NASM 5591-2000 Fasteners; Panel; Nonstructural.pdf

1、NASM 5591-2000 Fasteners; Panel; Nonstructural_0318743 0508322 931 m ADOPTION NOTICE custodians : -y - AR Navy - AS Air Force - 99 DLA- IS Adopting activity: DLA- IS (Project 5325-1031-002) NASM5591, FASTENERS; PANEL; NONSTRUCTURAL was adopted on 29 JUNE 2000 for use by the Department of Defense (Do

2、D). Proposed changes by DoD Activities must be submitted to the DoD Adopting Activity: Defense Supply Center Philadelphia, ATTN: DSCP-ILEA, 700 Rohbins Avenue, Philadelphia, PA 19111- 5096. DoD Activities may obtain copies of this standard from the Standardization Document Order Desk, 700 Robbins Av

3、enue, 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. Copyright Aerospace Industries Association of America Inc. Provided by I

4、HS under license with AIA/NASNot for ResaleNo reproduction or networking permitted without license from IHS-,-/:#:#$#:$*:$#:#NATIONAL AEROSPACE STANDARD 0 COPYRIGHT 2000 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED NASM5591 SPECIFICATION FASTENERS; PANEL; NONSTRUCTURAL 1. SC

5、OPE 1.1 Scope. This specification covers nonstructural panel fasteners used on internal or external parts of aircraft. 1.2 Classification. Panel fasteners shall be of the following types, classes, styles, and sizes, as specified (see 3.2 and 6.2): Type I Type II Type III Class A Class B Style 1 Styl

6、e 2 Style 3 Sizes Flush head Oval head Wing head Floating receptacle Rigid receptacle Type I for deep dimple without grommet; Types II and III for undimpled sheet without grommets. Type I for deep dimple with grommets; Types II and III for undimpled sheet with grommets. Type I for shallow dimple wit

7、h grommet; Types II and III for undimpled sheet with grommet. Each head type shall be furnished in the sizes shown on Figure l. 2. APPLICABLE DOCUMENTS 2.1 Government documents. 2.1.1 Specifications, standards and handbooks. The following specifications, standards and handbooks form a part of this d

8、ocument to the extent specified herein. Unless otherwise specified, the issues of these documents shall be those listed in the issue of the Department of Defense Index of Specifications and Standards (DoDISS) and supplement thereto, cited in the solicitation. SPECIFICATIONS FEDERAL QQ-A-25014 Alumin

9、um Alloy Plate and Sheet 2024 QQ-P416 Plating, Cadmium (Electrodeposited) THE INITIAL RELEASE OF THIS DOCUMENT SUPERSEDES MIL-F-5591, REVISION C, AMENDMENT 2. LIST OF CURRENT SHEETS SHEET 1 OF 16 FSC 5325 REVISION APPROVAL DATE MAY 2000 USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE

10、 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 APPLICABILITY THERETO O

11、F 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 AEROSPACE STANDARD O COPYRIGHT 2000 AEROSPACE INDUSTRIES ASSOCIAT

12、ION OF AMERICA, INC. ALL RIGHTS RESERVED NASM5591 SPECIFICATIONS (Continued) PPP-H-1581 MILITARY DOD-D-1 O00 MIL-A-8625 MIL-S-18728 MIL-S-18729 STANDARDS MILITARY MIL-STD-105 MIL-STD-1312 Hardware (Fasteners and Related Items) Packaging and Packing for Shipment and Storage of Drawings, Engineering a

13、nd Associated Lists Anodic Coatings, for Aluminum and Aluminum Alloys Steel Plate, Sheet, and Strip, Alloy 8630, Aircraft Quality Steel Plate, Sheet, and Strip, Alloy, 41 30, Aircraft Quality Sampling, Procedures and Tables for Inspection by Attributes Fastener, Test Methods (Copies of specification

14、s, standards, drawings, and publications required by suppliers in accordance with specific procurement functions should be obtained from the procuring activity or as directed by the contracting officer.) 2.3 Order of precedence. In the event of a conflict between the text of this document and the re

15、ferences cited herein (except for associated detail specifications, specification sheets or MS standards), the text of this document takes precedence. Nothing in this specification, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 3. REQUIREMENTS 3.1

16、 Qualification. The fastener manufacturer shall be responsible for conducting qualification tests and furnishing part drawings, certified qualification test reports (if required by the purchaser) and test samples. The fasteners furnished under this specification shall be produced using the same manu

17、facturing methods as those used to produce fasteners that have passed qualification tests. The purchaser may apply any or all tests specified herein to any product represented as meeting this specification, at any time, to verify conformance. 3.2 Design. The style 1 fastener shall be of the stud-rec

