1、NASM 5673-1998 Pin, Straight, Headed_NASM5673 ADOPTION NOTICE NASM5673, Pin, Straight, Headed, was adopted on 01-OCT-98 for use by the Department of Defense (DoD). Proposed changes by DoD activities must be submitted to the DoD Adopting Activity: Commander, Defense Industrial Supply Center, 700 Robb
2、ins Avenue, Philadelphia, PA 19111-5096. DoD activities may obtain copies of this standard from the Standardization Document Order Desk, 700 Robbins Avenue, Building 4D, Philadelphia, PA 19111-5094. The private sector and other Government agencies may purchase copies from the Aerospace Industries As
3、sociation, 1250 Eye Street NW, Washington, DC 20005. Custodians : Navy - AS Air Force - 99 Army - AR DLA - IS Adopting Activities: (Project 5315-0622) DLA - IS FSC 5315 DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited. Copyright Aerospace Industries Association of Ame
4、rica Inc. Provided by IHS under license with AIA/NASNot for ResaleNo reproduction or networking permitted without license from IHS-,-/:#:#$#:$*:$#:#STD.AIA/NAS NASM5673-ENGL 1998 0318743 0505961 3T5 NATIONAL AEROSPACE STANDARD 0 COPYRIGHT 1998 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, WC, ALL RIG
5、HTS RESERVED NASM5673 SPECIFICATION NASM SPECIFICATION PIN, STRAIGHT, HEADED This specification is approved for use by all Departments and Agencies of the Department of Defense. 1. SCOPE 1.1 Scope. This specification establishes the requirements for the manufacture and inspection of one type of stra
6、ight headed pin. 1.2 Classification. Pins shall be fabricated from any one of the following compositions (see 3.1): a. 4037,4130 or 8630, steel alloy. b. PHI 3-8Mo. corrosion resistant steel (cres). c. TibAMv. titanium alloy. d. 8740 steel alloy. 2. APPLICABLE DOCUMENTS 2.1 Government documents. 2.1
7、.1 Specifications, standards and handbooks: Unless otherwise specified, the following specifications. standards and handbooks of the issue listed in that issue of the Department of Defense Index of Specifications and Standards (DoDISS) specified in the solicitation form a part of this specification
8、to the extent specified herein. THE INITIAL RELEASE OF THIS DOCUMENT SUPERSEDES MIL-P-5673, REVISION D. LIST OF CURRENT SHEETS NEW NEW NEW NEW 3 NEW 7 NEW 4 NEW SHEET 1 OF 6 FSC 531 5 APPROVAL DATE: OCTOBER 1998 REVISION: USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS EN
9、TIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUlTABlLlM OF ITEMS FOR ANY PARTICULAR APPLICATION, OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO OF PATENT OR TRAD
10、EMARK RIGHTS Copyright Aerospace Industries Association of America Inc. Provided by IHS under license with AIA/NASNot for ResaleNo reproduction or networking permitted without license from IHS-,-/:#:#$#:$*:$#:# STD.AIA/NAS NASM5b73-ENGL 1998 0318743 0505962 231 NATIONAL AEROSPACE STANDARD 8 COPYRIGH
11、T 1998 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED NASM5673 SPECIFICATIONS FEDERAL QQ-C-320 QQ-P416 PPP-H-1581 MILITARY MIL-Sb049 MIL-Sb050 MIL-S-6758 MIL-H-6875 MIL-T-9047 MIL-L46010 MIL-C-83488 STANDARDS MILITARY MIL-STD-105 MIL-STD-1312 MS20392 Chromium Plating (Electrod
12、eposited). Plating, Cadmium (Electrodeposited). Hardware (Fasteners and Related Items). Packaging of. Steel, Chrome-Nickel-Molybdenum (8740) Bars and Reforging Stock (Aircraft Quality). Steel, Chrome-Nickel-Molybdenum (8630) Bars and Reforging Stock (Aircraft Quality). Steel, Chrome-Molybdenum (4130
13、) Bars and Reforging Stock Aircraft Quality. Heat Treatment of Steels (Aircraft Practices), Process for. Titanium and Titanium Alloy Bars (Rolled or Forged) and Reforging Stock, Aircraft Quality. Lubricant, Solid Film, Heat Cured, Corrosion Inhibiting. Coating, Aluminum, Ion Vapor Deposited. Samplin
14、g Procedures and Tables for Inspection by Attributes. Fasteners, Test Methods. Pin, Straight Headed. (Copies of specifications, standards, handbooks, drawings, and publications required by manufacturers in connection with specific acquisition functions should be obtained from the contracting activit
15、y or as directed by the contracting officer.) 2.2 Other publications. The following document) form a part of this specification to the extent specified herein. The issues of the documents which are indicated as DoD adopted shall be the issue listed in the current DoDlSS and the supplement thereto, i
