NASM 22978-2000 Fastener, Rotary, Quick-operating, High-strength.pdf

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1、NASM 22978-2000 Fastener, Rotary, Quick-operating, High-strength_0338743 0508304 93b W -2978 ADOPTION NOTICE NASM22978, nFASTENER, ROTARY, QUICK-OPERATING, HIGH-STRENG= I, was adopted on 29 JUNE 2000 for use by the Departrent of Defense (DoD). Proposed changes by DoD Activities u8t be submitted to t

2、he 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 Avenue, Building QD, Philadelphia, PA 19111-5094. The private se

3、ctor 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 : Navy - AS Air Force - 99 DIA-IS Adopting activity: DIA- IS (Project 5325-1033-002) COPYRIGHT Aerospace Industries Associa

4、tion of America, Inc. (AIA NAS)Licensed by Information Handling ServicesNATIONAL AEROSPACE STANDARD O COPYRIGHT 2000 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED NASM22978 SPECIFICATION FASTENER, ROTARY, QUICK-OPERATING, HIGH-STRENGTH 1. SCOPE 1 .I Scope. This specification

5、covers the general requirements for a high-strength, quick- operating, rotary fastener. 1.2 Classification. Fasteners furnished under this specification shall be of the following types, as specified (see 6.2): Type I - Flush head Type II - Protruding head 2. APPLICABLE DOCUMENTS 2.1 The following do

6、cuments, of the issue in effect on the date of invitation for bids or request for proposal, form a part of this specification to the extent specified herein: SPECIFICATIONS Federal QQ-A-287 Aluminum Alloy Plate and Sheet, Alclad 7075 QQ-A-362 Aluminum Alloy Plate and Sheet, Alclad 2024 QQ-Pd16 Plati

7、ng, Cadmium (Electrodeposited) Military MIL-H-3982 Hardware (Fasteners and Related Items) Packaging and Packing for Shipment and Storage of MIL-S-5000 Steel, Chrome-Nickel-Molybdenum (4340 or E-4340) MIL-C-5541 Chemical Films for Aluminum and Aluminum Alloys MIL-S-6050 Steel, Chrome-Nickel-Molybdenu

8、m (8630) Bars, MIL-H-6875 Heat Treatment of Steels, (Aircraft Practice) MIL-A-8625 Anodic Coatings, for Aluminum and Aluminum Alloys MIL-S-18728 Steel Plate, Sheet, and Strip, Alloy, 8630, Aircraft Quality MIL-S-18729 Steel Plate, Sheet, and Strip, Alloy, 41 30, Aircraft Quality Bars and Reforging S

9、tock Rods, and Reforging Stock (for Aircraft Applications) Process for THE INITIAL RELEASE OF THIS DOCUMENT SUPERSEDES MIL-F-22978, REVISION A, AMENDMENT 1. LIST OF CURRENT SHEETS NO REV NEW 12 NEW 9 NEW 6 NEW 3 NEW 11 NEW 8 NEW 5 NEW 2 NEW 13 NEW 10 NEW 7 NEW 4 NEW 1 REV NO REV NO REV NO REV NO . .

10、 , NFW 17 NEW SHEET 1 OF 13 FSC 5325 APPROVAL DATE MAY 2000 USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT REVISION QUALIFY SUPPLIERS OR CERTIFY CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION

11、 OR CLAIM RESPECTING (1) THE SUITABILITY OF ITEMS FOR ANY PARTICULAR APPLICATION, OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO PF PATENT OR TRADEMARK RIGHTS. COPYRIGHT Aerospace Industries Association of America, Inc. (AIA NAS)Licensed by Information Handling ServicesSTD.AIA/NAS NASfl22976-ENGL

12、2000 I 0338743 0507043 800 I NATIONAL AEROSPACE STANDARD O COPYRIGHT 2000 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED NASM22978 STANDARDS Federal FED. STD. NO. 66 Steel: Chemical Composition and Hardenability FED. STD. TEST METHOD NO. 151 Metals; Test Methods Military MIL-S