18、eptacle design. When the fastener is opened, the stud assembly shall be retained by the outer panel and the receptacle shall be retained by the panel support. The styles 2 and 3 fasteners shall be of the stud-grommet-receptacle design. When the fastener is opened, the stud shall be retained in the p

19、anel. The grommet shall be designed to guide the stud into the outer panel and to prevent contact between the outer panel and the stud and shall be independently retained in the outer panel. The design of each style fastener shall permit the removal of the stud or stud-grommet combination and shall

20、permit replacement with a fastener conforming to the dimensions specified in Table I. Grommets shall be removable without damage to the panel. 2 APPROVAL DATE MAY 2000 USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY REVISION SUPPLI

21、ERS 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 APPLICABILITY THERETO OF PATENT OR TRADEMARK RIGHTS Copyright Aerospace Industries

22、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 NASN557L-ENGL 2000 m 031,8743 0509020 201 m NATIONAL AEROSPACE STANDARD O COPYRIGHT 2000 AEROSPACE INDUSTRIES ASSOCIATION

23、 OF AMERICA, INC. ALL RIGHTS RESERVED NASM5591 3.2.1 Dimensions. Overall dimensions, rivet spacing, rivet hole size, and diameter of dimple and hole shall be as specified in Table I. 3.2.2 Engaging. The stud shall engage the receptacle within 180 degrees of rotation in the clockwise direction as vie

24、wed from the outside panel. 3.2.3 Locking. The stud shall be positively locked within 85 to 135 degrees of clockwise rotation, as viewed from the outside panel after the stud has been engaged. 3.2.3.1 Stop. A positive stop shall be provided to prevent the stud from being turned past the position of

25、full lock. 3.2.4 Unlocking. The stud shall unlock within 85 to 135 degrees of counterclockwise rotation, as viewed from the outside panel. 3.2.5 Heads. 3.2.5.1 Flush head - Type I. The stud heads shall be flush with the surface of the outer panel within k0.015 when the fasteners are installed in mou

26、nting holes conforming to the dimensions specified in Table I and locking the total applicable panel thickness. 3.2.5.2 Oval head - Type II. Application of the oval head studs shall not require dimpling or countersinking of the outer panel. 3.5.2.3 Wing head - Type III. The wing head fastener shall

27、be designed for operation without tools. Application shall not require dimpling or countersinking of the outer panel. 3.2.6 Screwdriver slots. The screwdriver slot in the head Types I and II shall be such that a conventional blade-type screwdriver may be used to lock and unlock the fastener. When th

28、e fastener is in the locked position the slot shall be in line with the receptacle mounting rivets. 3.2.7 Floating receptacle. The class A receptacle shall be floating and shall provide a minimum lateral movement as specified in Table II. Lateral movement is measured in all directions from the cente

29、r or neutral position. 3 APPROVAL DATE MAY 2000 USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY REVISION SUPPLIERS OR CERTIFY CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RE

30、SPECTING (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 networking permit

31、ted without license from IHS-,-/:#:#$#:$*:$#:#NATIONAL AEROSPACE STANDARD O COPYRIGHT 2000 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED NASM5591 TABLE I. Panel fastener dimensions. SIZE H D B A STYLE H L K J DEGREES F DIA DIA DIA TYPE NUMBER CLASS MAX MAX MAX i0.005 DIA MIN

32、MAX MAX MIN MAX MAX 1 - .390 .919 lI,llI 2.000 0.625 1.375 0.125 118 120 0.774 0.700 0.720 0.390 0.919 I 7 A - ,125 1.625 ,562 1.000 .m 118 120 .713 .mo ,650 .327 .ao7 I 5 A 1 2.000 ,625 1.375 .125 - - .390 .822 II. 111 2.000 525 1.375 .i25 118 120 .774 .7oo ,720 .mo .a82 I 7 B 1 2.000 ,625 1.375 1

33、0 5 I .713 .327 - .327 .713 11,111 1.625 .562 1.000 .m 118 120 ,713 mo .mo - .125 1.000 .562 1.625 1 A 2 1.375 .43a 0.750 .o94 98 100 .47a ,396 .233 .510 I 2 B 1 1.375 .43a 0.750 .o94 - - .233 557 II, 111 1.375 ,438 0.750 .o94 98 loo ,478 ,396 .416 ,233 .557 I 11,111 .510 .233 - - ,094 0.750 .438 1.

