:1981+A1:2013 S 137, Specification for high chromium-nickel corrosion-resisting bright bars (free machining) (880–1 080 MPa; limiting ruling section 70 mm) iv S 154, 21/2 per cent nickel-chromium-molybdenum steel billets, bars, forgings and parts (880–1 080 MPa: limiting ruling section 150 mm) BS 2870, Rolled copper and copper alloys Sheet, strip and foil S 510, Carbon steel sheet and strip (430–540 MN/m2) (suitable for welding) BS 2874, Copper and copper alloys Rods and sections (other than forging S 511, Deep drawing carbon steel sheet and strip (280–400 MN/m2) (suitable stock) DEF STAN, 03-9 Electro-deposition of silver DEF STAN, 03-9 Electro-deposition of silver for welding) BS 3488, Technical lanolin DTD 10, High High nickelanhydrous copper alloy alloy sheets and and strips strips DTD 10, nickel copper sheets S 526, Softened BS 18/10 chromium-nickel corrosion-resisting steel sheet strip 3A 125 to 3A 132, 3A 136 to 3A 3Aand 147 to A 102, Steel bolts (Unified hexagons and Unified threads) for143, aircraft DTD 417, Lubricating oil, aircraft controls: anti-freezing DTD 417, Lubricating aircraft controls: anti-freezing (titanium stabilized: 54oil, hbar) 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, A 104,904, Corrosion-resisting steel bolts (Unified hexagons and Unified threads) DTD Cadmium DTD Cadmium plating S 527,904, Softened 18/10plating chromium-nickel corrosion-resisting steel sheet and strip for aircraft 3A 193, 200, 3A 201, publication 2A 213 to3) 3)2A 216:1981 c) Society stabilized: of British British Aerospace Companies (SBAC) publication (niobium 54 hbar) 3A c) Society of Aerospace Companies (SBAC) A 169, Aluminium alloy bolts (Unified hexagons and Unified threads) RS 732, Manufacturers identification monograms forto aerospace fasteners BS 3Aspecifications 125 to 3A 132, 3A 136 3A 143, 3A for 147 to b) Ministry of Defence RS 732, Manufacturers identification monograms for aerospace fasteners aircraft 3A 3A 3Aall 181, 3A 186, 3A 187, This publication does not purport to180, include all the136 necessary provisions of a192, ADpublication 114, Design requirements, qualification approval tests and acceptance test This does not purport to include the necessary provisions of a BS 3A168, 125 to 3A 132, 3A to 3A 143, 3A3A 147 to B 11, Brass bars suitable to be brazed or silver soldered 2) contract Users responsible for its correct application for AGS 2000are series stiffnuts (BA and BSF threads) contract Users are responsible for its correct application 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, L 80, Sheet and strip of aluminium-2 /4 per cent magnesium alloy (soft-0) DEF 151,Specification Anodizing of for aluminium anddoes aluminium alloys BS 1872: electroplated coatings of2A tin 3A 193, 3A 200, 3A 201, 213 to 2A 216:1981 Compliance with a a British British Standard cannot confer immunity Compliance Standard cannot confer immunity does L 81, Sheet with and strip of aluminium-2 /4 per cent magnesium alloy DEF 2331, Protective PX-1, dyed and undyed from legal obligations from legal obligations DEF STAN, 03-9 Electro-deposition of silver (three-quarter hard-H6) DEFStan STAN, 03-8 Electro-deposition of tin DTD High nickel copper alloy strips.Soft Film, Cold Application Def 80-217: Corrosion L 163,10, Specification for sheetPreventive and sheets strip Compound: ofand aluminium-coated DTD 417,03-19: Lubricating oil, aircraft controls: anti-freezing aluminium-copper-magnesium-silicon-manganese alloy (solution treated, cold Def Stan Electro-Deposition of Cadmium worked for flattening and aged at room temperature) 2) DTD 904, Cadmium plating Def-Stan Acid Anodizing of Aluminium and Aluminium Alloys Referred to in03-25: foreword only DEF STAN, 03-9Sulfuric Electro-deposition of silver (Cu 4.4, Mg 0.5, Si 0.8, Mn 0.8) c) Society of British Aerospace Companies (SBAC) publication 10: Nickel-Copper Alloy Cold Rolled and Annealed Sheet3)and Strip DTD 10, High nickel copper alloy sheets and strips DEF 03-9 Electro-deposition of silver L 168,STAN, Specification for bars and extruded sections of © BSI 2010 RS 732, Manufacturers identification monograms for aerospace DTD 417, Lubricating oil, aircraft controls: DTD 10, High nickel copper alloy sheets andanti-freezing strips.alloy (solutionfasteners aluminium-copper-magnesium-silicon-manganese treated and 3) This publication does not purport to include allanti-freezing the necessary provisions of a DTD 904, Cadmium plating artificially aged) (not exceeding 200 mm diameter or minor sectional c) ADS Group Limited (ADS) publications DTD 417, Lubricating oil, aircraft controls: contract Users are responsible for its correct application dimension) 3) c) Society British Aerospace Companies Monogram (SBAC) publication ADS RS732 Manufacturers for Aerospace Fasteners DTD 904, of Cadmium plating.Identification S 80, Specification for high chromium-nickel corrosion-resisting steel billets, Compliance a British Standard does cannot confer immunity RS 732,QUALIFIED Manufacturers identification monograms for aerospace TS200 MANUFACTURERS FOR ADS AEROSPACE 3) fasteners c) Society ofwith British Aerospace Companies (SBAC) publication bars, forgings and parts (880–1 080 MPa; limiting ruling section 100 mm) from legal obligations INDUSTRY STANDARD PARTS AGS, ESC SERIES) This publication does not purport to (AS, include allAND the necessary provisions of a RS 732, Manufacturers identification monograms for aerospace fasteners S 92, Carbon-manganese steelfor (suitable for welding) contract Users are responsible its correct application This publication does not purport to include all the necessary provisions of a 1/ per cent nickel-chromium-molybdenum steel S 95, 1Users contract are a responsible for its correct Compliance with British Standard doesapplication cannot confer immunity S 112, Semi-free cutting carbon steel, bright bars for machining (primarily from legal obligations Compliance a British Standard does cannot confer immunity confer immunity from intended forwith the manufacture of nuts) cannot legal from obligations legal obligations S 113, “40” carbon steel bright bars for machining (primarily intended for the manufacture of nuts) S 114, Manganese-molybeenum steel S 117, per cent chromium steel S 137, Specification for high chromium-nickel corrosion-resisting steel bright bars (free machining) (880–1 080 MPa; limiting ruling section 70 mm) S 154, 21/2 per cent nickel-chromium-molybdenum steel billets, bars, forgings and parts (880–1 080 MPa: limiting ruling section 150 mm) S 510, Carbon steel sheet and strip (430–540 MN/m2) (suitable for welding) S 511, Deep drawing carbon steel sheet and strip (280–400 MN/m2) (suitable for welding) S 526, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (titanium stabilized: 54 hbar) S 527, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (niobium stabilized: 54 hbar) b) Ministry of Defence specifications Summary of Summary of pages pages AD 114, Design requirements, qualification approval tests and acceptance test This document a cover, inside front pages This comprises a front front(BA cover, an inside front2)cover, cover, pages ii to to vi, vi, fordocument AGS 2000comprises series stiffnuts andan BSF threads) pages to 31 and a back cover pages to 31 and a back cover DEF 151, Anodizing of aluminium and aluminium alloys This standard has (see copyright date) and may have had This standard has been been updated updated (seeand copyright DEF 2331, Protective PX-1, dyed undyed.date) and may have had amendments amendments incorporated incorporated This This will will be be indicated indicated in in the the amendment amendment table table on on the the DEFfront STAN, 03-8 Electro-deposition of tin inside cover inside front cover 2) Referred to in foreword only from the Society of website British Aerospace Companies, 29 King King Street, Street, St James’s, the Society of British Aerospace Companies, 29 St James’s, TS200 only from is obtainable from www.adsgroup.org.uk London, London, SW1 SW1 © BSI 2010 3) 3) Obtainable Obtainable iv Summary of pages This document comprises a front cover, an inside front cover, pages i to vi, pages to 31 and a back cover 2010 © BSI © © BSI The 2010 British Standards Institution 2013 v