AECMA PREN 2583-1987 Aerospace Series Bolts in Heat Resisting Nickel Base Alloy NI-P100HT(Inco 718) Classification 1275 MPa 650 Degrees Celsius Technical Specification Issue P 1《航空.pdf

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1、I l i I I l l l l I Edition approved for publication 2 November 1987 AECMA PREN2583 87 101231L 0003b01 8 - Comments should be sent within six monfhs C8 Chairman Mr. WILLIAMS after the date of publication decision A.E.C.M.A. 88, Ed. Malesherbes 75008 PARIS - FRANCE A.E.C.M.A. STANDARD NORME A.E.C.M.A

2、. A.E.C.M.A. NORM prEN 2583 Issue P 1 22 May 1987 DIT PAR LASSOCIATION EUROPEENNE DES CONSTRUCTEURS DE MATRIEL AROSPATIAL 88, boulevard Malesherbes, 75008 PARIS -TL. 45-63-82-85 UDC : Key words ENGLISH VERSION Aerospace series Bolts in heat resisting nickel base alloy NI-PI 00HT(lnco 71 8) Classific

3、ation : 1275 MPa/650 OC Technical specification Srie arospatiale Luft- und Raumfahrt Vis en alliage base nickel rsistant chaud NI-PI OOHT (Inco 71 8) Classification : 1275 MPa/650 OC Schrauben aus hochwarmfester Nickelbasislegierung NI-PI OOHT (Inco 71 8) Klasse : 1275 MPa/650 OC Spcification techni

4、que Technische Lieferbedingungen This Aerospace Series pre-standard has been drawn up under the responsibility of AECMA (Association Europenne des Constructeurs de Ma frie1 Arospatial). It is published on green paper for the needs of AECMA-Members. It has been technically approvedby the experts of t

5、he concerned AECMA Commission following comment by the Member countries. Subsequenf to the publication of this pre-standard the Pechnical content shall not be changed to an extent that interchangeability is affected, physically or functionally, without re-identification of the standard. After examin

6、ation and signature of the AECMA Standard Checking Centre (NPS) and formal agreement of the Official Services of the Member counfries it will be submitted as a draft European Standard to CEN (European Committee for Standardization) for final vote. Copyright Association Europeene des Constructeurs de

7、 Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-,AECMA PREN2583 87 10123LL O003602 T prEN2583 Page 2 Contents - 1). Scope and field of application 2). References 3). Definitions 3.1). Production batch. 3

8、.2). Inspection lot. 3.3). Discontinuities. 3.4). Test temperature. 3.5). Simple random sampling. 3.6). Critical defect. 3.7). Major defect. 3.8). Minor defect. 3.9). Sampling plan. 3.10.Limiting quality. 3.11).Acceptable quality level. 3.1Z).FinisRed bolt. 3.13).Definition document. 4).Certificatio

9、n and quality assurance. 4.1). Qualification. 4.2). Acceptance. 4.3). Quality system certification. 4.4). Responsibility for inspection and tests. 4.5). Inspection and test report. S).Table 1 : Technical requirement and test methods. 5.1). Materials. 5.2). Dimensions. 5.3). Manufacturing. 5.4). Mech

10、anical properties. 5.5). Metallurgical properties. 5.6). Product identification, 5.7). Delivery. Table 2.: Material removal. Table 3.: Qualification testing requirements for Table 4.: Summary of tests - Qualification and Table 5.: Minimum tensile ,tension fatigue and stress Table 6.: Classification

11、of defects. Table 7.: Sampling plans for visual inspections and Table 8.: Sampling plans for the inspection of Table 9.: Thread discontinuities - maximum depth TablelO.: Variable sampling for tensile tests. bolt samples. Production acceptance. rupture loads. dimensional characteristics. mechanical a

12、nd metallurgical characteristics. of permissible faults Figure 1.: Head structure and grain flow. Figure 2.: Distortion in fillet area. Figure 3.: Grain flow in thread. Figure 4.: Non-permissible laps,seams and surface irregularities. Figure 5.: Permissible laps, seams and surface irregularities. Fi

13、gure 6.: Crest lap imperfections. Figure 7.: Metallurgical specimens. 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 PREN2583 87 m 1012311 O0036

14、03 1 m * 1. 2. prEN2583 Page 3 Scope and field of application This standard specifies the technical, qualification and quality assurance requirements for bolts in material NI-PlOO-HT(1nco 718) of tensile strength class 1275MPa at room ternperature,maximum test temperature of material 65OoC. Primaril

15、y for Aerospace applications it is applicable to such bolts definition References IS0468 ISO 2859/1 IS33452 I503453 IS03534 IS06508 IS07961 IS09002 EN2002-8 EN2952 EN3039 EN3041 EN3042 EN3219 CN/TR3040 when referenced on the product standard or document. : Surface roughness - parameters, their value

16、s and general rules or specifying requirements. : Sampling proceqres for inspection by attributes - Part i: Sampling Plans indexed by Acceptable Quality Level(AQL) for Lot by Lot inspection (Revision of ISO2859-1974). 1). : Non Destructive Testing: Penetrant inspection - General principles : Non des

17、tructive testing - Liquid penetrant inspection - Means of verification : Statistics -Vocabulary and symbols : Metallic materials: Hardness test: Rockwell : Aerospace: Fasteners , bolts: test methods. i). : Quality systems - Model for quality assurance : Aerospace Ceries: Test methods-for metallic te

18、st. Scales A,B,C,D,E,F,G,H,K. in production and installation. materials - Part 8: Micrographic determination of grain size :Aerospace Series: Heat resisting nickel base alloy NI PlOO HT - Solution treated and cold worked bar for hot upset forging for fasteners Aerospace series: Quality systems: sup

19、lementary requirements to IS09002 appyicable to the manufacture/processing of materiel for propulsion standard parts. 1). Aerospace series: Propulsion standar par s Manufacturing process - change procaure Foi qualified parks- i). Aerospace ser%es t PropUlSiQri at-andard parGf5 f Qualification proced

20、ure. 1) Aerospace Series: Heat resistin nickel base alloy NI PlOO HT - Cold worked and softened- Bar and wire for continuous cold forging or extrusion of fasteners. Aeros ace series: Propulsion standard Qualification : List of qualified manu!$z%;ers. 1) i) In preparation Copyright Association Europe

21、ene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PREN2583 87 E 1012311 0003b04 3 M prEN2583 Page 4 3- Def.initians. 3 - 1 3 . 2 .3. 3 :3 - 4 3.5 13- 6 3.7 3.8 Production batc

22、h: Quantity of f-inished bolts fabricated by the same process from a single material cact(sing1e heat. of alloy) ,having the same basic part number and diameter, heat treated.togetner to the same specified condition and produced as one continuous run. Inspection lot: Consists of bolts from a single

23、production batch of the same part number which completely defines the bolt. Discontinuities. .3.3.1 Crack: Rupture in the material which may extend in any direction and which may be intercrystalline or tranccrystallyne in character. 3.3.2 Seam: Longitudinal surface defect in the form of an unwelded

24、open fold in the material. 3.3.3 Lap: Surface defect caused by folding over metal fins or sharp corners and then rolling or forging them into the surface. 3.3.4 Inclusion: Non-metallic particles originating from the material making process. They may exist as discrete particles or strings of particle

25、s extending longitudinally. Test temperature: Ambient temperature, unless otherwise specified Simple random sampling 1): The taking of n items from a population of N items in such a way that all possible combinations of n jtems have the came probability of being chosen - Critical defect I): A defect

26、 that according to judgement and experience, is likely to result in hazardous or unsafe conditions for individuals using, maintaining, or depending upon the considered product, or that is likely to prevent performance of t.he function of a major end item. Major defect 1): A defect other %han critica

27、l, that is likely to result in a failure or to reduce materially the useability of the considered product for its intended purpose. Minor defect 1): A defect that is not likely to reduce materially the useability of the considered product for its intended purpose, or that is a departure from establi

28、shed specification having little bearing an the effective use or operation of this product- 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 0. I 1 O

29、O - a AECMA PREN2583 87 m iIOiI23LL 0003605 5 mp prEN2583 Page 5 3.9 Sampling plan 1): A plan according to which one or more samples are taken in order to obTain information and possibly to reach a decision. 3-10 Limiting quality LU i): In a sampling plan, a quality 10 level which corresponds to a s

30、pecified and relatively low probability of acceptance - in this case 10% probability of acceptance. It is the limiting lot quality characteristic that a lot of this quality would occur. When expressed as a per cent defective, it may be referred to as a lot tolerance per cent defective. 3.11 Acceptab

31、le quality level I): A quality level which in a sampling plan corresponds to a specified but relatively high probability of acceptance. It is the maximum per cent defective (or the maximum number of defects per hundred units) that., for purposes of sampling inspection, can be considered satisfactory

