AECMA PREN 3298-2006 Aerospace series Inserts thin wall self-locking Installation and removal procedure Edition P 2《航空航天系列.插件薄肩自锁安装和移除程序.P2版》.pdf

《AECMA PREN 3298-2006 Aerospace series Inserts thin wall self-locking Installation and removal procedure Edition P 2《航空航天系列.插件薄肩自锁安装和移除程序.P2版》.pdf》由会员分享，可在线阅读，更多相关《AECMA PREN 3298-2006 Aerospace series Inserts thin wall self-locking Installation and removal procedure Edition P 2《航空航天系列.插件薄肩自锁安装和移除程序.P2版》.pdf（16页珍藏版）》请在麦多课文档分享上搜索。

1、ASD STANDARD NORME ASD ASD NORM prEN 3298 Edition P 2 October 2006 PUBLISHED BY THE AEROSPACE AND DEFENCE INDUSTRIES ASSOCIATION OF EUROPE - STANDARDIZATIONGulledelle 94 - B-1200 Brussels - Tel. + 32 2 775 8126 - Fax. + 32 2 763 3565 - www.asd-stan.orgICS: Supersedes edition P 1 of June 1993 and wil

2、l supersede EN 3298:1998 Descriptors: ENGLISH VERSION Aerospace series Inserts, thin wall, self-locking Installation and removal procedure Srie arospatiale Douilles filetes, paroi mince, freinage interne Procdure dinstallation et dextraction Luft- und Raumfahrt Gewindeeinstze, dnnwandig, selbstsiche

3、rnd Ein- und Ausbauverfahren This “Aerospace Series“ Prestandard has been drawn up under the responsibility of ASD-STAN (The AeroSpace and Defence Industries Association of Europe - Standardization). It is published for the needs of the European Aerospace Industry. It has been technically approved b

4、y the experts of the concerned Domain following member comments. Subsequent 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 an

5、d review by users and formal agreement of ASD-STAN, it will be submitted as a draft European Standard (prEN) to CEN (European Committee for Standardization) for formal vote and transformation to full European Standard (EN). The CEN national members have then to implement the EN at national level by

6、giving the EN the status of a national standard and by withdrawing any national standards conflicting with the EN. Edition approved for publication 31 October 2006 Comments should be sent within six months after the date of publication to ASD-STAN Mechanical Domain Copyright 2006 by ASD-STAN Copyrig

7、ht Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-prEN 3298:20062 Contents Page Foreword2 1 Scope 3 2 Normative references 3 3 Hole serration profile (short in

8、serts)4 4 Installation of inserts.5 5 Minimum criteria for the installation and removal tools and their methods of application.5 6 Assembly tools and gauges .5 6.1 General5 6.2 Installation drive tool.5 6.3 Swage tools6 7 Installation procedure .7 7.1 Insertion7 7.2 Insert alignment prior to swaging

9、8 7.3 Swaging 9 7.4 After swage inspection 10 7.5 Inspection for minimum locking torque .11 8 Insert removal and replacement 12 Annex A (informative) Recommended tooling 14 Foreword This standard was reviewed by the Domain Technical Coordinator of ASD-STANs Mechanical Domain. After inquiries and vot

10、es carried out in accordance with the rules of ASD-STAN defined in ASD-STANs General Process Manual, this standard has received approval for Publication. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction o

11、r networking permitted without license from IHS-,-,-prEN 3298:20063 1 Scope This standard specifies the conditions of installation and removal (hole serration profile, tools, swaging procedure) of self-locking thin wall inserts defined by EN standards, for aerospace applications. 2 Normative referen

12、ces The following referenced documents are indispensable for the application of this document. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies. EN 3236, Aerospace series Inserts, thin wall,

13、 self-locking, short, in heat resisting nickel base alloy NI-P100HT (Inconel 718), silver plated internal thread. EN 3237, Aerospace series Inserts, thin wall, self-locking, long, in heat resisting nickel base alloy NI-P100HT (Inconel 718), silver plated internal thread. EN 3676, Aerospace series In

14、serts, thin wall, self-locking Design standard. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-prEN 3298:20064 3 Hole serration profile (short insert

15、s) Figure 1 and Table 1 provide details of the insert part number and associated bolt thread in relation to the serration profile in the counterbore of the installation hole. AA AD AB AE1 AC Key 1 Corners may vary from a sharp corner to a radius within the profile tolerance Figure 1 Table 1 Dimensio

