agard report no.721 fatigue rated fastener systems · 5.2 corrdation of fatigue ... 14 comparison...
TRANSCRIPT
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AGARD REPORT No.721
Fatigue Rated Fastener Systems
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Appiovwd lot public «iea*«| Distribution Unlimited
DISTRIBUTION ANO AVAILABILITY ON BACK COVER
86 2 24 039
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AGARD-R-721
f
NORTH ATLANTIC TREATY ORGANIZATION
ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT
(ORGANISATION DU TRAITE DE L'ATLANTIQUE NORD)
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AGARD Report No.721
FATIGUE RATED FASTENER SYSTEMS
Edited by
H.H.van der Linden
This Report wa* vpon .t »red by the Structures arid Materials Panel of AGARD.
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THE MISSION OF AGARD
The mission of AGARD is to bring together the leading personalities of the NATO nations in the fields of science and technology relating to aerospace for the following purposes:
— Exchanging of scientific and technical information;
— Continuously stimulating advances in the aerospace sciences relevant to strengthening the common defence posture;
— Improving the co-operation among member nations in aerospace research and development;
— Providing scientific and technical advice and assistance to the Military Committee in the field of aerospace research and development (with particular regard to its military application);
— Rendering scientific and technical assistance, as requested, to other NATO bodies and to member nations in connection with research and development problems in the aerospace field;
— Providing assistance to member nations for the purpose of increasing their scientific and technical potential;
— Recommending effective ways for the member nations to use their research and development capabilities for the common benefit of the NATO community.
The highest authority within AGARD is the National Delegates Board consisting of officially appointed senior representatives from each member nation. The mission of AGARD is carried oui through the Panels which arc composed of experts appointed by the National Delegates, the Consultant and Exchange Programme and the Aerospace Applications Studies Programme. The results of AGARD work are reported to the member nations and the NATO Authorities through the AGARD scries of publications of which this is one.
Participation in AGARD activities is by invitation only and is normally limited to citizens of the NATO nations.
I he content of thi% publication lias been reproduced directly from material supplied by AGARD or the author
Published November I «85
'& i. Op) right C AGARD 1««5 All Rights Reserved
ISBN «Mitt-15124
I'nnied b\ Spc uili\*d I'rti.ung Vnitn / tmiifj 40I tugnrll IMIW, Litughtutt. ki*M Hi 10 Ml
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PREFACE
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In recent years, the SNIP has placed considerable emphasis on cooperative R&D programmes, especially where there are several variables to consider and where several identical tests must be made to evaluate the scatter in the results. Fatigue and corrosion tests lend themselves particularly well to this treatment, since one laboratory working on its own could spend a vast amount of time and money in deriving all the requisite data before any analysis of the res ills could be undertaken. By inviting the participation of several laboratories (even though these may be in separate countries), the work can proceed in parallel, thus reducing the total elapsed time. Moreover, each participant can reap the benefits of the whole programme for a small outlay.
Successful ventures in recent years include the Critically-Loaded Holes Programme and the Corrosion Fatigue Cooperative Testing Programme. This report presents the findings of the latest cooperative programme to be completed — an evaluation of Fatigue-Rated Fastener Systems.
Despite the advent of adhesives. composite materials, integrally-machined components and diffusion bonding, mechanical fasteners arc still the most common means of joining parts together in the aerospace industry, and will remain so fcr many years to come. The designer needs to know which fastener systems are the most ef Icicnt, and this programme studied a number of systems from the fatigue point of view. In this context, 'system' means not only the fastener itself, but also the way in which the hole is prepared and the fit of the fastener in the hole.
The thanks of the Panel arc due to the collaborating laboratories and especially to the Coordinator, Mr H. II. van der Linden, who was responsible not only for organising the programme but also for much of the analysis and the preparation of this report.
W.G.HEATH Chairman, Working Group on Fatigue-Rated Fastener Systems
Acce-Jon For
NTI3 CRA&I DTIC TAB U a tnou:tetd J.-titiGltiOri
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By Oit ib'jtto./
Availability Codes
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CONTENTS
PREFACE
SUMMARY
1. INTRODUCTION
2. OBJECTIVES, METHODS AND MEANS
3. PROGRAMME OVERVIEW 3.1 No-load transfer joints 3.2 Low load transfer joints 3.3 High load transfer doublt shear joints 3.4 High load transfer single shear joints
3.4.1 Background of the single shear designs 3.4.2 Core programme
3.5 Assess to all details
4. TEST PROCEDURES 4.1 Measurement of load transfer and secondary bending
4.1.1 Secondary bending 4.1.2 Load transfer
4.2 Data recording
5. SPECTRA 5.1 The manoeuvre spectrum FALS f/AFF —MCT 5.2 The standard load sconces for transport aircra* wings TWIST and MINI TWISI
5.3 Constant amplitude loading
6. METHODS FOR ANALYSING THE FRFS PROGRAMME DATA
7. RESULTS OF THE FATIGUE R TED FASTENER SYSTEMS TESTING PROGRAMME 7.1 Presentation of fatigue life data 7.2 Results of the measurements of secondary bending and load «ransfer
7.2.1 Reverse double dogbone specimen 7.2.2 Core programme »ingle shear joints 7.2.3 Care programme double shear joints
7.3 Measured fit and surface roughness 7.4 Cost of fastener systems 7.5 Locations of primary fatigue crack origins
I. CORRELATION ANALYSIS 1.1 Correlation of fatigue lives of open bole specimen and no load Iransirr joints 5.2 Corrdation of fatigue «ves of no load and lo« load transfer joints g J Lo« <o*d transfer joints fatigue life tnaly sis results 14 Comparison of UK and AGARD low toad transfer joint design t.5 Correlation of fatigue »ves of double shear and lo« load transfer joints g.» Doutne shrar joint» fatigue life analysis results
8.6.1 Pa?lkipanis programmes «.6.2 Core programme
8.7 Sftjdj shear joint fatigue life analysis result« 8.7.1 ParticipaiK* programme» 1.7.2 Cart ptugraavn*
• .1 Correlation of fatigue lives aud cost of fastener »vstcn»
9. DISCUSSION 9.J DclCftUHVBlkK»of!»tiCUclMO
9.2 evaluation of the fastener gjfffJM configure» 9.3 Prime pammrtm in fastener «ystrm «election 9.4 Design data 9.5 Reference datum 9.* ksprriwrnUl method»
It. CONCLUSIONS
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II. REFERENCES
TABLES
FIGURES
ANNEX 1: AGARD SMP WORKING GROUP ON FATIGUE RATED FASTENER SYSTEMS
ANNEX 2: FASTENER SYSTEMS
ANNEX 3: MEASUREMENT OF FIT AND SURFACE ROUGHNESS 52
ANNEX 4: DETERMINATION OF SECONDARY SENDING AND LOAD TRANSFER 54
ANNEX 5: RESULTS OF THE MEASUREMENTS OF SECONDARY BENDING AND LOAD TRANSFER 59
ANNEX 6: TABULAR PRESENTATION OF FATIGUE LIFE DATA 74
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— FATIGUE RATED FASTENER SYSTEMS
-AN AGARD COORDINATED TESTING PROCRAMME-
by H.H. van der Linden
National Aerospace Laboratory NLR Anthony Fokkerweg 2 1059 CM Amsterdam The Netherlands
SUMMARY
This final technical report contains the description, test results, analysis and conclusions of a coll.Sor.tive fatigue test programme which assessed the fatlpue live- of a range of f.sten.r system, using
f^VhSVoVd'ÄS single shear joint de.ign. «ere ev.lu.ted and compared f an extensive core
programme; .econdary bending and lo.d tr.n.f.r were determined experimentally. PM1Btrl.. Th. Between seven and eight hundred specimens were fatigue tested by participants in seven countries The fatlaue te.t. were c.rried out mainly under FALSTAFF; aome test series were done under MINI-TWIST and onitänt amplitude loading. Th. sheet «t.ri.l. us.d were fro« th. 2000- and 7000- alumlnlu, .lloy wit*. Z Um ranged fro« .t.nd.rd bolt, to tapered fastener., installed in holes which were drill.d.
T1£t•t*Z"tl£%i'•ij*l. -Chod .nd ,r.phic.l method, were used to corre!£»-->»£ to find trend, .»ong the variables. In additional the co.t figur.. w.r. related with the f.tlgue p.rfor-
mance.
The ACARD coordinated Fatigue Rated Fastener Systems programme not only identified the prime para-
meters in fautener system selection but also quantitatively evaluated these.
HlxhlUhts of the data Indicate that: _„m#„ . secondary bending proov.d to be a prim, parameter. At moderate to high values it tend, to nullify
the beneficial effect of fatigue enhancement fastener system.; . .t low to moderate secondary bending (or at the ab.ence of it) th. it cl.mplng and cold work are
Jri». parameters. At high lo.d tr.n.f.r and at high f.tlgu. lo.d level, th. be.t results ar, obtained
with cold worked hole, plus high Interference fit fasteners; • double shear Joints clearly show a fa.tener system rating; • the hole quality a. such is not a prime parameter. However, dimensioning to llM to obt.ln a close
tol.r.me fit results in holes with good fatigue quality; . incr...ing co.t. of th. f..ten.r system might result in a better f.tlgue performs. Moderate to
high .econdary bending tend, tc nullify th« extra co.t» of f.tlgu. enhancement fastener system. The conclusion, of th. report present a co.t effectivene.s rating of deferent fastener systems applied in
double shear and low load tumfer Joint.
1. INTRODUCTION
The application of shear loaded fastener systems with known or advertised good fatigue performance Is easing considerably, both in new aircraft designs and in modification, of older ones. This Increase In
,.,. It accompanied by an Increase in research and development. The Structure, ard Materials Panel of the Advisory Croup for Aerospace Research and Development (ACARD) recognised this Mid appointed working groups to carry out collaborative fatigue test programmes o., fatigue rated fastener systems In aluminium alloy
Increa use
structural joints.
A first programme, the Critically Loaded Hole Technology MlM Collaborative Test Programme (reference 1). wa. carried out in the period October 1976 up to October 197» in wh«eh open hole and low load transfer Joint specimen, were fatigue te.t.d under FALSTAFF fllght-by-flight loading. The re.ult. can be summarised as follows: • con.l.lent fatigue or. can be generated In complex fatigue testing hetwes.» the participants; • interference fit fa.tener systems «re relatively Insensitive to effects of hole quality; • valuable design data was generated on low load transfer joints.
After completion of (he Critically Loaded Hole Technology P'lot Collaborative Test .'regramm« a follow- un programme wa. defined In 1979: the Fatigue Rated F* atener System* IFKFS) programme, coordinated by the author of the present paper. ..... Til* FRFS programs« assessed the fatigue live* of a range of fasten«! ay.tee* using different Joint teat specimens, in addition the co.t figures were rt lated with the fatigue p«r!\rm*nce. t. ,efere.,ce jlalum !*r th« comparison of test results produced In different «ountrlea was establUhed by *=»«» of core program- ... Result* were analyse* ay the Air Force Flight Dynamics Laboratory CWA) and th« National Aerospace Laboratory. NU (The Nether land.). This ACARD Report describes the FRrt pro,.amme and presents the results ui analy.i*.
j. autetiitt. Ktruoos AND H*A»S
The objective, of (he i-ooperaiivr programme were: ... • to determine the fatigue lives for a rann« »« fatigue rated fastener *ye:ema In different materials in
combination with a selection of hole preparation techniques and In.ta.Uatio« parameters; • to establish the co.t figure, oi each faateeer «yater. Ja relatio* i» Us fatigue performance; • i» identify the prim* parameter, involved in fa«*«*» Jfttm seiet:lea; • to generate de.tgn data for a number of fastener system«; • to develop a reference datum for the comparison of te.t reacts prodwe.d in different countries using
different specimen geometries; • to develop experimental method, for fa.tener sy.tem fatigue rat lag.
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,t„M. n A, a fir« step each participant defined his Seven countries participated in ^VW~«£*£ Vhi, munition specified plat, material, thick-
own programme, which could be active, f*"^* ^gS hole production tooling, fastener type, fastener ne^s surface treatment, lnterfay surface sealant, final now P ^ for««d a total matrix of ^"'fatigue loading programmes and load Uwlt. t* F*«^\^ *J\^imm geometry, were adjusted to e. ing variables. Elements of the ».«lK. I« JjjMJJJ ^"^ tion. Fur
Plher. a „umber of additional pro-
Tive ^V^/^^Z:^^n^o^U0n of results produced in different countries
TlnTnot completely identical specimen designs.
For clarity the FRFS programme was split up in four parts:
. No load transfer jolncs (NLT). • Low load transfer Joints (LLT). • Double shear Joints (DS).
during fastener installation.
TWIST and under constant amplitude loading, reported on an special form.
Fatigue live, were evaluated in terms of: . fastener system, fit and hole quality;
iSI-«--.<•*<»> —• «•- - ""•'•" "•"'""d l0 "°a"*"""-
manufactured fro» one mater lal. ».«.«, and fit) were selected and defined; the third arss r-aarJsr ssssu.-ss.tu. M - — - specified.
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3. PROGRAMME OVERVIEW
M originally envisaged the • '/^^^"^ requirements " »•"'l*-1 ^2»L Ä «S characteristic specimen «-I... !• M—«•- ln
stews si5?^-srttrB s...««•**-«• 1.1 Hu-load transfer Wnts — *" v. . T«.- I.-,''T fastener mounts » small non
TH. «.-load transfer specie« ha- a continue-**"-?£ ?„ £^ and secondary biding I. load carrying pUt. to the dogbone (figure la b). ^J^^-i«.. „„„ rating as for other type, of
of fastener systems.
1 > tow l^ai transfer lojyd» ,, , . ,
L ZTT— rasa asassuu sswa: s &rS •tf. Technology *•**-• In I*-« **^JE%*EmE*lm S- transfer ,««-« «-«*U i-**-.J »-
SS Ä«S. I« ape,o.i-«cly I * •*• SJ^JliJSlJ allow ^.1^ N — I» •*«•[-; „„1. .tt*h* to spars. Ut eaaa*le. A »W »Wg"~ „Malm.« by the other participants. Hole «ha« K, g* deviating «^Mj.. IfJgJ JJ^-J ^ ^_ beBan.
1 I "t> '»«* "»»•«>' ***U "h*'tr 3>>'*"
—ZZTZ....... -——' r;s. !i^rLr.i«*^^--'%•"»"•
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jjA High load transfer single shear joint«
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Single shear Joints are exposed to secondary bending caused by asymmetric eccentricities of the load carrying members. The amount of bending depends strongly on the Joint geometry. It Is generally recognised that differences In fastener systems tend to be overshadowed by excessive bending. Representation of a realistic bending situation by individual participants resulted in a number of different specimen geo- metries. These were evaluated under a range of variables directed to the requirements of individual parti- cipants (table 6).
3.4.1 Background of the single shear designs
Four designs will be described (figures 7 to II): e lap Joint, a three row-type (F) and a two row-type (US); e X-type Joint (SH); e Q Joint (UK); * IS dogbone specimen.
Lap Joints are used in an aircraft structure only if a double strap can not be applied. This type has a very high bending stress, which is in the order of the axial stress component. At least two fastener rows are present. In a two r ,w lap Joint the load transfer per row is 50 X of the total load. The load transfer decreases somewhat when three rows will be present. Due to the high bending and high load transfer this Joint is the most fatigue critical one, i.e. it will give the shortest fatigue lives. One might argue that this specimen Is unreallsclcly severe because in the aircraft structure the bending Is reduced by the support of other structural elements, e.g. stringers or ribs. Nevertheless, the fatigue data generated using the lap Joints are used as one of the extreme data sets in between which a designer Inter- polates to obtain fatigue life estimates for his Joint configuration. The US lap Joint specimen (figure 8) is a standard one of MIL-STD-1312 (Method t>, 15 December 1977).
The IS dogbone specimen might be considered as a standard one within the ACARD community: it Is used In the corrosion fatigue testing programmes CFCTP (Corrosion Fatigue Cooperative Testing Programme) and FACT (Fatigue In Aircraft Corrosion Testing). The specimen simulates the load transfer and secondary bend- ing characteristics of runouts of stiffeners attached to the outer skin, and was developed by the Labora- torium für Betriebsfestigkeit (I.BF) in West Germany. The design goals were a load transfer of 40 X and a seconJary bending ratio of 0.50 (figure 11). However, an Investigation (reference 2) suggested that In this type of specimen the load transferred was unrepresentatlvely low and dependent upon tie type of fastener Installed. Further, reference 1 shows a relatively low load transfer and lndicatea a fastener fit dependence. The compression limit load la about - 10 W, i.e. a specimen without ant 1-bucklir.g guides will not buckle when compression loads do not exceed - 10 kN. The (bolted) grips and clamplng-ln procedure are well documented(reference 4 ).
In the UK an alternative specimen was designed (reference 51 that attempts to alleviate some of the problems associated with e.g. the IS dogbone joint. The alternative dealvn. -he q Joint (flgur,- 10). is based on a single lap joint, but the addition of a further load carrying member controls bend ng by providing extra late.-al stiffness. Further, the double shear connection at the second fastener row ensures that fatigue failures do occur at the single shear connection.
The advantage over the IS dogbone lies In the faet that It la a 100 Z load transfer joint. In the IS dog- bone the load can by-pas. the fastener In a clearance condition before load la transferred in bearing. In the q joint the slitter double shear connection might be expected to transfer mure load than the single shear TUI; thus, a load transfer somewhat Lr*f*f than 50 X la expected. Initial testing (reference 5) suggested rhat the bending rail» is approximately 0.5; this ratio may de- crease to a value nearer 10 0.4 under dynamic loading conditions. A disadvantage la that the q joint la more complicated and ilms mure expensive Hum the IS dogbone.
The X lype (figure v) is a Swedish development. It la a two row Joint because a known load tranafer. independent of the Ivp* of fastener, may »e obtained with a maximum of two rows. The design has splice plate areas equal to the base plate areas, implying a theoretical 50 X load transfer per row and indepen- dent of fastener ttiffeaees. The splice p ate centres of gravity coincide with the baae plate centre of 6eavlty, lmp.ying teru gross exceatrtclly and no major secondary bending. tompa-,.'. to other splice plate configurations (reference b) the X type had Ihe moat unllorm load transfer distribution over the fasteuera rurther. the splice plate stiffening effect is very local.
1.4.2 Cure programme
Primary objective of the core ptograime was to evaluate and compare different designs In use In the participating institutes and companies. To obtain an tmprea.iou of the lnfluei.ee of bending on the fatigue life, ao called "double sheaf equivalent »|l«Ct—M* Were derived from the »Ingle .heat ones (figure. a. 11. II] In which the asymmetric aide sheet of the »Ingle shear design w*. replaced by two symmetrically placed • ide sheet, each having half the ihleknes. of the original one. Tfce double .he.f feature exclude. secaJarv bending.
However, load transfer might net have been completely Mont teal in the two de.tgas because of changed la. tenet tilt and beading character 1st !:• and the prc.eece of two locations of {fictional toad transfer In.tead or one.
table J. which reviews the core programme, .now. as an «sample, the IS dogton. specimen and lt. doubl« .hear equivalent de.lgn.
All specimens In the core prograe*.. namely all .Ingle and double .teat design., were manufactured rrom one material, i.e. the 5 mm thick Joio-T?» cote programme material, which was tur-tished b, the vs. Surface treatment. Interlay sealant, load level, and load spectrum were .peclfled (Anne« 1). two Ustener ay.terns Were .elected a-uj specified (Annen J): • Fastener .yst.m A: a counter.uuk Bl-..uk Installed with clearance fit In a reamed hole (FKTi-A). • Fastener svete« I: a Counter.unk lll-Lok Installed with t?tetf,fcuce ill In a cold worked and reamed
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hole (FRFS-B). A third, optional, fastener system was defined because of completeness; this fastener system also had a
countersink Hl-luk but It was Installed with high Interference in a reamed hole.
All core programs« specimens then were fatigue tested to failure under FALSTAFF /light simulation loading. As in the other programmes, fit and aurface roughness were measured during fastener installation (Annex 3). In addition to the fatigue tests, one specimen of each combination of specimen design and fastener system was instrumented with strain gauges to measure load transfer and secondary bending.
3.5 Assess to all details
The programme overview showed that various Joint geometries were used to evaluate different materials,
bolts, fastener systems, etc.
The tables refer to: e figures 1-12 for specimen configuration details; • table 8 for the nechanlcal properties of materials; • table 9 for the faying surface treatment details; • table 10 for the fastener systems. It should be noted that the presentation of application and manufacturing Instructions la beyond th* scope
of this report.
4. TEST PROCEDURES
The stress levels are given as gross area stress, ui.less otherwise Indicated. Guidelines for tearing have not been given since the Critically Loaded Hole Technology programme (reference 1) showed that: e th* participating laboratories could apply spectrum loads satisfactorily; • there was the ability to generate consistent data in complex fatigue testing between the participants; • all the data generated at different laboratories were accepted by all participants.
4.1 Measurement of load transfer and secondary bei....>»
Based upon the procedures of the I.BF (FRO and upon experience of SAAII-SCANlA and KFA (SW). RAE (UK) and the NLR (NL) standard procedures were developed (references 7, 8); these procedures are alao given lr.
Annex 4.
Each single shear Joint was Instrumented with a large number of strain gauges to determine the 1'iad transfer and secondary bending. Load transfer was also measured on the double shear equivalent »specimens
of the single shear core programme.
4.1.1 Secondary bending
Secondary bending la of Interest at the fatigue critical cross section. Usually a crack started at a hole or at the faying surface close lo a hole. The location of erack Initiation was not accessible In most cases, so a neighbouring position was chosen for the measurement. The conventions adapted by the working group are given in figure 13. Jarfall (reference ») showed that displacement of the strain gauge by »/» of a fastener diameter In the transverse direction changed the secondary bendlag by not more than I to I X; so the accuia-v of positioning In transfer direction was not toe critical. Positioning In the axial direction required a hlghe« acci-racy since the strain gradient was very sleep: for a point at the same distance on tSe ofpuaile side of .fte fastener the secondary bending «= ol (he same order of magnitude but of reversed sign. Jarfall (reference *) confirmed this using measurements on X type Joints.
4.1. •? Lt^d transfer
• v definition (he loggl transfer la the percentage of (be lotal load tranafe-fed at a particular point of :•--..! transfer. The by-pass load (flguie 11) was thus mrseured aft of each fastener row. Keaauicaentfc by Eriksson and Magnussen (reference 10) showed that (he strain distribution aft of the fastener row Is not uniform; therefore, a row ot strain gauges was bonded to allow Integration over the stenbei width. In older lo »misuse ihe number ot attain gauges, aXtaia gauge» were bonded only al maxima and minima of ihe strain distribution. further, the gauges wete locatnd at equal distances (In ifee load direction) from points of load transfer. tne distance between two fastener rows was usually 4 fa.teuer diameters; (bus (fee gauge. Were bonded at 2 diameter afl of Ihe faalencl row. Also attain gauges Were bonded a! feolh aide, of the attest lo dele.mine (he aslal strain (figure U). which was uacd for (he de(ermtna( ion of ihe by-paas load.
ttaia recording
Individual data .heel, wele completed for aaeh a»e. la-n: • :,e Eci-.aitacr.1.: of fit and .-.--'. Ii. c iuu|lu»ii nie rccaldcd on the mala .Heel i.iw.c. "-':; an esample of the leet data sheet, of ijtnat leg from the IX. Is given In (able ll; the di-la Sheet fof repelling the load fianatet and Secondary bending measurement a. ace Annes *.