v v vi blank Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A200, 193,3A 3A201, 200,2A 3A213 201, to 2A 216:1981 3A 193, 3A to2A 2A213 216:1981+A1:2013 2.3 Section General requirements DEF STAN, 03-9 Electro-deposition of silver batch DTD 10, High nickel copper alloy sheets and strips the output of an effectively continuous production DTD 417, Lubricating oil, aircraft controls: anti-freezing run of each size of nut, free from any changes such 1.1 These British Standards cover the dimensions, 904, Cadmium plating as might be expected to result in an appreciable material, finish, testing andDTD identification of in the(SBAC) qualitypublication of the finished aircraft stiffnuts with Unified threads to variation 3) product c) Society ofAccording British Aerospace Companies (See section 2.) the materials used in their RS construction, the 732, Manufacturers identification monograms for aerospace fasteners stiffnuts are classified as satisfactory for use at 2.4 This publication does not purport to include all the necessary provisions of a sustained temperatures within the following bolt contract Users are responsible for its correct application ranges: unless otherwise stated, the term “bolt” includes a) p 75 C to + 425 C:Compliance corrosion-resisting with asteel Britishany Standard cannot immunity screweddoes bolt or stud ofconfer the same material, screw nuts, silver plated or unplated from legal obligations thread and finish as the standard bolt specified in clause 14 b) p 75 C to + 200 C: steel and corrosion-resisting steel nuts, cadmium plated 2.5 c) p 75 C to + 125 C: aluminium alloy, brass or bolt tolerance test bronze nuts a test to measure the torque required to remove a Scope NOTE All nuts are capable of remaining effective for servicing operations at p 40 C 1.2 Stiffnuts of the following types are covered by these British Standards: a) hexagon nuts: ordinary, thin and cap b) anchor nuts: 1) double-lug fixed: ordinary, thin and cap 2) double-lug floating: ordinary and thin 3) single-lug fixed: ordinary and thin c) stripnuts floating: ordinary and thin 1.3 In these standards, the nut bodies, whether of normal hexagon form or not, have a thread strength as least as great as the corresponding standard nuts Definitions For the purposes of these British Standards the following definitions apply 2.1 attachment plate (or cage) the formed sheet-metal plate of a floating anchor nut that carries the rivet lugs and retains the nut body, allowing a specified float in relation to the structure 2.2 baseplate stiffnut from a bolt of minimum diameter after the friction element has been strained by assembly on a bolt of maximum diameter 2.6 cap nut a stiffnut whose threaded bore is closed by a metal cap above the friction element, to prevent leakage of liquid or gas 2.7 endurance test a test to measure the torque required to remove a stiffnut from a standard bolt after a specified number of applications 2.8 fixed anchor nut a stiffnut having, at the bearing face and integral with the nut body, a lug or lugs by which it may be riveted in position, the nut becoming rigidly located in relation to the supporting structure 2.9 floating anchor nut a stiffnut in which the nut body, integral with a baseplate, is retained in an attachment plate that has lugs by which it may be riveted in position Provision is made for a limited amount of movement of the nut within the attachment plate to allow alignment on assembly the plate, normal to the axis of the nut, that forms Summary of pages the rivet lugs of a fixed anchor nut or the flange of a 2.10 friction This document comprises cover,element an inside front cover, pages i to vi, floating anchor nut or stripnut for retaining the nuta front pages to 31 and a back cover body in the attachment plate The baseplate is the portion of a stiffnut, above the nut body, always integral with the This nut body standard has been updated (see copyright andbetween may have designed to imposedate) friction thehad stiffnut and amendments incorporated This be indicated the amendment table thewill screw thread onin which it is mounted Theon the inside front cover friction element is contained between the minimum thread length and the maximum overall height of the stiffnut, and within the maximum plan form of the standard nut body 3) Obtainable from the Society of British Aerospace Companies, 29 King Street, St James’s, London, SW1 © BSI BSI 2010 © The 2010 British Standards Institution 2013 v Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 216:1981+A1:2013 BS 2870, Rolled copper and2.18 copper alloys Sheet, strip and foil torsional strength test (for anchor nuts and BS 2874, Copper and copper alloys Rods and sections (other than forging stripnuts) stock) the baseplate is said to be integral with the nut body BS 3488, Technical when the two are manufactured in one piece or anhydrous a testlanolin to confirm that the anchorage will withstand when they are joined by welding, brazing or similar torsion likely to bethreads) applied for through the bolt A 102, Steel bolts (Unified any hexagons and Unified aircraft fusion process under adverse conditions of assembly A 104, Corrosion-resisting steel bolts (Unified hexagons and Unified threads) 2.12 for aircraft Design and dimensions nut body A 169, Aluminium alloy bolts (Unified hexagons and Unified threads) for the portion of a stiffnut containing the screw thread 3.1 All nuts shall, after coating where applicable, aircraft to the dimensions and tolerances specified and having wall thickness and height to toconform B 11, Brasssufficient bars suitable be brazed or silver soldered in Table to Table 12 provide the required strength L 80, Sheet and strip of aluminium-21/4 per cent magnesium alloy (soft-0) 3.2 The friction elements and certain other features 2.13 L 81, Sheet and strip of aluminium-2 cent magnesium of the nuts1/are defined in Table alloy to Table 12 by per random sample (three-quarter hard-H6) maximum envelope dimensions, and in section by a sample taken in such a manner that every nut in functional test requirements For inspection L 163, Specification for sheet and strip of aluminium-coated the batch has a substantially equal chance of purposes the manufacturer provide approved aluminium-copper-magnesium-silicon-manganese alloyshall (solution treated, cold selection, so that the sample is thus a representative drawings (see clause 10) of all such features, with worked for flattening and aged at room temperature) cross section of the whole batch dimensions and limits and including (Cu 4.4, Mg 0.5, Si 0.8, Mnadequate 0.8) specifications for jointing processes and 2.14 L 168, Specification for bars and extruded sections of non-metallic locking elements Any changes in these stiffnut aluminium-copper-magnesium-silicon-manganese alloy (solution treated and features shall be notified to the quality assurance a nut body surmounted by aartificially device thataged) imposes (not exceeding 200 mm diameter or minor sectional authority (see clause 10) who may require friction between the nut anddimension) the screw thread on requalification testing before approving the drawing which it is mounted; the friction of such a value S 80, is Specification for highchanges chromium-nickel corrosion-resisting steel billets, that the nut may be considered The (880–1 080 MPa; limiting ruling section 100 mm) bars,self-retaining forgings and parts friction is independent of the loading on the face of Material and manufacture S 92, Carbon-manganese steel (suitable for welding) the nut 2.11 integral steel metal caps, attachment S 95, 11/2 per cent nickel-chromium-molybdenum 4.1 Nut bodies, baseplates, platessteel, and bright strips shall be manufactured from the S 112, Semi-free cutting carbon bars for machining (primarily appropriate intended for the manufacture of nuts) materials specified in Table a number of nut bodies integral with baseplates in a Materials used in friction elements and in jointing S 113, for “40” carbontosteel bars for machining (primarily intended for the continuous strip of formed section riveting the bright processes shall be in accordance with the approved manufacture of nuts) supporting structure Provision is made for a drawings; they