16、ns (mm) Bolt thread diameter Short inserts No of serrations AA AB AC AD AE MJ5 0,80 MJ6 1,00 MJ7 1,00 MJ8 1,00 MJ10 1,25 EN3236-050 EN3236-060 EN3236-070 EN3236-080 EN3236-100 18 24 27 28 33 0,41 0,28 0,25 0,27 0,27 7,46 8,55 9,51 10,50 12,48 7,25 8,30 9,30 10,25 12,25 0,13 0,10 0,10 0,10 0,10 114,5

17、 82,0 83,0 83,3 84,3 For recommended serration profile gauge numbers, see Annex A, Table A.1. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-prEN 329

18、8:20065 4 Installation of inserts Pre-installation requirements Prior to installation, check that the tapped hole, counterbore and serrations (if applicable) are free from burrs and foreign particles, grease, oil, etc. This will particularly apply to removal of the burrs produced by the cutting of t

19、he serrations. The required insert shall be inspected to ensure that it is clean and free from protective grease etc. Inserts installed in steel, heat resisting alloy or titanium alloy components may be lightly smeared externally with clean engine oil (i.e., any of the recognised oils used for the e

20、ngine lubrication system. If in any doubt, consult the Controlling Quality Engineer) to facilitate assembly into the tapped and serrated counterbored hole. Inserts installed in aluminium or magnesium components must be lightly smeared externally with a suitable jointing compound to prevent electroly

21、tic corrosion. A minimum of 10 minutes air drying time shall be allowed before installation of insert. 5 Minimum criteria for the installation and removal tools and their methods of application The tools and their methods of application described in this standard are not mandatory and show only the

22、basic principles to be observed to achieve the satisfactory installation and subsequent swaging or removal of the inserts. 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

23、the threads or the locking zone of the insert or the component into which it is being installed. Always ensure the appropriate tool/insert size combinations have been chosen for either the insertion or swaging of the insert to enable correct installation of the insert. See 6.2 and 6.3. During the sw

24、aging operation, the component into which the inserts are installed shall be adequately supported to ensure no flexing or distortion at the insert assembly face occurs. This particularly applies to drum shaped components which are prone to flexing. 6 Assembly tools and gauges 6.1 General The tools a

25、nd methods shown in this section for the installation, swaging and removal of thin wall inserts are mandatory (see clause 4) for standard installations. When installing inserts in counterbores or other applications, e.g., curved surfaces, where standard tooling is unsuitable, alternative tools are p

26、ermissible but all the dimensions in the tables must be adhered to. 6.2 Installation drive tool Figure 2 shows an example of the installation drive tool configuration and Table 2 gives the relevant tool dimensions to ensure the correct tool size is used for screwing the insert into the tapped hole.

27、The driving feature shall be hexagonal, the insert driving feature shall be tri-lobed but other tool features may vary depending upon the manufacturer Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or n

28、etworking permitted without license from IHS-,-,-prEN 3298:20066 D EBA 0,55 0,50 C Figure 2 Table 2 Dimensions in millimetres A B C D E Short insert Long insert 0,3 0,2 + 0,050 0,15 0,05 EN3236-050 EN3237-050 7,3 2,50 4,435 1,05 6,95 EN3236-060 EN3237-060 8,5 2,70 5,325 1,30 7,95 EN3236-070 EN3237-0

29、70 10,5 3,10 6,325 1,55 8,95 EN3236-080 EN3237-080 12,5 3,50 7,175 1,75 9,95 EN3236-100 EN3237-100 16,0 4,20 9,015 2,25 11,95 For recommended drive tools, see Annex A, Table A.2. 6.3 Swage tools Table 3 gives the tool dimensions related to insert diameter code to ensure the correct tool size is used

30、 for swaging the insert into the component. Figure 3 shows an example of the swage tool configuration. The swage tool has a protective nylon washer, see Figure 3, which acts as a stop during the swaging operation and helps to protect the surface of the component from damage. This must be replaced wh

31、en dimension “Fmax.“ is exceeded. The use of incorrect tools will cause damage to the insert and surrounding material and may also cause the flange(s) of the component to be distorted. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA

32、Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-prEN 3298:20067 F GH1 2 32,5 1,5 Key 1 Shape optional 2 Rad. J 3 Nylon stop washer (Replaceable) Figure 3 Table 3 Dimensions in millimetres F G H Rad. J Short insert Long insert + 0,1 0 0,015 0,015 0,25 EN3236-050 EN3

