1、 STD*AECMA PREN i034-ENGL 2000 D 303233L 0037852 LIT D Edition approved for publication 2000-02-29 AECMA STANDARD NORME AECMA AECMA NORM Comments should be sent within six months C8 Chairman after the date of publication to Gulledelle 94 AECMA Mr Feltham B-1200 BRUXELLES prEN 4014 Edition P I Februa
2、ry 2000 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - 8-1200 BRUXELLES - Tel. (+32) 2 775 81 10 - Fax. (+32) 2 775 81 11 ICs: 49.030.50 Descriptors: aircraft industry, joining adaptor, specification, design, utilization, characteristic, dimension, hole size, d
3、esignation ENGLISH VERSION Aerospace series Inserts, thickwall, self-locking Design standard Srie arospatiale Douilles filetes, paroi renforce, freinage interne Norme de conception Luft- und Raumfahrt Gewindeeinstze, dickwandig, selbstsichernd Konstru ktionsnorm This “Aerospace Series“ Prestandard h
4、as been drawn up under the responsibility of AECMA (The European Association of Aerospace Industries). It is published on green paper for the needs of AECMA- Members. It has been technically approved by the experts of the concerned Technical Committee following comment by the Member countries. Subse
5、quent to the publication of this Prestandard, the technical content shall not be changed to an extent that interchangeability is affected, physically or functionally, without re-identification of the standard. After examination and signature of the AECMA Standard Checking Centre (NPS) and formal agr
6、eement of the Official Services of the Member countries it will be submitted as a draff European Standard to CEN (European Committee for Standardization) for formal vote. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleN
7、o reproduction or networking permitted without license from IHS-,-STD-AECMA PREN 4OLLI-ENGL 2000 D 10123LL 0017853 O5b Page 3 prEN 4014: 2000 I Scope This standard specifies the use and installation hole dimensions for EN standard, self-locking, thickwall inserts and provisions for component salvage
8、, for aerospace applications. 2 Normative references IS0 5855-1 Aerospace - MJ threads - Part I : General requirements IS0 5855-2 Aerospace - MJ threads - Part 2: Limit dimensions for bolts and nuts EN 3831 Aerospace series - Inserts, thickwall, self-locking, in heat resisting steel FE-PM3801 (17-4P
9、H), Mos2 coated 1) EN 4015 Aerospace series - Inserts, thickwall, self-locking - Installation and removal procedure 1) 3 Design Typical examples of installed inserts are shown in figures 1 and 2. 3. I The thickwall self-locking screw thread inserts may be used in tapped blind holes and tapped throug
10、h holes. The minimurn flange thickness dimensions K given in tables 3 and 4 are less than the insert lengths, When using these minimum flange thicknesses, protrusion of the inserts will occur (see figure 5, footnote ”). Designers must therefore ensure that the inserts do not protrude into an abutmen
11、t face or foul any other adjacent features. 3.2 The installed insert is consistent with metric size bolt and MJ thread to IS0 5855-2. 3.3 figures 1 and 2). The minimum selected bolt length shall ensure full thread engagement with the insert (see 3.4 heat resisting steels and titanium alloys. These s
12、crew thread inserts may be used in aluminium alloys and in harder materials, such as Key 1 I ,5 pitches minimum Figure 1 Key 1 13 pitches minimum Figure 2 1) Published as AECMA Prestandard at the date of publication of this standard Copyright Association Europeene des Constructeurs de Materiel Aeros
13、patial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-STD-AECMA PREN LiOLY-ENGL 2000 = LOL231L 0037859 T72 = Page 4 prEN 4014: 2000 Bolt thread diameter MJ5 x 0,8 4 Use Self-locking torque Nm min. max. 0,25 2 4.1 General A sel
14、f-locking thickwall insert as shown in figure 3 is a sleeve of metal which is threaded both internally and externally, with an externally serrated upper portion. These inserts are screwed into tapped holes which contain counterbores (see 5.1) and are fixed by swaging the serrated portion into the co
15、unterbore of the component (see figures I and 2) thus preventing the insert moving during the installation or removal of a bolt. The self-locking zone of these inserts is positioned at the opposite side from the counterbored portion. 1 c 2 Key 1 2 Knurled end to be swaged into the counterbore of the
16、 parent component Formed out-of-round to achieve self-locking feature Figure 3 4.2 Performance The thickwall inserts according to EN 3831 have a minimum performance of 25 re-uses at ambient temperature and 5 re-uses after 350 “C baking at the maximum operating temperature: 350 “C. The self-locking t
