1、AECMA STANDARD NORME AECMA AECMA NORM Edition approved for publication 2002-03-29 prEN 2286 Edition P I March 2002 Comments should be sent within six months after the date of publication to Gulledelle 94 Mechanical Domain Mr Feltham AECMA-STAN 5-1200 BRUXELLES PUBLISHED BY THE EUROPEAN ASSOCIATION O
2、F AEROSPACE INDUSTRIES - STANDARDIZATION (AECMA-STAN) Gulledelle 94 - B-1200 BRUXELLES - Tel. (+32) 2 775 81 10 - Fax. (+32) 2 775 81 11 Will supersede ICs: EN 2286: 1989 Descriptors: ENGLISH VERSION Aerospace series Bushes, flanged aluminium alloy with self-lubricating liner Dimensions and loads Sr
3、ie arospatiale Bagues paulement en alliage daluminium garniture autolubrifiante Dimensions et charges Luft- und Raumfahrt Buchsen mit Flansch aus Aluminiumlegierung mit selbstschmierender Beschichtung Mae und Belastungen This “Aerospace Series“ Prestandard has been drawn up under the responsibility
4、of AECMA-STAN (The European Association of Aerospace Industries - Standardization). It is published on green paper for the needs of the European Aerospace Industty. It has been technically approved by the experts of the concerned Domain following member comments. Subsequent to the publication of thi
5、s 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 review by users and formal agreement of AECMA-STAN it will be submitted as a draft European Standar
6、d 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 ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 2 prEN 2286: 2002 Con tents Pag
7、e 3 Normative references . . 3 Required characteristics . . 3 . Designation 6 Marking . 6 Technical specification . . 6 Design recommendation . 7 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or network
8、ing permitted without license from IHS-,-,-Page 3 prEN 2286: 2002 1 Scope This standard specifies the characteristics of flanged bushes in aluminium alloy with self-lubricating liner and the design recommendation of shafts and housings. The bushes are intended for operation within the temperature ra
9、nge of - 55 OC to 163 OC and assembly with an interference fit into fixed and moving aerospace parts. 2 Normative references This European Standard incorporates by dated or undated reference, provisions from other publications. These normative references are cited at the appropriate places in the te
10、xt and the publications are listed hereafter. For dated references, subsequent amendments to or revisions of any of these publications apply to this European Standard only when incorporated in it by amendment or revision. For undated references the latest edition of the publication referred to appli
11、es. EN 2086 EN 2101 EN 2284 EN 231 1 EN 2701 Aerospace series - Aluminium alloy AL-P2618A - T851 - Hand forgings - a I 150 mm 1) Aerospace series - Chromic acid anodizing of aluminium and wrought aluminium alloys Aerospace series - Sulphuric acid anodizing of aluminium and wrought aluminium alloys A
12、erospace series - Bushes with self-lubricating liner - Technical specification Aerospace series - Aluminium alloy (2024) - Solution treated, water quench, cold worked and naturally aged (T3) - Drawn tube for structures - 0,6 I a I 12,5 mm 2) Aerospace series - Aluminium alloy 2024-T3511 drawn bar a
13、I 75 mm 2) EN 2704 3 Required characteristics 3.1 Configuration: according to figure I. Dimensions, masses: according to figure 1 and table I. Dimensions apply after surface treatment. Configuration - Dimensions - Masses 3.2 Surface roughness According to figure 1. 3.3 Materials Bush: Aluminium allo
14、y according to EN 2086, EN 2701 or EN 2704. Liner: Self-lubricating wear resistant material consistent with the requirements of EN 231 1. 3.4 Surface treatment Chromic acid anodizing according to EN2101A or Sulphuric acid anodizing according to EN2284A. 1) Published as AECMA Prestandard at the date
15、of publication of this standard 2) Published as AECMA Standard at the date of publication of this standard 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-
