SAE AS 4877G-2017 Bolts and Screws Nickel Alloy UNS N07718 Classification 185 ksi 1200 Procurement Specification.pdf

1、_ SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising there

2、from, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be revised, reaffirmed, stabilized, or cancelled. SAE invites your written comments and suggestions. Copyright 2017 SAE International All rights reserved. No part of this p

3、ublication may be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of SAE. TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada) Tel: +1 724-776-497

4、0 (outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org SAE values your input. To provide feedback on this Technical Report, please visit http:/standards.sae.org/AS4877G AEROSPACE STANDARD AS4877 REV. G Issued 1995-02 Reaffirmed 2004-02 Revised 2017-10 Supe

5、rseding AS4877F Bolts and Screws, Nickel Alloy UNS N07718, Classification: 185 ksi/1200 F Procurement Specification FSC 5306 RATIONALE Classification for fatigue strength added, AS6416 definition document added, clarification on solution treatment, flow lines, and grain size paragraphs added, deleti

6、on of cold from rolled thread requirement, Test loads rounded up or down. Table 1: Thread size for 0.164-32 corrected was 0.165-36, associated load corrected to 2871 from 3871. Figures 2A and 2B deleted. Figures 2 to 8 redrawn and renumbered. Paragraphs 3.3.5, 3.7.1.1.1, 3.7.1.1.2, 3.7.2.1, 3.7.2.2

7、reworded, 3.7.1.1.3 reworded and renumbered. 1. SCOPE 1.1 Type This procurement specification covers bolts and screws made from a corrosion and heat resistant, age hardenable nickel base alloy of the type identified under the Unified Numbering System as UNS N07718. 1.1.1 Classification AS4877 (where

8、 “-1“ is not included) a. Tensile strength at room temperature 185 ksi minimum b. Maximum test temperature of parts 1200 F c. Tensile strength at 1200 F 145 ksi minimum d. Stress Rupture: 100 ksi stress rupture strength at 1200 F e. Fatigue strength at room temperature 105 ksi minimum AS4877-1 a. Te

9、nsile strength at room temperature 185 ksi minimum b. Ultimate Double Shear Strength at room temperature 111 ksi minimum SAE INTERNATIONAL AS4877G Page 2 of 21 1.2 Application Primarily for use in aerospace propulsion systems as follows: a. For use up to approximately 1200 F where elevated temperatu

10、re tensile strength, stress-rupture strength, and resistance to relaxation are required. b. For use up to approximately 800 F where fatigue resistance and tensile strength are required. 1.3 Safety-Hazardous Materials While the materials, methods, applications, and processes described or referenced i

11、n this specification may involve the use of hazardous materials, this specification does not address the hazards which may be involved in such use. It is the sole responsibility of the user to ensure familiarity with the safe and proper use of any hazardous materials and to take necessary precaution

12、ary measures to ensure the health and safety of all personnel involved. 2. REFERENCES 2.1 Applicable Documents The following publications form a part of this document to the extent specified herein. The latest issue of SAE publications shall apply. The applicable issue of other publications shall be

13、 the issue in effect on the date of the purchase order. In the event of conflict between the text of this document and references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has be

14、en obtained. 2.1.1 SAE Publications Available from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Canada) or +1 724-776-4970 (outside USA), www.sae.org. AMS2750 Pyrometry AMS5662 Nickel Alloy, Corrosion and Heat-Resistant, Bars, Forgings, and

15、Rings 52.5Ni - 19Cr - 3.0Mo - 5.1Cb (Nb) - 0.90Ti - 0.50AI - 18Fe Consumable Electrode or Vacuum Induction Melted 1775 F (968 C) Solution Heat Treated, Precipitation-Hardenable AS1132 Bolts, Screws and Nuts - External Wrenching UNJ Thread, Inch - Design Standard AS3062 Bolts, Screws and Studs, Screw

16、 Thread Requirements AS3063 Bolts, Screws, and Studs, Geometric Control Requirements AS6416 Bolts, Screws, Studs, and Nuts, Definitions for Design, Testing and Procurement 2.1.2 ASME Publications Available from ASME, P.O. Box 2900, 22 Law Drive, Fairfield, NJ 07007-2900, Tel: 800-843-2763 (U.S./Cana

17、da), 001-800-843-2763 (Mexico), 973-882-1170 (outside North America), www.asme.org. ASME B46.1 Surface Texture (Surface Roughness, Waviness, and Lay) SAE INTERNATIONAL AS4877G Page 3 of 21 2.1.3 ASTM Publications Available from ASTM International, 100 Barr Harbor Drive, P.O. Box C700, West Conshohoc

18、ken, PA 19428-2959, Tel: 610-832-9585, www.astm.org. ASTM D3951 Commercial Packaging ASTM E8/E8M Standard Test Methods for Tension Testing of Metallic Materials ASTM E21 Elevated Temperature Tension Tests of Metallic Materials ASTM E112 Determining Average Grain Size ASTM E139 Conducting Creep, Cree