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5. SPECTRA
r..„:.>. says rursj: a?-rs,-ss, äV."""' u-d'- s•"d F
- U Th« manoeuvre »pact rum FAI.STAFF
TM essential properties may be «unrasrixed as follows:
' mnwSr**" * ,0*d '•',u•nc•, drflMd by *uec'"lv' *•*" "nd t,,rou»h'' -**m • ""«*" .f ThU block alt« conform, with .v.r.,. aoropa.r. annual flght.r utlll.atlon.
..r co-bao and ni.bc. *,* A; ,u SiSESÄÄi cJyLSÄSJlX^ (e-8-
• Ä^ssirriSÄ si.!"-cycu-Th- -jority ,,f "*•• • i°*d •**••- ' ^eÄta FA,'STAFF T"M con'1"* °' "9" nuBbcr-- "Hi«l fro. . to 32.
tu-pi.i« r.JKTRAN listing of th« program to generate FAI.STAFF.
' ^r2!o•Xm^'i::rnx°*'to " are Arbirrary ••*•• •—•" ••—••-»«,. ,„„,
.iMr.d .. th. one „ceded one. pP, ,,mVrel I ifgh,* § " ( ,runca,lon ,e"*>"> «"••
« <M Mghe.t l„. lev.. I. the spectrum. •„ ,„,, repiirt S?JJ SüÄtoÄ. "" •"»•ri~M
i-L^ä-iiaatea tsri aaasssM ««* mams gjfgiH am TWIST ^Nm;^
-., AAS Ät^srajsjÄsaTrrsatsia srsv." - - "• fcrcnt flight..
f
There .re ten differ*«, flight typ... raof.Ua früB M«, (A) fu ,«.„ ,.1 ,.^.rf«,, „ , occurrence ,| e4th tUgn lype and u£ cach B « -«tMr=.ch ,yee ur , , M na' '-««-«"F •»
",U"" * *•* *»1"- »-" '»«-. «-1« >"..«!.• 3 the TrlJce .cVelc.^re CRJ f!1"-ta ^ "*"
• Tfce flight. M. u.aa far each Jlighi .,c applud l„ a faBdlM, . ,. «verr fllghia la a«i «Howe*. " "",d'H* !";'il«B« ""ept (Ml «lu.l.rlng of
• SÄWa ;'^i^/.''.i;;J.-",-r^,;::r^.r^.''-''" - - • - h.Vc . dlffcent U«4 „,«„«. ' ' **** "MN. thua UlgMa o! «(« ,aBc |yf, gcucr.lt,
TM poaill.H.a Of |he actclcst f 1 ' .hi I •« Tuf« ^. . ltl, , («mo. e IW1ST fl,c: 14i6 »«»• *J« **» <typ* i)i wi. .-»ift .«ui mi The higher Uad „, be lÄrl-fc- lh
.ppr«,^,e,y ,„ ltma „, alftfaft U|# uf w# JJJ 4üoo JJ^J"" « '* »^ I«-« U c.cCc,
Tie ».it. differ.«!« be.»„« TV1ST «d NIKt-Twtst la ttL.t .1^ !-,. .
TM ^.««tc.iatl, ...... le«l ia .he *eiB ..,„. U.cl |* fU*h«. i mi'
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6. METHODS FOR ANALYSING THE FRFS PROGRAMME DATA
A st.tlstlcsi analysis of UM FRFS program». Uta ha* b..n c.rri.d out by Mr. I.M. Pott.r, Air Fore. Wright Atron.utlc.1 Labor.torl... Dayton. Ohio, USA. It w.. a..um.d that aach participant of h. FRFS program», would uaa adäquat* .tatiatlcal mathodology within th* portion of tha program for which thay
Th. NoVthmat Analytical STATPAK aoftwart waa u.ac1 to p.rfor« tha atatiatlcal analyaaa. Tha analyala methodology uaad waa that of multiple llnaar ragraaalon. Thia Mthodology *»aa choaan alnca It la uaaful whara th.re exiata more than ona component affactlng tha parfonaanca of a product. In tha FRFS program», th. fatlgua life la a product of a.v.ral p.ramatara (a.g. apactaan daalgn. atr.aa. faatan.r typ.. MMUl, lntarfaranca. intarfay traataant. hola quality) whoaa intaractlona ara not «p.clfically d.fln.d. Th. FRFS program coa^ounda tha probl*» by adding tha varlablaa of differing taat organlaatlona and manufacturing procaaaaa to raault In a final raport which haa numerous intrinsic variation*.
Multiple llnaar ragraaalon approachaa aasum* that two or »ore varlablaa ara related to each other
with an aquation of tha form given In equation 6.1.
Y • BO + II * XI + 12 • X2 • B3 * X3 + .. • XN (6.1)
where Y 1* the dependent variable and the X'a are the independent varlablaa and the B a are the coeffl- ci«utr which are calculated in the rejreaalon proce.s. Th. STATPAK program* assume that there la no alf.nl- flcant interaction b.twe.n the independent varlablaa and that each variable contrlbutea approximately
equally tu the regression, , As a completion of the statistical analyel« the following correlatlona were made graphically, a open hoi. Joints vs no load transfer Joint»; • no load tranafer Joints "a lov load transfer Joints; • low load transfer Joint* vs double shear Joints; e aecondary bending va fatigue life; e load tranafer vs fatigue life; • fatigue performance vs cost.
7. RESULTS OF THE FATIGUE RATED FASTENER SYSTEMS TESTING PROCRAMMF.
7.1 Presentation of fatigue life data
The conpl.t« set of fatigue Ufa oata for the FRFS programs» 1* given In the tablea 6-1 to 6-21 of Annex 6; the framed number* are the log mean Ufa figure«. The fatigue life data are plotted .'n figure* 17 to 41 Inclusive per participant and test schedule. A». 1 stresses are gruas area stresses, unless otherwise Indicated.
7.2 Reaulta of the measurements of secondary bending and load transfer
Secondary bending and load transfer have been deter.l-.-d on reverse double dogbone specimen, tha .Ingle shear and double shear core programme specimens using standard Instrumentation and procedures Full letalls of the measurements are given in Annex 5. which alao presents the secondary bending and load tranafer as function of applied load. Table 11 at the fatigue teat stress levels.
aria«*, the values of secondary bending and load tranafer
The following deviations from the standard procedures and InstrumenlalIon were observed: the French type D double shear Joint had broached Instead of reamed holes; since the fit waa within the specified range, this should not influence (he results; the US type C2 lap Joint was not Instrumented according to the r«FS requirements: the secondary bending gauges were located too far from the fastener«. Therefore, a bendln, value «as recorded which was too l»w Further, contrary to Its condition du.lag the fatigue (eating the »peclmen had no bending restraint during the measurements. No luad transfer gauge, were applied; the load transfer I* estimated to be close to iO t because the «peclmen Is a two row joint; the double «hear equivalent de«tgf. of type « (USA) had aide «heel« which had twice the thickness as ws. specified. Moreover, the load transfer gauge» were bonded only at the locations giving the lowest «esp«/a«e, I.e. directly behind the fastener: tho .urface (rea(ment of (he French core program «peel«*« had only enosy paint a« surface (rea(men(
l««(ead of primer * KWtaati (he Swedish X Joint« Were provided with uversl'sd holes.
7.2.1 Reverse daub I* dogbone specimen
A* an addition to the programme France Instrument-d and tested rever.e double dogbone .peclmen«. one .el being tt.de of 2024 and one o* 7074. each containing two Ml-loa« mounted with high Interference In reamed holes, fccau.e this fastener system (and la particular the fit) were not the «ome a. the cor. programme taetener .ystema (FtrS-A and -B) the teaulis of the mea.urement. cannot be compared directly with (he te.ult. of the core programme mea»uremen(«. Nevertheless, lb. results «how lntere.ttng trend». There I« a large dlfreienc. In «econdar* bending and load tr.n.fei behaviour hetwen (h. 2024- and .074-aUey .p«tlas.a«. Secondary bending end load transfer -re higher for the 2024-alley «peclmen: the aecondary heading ratio of .2» might be considered as a very high value lor (hi« Joint type. It Is meted here that the clamping procedure 1« crucial when u.lng wedg« itpe grip«; exploratory teafa at WJl showed that load tranafer might ev*a rev«r.e If no «pedal precaution« were taken. It t« essenlLl t» present relative motion of the two dogbone« at «He typical end* <.:,*, «lamming in. The .olullon use.« at «U 1« given In figure i-'. e.raswy u.ed a pin loaded hole solution, figure 2b.
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7.2.2 Core programme single shear joints
The effect of applied load on secondary bending 1» large for lap Joint type specimen. A more moderate effect is observed on the Q type. Th same classification applies to the effect of the fastener system on the secondary bending. A remarkably low bending Is observed at the FRFS-A (clearance fit) 1*5 dogbone specimen. The latter type shows more clearly the effect of the fastener system. In general the load trans- fer is less affected by the applied stress. Further, the influence of the fastener system on the load transfer variation is small for the lap Joint and \H dogbone, and very small for the Q type Joint. No secondary bending and load transfer measurements are available for X type Joints with FRFS-A and -B. For reasons mentioned in 3.4.1 the load transfer is 50 X and is independent of the fit. The secondary bending ratio, determined in another programme, is about 0.S0.
7.2. Core programme double shear joints
The Cl and D types show a negligible dependence of load transfer on the applied stres« level. In both types the first fastener row, i.e. the first row where load is transferred from the base to the side sheets, has the highest load transfer, while the one or two fastener rows in the middle contribute only a little to the load transfer. The locations of highest load transfer coirespond with the failure initiation situs. The change from a clearance fit to an interference fit results in an increase in end row load transfer and a decrease in load transfer in the middle fastener row(s). No load transfer measurements were made on type M , M and H.. The last is a two row Joint i.e. it has a load transfer of 50 X whilst the load transfer of
M . M, Is estimated So be about 20 X.
l.j Measured fit and surface roughness
The tables that present the f tigue life data, see Annex 6, give characr^ristlc values of applied fit, either as an average value or as a range. The programme called for the measu ement of fit and hole sur.'ace roughness. Some participants limited their efforts to the measurement of the diameter of a satp!« of the fasteners and holes. The participants will report in detail on the measurements made. Hole surfaces rough- ness measurements were only made by two pa.ticipants and are therefore not presented.
I
7.4 Cost of faBtener system»
The cost of fastener systems consists of: • equipment and tcols; • purchase cost, which depends on fastener type, fastener material and nuasber of fasteners ordered; • preparation of tooling, sealant etc.; • installation:
- positioning of tool - predrlll - clamp - drill
deburr inspection of hole
- application of sealant/primer In hole Installation of fastener Inspection of fastener.
Table 14 reviews available information; cost are transposed into US dollars. The purchase cos. per fastener drop sharply when the number of purchased pieces Increases; for some fastener syscems this is illustrated in figure 44. The relative cost of fastener systems can be compared using table 15. A compre- hensive cost comparison can not be made because the total expenses should include not only the total direct costs SUCH as fastener purchase cost and manhours for Installation, but also writing off of equipment, cost of tooling, manhours tor preparation, etc. The latter three cost elements can not be given as cost per fastcnei Installation because the Information necessary for this depends on the number of fasteners per compouent. total number ol exponents etc. For illustration figures 45-46 detail 'he contribution of some cost elements that contribute to the total installation expenses. Evaluation of the costs el ditfeient fastener systems is vety dlffl> First, the participants' da' n the same taatener system deviate widely, as Illustrated by the tapeflok system data. Nevei t heless. hi« is the must time cotisumlng fastener system. S'ieclal precautions should be taken to ensure that the m.-.ture is securely clamped together. Checking the hole for Seating area is a time consuming but essential Operation. All operations must be closely controlled and carried out by skilled personnel. The cost of this tapere.' fastener is high, but the cost of equipment and tools does not ;XCee«' that of standard fasteners. These costs are l.igh for the equipment for cold work piocejses of which the sp I sleeve 1 = the most time consuming. This la caused by the need to remove the sleeve and ream tu *Ue. It is noted that reaming and counters Inking after the actual cold work process is not necessary any mure l* s new version of this culd work system.
/'.5 i-uca'ioiis of primary fatigue crack origins
The programme description required the evaluation of fatigue lives lion site». Halfway through the programme all participants were requested to the XL*. !l was 'he intention to examine and I« determine the tatigu
terms of fatigue crack initia- i send fractured specimen halves rack origliiD at a single source
Id not be achieved up to the lu l ne .^(.R. II wan "lie .:;cui ,uu w Kj.3v4.tc »*•«* v" wf,ii.w ...» - .' • - t •* » •—v » *-..£..... w« — «...fc.» w^w.«»
followed by the classification of the crack origins. However, this goal could not be achieved up to the moment the report was written. Fortunately, some participants identified and reported the primary fatigue crack origins themselves.
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8. CORRELATION ANALYSIS
8.1 Correlation of fatigue lives of open hole specimen and no load transfer Joints
Figure 17 presents the open hole specimen and NLT Joint fatigue life data for the 2024 and 7010 alloys. Both specimen types do not end up with the same fatigue lives; the NLT Joint gives the longer lives, except for the 7010 alloy In the lower stress level region. Further, the 7010 and 2024 alloy results, for each specimen type, arc relatively close, but again with above exception. The results show that the presence of a transition fit fastener tends to give better fatigue lives compared to the open hole situation.
8.2 Correlation of fatigue lives of no load and low load transfer joints
Fatigue test data of both designs are available only for 2024 aad 7050 specimens having an interfer- ence fit Lockbolt fastener system (figure 47). The 7050 results are very promising; the flops is the same for both designs, while the low load transfer Join'.s have a somewhat shorter fatigue life. The lives of the 2024 alloy specimen tested at the unreallstlcly highest stress level are short. At the lower stress levels the slope is never the sam» for the two Joints. But the general picture is, for both materials, that there Is no significant difference In trends between the no load transfer and low load transfer Joints. The statistical analysis indicates that a possibility exists that the no load transfer specimens could be substituted for the low load transfer Joints to evaluate fastener systems. The likelihood of the same fastener rating being observed In both specimen designs cannot be considered on the basis of the present results. It can only be concluded that the results point towards similar trends of the effect of stress level on the fatigue life.
8.3 Low load transfer joints fatigue life analysis results
The statistical analysis was limited to those specimens where the holes were not cold worked prior to fastener Installation. A cold working Independent variable would be possible but the data packages received did not contain the cold hole expansion measurements.
The data were analysed with the only variables which had specific quantification associated with them; they were (1) fatigue life, (2) applied stress and (3) fastener Interference. The effect o learning com- pared with drilling of the fastener hole was analysed separately in the c<«se of the 7000 lea aluminium specimens. The fastener Interference was given as a positive number If there was interference between the pin and the hole; if there was clearance the Interference was assumed to be zero for purposes of this analyses. In those cases where a range of Interferences was specified, the mean of the range was assumed. All material results were considered as a part of either a 2000 or a 7000 series aluminium pool.
The multiple linear regression analysis results are given in equations 8.1 anv 8.2 for the reverse double dogbone 7000 and 2000 series aluminium alloy specimens, respectively.
N - 10 A (5.734 - (0.006127)*Stress • (0.00364)*Interference)
N - 10 A (7.0";5 - (0.013322)*Stress + (0.02210)*Interferenc«)
where
(8.1)
(8.2)
N - fatigue life in flights (1AI.STAFF) Stress • maximum spectrum stress, t fa Interference • difference between fasten«, and hole size, ,c
The equations make Bsnse in that the higher the «tress, the shorter the fatigue life and the higher the Interference the longer the life, ..:. many InvestlgatIons have confirmed qualitatively. The equations ti leate that, for the range ot data Investigated, the 7000 series alloys have a longer fatigue life and h..ve a steeper slope relative to the «fleet of stress than the 2000 series aluminium. At zero interference the crossover where the 7000 series becum~s shorter lived Is at a strcsa af 180.9 Mfa and a life of 42250 flights.
A review if the data Indicates an Interesting trend tn the effect of interference on fatigue perform-
ance. The coef fie lent a of the 2000 series data are a factor of six greater than those of 7000 materials. It may be an unfair comparison since the majority of the .'000 ,-oupons were manufactured within the lange of 15 to 40 »• Interference with only (he USA specimens at zero cl.-aranee (prior to rlvettlng) for two typea of aluminium rlvrta which arc themselves not eorildeied to be high-performance, fallKue rated fasteners. The effect of Interference calculated here Is grossly overstated for the 2000 series aluminium coupons. The 7000 series data are considered to be mot.; typical of interference fit fastened low load transfer specimens. The 7000 series data indicate that Interference between fastener and hole result In a faetov of approxi- mately 50 percent Increase In fatigue life for 50 vm (0.002 Inches) hoi* interference.
The analyses fit the data as can be Seen In figures «8 and 4'* for the 7000 and 2000 aeries aluminium alley mateilals, respectively, lu the 7000 series data, the multiple linear regression curve at zero Inter- ference appears to fall in the middle of the data whereas the 2000 series regression llr.e Is at the lower limit >=f the data. The .'000 aeries regression Hue appears to go through the middle of the USA data which had squeezed rivets Installed. As dlacusned in the previous paragraph, the USA data Were used as zero clearance data in the analysts; it Is noted that some Interference «111 be present after rivet Installa- tion.
Since the other data are significantly offset to the right of the USA data, the regression Indicated a strong effect ot interference on fatigue life tor the .'000 series »pe> lmens. The 7000 series data has a »such smaller coefficient of lnterferer.ee.
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I
problem of calculating where a parameter ha, no JSntlt«iv f « i li* ' "lu,tMtM °ne «*y *0 avoid ehe independent value ' 1 • was assigned^ those soecZnt IM "h ««ociated with it. In this case, the
were drilled. In order to equitably collet. tsTn.l^s s th^rl"^ "1 "" V'lu- '0' t0 ChoS« whlch
holes were removed from the data s. . The' result is given in equ.tioT Mrle' "** *" ^"^
N - 10 A (5.5974 - (0.00575)*Stress + (0.00380)»Interference - <0.000812)*Ream) (8.3)
This equation is somewhat different from thar nf p„ HI _„. . . but also because ten (10) specimen, we« removed La't^L * , T" ? "ddItI°nal "• has been added Note that the coefficients of the »«„ ,tTl i„terL. /w? ^ F"nCh a*"ci•° ««e deleted, fro« those given in Eq. 8.1. The coeff c'ent to tt W ZllV.if *< """ Ch"n8ed iw th*n 10 Percent
variable is limited in value to lithir 'o",r '1' tta^Jr * " -°-000<312- Sln« the "Ream" cient. A typical effect of the "Ream" variable woolh re r\ • .w T?" '" "^^ froB1 Chts coef""
•nd t2*~^ hoi. specimens with LoCtbolt fasteners
were not further investigated "using \". u W.rSlio'n ."1^ Ä?"- e"*nt-n«».. These data hole quality parameters. P regression since there was no way to quantify the
tab.. do,bo„. .p«l„„.. Th. „„,.., .«C... ,".„" °" J 1. ,,' '•"•'-»«• •" "•. ACAU ,..T..
«trees while Increasing ,h. maximum w tSTuSf2SS£ f ,h "T *? •1"»""'». component of the increase in fit fro. a medium to a high v.lu". r k" ?"*" h»f*« " difficult. The
An interference of one psf rcnt „, th* fasteneV ul^,Jr ' ,, ".f ""^ " ,"HU'"t- »••*""—•" 1" W». value (reference .)). No significant «|f3££ ^ » id'. ^ "* ""•""•«' " •« •>«!—
zrzzs&rfaiuu" «-»* *<*« "2ä ttffÄ srsasrra= a*a * ~^7^«^ g -£. - ~M wording t. spolled
the Netherlands). 6 "' "t4t,e/ »« larger under M1S1-TVIST 111 loading (France.
The au«*rv.u* fa.tener ,f,f9m eva',„ated ,a tile l% „, ,ju
•iatsitasgLaLig taj ACA*D to» IOHJ »,W,„ ,uiatJjSiy&
tusBcd in detail in N.1».
The fatigue teat results fa- rl,. I . i • A— U figure » aW 3S L ITJZ lr?J'•!Zl 'l'***t-i W«*~« «« M«« in Anne, » aBd 4re very gto*U. I« should be noted that «he lif. lÜ"J^J"|» J"«.r—. mil« the dM,aote fit resuU. are
t ia, the Mfr«.!« region ar„.o,d a eld «^ M J J ' ' f r»"M <'•»«««• UJ Indicate dieter I. L.,. BU,„. 5|nte ,he m ' JJ JWJ c, ends to a gt„ appfolljBa|e,y |h-| „, ^ (>
that a. high an afti>unl B< wM could no, bedeJTl^ "> < edB" "4rSl"' " U •,°"ibU
«« failure »,des: the U* Join, frtUJ fro. I trettiat ' ,?,f Wi? W"^k*', 'HCla^l. l«ve differ-
»C*W J.U< fails Ir«. „rigin. „ thc Lre" \he LoU* UltLTS "" t.h".büre ? «* UU »*»« th« MfM by cold wooing. .lBl, the ^ 45^^^^^,^^"^ " "«-»»
!
!
"
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10
8.5 Correlation of fatigue live« of double shear and low f,.n.f» j,«.».
banus may overlap (partly). The Dutch maulr» tfi~,.r. n\ _v .w Jui"«-» \rigurea 3J-5bj,but scatter- haa better UU^^wtMt^ia^tZSr^xl 51? , t * contr"y: «• low load transfer joint designs is compared " HLT *H*1* **' J°int- Next th« f"ten« 8V"e» rating in both
rHSfr=r~ SäST« ääTä & worked hole, or interfere""A faste'ers witn th^ exLotiol, o'f'ih. rT't "' f"ten-r8 Ve"U8 C°ld"
B.ft Double shear lolnts fatigue life analvsl« result.