16、f applicable. Society of Automotive Engineers, Inc. AMS 2300 Premium Aircraft Quality Steel Cleanliness, Magnetic Particle Inspection Procedure. AMS 2301 Aircraft Quality Steel Cleanliness, Magnetic Particle Inspection Procedure. AMS 2631 Ultrasonic Inspection of Titanium Alloys. AMS 5629 Steel Bars
17、, Forgings, Rings, and Extrusions, Corrosion Resistant. AMS 2632 Ultrasonic Inspection of Thin Materials 0.5 Inch (13 mm) and Thinner. AMS 6300 Steel Bars and Forgings, 0.25 Mo (0.35-0.4OC) (SAE 4037). (Application for copies of AMS publications should be addressed to the Society of Automotive Engin
18、eers, Inc., 400 Commonwealth Drive, Warrendale, PA 15096). 2 APPROVAL DATE: OCTOBER 1998 USE OF OR RELANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKE
19、S NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF ITEMS FOR ANY PARTICULAR APPLICATION. OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO OF PATENT OR TRADEMARK RIGHTS REVISION; Copyright Aerospace Industries Association of America Inc. Provided by IHS under license with AIA/NASNot for R
20、esaleNo reproduction or networking permitted without license from IHS-,-/:#:#$#:$*:$#:#STD-AIAINAS NASM5673-ENGL 1998 m 0338743 0505963 L78 m NATIONAL AEROSPACE STANDARD 0 COPYFUGHT 1998 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED NASM5673 American Society for Testing and M
21、aterials ASTM A380 Cleaning and Descaling Stainless Steel Parts, Equipment and Systems. ASTM E1444 Magnetic Particle Examination, Standard Practice for. (Application for copies of ASTM publications should be addressed to the American Society for Testing an1 1916 Race Street, Philadelphia, PA 19103.)
22、 d Materials. (Industry association specifications and standards are generally available for reference from libraries. They are also distributed among technical groups and using Federal agencies.) 2.3 Order of precedence. In the event of a conflict between the text of this specification and the refe
23、rences cited herein, the text of this specification shall take precedence. 3. REQUIREMENTS 3.1 Material. Headed straight pins shall be fabricated from any of the following materials as specified (see 6.2): a. Steel alloy - UNS G40370 (AISI 4037) per AMS 6300 or UNS G41300 (AISI 41 30) per MIL-S-6758
24、 or UNS G86300 b. Steel alloy - UNS G87400 (AISI 8740) per MIL-S-6049. c. Cres (PH13-Mo) - UNS S13800 (AISI S13800) per AMS 5629. d. Titanium alloy (Ti-6Al4v) - UNS R56400 per MIL-T-9047. (AISI 8630) per MIL-S-6050. 3.2 Design and construction. Headed straight pins shall be of the material, size and
25、 dimensions specified on MS20392. 3.2.1 Shear strength. The shear strength of the pins shall be not less than that specified in table I, table II, table 111, and table IV for 4037, 4130, and 8630 steel alloy, cres, titanium alloy and 8740 respectively. TABLE 1. Shear strength of steel alloy, 4037, 4
26、130, and 8630, headed straight pins. I/ Nominal (pounds) strength in in double shear Size Minimum Minimum strength (pounds) single shear 125 920 1 840 .I56 4.140 I 2.070 .I88 1,430 2,860 250 11,500 ,312 3.680 7,360 11 -270 22.540 -438 8,290 16,580 .375 5.750 . L ,500 14,720 .562 46.020 ,625 18,640 3
27、7,280 23.010 . 29,440 ,- - . .- - ,750 33,140 ,875 117,820 1 .o0 45,100 90,200 58,910 66,280 . - - - I/ Unit shear stress is 75,000 pounds per square inch (psi) in single shear, based on 125,000 psi minimum tensile strength. 3 APPROVAL DATE: OCTOBER 1998 USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY
28、NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF ITEMS FOR ANY PARTICULAR APPLICATION, OR (2) THE EXISTENCE OF OR APPLI
29、CABILITY THERETO OF PATENT OR TRADEMARK RIGHTS REVISION; Copyright Aerospace Industries Association of America Inc. Provided by IHS under license with AIA/NASNot for ResaleNo reproduction or networking permitted without license from IHS-,-/:#:#$#:$*:$#:# STD.AIA/NAS NASM5673-ENGL 3998 0338743 050596
30、4 004 NATIONAL AEROSPACE STANDARD 0 COPYRIGHT 1998 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED NASM5673 TABLE II. Shear strength of cres, PH13-8Mo, headed straight pins. I/ - 1/ Unit shear stress is 125,000 (psi) in single shear, based on 220,000 psi minimum tensile strengt
