1、NASM 5674-2000 Rivets, Structural, Aluminum Alloy, Titanium Columbium Alloy - General Specification For_ADOPTION NOTICE NASM5674 NASM5674 , RIVETS , STRUCTURAL, ALU ALLOY , TITANIUM COLUMBIUM ALLOY , GENERAL SPECIFICATION FOR If, was adopted on 29 JUNE 2000 for use by the Department of Defense (DoD)
2、. Proposed changes by DoD Activities must be submitted to the DoD Adopting Activity: Defense Supply Center Philadelphia, ATTN: DSCP-ILEA, 700 Robbins Avenue, Philadelphia, PA 19111-5096. DoD Activities may obtain copies of this standard from the Standardization Document Order Desk, 700 Robbins Avenu
3、e, Building 4D, Philadelphia, PA 19111-5094. The private sector and other Government agencies may purchase copies from the AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. , 1250 EYE STREET, N. W. , WASHINGTON, DC 20005-3924. Custodians : Army - AV Air Force - 99 DLA-IS Adopting activity : DLA-IS (
4、Project 5320-1027-002) I f AMSC N/A DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimit _. FSC 5320 Copyright Aerospace Industries Association of America Inc. Provided by IHS under license with AIA/NASNot for ResaleNo reproduction or networking permitted without license fr
5、om IHS-,-/:#:#$#:$:*:$#:# - - - STD.AIA/NAS NASM5b7Y-ENGL 2000 0338743 0508932 488 NATIONAL AEROSPACE STANDARD 0 COPYRIGHT 2000 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, MC. ALL RIGHTS RESERVED NASM5674 SPECIFICATION RIVETS, STRUCTURAL, ALUMINUM ALLOY, TITANIUM COLUMBIUM ALLOY GENERAL SPECIFICATI
6、ON FOR 1. SCOPE 1.1 Scope. This specification covers aluminum alloy and titanium columbium alloy rivets. 1.2 Classification. 1.2.1 Composition and condition. The rivets shall be furnished in the following compositions and conditions. Composition 1 1 O0 (UNSA9 1 100) 20 17 (UNSA920 17) 2024 (UNSA9202
7、4) 2117 (UNSA92117) 22 1 9 (UNSA922 19) 22 19 (UNSA922 19) 5056 (UNSA95056) 7050 (UNSA97050) 45cb (UNSR58450) Temper -F -T4 -T4 -T4 -T8 1 -T62 -H32 -T73 Condition As fabricated; Solution heat treated and naturally aged Solution heat treated and naturally aged Solution heat treated and naturally aged
8、; Solution heat treated and naturally aged; and artificially aged (inactive for new design); Solution heat treated and artificially aged; Strain hardened and then stabilized; Solution heat treated and artificially aged; Per AMs 4982; (inactive for new design); (inactive for new design); 2. APPLICABL
9、E DOCUMENTS 2.1 Government documents. 2.1.1 Specification, standards and handbooks. The following specifications, standards and handbooks form a part of this specification to the extent specified herein. Unless otherwise specified, the issues of these documents shall be those listed in the issue of
10、the Department of Defense Index of Specifications and Standards (DODISS) and supplement thereto, cited in the solicitation (see 6.2). THE INITIAL RELEASE OF THIS DOCUMENT SUPERSEDES MIL-R-5674, REVISION F, AMENDMENT 2. LIST OF CURRENT SHEETS NEW NEW NEW NEW NEW NEW Sheet 1 of 9 FSC 5320 APPROVAL DAT
11、E MARCH 2000 REVISION USE OF OR RELIANCE 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 MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF ITE
12、MS FOR ANY PARTICULAR APPLICATION, OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO OF PATENT OR TRADEMARK 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-,-/:#:
13、#$#:$:*:$#:# - STD.AIA/NAS NASMSb74-ENGL 2000 0338743 0508933 334 NATIONAL AEROSPACE STANDARD 0 COPYRIGHT 2000 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED NASM5674 SPECIFICATIONS FEDERAL QQ-A430 MILITARY MIL-C-554 1 MIL-H-6088 MIL-A-8625 STANDARDS MILITARY MIL-STD-105 MIL-S
14、TD- 129 MIL-STD- 13 12 - Aluminum Alloy Rod and Wire; for Rivets and Cold Heading. Chemical Conversion Coatings on Aluminum Alloys. Heat Treatment of Aluminum Alloys. Anodic Coatings, for Aluminum and Aluminum Alloys. Sampling Procedures and Tables for Inspection by Attributes. Marking for Shipment
15、and Storage. Fastener Test Methods. (Unless otherwise indicated, copies of federal and military specifications, standards and handbooks are available from the Defense Printing Service Detachment Office, 700 Robbins Avenue, Bldg. 4-D, Philadelphia, PA 191 11-5096.) 2.2 Nongovernment publications. The
16、 following documents form a part of this document to the extent specified herein. Unless otherwise specified, the issues of the documents which are DoD adopted are those listed in the issue of the DODISS cited in the solicitation. Unless otherwise specified the issues of the documents are listed in
17、the DODISS are issues of the documents cited in the solicitation (see 6.2). SOCIETY OF AUTOMOTIVE ENGlNEERS AMs 4982 - Titanium Alloy Wire - 45Cb (Application for copies should be addressed to the Society of Automotive Engineers, Inc., 400 Commonwealth Drive, Warrendale, PA 15096.) AMERICAN SOCIETY
18、FOR TESTING AND MATERIALS (ASTM) B 565 - Shear Testing of Aluminum and Aluminum Alloy Rivets and Cold-Heading D 3951 - Standard Practice for Commercial Packaging E8 Tension Testing of Metallic Materials Wire Rods (Application for copies should be addressed to the American Society for Testing and Mat
19、erials, 19 16 Race Street, Philadelphia, PA 19 103- 1 187.) 2 APPROVAL DATE MARCH 2000 REVISION USE OF OR RELIANCE 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.
20、AIA MAKES 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 Copyright Aerospace Industries Association of America Inc. Provided by IHS under license with AIA/NASNot for Res
21、aleNo reproduction or networking permitted without license from IHS-,-/:#:#$#:$:*:$#:#- - STD*AIA/NAS NASN5674-ENGL 2000 E 0336743 0506934 250 W NATIONAL AEROSPACE STANDARD 0 COPYRIGHT 2000 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, MC. ALL RIGHTS RESERVED NASM5674 (Nongovernment standards and oth
22、er publications are normally available from the organizations that prepare or distribute the documents. These documents also may be available in or through libraries or other informational services.) 2.3 Order of precedence. In the event of a conflict between the text of this document and the refere
23、nces cited herein (except for related associated detail specifications, specification sheets, or MS standards), the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 3. REQUIREMENTS 3.1
24、 Military standards. The individual item requirements shall be as specified herein and in accordance with the applicable standard. In the event of any conflict between the requirements of this specification and the standard, the latter shall govern. 3.2 Material. The rivets shall be made from materi
25、al conforming to QQ-A430 or AMS 4982, as applicable. 3.2.1 Grain size. Five (5) or finer except for AMS 4982 and aluminum alloys 1100 and 5056. 3.3 Design. Rivet design shall be as specified on the applicable standard. 3.4 Shear strength. The undriven shear strength of rivets greater than 0.0937 inc
26、h in diameter shall be as specified in Table I when tested as specified in 4.5.2.2. Shear strength tests on 2017,2024,2117,2219 and 7050 rivets shall be made with the rivets in the heat-treated condition (see 4.4.1 and 4.4.3). TABLE I. Undriven shear strength. Rivet I Shear strength (lblin2) ComDosi
27、tion I Termer I Minimum I Maximum A I I 1100 I F NIA I NIA 1 5056 NIA 26.000 T4 21 17 NIA 24,000 H32 r I I 2219 I T81 I 32,000 I NIA 1 2219 T4 I 35.000 I 42.000 11 2017 T62 1 32,000 I NIA I I I - I 2024 I T4 I 37,000 I NIA 7050 59.000 50.000 450 46,000 4 1,000 T73 - 11 See applicable military standa
28、rds for additional requirement. APPROVAL DATE MARCH 2000 REVISION USE OF OR RELIANCE 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 MAKES NO REPRESENTATION OR
29、 CLAIM RESPECTING (1) THE SUITABILITY OF ITEMS FOR ANY PARTICULAR APPLICATION, OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO OF PATENT OR TRADEMARK RIGHTS Copyright Aerospace Industries Association of America Inc. Provided by IHS under license with AIA/NASNot for ResaleNo reproduction or networki
30、ng permitted without license from IHS-,-/:#:#$#:$:*:$#:# STD.AIA/NAS NASMSb74-ENGL 2000 W 0338743 0508935 397 NATIONAL AEROSPACE STANDARD Q COPYRIGHT 2000 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, MC. ALL RIGHTS RESERVED NASM5674 3.4.1 Tensile strength. In lieu of a shear test, a tensile test sha
31、ll be performed on rivets smaller than 0.0937 inch diameter, on rivet lengths less than 1.5D, and on nonstandard diameter rivets for which a shear test fixture is not available (see 4.5.2.2). The wire or rod samples shall be taken from the same material lot that the rivets are made from and heat-tre
