1、STD-AECMA PREN 9957-ENGL 2000 023LI1 0038957 57T AECMA STANDARD NORME AECMA AECMA NORM prEN 4459 Edition P 1 October 2000 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - 8-1200 BRUXELLES - Tel. (+32) 2 775 81 1 O - Fax. (+32) 2 775 81 11 ICs: 49.030.20 Descripto
2、rs: ENGLISH VERSION Aerospace series Studs, in titanium alloy TI-P64001, with serrated locking ring in corrosion resisting steel Design standard Srie arospatiale Goujons, en alliage de titane lI-P64001, avec bague de verrouillage dentele en acier rsistant ia corrosion Norme de conception Luft- und R
3、aumfahrt Stiftschrauben, aus Titaniegierung Ti-P64001, mit Ringsicherung aus korrosionsbestandigem Stahl Konstruktionsnorm This “Aerospace Series“ Prestandard has been drawn up under the responsibilify of AECMA (The European Association of Aerospace Industries). It is published on green paper for th
4、e needs of AECMA- Members. It has been technically approved by the experts of the concerned Technical Committee following comment by the Member countries. Subsequent to the publication of this Prestandard, the technical content shall not be changed to an extent that interchangeability is affected, p
5、hysically or functionally, without re-identification of the standard. Affer examination and signature of the AECMA Standard Checking Centre (NPS) and formal agreement of the Officiai Services of the Member countries it will be submitted as a draft European Standard to CEN (European Committee for Sta
6、ndardization) for formal vote. Nota - Extra copies can be supplied by B.N.A.E. - Technopolis 54 - 199, rue JeanJacques Rousseau - 92138 ICSY-LES-MOULINEAUX CEDEX C8 Chairman I Edition approved for publication Comments should be cent within six months after the date of publication to Mr Feltham I AEC
7、MA I Gulledelle 94 2000-1 0-31 8-1200 BRUXELLES 0 aecma 2000 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1 Scope This standard specifies the use an
8、d installation hole dimensions for EN standard, studs, in TLP64001 I with serrated locking ring in corrosion resisting steel, for aerospace applications and provisions for component salvage. 2 Normative references IS0 5855-2 Aerospace - MJ threads - Part 2: Limit dimensions for bolts and nuts EN 442
9、1 Aerospace series - Studs, in titanium alloy Tl-P64001 I Mos2 coated, with serrated locking ring in corrosion resisting steel - Strength class: 1 100 MPa (at ambient temperature) 1) EN 4460 Aerospace series - Studs, in titanium alloy TLP64001 I with serrated locking ring in corrosion resisting stee
10、l - Installation and removal procedure 1) 3 General 3.1 Description See figure 1. Key 1 Nut end threads 2 Locking ring 3 Serrated collar 4 Installation end threads 5 Same thread diameter on both ends Figure 1 1) Published as AECMA Prestandard at the date of publication of this standard - Previous pa
11、ge is blank. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-STD.AECMA PREN 4459-ENGL 2000 M ItOL2333 0038959 342 M Page 4 prEN 4459: 2000 3.2 Installa
12、tion The studs are placed in their hole by hand (see figure 2). Rotational movement of the studs is prevented by installing the locking ring. This ring mates with the serrated collar on the stud and forms its housing in the casing, thus securing the stud. For installation in hard materials, ring hou
13、sing shall mandatorily be presserrated. The assembly thus made is inseparable, disassembly can only be achieved by destroying the locking ring and the stud. 1 Key 1 Ring installed Figure 2 3.3 Use Studs can be used: - in various “soft“ materials such as light alloys and “hard“ materials such as nick
14、el or titanium alloys; - in blind or through tapped holes, as shown on figures 3 and 4; - with MJ thread nuts in accordance with IS0 5855-2. On nut end, stud lengths are incremented to enable optimum installation for different grip thicknesses. I I Key 1 1,5 pitches min. 2 1,5 pitches max. 2 t Key 1
