SAE AS 7466E-2014 Bolts and Screws Nickel Alloy UNS N07718 Tensile Strength 185 ksi Fatigue Rated Procurement Specification《UNS N07718拉力强度185 ksi额定疲劳度镍合金螺栓和螺丝采购规范》.pdf

《SAE AS 7466E-2014 Bolts and Screws Nickel Alloy UNS N07718 Tensile Strength 185 ksi Fatigue Rated Procurement Specification《UNS N07718拉力强度185 ksi额定疲劳度镍合金螺栓和螺丝采购规范》.pdf》由会员分享，可在线阅读，更多相关《SAE AS 7466E-2014 Bolts and Screws Nickel Alloy UNS N07718 Tensile Strength 185 ksi Fatigue Rated Procurement Specification《UNS N07718拉力强度185 ksi额定疲劳度镍合金螺栓和螺丝采购规范》.pdf（24页珍藏版）》请在麦多课文档分享上搜索。

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 2014 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:/www.sae.org/technical/standards/AS7466E AEROSPACE STANDARD AS7466 REV. E Issued 1992-05 Revised 2014-08 Supersedi

5、ng AS7466D Bolts and Screws, Nickel Alloy, UNS N07718 Tensile Strength 185 ksi, Fatigue Rated, Procurement Specification FSC 5306 RATIONALE This limited scope change corrects an error in the callout for 0.4375-20 threads in Table 2A. 1. SCOPE 1.1 Type This procurement specification covers aircraft-q

6、uality bolts and screws made of corrosion and heat resistant, age hardenable nickel base alloy of the type identified under the Unified Numbering System as UNS N07718. The following specification designations and their properties are covered: AS7466 185 ksi minimum ultimate tensile strength at room

7、temperature. 155 ksi minimum ultimate tensile strength at 800 F. 105 ksi tension to 10.5 ksi tension fatigue at room temperature. AS7466-1 185 ksi minimum ultimate tensile strength at room temperature. 111 ksi minimum ultimate shear strength at room temperature. 1.2 Application Primarily for aerospa

8、ce propulsion systems applications where a good combination of tensile strength and fatigue resistance are required; also, where a good combination of tensile strength, and shear strength are required. 1.3 Safety - Hazardous Materials While the materials, methods, applications, and processes describ

9、ed or referenced in 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 ne

10、cessary precautionary measures to ensure the health and safety of all personnel involved. SAE INTERNATIONAL AS7466E Page 2 of 24 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 a

11、pply. The applicable issue of other publications shall be 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 applicabl

12、e laws and regulations unless a specific exemption has been 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 724-776-4970 (outside USA), www.sae.org.2.1.1.1 Aerospace Material Specificat

13、ions AMS2750 Pyrometry AMS5662 Nickel Alloy, Corrosion and Heat-Resistant, Bars, Forgings, and Rings, 52.5Ni - 19Cr - 3.0Mo - 5.1Cb (Nb) - 0.90Ti - 0.50Al - 18Fe, Consumable Electrode or Vacuum Induction Melted, 1775 F (968 C), Solution Heat Treated, Precipitation-Hardenable 2.1.1.2 Aerospace Standa

14、rds AS1132 Bolts, Screws and Nuts - External Wrenching, UNJ Thread, Inch - Design Standard AS3062 Bolts, Screws, and Studs, Screw Thread Requirements AS3063 Bolts, Screws, and Studs, Geometric Control Requirements AS8879 Screw Threads - UNJ Profile, Inch, Controlled Radius Root with Increased Minor

15、Diameter 2.1.2 AIA/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 Strength

16、 NASM1312-11 Fastener Test Methods, Method 11, Tension Fatigue NASM1312-13 Fastener Test Methods, Method 13, Double Shear Test NASM1312-18 Fastener Test Methods, Method 18, Elevated Temperature Tensile Strength 2.1.3 ASME Publication Available from ASME, P.O. Box 2900, 22 Law Drive, Fairfield, NJ 07

17、007-2900, Tel: 800-843-2763 (U.S./Canada), 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 AS7466E Page 3 of 24 2.1.4 ASTM Publications Available from ASTM International, 100 Barr Harbor

18、 Drive, P.O. Box C700, West Conshohocken, 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 for Metallic Materials ASTM E112 Determining Average Grain

19、Size ASTM E140 Standard Hardness Conversion Tables for Metals Relationship Among Brinell Hardness, Vickers Hardness, Rockwell Hardness, Superficial Hardness, Knoop Hardness, and Scleroscope HardnessASTM E1417/E1417M Standard Practice for Liquid Penetrant Testing 2.2 Definitions BURR: A rough edge or

20、 ridge left on the metal due to cutting, grinding, piercing, or blanking operation. COLD ROLLING: Forming material below the recrystallation temperature. CRACK: Rupture in the material which may extend in any direction and which may be intercrystalline or transcrystalline in character.DEFECT: Any no

21、nconformance of the unit or the product with specified requirements. DEFECTIVE: A unit of the product which contains one or more defects. DISCONTINUITY: An interruption in the normal physical structure or configuration of a part; such as a lap, seam, inclusion, crack, machining tear, or stringer. HE