32、ated with the rivets it represents. Tensile properties shall be as specified in QQ- A-430, Table III or AMS 4982. A tensile test is not required for 1100-F and 5056-H32 aluminum alloy rivets. 3.5 Heat treatment. Heat treatment of aluminum alloy 201 7-T4,2024-T4,2 1 17-T4,22 19-T62,22 19- T8 1 and 70
33、50-T73 rivets shall be in accordance with AMs 2770 with the exception that both electrical conductivity and hardness testing is not required. Heat treatment for 450 rivets shall be in accordance with AMs 4982. 3.6 Finishes. Finishes shall be as specified on the applicable standards. 3.7 Roundness an
34、d runout. Rivet heads shall not deviate from true roundness and runout with the shank by an amount which will produce a full indicator movement greater than the value specified in Table II for the corresponding rivet diameter. The reading shall be taken with the indicator touching the periphery of t
35、he head as the rivet is rotated with the shank as an axis. TABLE II. Tolerances on roundness and runout. Total variation in indicator Nominal diameter of reading on rivet head rivet shank (inch) Flush head I Protruding head I (inch) (inch) 0.062.0.094. O. 125 I 0.0 1 o I 0.010 I 0.156.0.187.0.219 I
36、I I 0.0 1 o I 0.0 15 i L 0.250 0.020 0.015 0.3 12.0.375 0.020 0.0 1 o 3.8 Discontinuities. Rivets shall be cold formed or forged to conform to the requirements of Table III. The rivets shall be free from surface discontinuities except that: a. Indented circles or arc lines concentric to the shank di
37、ameter, not greater than 0.004 inch in depth, are acceptable. b. Smooth irregularities at the periphery of the head that do not extend inside the minimum head diameter, as defmed on the applicable standard, are acceptable. No material separation is permitted. 4 APPROVAL DATE MARCH 2000 REVISION USE
38、OF OR RELIANCE 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 MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF ITEMS FOR ANY PARTICULAR APPL
39、ICATION, OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO OF PATENT OR TRADEMARK 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-,-/:#:#$#:$:*:$#:#NATIONAL AEROS
40、PACE STANDARD O COPYRIGHT 2000 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED NASM5674 TABLE III. Discontinuities. Maximum depth Location For shank dia .2812 & .3125 .O06 and minor isolated inclusions shank For shank dia up to .250 .O04 Laps, seams, die marks, etch pits Top of
41、 head and end of normal to surface 1/ Permissible condition For shank dia .3437 & .3750 .O07 Shank and bearing area of Isolated nicks, abrasions, etch I head I pits, minor isolated inclusions, intergranular corrosion laps, I 0.004 I I seams. die marks. fins, etc. I I I Continuous longitudinal defect
42、s I .I 0.002 - I! Measured perpendicular to a line tangent to the curved surface at the point of intersection with the discontinuity. Flat or end surfaces are not curved. 3.9 Driveability. When upset in a futture in accordance with Figure 1 aluminum alloy 7050 rivets shall have a bucked head not les
43、s than 1.6 times the rivet diameter. Rivets of all other alloys shall have a bucked head diameter of not less than 1.5 times the rivet diameter. The bucked head height shall not exceed 0.3 times the rivet diameter (see Figure 1 and 4.5.2.4). 3.9.1 Cracks. The bucked head of driven rivets (all alloys
44、) shall show no cracks when visually inspected without magnification. 4. QUALITY ASSURANCE PROVISIONS 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.
45、 Except as otherwise specified in the contract or purchase order, the contractor may use his own or any other facilities suitable for the performance of the inspection requirements specified herein, unless disapproved by the procuring activity. The procuring activity reserves the right to perform an
46、y of the inspections set forth in the specification where such inspections are deemed necessary to ensure supplies and services conform to prescribed requirements. 4.1.1 Responsibility for compliance. All items shall meet all requirements of Section 3 and 5. The inspection set forth in this specification shall become a part of the contractors overall inspection system or quality program. The absence of any inspec