15、 Flange 2 Receiving pari Figure 3 Figure 4 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-STD-AECMA PREN 4457-ENGL 2000 LOL23LL 00187b0 Obil Page 5 pr
16、EN 4459: 2000 3.4 Recommendations Studs to EN 4421: - maximum operating temperature is 350 OC; - it is not designed to take shear loads; - it shall not be used on rotating parts; - for installing studs in light alloys, prebroaching of tapped hole is optional. Correct stud installation shall be check
17、ed (by tests). 4 Required characteristics See figures 5 and 6 and table 1. 4.1 Holes 1 Beanngface Diameter A: spotfacing is recommended for installation in aluminium alloys to prevent the bearing face from swelling. Figure 5 Dimensions in millimetres 2 3 Key 1 Thread pitch diameter 2 Normal boss 3 R
18、epair-size boss a C = minimum completely formed thread length E = C + 3 pitches, require manual tapping El = C + 5 pitches, minimum length for machine tapping i= minimum hole centeriine to part edge distance for installation Y = calculated on following basis: Y = 0,002 C Diameter G min. = 2 T Diamet
19、er Gl min.: there are no oversized studs for repair, diameter GI e shall be sized for the type of repair considered at design stage. Figure 6 Table 1 Dimensions in millimetres Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for Re
20、saleNo reproduction or networking permitted without license from IHS-,-,-4.2 Serration Figure 7 shows a serrated hole. Serration are to be made according to the hardness of the material; dimensions and profiles are defined in accordance with EN 4460 using a broach installed on a hand or machine tool
21、 as shown on figures 8 and 9 and in table 2. Sufficient space shall be provided around each hole to allow access for the broaching tool, see figure 7. 1 Key 1 Serrations Table 2 I Nut end Broaching tool threaddiameter 1 A I L I Figure 7 -c P 1 2 Key 1 Broach 2 Pilot Hand tool Figure 8 Dimensions in
22、millimetres I I 037 max. Key 1 Clearance: 2 min. Machine tool Figure 9 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-STD-AECMA PREN Li459-ENGL 2000 L
23、O123LL 0038762 737 D Page 7 prEN 4459: 2000 5 Installation Installation of the stud shall be in accordance with EN 4460. Determining grip thicknesses: see figure 1 O. Key 1 X = distance between the bearing face and the first completely formed thread of the stud A = griplength Amin. = Xrnax. A rnax,
24、= L min. - (1,5 pitches + H max.) H = height of nut L 13 pitches = minimum protruding length of the stud end from the nut = distance between the bearing face and the stud end. This value corresponds to length Lin product standard. Figure 10 6 Provisions for component salvage When studs are selected
25、for a design, consideration shall be given to the feasibility of component salvage where the original hole could be damaged during manufacture, or where the hole is machined out of position. Before provision is made for component salvage, consideration shall be given to component cosffmass requireme
26、nts, e.g. for an inexpensive component salvage may not be an economic proposition, whereas an expensive component may necessitate salvage. Where provision for salvage is made, the component will be heavier because of the increase in wall thickness around the tapped holes. Copyright Association Europ
27、eene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-STD.AECMA PREN qLi59-ENGL 2000 m 10l12311 00187b3 73 Page 8 prEN 4459: 2000 7 Designation EXAMPLE: EN4459-050-S Number of this sta
28、ndard 1 Diameter code (see table 1) Serration code (see table 1) 8 Drawing presentation 8.1 Definition drawing EXAMPLES: see figures 1 1 and 12. 1 1 Shear hole Serrated hole Key Key 1 HOLE EN4459-060 1 HOLE EN4459-0604 Alternatively, the hole may be fully dimensioned on the drawing. Figure 11 Figure
29、 12 8.2 Assembly drawing EXAMPLE: see figure 13. Key 1 STUD EN4421 -060 2 INSTALLATION EN4460 Figure 13 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