31、h. TABLE 111. Shear strength of titanium alloy, Ti-6A14V, headed straight pins. J/ Nominal in single shear in double shear Size Minimum strength Minimum strength (pounds) (pounds) -125 1.170 2340 .156 4.660 9.320 .250 2,620 5.240 .188 1,820 3.640 ,312 18.650 37.300 .500 14,280 28.560 .438 10.500 21,
32、000 .375 7,290 14.580 ,562 23,610 .625 74,61 O 149,220 1 .o00 57.120 1 14,240 ,875 4 1,970 83,940 .750 29.150 58,300 . 47,220 - .- _. - il Unit shear stress is 95,000 psi in single shear, based on 160.000 psi minimum tensile strength. 4 APPROVAL DATE: OCTOBER 1998 USE OF OR RELIANCE UPON THIS DOCUME
33、NT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF ITEMS FOR ANY PARTICULAR APPLICATION, OR (2) THE EXISTENCE O
34、F OR APPLICABILITY THERETO OF PATENT OR TRADEMARK RIGHTS REVISION; Copyright Aerospace Industries Association of America Inc. Provided by IHS under license with AIA/NASNot for ResaleNo reproduction or networking permitted without license from IHS-,-/:#:#$#:$*:$#:#STD.AIA/NAS NASM5673-ENGL L998 03187
35、43 05057b5 T40 NATIONAL AEROSPACE STANDARD 0 COPYRIGHT 1998 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, WC. ALL RIGHTS RESERVED NASM5673 TABLE IV. Shear strength of steel alloy, 8740, headed, straight pins. J/ Nominal in single shear in double shear Size Minimum strength Minimum strength - 1/ Unit
36、shear stress is 108,000 psi in single shear, based on 180.000 psi minimum tensile strength. 3.3 Heat treatment. 4037. 4130, and 8630 steel alloy pins shall be heat treated to 125.000 to 150.000 psi tensile strength in accordance with MIL-H-6875 and shall have a Rockwell hardness of C265 to C32. Cres
37、 pins shall be heat treated to 220,000 to 240,000 psi tensile strength in accordance with MIL-H-6875. Titanium alloy pins shall be heat treated to 160.000 to 180,000 psi tensile strength in accordance with MIL-H-81200. 8740 steel alloy pins shall be heat treated 180,000 to 200,000 psi tensile streng
38、th in accordance with MIL-H6875 and shall have a Rockwell hardness of 39 HRC to 43 HRC. 3.4 Finish. Steel alloy pins shall be cadmium plated in accordance with QQ-P-416, Type II, Class 2. Cres pins shall either chrome plated in accordance with QQ-C-320, class 2, or cleaned, descaled and passivated i
39、n accordance with ASTM A380. Titanium alloy pins shall either have no finish or shall be aluminum coated in accordance with MIL-C-83488, Class 3, and lubricated with solid film lubricant in accordance with MIL-L-46010. 3.5 Workmanship. Pins shall be free from burrs, fins, cracks, tool marks, rust, s
40、cale and other defects which might adversely affect their serviceability. 3.6 Recycled, virgin and reclaimed materials. There is no exclusion to the use of recycled or reclaimed materials and no mandate for the use of virgin materials as long as it meets the requirements of this specification. 4. QU
41、ALITY ASSURANCE 4.1 Responsibility for inspection. Unless otherwise specified in the contract or purchase order, the contractor is responsible for the performance of all inspection requirements as specified herein. Except as otherwise specified in the contract or purchase order, the contractor may u
42、se his own or any other facilities suitable for the performance of the inspection requirements specified herein, unless disapproved by the Government. The Government reserves the right to perform any of the inspection set forth in the specification where such inspections are deemed necessary to assu
43、re supplies and services conform to prescribed requirements. 4.2 Classification of inspection. The inspection requirement specified herein is classified as quality conformance inspection. 4.3 Quality conformance inspection. 4.3.1 Inspection lot. An inspection lot shall be as defined in MIL-STD-105 a
44、nd shall consist of all pins of the same MS part number which, if heat treated, shall have been heat treated in the same batch and shall be submitted for inspection at the same time in connection with the same contract or order. 5 APPROVAL DATE: OCTOBER 1998 REVISION; USE OF OR RELIANCE UPON THIS DO
45、CUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO OF OR APPLICABILITY THERETO OF PATENT OR TRADEMARK RIGHTS REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF ITEMS FOR ANY PARTICULAR APPLICATION, OR (2) THE EXISTENCE Copyright Aerospace Industries Association of America Inc. Provided by IHS under license with AIA/NASNot for ResaleNo reproduction or networking permitted without license from IHS-,-/:#:#$#:$*:
