AECMA PREN 3765-1997 Aerospace Series Electrolytic Silver Plating for General Use Steels Heat Resisting Alloys Copper and Copper Alloys Edition P1《航空航天系列电解镀银通用铜和铜合金钢》.pdf

1、AECMA STANDARD NORME AECMA AECMA NORM prEN 3765 Edition P 1 April 1997 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - 8-1200 BRUXELLES - Tel. (32) 2 775 81 10 - Fax. (32) 2 775 81 11 ICs : Descriptors : ENGLISH VERSION Aerospace series Electrolytic silver plati

2、ng for general use Steels, heat resisting alloys, copper and copper alloys Srie arospatiale Luft- und Raumfahrt Argentage lectrolytique pour usage gnral Aciers, alliages rsistant chaud, cuivre et alliages de cuivre Elektrolytisches Versilbern fr allgemeinen Gebrauch hochwarmfeste Sthle, Legierungen

3、Kupfer und Kupferlegierungen 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 AECMA-Members. It has been technically approved by the experts of the concerned Tec

4、hnical 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 functionally, without re-identification of the standard. After examination and sig

5、nature 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) for formal vote. Nota - Extra copies can be supplied by B.N.A.E. - Technopolis 54

6、 - 199, rue Jean-Jacques Rousseau - 921 38 ISSY-LES-MOULINEAUX CEDEX Edition approved for publication 1997-04-30 Comments should be sent within six months after the date of publication to AECMA Gulledeiie 94 B-1200 BRUXELLES C7 Chairman Mr Wright aecma 199; Copyright Association Europeene des Constr

7、ucteurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-STD*AECMA PREN 37b5-ENGL 1777 W L03231L 0032773 277 Page 3 prEN 3765 : 1997 1 Scope This standard defines the electrolytic silver plating of stee

8、ls, heat resisting alloys, copper and copper alloys used in aerospace construction. 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 text and the publicat

9、ions 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 applies. IS0 1463 IS0 21

10、77 IS0 2859-1 IS0 3882 EN 2000 EN 2828 EN 2829 EN 2830 EN 2831 EN 2832 Metallic and oxide coatings - Measurement of coating thickness - Microscopical method Metallic coatings - Measurement of coating thickness - Coulometric method by anodic dissolution Sampling procedures for inspection by attribute

11、s - Part 1 : Sampling plans indexed by acceptable quality level (AQL) for lot-by-lot inspection Metallic and other non-organic coatings - Review of methods of measurements of thickness Aerospace series - Quality assurance - EN aerospace products - Approval of the quality system of manufacturers Aero

12、space series - Adhesion test for metallic coatings by burnishing Aerospace series - Adhesion test for metallic coatings by shot peening Aerospace series - Adhesion test for metallic coatings by shearing action Aerospace series - Hydrogen embrittlement of steels - Test by slow bending Aerospace serie

13、s - Hydrogen embrittlement of steels - Notched specimen test 3 Purpose of process To prevent fretting or seizure. 4 Definitions For the purposes of this standard, the following definitions apply Batch : Unless otherwise specified, it comprises parts of the same nature (shape, size, material) treated

14、 at the same time in the same bath and after having undergone the same pre-treatment and post-treatment. Ra : Surface condition - Arithmetic mean deviation of roughness, expressed in pm. Rm(max.) : Maximum specified tensile strength. Copyright Association Europeene des Constructeurs de Materiel Aero

15、spatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-STD-AECMA PREN 37b5-ENGL 11997 E LDL23bL 00112974 LU5 E Page 4 prEN 3765 : 1997 5 Classification of coatings 5.1 Type A Electrodeposit of silver, on a nickel strike with

16、 or without an undercoat of nickel, applied to parts which may reach 760 OC in continuous operation. 5.2 Type B Electrodeposit of silver, on a copper undercoat, applied to parts which may reach a maximum of 150 OC in continuous operation. 6 Information for the processor In addition to the designatio

17、n (see 151, the following information shall be given : the reference of the substrate standard and the metallurgical condition of the substrate ; the areas to be treated ; the duration and temperature of heat treatments before and after processing ; the electrical contact points or the areas where t

18、hese are prohibited ; the surface of the part in dm2 ; if required, the mechanical finishing. Condition of parts prior to processing Manufacturing process All welding, brazing, heat treatments including stress relief and machining operations, with the exception of those possibly performed on the coa

19、ting, shall have been completed before coating. The stress relief heat treatment conditions shall be determined according to the nature and the strength of the material. Stress relief treatment of nickel and copper alloys is not required. A slight discoloration by superficial oxidation is permitted.