H.h.l Participants programmes
have 2L^4322^^KiS 3,,th4tf r
he WTT Mde °f the 705° "d the /07i •»«*• be spectra the 202« spec^l-en. have -« eau-1 oV 22* 'V* hl»h M1«'-•'ST III stress level. Under both
worse performance is found a The highest S^wJ^vSTZh^ {"JT! ""/" ^ *»» " alloy series was also found in the lot load tr.n.'lr jolnl^Jrograle ° '" "*""' - *" "° ^"^
^mvlJ^JL^^^ !S^äS^l ^"ff".* about 201 and 50 »• «*»<•th« show that cold work, in combination with "ea« J lit "Vf-! "T ' "* "^ lü"d '"""«' Joint8 al" except at the highest stress level Em 1.1.1. . . ' "uPerlor <» • ~dluB interference fit and. (split sleeve) cofd work result, fal'l at ho h Vr ."T* f*': '" **" BrllI"h r"ult» *hu" «h« Che «nee eyste* (Hl-tigue and Tap.rlos, Vn V«. f i?£Ä a^miTK ^ T*! °f <"" hl«h iBte""- scatter band» prevents the »allng of . straUht for^.rJ . t* ^"^^ •" ov«rl*PPlng •« *••>« Nevertheless, the UK results further .!»E« Sat »rr .! Tlt^r.-* r'nkln« "* ^ f"tener •"" — • tio„ with a «diu. to „ig», *x3sjtt&'*s?2£&? i»t"£r:"Jr±.e;u ^in c-bi- High interference system.^ ffÄ^Ä Ä^^tftiVt^Är "* H1-t,8U' »•»»..• Core prugra»e
Using the high load transfer (type t>) double sti^ar *,.<-. i. i„ t- interference) is superior to Flfti* KfiiSS fioTJllS he VenT huh ^1 «*»W^* —-«« turn, gives significantly longer lives than «rs H Vhi V the/renth hl»-h »"'erferef.ee system. In its £1 need to be cü3bl„ed li th "Lcdiul " ft l^e Cr" ffi^fSÄ.- ^ f-tlWl- "' M'' th" — Th. correlation wit« the load «ran.«« values will b. m.4. JJ [ j '
T^a)^^^^:^l<XZ BSÄT1KlcndB ,üh!e -lur lhan lB
the Join:. The slngl« -h..r fu%mtt» til, in cle.ralce I ft h,T" , T^ " al "* ÜUl*r "ur,ace of
1« double .hear joints. This factor, together wühThe ,1 « ,K .' , , K"* * "-XUr b"rtB« at"'1 thaB
SÄÄÄJT*-by ----- • •?-- SÄÄVS !23ÄS! Sjra
*. .he 10,4 ,Uoy .^imen. «4 the M„ allo, ÄÜfÄtjÄTÜTÄ ^ "o« ffij gS-jT" "^
«M^ÄIfffS^^ «**« »' —«-« 1» If «he I«« rive,; ,hl/u ^M strUiS for Üeärli - "lV*" * Ur** ,ftCfMM ln "'• co-Jured «" r.tlgu. character! t.ca a^"ÄNÄÄ ^ «-^U.^?tS^'1^ '^"^ — better c!,»„ the >0it countersiBk uu Thi- r- ... *** »'"•• '»»•« U t rialnlv mot the almulated condltloT U ""*" '"'«•", ~ »*•<**' «*Wl-W Cor the Irily rivet "under
(agurriirsh^t'^iTfe^/eririrti,:: iS/^j^?;£i2 ^ £ "r-*—«-siMvköit the», fa.tener sy.te-» fall i„ ,he scatterbanJ' eTwiT « . * f "P**1-0- »WWW, the result« of .-tent fastener sy.,_ te0o lo .^V^lSK UvTlTl{1^^^^ '^ "—- »" dl"
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1.7.2 Core programme
As pointed out in 3.4.2 all specimens, i.e. all single shear and their double shear equivalent de- signs, were manufactured from one material and provided with one type of surface treatment. One half of the specimens were installed with fastener system A (FRFS-A), which has a countersunk Hi-lok installed with clearance fit in a reamed hole. The other half was installed with FRFS-B: a countersunk Hi-lob in- stalled with interference fit in a split si«eve cold worked ana reamed hole.
This section analyses the results from this and the double shear core programme. The multiple linear regression analysis was performed on the singlt, shear cata, except for the X joint data. The equation which best fits the data is given as:
N - 10 A (5.874 - (0.006507) * stress - (0.00994)* secondary bending + (0.009874) * load transfer. (8.4)
The coefficients of the secondary bending and load transfer are approximately 0.01, indicating that a 100 percent value of either secondary bending or load transfer will result in a change in life of a factor near ten. According to this equation, secondary bending results in a decrease in life and load transfer results in an Increase. It is noted that the analysis treats the secondary bendlne and load cranafer as independent variables, but they are not in actual Joints.
It was thought that it may be possible to superimpose the secondary bending stress onto the applied stress This was done for the single shear specimens by multiplying the applied stress by a factor of (1 + second- ary bending/100). The resultant relationship is:
N - 10 A (5.3822 - (0.003699) * (stress * (1 + secondary bending/100)) + (0.002200) * Load transfer) (8.S)
This statistical correlation resulted In approximately the same coefficient of correlation at th: t of eq. 8.4 but the load transfer coefficient Is significantly lower. Apparently the extension of th. stress scale with the addition of the secondary bending lets the load transfer take on a different level of Im- portance within the multiple linear regression. The degree of correlation In the equation Indicates that secondary bending is a primary component in the fatigue behaviour of »ingle shear specimens.
Figure 58 presents th« fatigue test results of the core programme single shear, double shear equi- valent and double shear designs. This figure also gives a regression line using equation 8.4, as an example.
The differences in life for single shear specimens with FRFS-A and with FKKS-B are small; in general FRFS-B gives only a small improvement in life. There are three exceptions: the X joint, where there is a significant difference between the fatigue lives obtained with FRFS-A and FRF.1-B (the FRFS-A series had slightly overslted holes, the FRFS-B series had very much oversized holes resulting in an average o! •) m clearance Instead of 25 urn interference), the Q joint, where there is no significant difference between the two fas.ener systems, thus Illustrating that the increase in bending when going from FRFS-A to FRFS-B is In balance with the decrease in load transfer (table 13) and th« C2 lap joint where the deviating correlation between fatigue life and stress level might be influenced by the bending restraint, preventing rotation and hü. hi, ,ecu»d,r» bending of the specimen at low loads and allowing rotation and thue high secondary
bend ng (SB» 1 00) at the high stress level. The bending restraint was not used during the secondary bending and lead transfer measurements. Consequently, the secondary bending value should not be used lu the •valuation cf the fatigue test results.
The small differences In fatigue lives under FRFS-A and -B allow a combined plot of fatigue life versus secondary bending to be made (figure S»). F-xeludtng the a lap joint result, for r««uBn mentioned previously, a rorrelatlon Is found between secondary bending, fatigue life and stream level: when ln.-reas- l«g the stress level a reduction In life Is fou«.d. but this reduction In life become, •ore pronounced with Increasing secondary bending. In conclusion, the beneficial effeet of falls« rated fastener «stems Is overshadowed by secondary bending of single shear joints. Load transfer plays a secondary rBle In this.
The double shear core programs« results (figure 58) .how. contrary i. the single shear design*, a large life Improvement when applying FRFS-B. It 1« noted that the re.ulis of the IS dogbone double shear specimens with FRFS-B are an underesttmat« since two tests were stopped at about 100.000 flights and a third lest was stopped due to test machine malfunctioning. Tnls programme part also .how. that the »tatement "the higher th«. load traust.,, the shorter the tallgu. lite could not b. confirmed for all Joints. It might be that small differences in the tit disturb -1.« rating of joints on the basi. of load transfer.
Comparison of the fatigue lives of »tagle .hear specimen, and the r double shear equivalent design, s enly possible with the type C lap joint and the IS dogbone specie.,. The first type ha. *uch sho.le,
live, for the single shear design. It Is noted that the FRFS-A double .hear equivalent specie,, ha. a love, load transfer than It. single shear counterpart. The double .hear equlv lent de.lgn of the IS uoghone ho. longer live, only for FRFS-B. Fasten., system A In the double .hea, equivalent e.s.gn B„ov. a \oe,whai swll.r fatigue life than the iS dogbon. ,.suits; this is cau.ed by th. tnc.a.e In load trans!«. In com- bination with a moderate fastener sy.t.m quality when ch-ngtng from a single shear to a double ll is noted that the fref-rh core programme specimens had only «poxy paint as Interlay
»•a Correlation of fatigue lives and cost of faftemer systems
irfac. .hear
t realm Joint. nt.
M•/°, 'Ti-ViMmi U V "l* ,h# ,ot*1 """ «««•• '•*• -"• '»•'"««" ^relu... cost (based on .5000 pieces) and the maahou,. for hoi« menu*acturtng and fasten., U .tailed*», ran p« .valuat.d tn more det.U. Th* eoat/ltfe pl.t. (figure. 40. «I) show envelopes. ,h. cost scale of which 1. .ff.tted .tron.lt by th« ..per loh system. If t-.la «yatem la omitted a general trend of better fatigue perform,«« with Increasing cost is observed In the high load t.ansfer data, receptions to this tr.ad are th. Huch-KXt which is more cost effective, and the Acres sleeve cold-working, which 1. »omewhat less cost effective'
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9. DISCUSSION
A. -«..on.. „ c.pur , th. „p„t m inuiy mmtm of th< rare ^ ^ ^
E»ch o, >„. OI,„C,IV„ ulu b, dl.en„.d.
——taiateaa al as aam •••—
SSJST^^^i^rSÄTi'Ä lÄth- "—rt - •*• p-p—• A h.K«l!"**"! ln»tall«d i» hol«, which wer. i , "' J? '•"•»•« r.ng.d fro» .ta„<Urd bolt to
2. 3. 4.
5.
6.
iaisaasa °* &a g - -r>rm ,-m.r riA1HL„
rZ V ^ " 5pUt SUeVe c»ld work mi«. »„.i „. "•»»«•«. Moderai.Jy cat effective *„ ,
SS wHÄS«Lf-Ä^ —; •>(
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U
Load transfer plays a secondary role In Che fatigue performance of simple shear Joints. In the double shear (core) programme, differences in fastener system, in terms of life improvement, are clearly show». Thus, load transfer is not as dominant as is the secondary bending in simple shear Joints. Further, the fatigue life rating of the different designs does net correspond with the load transfer value« measured in the core programme. This might be caused by the differences in interfay surface treatment (French specimen) and differences in fit as applied by the different participants. Considering other data it is concluded that fastener installation parameters (fit, clamping, cold work) and load transfer are also Important parameters. It is suggested that hole manufacturing to size and fastener installation should be done at a single source for this kind of core programme.
Thus, fastener interference is a prime parameter, except when applied in single shear Joints. However, no optimum value can be given. Results suggest that the interference should be at least 1 X of the fastener diameter. But with high load transfer in combination with high fatigue stress levels the cold work plus
high interference is the prime parameter.
Last but not least: the cost of the fastener syst«m, of course, is also a prime parameter. In conclu- sion: the FRFS projrammc not only Identified the prime parameter« in fastener system selection but also
qualitatively evaluated these.
9.4 Design data
The large number of specimens tested and the numerous variables Included in the programme yielded in a large amount of variable design data. It will be clear that the programme did not cover all variables, simply because the total programme was built around the various participant's individual choice of program-
mes.
9.5 Reference datum
The core programmes allowed a comparison of different Joint geometries I' rom various participants. Not only the fatigue tests, but in particular the determination of secondary bending, load transfer and fit contributed largely to the understanding of the behaviour of complex Joints. The lntormation obtained might
serve as a good reference datum for comparison of test results to be produced In future. Moreover, the core programme results are a first step towards the definition of standard specimen for the evaluation of fatigue rated fastener systems, which will be a new ACARD SM!' activity.
9.6 Experimental methods
Each participant used his owr. experimental techniques. The report focused on the clamping procedures of "clamping sensitive" Joints as the reverse double dogbone and IS dogbone. Clamping sensitivity may occur when a Joint does not tranater all loads from one base sheet to one other base sheet.
Experimental methods were developed with regard only to the measurement of secondary bending and load transfer. However, the pre-loading procedure should be specified exactly. The following preloading is pro- posed:
0 load - 100 1 FALSTAFF - Hin. load FALSTAFF -• 0 5000 cycles: 0 load - 50 2 FALSTAFF - 0 0 load - 100 I FALSTAFF - Mln. load FALSTAFF - 0 5000 cycles: 0 load - 50 I FALSTAFF - 0 0 lead - 100 X FALSTAFF - Min. load FALSTAFF . 0; at the 100 I FALSTAFF the measurements should be made.
Further, the form to record standard test lntcimal luii was not used widely In the programme. This !s In contrast with the success of the form to record the measured fit. The procedures to measure the fit worked well.
10. CUHCLUSiUHS
The HUM coordinated Fatigue Staled Fas' -Her Systems progra lias demonstrated that:
(1) Secondary bending proved to be a prime parameter. At moderate to high values it tends tu nullify the beneficial effee; of fatigue enhancement fastener system*; die fastener installation parameters (fit, clamping and c«,d Murk) are M prime parameters In that situation.
(2) Single shear Joints are the NDSt severely loaded Juinte with regard lu fatigue. (1) When secondary bending is present the luad transfer plays a sec-ndary rSle. (4) At low to moderate secondary betiding or at the absence at it '.'.-- fit. clamping and told work arc prime
parameters. At high load tranater and at high tatlguc luad levels the best results are obtalnel with cold worked holes plus high interference ':: fasteners.
(5) : •..Me shear Joints clearly show a fastener system tallng under realistic fatigue loading: the lite improvement mechanisms are more marked in these Joints than in .-.-* luad transfer/low secondary bending Joints.
(ft) The low load transfer Joints and the high load Hamster double shear Joint are not equivalent with tegafd tu the fastenrr system rating and c.-?t effectiveness.
(7) Results suggest that (he died ul stress level Is the same tur no load and low load transfer Joints; the luv luad transfer joint has somewhat shirter lives,
(g) The hole quality as such Is not a prlifee parameter. However, dimensioning to site to obtain a clos« tolerance fit results in holes with good fatigue quality.
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14
(9) Increasing costs of the listener system might result in a better fatigue performance, but - moderate to high secondary bendins tends to nullify the extra costs of fatigue enhancement fastener
systems;
- both in high load transfer double shear and In low load transfer Joints the Huck-EXL system is the most cost effective and the Taperlok the most cost ineffective of the sysceais evaluated. The Huck- crimp system is moderately cost effective for the double shear Joints and at cost effective as the Taperlok system In low load transfer Joints; while the opposite applies for the Acres cold work system.
The Split Sleeve cold work system is moderately cost effective for both types of Joints, but it is understood that neb developments will eliminate the time conaumlng, and thus costly, reaming to size operation. The clearance fit Hi-lok system Is cost ineffective particularly at high load transfer in combination with high fatigue load levels;
- care should be taken when trying to establish the potential cost benefits or penalties in practical situations.
(10) Valuable results and,a large amount of design data were generated in international cooperation by combining participants programmes and adding core programmes.
Cl) The results of the core programs*« provide an excellent basis for the comparison of test results produced using different specimens.
(12) The core programme results are a first stop towards the definition of standard specimens; the low load transfer core programme showed that the use of standard or reference specimen results In easily com- parable fatigue test data.
(13) Standardireu fatigue test spectra are undlspe-.isable.
(14) Fatigue tests on fastened Joints should be accompanied by the determination of secondary bending and load transfer on each combination of specimen type, material and fastener system.
(15) The requirements and standard instrumentation for the determination of secondary bending and load transfer need only to be adjusted -as proposed- with regard to the pre-loading procedure.
(16) The diameters of each hole and fastener should be measured In fatigue test programmes, which evaluate bolted Joints. The procedures adopted in this programme worked well.
II.
1.
REFERENCES
Coombe. T. and Urrl. R.B.. Critically loaded hole technology pilot collaborative test programme. Final technical report. ACARD Report no. o78. November 1980.
Perret, B.H.E., Some measurements of load transfer and secondary bending In fastener joint specimens for the proposed evaluation of "fatigue resistant" fasteners. RAE Tech. Memo Structures 950, Hay 1979.
Van der Linden. H.H., Fatigue rated fastener systems in aluminium alloy structural Joints. NLK MP 8JÜ45 U. July 1981.
Uanhill. R.J.H. and De Luccia. J.J., An ACARD-coordlnated corrosion fatigue cooperative testing pro- gramme. ACAR1) Report no. 695. Februar> 1982.
"errel, H.H.E.. A high load transfer Joint suitable for the evaluation of fatigue resistant fasteners. RAE. A note for presentation at the ACARD iMP "Fatigue Rated Fastener Systems" meeting. September 1981.
Jarfall. L.. Review of some Swedish works on aeronautical fatigue during the period May 1971 to April 1975. 1CAF document no. 800. Mln-ites of the Fourteenth Conference of the 1CAF. Lausanne. 1975.
Van der Linden. H.H.. Determination of secondary bending and load transfer. NLR Memorandum SB-81-08J V.
Circular letter dated 22 April 198»: modified figurea 1 and 6 of NLR Memorandum 5B-81-08J li.
Jarfall. L.. Determination of secondary bending and load transfer. SAAg-SCANlA document FKHl'-8'-lJ April 1982.
10.
il.
12.
13.
14,
Eriksson. F. and Magnusson. A.. Determlnattun of load irau.ler dletrllutlon of bolted single »hear Joint by Integration method. FFA Progress Report HU-2J12/1. July 1982.
Various author». Dea< = lf>< >..,: of a Ptghler Aircraft Loading STAndard F-..« Fatigue e.aluallot. FALSTAFF F • W (Swltserlaud). LBF (Germany). KLR (The Netherlands) and lAftC (Uermany). Karcti 197».
De Jong«. J.B.. ScMU«. 0.. Lewak. H. and Schljve. J., A atandardUed load sequence for flight »imula- tlon tests on transport aircraft wins »trueture». MUt TR 71029 Ü.
Kalek. HtllF-rechl. garnert. «offer. Vergleichende Schwingtest l8kelt »Untersuchungen an einschalt c igen Fas»uletv«rt,lndungen unter Elntelt lugbelastuagea. Vet.uclbb« reicht VI171. MtÜ-VFV. August i981.
Dietrich. C. Potter. J.M.. itress mea.ufem.at» on col4-*ork*d fastener hole». Advances in X-rav analysis. Vol. 20 (19??). Edlted by tt.F. McMurdl«. C.S. garreit. J.8. Kewklrk and CO. tuud.
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15
COUNTRY
FRANCE
GERMANY
ITALY
I THE NETHERLANDS
SWEDEN
UNITED KINCDOM
WITED STATES OF AMERICA
p.—< . TABLE 1 -.rticip.„t. of ch. ,.etgu. ^ FMCMer sy8ten ?rograaae
CODE
FRC
NL
UK
liSA
PARTICIPANTS
Cntr. d'E.,1.. A.,0—tiqu. d. TouloU8.-CEAT
peinigt. Flugt.chntach. W.rka VtV-MBB
University of Pisa
National Aero.p.c, Labor.tory-HLR
SAAB-SCANIA
Roy-1 Aircraft E.t.bli.hmant
_Air ***** ««.rial. Laboratory
_AlLrorc' Fli«>" Dynamic. Laboratory
J-P. Hertenan
K. Hoffer
C. Tavallini
H.H. van dar Lindarr
L- Jarfall
R. Cook
R.B. Urrl
1
, , TABLE 2 KalUUe Rat"d *"•«' «Ntt. pro.ra... parll
JOINT DESIGNS AND
EXAMPLE
*> 1-<'AD TRANSFER
LOU LOAD TRANSPER
M.L.T DOUBLE SHEAR
«•t-.T. SljicLt SHKAI
PARTICIPANTS PROGRAMMES
»S DOGtOMI
: to» ta4c • *ee (able 1
rite I Nl. K L-SA
y s M. w
r S
MA
CORE
PROGRAMMES
s NL
w. 11.
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16
TABLE 3 No load tranafar joints progranm«
PARTICIPANT CORE PROGRAMME
F S
MATERIAL
2024-T3 2024-T3S1 2214-T651 7475-T7351 7050-T7651
• • • •
• •
0
FAYINC SURFACE ANODIZING. PAINT AND SEALANT
RARE
•
• • 0
HOLE QUALITY BROACH
REAM
• • •
0
o
FASTENER LGCKBOLT, CSK BOLT, CSK. HEX.
RIVET. CSK. UN.
• • • •
o
FIT TRANSITION
INTERFERENCE • • • o
0
SPECTRUM FALSTAFF • • • 0
TABLE * Low load tranafcr Joint» prograa
PARTICIPANTS
F FR£ 1 NL UK
core
USA
MATERIAL 2024-TJ 7010-T7* 70*O-T74
a
e
o
e e a
a a
a 0
a a a a o a
o
FAtllf; SURFACE
Mioettt «ie. PRIMER SEALANT
o 0 •
a o a
o a a
a a a
a a o
0 0
a a
0
0
0
0
U
a
0
0
0
a
0
a a
o 0
0
mm QUALITY
MULL UM ÜKiU. REAM BROACH *>LD WORK
o a
o a
a
- u
0
• a
0
a a
0
a
0
FASTlÄtR
Ml-U« LOCKSULT TATKtU* Hl-TICUE NUCKCRtM»' WN-X EXL RtVfT BOLT
o
0 • • •
0
a
0 a a 0
0
a
« 0 a
0
FIT CUAXAKCC ItrruratKKCE TRANSIT!«*
a 0
a a a a
0
0
a a
a a
a
a
0
a
SPECTRUM FALSTAFF MIW-TM1«
0
0
a 0 a 0 a a
a a *
a a a a a u
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'-*•'
!
TABLE 5
Double sheet Joints programme
PARTICIPANTS
F NL S UK DESIGN m— 33 II II •* mm
2024-T351 • • • • • HATERIAL 7050-T7651
7175-T7351 7010-T7651
• •
• • • FAYING ANODIZE etc. • • • SURFACE PRIHER • • • • •
SEALANT • • • • • • • DM DRILL •
HOLE REAM • e QUALITY BROACH
COLD WORK •
• • HI-LOK « • • • • TAPERI.OK •
• HI-TICUE FASTENER HUCK CRIMP •
HUCK-EXL • RIVET 50LT • CLEARANCE • •
FIT TRANSITION INTERFERENCE • • • • • FALSTAFF •
SPECTRUM MINI-TWIST CONST. AMPL.
• •
• ——.
• • •
'
TABLE 6 Singt» ahcar joint* prugran
DtSlt*
MAT tit! AL
FAY INC SURFACE
HOLE QUALITY
FA5TUft«
m
irtCTMM
22U-TJ 707J-T7« 7475-T7JM
CLAD AMOUUE etc. PRIMER
Sf-LAXT
TOPCOAT
PARTICIPANT
DRILL REAM
BROACH
Ml-U* LUCKBOLT
SULKVBULT BOLT
CUAR.Mk-E
TRAKMTtt*
IKTEftFtfeEIICE
FAUTAW
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^w ••r
is
I Cora progr«
TABLE 7 on single shear jolnca
MEASUREMENT OF SECONDARY
•ENDING AND LOAD TRANSFER
FATIGUE Tfc STS ON SINGLE
SHEAR JOINTS AND THEIR
DOUBLE SHEAR EOUIVALENI DESIGNS
NL
ALL SPECIMENS:
O MATERIAL ALUMINIUM X*OT7#. I.tfim
o INTERFAY: EFOXY PRIMER
ANOCR I4JIGUALANI
O TWO FASTENER SYSTEMS
'ASrfMfR
SYSTEM caof
HOLE
QUALITY
C
OMKJNAl
REAM
J'A» COLD WORK AND
Ml AM
FASTEN
ER
Ml-LOK
• U !»• I CSK
FIT
•CLEARANCE
INTERFERE NCf
» 110
[
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19
TABLE 8 Mechanical propertie« of material»
»qvnct KlMVEa
r*«Ticirun ALLOT «'«I mATHOfT
»AITINC TMSi-KHr-.-.
rinAi TMCMm
Dincrio* TDUU» TIKL0 mni
IILTIMTf mus
l*T-l>
tLOMCATlO*.
I
Totmc'i BOH
•OUU.I
1
KAHUiAirruna
1 nu*ci ibit Till »..-. 14* 111
II! 10.4 11.. CKCUHII
> 101« 1014
TIM Till
11 • 10 •
111 «it 411
II 14. J
ALCOA
* 1114 Till 10 . 111 441
444
411 110
101
1.1 10
1.1
CKHK!»
C4CBW»
1 • ;oio »010
1(441 Trtji
1 II •
111 411
411
111 111
141
11 II
1!
ACAAD UTU1AL ' ' MAM
ALCOA
• .'07» »4M
TM1I tMJI
II -. 11 .
411 444
441 411
»JJ 110
101 104
II i.i
ii.i I.I
CICIDUt
rieietm
» ree. >ir. 1014 TJ 1 111.? 4)0.1 :o,i «•;«) ; i ..«•:'! I
10
II
cttjujn
ITAU
;o*.o
1014
Tl»
TW
1
1
111.0 110.0 ii.i •Uli AUAkO WTUIAl. "' *.|rna
11 II
TH »muuujuibi
101» ;oio
T> Tl» »(.A.:- KATU1A1 " tlA
14 IX '010 TI»1I I'J - t «10 110 • It 10» Tl» 1 4CAAD UTUlAi " Al
1» i;
BM 1014 .014
Tl T3M
1.1 1.«
:.i
CUB
CLM
••
it N 11
cut! ruu«
•-.in*
10*0
tori .'014 1010 10*0
tl«
tl« Tl tl»tl T'»
l
I.I t
no* >
I
I 1
IM «11 ill
4M 4M Ml
l».l 11.0 11.0 1
•1100 10 »00 14,:»
ACAtO HITtttAL "
AC«*» NATUIAL "
1UU HATttlAl
ALCUA
ALU1A
ALCOA
1
!
TA»U » Tayittfi Juitav't ires
sty.t». r Mattet »MR .»..:<- LAtiO Uta*» HMMM iiaiMt lAXTtM« UrtJIiLAttO»
• fkABtl «Ml Nttl 11*1 A** • Mit HI*- AM . " H>
; . 1RII rltatm 111 A» IMl 'l!l unr ÜR
» IM lit»«* HPUll-5 an
« ILOktCt 1MB MHM m*tt Hi
•- ••••• •MUHi •HI itMAll --».••«» »•41»»« an . .: •) - •-
« a—HIM ::m ia>Kaa»tt M-KI ' Mi«aH Ml, 1». :.,«,.. -.i,
i 1ULI AAv«•:::•. rl:u M**iH •*; • n r»l«n • tat «-»I MM •Han H***t< ••*. 1 «n
i --» « Alt« k.«i::i = ntaU -»iU . riu.it. A Ht ii •Mi HHM rll.Jl«
ii •BIT»» mm Al as BOM* iraAt Mtati Tctot» Nit:: M «ti »:T» ran:: AM
it •u . - - M •MtH ir.-."' ntau **nnmmx mm • ii >w •> ••—» •-r. '1 ;».«;! MllUt NTS A • I
it HHH ÖU*» M ':• . •MiU Ml
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20
TABLE 10 Fastener »y»tcno
SKUIWC» "AIT It I "ANT noil nooocio» mrs rAsrmi riT mrnu
i PIANCI UAH TU • 4.11 wu Ki-uw t ».11. H..1. cat Cl.-AIANCt 10-11) 2 IIOACN nll.ll NOLI Nl-U* » I.M, Tt. CM CLIAIANCI 10-10 ) UM (1 1.71-1.»)) - COLD UOMIK 1 t - MAM TO 1.1} 1(1 U* 1 ».11. 1MB), CM iirrnnuKci n-ii 4 UAH II 1.71-1.»7) - COLD UOU1W 1 t - 1'iwl TO 4.11 NI-LC« 1 t.ll, Tl. CM iNTJWiuact ii-ii 4 »Iiurii TO 1 4 KOI.« L0CM0LT »L f ». TA»». CM i-Ttiruoci i»-i> » MAR TC t ».Jl NOLI Nl-U» $ ».11. TA»V. lull ran INTI.IrtMNCI (C > r.i.cUMirr MAM TO • ».10 (Ml) Nl-U» NU0---0-7. COLLAI M.70-» INTUrUDR.t 12 • BOUIil NUU.II DULL TO 1 4.2» (Nil) DITTO irrurrHKi i» 1 MAM TO f 4. )0 (1?) DITTO mrumniti it
10 OOllL! MAICI» Dt!U TO t 4.24 (Nil) DITTO INTIiirUIOKI 40 1! MAM TO • 4.M AM 4.10 IN.'I DITTO CUUIAMCI 12 12 MAM TO | 4.2» (HI) LIXXtULT JALf t-T «-0). COLLAI » LC-C 1 imiruoct i) 1) DOUILl NAIC1N II»111 I" * 4.24 (Nil) DITTO INTUrfUBCI 21 1» DITTO LocMOLT en i it-or o-->. COD-UI 2 «cc-e-» irriiiruiMcl 42 II TAM.LOCI HAMM (TBt. 20*0 M 1-4) TArULOOl Hfl 200-4-», COLLAI TU 1010-4 IKTfirtMKI 1' 1» ITU-T MIU * 4.1 '.HAMIIAL) • MAM I ll» - ..« lakl« III Ni-L0l 1 1. Tl. CM. IMAI TTW. !Jl 2*7*7-01 INTUrUCMCI 11-41 1» MUX t 1.1 (MANUAL) - MAM t 4il - ••• lakl« IM Itl-n« * », Tl. CM. SNKAI Ttrt. LN 2»'»7-0» i-TMrtinct 11-4} 11 »«ill * 1.1 (MANUAL) - MAM 1 III • m 1.41. IT» Nl-U» f ». Tl. CM. TDniON TTtt.
"A* 1211-0» iHTiarunci n-*>
1» MILL t 1.1 (MANUAL) - MAM » 4.4 - ... 1.41. |r» 111.*, ||, Tl. ntOTtimiNC, IMAI TTM. t.» 2*2*4-0»
iNTurunct 11-41
20 MIU * 1.1 (MANUAL) - (UN 1 HI - M. «Ill IU Nl-LOI. » 1. Tt. CM. IMAI TTM. LN 21'17-M
INTUMHKI 14-11
-•1 MIU ( 1.211-1. )H • Mt IT Si.ir.vi COLD HUM 1. !!-*.») 1 . - MAN I '•»» - ... 1441« ICW* ITD. »OLT. ( ». Tl. CM. LN 2**V»-«4 CLUIAMC1 10-40
II MAM - ... 11 - Nl-U». * 4. Tl. CM. M»TMll-0»-H SIMILAI TO LN 2*2*'
lNTUMUMCI 11-41
21 COte HUM. MAM - ... 21 - ITD. »OLT. • «. Tl. CU, U 2«41»-0» iinmiun 11-41 !• T»t Uil «11 RAICH DULL t .14*1" • ... I*ktl 1 • Ni-u» NLiovr-«-». ncr.t.. % ».» TtAMIITlOM ii-tt 21 wmillir.-. ITANUAIS BNILL I ».4 - m 1.11. 1 - DITTO CLIAIASCI »1-211 2» BOUILI KJ.4i.in MILL - MI I.I). I - «1-LOI ill 14-0-2. C«. 1 4.11 irrturnu- i 20-40 .'! MAM - ... <akl« ) . DITTO inu^UIMCI OO-IM 21 CnL» Wt'U I.M 1 - MAM - Mt) lall. / • DITTl1
ILIAIAMCt O-ll .•» UK nil' ill» To f .2100"-. :>(>»" (Ml-CM-BUDM Nl-LB» «-»AST NOT (»0-00 14. la) 10 D*iU-tA«l MAMM Tiriiui )! MIU-UAM TO • :..'."- :.i/'-ir.l ll.:l> NI-T1CUI «-»AST HUT (»0-100 11. Ul) 12 M1U-UAN TO 1 r.o:-- . :-.i~ •in-.-» l-ibu MXietl»-Htn (»» it u) 11 Mllt/CM TO * .2»»"-. 141" MING c-v. i CUT» IBID
CVTTH-BUUM-NilUl KAttbUl lOLD NtXX To t .24»"-.24»" «K* ML. COUAI WtTN avu SWAUING TOOL
1* MILL-MAM TO t .;n"-.:»--i/uta IUUT m.r »um COLD 4UM-MAN TO r .24** .24*" CU DtNOU
a: •:» I-IA9T NOT !«.• !•!• 1» U)
11 M1LL-UAM TO t .111"- tW*fM tUIVU-lBSU? COUI lOtAlMU .-• «I-. 1LMVKI 4-«
Nl-U» l-fAST NUT i»u-m Ik 1.1
21-11; to***.* »ALU! i-oNftkHt» LRU I but)»! Of 11 IT 1*1 -A-TatNG AM» IMMKBlATftl Mit»
tt au j-i4lt.ii:- MIU-0UCU Tu ttäTlNL
I0VO-I JöLl» HVtT ,1.5 .-04:4)1 Haas laic v • l/l»" rUfSS k» I UIIIU klgi«t2ts A II STA-UA» ••!.:.. i-tlil» 2024
M :iuä'U: lllii Hr.U r.i UL-NMI-). 1*41. 1.1.1 (A) .01) »!«T < l/ll" (MltMIOl J0J4-T!(M).*iC"i£t3 1» »irto DI'W '•IS-ttitll. 40 HTTO ll«W t 1/4" IMS20*H>> 2024-TllMI. «1 Birw »it»» wMuniit). 4j »iff» um » Ulf (as:m:i> :s2i-ri(»»». 41 HTTO •if» fino-t'xi). 44 »Iff» ItVtt 4 \- (Ma2042l) .'..;. •!.»•: . II Nn t v itmii>i**> ••.:••:• <• J.t-, 4« tl
HTTO 9 v wmtm j«4-tn»»i. »Iff» • i* »mill '--.:>»'mi .
4» .'-<• MIU 1 ».*, MIU «.i..:. «Mt « ».Mi-«..11* «l-U» Nt-1»--»-» S. OALLA» 4S.-I0.» (tlttf) atett U.SINR ru»
4*
u •.-•I mi MAM to < .»*".. ml" «fS-A
!UMik".t ri» iktia-4. cuLLAI HI- i i-ttirUI4Kt 44
1! KM 1 « Mill litl ft. • 1.4-4.1, MA« t" * I.M] (I,» • : . .» MU4-U-M \- All INT, 1 kB
:_«>;• .i; .. _
j
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TABLE 11 Standard test info-":ion to be recorded
FATIGUE TEST
(a) General Data Date and location of testing Manufacturer/model of fatigue test machine
Test temperature (*C) Relative humidity (X).
(b) Specimen Data Matertal specifications Type of specimen, including interfay compounds, etc.
Specimen identification Type of »urface (machining history and treatment)
Fastener system: fastener type dry/wet installed
fit hole preparation technique
Installation coata of the fastener system.
(c) Test Data Type of loading
rr:;.ncylCof«xi-:-yio.d excursion (for standard spectrum loading) Characteri.tic stress level, (mean, or peak stress for standard spectrum loading)
Cyclic waveform Number of cycles or flights to failure Fracture surface observations including initiation sites.
I
TABLE 12
«Ä! 8S.-CS Ä.M* S15ÄÄÄS.S8 SMS
ruiM «u»>i »r rilabn
1> MM hlvC* of 4000 ü i*i.i»
Ku*t«i el wai la Hi ((« 1 «,«l ..) .1 ih* 10 r^IUuJ . l.v.l. Teial nu«b«r oJ evtl.* Ml
flight i II tu IV V VI VII Vlll U I
* 1 1 1 I 1 4 -•
'•~f It 14 4M t>»4> -•••> (0) 1400 ;420)
i 1
111 (:•*) II* (0) C 1 20« 4*0 («) t> » 144 ',14») M) (0) »00 (200) i ill (0) 440 (1)0)
t M 70 VI) 411 (0) 4*0 (*0) G in 21) (21) 240 (40)
N 4)0 4» (4) JO (4)
I )
tow nil
24 (I) 24 (2)
Tit«: Mabel »1 «»«!•• Hi »»•<• «1 *'J00 .11»*«-
l -• 4 II 42 142 100 4I>0 14*00 14*4*4 (1*422)
C.B.UII» B«**r .1 i«*» I .'* 1010 «00 '0000 I»»»*4
tytlM H' »l—k •» tooo rua>i*
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22
TABLE 13 Secondary bending ar.d load transfer of single shear core programme
specimens at fatigue test stress levels
SINGLE SHEAR CORE PROGRAMME SPECIMEN
STRESS LEVEL (MPa)
FRFS-A FRFS-B
SB LT (I) SB LT (X)
ISO 200
1.32 1.23
54 54
1.52 1.42
41 43
210 263
.42
.44 47 49
.53
.53 43 43
150 200
- [IS51SP - <3> 50 50 TYPE C2 *3
200 250
.04
.09 25.4 25.8
.21
.22 22.7 23.8 1*5 DOCBUNE 1
X JOINT tktt 150 .80 50 ®
!
SINGLE SHEAR CORE PROGRAMME SPECIMEN
STRESS LEVEL (MPa)
_LT_(Zj_
FRFS-B
LT (Z)
TYPE „1 DS-JOINT 150 20U
250
45.8 46.0 46.7
42.0 43.8 44.4
TYPE 0 DS-JOINT
IS DS DOCBONE
200 250
33.8 33.9
200 250
41.8 41.7
41 40
DOUBLE SHEAR OF TYPE C2
150 200 [S]
TYPE Ml 6 M2
TYPE HI
NOMINAL VALUE LT - 20 I (5)
NOMINAL VALUE LT • 50 t @
(!) without bending restraints
(7) Instrumentation not In accordance with requirements
Q) ::••:•! iii.i : value, not measured with FRFS-A, -B; measured in:
6 mm plate: SB • 0.83 4 mm plate (150 MPa): SB - 0.73 LT • 47
( 50 MPa) LT - 50
(X) aide aheeta t lnatead t/2
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23
TABLE 14 Cost of fastener systems
PARTICIPANT FASTENER SYSTEM COST OP
EQUIPMENT
AND TOOLS <s>
© ® <D •© COST PER TIMt
FASTENER (5)
INSTALLATION TIME PE« FASTENER (»In)
TOTAL COST PER 1000 FASTENER INSTALLATIONS (S>
(7) * pradrlll up to lnatallatlon
GERMANY (GP) LOCMOLT • DM TAPERLOK
; 1.36 1.1'. «ln.(i)
.62 aln.(l) '2.39 ala.(l)
1.16 1.08 3.18
1723 818
2416
ITALY
Tl HI-LOK CSK SHEAR TI HI-LOK PROTR. SHEAR Tl HI-UK CSK TLNSION CW+Tl HI-LOK CSK SHEA« CU*TI STD. BOLT CSK
- 1.00
I par 25000
0.6* (2)
1.54 1.51 1.68 2.64 2.78
1483 1473 1526 1827 1811
NETHERLANDS Hl-LOK/STD.OR DM DRILL HI-LOK/UAM HI-LOK/CU • REAM :
1.12 par 1.12 25000 1.42 (3)
1.36 h (4) 1.80 h (A) 2.28 h (4;
S.21 (5) 3.57 (5) 4.29 (5)
2126 2239 2764
UNITED KINGDOM
KI-LOK/PLANE HOLE TAPER1.UK HUCK-FJCl HI-TIGUE HUCKCRINP Hl-LOK • at HI-LOK • ACRES CV
101» 1080
SAO 10A6 »7
«271 209«
1.31 3.«8
.67
1.58 (3) 1.8» ())
3.2 26.0 7.0 5.5 7.0
10.3 8.3
1683 11627 2663 3433 2923 4807 4491
USA III-LOK SLEEVIOLT
54 (6) 60 (6) ;
' — J (1) lncludaa oraparatIon of tooling, • (2) »lthout cr.I of ilMV« (3) lnclualva coat of alaava (i) tndlcatad tlaa la par taat aarlaa (5) lnclualva aaalant and prlaar appll (6) Includaa hola and faatanar liapactlon (7) aaauaad: 1 aanhour • S 18.8
lant and of luapactlau
tin
V
f
TASLE 15 Relative cost of fastener syst«
PARTICIPANT -ASTENER SYSTEM RELATIVE COST OP EQUIPMENT AND TOOLS
RELATIVE COST PER FASTENER
RELATIVE PRFPARINC TIME
RELATIVE INSTALLATION TIME PER FASTENER
RELATIVE TOTAL COST PER FASTENER INSTALLATION
GERMANY HI-LOK + DM (CP)-LOCKBOLT + DM TAPEILOK
- 100 35
106
100 5*
210
too 93
274
100 47
141
ITALY
Tl HI-LOK CSK SHEAR Tl HI-LOK PROTR SHEAR Tl HI-LOK CSK TENSION CVHT1 HI-LOK CSK SHEAR CVM-T1 STD BOLT CSK
- 100
64
- 100 98
109 171 181
100 99
103 123 122
THE NETHERLANDS
Hl-LOK/STD or DM DRILL HI-LOK/REAM HI-LOK/CV • REAM
- :oo 100 127
100 115 146
100 111 134
100 105 130
UNITED KINGDOM
HI-LOK/PLANE HOLE TAPERLOK HUCK-FJtL HI-TICUE HUCKCRIMP N'-LOK • CU p-I-LOK • ACRES CW
100 106
53 102
58 «19 206
100 2 JO 45
113 48
104 125
-
100 500 135 10* 135 198 160
100 691 170 204 174 286 267
IMA HI-LOK SLEEVBOLT - - -
100 111
-
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7.4
ir
UM I 3 SECTION A - A l*-*H
Fig. la No load transfer specimen - French design
© DIMENSIONS IN mm
• so 96 p
«8
• i —
34
1— ^4-- 5
_-.
Fig. lb No load transfer specimen - Sweden
CD OIMINSIO« IN .
"I f r
CD DIMENSION» IN »» I
Fie. le »o load transfer open hole specimen - Sweden
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25
Fig. 2a ACARD low load transfer reverse double dogbone specimen
CLAMPING AREA
Fig. 2b ACARD lir. ioad transfer reverse double dogbone speciaen (specinen configuration of FRC)
+ ÜAAIN
-"•> fASTENEH
•^ ^
Tl
¥ Fig. 2c UK low load transfer reverse double dogbone speciaen
DIMENSION» IN mm |
® OlME NSlONS. IN •
,
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26
I
+ + + + + + +
+ + + + + + + +•
Fig. 3 High load transfer double shear joint, type D - France
CD DIMENSIONS IN'
/ FASTENER
+ 111
25 ?s + +
25
"I- 4- 12»
126 1 •• is 6
100 80 100
no *
I -L
1-2» (3) I DIMENSIONS IN •
Fig. 4a Medium load transfer double shear joint, type Mi - (he Netherlands
-r kr r
y
® | o.-MtmiuNi IN...., |
'**• 4b *•*»<• >U*J transfer double shear joint, type M2 - the Setherlands
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27
II / + t N 4 -t-
II
12.5
25
+ +!!+ + + +!!+ +
25
' 12.5
12.5
90
_25 12 512.6 25 12 5
101
___ »1 *1
w
f
1 ' I I s„ ® DIMENSIONS IN r
Fig. 5 High load transfer double shear joint, type HI - the Netherlands
V, c- TV FASTtNCK
4r
- BSSBB3 E$22j5"£SS£££^^^^J SECTION A - A
rig. 6 High load trans.'er doubl« shear joint, type H> - United Kingd
®> [ DIMENSION« IN MI |
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28
^ + + + T +
126
12.5
12.5
12.5
*
3= -i 1 1. I I ' "&
Fig. 7 High load transfer single shear joint, type C - France
CD DIMENSIONS IN r
431 S
FASTENER
• »'• > W4 rr 12 7
12 »
GRAIN
K 4 + +
244 SOS
-J L rttta
+ +
r" j=±=±
1—t-
® DIMENSIONS IN •
Fig. 8 High load transfer lap joiut specimen, type C2, and its double shear equivalent, type D2 - USA
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^ ^r + t I + + !-
+ | II + •
+ + I! +- +
U^Ai A I-
•i-V~3k
29
SECTION A - A ICOUNTtASIN« IN
•AM PLAT!)
1
I
+ ¥
+ 4 «I + +
T- + |i + t 1—M
! + + 4- +
:± * FOR ,l . B ......
Fig- 9 High load transfer sinBle shear X joint» - Sweden
'OH DIMENSIONS SCI TV« 1 ABOVE
© DIMENSIONS IN
«CTION A - A @
fig. 10 High load «*,,;«., Q jüinl . united KinÄdo» CUMtNSiOMI r^J
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30
-4s- R » 7S.0
+• —(- - I».O|80 Or
"fr
FASTENER HOLES
TV« H/3D (USA)( NL
TYPE 11/2DI <s> DIMENSIONS IN r
Fig. II The IJ-dogbone specimen, type UD, and its double shear equivalent design, type I|DS - USA (IjD type) and the Netherlands (both types)
+ + J4 + 4 " 4"
+ il + 4 + 4 4 T j-
IM
HI A
„ ,,t T
J«L
KCTIOM A - A
,,,,ij»jjWmltuJm|iu.- n/- 1 ... ! L>
Fig. 12 High load trainier double »hear joint, type Cl - France
CD [ PIMtNSlüN» IN «v»~|
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SECONDARY BENDING
STRAIN GAUGES 5E?C SHALLOW HECESS
LOAD TRANSFER
•£ '..••VPA5S LOAD •'/,/.•
-^SKSSKILI '//////T TOTAL LOAD
SECONDARY UNDING
WHERE
*« - AXIALSTRAIN
«b • •INDINO STHAIN COMPONENT
LOAD TRANSFER
LT
IS EXPRESSED AS THE PERCENTAGE OF THE TOTAL LOAD
«• »OTM SIDES OF DOGSONE
<=> SINGLE GAUGES
— GAUGES ON EDGE
d FASTENER DIAMETER
Fig. IJ Secondary tending and load transfer. Definitions and position of «;ra
'
'
I
an gauges
S! |~1 'HIIFJ I I llimj -TTTTTTTT] \ \ T TTrTT] 1 1 T TTTTT1
'"", ' ' MI ml i iumd.. i i mini Lxxxmi '• »0* HJ* Jo4 ,p*
CxCtEOlNGS FÜ iiOCK l?00 FLIGHTS)
ri«. I« FALSYAFF u»i »ftcttm
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32
Fi*. 15 Part of FAI.STAFF ••qiwtlCt
TOTAL NUMMft 0» CVCLU AT € ACH GUST LIVIL M« ILOCKO««0OC»LlOMT»
CUMULATIVE fRfQUCNCVPCKtLUCK Of 4000 F LIGHTS
Fig. Id The guai apci'irua TWIST
10* 10'
ST«US LIVIL
mht j»r-
200 -
110-
T—r i t»m» T- i t i > • i IT" -T T I t T
Ü
• 101« T?»l rtttutn
IIAlANf »tlMU 3
! Nil HI tO« 1.1 10 INI M
t MM T] OHNMQU A NIT »PL» Cvie iNf M
.^ ©
0Da~ -£-- A
'.00*-r 10*
t I 1 1 I -LlL 1 I 11 III. 1—t- I t 1 llli, I—I 1 111 !0* to
FLIGHT! TO FAUURI IFALJTAFFI
Fig. I? DpeO hole «peciaen aa£ Uo loaJ traß.fcr joint» - iweden
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33
-T T 1111 T f I I I Mil T—r-i i rrn 1—I I • ' ' '
350
300 STRESS LEVEL IMPil
©•
150
• »34-TJtl ANODIZI
»14-TMt PHIMER
• M7i-T7J»1 SEALANT •ROACH LOCKWLT
0
K
TMO-TTtBI
M*-TJi1
INT K> (i'n
•AMI
\[, ;I. 'if > FLIGHTS TO FAILURE (FALSTAFF)
STRESS LEVEL (MF-il
o-
200
ANOOI2I
1-hiMrH
HALANT
INI I l«-JI ,»«1
J 1.1 It Uli 10' 10* »•
FLIGHTS ro FAILURE IFALSTAFFI
_i_uil 1 L-i-l-LlAJ. .0» '
rig. I» Luw l"»«l trdBofei joint» - Kraiu-e
T 1 t T I Itlj » r
FLIGHTS TO FAILURE (FALSTAFF)
10* «»• CYCLES TO FAILUM
iCOHSTANt AM^LlTUOtl
ri*. W UJW 1O«4 irABiter }eiaca - fr*»«-« fig. 2! UJW luaJ irattmter joinl» - fraoco
![Page 40: AGARD REPORT No.721 Fatigue Rated Fastener Systems · 5.2 Corrdation of fatigue ... 14 Comparison of UK and AGARD low toad transfer joint design t.5 Correlation of fatigue »ves](https://reader033.vdocuments.site/reader033/viewer/2022051321/5af553757f8b9a190c8e2bfa/html5/thumbnails/40.jpg)
34
10J ,0» 10"
FLIGHTS TO FAILURE (FALSTAFF)
STRESS
LEVEL IMP«!