22、AT PATTERN: A discernible difference in etched appearance between the head and the shank caused by plastic forming of the head. INCLUSION: Nonmetallic particles originating from the material making process. They may exist as discrete particles or strings of particles extending longitudinally. LAP: S

23、urface imperfection caused by folding over metal fins or sharp corners and then rolling or forging them into the surface. The allowable lap depth shall not exceed the limit specified herein. The minimum condition that shall be rated as a lap is a fold having its length equal to or greater than three

24、 times its width with a depth of 0.0005 inch when viewed at 200X magnification. MACHINING TEAR: A pattern of short jagged individual cracks, generally at right angles to the direction of machining, frequently the result of improperly set cutting tools, or dull cutting tools. PRODUCTION INSPECTION LO

25、T: Shall be all finished parts of the same part number, made from a single heat of alloy, heat treated at the same time to the same specified condition, produced as one continuous run, and submitted for vendors inspection at the same time. SEAM: Longitudinal surface imperfection in the form of an un

26、welded, open fold in the material. SAE INTERNATIONAL AS7466E Page 4 of 24 STRINGER: A solid nonmetallic impurity in the metal bar, often the result of an inclusion that have been extended during the rolling process. TIGHT BURR: A burr closely compacted and binding in the periphery of a part without

27、loose ends and is within the dimensional limits of the part. 2.3 Unit Symbols C - degree Celsius F - degree Fahrenheit HRC - hardness Rockwell C scale lbf - pound-force % - percent (1% = 1/100) sp gr - specific gravity ksi - kips (1000 pounds) per square inch 3. TECHNICAL REQUIREMENTS 3.1 Material S

28、hall be AMS5662 heading stock. 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. Dimensions apply after plating but before coa

29、ting 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 thread UNJ profile and dimensions shall be in accorda

30、nce 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 specified in AS3062. 3.2.3.2 Chamfer The entering end o

31、f the thread shall be chamfered as specified on the part drawing. SAE INTERNATIONAL AS7466E Page 5 of 24 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 Fabrication 3.3.1

32、Blanks Heads shall be formed by hot 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. Flash or chip clearance

33、 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, shall be solution heat treated and precipitation heat treated as follows: 3.3.2.1 Heating Equipment Furnaces may

34、 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 to AMS2750. The heating medium or atmosphere shall cause no surface hardening by carburizing or nitriding. 3.3.2.2

35、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 quenching in oil, water, or an inert gas. 3.3.2.3 Precipitation Heat Treatment After solution hea

36、t treatment as in 3.3.2.2, 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 hour and cooling at a rate equivalent to a

37、ir cool. Instead of the 100 F per hour cooling rate to 1150 F 15 F, blanks 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 oxide and oxide penetration resulting fro

38、m prior heat treatment shall be removed from the full body diameter and bearing surface of the head of the solution and precipitation heat treated blanks prior to cold working the under head fillet radius and rolling the threads. The oxide removal process shall produce no intergranular attack or cor

39、rosion of the blanks. The metal removed from the bearing surface of the head and the full body diameter of the shank shall be as little as practicable to obtain a clean, smooth surface. SAE INTERNATIONAL AS7466E Page 6 of 24 3.3.4 Cold Rolling of Fillet Radius After removal of oxide as in 3.3.3, the

40、 head-to-shank fillet radius of headed parts having the radius complete throughout the circumference of the part shall be cold rolled. The cold rolling shall be sufficient to remove all visual evidence of grinding or tool marks. Distortion due to cold rolling shall conform to Figure 2, unless otherw

41、ise 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 inch below the contour at “B“ as shown in Figure 2; distorted areas shall not extend beyond “C” as shown in Figure 2. In configurations having an undercut connec

42、ted with the fillet radius, the cold rolling will be required only for 90 degrees of fillet arc, starting at the point of tangency of the fillet radius and the bearing surface of the head. For shouldered bolts, having an unthreaded shank diameter larger than the thread major diameter and having an u

43、ndercut connected with a fillet between the threaded shank and the shoulder of the unthreaded shank, the cold rolling will be required only for 90 degrees of fillet arc, starting at the point of tangency of the fillet radius and the shouldered surface of the unthreaded shank.3.3.5 Thread Rolling Thr

44、eads shall be formed on the finished blanks by a single rolling 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 gr 1.42) and 9 volu

45、mes 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. Immediately after removal f

46、rom the cleaning solution, parts shall be thoroughly rinsed in clean water at 70 to 200 F. 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, raised or depressed no more than 0.010 inch maximum, with round

47、ed 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 the plating specification. 3.6 Mechanical Properties Where AS7466 is specified, parts shall conform to the requirements of 3.6.

48、1, 3.6.2, 3.6.3, and 3.6.4. Where AS7466-1 is specified, parts shall conform to the requirements of 3.6.1, 3.6.3, and 3.6.5. Threaded members of gripping fixtures for tensile and fatigue tests shall be of sufficient size and strength to develop the full strength of the part without stripping thethre

49、ad.AS7466 finished parts shall be tested in accordance with the following applicable 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 Tensile Strength at 800 F: MIL-STD-1312-18 in accordance with NASM1312-18d. Fatigue Strength at Room Temperature: MIL-STD-1312-11 in a