20、 7.2 Surface roughness Unless otherwise specified the functional areas of the part to be coated shall have : Ra 1450 MPa Steels with R, (max.) I 1450 MPa Case hardened steels and other materials Type A 1) . Minimum Time 18 h 2h 5h Substrate I Type - Steels with 1 1 O0 I R, (max.) I 1450 MPa Steels w

21、ith R, (max.) 1450 MPa B I Other materials see annex C 3 see annex D 4 3 A Heat resisting steels and heat resisting alloys 2 4 3 2 3 2 3 3 Copper and I I 1 copper alloys 1 2 _ _ _ 1) Applies exclusively to parts not exposed to corrosion (e.g. parts inside sealed casing) 9 Post-treatment It shall be

22、carried out within 24 h of coating, unless otherwise stated in the design document, in accordance with table 2 : 130 - 150 5hto12h 130 - 150 24 h 130 - 150 Ih 1) Parts may be heat treated for a shorter time at a higher temperature if the conditions have been shown to be effective in reducing hydroge

23、n embrittlement and do not affect the performance of the part. 10 Removal of the silver plating The solution shall not attack the base metal (example for steel : an aqueous solution of nitrobenzene sulphonate sodium salt 55 g/l to 65 g/l and sodium cyanide 90 g/l to 100 g/l, temperature 30 OC to 70

24、OC). 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-,-,-11 Required characteristics 1 1.1 Appearance The coating shall have a smooth, adherent, satin and

25、uniform appearance, free from : - cracks ; - rough, burnt or excessive build-up ; - uncoated areas ; - pitting ; - blisters, pores or exfoliation. Some slight variation in brilliance, due to the geometry of the part is accepted. 11.2 Adhesion The deposit shall adhere to the whole surface. The deposi

26、t shall satisfy the test in 12.1 .I and 12.2.3. 11.3 Thickness Unless otherwise specified in the design document, the thickness of the silver, including any strike treatments, shall be (8 f 2) ym and the thickness of any undercoat shall be 3 ym to 10 pm. 1 1.4 Composition of the deposit Unless other

27、wise specified, the deposited metal shall contain at least 99,9 % of silver for type A and 99,5 % for type B. 11.5 Hydrogen embrittlement The application of coating system shall not cause any irreversible hydrogen embrittlement. 12 Inspection 12.1 Inspection of plated parts 12.1 .I Appearance and ad

28、hesion The visual inspection shall be made with a magnification of x 2,5 to show a lack of adhesion in the form of blisters or exfoliation. 12.1.2 Thickness 12.1.2.1 Local thickness IS0 3882. In case of dispute, IS0 21 77 or IS0 1463. 12.1.2.2 Average thickness - calculate the surface of the part ;

29、- after degreasing, weigh the part to the nearest O, 1 mg ; - remove the coating (see clause 10) : - rinse, dry and weigh. Loss of mass (9) x 10 O00 Surface (cm21 x 10,5 (g / cm3) Average thickness in prn = Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS und

30、er license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 7 prEN 3765 : 1997 Number of encrustations On 1 mm I10 On 10 mm I50 12.2 Test pieces Total length 5 0,06 mm I0,3 mm 12.2.1 General - Test pieces shall be made from the same material, with the

31、 same heat treatment condition as the parts they represent. - They shall undergo the same treatments at the same time in the same baths as the batch they represent. - Their form shall be representative of areas to be treated. - Inexpensive parts may be used as test pieces. - The definition of the te

32、st pieces shall be stated in the documents specified in 13.1. 12.2.2 Metallographic examination On a section taken through the coating, no dirt or contamination shall be visible at x 300 magnification on the metakoating interface. Some inclusions within the coating are tolerated, see table 3. 12.2.3

33、 Adhesion A test piece shall be heated at (510 f IO) OC for type A or (140 f IO) OC for type B and held for 1 h at this temperature before cooling. Examination at a magnification of x 10 shall show no blisters or exfoliation. Additionally, after heating, one of the following adhesion tests shall be

34、carried out : EN 2828 or EN 2829 or EN 2830. 12.3 Process - calibration of measuring instruments ; - bath analyses. The following tests shall be carried out : 12.3.1 Hydrogen embrittlement - no rupture before 200 h (as EN 2832) - apart from measuring errors, initial ductility is restored as per EN 2