13、TD-129 Marking for Shipment and Storage MIL-STD-130 Identification Marking of US Military Property MS9006 Recesses Cross, Low Torque Drive, Dimensions and Gage MS17731 Fasteners, Rotary, Quick-Operating, Flush Head, Floating Type, MS17732 Fastener, Rotary, Quick-Operating, Protruding Head, Floating

14、Dimensions For 2210 Lbs. Min Tensile Strength Type, 221 O Lbs. Min Tensile Strength (Copies of specifications, standards, drawings, and publications required by suppliers in connection with specific procurement functions should be obtained from the procuring activity or as directed by the contractin

15、g officer.) 3. REQUIREMENTS 3.1 Qualification. The 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 produc

16、ed using the same manufacturing methods as 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 Materials. Materials shall be carbon

17、or alloy steel selected from one of the following tables titled: “Standard Nonresulphurized Carbon Steels: Compositions and Forms Available” “Standard (SAE) Nonresulphurized Carbon Steels for Plates, Sheet, Strip, Structural Shapes, and Welded Tubing” or “Standard and Tentative Standard Alloy Steels

18、” of Federal Standard No. 66. The material shall be sound, of uniform quality and condition, free from pipes, and shall not contain decarburization, carburization, lap, cracks, twists, seams, or other defects detrimental to the fabrication or performance of parts. 3.2.1 Heat treatment. Heat treatmen

19、t of steel shall be in accordance with Specification MIL-H-6875. SHEET 2 REVISION APPROVAL DATE MAY 2000 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 ST

20、ANDARDS. AIA MAKES NO OF OR APPLICABILITY THERETO PF 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. (AIA NAS)Licensed by Information Handling

21、ServicesSTD=AIA/NAS NASM22778-ENGL 2000 I0338743 0507044 747 NATIONAL AEROSPACE STANDARD O COPYRIGHT 2000 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED NASM22978 3.3 Design and construction. The fastener shall be of the stud receptacle design and shall be so constructed that

22、neither the stud assembly nor the receptacle assembly can be inadvertently disassembled during normal operation. The design shall be such that the stud and receptacle can be removed and replaced in service with any other acceptable fastener of the same type without deviation from the dimensions note

23、d herein and without the use of special tools. The fastener shall provide for retention of the stud in the outer sheet when unfastened. 3.3.1 Curved sheet installation. The fastener shall be adaptable to a rigid, curved sheet installation wherein the radius of curvature is not greater than 12 inches

24、 and the included angle between extreme fasteners is 90 degrees when tested in accordance with 4.6.1 1. The fastener shall also be adaptable when the sheet has a radius of curvature not greater than 24 inches, is hinged at one side, and the included angle between the hinge and any fastener is 45 deg

25、rees. 3.3.2 Dimensions. The stud assembly and receptacle assembly shall fall within the envelope dimensions and shall conform to the detail dimensions shown on Standards MS17731 and MS17732 for the applicable type. 3.3.3 Stud assembly. The stud assembly configuration may employ a shear bushing, reta

26、iner ring, and other components. 3.3.3.1 Recess. The recess in the head of the stud shall be of the cross-recess type in accordance with the dimensions shown on Standard MS9006. 3.3.3.2 Head flushness. In designs utilizing a shear bushing-type component the stud shall be flush with the top of the sh

27、ear bushing within k0.005 inch. 3.3.4 Receptacle assembly. The receptacle assembly shall be of a floating type and have a minimum float of 0.020 in any direction from the centered position. 3.3.5 Locking and unlocking. When the stud assembly is mated with its receptacle assembly, the installed faste

28、ner shall be capable of being fully locked (see 6.4.2) within two complete rotations in the clockwise direction as viewed from the outer sheet. After rotation in the counterclockwise direction to the point of disengagement, and when the inner and outer sheets are then separated by an amount equal to

29、 the applicable minimum sheet pull-up value, the fastener shall be capable of relocking without additional counterclockwise rotation. The fastener shall be considered to be fully locked when tightened to a torque conforming to the sheet separation requirement specified in 3.5.5 but which does not ex

30、ceed the applicable maximum locking torque value listed in table I. The fully locked fastener shall unlock to the point of complete disengagement within two complete rotations in the counterclockwise direction as viewed from the outer sheet. 3.4 Finish. Parts of carbon or alloy steel shall be cadmiu

