AECMA PREN 3388-1990 Aerospace Series Fasteners Externally Threaded in Heat Resisting Nickel Base Alloy NI - P100HT (Inconel 718) Classification 1275 MPa 650 Degrees Celsius Manufa.pdf

1、A.E .C. M .A. STAN DARD NORM E A.E.C. M .A. A.E.C.M.A. NORM Edition approved for publication Comments should be sent within six months after the date of publication decision 88, Bd. Malesherbes 1990-08-24 A.E.C.M.A. 75008 PARIS - FRANCE prEN 3388 issue P 1 August 1990 C8 Chairman Mr. WILLIAMS DIT PA

2、R LASSOCIATION EUROPENNE DES CONSTRUCTEURS DE MATERIEL AROSPATIAL 88, boulevard Malesherbes, 75008 PARE -TL. 45-63-82-85 UDC : Key words : ENGLISH VERSION Aerospace series Fasteners, externally threaded, in heat resisting nickel base alloy Nl-Pi OOHT (Inconel 71 8) Classification : 1275 MPa/650 OC M

3、anufacturing method optional Technical specification Srie arospatiale Luft- und Raumfahrt lments de fixation, filets, en alliage base nickel rsistant chaud NI-PI OOHT (Inconel 71 8) Classification : 1275 MPa/650 OC Mode de fabrication non impos Verbindungselemente mit Auengewinde aus hochwarmfester

4、Nickelbasislegierung NI-P100HT (inconei 71 8) Klasse : 1275 MPa/650 OC Herstellverfahren nach Wahl Spcification technique Technische Lieferbedingungen This Aerospace Series pre-standard has been drawn up under the responsibility of AECMA (Association Europenne des Constructeurs de Matriel Arospatial

5、). It is published on green paper for the needs of AECMA-Members. It has been technically approved by the experts of the concerned Commission following comment by the Member countries. Subsequent to the publication of this pre-standard, the technical content shall not be changed to an extent that in

6、terchangeability is affected, physically or functionaly, without re-identification of the standard. After examination and signature of the AECMA Standard Checking Centre (N?S) and formal agreement of the Official Services of the Member countries it will be submitted as a draft European Standard to C

7、EN (European Committee for Standardization) for final 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-,-,-I i AECMA PREN3388 90 W LOL23LL 0005640 6 p

8、rEN 3388 Page 2 Contents. 1). Scope and field of application 2). References 3). Definitions 3.1). Production batch. 3.2). Inspection lot. 3.3). Discontinuities. 3.4). Test temperature, 3.5). Simple random sampling. 3.6). Critical defect. 3.7). Major defect. 3.e). Minor defect. 3.9). Sampling plan. 3

9、.10).Limiting quality. 3.11).Acceptable quality level. 3.12).Finished part. 4).Certification and quality assurance. 4.1). Acceptance- 4.2)- Quality system certification. 4.3). Responsibility for inspection and tests. 4.4). inspection and test report. . 5I.Table 1 : Technical requirement and test met

10、hods. 5.1). Material. 5-21. Dimensions. 5.3). Manufacturing. C.4). Mechanical properties. 5.5). Metallurgical properties. 5.6). Product identification. 5.7). Delivery. Table 2.: Summary of tests - production acceptance. Table Li.: Minimum tensile loads. abe 4.: Classification of- defects. Table 5.:

11、Sampling plans for visual inspections and Table 6.: Sampling plans for the inspection of Table 7.: Thread discontinuities - maximum -depth Table Ei.: Variable sampling for tensile tests. Figure 1.: Distortion in fillet area. Figure 2.: Non-permissible laps,seams and surface irregularities. Figure 3.

12、: Permissible laps, seams and surface irregularities. Figure 4.: Crest lap imperfections. Figure 5.: Metallurgical specimens. I dimensiona characteristics. mechanical and metallurgical Characteristics. of permissible faults. o O Copyright Association Europeene des Constructeurs de Materiel Aerospati

13、al Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PREN33BB 90 LOLS3LL 0005b41 B -A - - prEN 3388 Page 3 O a O -0 1 Scope and field of application This standard specifies the technical and quality assurance requirements

14、 for externally threaded fasteners in material NI-P100-HT (Inca 718) of tensile strength class 1275 MPa at room temperature, maximum test temperature of material 650 “C. The externally threaded fasteners specified herein may be manufactured by machining from bar Gr by forging ar the manufacturers op

15、tion, if forged there is no requirement for control of grainflow. Primarily for Aerospace applications it is applicable to such externally threaded fasteners when referenced on the product standard or drawing. 2 References IS0 468, IS0 2859/1, IS0 3452, IS0 3453, IS0 3534, IS0 6508, IS0 7061, IS0 90

16、02, EN 2952, EN 2961, EN 3039, EN 3219, Surface roughness - parameters, their values and general rules for specifying requirements Sampling procedures for inspection by attributes - Part 1 : Sampling Plans indexed by acceptahle Quality Level (AQL) for Lot by Lot inspection (Revision of IS0 2859-1974