200
Fi». 22 Low load transfer joint« - F«d. Rep. of Cernany
-i r-T-'T 1 llll—
o "5"
rofo- RtAMl
itl 10* '«til
INT .'.•
ttALANT DM
MAM]
INT 40
CL i:
VU L I I I HI I I l I I llll
10* «>"
FLIGHTS TO FAILURE (FALSTAFFI
Fig. 21 Low load tranater joint» - FttC
FLIGHTS TO FAILURE IF ALSTAFFI
Fig. 24 Low load tranater joint» - FSC
»0 -
WO
STRESS
LEVEL <MJV
no
MO
IV,
100
-T r-T-TT»TT| T 1 TTTUtp f -i rrrrrn T—T T I I TTT)
o
ANOOl/IMU
MHMV St*'. AN I
Ml tO«
D.'. '
a» f* i»» f*
CW i«
B» M
CUM
J.,.1.1 t >1J i ml )' 10"
FL'äMTS TO FAILURE tF ALU A» Ft
r»,j. 2i L..-W imi www*« j«»in«* - it»»y
![Page 41: AGARD REPORT No.721 Fatigue Rated Fastener Systems · 5.2 Corrdation of fatigue ... 14 Comparison of UK and AGARD low toad transfer joint design t.5 Correlation of fatigue »ves](https://reader033.vdocuments.site/reader033/viewer/2022051321/5af553757f8b9a190c8e2bfa/html5/thumbnails/41.jpg)
35
STRESS LEVEL (MPi)
300 -
260 -
200 -
150 -
"1 1—I I I l l I I 1 1 I I I I I I
PRIMER
SEALANT
ANODIZING
PRIMER
SEALANT
Cg)
J I ' I I 111) J I I I 11II 10« 105
Fig. 26 Low
FLIGHTS TO FAILURE (FALSTAFF)
load transfer joints - the Netherhnds
"I 1—I I I I III
HI-LOK
PROTR.
STRESS LEVEL IMP.)
80
70
CLEAR 25-INT.76
CLEAR 63-266
10"
-I—I I I 11II
MINITWIST III
®
i i i i l i i 11 10s
J 1—1 I III 10B
FLIGHTS TO FAILURE (MINITWIST III)
Fig. 27 Low load transfer joints - the Netherlanls
I
STRESS LEVEL IMP.)
V5
Mill 1 1
, , I 1 1 1 I 1 III I i i 1111ii
Cg) _• O
_• •
•
7010-
T766I
ALOCHROMED
PRIMER
SEALANT
REAM HI-LOK CL13-«! REAM TAPERLOK INT 48-108 REAM HI-TIGUE INT 7«-127
REAM HUCKCRIMP CL 13-41
ORILL *HUCK CV* HUCK EXL INT 31-144 SPLIT SLEEVE DM • REAM HI-LOK CL13-INT J»
ACRES SLEEVE CW HI-LOK CL 13 - INT 13
250 AOARO DESIGN
• HlAM HI-LOK CL 13-81
SPLIT SLEEVE ON* REAM HI-LOK CL13-INT 39
200
^\
<3>.
i 11
STRESS LEVEL 200 (MPil
ISO ISO
too 1111 ,1 1111 ml i i 1111ill 10* io»
LOG MEAN FLIGHTS TO FAILURE (FALSTAFF)
Fig. 28a Low load transfer joints - UK
10" 10*
FLIGHTS TO FAILURE (FALSTAFF)
Fig. 28b Low load transfer joints - UK
JOO STRESS LEVEL IMP.!
200 -
ISO
~l »—1 M1I11 ~T T—t T 1 ITT
(USA)
• o"
"5" B
-TS OHUl RIVITJOM HANOtUCMO
MACH MUM»0 RIVET RNO MANO «00110
MACH SOutfltO
100 10
J—• I I I III 10
J L_l_
FLIGHTS TO FAILURE (FALSTAFF)
Fit. *• Low load transfer joints - USA
100
"1 1 I 1 1 I Til
ALOOINE
PRIMER
REAM HI-LOK INT 3 CD-
• rose irs*i rniMüM PRPS-A LT • 330
i»» FRFB-fl LT "41» a •
«to
imi ••It ALOOINE
PRIMER
REAM HI-LOK NT (0
i null 10*
-i—i • i i • HI 10»
FLIGHT'S TO FAILURE (FALSTAFF)
Fi*. J° Typ« D doubl« ahear joint« - Franca
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36
130 - STRESS LEVEL
IMP«) 120j-
110-
100 -
80
TTI 1 1—I I I MM 1 1—r~TT MINITWIST III
CD
• 20M-T3B1 ALODINE
PRIMER
REAM MI-LOK INT SO
• 7075-T7351
a m
70SO- T7S61
!• S
1-19
J_ü I I I I I I 11 10" "* " " 10»
FLIGHTS TO FAILURF MINITWIST Uli
Fig. 31 Type D double shear joints - France
STRESS LEVEL
(MPs)
1 i i i 111| i i i i i i rr
CS) INDIVID- MLT HLT
UAL TEST
RESULTS
Ml »M2 H.I • • 7060
-TT6
PRIMER SEALANT
FRFS-A 300 o • FRFS-B
250 -< • m fl^-o-
200 -< rfP* 8*
150
i
103 10* 1Ü* FLIGHTS TO FAILURE (FALSTAFFI
Fig. 32 Medium and high load transfer double shear joints - the Netherlands
STRESS LEVEL
IM») 1001
•o-
•0-
70
"1 1 1 TIMM
MLT HLT Ml ft Ml
1 1 I I I II
MINITWIST III
ANOOI«
PRIMER SEALANT
I 1 I 1 111 10' 10» 10*
FLIGHTS TO FAILURE IMINITWIST III)
Fig. Ji Medium and high load transfer double shear joints - the Netherlands
10* 10' FLIGHTS TO FAILURE (FALSTAFFI
Fig. 34 High load transfer double shear joints - United Kingdom
•
STRESS LIVIL iMf.i
»0 •
-»—t t I nn -»—r I T 1 I IT
• 20:« T»I ANOD1« ItHOACn
PRlMfR j
St ALANT 1
lOCKIOlT
• mi tt-at
o ni«-TWi
O nr» UM'
* rote it* TO» COAT 1
r FRFS-A
CD.
FLIGHTS TO FAILURE iFALSTAFfl
rig. IS Type C lap joint - France
T ! T III
• 70*0-TN PRIMER
St ALAN t
PUPS A
PNPS a
M0 STRESS LEVEL
( UK)
IMP.)
X •
700 V
ISO
m , , , Mini 1 lllil 10J 10*
FLIGHTS TO FAILURE (FALSTAFFI
Fig. 16 Q-lype joint - United Kingd«*
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37
I
ALL STRESS LEVELS 200 MP.
2024-T3 RIVET
7080-T73 RIVET
2024-T3 RIVET
7060-T73 RIVET
12024-T3 RIVET
70B0-T73 RIVET
2024-T3 RIVET
70SO-T73 RIVET |
2024-T3 gRILES
7060-T73 FLUSH HEAD
0 3/16
2024-T3
MATERIAL
THICKNESS
(INCH)
.083
01/4
0 3/16
FRFS-A
FRFS-B
70BO-T7S PRIMER SEALANT
PROTRUDING SQUEEZE
COUNTERSUNK
FOR STRESS LEVEL 160 MPi SEE RIGHTHANO FIGURE
I I I I I I
jn- j i 111111
200 <;
STRESS LEVEL
IMP.) 150 <^
10« 10" FLIGHTS TO FAILURE (FALSTAFF)
Ä
i i • i i I nl J I I I I I I I 10* 10'
FLIGHTS TO FAILURE (FALSTAFF)
Fig. 37 Type C2 lap joints - USA
"TRESS LEVEL IMP.)
1 1 T I I T 11! 1 1 1 1 1 1 1 1
• 7060 T76 PRIMER
SEALANT
FRFS-A
FRFS i
• . 0
»050
•ARE
T7i
1-3 2
ANODIZE
PRIMER
REAM HI-LOK SLIGHT PRESS
300 SLEEVE BOLT INT 64
(NL)®
250
"ST s 200 - -X_ J
150
100 1 4 I1
FLIGHTS TO FAILURE IFALSTAFFI
Fig. )8 1} dogbone joint» - the Netherlands and USA
STRESS LEVEL IMP«)
JOO —i— 1—r- IP TT
1 T 1 » • T M
0 M.-4 n ••»• O» INT-JB CHAR 10
• 0 »0*0 i;o
»Mrs A BUT tit »« 22 47
250 i«! 1 nut CLEAR I j*
CD uuu
V
A* o
%
IM
nl
0 \*1V )
10J 10*
I i IGHTS TO FAILURE (FALSTAFF)
Fig. it Single *he«r X joint« - Sweden
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38
FLIGHTS TO FA.LURE IF«LSTAFF)
rli. ,0 Type C doubl. shear Joint - France
FLIGHTS TO FAILURE (FALSTAFF1
Fig. 41 'i double shear joint - the He:herlands
I
rli. ,: «•»!« •— — ,l" reVef,e auuble do6bonc jp«elM«
![Page 45: AGARD REPORT No.721 Fatigue Rated Fastener Systems · 5.2 Corrdation of fatigue ... 14 Comparison of UK and AGARD low toad transfer joint design t.5 Correlation of fatigue »ves](https://reader033.vdocuments.site/reader033/viewer/2022051321/5af553757f8b9a190c8e2bfa/html5/thumbnails/45.jpg)
39
o o o LOAD
TRANSFER
AT EACH
FASTENER ROW
•87 20.2 33.1 FRFS-A
44.4 18.3 37.3 FRFS-S TYPE'Cr DOUBLE SHEAR JOINT - FRANCE
<o o 0> o LOAD
TRANSFER
AT EACH
FASTENER ROW
339 >1.3 19.3 2S.S FRFS-A'
41.7 14J 18.5 27.0 FRFS-r TYPE D" DOUBLE SHEAR JOINT - FRANCE
Fig. 43 Load transfer at each fastener row in multiple row double shear joints
!
FURCMASI COST
IU5 S/FiECE) 4
Fi». 44 Purchase cost per fastener (US $)
INSTALLATION
TIM« OF
FASTtNENS '
miNTitcc
FASTfNER TYM
MI-LO* LOCKSOLT iwimu>
WLOCKEOLT
FRO;
• F*t#A«IMC TIME
FASTtNER INSTALLATION
-WtTASUMSLT
Ot SUMMING.
ORlLUNO
CLAMFIMO
FUE-OMILUNC
Fif. tS Installation time ol Fat: ! astencr «yiteat
![Page 46: AGARD REPORT No.721 Fatigue Rated Fastener Systems · 5.2 Corrdation of fatigue ... 14 Comparison of UK and AGARD low toad transfer joint design t.5 Correlation of fatigue »ves](https://reader033.vdocuments.site/reader033/viewer/2022051321/5af553757f8b9a190c8e2bfa/html5/thumbnails/46.jpg)
"
I
40
INSTALLATION
TIME OF 18
FASTENER
(MIN/PIECE
TORQUE DOWN
INSTALLATION PIN
CHECK HOLI FOR RIFLING • Y SLEWING
DUPLEX HAND REAMER
HI-LOK HUCKCRIMP KI-LOK HI-LOK HI-TIGUE HUCKEXL IN IN TAPIRLOK
SPLIT ACRES SLEEVE SLEEVE
<>v HOLE CW HOLE
Yi-\. 46 Installation time of UK fastener systems
"*It,^%fe 300
STRESS
LEVEL
IMPn 7S0
200
T 1 I llllll 1—I ! ; 1 TTT
-
101 I—I llllll 1—I I I I 1111 . I i i i i ml i
10* 10*
FLIGHTS TO FAILURE (FALSTAFF)
Kig. 47 So load trainier and low load tratiilcr joint» - Frame
STRESS
LEVEL
r t
aa a Vi »000 SERIES Al
* N MULTIPLE LINE A« MUNtlSlON
y- CU*Vf MHO IftlERFtlUNCf
i 1 -
ij a 0OWMT*n
o ML
Sft» • UK
FRli ^n A F •
i K
JÜÜ
300 -
IK» 10000 t FAtlGUE LIFE (FLIOHTSI
Kin. 48 Aualy.ss o« U.T-revcr»e double dogbone /0O0 «eric» tpeiiaen*
STRESS
LEVEL •-MP,.
•oooooo
7000 SERIES Al
/ Ml» f IPLf LIME All Ht uHtSSlON CUftVE «P-O INTtHFlntNCI
<
\ •»
COUNTRY
o f
• rna 0 i
• USA
300
MO
1000 I0OO0 »
FATIGUE LIFE tFLlOMTVI
fig. 49 Analysis at LLT-reveree double dogboac 2000 series speciaens
![Page 47: AGARD REPORT No.721 Fatigue Rated Fastener Systems · 5.2 Corrdation of fatigue ... 14 Comparison of UK and AGARD low toad transfer joint design t.5 Correlation of fatigue »ves](https://reader033.vdocuments.site/reader033/viewer/2022051321/5af553757f8b9a190c8e2bfa/html5/thumbnails/47.jpg)
41
10* ,o» FLIGHTS TO FAILURE (FALSTAFF)
Pig. 50 Fit versus f«tigu* life, NLT and low load transfer joints, stress level 280 MPa
2«10J '0* to»
FLIGMS T( FAILURE (FALSTAFF)
Fig. 51 Fit versus fatigue life, Ni.T and I.LT joints, stress icvel 280 MPa
M0 TANGENTIAL
RESIDUAL STRESS
IM*"») 2O0
1 HOLf OlAMtTfR O 1X1 1217 1 INTfMMMNCf 0011 00*0 j
FASTfNER HOLE
I
Pi«. »J Tangeatial stress at fesietwr h-U .. a flMCllM ot the i„ter!er«B«e. (MM-VTW)
![Page 48: AGARD REPORT No.721 Fatigue Rated Fastener Systems · 5.2 Corrdation of fatigue ... 14 Comparison of UK and AGARD low toad transfer joint design t.5 Correlation of fatigue »ves](https://reader033.vdocuments.site/reader033/viewer/2022051321/5af553757f8b9a190c8e2bfa/html5/thumbnails/48.jpg)
42
360
STRESS
LEVEL
IMP.)
200-
160-
~\ I I I Mill I I I I I I III
m.
+ -$-
ALOCHROMEIfljAM PHIMER TA'ERRSAM SEALANT REAM
DRILLCW SPLIT CW ACRES CW
Hk±OK_
m$h
~ I I i nil
CLEAR. 13-t-l
Hl- HUCKCWlM»
HJ^ -LÖS
we* TJ
IWT. M-144
«ft EMM
@-
J I I I I I III I I I I I 111 I I I I I I 11
10* 10' 10» 10«
FLIGHTS TO FAILURE (FALSTAFF)
Fig. 53 Log mean fatigue lives of low load transfer and double shear specimens - UK
360
STRESS
LEVEL
(MP.)
200-
1*0-
"I 1—I T T Till r i 1—i i i r T r
A\LLT A MLT ALOCHROME PRIME*
»t>LAWT DRILL CW HUCKEXL INT H-144*
• LLT 0 MLT REAM HI-TIGUE INT 76-117 |
®
100 10
-J 1—I I I I I II 1 1—LI I I III 1 1—1 1 M.L 10* 10*
FLIGHTS TO FAILURE (FALSTAFFl
Fig. 54 Kdliguc lives of low 'ad tranater and double shear joint» - UK
STRESS
LEVEL
IMP.)
140
I»
120
,00
~f »—I T « T T Tt r r TTTTTTT ? 1—T~r T H
MINITV» ST III
10'
ALOOINI 1-MIMtM JfALANT
CD
j—i—i i i i tt, i 10' 10*
FLIGHTS TO FAILURE IMINITWIST tin
10«
Fig. 55 Fatigue live« of low load transfer and double shear joints - France
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FLIGHTS TO FAILURE (MINITWIST III) FLIGHTS TO FAILURE (MINITWIST III)
Ht. 56 F.ti8ue liv., of luu lMd transfer a„d doublo shcar ([ype D) sp8c.Ben _
T 1—r-rr-r
IX) -
100 STRESS
LEVEL
IMP,| 90
70
MINITWIST III
• LLT MM ANOOIZf
IIALANT
OM Ml-LOU a MLT
0 MLT
A. * I 111. -J 1 1 I I | |,j 10» ,0.
FLIGHTS TO FAILURE (MINITWIST Mil
fig. 17 Luw Jo4d uailir, Mjiu. »4 high lo*d tr».?„ double »hear joints - the Nether Und»
FLIGHTS TO»AHUM IFALSTAFF
tit. 1» Siii*le «ht*r an4 double »!>e«f tor« pro« r sake apciaeai
![Page 50: AGARD REPORT No.721 Fatigue Rated Fastener Systems · 5.2 Corrdation of fatigue ... 14 Comparison of UK and AGARD low toad transfer joint design t.5 Correlation of fatigue »ves](https://reader033.vdocuments.site/reader033/viewer/2022051321/5af553757f8b9a190c8e2bfa/html5/thumbnails/50.jpg)
44
180
1.40 •
1.20 -
1.00 SECONDARY BENDING AT
FATIGUE TEST STRESS 80
LEVEL
80 -
40 -
20 -
1 I I II ill 1 1 1—i—r-r-r-i
FATIGUE TUT STRESS LEVEL
• isoMft 0 300 Mf.
0 MOM*,
NOT REfREUNTATIVE (TYU a\
FATIGUE TUT WITH
SB ME ASUMME Hit
WITHOUT
UNDING
RESTRAINT
NOMINAL VALUE OF SI
FLIGHTS TO PAILURE IFALSTAFF)
FIR. *9 Fatigue life verm» secondary bending for a-'ngle »hear core progranme specimens having FRKS-A or IRFS-B
11827
8000 TOTAL
DIRECT COST n* ion
FASTENER 1000 INSTALLATIONS
mm
T i r—r-r-r-ri 1 1 1—m TT
EASTINf N SVflTf M
TV« H} OOUSLE SMEAR JOINT
TAMRLO»/INT «I IM
»UT «LttVE CWlCL IS-IWT I
«»HOW. I] ill I]
NI-TtOUS/INT l«-1TT
^s.r*R*>*W I»-« "Ut* 4»U*T * <«
m toncc M «i
,0* -J J- * .»• » «• *-4.i -.—. i ., i i. 1.1 i , _|_
.0« •J—I—I 111
»' ,0«
E'lQMTS TO FAILURE iFALJTAMl
Fig. 40 Log steAB ta;jgue .if* »erw. total iitett ~ost per 1000 fastener instalUt i«u
![Page 51: AGARD REPORT No.721 Fatigue Rated Fastener Systems · 5.2 Corrdation of fatigue ... 14 Comparison of UK and AGARD low toad transfer joint design t.5 Correlation of fatigue »ves](https://reader033.vdocuments.site/reader033/viewer/2022051321/5af553757f8b9a190c8e2bfa/html5/thumbnails/51.jpg)
45
TOTAL DIRECT COST
PER 1000 FASTENER
INSTALLATIONS
(US$1 5000
4000
2000
1000 -
1 i—i—r i MI
LOW LOAD TRANSFER JOINTS
SrLITSLMVECW-UK
ACRES CW - UK
ITALY MO MS*
LOCK10LT/1NT 41 - FUG
UK RESULTS 164 MPi
Hl-T )OUE - UK
MUCKCRIMf - UK HUCKIXL-UK
TAPERLOK-FRG
•OLT + CW/IMT -I MI-LOK
WWIT-l-pp 1/^ SYSTEM«/ JjJ «If / CL*INT L ( '
ITALY. 2CO Mfa
-I 1 L I 111!
FRG. 3S1MP. FFtG. »IM
-» 1 1 L...1 III] 1 | I I I I '° 10J ,o«
FLIGHTS TO FAILURE (FA_3TAFF)
fit. 61 LoS mean Eatigut life versus total direct coat per 1000 fa.tener installation*
HI-LOK/CL 13-61
TAPERLOK
HUCK-EXL
HI-TlGUE
HUCKCRIMP
MI-LOK «CW
sza.
Hl LOK • ACRES CW Z553
SI
*3
TYPE MJ DOUiLE SMEAR JOINT
l»I MPs :MM»,
22L
Z3L
-A -J 1 , 1 L_ 0 10 ?0 30 40 50
COST r IR f t .GHT . !HÜi^££L£«lii* fllGMtSfO^AILUdl
00
FiS. 6.' C«paii»o« »f can per IOOO faaleaer inst.,1 lat i«ma relative the »«*«, of flight. ,o fai'u«
Hl LOKtL 13 «I
TAPfRLOK
HUCK-tKl
HI-TlOUf
HUCKCRIMP
HI-lOK.CW
NI-LO* »ACRES CW
prr—T7—-n S2L
=3
• —» '-".va.
t/M/A, * ' 1 , I.
COST PfR f LICHT-
30 40 M
H»Al ftrMCT CO«t . 108
*li6HTI!0»*iLu*t
10* IOAO !h»l,i.in JOINTS
BIMUf. Ml».