31、m plated in accordance with type II, class 3 of Specification QQ-P-416. SHEET 3 REVISION APPROVAL DATE MAY 2000 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 AEROS

32、PACE STANDARDS. AIA MAKES NO OF OR APPLICABILITY THERETO PF 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. (AIA NAS)Licensed by Information Ha

33、ndling Services3.5 3.5.1 3.5.2 3.5.3 3.5.4 3.5.5 3.5.6 3.5.7 NATIONAL AEROSPACE STANDARD O COPYRIGHT 2000 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA. INC. ALL RIGHTS RESERVED TABLE I. Room temperature mechanical properties Requirement Torque value Locking torque 4,650 pounds (min) Ultimate shear lo

34、ad 75 inch-pounds (min) Torque out 35 inch-pounds (max) Unlocking torque 30 inch-pounds (max) Not to exceed 0.01 5 inch Sheet separation 1,700 pounds (min) Rated tensile load 2,21 O pounds (min) Ultimate tensile load 3,580 pounds (min) Rated shear load (test condition) at rated tensile load Sheet pu

35、ll-up 1/16 inch (min) Receptacle push-out 125 pounds (min) Stud push-out 150 pounds (min) NASM22978 Performance. Locking and unlocking torque. The maximum locking torque value specified in table I shall not be exceeded while operating the fastener through the entire range of sheet pull- up from init

36、ial engagement to the full locked condition when tested in accordance with 4.6.2. The unlocking torque value specified shall not be exceeded while rotating the fastener from the fully locked condition to the point to the point of complete disengagement. Torque-out. When the installed fastener is sub

37、jected to the torque-out values specified in table I in accordance with 4.6.3, there shall be no failure (see 6.4) or permanent deformation to any of the fastener components. Shear. The fastener shall not develop permanent deformation when subjected to the rated shear load and shall withstand the ul

38、timate shear load specified in table I without failure when tested in accordance with 4.6.9. Tension. The fasteners shall not develop permanent deformation when subjected to the rated tensile load and shall withstand the ultimate tensile load specified in table I without failure when tested in accor

39、dance with 4.6.5. Sheet separation. The sheet separation determined in accordance with 4.6.6 shall not exceed the value specified in table I when the installed fastener assembly in the fully locked condition is subjected to the rated tensile load specified in table I. Sheet pull-up. The installed fa

40、stener shall be capable of initial engagement when a sheet separation condition exists at the fastener of not less than the values specified for “Sheet pull-up” in table I. The fastener shall then be capable of drawing the sheets together at the fastener to the fully locked condition when tested in

41、accordance with 4.6.2. Stud push-out. The stud assembly of the installed fastener shall withstand the push-out values specified in table I without permanent deformation to any components or separation from the sheet when tested in accordance with 4.6.12. APPROVAL DATE MAY 2000 USE OF OR RELIANCE UPO

42、N 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 APPLICATION, OR (2) TH

43、E EXISTENCE OF OR APPLICABILITY THERETO PF PATENT OR TRADEMARK RIGHTS. SHEET 4 REVISION COPYRIGHT Aerospace Industries Association of America, Inc. (AIA NAS)Licensed by Information Handling ServicesNATIONAL AEROSPACE STANDARD O COPYRIGHT 2000 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIG

44、HTS RESERVED NASM22978 3.5.8 Receptacle push-out. The push-out test load shall be applied axially to the receptacle body through a stud of the type fastener being tested and sufficiently long to transmit the entire test load to the receptacle components. The receptacle assembly shall be mounted in t

45、he same fixture as used for the tension test specified in 4.6.13. 3.5.9 Vibration. The fastener assembly shall be capable of withstanding the vibration test specified in 4.6.8 without fastener failure and with no more than a IO-percent reduction in the torque required to lock the fastener assembly.

46、3.5.10 Shear fatigue. There shall be no single fastener failure of the fastener assemblies when fatigue tested in accordance with 4.6.7. 3.5.1 1 Corrosion resistance. The fastener assembly shall be capable of withstanding the salt spray test specified in 4.6.10 without becoming inoperable within the locking and unlocking torque specif