1、STD-AECflA PREN 39Lb-ENGL 11999 IBg 1012311 0046494 O58 AECMA STANDARD prEN 3926 NORME AECMA Edition P 1 AECMA NORM September 1999 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - 8-1200 BRUXELLES - Tel. (+32) 2 775 8110 - Fax. (+32) 2 775 81 11 ICs: 49.030.99 Ed
2、ition approved for publication Descriptors: aircraft industry, joining adaptor C8 Chairman Comments should be sent within six months after the date of publication to ENGLISH VERSION Aerospace series Insert, thin wall Salvage procedure for components Srie arospatiale Douilles filetes, a paroi mince P
3、rocdure pour rcupration Luft- und Raumfahrt Gewindeeinstze, dnnwandig Verfahren fr Nacharbeit von Bauteilen This “Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA (The European Association of Aerospace Industries). It is published on green paper for the needs of AECM
4、A-Members. It has been technically approved by the experfs 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, physically or fun
5、ctionally, without re-identification of the standard. Affer examination and signature of the AECMA Standard Checking Centre (NPS) and formal agreement of the Official Services of the Member countries it will be submitted as a draft European Standard to CEN (European Committee for Standardization) fo
6、r formal vote. 1999-09-30 AECMA Guiledelie 94 8-1200 BRUXELLES Mr Feltham aecma 1999 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 37L
7、b-ENGL I979 LOL23LL OOLb495 T74 Page 3 prEN 391 6: 1999 I Scope 1 .I thin wall inserts. within assemblies. This specification covers the accepted methods for the reclamation of installation holes for standard 1.2 hole, or to rectify any out of position of the hole within the specified parameters of
8、use. To enable rectification when defects or damage occur to the standard insert tapped installation 1.3 replacement oversize thinwall insert. To control there machining of the existing insert hole and the installation requirements of the 2 Normative references IS0 965-1 IS0 general purpose metric s
9、crew threads - Tolerances - Part 1 : Principles and basic data IS0 5855-2 Aerospace - MJ threads - Part 2: Limit dimensions for bolts and nuts EN 3913 Aerospace series - Insert, thin wall, self-locking, short, in heat resisting nickel base alloy NI-PH2601 (NI-PIOOHT, Inconel 718), silver plated on i
10、nternal thread, for salvage of components 1) EN 3914 Aerospace series - Insert, thin wall, self-locking, long, in heat resisting nickel base alloy NI-PH2601 (NI-PIOOHT, Inconel 718), silver plated on internal thread, for salvage of components 1) EN3915 Aerospace series - Insert, thin wall, self-lock
11、ing, Mj threads, in heat resisting nickel base alloy NI-PH2601 (NI-PI OOHT, Inconel 71 8), for salvage of components - Classification: 1 275 MPa (at ambient temperature) / 550 “C - Technical specification 1) 3 Conditions of use 3.1 Engineering Drawings. After reclamation, assemblies shall conform to
12、 the dimensional requirements of their respective 3.2 Table 1 shows the values for the maximum out of position as applied to the theoretical centreline of the original hole. In practice this is a cylinder of diameter x,xx applied down the theoretical centreline of the original hole. If the actual po
13、sition of the hole centreline falls outside the perimeter of this cylinder the hole cannot be reclaimed. 3.3 been used in the original design. (See EN 3676, Table 6). Salvage using oversize inserts is only possible if the Boss thickness for component salvage has 1) Published as AECMA Prestandard at
14、the date of publication of this standard. Prcvious page 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-,-,-3.4 The reclamation facility shall at
15、this stage investigate the component Engineering Drawings to check that the operations detailed and controlled by sections 4 and 5 will not cause a further non conformance of the component. Standard insert internal thread size I 3.4.1 Table 2 demonstrates that 2 types of oversize insert can be used
16、ie long or short. Before commencing reclamation the original Engineering Drawings shall be checked to establish which type of standard insert has been used e: long or short. The replacement oversize insert and accompanying dimensions from this specification shall correspond with it, je: short for sh
17、ort, long for long. I Maximum out of position of the original hole (regardless of feature size) 3.4.2 conformance occurring to the oversize insert hole cannot be rectified using this method. Only 1 reclamation is possible using the oversize insert method for any one hole. Further non M J 5x0,8-4 H6H