»i«. 41 CwrarLoe »f CM! per IOOO tait.ner LuCalUttoM related i„ «»«, Ilutfc#r „f «a^, ^ ill-»,. to failure • '
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46
ANNEX I
OBJECTIVES
DETERMINATION OF FAT.GUE LIVES FOR A flANGE OF FAT.GUE RATED FASTENER SYSTEMS AND M ..*R.AL
IN COMBINATION WITH HOLE PREPARATION TECHNIQUES
ESTABLISHMENT OF COST FIGURES IN RELATION TO FATIGUE PERFORMANCE
IDENTIFICATION OF THE PRIME PARAMETERS INVOLVED IN FASTENER SYSTEM SELECTION
DEVELOPMENT OF A REFERENCE DATUM FOR THE COMPARISON OF TEST RESULTS PRODUCED IN
DIFFERENT COUNTRIES USING DIFFERENT SPECIMEN GEOMETRIES
DEVELOPMENT OF EXPERIMENTAL METHODS FOR FASTENER SYSTEM FATIGUE RATING
'
Fig '-' ACARD SMP working group on fatigue rated fastener ayatt
EACH PARTICIPANT IDENTIFIED MIS OWN PROGRAMME (ACTIVE OR DESlREOl
A COMPOSITE TEST MATRIX HAS MEN CONSTRUCTED FOR DIFFERENT TYPES OF JOINTS
- NO 10AU 1RANSMH Sri, lUt US
- LOW LOAO fHAMSl 11! 1KUIMIM IHtVtHSC uouBlf DOOaOMII - DOUBLi SM1AM irtCIMtNS
- «INULf INI AN iftClUtHt IMCONOAHY atNDINCl
MAIN VARIABLES
• ALUMINIUM AlLOYl
• FAVMIUSUftFACf THtAIUiNl • MATtMlAl lirii.li«
• •AStf.tn S.sltMl INCUMaiNAflONWirnMl • MOlri fNtrAHAIlUN ttCMMIUufl
• FALlTAM /MtNltWlgt
• LOAD ItVrSU
FATIGUE RATEOFAJTENtR SYSTEMS PROGRAMMS
• *:.. -,.••••. • u* r«Oä«*S«Mt» tU tllMlftATC: UMMCtHAH* , .**•,** I KM ANU 10 MIM a*»» -•- E«A| . rr. ,.-.,M . . -. t"A-.t
• ALACO* A BMMJU Müll motmmcmt* A«Maw.lftt.ktafb«l,a,utt tVAVUA»f.O ANu UJMr AHrt l>
• *AUOut LlvUmil M tvAiuAftuiait»«M»u»
- mat AiiAiK» coat» a» tut #AjttMta trait« - * MT««* IXItM AS: »Ol* r-tf«,!^ »aCMÜiau* uteD - . • ••- A • . N Ctt - „c . A • • „ t CMA6» «.If lAlftX, »•«*»
F ifi. l"l Wrltiod» atri arraiu uf *,.eUBA>l i llakcal
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47
\
NO LOAD TRANSFER JOINTS
• TESTP«OGRAMMES:PERTHEPART,C.PANTSSTANOARDS
-PARTICIPANTS ..... -MATIR.AL «ANCEANDSWEDCN
-mmmvmrn imumm T* ""' ' ~ PASTINIR lYITfM
;olTl.„f,wocw M«. WW^AU.0
- HOtf QUALITY •' PART.C.PANTS STANDARD
- LOAD LIVil "" •* 'A"TIC"*NT* «TANDARD *» MP. AND 35, « „p.. 0BOS$ A„A JTRf u (MUTM#(
# WEASUREMENT0FF,T*ND^«^En0UGHNESS(EACHH0L£,
• LOW LOAD TRANSFER JOINT«:
• TEST PROGRAMME
- MATIRIAL
- INTSRMY SURPACI TRJATMINT
-'A«T|NIRSYJTtM -PIT
-NOLI QUALITY
-LOAOLIVIl«
W10-TTM1 i,. 5mm, Pfl UJI
H. LOS. «eit.csK
CLIAHANCt. PER UK STANDARD
• *«AMSO.P€Ro<STANOARO
1;C0LDW0R«D.R|AM,D.riR OK STANDARD « UP. AND *0 MP. NIT SICTION STRISS lf ALSTAPP,
im»«»! OP m AN0 SUBMCE R0UGHNess (£ACH HOLE)
.-rCRAPH,C,NVfSTlGATI0NT0ES SHSTAT.ST.CAL^ATIO.C CRACK 1NITIATI0N
• DOUBLE SHEARJOINT«:
• TISTPROGNAMMFS
»MRIt Of SIGNS 1100 T B'IUB«»
OAO L..LS JiZmSSSSTSi" ""—• « ****** Uf *MU ' ' '"«• *«" SIRfH ,»ALSTA»*| • «...»«« raco„(lAr( „„ ,(JULIJ w 01„,Mweou>mi|)
-PAAflCll-ANfS -MATtNlAL
- «TtWAv Su«»ACI raiATMCM -»AJUNtRJV.ftW«
-lOAÖLtVlU
twfbcN OK TN» NITN(HI.ANOS
»•»-»»•II,!«-.!
*PO.* PR.«« AND «TIM«, „ALANT «,-,«,. 0
• «••-LOK CHARANtt.RCAMfOMOLI
ss&slaÄ-ssa- • «A^MM.HTO, ,„ ^0SU„AC| HOuOMNtsaj(ACMHOi|i
SrW^-W^---^-nOT^B^Tww^cw-itT(AT(ag
'ifi. 1-1 r,liSue r •ted fMI rt" »'»stmme. :Umm*ty
v
i
lu be H
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4,S
I
0 SINGLE SHEAR JO.NTS
• TEST PROG KAMMES A RANGE OF HIGH LOAD TRANSFER SINOLE SHEAR JOINTS WILL BE TESTED
- FRFS LOAO LEVELS 180. MO AND 2S0 MP. (SEE TABLE 121 GROSS AREA STRESS IFALSTAFF)
• CORE PROGRAMME TO EVALUATE A?JD COMPARE OIFFERENT HIGH LOAD TRANSFER SINOLE SHEAR JOINTS.
TESTS ON SINGLE SHEAR JOINTS ANO THEIR DOUBLE SHEAR EQUIVALENT DESIGNS THE DOUBLE SHEAR
EQUIVALENT DESIGN IS A SIMPLE DERIVATIVE OF THE SINGLE SHEAR SPECIMEN:
THE ASYMMETRICAL SIDE*LATE IS REPLACED BY TWO SYMMETRICAL
SIDE PLATES OF THE HALF THICKNESS THE DOUBLE SHEAR SPECMEN
HAS NO SECONDARY BENOINO.
• PARTICIPANTS
• MATERIAL
• INTERFAY SURFACE TREATMENT
• FASTENER SYSTEM
- LOAD LEVELS
USA FRANCE, SWEOEN. THE NETHERLANDS. UK
70SO-T78 It • 5 mml (IF NECESSARY MATERIAL SHOULD BE Mil LEU
DOWN TO 2 8 mml
EPOXY PRIMER ANO INTERFAY SEALANT PR-I43I -0
. HI-LOK. CLEARANCE. REAMED HOLE
b HI-LOK. INTERFERENCE. COLO WORKED HOLE. REAMED
c OPTIONAL HI-LOK. INTERFERENCE, REAMEC HOLE
180. 700 AND 280 MPi ISEE TABLE A2I QROSS AREA STRE» IFALSTAFFI
• MEASUREMENT OF LOAD TRANSFER AND SECONDARY BENDING OF TEST PROGRAMME - ANO CORE
PROGRAMME SPECIMENS USING STANDARD PROCEDURES MEASUREMENTS ON EACH COMBINATION OF
SPECIMEN DESIGN ANO FASTENSK SYSTEM
• MEASUREMENT OF FIT AND SURFACE ROUGHNESS (EACH HOLE)
• FRACTOGRAPHIC INVESTIGATION TO ESTABLISH STATISTICAL INFORMATION OF THE CRACK INITIATION
SITES
Kie. l-l ConeluJed
Q FIRST DEFINITION OF PROGRAMME CONTENT {
AUHtEMENI ON -RtXiHAMME '.>•.:;•.! ETC • CONFIRMATION Of COORDINATION ARRANGEMENTS
[ ""' 23 **ocu*IMM-,'T °* C0** PROORAMME MATERIAl
! '"" I \ """'W^ "E TAILED PROGRAMME OESCRlPTlON
O FINAL OlSCUSSlON OF .ME PROGRAMME
(- ••-,: "\n ' ' -."•• • •,
I AUHlCATlON OF CORE PRUGRAMME SPECIMENS
FATlGuE TtillNG
0 PROGRESS REPORT »Q*rANEi MEMBERS
I A TEST HEiULn AVAILABLE
O E »CHANGE ANO OltCUSÖlO* OF RESui II
I i ANALYSIS OP DATA iCOOROMATORl
4'-n»r- REPORT CIRCULATE!» FOR COMMENT
Q FINAL SESSION
PUBLICATION 0# REPORT A
fig. '"» Schedule and •üeitaoe» {or cbe FtfS pro6iaR»c
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TABLE I-I Number of specimens for different load levels of the
double shear joints core programme
LOAO LEVEL
(MP.I
FASTENER SYSTEM
HI-LOK. CLEARANCE. REAMED HOLE
HI-LOK. INTERFERENCE. REAMED HOLE
HI-LOK, INTERFERENCE. COLD WORKED AND REAMEOHOLE
NUMBER OF SPECIMENS
200
280
280
3
3
(3)
(3)
13)
(3)
3
3
(3)
•
!
I OPTIONAL
TABLE 1-2 Number of specimens for different load levels of the single
shear joints / double shear equivalent Cot* programme
FASTENER SYSTEM
HI-LOK. HI LOK, HI-LOK. SPECIMEN LOAO CLEARANCE. NTERFERENCE. INTERFERENCE.
DESIGN LEVEL
IMP»)
REAMED HOLE REAMED HOLE COLD WORKED AND REAMEOHOLE
NUMBER OF SPECIMENS
150 3 (31 3 SINGLE Si I All
JOINTS 200 3 (31 3
260 I3l (3) 13)
150 3 (3) 3 DOUBLE SHEA»
EQUIVALENT 200 3 (3) 3
250 131 (31 (3'
150 131 131 «31 1 1 : DOGBONE
1 'ft MINIS 200 3 (3) 3
250 3 (3) 3
150 (3) (3) 13) DOUBLE SHEAR
EQUIVALENT 200 3 13) 3
250 3 13) 3
( (OPTIONAL
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50
ANNEX 2
ORIGINALLY PUBLISHED AS: APPENDIX A/FRFS/NOV. 1981
FASTENER SYSTEMS
Three fastener systems are selected for application in two core programmes of the Fatigue Rated Fastener Systems programme (see reference 1). Basically the fastener systems are as follows:
fastener system hole quality fastener fit
+ clearance
- Interference (mm)
FRFS-A FRFS-B
FRFS-C -OPTIONAL-
reamed cold-worked (3 X) and reamed
reamed
Hi-I.ok, CSK, 0 6. 33 mr.
• .020 ' -010
- .025 * -010
z .010 - .090
The fastener type selected, hole production procedures, interfay surface treatment and installation proce- dures are described.
Fasteners
All fasteners to be used are cadmium plate steel Hi-lok H1.-19-8-7 together with HL-70-8 collars The coding HL-19-8-7 refers to:
HL-19: pin part number - 8: 8/32 inch or 6.35 mm nominal diameter pin - 7: 7/16 inch or 11.11 mm maximum grip length.
The collars are made of 2024-T6 aluminium alloy;
the coding - B refer* to nominal thread size of 8/32 inch or 6.35 mm. The nominal diameter of the pin is 6.35 mm; the specified minimum and maximum diameter are 6.312 mm and 6.337 mm respectively. However, practice shows that the pin diameter is between 6.325 and 6.337 mm.
Fastener holes
Table 2-1 gives the hole preparation for each fastener system. Nominal tool diameters should be selected very cirefully by eacn participant to arrive at the required fit. The cylindrical parts of all fastener holes must be reamed as a last working procedure. Countersinking is done after reaming of the cylindrical parts of the fastener hole*. Dimensions of the countersink are given in the following figure:
Dimension» of the countersink
After countersinking all hole edges at interfaying and break out surfaces, .xcept the countersink, are lightly debufied.
As indicated earlier the fastener system B is an Interference fit Hi-lok in a .old-worked, reamed hole (see table 2-1).
The holes must be cold-worked using the Split Sleeve Cold Expansion Process (CX) of Fatigue Technology Inc.. USA; detailed Information about the hole production Is given in the following (see also reference 2) The starting holes shall be reamed to dimensions as given In table 2-1; these dimensions correspond with those of reference 2. ll a cutting fluid leave» an excessive lubricant reildue in the hole, the residue must be removed before split sleeve cold expansion. The major and minor diameter of the mandrel are given In figure i'-l. The mendrel major diameter Is allowed to shrink or wear a baxlc.ua ot .015 a« (.0006 Inches) tro« the nominal diameter before replacement Use oi a reamer with a ton-cutting pilot is required as a quality control measure to ensure that all holes are cold expanded prior to post siting. The pilot diameter will not fit Into a starting hole, but will fit Into a cold expanded hole.
The cold expanded hole has an axial 'Idge which corresponds with the position of the split In the sleeve. Post siting is required to clean up the hole in order to provide the desired fastener fit. The maximum metal removal la limited to 10 t of the nominal hole diameter or 1.575 am (0.062 laches) whichever is less.
The KTl process specification allows that the finished hole contains a region near the entry, exit ot Interlace which does not totally clean up during the posi siting opera.Ion. The hole will be acceptable providing the region does not exteud axlally by more than . 50B am (.O'O Inches) or 10 t of the detail thickness, whichever Is less.
Machining of countersinks shall be performed after po«t sice reaming. All hole edges at Interfaying and break out surfaces, except the countersink, are lightly deburred.
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51
Faying surface treatment and assembly of specimens Common to all participants of the Double Shear and Single Shear Core Programmes is the scheme of faying surface treatment and wet installation of the fasteners. Following machining, hole production and measurement of all holes (see reference 3) specimens will receive a faying surface treatment as follows:
cleaning (degreasing) with suitable solvent; application of epcxy primer, except in countersunk holes, to a dry film thickifess of .05 - .13 mm; cure primer; upon assembly the faying surfaces of the joint specimens will be coated with Products Research and Chemical Corporation (PRC) PR-1431G or equivalent. The sealant is applied using a standard short nap paint roller (see PRC Interim Technical Data Sheet for the PR-1431-G corrosion inhibitive sealant); no topcoat is to be applied to the specimens.
i
References
1. Van der Linden, H.H., AGARD SHP Working Group on FRFS, Revision C, July 1981.
2. CX Process Specification: Cold Expansion of Fastener and other Holes using the Split Sleeve System, FT I 8101, Fatigue Technology Inc. Draft, May 1981.
3. Measurement of fit and surface roughness, Appendix B / FRFS, August 1981. Also as Annex 3 of this report.
I TABLE 2-1
Fastener systems
FASTENER SYSTEM CODE FRFS-A FRFS-B FRFS-C optional
Hi-LOK HL-19-8-7. nom. dia 6.35 FASTENER min. dia. 6.312, max. dia. 6.337
practice: dia. 6.325 - 6.337
PREDRILL X X X DRILL X X X REAM X TO: 5.71 - 5.79 mm X COLD WORK 3 %
split sleeve process
(CX) of FTI REAM X
COUNTERSINKING.
DEBURRING OF ALL HOLE EDGES, except the countersink
MEASUREMENT OF FIT
INTERFAY SURFACE TREATMENT - cleaning
- epoxy primer - sealant PR-1431-C
WET INSTALLATION OF FASTENERS (PR-1431-G)
FIT + clearance •.010 i.OlO t.010 -interference + .020 -.025 -.090
(dimensions in mu)
MAJOR DIAMETER MINOR OIAMETER
MANDREL
ATTACHMENT
FASTENER SYSTEM!
Ml 1TANOARO TOOL NUMiER «-J-N
«« MANDREL MAJOR OIAMETEH 6 «64 " 0'
MINOR 01AME TE R i 2 ÖJ * °
SLEEVE DIMENSION
THICKNESS ISl"
Fig. 2-1 Split sleeve cold expansion mandrel
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52
ANNEX 3
ORIGINALLY PUBLISHED AS: APPENDIX E / FRFS - AUGUST 1981
MEASUREMENT OF PTT AND SURFACE ROUGHNESS
Bremen. . . . - ,» The procedure is as follows (see table 3-D
* Each Specimen; - specimen identification; - identification of the fastener holes.
* ^l—rS^two diameter (perpendicular) on the top side of the specimen, calculation of the
^ SÄ two diameters (perpendicular) on the bottom side of the specimen, calculation of
the average value; c average figures found under a and b; d measure the fastener diameter (twice), e calculate the average fastener diameter; f establish the fit.
&^££Z££U<2& * characterized using in house eouipment.
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53
TABLE 3-! Measurement of fit and surface roughness
I
Me
Ho*
Na
HW.O.. 0 m. HMD. »to«. * FmwDit 0 -., MM,
Rc**h Not«
• 3 MM»»—!»! A~«
1 I Awa» Awrap t 3 m—MM A«. InMfl. CtMTMC*
TABLE J-2 Measurement of fit and surface roughness. An example
•M
Ma
WtWfH HMO. »,_„- > • •MO» * r«
••i
«•>*• MM»
1 1 Anaiaja •'• , ,' »•» •"• 1 1 III» HI I 1
us • ni
!-•" f—
• 1 A
• UK
»Ma
»II
• 311
»Jll
• 310
*1K>
• lit
•11«
«111
• 111
UM •JM
Oil
• IK
• 111
• 111
•ni • •I*
• an
—
to-, mr —-. A««««
L~_ . 1* L«U7L-IiL: •««... ; M-^=±*=
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ANHEX 4 „.„AMCFFR
*„r the determination SUMMAKV r Sy8teM Program a procedure for
It is strongly recommendea oy
- ass--1— •-" b) It, the case of joints gtde rf
figure 4-2. should be bonded. I...
t*«ss3?sr ~: -—- - •" ifZ 5TSSS-.. ••». .„. „ „ _.,....,,.....- - A^A m use strain gauge»
Further it 11 recommended to
pectlvely.
I
tM »^»:::;;:::::;:—- - - - of the pUte. (referencea 4. »> -8 »l
«...- |^Jt^-J^5r£^.rwrÄJ!Ä!^,'-» -—• re8idu.l ^4ür he -e.-«re-nt ahould be repeated -ft«
,) Note: The loads ifflH* »«• teat».
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\
i
SS
Results of the first load cycle are given in figure 4-5.
Also stabilised load-elongation curves were obtained: an approximate linear relationship waa found (figure
3. DETERMINATION OF LOAD TRANSFER
In Joints load is transmitted from one plate to another at each fastener row. The determination of load transfer is based on strain measurements during loading and unloading.
The position of the strain gauges, the definition of load transfer and load application are described in the following.
3.1 Position of the strain gauges
The position of the strain gauges is given in figure 4-6. At site 'a' the total (axial) load, carried through the joint, il .vnasured. At site V the bypass load (figure 4-7) Is measured.
The variation in load transfer over cross-section "A" is establishes using a number of strain gauges; the position of the strain gauges is given in figure 4-6. In order to e\rlude the effect of secondary bending loads the strain gauges should be bonded on opposite sides of ttw pi»it. Shallow recesses should be manu- factured in the opposite plate to accommodate the interference gauges) and wires; the dimensions of the shallow recess are given in figure 4-1. The dimensions of the strain gauges are given in section 2.1.
3.2 Definition of load transfer
Load transfer is defined as the load which is transferred from o:.e plate to another. That part of the load which is not transferred is called the bypat.tt-.ig loud. Load transfer and bypassing load are given schematically in figure 4-7.
Load transfer -in most cases- is expressed as the percentage of the total load each fastener row transmits (reference 4); therefore the percentage of load transfer is given by:
axial load site 'a' - axial load site 'c' ... , axial load site V.' x ,0° Z
I*
I I
3.3 Load application
The procedure is Identical to the one used in the determination of secondary bending; therefore see section 2.3 of this memorandum.
4. CONCLUSIONS
Procedures for the determination of secondary bending and load transfer, based upon the usage of strain gauges have been described.
The strain gauge measurements are carried out at a number of steps under static loading. From the measurement the secondary bending ratio and the percentage of load transfer can be derived.
5. REFERENCES
1. Heath. W.O., Fatigue Rated Fasteners. ACARD SMP. Sub-Cotnlttee Report. Fa.'.l 1980.
2. Van der Linden. H.H.. Working Croup on Fatigue Rated Fastener Systems, Revision C, July 1981.
3. Schütz. D. and Lovu;k, H.. The Effect of Secondary Bending on the Fatigue Strength of Joints. Laboratorium für (Ittr.lbsf.Stlgktit. Report FB - 113 (1974). REA Library Translation 1858.
4. Perrett, B.. Some Measurement» of Load Transfer and Secondary Bendlnj In Fastener - Joint Specimens for the Proposed Evaluation of 'Fatigue Resistant' Fasteners. REA Tech. Memo Structures 950.
5. Jarfall. J., kevlew of Some SweJlsh Works on Aeronautical Fatigue During the Period May 1973 to April 1975. FFA Technical Note No. HE-1684.
Also in: Minutes of the Fourtheenth Conference on the International Conference on Aeronautical Fatigue (ICAF), Lausanne, 1975, ICAF-Document No. 800.
6. Schütz. D.. Fran». J. and Cerhari. J.J.. Der Einfluss der Lasiübrrtragung auf der Schwingest igkelt von Fugungen mit Schubbeanapruchten Befestigungselementen. Fraunhofer Institut für Betrlebsleatlgkell (LBF). Inslllutdveröffentllchungen. Heft 9. 1980. pp. 141-15*.
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5ft
TABLE 4-1 Values of load transfer and secondary bending ratio
Specimen type Specimen number Max. load (MPa) Min. load (MPa)
I of the maximum load
in FALSTAFF
Secondary bending ratio
X load transferred
0 16.7 33.3 50 66.7 83.3 100 83.3 66.7 50 33.3 16.7 0
minimum load 0
'.ANGiNT TO THE SHAFT OF THE FASTENERS
SECTION A - A
SHALLOW RECESS (WIDTH is
Kig. A-I Position of «train gauges in secondary bending measurement» in joints witli several fastener-, in a row
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57
SECTION A - A
TANGENT TO THE SHAFT OF THE FASTENER
H STRAIN GAUGE
Kswww: f.vw.N
d-SHAFT O'AMITFIS
Fig. 4-2 Position of strain gauges in secondary bending measurements with one fastener in a row
STRAIN GAUGE-
Fig. 4-3 Definition of secondary bendir
1
•H
i_.
••l-tl CMC. WATtHl*,
3 1*4 1
FAIUNtW
MUCKKXT. CTWl
'ig. 4-4 Single »her lap joint used Ut steä.uresteui oi tfeoaiart bending (fei f, i) - Sot (he KRIS procedure
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58
ZERO POINT FOR STAblLIZEO MEASUREMENT
Fig. 4-5 Relationship between measured elongation and external load; single shear lap ioint (fits 4 4) (Ref. 4.3) *
•-HH j
u STRAIN GAUOI ON UN« Slut OF IME SHEE1 ONLY
• STRAIN GAUGES ON »OTM SIDES OF THE Mill 1
- STRAIN GAUGE ON EDGE OF THE SHEET
PERCENTAGE OF LOAD TRANSFER u. FASTENER
RO¥ I IS GIVEN HI
AXIAL LOAD SITS AXIAL LOAD SITE
AXIAL LOAD SHE
Tig. 4-6 Determination oi the percentage of load transfer
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59
ANNEX 5
RESULTS OF THE MEASUREMENTS OF SECONDARY BENDINC AND LOAD TRANSFER
Thla section presents the full datalla of the measurements of secondary banding and load tranefar. Tabla 5-1 to to 5-18 presents the valuaa of secondary banding and load tranafar aa raportad by tha partlci- panta.