17、) 1) Non destructive testing - Penetrant inspection - General principles Non destructive testing - Liquid penetrant inspection - Means of verification Statistics - Vocabulary and symbols Metallic materials : Hardness test : Rockwell test. Scales A, B, Aerospace : Fasteners, bolts : test methods 1) Q

18、uality systems - Model for quality assurance in production and installation Aerospace series : Heat ressting nickel base alloy NI-P100-HT - Solution treated and cold worked bar for hot upset forging for fasteners 2) Heat resisting nickel base alloy NI-P100-HT - Cold worked and solution treated - Rar

19、 for machining for fasteners Aerospace series : Quality systems : supplementary requirements to IS0 9002 applicable to the manufacture/processing of materiel for propulsion standard parts i) Aerospace series : Heat resisting nickel base alloy NI-P100-HT - Cold worked and softened - Bar or wire for c

20、ontinuous cold forging or extrusion of fasteners C, D, E, F, G, Hs K 2) 2) 1) In preparation at the date of publication of the present standard. 2) Published as AECMA pre-standard at the date of publication of the present standard. Copyright Association Europeene des Constructeurs de Materiel Aerosp

21、atial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,- AECMA PREN33BB 90 W LOL23LL 0005642 T W prEN 3388 Page 4 3. sphere shall not cause any surfacefshall be approved. I I I I I Icontamination except as pernitted I I I I I I

22、 :by clause 5,5.2. I I l I 1 I ;Any scale which will not be reiiov-lThe equipmt for abrasive 1 I I I I led by subsequent machining shall :blasting shall be approved. I I I l I :be removed by abrasive blasting. I I I 1 15.3.3 IHeat treatrent :The heat treatment iediur or atmo-IThe heat treatrent equi

23、pment 1 I l l I I I I 1 1 I I 1 I I l I l I l I I I I I I I I I I I I l I 15.3.3.1 Isohtion heat :Forged parts shall be solution I I I I I I l I I l I I I I I I I I l 1 I l I I 1 I I I I I I l l I I treatment Itreited atoa taperature of I I I I I I 1930 C-1010 C,holding at th8 se1ec-I I I I I I Ited

24、 taperature within t5 C for f I l I l I :not less than 1 hour, a-I- 15.3.3.2 :Precipitation :Before thread rolling the parts I l :heat treatment Ithe parts shali be grecipitation I I I I I l Itreated at 720 C t5 C holding at I I I I I Iheat sor 8 hours,-furnace cqling I 1 I I I I :at 55 C tSC per pu

25、r to 620 C t5I I I l I I IC, holding at 620 C for 8 hours- I 1 I I I :followed by air o; faster. I I l I I I :Instead of theo55 C per hour cool-I . I I 1 I l ling rateto 620 C, parts may be I I I l I I Ifurnace cooled at a;y rate provi- I I I I I I lded the time at 620 C is adJUSted I I I I l I :to

26、give a total precipitation tiiteI I I I I I lof approximately 18 hours. I I I I I-1-1- ;-l-I I 1 surface ;treatment the parts shall have all I I I I I Icontamination fthe shank and tearing surface of I I I I I I ithe head ground: I 1 I I l I la) for the removal of all surface I I I I I I I contamina

27、tion and oxide I I l I l penetration, 1 I I I I I Ib) to obtain a clean siooth I l I I I I 1 surface. I l I I (-I-1- ; - 15.3.5 ;Threads ;Threads shall be forred on the I I I I I I :solution treated, precipitation I I I l I I Itreated and iiachined parts by a I I I 1 I I !single thread rolling opera

28、tion. I I I I I I I I I I l 1 1 I I I l I l 1 I I 1 I I I I I I I 1 I I 1 I l I I I I l 1 I I I 1 I 1 I I l I I I I I I I I I I I I I I I I I I I I 15.3.4 1Reioval of IAfter solution and precipitation I I l I I I I l I I 1 l l l I l I I I I I I I 1 I I I I 1- I l l I I I l I l l I I I I I I I 1 I I

29、I I I-! I I l I I l I I l I I I I I l l I l 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-,-,-AECMA PREN3388 90 W LOl1231L 0005b117 9 W O O prEN 3388 Pag

30、e 9 15.3.6 ;Cold rolling I I I I I I I I I I I I I I I I I I l I I I I I l I I I I I I I l I I I l I I I 1 1. I r I l l I l I I 1 I I I I I I l I I I I I I I I I I I I I I I I 1 I I I I I l I I 1 I I :If specified on the product stan- IDiiencional check (see 5.5.2): Idard parts shall, after completi

31、on fand visual exaiination. I lof solution, precipitation treat- 1 I 1 Iient and iachining, have the : I Ifillet radius cold rolled suffi- f I l iciently to remove all evidence of I I I machining. I I :Cold rolling the head to shank : I ifillet radius may cause distortion: I lof the fillet area. I l