shall not be adversely affected by limited amount of movement theManganese-molybeenum nuts within the contact S of 114, steel with or immersion in fuels, lubricants or attachment strip to allow alignment on assembly S 117, per cent chromiumother steel.fluids used in aircraft (e.g water, petroleum oils, synthetic oils (sebacic and adipic esters), 2.16 S 137, Specification for high chromium-nickel corrosion-resisting steel bright silicone greases, castor oil, mixtures, thrust test (for anchor nuts) bars (free machining) (880–1 080 MPa; limiting rulingpropan-2-ol section 70 mm) ethanol, methanol, ethanediol, glycerol) a test to confirm that the anchorage withstand S 154, 21/will per cent nickel-chromium-molybdenum steel billets, bars, forgings Nut bodies be produced the thrust likely to be applied a bolt under080 MPa:4.2 andbyparts (880–1 limiting rulingshall section 150 mm).by a machining process; baseplates of anchor nuts shall either be adverse conditions of assembly 2) (suitable for welding) S 510, Carbon steel sheet and strip (430–540 MN/mpart machined as an integral of the nut body or shall 2.17 2) (suitable S 511, Deep drawing carbon sheet and MN/m besteel produced fromstrip strip(280–400 or sheet and joined by torque test for welding) welding, brazing or other fusion process The body a test to measure the torqueSrequired to remove and base-plate of floating anchorsteel nutssheet and and stripnuts 526, Softened 18/10achromium-nickel corrosion-resisting strip stiffnut from a standard bolt shall be separate from, but shall be retained within, (titanium stabilized: 54 hbar) the attachment plate or strip S 527, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip 4.3 The friction device shall not cause undue (niobium stabilized: 54 hbar) damage or excessive wear on the thread of the bolt b) Ministry of Defence specifications The endurance test (see clause 17) shall serve to AD 114, Design requirements, qualification approval tests and acceptance indicate the satisfactory nature of the design in test this 2) for AGS 2000 series stiffnuts (BA and BSF threads) respect DEF 151, Anodizing of aluminium and aluminium alloys DEF 2331, Protective PX-1, dyed and undyed DEF STAN, 03-8 Electro-deposition of tin 2.15 stripnuts 2) iv Referred to in foreword only © BSI 2010 © The British Standards Institution 2013 0.266 0.329 0.391 0.454 0.516 in 0.128 0.154 0.180 0.206 max 0.256 0.319 0.381 0.444 0.506 0.048 0.048 0.048 0.048 0.048 0.270 0.310 0.345 0.420 0.460 118 0.144 0.170 0.196 0.035 0.035 0.035 0.035 0.127 0.168 0.208 0.225 in Thread axis to be within 0.006 in of specified position and rivet holes to be within 0.0015 in of specified position: to be inspected with a gauge of the relevant dimensions specified in Table 18 0.115 0.150 0.150 0.150 0.150 0.080 0.080 0.115 0.115 in in max in S R –0 +0.005 Q Depth D Diameter 21 20 Counterbore 19 18 Radius Radius 17 0.035 0.035 0.035 0.035 0.058 0.058 0.058 0.058 0.035 0.035 0.035 0.035 0.035 in in max 0.058 0.058 0.082 0.082 0.082 0.540 0.620 0.690 0.840 0.920 0.740 0.865 0.940 1.060 1.135 0.300 0.310 0.380 0.530 0.610 0.101 0.133 0.133 0.133 0.133 0.313 0.333 0.433 0.458 0.422 0.491 0.614 0.653 0.140 0.160 0.190 0.215 0.070 0.070 0.101 0.101 in max max in in max in E P O T 16 15 Thickness of baseplate 14 13 12 11 The nut body shall be round or hexagonal and shall either be made in one piece with the baseplate or be joined to it by welding or brazing Diameter of rivet holes For convenience ordinary nuts only are illustrated NOTE a NOTE Distance of rivet holes N S 95, 11/2 per cent nickel-chromium-molybdenum steel 0.096 0.128 0.128 0.128 0.128 0.375 0.425 0.475 0.550 0.600 0.331 0.384 0.468 0.527 0.596 0.398 0.468 0.572 0.652 0.742 0.065 0.065 0.096 0.096 0.220 0.250 0.300 0.325 0.201 0.237 0.291 0.299 0.233 0.273 0.333 0.343 in in in max max in M 10 Ordinary nut Overall height L Radius S 112, Semi-free cutting carbon steel, bright bars for machining (primarily intended for the manufacture of nuts) S 113, “40” carbon steel bright bars for machining (primarily intended for the manufacture of nuts) S 114, Manganese-molybeenum steel S 117, per cent chromium steel S 137, Specification for high chromium-nickel corrosion-resisting steel bright bars (free machining) (880–1 080 MPa; limiting ruling section 70 mm) Thin nut 0.123 0.156 0.198 0.240 0.281 0.190 0.240 0.302 0.365 0.427 0.431 0.493 0.554 0.679 0.741 0.438 0.500 0.562 0.688 0.750 a 0.2500 0.3125 0.3750 0.4375 0.5000 /4 in UNF 5/ in UNF 16 3/ in UNF /16 in UNF 1/ in UNF E G J L N 0.063 0.079 0.103 0.113 0.095 0.115 0.145 0.157 183 0.245 0.307 0.339 0.188 0.250 0.312 0.344 A B C D 0.1120 0.1380 0.1640 0.1900 in Nominal size Referred to in foreword only No 4-40 UNC No 6-32 UNC No 8-32 UNC No 10-32 UNF in in min in in max B Part reference Diameter or width across flats of nut body Ordinary nut 2) Thread length G S 154, 21/2 per cent nickel-chromium-molybdenum steel billets, bars, forgings and parts (880–1 080 MPa: limiting ruling section 150 mm) S 510, Carbon steel sheet and strip (430–540 MN/m2) (suitable for welding) S 511, Deep drawing carbon steel sheet and strip (280–400 MN/m2) (suitable for welding) S 526, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (titanium stabilized: 54 hbar) S 527, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (niobium stabilized: 54 hbar) b) Ministry of Defence specifications AD 114, Design requirements, qualification approval tests and acceptance test for AGS 2000 series stiffnuts (BA and BSF threads)2) DEF 151, Anodizing of aluminium and aluminium alloys DEF 2331, Protective PX-1, dyed and undyed DEF STAN, 03-8 Electro-deposition of tin Thin nut Table 11 — Dimensions and part references of ordinary and thin single-lug fixed anchor nuts (A 157 to A 164, A 200 and A 201) L 81, Sheet and strip of aluminium-21/4 per cent magnesium alloy (three-quarter hard-H6) L 163, Specification for sheet and strip of aluminium-coated aluminium-copper-magnesium-silicon-manganese alloy (solution treated, cold worked for flattening and aged at room temperature) (Cu 4.4, Mg 0.5, Si 0.8, Mn 0.8) L 168, Specification for bars and extruded sections of aluminium-copper-magnesium-silicon-manganese alloy (solution treated and artificially aged) (not exceeding 200 mm diameter or minor sectional dimension) S 80, Specification for high chromium-nickel corrosion-resisting steel billets, bars, forgings and parts (880–1 080 MPa; limiting ruling section 100 mm) S 92, Carbon-manganese steel (suitable for welding) Length of baseplate (for ref only) iv 18 BS 2870, Rolled copper and copper alloys Sheet, strip and foil BS 2874, Copper and copper alloys Rods and sections (other than forging stock) BS 3488, Technical anhydrous lanolin A 102, Steel bolts (Unified hexagons and Unified threads) for aircraft A 104, Corrosion-resisting steel bolts (Unified hexagons and Unified threads) for aircraft A 169, Aluminium alloy bolts (Unified hexagons and Unified threads) for aircraft B 11, Brass bars suitable to be brazed or silver soldered L 80, Sheet and strip of aluminium-21/4 per cent magnesium alloy (soft-0) Width of baseplate (for ref only) Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A 147 to 3A 168, 3A 180, 3A 181, 3A 186, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 216:1981+A1:2013 3A 187, 3A 192, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 © BSI BSI 2010 2010 © © The British Standards Institution 2013 Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The 3) Obtainable from the Society of British Aerospace Companies, 29 King Street, St James’s, London, SW1 For convenience ordinary nuts only are illustrated Summary of pages This document comprises a front cover, an inside front cover, pages i to vi, pages to 31 and a back cover This standard has been updated (see copyright date) and may have had amendments incorporated This will be indicated in the amendment table on the inside front cover Compliance with a British Standard does cannot confer immunity from legal obligations No 8-32 UNC No 10-32 UNF /4 in UNF 5/ 16 in UNF 0.1640 0.1900 0.2500 0.3125 in Part reference C D E G 0.312 0.344 0.438 0.500 in max in 0.307 0.339 0.431 0.493 B Ordinary nut 0.145 0.157 0.190 0.240 in Thin nut 0.103 