19、p-Rupture, and Stress-Rupture Tests of Metallic Materials ASTM E140 Standard Hardness Conversion Tables for Metals Relationship Among Brinell Hardness, Vickers Hardness, Rockwell Hardness, Superficial Hardness, Knoop Hardness, and Scleroscope Hardness ASTM E1417/E1417M Standard Practice for Liquid P

20、enetrant Examination 2.1.4 NAS Publications Available from Aerospace Industries Association, 1000 Wilson Boulevard, Suite 1700, Arlington, VA 22209-3928, Tel: 703-358-1000, www.aia-aerospace.org NASM1312-6 Fastener Test Methods, Method 6, Hardness NASM1312-8 Fastener Test Methods, Method 8, Tensile

21、Strength NASM1312-10 Fastener Test Methods, Method 10, Stress Rupture NASM1312-11 Fastener Test Methods, Method 11, Tension Fatigue NASM1312-12 Fastener Test Methods, Method 12, Thickness of Metallic Coatings NASM1312-13 Fastener Test Methods, Method 13, Double Shear Test NASM1312-18 Fastener Test M

22、ethods, Method 18, Elevated Temperature Tensile Strength 2.2 Definitions Refer to AS6416. 2.3 Unit Symbols C degree Celsius F degree Fahrenheit cm3 cubic centimeter g gram, mass % percent (1% = 1/100) SAE INTERNATIONAL AS4877G Page 4 of 21 lbf pound-force ksi kip (1000 pounds) per square inch sp gr

23、specific gravity 3. TECHNICAL REQUIREMENTS 3.1 Material Shall be AMS5662. 3.2 Design Finished (completely manufactured) parts shall conform to the following requirements: 3.2.1 Dimensions The dimensions of finished parts, after all processing, including plating, shall conform to the part drawing. Di

24、mensions shall apply after plating, but before coating with dry film lubricants. 3.2.2 Surface Texture Surface texture of finished parts, prior to plating or coating, shall conform to the requirements as specified on the part drawing, determined in accordance with ASME B46.1. 3.2.3 Threads Screw thr

25、ead UNJ profile and dimensions shall be in accordance with AS8879, unless otherwise specified on the part drawing. 3.2.3.1 Incomplete Lead and Runout Threads Incomplete threads are permissible at the entering end and the juncture of the unthreaded portion of the shank or adjacent to the head as spec

26、ified in AS3062. 3.2.3.2 Chamfer The entering end of the thread shall be chamfered as specified on the part drawing. 3.2.4 Geometric Tolerances Part features shall be within the geometric tolerances specified on the part drawing and, where applicable, controlled in accordance with AS3063. 3.3 Fabric

27、ation 3.3.1 Blanks Heads shall be formed by hot forging or cold forging; temperature for hot forging blanks shall be within the range of 1650 to 2000 F. Machined heads are not permitted, except lightening holes may be produced by any suitable method. Wrenching recesses may be forged or machined. Fla

28、sh or chip clearance in machined recesses shall not cause recess dimensions to exceed the specified limits. 3.3.2 Heat Treatment Headed blanks, before finishing the shank and the bearing surface of the head, cold rolling the head-to-shank fillet radius, and rolling the threads shall be solution and

29、precipitation heat treated as follows: SAE INTERNATIONAL AS4877G Page 5 of 21 3.3.2.1 Heating Equipment Furnaces may be any type ensuring uniform temperature throughout the parts being heated and shall be equipped with, and operated by, automatic temperature controllers and data recorders conforming

30、 to AMS2750. The heating medium or atmosphere shall cause no surface hardening by carburizing or nitriding. The heat treatment atmosphere or medium shall not cause any surface contamination except as permitted by 3.3.3. On unplated bolts, discoloration from heat treatment is acceptable, but no scale

31、 is permissible. 3.3.2.2 Solution Heat Treatment Headed blanks shall be solution heat treated by heating to a temperature within the range 1725 to 1850 F, holding at the selected temperature within 25 F for 1 hour 0.1 hour and cooled at a rate equivalent to air cool or faster. 3.3.2.3 Precipitation

32、Heat Treatment After solution heat treatment, as in 3.3.2.2, headed blanks shall be precipitation heat treated by heating to 1325 F 15 F in a controlled atmosphere, holding at heat for 8 hours 0.25 hour, furnace cooling at 100 F 15 F per hour to 1150 F 15 F, holding at 1150 F 15 F for 8 hours 0.25 h

33、our and cooling at a rate equivalent to air cool. Instead of the 100 F per hour cooling rate to 1150 F 15 F, parts may be furnace cooled at any rate provided the time at 1150 F 15 F is adjusted to give a total precipitation heat treatment time of approximately 18 hours. 3.3.3 Oxide Removal Surface o

34、xide from prior heat treatments shall be removed prior to rolling the fillet radius and threads. 3.3.4 Cold Rolling of Fillet Radius After removal of oxide as in 3.3.3, the head-to-shank fillet radius of parts having the radius complete throughout the circumference of the part shall be cold rolled.