32、 I Ihy such distortion shall be in I I laccordance with the requireients I I :of figure 1 unless otherwise 1 I l Ispecified on the product standard I lor drawing. I I :For parts with cpound radii bet-: I Iween head and shank, cold work : I lonly the radius that blends with I Ithe head, however it is

33、 acceptable: I Ifor cold work to extend over the f I I compound radius. 1 I I !The fillet shall not show evidence;% 5.5.3.1 I :of sem or inclusions. I I I I I l A I tables f I 1 I I 1 I I I I I I I I I I I I I I t 1 l I I I I I I t I 1 I I I I I l I 1 I I l 4a5 f I I I I I I I J I I I I I I t l I I

34、I I I I l I I l I I l I I I I I I I l l I I 15.3.7 :Surface :The surface roughness shall be as :The surface roughness of the I I I I I I I l Iroughness Ispecified on the product standard :thread shall be determined by: A tables l l for drawing prior to protective Ivisual coiparator nethod I ! 4a5 I

35、I I treatient . :See ISOjR468 I 1 I I-I-:-:-l- ;- f5.3.8 :Surface :Where applicable, all surfaces I% applicable coating I 1 I I 1 I I l l coating Ishall be coated as specified on :specification. tables I I l fthe product standard or drawing I I I485 I-f-1-:-1- i- I (properties I I I l I 15.4 :Mechan

36、ical I I I I I I I I I I I I I l I I I l l I I I 1 I I I l I I I 1 I I I I I r I I I I I I I I I l I l I I I I I I I I I I I I I I I I I 1 I I I l I I I 1 :-I-I-l-I-l -I I :strength :and the iiniiua tensile loads lable to the following: 1 I 1 I I I I Ispecified in table 4. Ialprotruding head bolts o

37、f f 1 I I l I r f grip length less than 2D; I I I 1 I 1 Ib)countersunk head bolts of f I I I I 1 i overall length less than 3DI I I I I f or bolts having an overaIl f I I I I I I length less than 18m. I I I I I I :In such cases acceptability f 1 I I I l Ishall be based on the results: f I I I 1 Ifro

38、i test bars of the same I I I I I I Iiaterial heat treated within 1 I I I I I tthe same process cycle. I 1 I I 15.4.1 Ifensile !The finished parts shall withst- :Tensile tests are not applic-: : I I 1 1 I I I I I I r I l I I I I I I I 1 1 I I I I I I I I I t I I . Copyright Association Europeene des

39、 Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PREN3388 90 m LOL23LL 0005b1i8 O m prEN 3388 Page 10 15.4.2 ;Hardness :The hardness of the finished partsIFor hardness testing see I

40、 I I Ishall be uniforn and within the lIS6508. IA I I I range Rockwll C36-C45, but hardn-; I I less of the threaded section and of I .I l Ithe head to shank fillet area may I I I I Ibe higher as a result of the cold I I 1 I I I l I 1 I I l I I 1 I table 6 COlUM A I I I I l I l :working operations, I

41、 I I I I I-I-I-l- I I I - i- 15.5 Iktallurgical I )Note: the saie test sample f I lproperties I Iiay be utilised for iore than: I I I I t lone test provided that none I I I I I I lof the characteristics of the: I I I I I Isaiples are altered during : I I I I I Ithe exaination procedure I I I I-f-I-I

42、-l I - I-# 15.5.1 :Surface I Ihardening Idness fro1 core to surface except f (X100.). Speciiens shall be I A f table 6 I I lac produced during cold working offtaken froi the finished bolts: f column BI I I Ithe head to shank fillet radius flscrews or studs as shown in I I I I I fand during rolling o

43、f threads. :figure 5, The speciaens shall: I I I I I :be etched in a suitable I I I I I I :solution. In case of dispute I l I I I :over the results of the I l l 1 I I I microscopic exaiination, : I I I I I laicrohardnecs testing shall i I I I I I fbe used as a referee f I I I I I :a Vickers hardness

44、 reading f I I I I I luithin 0,08m of an unrolled f I I I I I :surface which exceeds the I I I l I I :reading in the core by nore f I I I I I :than 30 points shall be evid-l I I I I I lence of nonconforiance to i I I l I I I this requireient . I I I 15.5.2 :Surface IThe bearing surface of the head,

45、:Microscopic exaiination I I .I I fcontauination :the head to shank fillet, shank :(see 5.5.1). I A i table 6 : I I Idiaaeter and threads shall be free: 1 I column a: l I Ifroi surface oxide. Depth of oxide: I I l I I :penetration on the umchined sur-: I I I l I Ifaces of the head shall not be 1 I I

46、 I I I ;greater than 0,025ie. I I I I I l I I 1 I I I l I I I I I I I I 1 I I I I I 1 I I I l I I I I I I 1 Parts shall have no change in har- Hicroscopic examination I I I I I I 1 I I I l I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I l I I I I I I I I l l I I I I I I I l I I l I I I I I I I I I I I I I I I I l I I I I I I I I I - I-# I-I-“-1-I- I I I I t 1 l l I I I I I I I l l I I 1 I t I 1 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permit