0.113 0.123 0.156 in Diameter or Thread length G width across flats of nut body 0.399 0.435 0.543 0.605 in max in 0.394 0.430 0.538 0.600 P Width of baseplate 0.496 0.516 0.646 0.714 in max in 0.491 0.511 0.641 0.709 F Length of baseplate 10 11 0.036 0.036 0.036 0.036 in nom E Thickness of baseplate Nut and baseplate 13 0.226 0.252 0.312 0.375 in D 0.244 0.324 0.383 0.463 in max Countersink diameter 12 0.473 0.509 0.617 0.679 in max W Overall width 14 15 0.022 0.022 0.022 0.022 in nom T Thickness Nominal size 19 DEF STAN, 03-9 Electro-deposition of silver DTD 10, High nickel copper alloy sheets and strips DTD 417, Lubricating oil, aircraft controls: anti-freezing DTD 904, Cadmium plating c) Society of British Aerospace Companies (SBAC) publication 3) RS 732, Manufacturers identification monograms for aerospace fasteners This publication does not purport to include all the necessary provisions of a contract Users are responsible for its correct application 17 0.270 0.270 0.270 0.400 in max in 0.250 0.250 0.250 0.375 X Distance Attachment strip 16 0.096 0.096 0.096 0.128 in in max 0.101 0.101 0.101 0.133 N Diameter of rivet holes 18 NOTE The nut body shall be round or hexagonal and shall either be made in one piece with the baseplate or be joined to it by welding or brazing Thread axis to be within 0.006 in of specified position: to be inspected with a gauge of the relevant dimensions specified in Table 17 NOTE Table 12 — Dimensions and part references of ordinary and thin stripnuts (A 165 to A 168) Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A 147 to 3A 3A 180, 3A 3A 186, 3A200, 193, 3A201, 200, 3A168, 201, to 181, 2A 216:1981 3A 193, 3A 3A 2A 213 to2A 2A213 216:1981+A1:2013 3A 187, 3A 192, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 © BSI BSI 2010 © The 2010 British Standards Institution 2013 v 19 19 Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The a Y diameter hole to be within 0.003 in of specified position and rivet holes to be within 0.0015 in of specified position: to be inspected with a gauge of the relevant dimensions specified in Table 19 b) a 1/4 in UNF thin stripnut with aluminium alloy nut and steel attachment plate at 1.6 in pitch comprising 12 pitches (i.e 13 nuts on a strip of overall length 20.5 in) is designated BS A 168 E/2X/12 a) a 5/16 in UNF ordinary stripnut with steel nut and steel attachment plate at 1.0 in pitch comprising 25 pitches (i.e., 26 nuts on a strip of overall length 26.75 in) is designated BS A 165 G/Y/25; in 2X 2Y 3X Y, etc Code letter 0.015 0.025 0.040 0.050 1.6 1.0 2.4 3.0 0.015 0.025 0.040 0.050 in in 0.015 0.015 0.025 0.025 in 0.030 0.030 in 0.040 0.040 in 0.305 0.313 0.346 0.399 in 0.347 0.357 0.413 0.483 in 0.209 0.235 0.305 0.367 in 0.204 0.230 0.300 0.362 in 0.053 0.053 0.053 0.053 in 0.424 0.460 0.568 0.630 in 0.337 0.369 0.463 0.525 in 0.342 0.374 0.468 0.530 0.1640 C 0.1900 D 0.2500 E 0.3125 G No 8-32 UNC No 10-32 UNF /4 in UNF /16 in UNF in Referred to in foreword only Examples for ordering (see 9.4): max min max Nominal size 2) iv 20 Pitch Nuts may be spaced in the same strip, at multiples of pitch V, the spacing required being indicated for ordering purposes by prefixing the code letter X or Y by the number of multiples required, e.g.: a max min max max max max Y H Q J Width Depth Float Assembly Attachment strip Width between flange lips a Internal Diameter of dimensions hole of channel Overall height L Transverse Axial Lateral (across (along rivet rivet axis) axis) No 8-32 UNC No 10-32 UNF 1/ in UNF 5/ 16 in UNF Nominal size 31 30 29 28 27 26 25 24 23 22 21 20 S 112, Semi-free cutting carbon steel, bright bars for machining (primarily intended for the manufacture of nuts) S 113, “40” carbon steel bright bars for machining (primarily intended for the manufacture of nuts) S 114, Manganese-molybeenum steel S 117, per cent chromium steel S 137, Specification for high chromium-nickel corrosion-resisting steel bright bars (free machining) (880–1 080 MPa; limiting ruling section 70 mm) S 154, 21/2 per cent nickel-chromium-molybdenum steel billets, bars, forgings and parts (880–1 080 MPa: limiting ruling section 150 mm) S 510, Carbon steel sheet and strip (430–540 MN/m2) (suitable for welding) S 511, Deep drawing carbon steel sheet and strip (280–400 MN/m2) (suitable for welding) S 526, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (titanium stabilized: 54 hbar) S 527, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (niobium stabilized: 54 hbar) b) Ministry of Defence specifications AD 114, Design requirements, qualification approval tests and acceptance test for AGS 2000 series stiffnuts (BA and BSF threads)2) DEF 151, Anodizing of aluminium and aluminium alloys DEF 2331, Protective PX-1, dyed and undyed DEF STAN, 03-8 Electro-deposition of tin Part reference L 81, Sheet and strip of aluminium-21/4 per cent magnesium alloy (three-quarter hard-H6) L 163, Specification for sheet and strip of aluminium-coated aluminium-copper-magnesium-silicon-manganese alloy (solution treated, cold worked for flattening and aged at room temperature) (Cu 4.4, Mg 0.5, Si 0.8, Mn 0.8) L 168, Specification for bars and extruded sections of aluminium-copper-magnesium-silicon-manganese alloy (solution treated and artificially aged) (not exceeding 200 mm diameter or minor sectional dimension) S 80, Specification for high chromium-nickel corrosion-resisting steel billets, bars, forgings and parts (880–1 080 MPa; limiting ruling section 100 mm) S 92, Carbon-manganese steel (suitable for welding) S 95, 11/2 per cent nickel-chromium-molybdenum steel Ordinary nut Table 12 — Dimensions and part references of ordinary and thin stripnuts (A 165 to A 168) X X X — Y Y Y Y 1.0 in Code letter 0.8 in Pitch Va BS 2870, Rolled copper and copper alloys Sheet, strip and foil BS 2874, Copper and copper alloys Rods and sections (other than forging stock) BS 3488, Technical anhydrous lanolin A 102, Steel bolts (Unified hexagons and Unified threads) for aircraft A 104, Corrosion-resisting steel bolts (Unified hexagons and Unified threads) for aircraft A 169, Aluminium alloy bolts (Unified hexagons and Unified threads) for aircraft B 11, Brass bars suitable to be brazed or silver soldered L 80, Sheet and strip of aluminium-21/4 per cent magnesium alloy (soft-0) Thin nut Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A 147 to 3A 168, 3A 180, 3A 181, 3A 186, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 216:1981+A1:2013 3A 187, 3A 192, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 © BSI BSI 2010 2010 © © The British Standards Institution 2013 Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A200, 193,3A 3A201, 200,2A 3A213 201, to 2A 216:1981 3A 193, 3A to2A 2A213 216:1981+A1:2013 b) Sizes 1/4 in UNF and above Appendix A Equipment for testing DEF STAN, 03-9 Electro-deposition of silver stiffnuts 1) Maximum effective diameter The maximum DTD 10, High nickel copper alloyeffective sheets and strips.is equal to class 3A diameter A.1 Test of squareness ofDTD face417, to thread Lubricating oil, aircraft controls:effective anti-freezing maximum diameter specified in A squareness gauge of a type suitable for use for the Table of BS 1580-1:1962, plus 0.0001 in for DTD 904, Cadmium plating test specified in 8.2 is shown in Figure 1/ in UNF and sizes up to and including 3) c) Society of British Aerospace Companies (SBAC) publication A.2 Torque and torsional strength tests plus 0.0002 in for sizes over 1/2 in UNF RS 732, Manufacturers identification monograms for aerospace fasteners The apparatus illustrated diagrammatically in 2) Minimum effective diameter The minimum This publication does not purport to includediameter all the necessary provisions of a Figure is suitable for measuring the unscrewing effective is equal to the maximum contract Users are responsible for its correct application torque of stiffnuts and the torsional strength of effective diameter, as defined in A.3.1 b) 1), anchor nuts in accordance with clauses 15 and 18 minus does 0.0006cannot in on sizes up to and Compliance with a British Standard confer immunity 1/ in UNF and minus 0.0008 in on For the latter test, the face plate shall be including from legal obligations substituted for the