17、orque values for the inserts are given in table 1. These are the values required to achieve the minimum re-usability performance in accordance with the technical specification of the inserts. MJIOx 1,25 I 12 I 9,5 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by
18、IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-STD-AECMA PREN 4014-ENGL 2UUfl E LU12311 0017855 929 E MJ8 x 1 MJ10 x 1,25 Page 5 prEN 4014: 2000 5,3 617 4.3 Installation restrictions In applications where it is necessary to pass items thr
19、ough the installed insert, care shall be taken to ensure that such items do not foul the locking feature of the insert. The maximum diameter X that can be passed through the insert is illustrated in figure 4 and dimensions are given in table 2. Figure 4 Table 2 Dimensions in millimetres Internal thr
20、ead size insert Diameter MJ5 x 0,8 I MJ6 x 1 317 I MJ7 x 1 1 485 I 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 LiOLLi-ENGL 2000 H 101
21、2311 0017B5b Bb5 Page 6 prEN 4014: 2000 Diameter code 050-0 060-0 070-0 080-0 100-0 5 Required characteristics Bolt thread Installation A E G Gib H K Li Lz M N diameter a thread diameter a + 0,l +0,2 +0,2 max. min. min. min. min. o min. min. min. o o MJ5 x 0,8 MJ8 x 1-4H5H 8,l 8 3,8 14 17 6,5 11,5 1
22、0 10 3 MJ6x 1 MJ9 x 1-4H5H 9,l 9 4 15 19 7,5 12,5 11,5 11 3,l MJ7x 1 MJlOx 1-4H5H 10,13 10 4,4 17 21 0,2 9 14 13,5 12 3,4 MJ8x 1 MJ11 x1-4H5H 11,13 11 4,7 19 23 11,5 16,5 15,5 13 3,6 MJlOx 1,25 MJS13x 1-4H5H 13,13 13 5,3 22 27 14 19 19 15 4 5.1 Installation hole See figure 5 and tables 3 and 4. Dime
23、nsions in millimetres 90“ f 5“ Kz- 1 Key 1 Serration, see 5.2. 2 Pitch diameter 3 Thread 4 Normal boss 5 Salvage boss a may protrude. K allows total installation of the threaded part of the insert with 0,5 mm underflush. The not threaded part of the insert LI min. = K+ 5 pitches. Allows machine tapp
24、ing, housing of the non threaded pari and a 1,5 pitches protrusion of the bolt. L2 min. = Insert length max. + 0,5 (underflush) + 13 pitches Spot facing of M is optional. It avoids swelling of the bearing face when installing in aluminium alloys and also when d broaching the serrated counterbores in
25、 harder materials. Figure 5 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-,-Diameter code 050-1 060-1 070-1 080-1 100-1 5.2 Serrati on Bolt thread Instal
26、lation A E G H K Li L2 M N + 0,l +0,2 + 0,2 diameter a thread diameter a max. min. min. min. o min. min. min. o o MJ5 x 0,8 MJ9 x 1-4H5H 9,l 9 3,8 14 6,5 11,5 10 11 3,l MJ6x 1 MJIOx1-4H5H 10,13 10 4 15 7,5 12,5 11,5 12 3,4 MJ7x 1 MJ11 x 1-4H5H 11,13 11 4,4 17 0,2 9 14 13,5 13 3,6 MJ8x 1 MJ12x1-4H5H
27、12,13 12 4,7 19 11,5 16,5 15,5 14 4 MJIOX 1,25 MJ14x 1-4H5H 14,13 14 5,3 22 14 19 19 16 4,2 Serration in counterbores is mandatory when the inserts are installed in hard materials : R, 620 MPa. It is optional in other materials. For serrated hole a “S“ is added to the designation (see clause 8). 5.2
28、.1 machine tool. The serration profiles are produced to EN 4015, using a broaching tool installed in hand tool or in 5.2.2 figure 6. Sufficient space shall be provided around each hole to allow access for the broaching tool, see Dimensions I in millimetres Figure 6 Copyright Association Europeene de
29、s Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-STD*AECMA PREN LiOLLi-ENGL %O00 m LO32333 0037858 b38 m Page 8 prEN 4014: 2000 6 installation EN 4015 Inserts shall be installed between 0,
30、3 mm and 0,5 mm below the surface of the component. 7 Provisions for component salvage When inserts are selected 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 positi
31、on. Before provision is made for component salvage, consideration shall be given to component cosmasc requirements, 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
32、 will be heavier because of the increase in wall thickness around the tapped holes. In the event of component salvage action, hole preparation, salvage insert selection and installation shall be in accordance with EN 4015. 8 Designa ti on EXAMPLE: EN40 14-050-0s I TT Number of this standard Diameter
33、 code (see tables 3 and 4) Serration (see 5.2) 9 Indication on drawings 9.1 Drawing definition EXAMPLES: see figures 7 and 8. Dimensions in millimetres 1 1 Key Key 1 EN4014-070-0 1 EN4014-070-0s Alternatively, the hole may be fully dimensioned on the drawing. Figure 7 Figure 8 Copyright Association
34、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 WA-ENGL zowo E 1012312 002757 571 rn 9.2 Assembly drawing EXAMPLE: see figure 9. P I Key 1 Insert EN3831 -070-0 installed to EN 401 5 Page 9 prEN 4014: 2000 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-,-