16、,-,-Page 4 prEN 2286: 2002 X Dimensions in millimetres I- a OSO to 0,75 Chamfer machined before bonding b i Y Chamfer or radius at manufacturers option Chamfer machined after bonding Figure I Table 1 Dimensions in miilimetre! Il - 0,l - 0,4 6 8 10 12 15 16 18 20 22 25 28 30 32 35 40 45 50 Mass in kg
17、ll O00 pieces I - I - 150.7 I - 160.3 1 - 169.9 179.6*189.2 198.81 Only bushes whose masses lie within the bold lines are standard. The recommended sizes are indicated by *. I Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for Re
18、saleNo reproduction or networking permitted without license from IHS-,-,-Page 5 prEN 2286: 2002 Table 2 d I /I I Permissible radial load IPermissible Permissible radial load 1 Permissible -1 static axial load c,“ ml static axial load c,“ kN I kN 1 kN 1 mml mml kN 1 kN I kN 6 6 - - 15 60,6 50,6 20 89
19、,4 74.6 8 6 - 28 22 100,9 84,3 88,3 25 118,2 98.5 8 10 - 28 1356 113,O I 15 64,9 54,2 I 10,l 8,4 886 14,2 11,9 6 8 - 20 95,8 80,0 30 22 108,2 90,3 93,4 33,6 16.1 13.4 10 12 8 10 12 - - - I 25 I 126.7 I 105.8 I 1 30 I 157,6 131,6 I 15 I 69.2 57.8 21 ,o 17,6 13.9 11.6 *I 39,4 20 102,2 85,3 _ 22 115.4
20、96.3 98,6 a7 L I 1 15 8 - 25 135,l 112,8 30 168,l 140.1 UL 353 29,7 14,8 12.4 10 12 - 41,3 31.6 32 181,3 151,1 20 111,8 93,3 22 126.2 105.4 15 16 10 - 41,2 34,3 24,l 20.1 35 25 147,8 123,4 106,2 30 183.9 153.5 12 15 - 45,l 313 26,3 42,6 35.5 35 219,9 183,6 20 127,7 106,6 18 10 12 15 20 - - - - 53.8
21、I 44.8 I 25 168,9 141 ,O 40 30 210,l 1754 119 26,8 22,4 49 68,O I 35 I 251.3 I 209.8 I 40 292,5 244,2 25 190.0 158.7 12 15 - 30 236,4 197,4 45 35 282.7 236.1 131.8 52,8 I I 1 20 22 - 40 329,l 274,8 45 375.4 31 3.5 12 15 - 25 1 21 1,2 176,3 30 I 262.7 21 9.3 20 22 - 144,6 35 314,2 262,3 40 365.7 305.
22、3 25 - 110,7 I 92,4 45 41 7,2 347,6 50 468.7 390.5 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-,-,-Page 6 prEN 2286: 2002 Number of this standard Code
23、for diameter d (see table 1) Code for length il (see table 1) J 4 Designation EXAMPLE: Technology code A B Without code Technology Bonded fabric liner Injection moulded liner Both technologies can be used at users convenience NOTE 1 The number of characters is constant, Zero (O) is inserted to the l
24、eft of the figure when the diameter d or length II is less than 10. NOTE 2 If necessary, the code 19005 shall be placed between the description block and the identity block NOTE 3 Parts manufactured before the issue of this standard shall be accepted without technology code. Table 3 5 Marking In add
25、ition to the manufacturers own marking, each bush and its package shall be marked with the identity block specified in clause 4 of this standard. The technology used by the manufacturer shall be stated within the identity block. Marking position and method are at manufacturers option and shall not h
26、ave any detrimental effect on the bush. Bushes which are too small to be marked with the full information required shall have this on the package only. 6 Tech n ka I specification According to EN 231 I. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under l
27、icense with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 7 prEN 2286: 2002 7 Design recommendation Bushes defined by this standard are intended to be installed by interference fit methods (see figure2). Therefore, the loads given in table 2 can only be
28、 ensured if the following mounting is applied. Key 1 Shaft 2 Bush 3 Housing a Housing diameter D H7 Sha diameter d f6 Figure 2 Hardness of the shaft: 50 HRC min. Surface roughness of the shaft: according to figure 2. The reduction in bore diameter d (see figure l), due to interference fit of the bus
29、h in the housing, has been taken into account when selecting tolerances for the shaft: f6 (clearance fit). When applied in actual usage, the coefficient of friction under load could be different from that defined in EN 231 1, since it depends on the following shaft definitions: Material, hardness, surface finish, surface treatment and installation conditions. 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-,-,-