33、237-050 2,255 5,975 3,775 0,65 EN3236-060 EN3237-060 2,455 6,995 4,575 0,80 EN3236-070 EN3237-070 2,655 8,005 5,575 1,00 EN3236-080 EN3237-080 3,055 9,025 6,275 1,00 EN3236-100 EN3237-100 3,755 11,085 7,775 1,15 For recommended swage tool numbers, see Annex A, Table A.3 and Table A.4. 7 Installation

34、 procedure 7.1 Insertion Screw the insert into tapped hole in a clockwise direction using the appropriate drive tool selected from Table 2 (Figure 2) until the insert is 0,40 mm to 0,65 mm (for manual installation) or 0,50 mm to 0,65 mm (for power tool installation) below surface of parent metal as

35、shown in Figure 4. Check that the insert is flush with or just below the bottom of the chamfer. Due to the configuration of the inserts, they may be “crimped” externally into an elliptical shape by the manufacturer to achieve the self-locking effect on the internal thread. This may make the insert a

36、 tight fit into the tapped hole and it may be necessary to apply additional torque. This shall be only up to a maximum of Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without l

37、icense from IHS-,-,-prEN 3298:20068 0,5 Nm using hand pressure only. If the insertion force is high it has been found to be beneficial to run a tap into the tapped hole that is at the upper end of the tolerance range (e.g., a GH 5 tap as designated in the USA). 2 1 23 4Key 1 Insert installation dept

38、h before swaging for manual tools: 0,400,65mm for power tools: 0,500,65mm (see clause 6 for after swage inspection) 2 Serrations in counterbore of hole Key 2 Serrations in counterbore of hole 3 Serrations on insert 4 Line up serrations between Insert and counterboredhole to provide “best fit” Figure

39、 4 Figure 5 7.2 Insert alignment prior to swaging Before swaging the insert ensure the mating component is well supported, especially in the area the inserts are installed Where a serrated counterbore is used, i.e. with the short inserts EN 3236 series in titanium, nickel and steel alloys, it is ess

40、ential that the insert serrations line up to provide “best fit” with the counterbore serrations whilst maintaining the 0,40 mm to 0,65 mm installation depth below the surface of the parent metal (see Figures 4 and 5). Where possible use 10 1 magnification plus illumination as an aid for fitting and

41、inspection. In some installations, the quality of the serrations may be better defined on one side of the counterbored hole than the other. In these cases, the insert serrations shall be aligned with the better-defined serrations on the hole to obtain the “best fit”. Copyright Association Europeene

42、des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-prEN 3298:20069 7.3 Swaging To swage and lock insert in place apply sufficient force to the appropriate swage tool selected from Table

43、 3 (Figure 3) using one of the following methods. First preference for swaging of inserts shall be power tooling (a list of approved power swaging tools is shown in Annex A), but where this is not practical manual swaging may be used, i.e. hammer or mechanical press. The insert is correctly swaged a

44、nd locked when the gauging criteria shown in 7.4 and Figure 6 is achieved. During the swaging operation care must be exercised to ensure no unwarranted force is used, which could cause damage to the component into which the insert is being installed. If difficulty is experienced with the removal of

45、the swage tool after swaging, its release may be assisted by a very gentle rocking action, care being taken not to cause cracking to the insert or damage to the parent component. Removal may be particularly difficult when inserts have been swaged into a non pre-broached hole, i.e. those assembled in

46、to light alloy components Key 1 When using manual swaging, inserts should be effectively installed when the replaceable washer face touches the parent component surface; this is not applicable with power tooling. In both instances the correct swaging shall be confirmed by inspection using correct af

47、ter swaging gauge, see 7.4. 2 Replaceable washer Figure 6 Swaging of insert Figure 7 After swage dimensions B A 1 2 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license

48、 from IHS-,-,-prEN 3298:200610 7.4 After swage inspection After the insert has been swaged, the swaged insert shall conform to the dimensional requirements of Figure 7 and Table 4. Inserts installed using a power tool will exhibit tooling steps caused by the split swaging jaws. The dimensional requirements “A” and “B” shall be inspected using one of the after swage checking gauges specified in Table 4 and shown in Figure 8, inserts installed using the power tooling will need to be inspected using the power tool after swage gauge (this gauge can als