chuck in the case of hexagonalsizes over 1/2 in UNF bodied nuts, the load being applied through the 3) Maximum major diameter The maximum hexagon socket in the sliding shaft With major diameter is equal to the class 3A roundbodied nuts, the face plate shall be fitted to minimum major diameter specified in Table the sliding shaft and the load applied through a of BS 1580-1:1962 screwed mandrel in the chuck 4) Minimum major diameter The minimum The spring balance used in this apparatus shall be major diameter is equal to the maximum major calibrated against deadweights traceable to diameter, as defined in A.3.1 b) 3), national standards minus 0.0004 in NOTE The weight corresponding to the interval between The root of the thread is cleared as for “Go” consecutive graduation marks should preferably comply with plug gauges specified in Figure 1a of Table 13, column 3, but may, at the discretion of the quality assurance authority, have wider graduations as indicated in BS 919-1:1960 column A.3.2 Low limit test bolts NOTE Other torque-measuring devices may be employed at the discretion of the quality assurance authority a) Sizes below 1/4 in UNF A.3 Bolt tolerance test 1) Maximum effective diameter The maximum For the purposes of the bolt tolerance test specified effective diameter is equal to the class 2A in clause 16, steel test bolts shall be used with minimum effective diameter specified in hardened threads ground to the dimensions and Table 40 of BS 1580-3:1965 limits specified in Table 14 The dimensions in the 2) Minimum effective diameter The minimum table have been calculated as follows effective diameter is equal to the maximum A.3.1 High limit test bolts effective diameter as defined in A.3.2 a) 1), minus 0.0004 in a) Sizes below 1/4 in UNF 3) Maximum major diameter The maximum 1) Maximum effective diameter The maximum major diameter is equal to the class 2A effective diameter is equal to the class 3A maximum major diameter minus 1.5 times the maximum effective diameter specified in class 2A major diameter tolerance specified in Table 40 of BS 1580-3:1965, plus 0.0001 in Table 40 of BS 1580-3:1965 2) Minimum effective diameter The minimum 4) Minimum major diameter The minimum effective diameter is equal to the maximum major diameter is equal to the maximum major effective diameter, as defined in A.3.1 a) 1), diameter, as defined in A.3.2 a) 3), minus 0.0004 in minus 0.0004 in 3) Maximum major diameter The maximum b) Sizes 1/4 in UNF and above major diameter is equal to the class 3A 1) Maximum effective diameter The maximum minimum major diameter specified in Table 40 Summary of pages effective diameter is equal to: of BS 1580-3:1965 This document comprises a front cover, an inside front cover, pages i to vi, 1/ (minimum class 2A effective diameter + 4) Minimum major pages diameter minimum to The 31 and a back cover major diameter is equal to the maximum major minimum class 1A diameter) This standard has been updated (see copyright date) andeffective may have had diameter, as defined in A.3.1 a) 3), where amendments incorporated This will be indicated in the amendment table on the minus 0.0004 in inside front cover class 2A and 1A minimum effective diameters are those specified in Table of BS 1580-1:1962 3) Obtainable from the Society of British Aerospace Companies, 29 King Street, St James’s, London, SW1 © BSI BSI 2010 © The 2010 British Standards Institution 2013 v 21 Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 216:1981+A1:2013 BS 2870, The Rolled copper andThe copper Sheet, strip and foil 2) Minimum effective diameter minimum root alloys of the thread is cleared as for “Go” plug effective diameter is equal to theCopper maximum gauges in sections Table of BS 919-1:1960 BS 2874, and copper alloys.specified Rods and (other than forging effective diameter, as defined stock) in A.3.2 b) 1), A.4 Anchor nut thrust test minus 0.0004 in on sizes to and BSup 3488, Technical anhydrous lanolin.suitable for use for the thrust test Apparatus including 1/2 in UNF and minus 0.0005 in on clause 19 is illustrated in Figure 11 A 102, Steel bolts (Unified specified hexagons in and Unified threads) for aircraft sizes over 1/2 in UNF NOTE The plates on which the nuts are mounted located by A 104, Corrosion-resisting steel bolts (Unified hexagons and Unifiedare threads) 3) Maximum major diameter The maximum means of holes fitting on dowels in the upper face of the base for aircraft anvil major diameter is equal to the class 1A A 169, Aluminium alloy hexagons and Unified threads) for of minimum major diameter specified in Table bolts The(Unified load shall either be applied direct by means aircraft of BS 1580-1:1962 dead weights or gradually, using a spring balance to B 11, Brass bars suitable torecord be brazed or silver soldered the load applied 4) Minimum major diameter The minimum major diameter is equalLto the maximum major 80, Sheet and strip of aluminium-21/4 per cent magnesium alloy (soft-0) diameter, as defined inLA.3.2 b) 3),and strip of aluminium-21/ per cent magnesium alloy 81, Sheet minus 0.0004 in (three-quarter hard-H6) L 163, Specification for sheet and strip of aluminium-coated aluminium-copper-magnesium-silicon-manganese alloy (solution treated, cold worked for flattening and aged at room temperature) (Cu 4.4, Mg 0.5, Si 0.8, Mn 0.8) L 168, Specification for bars and extruded sections of aluminium-copper-magnesium-silicon-manganese alloy (solution treated and artificially aged) (not exceeding 200 mm diameter or minor sectional dimension) S 80, Specification for high chromium-nickel corrosion-resisting steel billets, bars, forgings and parts (880–1 080 MPa; limiting ruling section 100 mm) S 92, Carbon-manganese steel (suitable for welding) S 95, 11/2 per cent nickel-chromium-molybdenum steel S 112, Semi-free cutting carbon steel, bright bars for machining (primarily intended for the manufacture of nuts) S 113, “40” carbon steel bright bars for machining (primarily intended for the manufacture of nuts) S 114, Manganese-molybeenum steel Figure — Squareness gauge S 117, per cent chromium steel S 137, Specification for high chromium-nickel corrosion-resisting steel bright bars (free machining) (880–1 080 MPa; limiting ruling section 70 mm) S 154, 21/2 per cent nickel-chromium-molybdenum steel billets, bars, forgings and parts (880–1 080 MPa: limiting ruling section 150 mm) S 510, Carbon steel sheet and strip (430–540 MN/m2) (suitable for welding) S 511, Deep drawing carbon steel sheet and strip (280–400 MN/m2) (suitable for welding) S 526, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (titanium stabilized: 54 hbar) S 527, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (niobium stabilized: 54 hbar) b) Ministry of Defence specifications AD 114, Design requirements, qualification approval tests and acceptance test for AGS 2000 series stiffnuts (BA and BSF threads)2) DEF 151, Anodizing of aluminium and aluminium alloys DEF 2331, Protective PX-1, dyed and undyed DEF STAN, 03-8 Electro-deposition of tin 2) iv 22 Referred to in foreword only © BSI 2010 © BSI 2010 © The British Standards Institution 2013 Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A200, 193,3A 3A201, 200,2A 3A213 201, to 2A 216:1981 3A 193, 3A to2A 2A213 216:1981+A1:2013 Table 13 — Calibration of spring balances for torque and torsional strength tests DEF STAN, 03-9 Electro-deposition of silver DTD 10, High nickel copper alloy sheets and strips Capacity of spring Allowance Graduation marks Minimum graduation DTD 417, Lubricating oil, aircraft controls: anti-freezing balance DTD 904, Cadmium plating not more than: 3) c) Society of British Aerospace Companies lb 30 grains (0.0685 oz) drams(SBAC) (0.125 publication oz) drams (0.25 oz) RS 732, Manufacturers identification monograms for aerospace fasteners lb /2 drams (0.09375 oz) drams (0.25 oz) drams (0.50 oz) lb 2This drams (0.125 oz)not purport to include dramsall(0.25 oz) 8provisions drams (0.50 publication does the necessary of oz) a contract Users are responsible for its correct application drams (0.25 oz) oz lb 21/2 drams (0.15625 oz) (0.1875 drams oz) confer oz lb with aoz) British Standard does(0.25 cannot immunity 3Compliance drams (0.21875 oz) drams (0.50 oz) oz 10 