18、 M JGxI -4H5H 3.5 Performance 0 0,5 0 0,5 It should be noted that the salvage inserts conforming with EN 391 5 give I O reuses at 550 OC. MJ8xl-4H5H MJI01,25-4H5H Table 1 0 0,5 0 0,5 Dimensions in mm 4 Re-machining of an existing insert hole 4. i aligned cutter (see Figure 1). The existing threaded
19、portion of the insert hole shall be completely removed by using a correctly 4.2 The cutter used shall enable the modified minor diameter B listed within Table 3 to be produced. 4.3 The old counterbore and serrations will be removed when the new counterbore is machined. 4.4 new oversize insert hole i
20、s machined in its correct position, see paragraph 3.2 and Table I. In the case of the original insert hole being out of position, the manufacture shall ensure that the Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo r
21、eproduction or networking permitted without license from IHS-,-,-STD-AECMA PREN 39Lb-ENGL 1999 a$I LOL231L 00Lb497 67 m Page 5 prEN 3916: 1999 Example Figure I 5. Insert and tapped hole particulars 5.1 and insert lengths. Table 2 provides details of the oversize insert part numbers in relation to th
22、e bolt thread diameter Table 2 Dimensions in rnm 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-,-,-STDaAECMA PREN 391b-ENGL 1999 a LO123Ll 00Lb496 7T3 m
23、Page 6 prEN 3916: 1999 Thread Minor B Hoe Length Associated bolt code a thread A max. min. diameter code 050 M J5xO18-4h6h MJ9xl,0-4H5H 82 8,1 L S L S L S L S L S 060 MJ61,0-4hGh MJ101,0-4H5H 9,24 9,11 070 MJ7x1,0-4h6h MJIIx1,0-4H5H 10,29 10,16 080 MJ81,0-4h6h MJ121,0-4H5H 11,29 11,16 1 O0 MJl01,25-
24、4h6h MJ141,0-4H5H 13,32 13,17 5.2 thinwall inserts. Table 3 and Figure 2 provide the necessary information for tapped holes to receive oversize C max. min. 9,l 9,o 10,13 10,O 11,13 11,0 12,13 12,O 14,15 14,O The counterbore depth DI applies when oversize inserts are to be installed into light alloy
25、components and prebroaching is not required. Counterbore depth D2 (refer to Table 4 and Figure 3) applies when oversize inserts are to be installed into hard materials, ie steels, nickel and titanium alloys, and the counterbore will need to be prebroached. Hoe diameter code 050 Table 3 DI D2 Chamfer
26、 G H M +0,13 +0,13 max. min. rt 0,25 L 2,59 14,8 17,951 10,03 S 2,97 9,25 12,4 Length code a 080 1 O0 L 3,OO 218 24,95 S 3,38 14,40 17,6 L 3,51 15,06 26,5 29,65 S 3,89 17,80 21,O 13,OO I 070 w 12,04 1- Length code L for long inserts (EN 3914 series), Code S for short inserts (EN 3913 series). Modifi
27、ed Minor diameter See paragraph 5.2. 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 3316-ENGL 1939 81111 L0123LL 00Lb439 b3T II Page 7
28、prEN 3916: 1999 Major diameter of 14 0 0,15 120“ 2 ; A Nlillll lG IH 4 MJlOx1,O 4H5H MOD MINOR DIA 9,11 TO 9,2& SEE PARA 5.3 W_A#PLE TiKEAO DIAMETER A MODIRED MINOR DIA THREAO CALL OUT:- FOR ALL OttiER PARTICULARS AND TITANIUM REFER ?O PARENT DRAWING 2,OO HIN AFTER FINA WACHINIMG, SEE PARA 3.3. THRE
29、AD PITCH DIA Figure 2 5.3 Table 4 and Figures 3 and 4 give the additional information required to produce the serrations in the counterbore for steel, nickel and titanium alloys. Serrations are required in the counterbore when oversize inserts are to be used in harder materials. These serrations are
30、 produced using a special broaching tool. Thread pitch 0 M to be broached in counterbore using a wobble broach with the cutting tool offset by 1“ to the broaching tool body a See paragraph 5.2. Figure 3 Hole serration profile (short inserts) Table 1 Figures I and 2 provide details of the insert part
31、 number and associated bolt thread in relation to the serration profile in the counterbore of the installation hole. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license
32、 from IHS-,-,-Page 8 STDeAECMA PREN 391b-ENGL 1999 W 1012311 001b500 LB1 prEN 391 6: 1999 AE“ Table 4 Dimensions in mm I l i L Number of max. I min. max. serrations J R2 Short Dimensions Associated bolt thread 1 inserts I AA I AB I AC I AD MJ5x0,8 MJ6xl MJ7xl MJ8xl MJ101,25 EN 3913-050 0,41 9,55 9,3
33、4 0,13 EN 3913-060 0,28 10,54 10,29 EN 3913-070 0,25 11,56 11,32 0,lO EN 3913-080 12,552 12,29 0,27 EN 3913-100 14,58 14,36 Senation form at mir position my vw dw fo bro.ch wear. 114,5 2,59 2,33 82,O 3 2,74 83,O 3 2,74 83,3 3 2,74 84,O 3,51 3,25 I I 27 28 0,25 32 33 40 Figure 4 6 Installation of ove