35、831. Other methods may be used subject to agreement by the purchaser. 12.3.2 Analysis of the deposit The method of analysis shall be agreed upon between the manufacturer and purchaser. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMAN

36、ot for ResaleNo reproduction or networking permitted without license from IHS-,-,-STD-AECMA PREN 37b5-ENGL 1777 LO323L3 0032978 850 = Page 8 prEN 3765 : 1997 13 Quality assurance 13.1 Approval of the processor See EN 2000. 13.2 Process qualification Before beginning production the processor shall su

37、bmit a series of pre-production parts and test pieces, made up by the first batch coated under series conditions, on which the tests in 12 shall be performed. 13.3 Acceptance The frequency and nature of the inspection of parts and test pieces, at acceptance stage shall be subject to agreement betwee

38、n the manufacturer and purchaser. It shall be stated in the document required in 13.1. The tests involved at acceptance shall be : - the visual inspection (1 2.1 .I - the local thickness (12.1.2.11, it shall be measured on one sample per batch defined in accordance with IS0 2859-1 : it shall be carr

39、ied out on the whole batch ; - code letter of the batch size, table 1, inspection level for special applications S3 ; - simple sampling plan under tightened inspection ; - acceptable quality level (AQL) 1,5 ; - the measuring of the adhesion on test pieces, it shall be carried out at a rate of one te

40、st piece per batch. 13.4 Fault sanction No reworking shall be permitted. All defective deposites shall be removed and parts shall be retreated. 14 The locally applicable regulations and laws shall be observed. Health, safety and environmental aspects 15 Designation EXAMPLE : i Number of this standar

41、d Plating type code (see 5) Nominal thickness of the undercoat in pm (O0 if no undercoat is provided) Nominal thickness of the silver deposit in pm , B - Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or

42、 networking permitted without license from IHS-,-,-STD-AECMA PREN 37b5-ENGL 1777 m 1012311 0012777 777 m Page 9 prEN 3765 : 1997 Annex A (normative) Nickel strike A.l Preparation After cleaning, masking if necessary, degreasing and pickling by a method appropriate to the material, the parts receive,

43、 for example, the following treatment : A.2 Bath - nickel chloride (“212, 6H2O) - hydrochloric acid (d = 1,161 - water - current density - time : 200 g/l to 240 g/l : 80 ml/l to 110 ml/l : supplementary for 1 I : 4 A/dm2 to 8 A/dm2 : up to 3 min Copyright Association Europeene des Constructeurs de M

44、ateriel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-STD-AECMA PREN 37bS-ENGL 1777 1012311 0032780 YO7 Page 10 prEN 3765 : 1997 Annex B (normative) Nickel plate B. 1 Preparation At the end of the nickel strike

45、treatment, without intermediate rinsing, the parts are treated, for example, in one of the following baths : 8.2 “WATTS type“ nickel bath - nickel sulphate (NiS04, 7 H20) - nickel chloride (NiC12, 6 H20) - boric acid (H3B03) - temperature - current density - theoretical rate of deposition : 220 g/l

46、to 280 g/l : 40 g/l to 50 g/l : 25 g/l to 35 g/l : 50 Octo 55 OC : : 2 A/dmz to 5 A/dm2 12 pm/h for 1 A/dm2 B.3 Nickel “Sulpharnate“ bath - nickel suiphamate expressed as Ni metal : 75 g/l to 90 g/l - nickel chloride (NiC12, 6 H20) : 25 g/l - boric acid (H3BO3) : 30 g/l to 40 g/l - temperature : 50

47、Octo55 OC - current density : 2 A/dmz to 8 A/dm2 - theoretical rate of deposition : 12 pm/h for 1 A/dm2 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-,-,

48、-STD-AECMA PREN 37b5-ENGL 1777 LOL23LL OOL278L 345 = Page 11 prEN 3765 : 1997 Annex C (normative) Silver strike c. 1 Preparation After applying an undercoat in an acid bath or a pre-treatment in an acid bath, the parts shall be neutralized in an alkaline solution. This neutralisation is not necessar

49、y in the case of an undercoat deposited in an alkaline media or having undergone an alkaline pre-treatment. c.2 Silver strike bath As a typical example the following bath may be used : - silver cyanide (AgCN) : 2 g/l to 4 g/l - potassium cyanide (KCN) : 60 g/l to 80 g/l - potassium carbonate (K2CO3) : 10 g/l to 50 g/l - temperature : 15 OC to 30 OC - current density : 1 A/dm2 to 2 A/dm2 - time :