lb legal obligations /2 drams 3from 14 lb 15 lb 20 lb 41/2 drams 41/2 drams drams (0.28125 oz) (0.28125 oz) (0.3125 oz) drams (0.50 oz) drams (0.50 oz) oz oz oz oz 28 lb 30 lb 40 lb drams drams (0.375 oz) (0.375 oz) oz oz oz oz oz oz oz oz 0.5 % of capacity oz oz ¸ Ơ Ô Ô Ô ˝ Ô Ô Ô Ô ˛ 50 lb 60 lb 100 lb not exceeding the weight corresponding to one-quarter of the interval between consecutive graduations NOTE 1 grain = 0.0648 grams; dram = 1.7718 grams; ounce = 28.3495 grams; pound = 453.592 grams NOTE Ounce equivalents in brackets are for information only Summary of pages This document comprises a front cover, an inside front cover, pages i to vi, pages to 31 and a back cover This standard has been updated (see copyright date) and may have had amendments incorporated This will be indicated in the amendment table on the inside front cover 3) Obtainable from the Society of British Aerospace Companies, 29 King Street, St James’s, London, SW1 © BSI BSI 2010 © The 2010 British Standards Institution 2013 v 23 Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 216:1981+A1:2013 BS 2870, Rolled copper and copper alloys Sheet, strip and foil BS 2874, Copper and copper alloys Rods and sections (other than forging stock) BS 3488, Technical anhydrous lanolin A 102, Steel bolts (Unified hexagons and Unified threads) for aircraft A 104, Corrosion-resisting steel bolts (Unified hexagons and Unified threads) for aircraft A 169, Aluminium alloy bolts (Unified hexagons and Unified threads) for aircraft B 11, Brass bars suitable to be brazed or silver soldered L 80, Sheet and strip of aluminium-21/4 per cent magnesium alloy (soft-0) L 81, Sheet and strip of aluminium-21/4 per cent magnesium alloy (three-quarter hard-H6) L 163, Specification for sheet and strip of aluminium-coated aluminium-copper-magnesium-silicon-manganese alloy (solution treated, cold worked for flattening and aged at room temperature) (Cu 4.4, Mg 0.5, Si 0.8, Mn 0.8) L 168, Specification for bars and extruded sections of aluminium-copper-magnesium-silicon-manganese alloy (solution treated and artificially aged) (not exceeding 200 mm diameter or minor sectional dimension) S 80, Specification for high chromium-nickel corrosion-resisting steel billets, bars, forgings and parts (880–1 080 MPa; limiting ruling section 100 mm) S 92, Carbon-manganese steel (suitable for welding) S 95, 11/2 per cent nickel-chromium-molybdenum steel S 112, Semi-free cutting carbon steel, bright bars for machining (primarily Figure 7— Torque-testing machine intended for the manufacture of nuts) S 113, “40” carbon steel bright bars for machining (primarily intended for the manufacture of nuts) S 114, Manganese-molybeenum steel S 117, per cent chromium steel S 137, Specification for high chromium-nickel corrosion-resisting steel bright bars (free machining) (880–1 080 MPa; limiting ruling section 70 mm) S 154, 21/2 per cent nickel-chromium-molybdenum steel billets, bars, forgings and parts (880–1 080 MPa: limiting ruling section 150 mm) S 510, Carbon steel sheet and strip (430–540 MN/m2) (suitable for welding) S 511, Deep drawing carbon steel sheet and strip (280–400 MN/m2) (suitable for welding) S 526, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (titanium stabilized: 54 hbar) S 527, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (niobium stabilized: 54 hbar) b) Ministry of Defence specifications AD 114, Design requirements, qualification approval tests and acceptance test for AGS 2000 series stiffnuts (BA and BSF threads)2) DEF 151, Anodizing of aluminium and aluminium alloys DEF 2331, Protective PX-1, dyed and undyed DEF STAN, 03-8 Electro-deposition of tin 2) iv 24 Referred to in foreword only © BSI 2013 2010 © The British Standards Institution Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A200, 193,3A 3A201, 200,2A 3A213 201, to 2A 216:1981 3A 193, 3A to2A 2A213 216:1981+A1:2013 Table 14 —Dimensions for high limit and low limit test bolts DEF STAN, 03-9 Electro-deposition of silver DTD 10, High nickel copper alloy sheets and strips DTD 417, Lubricating oil, aircraft controls: anti-freezing DTD 904, Cadmium plating c) Society of British Aerospace Companies (SBAC) publication 3) RS 732, Manufacturers identification monograms for aerospace fasteners This publication does not purport to include all the necessary provisions of a contract Users are responsible for its correct application Compliance with a British Standard does cannot confer immunity from legal obligations Thread High limit test bolt Effective diameter No 8-32 UNC No 10-32 UNF /4 /16 /8 7/ 16 in UNF in UNF in UNF in UNF /2 in /16 in /8 in /4 in UNF UNF UNF UNF /8 in UNF in UNF Low limit test bolt Major diameter Effective diameter Major diameter max max max max in in in in in in in in 0.1438 0.1698 0.1434 0.1694 0.1580 0.1840 0.1576 0.1836 0.1394 0.1653 0.1390 0.1649 0.1541 0.1801 0.1537 0.1797 0.2269 0.2855 0.3480 0.4051 0.2263 0.2849 0.3474 0.4045 0.2435 0.3053 0.3678 0.4294 0.2431 0.3049 0.3674 0.4290 0.2217 0.2797 0.3421 0.3985 0.2213 0.2793 0.3417 0.3981 0.2392 0.3006 0.3631 0.4240 0.2388 0.3002 0.3627 0.4236 0.4676 0.5266 0.5891 0.7096 0.4670 0.5258 0.5883 0.7088 0.4919 0.5538 0.6163 0.7406 0.4915 0.5534 0.6159 0.7402 0.4608 0.5193 0.5816 0.7016 0.4604 0.5188 0.5811 0.7011 0.4865 0.5480 0.6105 0.7343 0.4861 0.5476 0.6101 0.7339 0.8288 0.9461 0.8280 0.9453 0.8647 0.9886 0.8643 0.9882 0.8203 0.9368 0.8198 0.9363 0.8579 0.9810 0.8575 0.9806 NOTE The above limits for the effective diameters are determined so that a high limit test bolt approximates closely to a British Standard bolt for aircraft with a maximum effective thread diameter, and a low limit test bolt is always less than a British Standard bolt for aircraft with a minimum effective thread diameter Summary of pages This document comprises a front cover, an inside front cover, pages i to vi, pages to 31 and a back cover This standard has been updated (see copyright date) and may have had amendments incorporated This will be indicated in the amendment table on the inside front cover 3) Obtainable from the Society of British Aerospace Companies, 29 King Street, St James’s, London, SW1 © BSI BSI 2010 © The 2010 British Standards Institution 2013 v 25 Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 216:1981+A1:2013 BS 2870, Rolled copper and copper alloys Sheet, strip and foil BS 2874, Copper and copper alloys Rods and sections (other than forging stock) BS 3488, Technical anhydrous lanolin A 102, Steel bolts (Unified hexagons and Unified threads) for aircraft A 104, Corrosion-resisting steel bolts (Unified hexagons and Unified threads) for aircraft A 169, Aluminium alloy bolts (Unified hexagons and Unified threads) for aircraft B 11, Brass bars suitable to be brazed or silver soldered L 80, Sheet and strip of aluminium-21/4 per cent magnesium alloy (soft-0) L 81, Sheet and strip of aluminium-21/4 per cent magnesium alloy (three-quarter hard-H6) L 163, Specification for sheet and strip of aluminium-coated aluminium-copper-magnesium-silicon-manganese alloy (solution treated, cold worked for flattening and aged at room temperature) (Cu 4.4, Mg 0.5, Si 0.8, Mn 0.8) L 168, Specification for bars and extruded sections of aluminium-copper-magnesium-silicon-manganese alloy (solution treated and artificially aged) (not exceeding 200 mm diameter or minor sectional dimension) Figure — Thrust-testing machine S 80, Specification for high chromium-nickel corrosion-resisting steel billets, bars, forgings and parts (880–1 080 MPa; limiting ruling section 100 mm) S 92, Carbon-manganese steel (suitable for welding) S 95, 11/2 per cent nickel-chromium-molybdenum steel S 112, Semi-free cutting carbon steel, bright bars for machining (primarily intended for the manufacture of nuts) S 113, “40” carbon steel bright bars for machining (primarily intended for the manufacture of nuts) S 114, Manganese-molybeenum steel S 117, per cent chromium steel S 137, Specification for high chromium-nickel corrosion-resisting steel bright bars (free machining) (880–1 080 MPa; limiting ruling section 70 mm) S 154, 21/2 per cent nickel-chromium-molybdenum steel billets, bars, forgings and parts (880–1 080 MPa: limiting ruling section 150 mm) S 510, Carbon steel sheet and