34、rsize inserts 6.1 6.1.4 the oversize insert, are free from burrs and any foreign particles, grease, oil, etc. P re instal lation requirements Prior to installation check that the tapped hole, counterbore and serrations (if applicable) to receive 6.1.2 Oversize inserts to be installed in aluminium or
35、 magnesium components shall be lightly smeared externally with a suitable universal jointing compound to prevent electrolytic corrosion. Care shall be taken to ensure the internal thread of the insert is not contaminated with any compound used. The relevant drying period shall be observed before ins
36、tallation of the oversize insert, when applying these requirements. 7 Minimum criteria for the installation and removal tools and their methods of application 7.1 The tooling and their methods of application described in this specification only show the basic principles to be observed to achieve the
37、 satisfactory assembly and subsequent swaging or removal of the oversize thinwall inserts, and are not mandatory. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license fr
38、om IHS-,-,-STDDAECMA PREN 39Lb-ENGL 1999 11111 1012311 0016501 018 Page 9 prEN 3916: 1999 7.2 The minimum dimensional requirements provided shall be achieved, and on no account shall the design of the tools or their methods of application, be such that damage may occur to the threads or the locking
39、element of the oversize thinwall insert, or the component into which they are being inserted. 7.3 Always ensure the appropriate tool/insert size combinations have been chosen for either the insertion or swaging of the oversize insert to ensure the inserts correct assembly. (See 8.2 and 8.3 respectiv
40、ely ). 7.4 During the swaging operation the component into which the oversize inserts are installed shall be adequately supported to ensure no flexing or distortion occurs at the insert assembly face. This particularly applies to components which are prone to flexing. 8 Assembly drive tool and swage
41、 tool 8.1 inserts are only examples and are not mandatory. The tools and methods shown in this section for the installation, swaging and removal of thin wall 8.2 dimensions to ensure the correct tool size is used for screwing the oversize insert into the tapped hole. The driving feature will be tri-
42、lobed but other tool features may vary depending on manufacturer. Figure 4 shows an example of the drive tool configuration and Table 5 gives the relevant tool I x (INT) Figure 4 Table 5 Dimensions in mm I I I I I I l Short insert Long insert X Y N P part number part number k 0,4 f 0,4 f 0,125 0,15
43、EN 3913-050 EN 3914-050 7,3 4,435 I ,O5 I EN 3913-060 I EN 3914-060 I 8,5 I 2,7 I 5,325 I 1,30 I I EN 3913-070 1 EN 3914-070 I 10,5 I 3,lO I 6,325 I 1,55 I EN 3913-080 EN 3914-080 123 3,50 7,175 1,75 EN 391 3-1 O0 EN 391 4-1 O0 16,O 9,015 2,25 Copyright Association Europeene des Constructeurs de Mat
44、eriel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 10 STD-AECMA PREN 371b-ENGL 1797 LOL2311 0036502 T54 prEN 391 6: 1999 Short incerf Long insert part number pait number 8.3 dimensions to ensure the correc
45、t tool size is used for swaging the oversize insert into the parent component. Figure 5 shows an example of the swage tool configuration and Table 6 gives the relevant tool OQ R OQ Rad S -r 0,015 rt 0,175 f 0,25 8.3.1 The swage tool has a protective nylon washer, see Figure 5, which acts as a stop d
46、uring the swaging operation and helps protect the surface of the component from damage, this must be replaced when dimensions R Max is exceeded. EN 3913-070 EN 3913-080 EN 3913-100 8.3.2 also cause the flange(c) of the components to be distorted. The use of incorrect tools may cause damage to the ov
47、ersize insert and parent material and may EN 3914-070 10,085 2,145 10,22 0,75 EN 3914-080 10,895 2,245 11,27 0,75 EN 3914-100 13,015 2,295 13,25 I ,o0 R (i NTERSECTION 1 SHAPE OPTION REPLAE E ABLE NY LON 5 TO? Figure 5 I EN 3913-050 I EN 3914-050 I 7,915 I 1,895 I 8,02 I 0,65 1 I EN 3913-060 I EN 39
48、14-060 I 8,965 1 2,045 I 9,065 I 0,75 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-,-,-9 Assembly procedure 9.1 Insertion Screw the oversize insert in
49、to the tapped hole in a clockwise direction using the appropriate drive tool selected from Table 5 until the insert is 0,4 to 0,65 mm below the surface of the parent metal, see Figure 6. 1 DRIVE TOOL 0,65mm 0,45rnrn Figure 6 9.2 Swaging 9.2.1 the area the inserts are to be installed. Before swaging the oversize insert ensure the mating component is well supporte