Figure 5-1 to 5-3 praaant graphically tha aacondary banding and load tranafar aa function of tha applied load. Tabla 13 of tha naln aactlon of thla raport sunmarizes tha valuaa of aacondary banding and load transfer. 1
TABLE 5-1 Valuaa of load tranafar and aacondary
banding ratio - Franca
Specimen type REVERSE DOUBLE DOCBONE Specimen number 7-1 2024 "Camat D" - H1-L0K
REAM; INTERFERENCE 80 urn Alcdine 1200, prla»r + PR1422
Max. load (MPa) 250 Mln. load (MPa) -54
Z of tha Secondary I load maximum load bending transferred In FALSTAFF ratio
SB1 SB2
0 .409 .249 _ 16.7 .359 .231 8.7 33.3 .333 .211 7 50 .314 .193 6.4 66.7 .295 .177 5.8 83.3 .273 .159 5.3
100 .256 .150 4.9 83.3 .277 .161 4.3 66.7 .298 .174 4 50 .322 .192 4 33.3 .342 .215 4.1 16.7 .366 .240 3.9
0 .397 .254 _ minimum load .370 .234 -10.4
0 .371 .241 -
LT - M., - N
M~~"
« *M,
H • aaUl »train (mean) In top sheet
*4 i| - T
•+»
r^ U^
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6(1
f
'
„ , TABLE 5-2
'
TAIL* 5-3
IfMSn typ« Spcctiwit nuabcr "*•• load (MJ*a) Hia. J04d (Hfa)
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61
TABLE 5-4 Value« of load transfer and secondary
banding ratio - Franca
TABLE 5-5 Valuta of loid tranafer and secondary
bending ratio - France I
Specimen type TYPE C - FRANCE, HI-LOK. CLEARANCE 10-30 um, FRFS-A
Max. load (HP«) 200 Min. load (MPa) -53.3
X of the Secondary Z load
maximum load bending tranaferred
in IALSTAFF ratio
0 . - 16.7 1.37 48.2
33.3 1.45 55.4
50 1.42 55.4
66.7 1.35 54.8
83.3 1.29 54.3
100 1.23 53.9
83.3 1.23 56.9
66.7 1.26 59.5
50 1.30 62.9
33.3 1.32 68.3
16.7 1.28 84.5
0 - - minimum load -6.39 38.1
0 ~
Specimen type C, HI-LOK, COLD WORK, INTERFERENCE 15 -35 urn, FRFS-B
Max. load (MPa) 200 Mln. load (MPa) -53.3
X of the Secondary Z load
maximum load bending transferred
in FALSiTAFF ratio
0 . - 16.7 1.62 43.2
i3.3 1.68 42.4
50 1.64 41.2
66.7 1.57 41.5
83.3 1.49 41.8
100 1.42 43.1
83.3 1.45 45.5
66.7 1.49 41.7
50 1.53 41.3
33.3 1.57 39.7
16.7 1.58 38
0 - - minimum load -2.95 24.8
0 - " NOTE: without sealant
LI •W- i 1 r
FIGURE Stt lABlf i *
.
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62
TABLE 5-6 Valuta of load transfer and aacondary
banding ratio - UK
TABLE 5-7 Values of load transfer and aacondary
banding ratio - UK
Specimen type Q-TYPE, NON COLD-WORKED, HI-LOK
Specimen number 10 Max. load (MPa) 350 NET Hin. load (MPa) -107 NET
taat run. AFTER 20.000 CYCLES cycle nr. BETWEEN 0 AND 30 kN
X of the Secondary Z load maximum load bending tranaferred In FALSTAFF ratio
0 0 0 16.7 .245 34.0 33.3 .295 38.5 50 .360 42.5 66.7 .395 4S.5 83.3 .430 47.5
100 .440 49.0 83.3 .400 50.0 66.7 .350 48.0 50 .300 52.5 33.3 .260 54.0 16.7 .370 55.0
0 0 0 minimum load .360 40.0
0 0 0
Specimen type Q-TYrE. COLD-WORKED, HI-LOK
Specimen number 3 Max. load (MPa) 380 NET Mln. load (MPa) -85.6 NET
teat run. AFTER 20.000 CYCLES cycle nr. BETWEEN 0 AND 30 kN
X of the Secondary X load maximum load bending tranaferred In FALSTAFF ratio
0 0 0 16.7 .344 33.5 33.3 .442 33.2 50 .522 39.6 66.7 .547 40.9 83.3 .537 42.1
100 .528 43.3 83.3 .512 43.4 66.7 .493 43.3 50 .475 43.8 33.3 .471 44.3 16.7 .48' 44.5 0 0 0
minimum load .277 37.0 0 0 ü
CSK .i _ a no
üEpäz&zzzz ^Cf. •<-+••
flGUM III TA81I i-g
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63
TABLE 5-8 Values of load transfer and secondary
bending ratio - USA
Specimen type C2 SINGLE SHEAR Specimen number B1/B2 Max. load (MPa) 196.85 Mln. load (MPa) 0
test run/cycle nr. 4
X of the Secondary Z load maximum load bending transferred in FALSTAFF ratio
0 16.7 1.32 33.3 1.30 50 1.18 66.7 1.09 83.3 1.07 not 100 1.05 established 83.3 1.04 66.7 1.02 50 1.11 33.3 1.24 16.7 1.43 0
minimum load - 0 -see note-
secondary bending ratio for strain gauges:
1&2 3&4 5&6
1.37 1.34 1.24 1.37 1.31 1.23 1.23 1.20 1.12 1.12 1.10 1.04
1.08 1.09 1.04 1.05 1.06 1.03 1.09 1.03 1.00
1.03 1.04 1.00 1.12 1.12 1.08 1.27 1.25 1.21 1.45 1.44 1.4C
aee figure below
1 1
I
average of 6 gauges
>-< 1 i- NOT!:
STRAIN GAUGE
INSTRUMENTATION NOT ACCORDING TO
FRPSPROCEDURES
DIMENSIONS N 3
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64
TABLE 5-9 Values of load transfer and secondary
bending ratio - The Netherlands
Specimen type IS DOGBONE - FRFS-A Specimen number 3A1 Max. load (MPa) 60.5 kN Min. load (MPa) -16.2 ki<
cycle nr. 5 and 100
X of the Secondary X load maximum load bending transferred in FALSTAFF ratio
cycle 5 cycle 100 cycle 5 cycle 100 cycle 1000
0 0 0 0 16.7 .018 .041 25.2 25.9
33.3 .068 .018 23.7 24.7
50 .009 .027 23.8 23.8
66.7 -.048 -.005 24.6 24.6
83.3 -.094 -.055 25.5 25.1 100 -.126 -.095 25.8 25.7
83.3 -.082 -.058 25.5 25.5 66.7 -.041 -.028 24.7 24.3
50 +.019 +.001 24.1 23.1
33.3 .067 +.026 23.5 22.4
16.7 0
minimum load 0
.065 +.026 22.6 20.9
-.075 +.054 13.6 12.7
• f
I
TABLE 5-10 Values of load transfer and secondary
bending ratio - The Netherlands
Specimen type 1*1 DOGBONE - FRFS-B Specimen number 381 Kax. load (MPa) 60.4 kN Mln. load (MPa) -16.2 kN
cycle nr. 5
1 e the Secondary X load maximum load bending transferred In '.ALSTArr ratio
cycle 5 cycle 5 cycle 1Ö00
0 0 0 0 16.7 -.086 20.1 22. f. 33.3 .Oil 22.1 50 . M 22.1 66.7 .187 22.2 83.) .. o 2). J
100 . i 23.8 83.3 ..Ml 23.3 66.7 .ISO 22.9 50 .160 23.1 33.3 .060 23.6 16.7 -.02J 24.9 0 . - -
•inlaua load -.055 32.6 19.5 0 - - -
No data at cycle 1000 available
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65
i
TABLE 5-11 Values of load transfer and secondary
bending ratio - France
Specimen type Cl, HI-LOK, FRFS-A
CLEAR. 10-30 vi
Max. load (MPa) 250 Mln. load (MPa) -66.7
Z of the Secondary I lead maximum load bending transferred in FALSTAFF ratio
LT1 LT2
0 _ 16.7 43.9 68.2 33.3 44.6 68.4 50 45.5 67.5 66.7 46.1 67.1 83.3 46.5 67 100 46.7 66.9 8S.3 47.1 68.8 66.7 47.1 69.6 50 46.6 70.7 33.3 45.6 72.4 16.7 42.4 76.6 0 -
minimum load 46.2 62.8 0 -
f
NOTF: without sealant LTI >• x 100 c
t-t LT2 - x 100
i r
~\
i vitw A
+ •• •• -f- •• 4 m
+ — — + i» + tm
+ — • + o
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66
!
TABLE 5-12 Values of load transfer and secondary
bending ratio - France i Specimen type Cl, COLD WORK, INT. 15-35 urn
FRFS-B Max. load (MPa) 250 Min. load (MPa) -66.7
- Z of the Secondary Z load
maximum load bending in FALSTAFF ratio
LT1 LT2
0 16.7 43 33.3 41.9 57.5 50 41.7 59.5 66.7 42.8 83.3 43.7
100 44.4 62.7 83.3 44.4 63.5 66.7 44.4 63.7
44.2 33.3 43.6 62.9 16.7 38.2 58.7
0 minimum load '•4.6 | 58.2
NOTE: without sealant
FIGURE SEE TAILES-M
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67
TABLE 5-13 Values of load transfer and secondary
bending ratio - France
Specimen type D FRFS-A'
Max. load (MPa) 250 Min. load (MPa) -66.7
X of the Secondary X load maximum load bending transferred in FALSTAFF ratio
LT1 LT2 I.T3
0 _ _ _ 16.7 23.8 47.3 54.9 33.3 28.5 51.7 69.7 50 31.5 53.8 73.2 66.7 32.4 54.5 74.2 83.3 33.5 54.8 74.4
100 33.9 55.2 74.5 83.3 32.9 55.1 75.7 66.7 32.3 54.8 76.2 50 31.6 54.7 76.1 33.3 29.4 54.0 76.7 16.7 22.9 53.4 79.3 0 - - -
minimum load 54.0 62.6 88.7 0 - - -
!
x 100
NOTE: without sealant
A •
i Y- i i
| VIEW *
+ - + - + - +
+ - + - + - -K m - m -
+ • + m
+ • + FASTINfM
•f - + - + - + L JLLJ 1
© OlMCNf IONS IN >
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68
'
i TABLE 5-14 Values of loud transfer and secondary
bending ratio - France
Specimen type Specimen number Max. load (MPa) Hin. load (MPa)
X of the maximum load in FALSTAFF
0 16.7 33.3 50 66.7 83.3
100 83.3 66.7 50 33.3 16.7 0
minimum load 0
1). FRFS-B'. COLD WORK HI-LOK, Int. 15-35 um 250 -67
Secondary bending ratio
Z load transferred
LT1
46.3 44.1 42.9 41.8 41.7 41.7 41.1 40.8 40.4 40.8 39.2
LT2
57.6 57.1 57.1 56.6 56.4 56.5 56.1 55.7 55.2 55.5 54.A
LT3
67.2 69.8 71.0 71.3 72.2 73.0 73.2 72.7 72.6 72.6 72.4
NOTE: without sealant
fIGUREStf TABLE S-U
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I
69
\
TABLE 5-15 Values of load transfer and secondary
bending ratio - The Netherlands
Specimen type 14 D0CB0NE DOUBLE SHEAR Specimen number 4A11 FRFS-A Max. load (MPa) 250 MPa, 60.5 kN Min. load (MPa) -16.2 kN
cycle nr. 1000
Z of the Secondary X load maximum load bending transferred in FALSTAFF ratio
0 16.7 41.9 33.3 35.7 50 35.7 66.7 35.2 83.3 34.7
100 35 83.3 32.8 66.7 31.3 50 29.3 33.3 25.6 16.7 15.2
0 _ minimum load _
0 -
TABLE -)-lb Value» of load transfer and secondary
bending ratio - The Netherlands
Specimen type |!| DCXJUONK DOUBLE SHEAR Specimen number 4B11 FRFS-I Max. load (MPa) 250 MPa, 60.5 kN Hin. load (MPa) -16.2 kN
cycle nr. 1000
X o! the Secondary t load maximum load bending transferred In PALSTAKF ratio
0 . 16.7 47.5 33.3 47.3 50 45.9 66.7 1.3.6 83.3 42.0
100 40.3 83.3 40.3 66.7 39.8 50 40.4 33.3 41.2 16.7 42.2 0 _
minimum load 48.1 0 -
flL'JNl SEI TABU S-16
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70
TABLE 5-17 Value« of load transfer and secondary
banding ratio - USA
Specloan typ« DOUBLE SHEAR EQUIVALENT
Specimen number Dl-1 Max. load (MPa) 196.85
Min. load (MPa) 0
Teat run, cycle nr . 1
t of the Secondary X load
maximum load bending tranalerred
in FALSTAFr ratio 1 \l * 8lx 100 I 1 [3 + IP 10° *
0 - 16.7 1-77 - 23
33.3 1-67 - 33
50 1-59 - 41
66.7 1-55 - 45
83.3 1-52 • 48
100 1-50 - 50
83.3 1-51 - 49
66.7 1-53 - 47
50 1-57 - 43
33.3 1-62 - 38
16.7 1-68 • 32
0 - ml ill nun load -aee note-
0 -
etrain at gauge nr.
3 5 7 8
. . _ _ 191 192 146 148 405 404 267 279 628 628 365 381 853 855 468 471 1077 1083 564 562 1302 1312 648 652 1070 1085 550 552 853 860 457 453 630 632 357 363 407 408 248 255 196 196 133 132
•W- MOTE: STRAIN GAUGE IMIHUMtNTAIION NOT ACCORDING TO fafSPHOCtOURtS
®
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7!
Fig. 5-1 Secondary bending and load tran.ter of rever
200 300 APPLIED STREW IMP.)
se double dogbone specimen - France
0 100 I» APPl If 0 STRESS <l«>tj
fit- S-.'a Secoodaiy bending and load tranit
100 MO Mo
APPLIEO STRESS MM
er ui type C lap joint - France
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72
Q JOINT FRFS-A
—-— FRFS-B
-100 0 100 200 300
APPLIED STRESS (MPi)
0 100 200 300
APPLIED STRESS (MPi)
Fig. 5-2b Secondary bending and load transfer of the Q joint - UK
160
SECONDARY BENDING _ «
-\— T r i i -r
<USA>-
SB 1.20
* V- ^£*— 8U NOTE NO BINDING RESTRAINTS
USED DURING MEASUREMENTS
1 ._!.. ......1 1 1 1 1 0 100 200 300 400
APPLIED STRESS IMPil
Pig. Me Secondly bending of the type C2 lai joint - USA
i moooMM • HfS A
*" »MSB
SiCONOAAY
•ENDING U
«oh
®
4 JJM1 l***^*^
-100 0 100 100 900
APniiOSTNftSIMP«)
T
•0 (S) LOAO
1HANSMH " IT
(T.) «0 creti 100
0
«Cil 1000 "
1 1 — 0 100 200 300
AffL.t Ü STIICB IMP.)
fig. >-** Secondary bead it« and load er anal er o* li dot>ona joint - the Hether tanda
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73
• DOUBLE SHEAR TYPE FRFS-A
. FRFS-B
i
1 1 1 r
TVMgl DOUBLE SfltAR 3 2 3
i r
-i 1 1 i i i
l-'ig. 5-3a
'» 200 300 4(X APPLIED STRESS (MPi)
Load transfer of type Cl double shear joint - Frarce
LOAD TRANSFER
LT
(Z)
' i 1 1 r
gyrrriiua
—i—i—i ' i 100 200 300
APPL IE 0 STRESS (MPil
Fig. 5-3b Load transfer of type D double shear joint - France
T 1 -r
LOAD TRANSFER
LT
•Oh
4U
' '/3DOÜBONE DOUItE SHEAR (A
J 1 L -i -I 1 u 0 «M 200 300
APHICO STRESS IMP.)
rig. S-Jt Lua4 tcaaafw of ij «t^b«,« MI«
»heat joint - the Nether laud*
400
LOAD TRANSFER
LT
C) 80
1 I 1 T-
*
•^
-X 1 L. -L 1 U »00 200 300
APPLIED STRESS IMP,)
:
Fig. S-U Lu4. iranafer of typ, c.' double .he« joint - USA
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74
ANNEX 6
TABULAR PRESENTATION OF THE FATIGUE LIFE DATA
Th« complete sat of fatigue life <Ut« for the FRFS programme Is given it. table 6-1 to 6-21; the
framed numbers are the log mean life figures.
\
TABLE 6-1 Open hole specimen results - Sweden
OPEN HOLE SPECIMEN SWEDEN
MATERIAL HOLE
LOAD LEVEL (MPa), Flights to failure and log mean
FALSTAFF
150 180 234
2024-T3 t • 5 mm
0 6 REAM 83281 92355 25000
231000 124539
6372 5631 6631
619.
7010-T73651 t - 120 mo
1)
9 6 REAM 92150 78845
134558 99249
1U52 5359 3572 5172 4626
Specimen width in the short transverse direction; specimen thickness - 5
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75
TABLE 6-2 No load transfer joints - France
NO LOAD TRANSFER JOINTS FRANCE
=fc MATERIAL FASTENER SYSTEM LOAD LEVEL (MP«), FLIGHTS TO FAILURE AND |LOC MEANI
ALLOY FAYING HOLE.
SURFACE QUALITY FASTENSR FIT
(urn) FALSTAFF
.00 223 260 290 1 300 351.6 1 392.5 2024-T3J1 ANODIZE
PRIME«
SEALANT
EAST. DM
INST.
RROACH LOCK WIT INTERFER- ENCE I6-J2
82973 78139 30960
24925 29150 27173
2052 2000
flöü]
173 173 81
11341 |5B550| |2 70001
22I4-T651 60032 >l33840
69632
23232 24173 24081
8225 7373 7373
|7630| |82400| (2 3800)
7475-T7361 4 3 34« 35160 68234
13432 14776 12 760
37J 432 573
|47000| |11*00]
705O-T765I 81)60 >l 68287
817«
10173 8930 8426
BEB) |lOJ90U| 1
2024-T1SI RARE 61684 8)428 668)2
3831 6232 4973 3232
1*4 )Ul
25
12
[>O06U| Hj] |
log mean life
TAIL! fc-j No I odd transfer joint» - Sweden
NU LOAD THASSFE« JOINTS SWEDEN
*
MATF HAL FASTENE* SYSTEM FALSTAFF (HFa)
ALLOY FAYINC
SL'NFACE HOL-
OUALITY FASTENEH FIT .'00 MFa .»•0 Wa
2024-T) eruxY rxiMtk
SEALANT
rnujie
ItEAM HLH-ll-0*-U $ 5.990
INT. AVE.-;
INT.-.'8 TO
CLEA*
•10
»120000 7MS1
U2572
1772 70JI 8572
7010- TJJ4S1
1)
44972 27929 74170
70)1 5572
10172
'f'1*» width In the «hurt traa*v«r»« dtr.cttoe t • 120 aa- I • S M,
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76
TABLE 6-4 No load transfer joints - France
LOU LOAD TRANSIT! JOINTS
HATE« I Al. T «r"E«SE DOU1I.« DOGIONE
PAimna STSTEM
TAT INC SWACE
i
ANODIZING MIKE» SEALANT
ALODINf FRIHK* SEALANT
NOLI QUALITY
7ASTENE»
LOCMOI.T INTEITMENCE I A-]]
LOAD LEVEL (W.) rtlCMTS TO fAILWE AW fcrmXl
TALSTAff
1 108716 120«)«
rrüiMi]
«AH liOOOO '1110
260
17212 1722) I 1*7)
fKTäö]
2»;»o .MI;«
20*0)
[Tmü]
151.*
n~ **2) H12 7*12 MM
[BBI
NINI-TVIST III
~M I iÖT
)IIMI ISMM I»»on»
**7M)|
4 71*0 WJJO
2*1*51 11*5*
»*7»0 io*ti:
I Mi«
BUBI
EÜ5D
J5BJ23
U«5* «410» 8)141 '«1»S IIMJ
|5»04»|
-•»•"•. i.
•1)7« 10710
Bsa
B53
CM.. I • 0.1
TIT TW
."•»«Hi 2 «MM )7 7t20
QHH3
2277)0 HUM 110310
I «4)40 117*70 I WHO
E3B
I It MO I5»5«0
flt74tf]
*«4«0 *»«20
gag
|«OI4Ö]
TABU fe-5 U.iw lo4d transfer joint - Germany
LOU U
HATE* I AL
AH THAIS»»« «>I»T5
• *Vf,SI BUVUE bW.»0«t
nil StSTW ~T
rt». a», (itatuar
AU-Ot EAtllH. Jf*lAl.
».1« •Jv-aLlTY
rASTtat» rii LllA» L»tl <«t4!
rtiuits to IUUH
IOA* tm
»lit»:- :
»AU tat LuAlt LEYU
ft tears it. r*iL»i
taA» Ltrti
riiitin
ntum n> (tueu
IMtWT»
AM)t2- IBt Hllata lULAa:
•IAH
•a t»lli
k*AH
• I . > I'.uruott 11
IM
IM .-« •»ii i««ll MM mn
<*i Mi -•Si
iiati 10»*» u«>4
Ml .'.'1
Ml ;»i
nan an an
lu- llt
ii.'j • 111 •an
1411 l>'I 1111
:«:i»r:.:»;.
1« roe :ID ::<s
lt.";
::: ;» :»J
»0(4
::•>!:
:i»<;
MS
«1
lii-i •Oil
Milr ItM
l»t .'It 111
i»'JfIUKt MS »>!•: «11 11111 1MB*
J»I
:»t • 41 -•s>i
aiu
r—-—f «i to»-: Uli»
J») :»i
IS!*» Ulli
i4a •44
»«ll 41'»
"ui.i 1! ,'M :tt 1»»
:•: ;.t ill»
:ii >a?