strip (430–540 MN/m2) (suitable for welding) S 511, Deep drawing carbon steel sheet and strip (280–400 MN/m2) (suitable for welding) S 526, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (titanium stabilized: 54 hbar) S 527, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (niobium stabilized: 54 hbar) b) Ministry of Defence specifications AD 114, Design requirements, qualification approval tests and acceptance test for AGS 2000 series stiffnuts (BA and BSF threads)2) DEF 151, Anodizing of aluminium and aluminium alloys DEF 2331, Protective PX-1, dyed and undyed DEF STAN, 03-8 Electro-deposition of tin 2) iv 26 Referred to in foreword only © BSI 2010 © The British Standards Institution 2013 21/2 21/2 3 0.423 0.456 0.498 0.540 0.581 2 2 0.363 0.379 0.403 0.413 in +0.030 –0 P /4 /4 /16 /16 1 in Q 15 14 /16 /8 3/ 1/ 1/ in R 16 DEF STAN, 03-9 Electro-deposition of silver DTD 10, High nickel copper alloy sheets and strips DTD 417, Lubricating oil, aircraft controls: anti-freezing DTD 904, Cadmium plating c) Society of British Aerospace Companies (SBAC) publication 3) RS 732, Manufacturers identification monograms for aerospace fasteners This publication does not purport to include all the necessary provisions of a contract Users are responsible for its correct application 0.123 0.156 0.198 0.240 0.281 0.371 0.437 0.521 0.605 0.687 0.220 0.282 0.345 0.407 0.470 0.2500 0.3125 0.3750 0.4375 0.5000 0.2620 0.3245 0.3870 0.4495 0.5120 /32 /8 1/ 1/ 1/ 0.373 0.406 0.448 0.490 0.531 /32 /32 /32 /32 /16 /4 1/ 1/ 1/ 0.375 0.425 0.475 0.550 0.600 /16 /16 /16 /16 0.220 0.250 0.300 0.325 in 1 11/8 11/8 13/8 13/8 13/8 13/4 13/4 /2 /2 5/ /8 /4 /4 3/ 1 in 0.015 0.313 0.329 0.353 0.363 in in 0.005 Drive fit F E C B 0.093 0.125 0.125 0.125 0.125 0.063 0.079 0.103 0.113 0.251 0.283 0.331 0.351 0.094 0.120 0.140 0.160 0.1120 0.1380 0.1640 0.1900 0.1240 0.1500 0.1760 0.2020 0.062 0.062 0.093 0.093 in in in in in in in +0.015 –0 +0.015 –0 0.005 +0 –0.0002 +0.0005 –0 +0 –0.0002 N M L K J H G 10 The screw plug shall enter to the full depth N when the anchor nut is correctly located on the gauge All gauging surfaces to be hardened within the range 700 HV to 850 HV Dimension in inches 11 12 13 Compliance with a British Standard does cannot confer immunity from legal obligations 3 in UNF in UNF in UNF in UNF in UNF /4 /16 3/ 7/ 16 1/ No 4-40 UNC No 6-32 UNC No 8-32 UNC No 10-32 UNF 0.015 D in A Nominal size 3) Obtainable Summary of pages This document comprises a front cover, an inside front cover, pages i to vi, pages to 31 and a back cover This standard has been updated (see copyright date) and may have had amendments incorporated This will be indicated in the amendment table on the inside front cover NOTE NOTE NOTE Table 15 — Acceptance gauge for ordinary and thin double-lug fixed anchor nuts (see Table 8) Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A 147 to 3A 3A 180, 3A 3A 186, 3A200, 193, 3A201, 200, 3A168, 201, to 181, 2A 216:1981 3A 193, 3A 3A 2A 213 to2A 2A213 216:1981+A1:2013 3A 187, 3A 192, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 from the Society of British Aerospace Companies, 29 King Street, St James’s, London, SW1 © BSI BSI 2010 © The 2010 British Standards Institution 2013 v 27 27 Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The /2 /2 1 3 /8 /8 /16 /8 in 2 /4 1/ /16 /16 3/ 16 3 /16 K in 21/2 21/2 in L 12 11 /8 1/ /32 3/ 32 /32 /2 1/ /8 /8 3/ /16 /4 1/ /4 1 /8 1/ /8 in Drive fit Drive fit G 3 in 0.015 H /32 in J 10 L 81, Sheet and strip of aluminium-21/4 per cent magnesium alloy (three-quarter hard-H6) L 163, Specification for sheet and strip of aluminium-coated aluminium-copper-magnesium-silicon-manganese alloy (solution treated, cold worked for flattening and aged at room temperature) (Cu 4.4, Mg 0.5, Si 0.8, Mn 0.8) L 168, Specification for bars and extruded sections of aluminium-copper-magnesium-silicon-manganese alloy (solution treated and artificially aged) (not exceeding 200 mm diameter or minor sectional dimension) S 80, Specification for high chromium-nickel corrosion-resisting steel billets, bars, forgings and parts (880–1 080 MPa; limiting ruling section 100 mm) S 92, Carbon-manganese steel (suitable for welding) in F S 95, 11/2 per cent nickel-chromium-molybdenum steel /4 1/ /4 1 0.093 0.125 0.125 0.294 0.356 0.419 /16 3/ 16 0.062 0.093 0.093 0.167 0.198 0.224 in in +0 –0.0002 +0 –0.0002 E D All gauging surfaces to be hardened within the range 700 HV to 850 HV /16 S 112, Semi-free cutting carbon steel, bright bars for machining (primarily intended for the manufacture of nuts) S 113, “40” carbon steel bright bars for machining (primarily intended for the manufacture of nuts) S 114, Manganese-molybeenum steel S 117, per cent chromium steel S 137, Specification for high chromium-nickel corrosion-resisting steel bright bars (free machining) (880–1 080 MPa; limiting ruling section 70 mm) 0.375 0.425 0.475 /4 3/ /8 13/8 13/8 11/4 /4 in UNF /16 in UNF /8 in UNF 0.250 0.300 0.325 /8 5/ /2 Referred to in foreword only 1 11/8 11/8 in in No 6-32 UNC No 8-32 UNC No 10-32 UNF in 0.015 0.015 C B A Nominal size of attachment plate NOTE S 154, 21/2 per cent nickel-chromium-molybdenum steel billets, bars, forgings and parts (880–1 080 MPa: limiting ruling section 150 mm) S 510, Carbon steel sheet and strip (430–540 MN/m2) (suitable for welding) S 511, Deep drawing carbon steel sheet and strip (280–400 MN/m2) (suitable for welding) S 526, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (titanium stabilized: 54 hbar) S 527, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (niobium stabilized: 54 hbar) b) Ministry of Defence specifications AD 114, Design requirements, qualification approval tests and acceptance test for AGS 2000 series stiffnuts (BA and BSF threads)2) DEF 151, Anodizing of aluminium and aluminium alloys DEF 2331, Protective PX-1, dyed and undyed DEF STAN, 03-8 Electro-deposition of tin 2) iv 28 M 13 BS 2870, Rolled copper and copper alloys Sheet, strip and foil BS 2874, Copper and copper alloys Rods and sections (other than forging stock) BS 3488, Technical anhydrous lanolin A 102, Steel bolts (Unified hexagons and Unified threads) for aircraft A 104, Corrosion-resisting steel bolts (Unified hexagons and Unified threads) for aircraft A 169, Aluminium alloy bolts (Unified hexagons and Unified threads) for aircraft B 11, Brass bars suitable to be brazed or silver soldered L 80, Sheet and strip of aluminium-21/4 per cent magnesium alloy (soft-0) Table 16 — Acceptance gauge for attachment plates for ordinary and thin double-lug floating anchor nuts (see Table 10) Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A 147 to 3A 168, 3A 180, 3A 181, 3A 186, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 216:1981+A1:2013 3A 187, 3A 192, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 © BSI BSI 2010 2010 © © The British Standards Institution 2013 Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The in 0.423 0.456 0.498 2 0.379 0.403 0.413 in +0.030 –0 +0.015 –0 P 14 21/2 21/2 in Q 15 /4 /16 5/ 16 5/ 16 /8 7/ 16 R 16 DEF STAN, 03-9 Electro-deposition of silver DTD 10, High nickel copper alloy sheets and strips DTD 417, Lubricating oil, aircraft controls: anti-freezing DTD 904, Cadmium plating c) Society of British Aerospace Companies (SBAC) publication 3) RS 732, Manufacturers identification monograms for aerospace fasteners This publication does not purport to include all the necessary provisions of a contract Users are responsible for its correct application 0.123 0.156 0.198 0.371 0.437 0.521 0.220 0.282 0.345 0.2500 0.3125 0.3750 /8 /8 /8 1 /8 1/ /8 1 /8 /8 /8 1 0.373 0.406 0.448 0.543 0.605 0.668 0.646 0.714 0.814 0.398 0.496 0.516 0.327 0.399 0.435 0.329 0.353 0.363 /8 1/ /8 in in in in 1 11/8 1 in 0.015 +0.0005 –0 +0.0005 –0 0.005 0.010 G F E C B 0.2620 0.3245 0.3870 0.079 0.103 0.113 0.283 0.331 0.351 0.120 0.140 0.160 0.1380 0.1640 0.1900 0.1500 0.1760 0.2020 in in in in in in 0.005 +0.015 –0 +0 –0.0002 K H J +0.0005 –0 N L 13 M The screw plug shall enter to the full depth N when the subassembly is correctly located in the gauge All gauging surfaces to be hardened within the range 700 HV to 850 HV Dimension in inches 10 11 12 Compliance with a British