34、375 2 A 7 I .945 .44e .832 1.000 .703 0.750 ,094 99 101 .4ao .437 ,450 ,257 .500 I 2 B 3 1.625 .734 1.000 ,125 - - .47a ,713 II, III 1.625 ,734 1.000 ,125 119 141 .6a7 .e60 .e80 ,478 .713 I 7 B 3 1.625 ,734 1.000 .125 - - ,478 ,713 II, III 1.625 ,734 1.000 ,125 139 141 .6a7 .mo .6ao ,478 .713 I 7s y

35、 A 3 1.750 ,734 1.375 ,125 - - ,478 ,833 II, III 1.750 ,734 1.375 ,125 139 141 .6a7 ,660 ,680 .47a .a33 I 7L Il A 3 1.375 .438 0.750 ,094 - - ,292 ,570 11, III 1.375 .438 0.750 ,094 98 loo .so .396 .494 ,292 ,570 I 2 B 2 1.375 ,438 0.750 .OM - - .292 ,570 II, III 1.375 .438 0.750 .OM 98 loo .550 .39

36、6 .494 ,292 ,570 I 2 A 2 1.625 562 1.000 .125 - - .4n ,832 II, III 1.625 562 1.000 .125 118 120 ,812 .ao 162 .3a5 .a32 I 5 B 2 1.625 562 1.000 .125 - - ,476 ,832 II, III 1.625 ,562 1.000 .m 118 120 .812 mo ,385 .832 I 5 A 2 2.000 525 1.375 .I25 - - .476 ,902 II, III 2.000 525 1.375 .i25 118 120 .a82

37、 ,700 .a32 .44a .go2 I 7 B 2 2.000 .625 1.375 ,125 - - ,476 .902 II, 111 2.000 .m 1.375 .m 118 120 ,882 ,700 _ II, 111 .500 .257 - - .O94 0.750 .703 1.000 II, III 1.625 .562 1.000 .125 - - .327 .ao7 N MAX 1.156 1.156 1 .o00 - - 1 .O32 0.875 0.875 - - 0.598 0.598 0.562 0.562 1.156 1.156 1 .o00 - - -

38、- 11 L and S indicate a long (L) and short (S) rivet spacing. The same stud and grommet may be used for both the L and S receptacles. 4 APPROVAL DATE MAY 2000 REVISION USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CE

39、RTIFY 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 APPLICABILITY THERETO OF PATENT OR TRADEMARK RIGHTS Copyright Aerospace Industries Associati

40、on of America Inc. Provided by IHS under license with AIA/NASNot for ResaleNo reproduction or networking permitted without license from IHS-,-/:#:#$#:$*:$#:#STD-AIA/NAS NASM559L-ENGL 2000 m 0318743 0507022 O8b m NATIONAL AEROSPACE STANDARD O COPYRIGHT 2000 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA

41、, INC. ALL RIGHTS RESERVED TABLE II. Mechanical properties. 2/ Size No. Style Locking torque, minimum Locking torque, maximum Unlocking torque, minimum Unlocking torque, maximum Initial tension, minimum Rated tensile load Rated shear load Locking stop strength, minimum Vibration requirements: Freque

42、ncy Amplitude Load Endurance, minimum Lateral movement of class A, Types I, II and III lb. in. lb. in. lb. in. lb. in. lb. lb. lb. lb. in. cpm flOO inches pounds cycles inches receptacles, minimum 1 &2 3.5 8 3.5 10.4 15 200 200 30 3600 1/16 75 5000 0.031 3 1 .o 11 1 .o 12.5 8 200 200 30 3600 1/16 75

43、 5000 0.031 5 1 &2 5.0 12 5.0 15.6 35 500 500 60 3600 1/16 175 25,000 0.062 1 &2 7.5 18 7.5 23.4 50 700 700 80 3600 1/16 225 40,000 - 1/ 0.62 NASM5591 3 5.0 20 7.5 25.5 35 700 700 60 3600 1/16 225 40,000 - I/ 0.062 - II When receptacle with 1 .OOO-inch rivet spacing is used, lateral movement may be

44、0.031 inch minimum. - 2/ See Figure l. 3.3 Interchangeability. All parts having the same manufacturers part number shall be directly and completely interchangeable with each other with respect to installation and performance. The drawing number requirements of DOD-D-1 O00 shall govern documentation

45、of and changes in the manufacturers part numbers. 3.4 Finish. Aluminum-alloy parts shall be coated with an anodic film in accordance with MIL-A-8625. Fasteners manufactured from steel or copper alloy shall be cadmium plated in accordance with QQ-P-416, Type II, Class 2 (see 4.6.1). 3.5 Performance characteristics. 3.5.1 Initial tension. The initial tension (bearing pressure) between the panels shall not be less than the value specified in Table II (see 4.4.3.1). 3.5.2 Sheet separation. The sheet separation shall be not greater