32、 as a process average. 3.12 Finished bolt: A bolt ready for use, inclusive of any possible treatments and/or surface coatings, as specified in the dimensional standard or definition document- 3.13 Definition document: Docimerit specifying all the requirements for bolts i.e. - metallurgical - geometr

33、ical and dimensional - Eunctional (strength and temperature classes). -_-_- :l)- Definitions taken in SO3534-1977 1 1 I I in course of revision within 150/TC69).: Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reprod

34、uction or networking permitted without license from IHS-,-,- . AECMA PREN2583 87 W LOL2311 000360b 7 W prEN2583 Page Ei 4 - Certification arid quality assurance. The allocation of tests corresponding to the requirements of this standard is as follows: 4.1 Qualification. 4.1-1 Purpose- The purpose of

35、 qualification tests is to ensure that the bolt design and bolt manufacturing conditions allow the bolt to comply with the requirements of this standard. 4 - 1 2 Conditions. The qualification tests summarised in table 3 shall be performed on each type and diameter of bolt. Proposed changes in manufa

36、cturing source or procedure shall be subject to the requirements of EN3041 - 25 bolts selected from a single inspection lot by simple random sampling shall be Subjected to the qualification tests. The number of bolts to be subjected to each test as well as the method(s) ta be used are specified in t

37、able I. The tests to be applied t.o each bolt. are shown in table 4. The test programme may possibly be reduced, this decision will be based on the comparison of results obtained from parts of similar design, size and manufacturing conditions- All or part of these tests may also be performed for pro

38、duction acceptance, when a reinforced inspection seems to be necessary, or to survey bolts that have not proved satisfactory in use. In that case, the sample to be subjected to these tests is the same as that used for production acceptance tests. 4.1.3 Qualification test requirements and procedures.

39、 The qualification test. requirements and procedures shall be to the requirements of EN3042. 4-1.4 Qualified manufact.urers- A list of qualified manufacturers for specific standard parts is listed in CN/TR3040. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS

40、 under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PREN2583 87 m LOL23LL 0003b07 7 m 4.2.1 Purpose- The purpose of acceptance tests is to check, as simply as possible, bv a method representative of actual use conditions, with the uncerta

41、inty inherant to statistical sampling, that the bolts constituting the batch satisfy the requirements of this standard. 4.2.2 Conditions. Acceptance tests are summarised in table 3. They chal1 be performed on each batch. Table i specifies- the test method and sampling plan to be irsed for each test.

42、 Bolts from the batch to be tested shall be selected by simple random sampling. Each bolt may be submitted ta several tests. The bolts t.o be subjected to destructive tests may be those on which non-destructive tests have been performed. 4.3 Quality system certification- 4.3.1 Purpose. The purpose o

43、f quality system certification is to ensure that the manufacturer has demonstrated the acceptability of his quality system and his ability for continuing production of parts to this standard, to the required level of quality. 4.3.2 Requirements and procedure. The requirements and procedures for qual

44、-ity system certification shall be to the requirements of SO9UQ2 and EN339- 4-4 Responsibilitv for inspection and tests. The manufacturer is responsible for the performance of all inspection and test requirements as specified herein. Each manufacturer will use their own or exceptionally. any other f

45、acilities approved in accordance with 4.1 and 4.2 for the implementation af these inspection and test requirements. 4-5 Inspection and test report. A test report showing actual numerical values shall be provided at the purchasers option as part. of the terms of the purchase order. Copyright Associat

46、ion Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PREN2583 87 W LOL231L 0003b08 O W prEN2583 Page 8 1 I I I ;standard or definition docuaent. :approved system of gau

47、ging. l I I I l I I I I l I I I l I I I I I I I I I I I I l l I I I I l l I I l-(-l-l l - I- (5.3.1 !Forging IThe heads of the bolts shall be :The method of forging shall I :formed by hot or cold forging. If (be approved. I I :hot forged the forgin temperature! Ishall not exceed 1150 C and shall lbe

48、 air cooled. The heating equipm-I :ent for forging shall be of a type: I I :which ensures a consistent tenper-: I I fature throughout the batch. I I I I I I I E I I I t I I I I I I I ;_-I -1-1 I - 15.3.2 l l :sphere shall not cause any surface:shall be approved. l l Icontaiination except as permitted I I l :by clause 5.5.6. I t :Anv scale which will not be reiaov-Ifhe equipment for abrasive l I l :ed by subsequent mach