;»i Hi **•
'Us S411
La»fcVt all*
latiimaii 1> i» * um
it* ' MW1
;:• la lallj
•ll*
!»il **u«
»a* »as
Jl'S lit» 411
KUU II
:;u Hitt sat 141
lalH 14*11 14*11
:»t »: Hi »4«
il:.I
•ati
1J. MM Me 4»
« = ": »*•«
1- tin*«'' utt *• j »MM :::
4M
«ail ••»Is »11*1
:»> HI »4«
Mail • mi
taa 4*a
illj aUi
_J taMauti imuttai
M» J IM! 11«
11* it's» ..'op
1»
m | •Oil ills f»»l
»it
411 .111
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TABLE 6-6 Lov load transfer joints - Italy
LOW LOAD TRANSFER JOINTS ITALY
EVERSE DOUBLE DOGBONE
MATERIAL FASTENER SYSTEM LOAD LEVEL MPa), FLIGHTS
ALLOY FAYING SURFACE
HOLE QUALITY
FASTENER FIT tin FALSTAFF
280 351.6
2024-T3 ANODIZING PRIMER SEALANT
REAM Hl-LOK
Ti CSK ff 5
INTERFER- ENCE 13-43
29125 31373 26232 34929 23628 ^*
log mean life
1287911
HI-LOK Ti CSK ff 6 TYPE
LN29797
22061 17032 19820 20032 16632
773 832 832 632 768
Eg] 119006[
HI-LOK TENSION Ti CSK 9 6
10026 18232 12625 13080 27276
773 373 432 373 373
[444] |15245|
HI-LOK Ti PROT-
RUDING 9 6
19302 2143? 18424 22432 25360
1212531
HI-LUK Tl CSK ff H
1NKERFER- ENCE 14-51
26673 21432 25773 13232 20573
120924)
COLD
WORK
REAM
BOLT
Ti CSK ff 6
CLEARANCE
10-40 3929 4142 3574 3726
232 432 37) 373 4)2
I 38)71
REAM HI-LOK Tl CSK ff t. TYPE
MSTNI 1
INTEKKEK- ENCE 13-43
2720' 16425 1681,7 14715 17BE)
[IBIBOI
COLD
WUKK
REAM
BOLT
Ti CSK ff 6
39 308 30013 28491 3*832 4.872
I3S3951
8)2 632 626 632 632
ß66]
I
-
![Page 84: AGARD REPORT No.721 Fatigue Rated Fastener Systems · 5.2 Corrdation of fatigue ... 14 Comparison of UK and AGARD low toad transfer joint design t.5 Correlation of fatigue »ves](https://reader033.vdocuments.site/reader033/viewer/2022051321/5af553757f8b9a190c8e2bfa/html5/thumbnails/84.jpg)
78
f TABLE 6-7
Low load transfer joints - The Netherlands
LOW LOAD VRANSFER JOINTS THE NETHERLANDS
1 1 REVERSE DOUBLE DOGBONE
MATERIAL FASTENER SYSTEM LOAD LEVEL (MPa), FLIGHTS TO FAILURE AND ILOC MEAN 1
SURFACE HOLE
QUALITY FASTENER FIT
urn FALSTAFF MINITWIST III
351.6 70 85 100
SEALANT
FAST. WET INST. WITH SEALANT
DM DRILL HI-LOK PROTRUDING
CLEARANCE 25- INT. 76
14111 23772 24560
8325 9159
66323 >148000 > 175000 261655
32106 48412 77378
>98632
>(58687|
log meanl life 1
[20440] > 11456041
DRILL CLEARANCE 63-255
6372 7124 8929
1 7401|
2129 2231
(Tml
22790 26681 26858
25656 16095 17378
[192681 1 253691
2024-T3 ANO- DIZING PRIMER SEALANT
FAST.WET 1 SSI AI.. WITH SEALANT
DM DRILL 111-LOK
CSK
INTERFER- ENCE 20-40
253646 359896
> 400000
120501 124708 147856
56106 75260
1331758) [130194| |S498l|
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79
TABLE 6-8 Low load transfer joints - United Kingdom
I
LOW LOAD TRANSFER JOINTS UNITED KINCDOM
REVERSE DOUBLE DOGBONE UK-DESIGN
MATERIAL FASTENER SYSTEM LOAD LEVEL (MPa), FLIGHTS TO FAILURE AND |LOG MEAN|
ALLOY FAYING HOLE QUALITY
FASTENER PIT lim
FALSTAFF
164 (• 280 NET) 206 (- 350 NET)
7050-T7651 ALOCHROMED REAM HI-LOK CLEARANCE 25231 6631 PRIMER 13-61 12372 5711 SEALANT 21359
19292 .log mean 4929
| 18938[ llfe
TAPER TAPERLOK INT. 54231 22972 REAM 46-106 37772
50631 24831
30796 14224 27172
27863 26811
| 37254| 123606|
REAM HI-TIGUE INT. 55351 17080 76-127 54772
53172 42172 74772
17729 22959 21572 23372
| 55109| |203A8|
REAM HUCKCRIMP CLEARANCE 12929 5280 13-48 10724
13172 11011 18959
5698 6128 5024 5024
I 5414| I 13069)
DRILL HUCK EXL INT. 27531 14224 38-144 80280 20631
HUCK 120272 26490 MANDRELL 39759 39111 COLD 36431 24205
| 52I32| |23625|
SPLIT HI-LOK TRANSITION: 72372 14725 SLEEVE 13 CLEAR. 82172 20711 COLD TO 39 INT. 40529 18031 WORK 43372
60572 23359 16559
REAM I 57585] [l843ll
ACRES HI-LOK TRANSITION: 54625 19372 SLEEVE 13 CLEAR. 34372 17031 COLD TO 13 INT. 60511 21231 WORK 38231
442 31 22989 19972
[705201 1 453641
REVERSE DOUBLE DOCBONE ^_ ACARD DESIGN "•
REAM HI-LOK CLEARANCE 26337 6221 13-61 19972
21724 24129
7031 6011 4480
23172 4729
rsTTTi [ .'29661
SPLIT HI-LOK TRANSITION: 136464 19172 SUEVE 13 CLEAR. »71572 13880 COLD TO 3» :NT. 507 59 ii'031 WORK 178745 22329 REAM 240231 39824
[JäZöil [136859]
I
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TABLE 6-9 Low load transfer joints - USA
I
LOW LOAD TRANSFER JOINTS USA
RSE DOUBLE DOGBONE
MATERIAL HOLE QUALITY
FASTENER LOAD LEVEL (MPa), FLIGHTS TO FAILURE
ALLOY FAYING
SURFACE FALSTAFF
261.9
2024-T3 CLAD t - 3.2
STANDARD DRILL. DEBURR
RIVET 2024 HAND BUCKED (ICE BOX)
4372 5772 2572 log mean
fwl?f Hfe
RIVET 2024 MACHINE SQUEEZED (ICE BOX)
1372 3572
Q214J
RIVET 7050 HAND BUCKED
2024 3480
|2654 |
RIVET 7050 MACHINE SQUEEZED
2231 2430
|232B 1
TABLE 6-10 Type D dcjble shear joint - France
DOUBLE SHEAR JOINTS FRANCE
11 Hi rYPE D JOINT 4444
MATERIAL FASTENER SYSTEM LOAD LEVEL (MPa), FLIGHTS TO FAILURE ' IND |L0G MEANl
ALLOY FAYING SURFACE
HOLE FASTENER FIT li m
FALSTAFF CAL R-.1 MINI-TWIST
200 250 300 180 109 130
2024-T351 ALODINE PRIMER
ALODINE PRIMER
REAM
REAM
HI-L0\
HI-LOK
INTERFPHENCE 80
>139726 233130
>174000 log >272195 mean
64797 73973 40573
13373 23760 39173
126750 285020 187560 "65210
117653 25656 98856 9656 73656 21656 87513 18856
>|l98187fUrc |57940| |23200| 1205891] |93000| |178501
7075- T7351
138373 94832
19740 47295 59573
1437601
41226 30422 21632
184070 2256)0 )95080 185550 189710
|1T)ÖÖÖ1
136412 50682 98786 41656 65099 45656
108095 62682
|114550| |100 50| |98700] [4960O|
7050- T7651
EPOXY PAINT
BROACH CLEARANCE 10-30
9179 9373
10973
37)0 4912 )J7)
n«54i (KRKS-V)
1 98iul
COLD WORK BROACH
INTERFERENCE 15-35
69760 850)2 50025
| 587.>5|
16*32
287)0 .'44)2
(VRFSJV) 120717]
ALODINE PRIME«
REAM HI-LUK IKTUtmKKUE 80
4597) 188)* 5157)
87)91 1349)6 52965 88412
|»62QO| imool
14477) 11)37)
SS03J 36797 5097)
2.'225 40812 206)2
195*00 1)9)40 120720 161410 16)510
|l540OU|
82612 24501 66857 41851 8)841 25456 71671 3309»
luiuei |(,690u) tMMI mau i29ml
![Page 87: AGARD REPORT No.721 Fatigue Rated Fastener Systems · 5.2 Corrdation of fatigue ... 14 Comparison of UK and AGARD low toad transfer joint design t.5 Correlation of fatigue »ves](https://reader033.vdocuments.site/reader033/viewer/2022051321/5af553757f8b9a190c8e2bfa/html5/thumbnails/87.jpg)
:
81
TABLE 6-11 Medium load transfer double shear joint - The Netherlands
DOUBLE SHEAR JOINTS TH.. BTHE 1
H f-
MATERIAL
6 M2-MEDIUM LOAD TRANSFER
FASTENER SYSTEM
ALLOY FAYING SURFACE
HOLE QUALITY
FASTENER FIT um
~ww „«,„„, ynr*,, fLiüMTS TO FAILURE AND |LOG MEAN]
MINI-TWIST FALSTAFF
70 85 100 200 250 2024-T3 ANODIZE
PRIMER SEALANT
DOUBLE MARGIN DRILL
HI-LOK INTERFERENCE 20-40
log mean life
99898 183526
>315666
> 57120 > 87716 112446
> f 82592) >1795401
REAM INTERFERENCE 80-100
>400000 164412 >250320 >259395
> 57377 78073
> I 669291 >|400000| >220190)
7050-T76 PRIMER REAM HI-LOK
TEST SERIES NOT
CLEARANCE 10-30
34432 11832
GH3
JRFS-A")
COLD WORK
VRFS-B)
INTERFERENCE 15-35 >16773 >16044
I
TABLE 6-12 High load transfer double shear joint - The Netherlands
DOUBLE SHEAR JOIKTS
TYPE Hl HICH LOAD TRANSFER
MATERIAL
ALLOY
2024-T3
FAY INC SURFACE
ANODIZE PRIMER SEALANT
FASTENER SYSTEM
HOLE QUALITY
DOUBLE MARGIN DRILL
7050-T76 ! PRIMER SEAUKT
COLD WORK REAM
REAM
COLD WORK REAM
FASTENER
HI-LOK
HI-LOK
KIT
THE NETHERLANDS
LOAD LEVEL (MPa). FLIGHTS TO FAILURE AND fLOC MEANI
INTERFERENCE 20-40 log Bean
life
INTERFERENCE 80-100
MINI-TWIST III
307691
f>0769l|
CLEARANCE 0-25
CLEARANCE 10-30
156681 157655
|l5716»l
'400000
»•oöoöol
INTERFERENCE IJ-J5
H5
56921 98496 121656
1880.'5
50991 61031
f»^6l
93197 106856 121578
10658.'
12412 24411
fw*Ö7l
11691
QU91J
1365- 48411
FALSTAFF
1441] 15448
>186J6 >34S29
nzz}
2 50
4041 5848 »573 5329
es 84 32 »425
13832 »14200
•uns)
!
![Page 88: AGARD REPORT No.721 Fatigue Rated Fastener Systems · 5.2 Corrdation of fatigue ... 14 Comparison of UK and AGARD low toad transfer joint design t.5 Correlation of fatigue »ves](https://reader033.vdocuments.site/reader033/viewer/2022051321/5af553757f8b9a190c8e2bfa/html5/thumbnails/88.jpg)
82
TABLE 6-13 High load transfer double shear joint - United Kingdom
DOUBLE SHEAR JOINTS UNITED KINGDOM
TYPE H2 - HIGH LOAD TRANSFER LOAD LEVEL <MPa), FLIGHTS TO
FAILURE AND |LOG MEAN|
MATERIAL FASTENER SYSTEM FALSTAFF
ALLOY FAYING SURFACE
HOLE QUALITY
FASTENER FIT
7010- T7651
ALOCROME PRIMER SEALANT
REAM HI-LOK CLEARANCE
13-61 37898 23172 30839 34929 14821 log
f 26875LÄ_l«e
7572 4031 •»559 3431 2959
| 4060|
TAPER
REAM
TAPERLOK INTERFERENCE 46-106
172929 91211
191085 134759
21421 42929 29206 47772
|141963| 133655|
REAM H1-T1GUE INTERFERENCE 76-127
66624 32796 52172
123227 41024
34224 27749 27031 12972 20924
| 5651o| 1233681
REAM HUCKCRIMP CLEARANCE 13-48
50911 14825 45274
143431 114529
18943 14329 17031 20572 19524
| 56214| 117937|
DRILL
HUCK
HANDEL
COLD
WORK
HUCK EXL. INTERFERENCE 38-144
211711 155031 155172 96996 146572
87511 58880 55172 59929 52972
|l485Bo] J61814|
SPLIT
SLEEVE
COLD
WORK
REAM
Hl-LOK TRANSITION: 11 CLEAR. TO 39 INT.
51172 76759
> 224420 166196 930„'i
31759 34525 27772 27359
[106 3B6J |i0212|
ACRES
SLEEVE
COLD
WORK
i
Hl-l.OK TRANSITION 13 CLEAR. TO 13 INT.
124759 41929 4563'.
13624 9031
16972 12329 30621
| 62034) |15H3|
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83
-
.
TABLE 6-14 'ijrpe C lap joint - France
I SINGLE SHEAR JOINTS FRANCE
TYPE C UP JOINT ^]]
MATE2IAL FASTENER SYSTEM LOAD LEVEL. FLIGHTS TO FAILURE AND |LOG MEAN|
ALLOY FAYING SURFACE
HOLE QVALITY
FASTENER FIT y n
FALSTAFF
112.5 150 200
2024-T3 ANODIZING PRIMER SEALANT
BROACH LOCKBOLT INTERFERENCE 16-22
53634 63426 71596 log mean
f6l4lb>-^-e-
10606 15432 14832
1431 1432 1130
|13440| |1320|
2214- T651
41825 64944 56522
16232 19822 20973
3432 2925 4832
(535501 [lB900| |3550|
7475- T7351
36206 26712 41625
8330 U330 13185
1681 1573 1112
(34270| [11060| |1430|
7050- T765
EPOXY PAINT
REAM
(FRFS^T)
Hl-LOK 9032 9632 8960
11144
2981 39/3 2573 2832
I 9860| |3050|
COLD
WORK
REAM
8832 137 30 12173
7944
3173 4973 337J
^RrS-B^ llOAlOl [3840l
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• 84
TABLE 6-15 Q-type joint - United Kingdom
I
SINGLE SHEAR JOINTS UNITED KINGDOM
INT LOAD LEVEL (MPa), FLIGHTS TO FAILURE
MATERIAL FASTENER SYSTEM |LOG MEANl
ALLOY FAYING SURFACE
HOLE QUALITY
FASTENER FIT FALSTAFF
191 280 NET 263 350 NET
7050- T76
PRIMER SEALANT
REAM HI-LOK CLEARANCE
10-30
INTERFER- ENCE 15-35
12128 14431 12160 13831 log 14031 mean
3925 2929 3444 4336
(FRFS-A)
(13280^ [36391
COLD
WORK
REAM
9631 12424 12329 16224 17631
?801 3172 3624 5323
'FRFS-B)
|13337| |3905|
.
TABLE 6-16 ll Dogbonc joint - USA
SINGLE SHEAR JOINTS USA
IS DOGBONE LOAD LEVEL (MPa).
FLIGHTS Tt) FAILURE AND
[LOG MEAN]
2
ALLOY
TERIAL FASTENER SYSTEM
FAYING SURFACE
HOLE Ql'ALITY
FASTENER FIT ;.m
FAtSTAFF
2 38
7075- T7o BARK t-1.2
ANOD1ZE PRIMER TOPCOAT '
not on iayint
nurtac«
REAM HI-LOK SLIGHT
PRESS
16772
22572
25529
19972 log nein
|.'U96l}- Ufe
REAM SLEEVHuLT INTER-
FERENCE
64
2)211 21729 Ulli
UJ07..1
![Page 91: AGARD REPORT No.721 Fatigue Rated Fastener Systems · 5.2 Corrdation of fatigue ... 14 Comparison of UK and AGARD low toad transfer joint design t.5 Correlation of fatigue »ves](https://reader033.vdocuments.site/reader033/viewer/2022051321/5af553757f8b9a190c8e2bfa/html5/thumbnails/91.jpg)
TABLE 6-17 Type C2 lap joint - USA
SINGLE SHEAR JOINT
2024-T3 CLAD
| THICK- NESS (inch) .63
TYPE C2 UP JOINT
FAYING SURFACE
.090
705Ö- T74
FASTENER JYSTEM HOLE
QUALITY
STANDARD
DRILL DEBURR
ffttHU suuurr
FASTENER
RIVET 2024-T3 (DD)-03/16- SQUEEZE-MS2Ö470 UNIVERSAL (PROTRUDING) HEAD
RIVET 7050-T73 (E)-03/16- SQUEEZE-MS20470 UNIVERSAL (PROTRUDING) HEAD
RIV1T 2024-T3 (DD)-01/4- SQUKEZE-MS20470 UNIVERSAL (PROTRUDING) HEAD
RIVET 7O50-T73 (E)-01/4- SQUEt?E-MS2ü470
UNIVERSE (PROTRUDING) HEAD
USA
LOAD LEVEL, FLIGHTS TO FAILURE AND ILOG MEAN I
FALSTAFT
RIVET 2024-T3 (DD)-03/16- SQUEEZE-MS20426 COUNTERSUNK HEAD
RIVET 7050-T73 (E)-03/16- SQUEEZE-KS20426 COUNTERSUNK HEAD
RIVET 2024-T3 (DD)-01/4- SQUEEZE-MS20426 COUNTERSUNK HEAD
RIVET 7050-T73 (E)-01/4- SQUEEZE-MS20426 COUNTERSUNK HEAD
RI VET 2024-TJ (Dl»-0l/4- SQUEEZK-»m8DD9 BRILKS FLUSH HEAD
wi-*j
COLD wuu «CAM
RIVET ?OSO-T7) (|)-fl/4. SQUEEZE-»man «KILES rtUSH HEAD
URS!
trrtkrucMLi!
200
4880 5831
11159
CüäL 2775 5031 2359
-HM 4824 4031
1772 2031 999 1372
14901 1172 1221 2129 1080
71571 4811 4396 4743 lo| 3711 mean
10830 14000 7996 10329
J372 1631 422 ( 2124
6111 1) 8580 1, •Mb 1) 15000 _-)
[
i»ar. s-.t« isutcner
.')tm lyttM lanl cllcr
"A"
LOAD ura. rtiiarrs TO rAlLUU AW
ISO TOST
14812 22201
<••-•>:••<
list;
w 2.773 41JOÜ 1*442 54118
2 (XI lSi70 1346] 18000 JHO 5626
i*jat »m •425
I UMJtll . Iiiim I
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86
TABLE 6-18 lj Dogbone joint - The Netherlands
SINGLE SHEAR JOINTS THE NETHERLANDS
LOAD LEVEL (MPa), FLIGHTS TO FAILURE AND ILOG MEANI 2
MATERIAL FALSTAFF
ALLOY FAYING SURFACE
HOLE QUALITY
FASTENER FIT 200 250
7050-T76 PRIMER SEALANT
REAM HI-LOK CLEARANCE 10-30
INTERFERENCE 15-35
18411 60372 56972 63831 log mean
life
9559 15419 23373 22231
(FRFS-A)
|44839|- 116635)
COLD
WORK
REAM
29572 40431 58231 35759
13524 14231 17962 19172
JRFS-B) [39722| [160451
I
TABLE 6-19 Single shear X joint - Sweden
SINGLE SHEAR X JOINT
MATERIAL
ALLOY
-sjfcasr-
FASTENER SYSTEM
HOLE QUALITY
FASTENER FIT
SWEDEN
FALSTAFF
1.50 MPa 200 MPa
2024-T3
7050-T76
7050-TH
HU4-U-O6-05 INT.
AV.-7: -28- + 10
112081 10211 18359 8711
|H776l
REAM
mirs-A»]
HL-l9-8-7 CLEAR. 29:
•II -•«7
1 I860 16972 11180 lo» Bc£
COU>
WORK
REAM
HL-t»-*-? CLEAR •9:
• 2 -»26
42772
10224
mrt-i*j MOTt: ftrS-A«: falllft» • 10 „» out.Ue the «petIf lial Ion of P».rS-A
rt-FS-»»: -10 „a elMr nc« ln«le«d of 25 ..a lalcffereuce
5329 5590 b>80
10929 I1M72 11172
[11416]
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K7
TABLE 6-20 Type CA double shear joint - France
DOUBLE SHEAR EQUIVALENT JOINT
in m TYPE Cl
MATERIAL
ALLOY
7050- T7651
FAYING SURFACE
EPOXY PAINT
FASTENERS WET INSTALLED
FASTENER SYSTEM
HOLE QUALITY
(FRFS-B)
FASTENER
HI-LOK CLEARANCE 10-30
INTERFERENCE 15-35
FRANCE
LOAD LEVEL (MPa)I, FLIGHTS TO FAILURE AND ILGG MEANl
FALSTAFF
150
106490
log mean J.Ufe
106490
200
38373 23912 22637 21797
25940
86360 79573 89832 41899 46432
8825 9173 10973
9613
28628 29160 27530
28430
I
TABLE 6-21 Ij Double shear joint - The Netherlands
DOUBLE SHEAR JOINTS THE NETHERLANDS
. l\ DOUBLE SHEAR DOCBONE LOAD LEVEL (MPa). FLIGHTS TO FAILURE AND (LOG HFÄN] * MATERIAL FASTENER SYSTEM FALSTAFF
ALLOY FAYING SURFACE
HOLE QUALITY
FASTENER FIT 200 2 »0
705U-T76 fktMEft
SEALANT
FASTENER
WET INSTALLED
REAM HI-LOK CLEARANCE
»0-iO
28)2* 49772 .'86 JB »2BJI log Bean
14772 IM24 12372 18)72
(FBFS-A)
COLD
WORK
REAM
INTERFEREXCK
»S-15
> i»;s6
EuS]
58172 »OB 11 M2 i i •»572
(FRFS-B) |B)6BB1
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<6$
REPORT DOCUMENTATION PAGE
1. Recipient's Reference 2. Originator's Reference
AGARD-R-721
3. Further Reference
ISBN 92-835-1512-9
4. Security Classification cf Document UNCLASSIFIED
S^righÄ Äl^^r^l^Ä^'sPace Research and Development North Atlantic Treaty Organization 7 rue Ancelle, 92200 Neuilly sur Seine, France
*
6. Title FATIGUE RATED FASTENER SYSTEMS
7. Presented at
8. Author(s)/Editor(s)
edited by H.H.van der Linden
10. Author's/Editor's Address
Various
9. Date
November 1985
11. Pages
94
TIjDisTribution Statement This document is distributed in accordance wtth AGARD policies and regulations, whi :h arc outlined on the Outside Back Covers of all AGARD publications.
13. Keywords/Descriptors
* Fasteners Fatigue (materials)
Fatigue tests Mechanical engineering -<
14. Abstract h In recent years the ae»«»space industry has developed many ways of joining parts *F*tKd«*te
also the preparation of the holes and the quality of fit. .' - /
llus Report was sponsored by the Strictures and Matemls Panel of AGARD
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•&
c i si 5 3 •= ^ u. u. u. ^
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