35、Cold rolling shall be sufficient to remove all visual evidence of grinding or tool marks. Distortion due to cold rolling shall conform to Figure 1, unless otherwise specified on the part drawing. It shall not raise metal more than 0.002 inch above the contour at “A” or depress metal more than 0.002

36、inch below the contour at “B” as shown in Figure 1; distorted areas shall not extend beyond “C” as shown in Figure 1. In configurations having an undercut connected with the fillet radius, the cold rolling will be required only for 90 of fillet arc, starting at the point of tangency of the fillet ra

37、dius and the bearing surface of the head. For shouldered bolts having an unthreaded shank diameter larger than the thread major diameter and having an undercut connected with a fillet between the threaded shank and the shoulder of the unthreaded shank, the cold rolling will be required only for 90 o

38、f fillet arc, starting at the point of tangency of the fillet radius and the shouldered surface of the unthreaded shank. The shank diameter on full shank close tolerance bolts shall not exceed the nominal thread diameter after cold rolling the head-to-shank fillet radius. 3.3.5 Thread Rolling Thread

39、s shall be formed on the finished blanks by a single cold or warm rolling (600 F) process after removal of oxide as in 3.3.3. 3.3.6 Cleaning Parts, after finishing, shall be degreased and immersed in one of the following solutions for the time and temperature shown: a. One volume of nitric acid (sp

40、gr 1.42) and 9 volumes of water for not less than 20 minutes at room temperature. b. One volume of nitric acid (sp gr 1.42) and 4 volumes of water for 30 to 40 minutes at room temperature. c. One volume of nitric acid (sp gr 1.42) and 4 volumes of water for 10 to 15 minutes at 140 to 160 F. Immediat

41、ely after removal from the cleaning solution, parts shall be thoroughly rinsed in clean water at 70 to 200 F. SAE INTERNATIONAL AS4877G Page 6 of 21 3.4 Product Marking Each part shall be identification marked as specified by the part drawing. The markings may be formed by forging or stamping, raise

42、d or depressed 0.010 inch maximum, with rounded root form on depressed characters. 3.5 Plating Where required, surfaces shall be plated as specified by the part drawing; plating thickness determined in accordance with MIL-STD-1312-12 in accordance with NASM1312-12. 3.6 Mechanical Properties Where AS

43、4877 is specified, parts shall conform to the requirements of Ultimate tensile strength at room temp, Ultimate tensile strength at 1200F, Hardness, Fatigue strength and Stress rupture strength at 1200 F. Where AS4877-1 is specified, parts shall conform to the requirements of Ultimate tensile strengt

44、h at room temp, Hardness and Ultimate double shear strength. Threaded members of gripping fixtures for tensile, fatigue, and stress-rupture tests shall be of sufficient size and strength to develop the full strength of the part without stripping the thread. The loaded portion of the shank shall have

45、 two to three full threads from the thread runout exposed between the loading fixtures during tensile, fatigue, and stress-rupture tests. AS4877 finished parts shall be tested in accordance with the following test methods: a. Hardness: MIL-STD-1312-6 in accordance with NASM1312-6 b. Ultimate Tensile

46、 Strength at Room Temperature: MIL-STD-1312-8 in accordance with NASM1312-8 c. Ultimate Tensile Strength at 1200 F: MIL-STD-1312-18 in accordance with NASM1312-18 d. Stress-Rupture Strength at 1200 F: MIL-STD-1312-10 in accordance with NASM1312-10 e. Fatigue Strength: MIL-STD-1312-11 in accordance w

47、ith NASM1312-11 AS4877-1 finished parts shall be tested in accordance with the following test methods: a. Hardness: MIL-STD-1312-6 in accordance with NASM1312-6 b. Ultimate Tensile Strength at Room Temperature: MIL-STD-1312-8 in accordance with NASM1312-8 c. Ultimate Double Shear Strength at Room Te

48、mperature: MIL-STD-1312-13 in accordance with NASM1312-13 3.6.1 Ultimate Tensile Strength at Room Temperature 3.6.1.1 Finished Parts Parts shall have an ultimate tensile load not lower than that specified in Table 1 and shall be tested to failure in order to observe fracture location, first measurin

49、g and recording the maximum tensile load achieved. If the size or shape of the part is such that failure would occur outside the threaded section, but the part can be tested satisfactorily, such as parts having a shank diameter equal to or less than the thread root diameter or having an undercut, parts shall have an ultimate tensile strength not lower than 185 ksi; for such parts, the