Standard does cannot confer immunity from legal obligations 11/2 11/2 15/8 in UNF /16 in UNF 3/ in UNF 1/ No 6-32 UNC No 8-32 UNC No 10-32 UNF D 1 /2 11/2 11/2 in A Nominal size 0.015 3) Obtainable Summary of pages This document comprises a front cover, an inside front cover, pages i to vi, pages to 31 and a back cover This standard has been updated (see copyright date) and may have had amendments incorporated This will be indicated in the amendment table on the inside front cover NOTE NOTE NOTE Table 17 — Acceptance gauge for ordinary and thin nut and baseplate subassemblies for double-lug floating anchor nuts (see Table 10) and stripnuts (see Table 12) Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A 147 to 3A 3A 180, 3A 3A 186, 3A200, 193, 3A201, 200, 3A168, 201, to 181, 2A 216:1981 3A 193, 3A 3A 2A 213 to2A 2A213 216:1981+A1:2013 3A 187, 3A 192, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 from the Society of British Aerospace Companies, 29 King Street, St James’s, London, SW1 © BSI BSI 2010 © The 2010 British Standards Institution 2013 v 29 29 Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The 2 8 /16 3 2 21 21 3 0.220 0.282 0.345 0.407 0.470 0.2500 0.3125 0.3750 0.4375 0.5000 2 2 0.094 0.120 0.140 0.160 0.1120 0.1380 0.1640 0.1900 in in 0.005 +0 –0.0002 R Q 15 14 0.423 0.456 0.498 0.540 0.581 0.123 0.156 0.198 0.240 0.281 0.371 0.437 0.521 0.605 0.687 /32 /8 /8 /8 /8 0.353 0.379 0.403 0.413 0.063 0.079 0.103 0.113 0.251 0.283 0.331 0.351 /32 /32 3/ 32 3/ 32 +0.0005 –0.0002 –0 in in in in 0.030 –0 0.015 –0 0.015 –0 P N M L 10 The screw plug shall enter to the full depth N when the anchor is correctly located on the gauge All gauging surfaces to be hardened within the range 700 HV to 850 HV Dimension in inches 11 12 13 L 81, Sheet and strip of aluminium-21/4 per cent magnesium alloy (three-quarter hard-H6) L 163, Specification for sheet and strip of aluminium-coated aluminium-copper-magnesium-silicon-manganese alloy (solution treated, cold worked for flattening and aged at room temperature) (Cu 4.4, Mg 0.5, Si 0.8, Mn 0.8) L 168, Specification for bars and extruded sections of aluminium-copper-magnesium-silicon-manganese alloy (solution treated and artificially aged) (not exceeding 200 mm diameter or minor sectional dimension) S 80, Specification for high chromium-nickel corrosion-resisting steel billets, bars, forgings and parts (880–1 080 MPa; limiting ruling section 100 mm) S 92, Carbon-manganese steel (suitable for welding) 0.093 0.125 0.125 0.125 0.125 0.062 0.062 0.093 0.093 in K S 95, 11/2 per cent nickel-chromium-molybdenum steel 0.1240 0.1500 0.1760 0.2020 0.2620 0.3245 0.3870 0.4495 0.5120 /8 /8 in /4 /4 /4 /4 1 0.373 0.406 0.448 0.490 0.531 /8 1/ 1/ 0.313 0.329 0.353 0.363 in 0.005 G in Drive fit J H S 112, Semi-free cutting carbon steel, bright bars for machining (primarily intended for the manufacture of nuts) S 113, “40” carbon steel bright bars for machining (primarily intended for the manufacture of nuts) S 114, Manganese-molybeenum steel S 117, per cent chromium steel S 137, Specification for high chromium-nickel corrosion-resisting steel bright bars (free machining) (880–1 080 MPa; limiting ruling section 70 mm) 0.375 0.425 0.475 0.550 0.600 1 11/4 11/4 13/8 /4 /4 1 16 in UNF in UNF in UNF 16 in UNF in UNF 0.300 0.310 0.380 0.530 0.610 0.220 0.250 0.300 0.325 0.140 0.160 0.190 0.215 1 1 /4 /4 3/ 3/ in in 0.015 0.015 D in in F B A Nominal size E No 4-40 UNC No 6-32 UNC No 8-32 UNC No 10-32 UNF Referred to in foreword only NOTE NOTE NOTE S 154, 21/2 per cent nickel-chromium-molybdenum steel billets, bars, forgings and parts (880–1 080 MPa: limiting ruling section 150 mm) S 510, Carbon steel sheet and strip (430–540 MN/m2) (suitable for welding) S 511, Deep drawing carbon steel sheet and strip (280–400 MN/m2) (suitable for welding) S 526, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (titanium stabilized: 54 hbar) S 527, Softened 18/10 chromium-nickel corrosion-resisting steel sheet and strip (niobium stabilized: 54 hbar) b) Ministry of Defence specifications AD 114, Design requirements, qualification approval tests and acceptance test for AGS 2000 series stiffnuts (BA and BSF threads)2) DEF 151, Anodizing of aluminium and aluminium alloys DEF 2331, Protective PX-1, dyed and undyed DEF STAN, 03-8 Electro-deposition of tin 2) iv 30 /4 /4 5/ 16 5/ 16 in in S 16 T 17 BS 2870, Rolled copper and copper alloys Sheet, strip and foil BS 2874, Copper and copper alloys Rods and sections (other than forging stock) BS 3488, Technical anhydrous lanolin A 102, Steel bolts (Unified hexagons and Unified threads) for aircraft A 104, Corrosion-resisting steel bolts (Unified hexagons and Unified threads) for aircraft A 169, Aluminium alloy bolts (Unified hexagons and Unified threads) for aircraft B 11, Brass bars suitable to be brazed or silver soldered L 80, Sheet and strip of aluminium-21/4 per cent magnesium alloy (soft-0) Table 18 — Acceptance gauge for ordinary and thin single-lug fixed anchor nuts (see Table 11) Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A 147 to 3A 168, 3A 180, 3A 181, 3A 186, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 216:1981+A1:2013 3A 187, 3A 192, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 © BSI BSI 2010 2010 © © The British Standards Institution 2013 Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The 8 3 21 in in Drive fit K 12 2 L 13 in M 14 DEF STAN, 03-9 Electro-deposition of silver DTD 10, High nickel copper alloy sheets and strips DTD 417, Lubricating oil, aircraft controls: anti-freezing DTD 904, Cadmium plating c) Society of British Aerospace Companies (SBAC) publication 3) RS 732, Manufacturers identification monograms for aerospace fasteners This publication does not purport to include all the necessary provisions of a contract Users are responsible for its correct application 4 4 16 16 32 32 8 0.093 0.125 0.294 0.356 0.500 0.500 0.400 8 3 0.093 0.093 in in 0.198 0.224 0.500 0.500 in in 0.400 0.400 4 3 in +0 –0.0002 +0 –0.0002 1.0 pitch 0.8 pitch 0.015 32 32 3 in 0.015 F E D C C B 16 16 3 in G All gauging surfaces to be hardened within the range 700 HV to 850 HV 8 1 in in Drive fit J H 10 11 Compliance with a British Standard does cannot confer immunity from legal obligations 2 11 11 in UNF 16 in UNF 11 11 No 8-32 UNC No 10-32 UNF in A Nominal size of attachment strip 2 3) Obtainable 0.015 Summary of pages This document comprises a front cover, an inside front cover, pages i to vi, pages to 31 and a back cover This standard has been updated (see copyright date) and may have had amendments incorporated This will be indicated in the amendment table on the inside front cover NOTE Table 19 — Acceptance gauge for attachment strips for ordinary and thin stripnuts (see Table 12) Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A 147 to 3A 3A 180, 3A 3A 186, 3A200, 193, 3A201, 200, 3A168, 201, to 181, 2A 216:1981 3A 193, 3A 3A 2A 213 to2A 2A213 216:1981+A1:2013 3A 187, 3A 192, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 from the Society of British Aerospace Companies, 29 King Street, St James’s, London, SW1 © BSI BSI 2010 © The 2010 British Standards Institution 2013 v 31 31 Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The Licensed Copy: Mr John Devaney, British Standards Institution, 27/07/2012 10:58, Uncontrolled Copy, (c) The British Standards Institution 2012 BS 3A 125 to 3A 132, 3A 136 to 3A 143, 3A 147 to 3A 168, 3A 180, 3A 181, 3A 186, 3A 187, 3A 192, 3A 193, 3A 200, 3A 201, 2A 213 to 2A 216:1981 +A1:2013 BSI — British Standards Institution BSI is the independent national body responsible for preparing British Standards It presents the UK view on standards in Europe and at the international level It is incorporated by Royal Charter Revisions British Standards are updated by amendment or revision Users of British Standards should make sure that they possess the latest amendments or editions It is the constant aim of BSI to improve the quality of our products and services We would be grateful if anyone finding an inaccuracy or ambiguity while using this British Standard would inform the Secretary of the technical committee responsible, the 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