1、NASM 7838-2001 bolt, internal wrenching, 160 ksi ftu_STD.AIA/NAS NASM7838-ENGL 2001 0318743 05092b0 751 NATIONAIL AEROSPACE STANDARD OCOPyRlGHT 2001 AEROSPACE INDUSTRIES ASSOCIATION OF AMERlCA INC ALL RIGHTS RESERVED ALL RIGHTS RESERVED NASM7838 SPECIFICATION BOLT, INTERNAL WRENCHING, 160 KSI FTU 1.
2、 SCOPE 1.1 Scope . This specification covers internal wrenching bolts for use in applications requiring 160 KSI tensile strength, 96 KSI shear strength, or high fatigue strength and combinations thereof 2. APPLICABLE DOCUMENTS 2.1 Government documents. 2. 1.1 Specifications, standards and handbooks.
3、 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 the Department of Defense Index of Specifications and Standards (DoDISS) and supple
4、ment thereto, cited in the solicitation. SPECIFICATIONS FEDERAL QQ-P-416 PPP-B-566 PPP-B-585 PPP-B-60 1 PPP-B-621 PPP-B-636 PPP-B-665 PPP-B-676 Plating, Cadmium (Electrodeposited) Boxes, Folding, Paperboard Boxes, Wood, Wirebound Boxes, Wood, Cleated-Plywood Boxes, Wood, Nailed and Lock-Comer Box, F
5、iberboard Boxes, Paperboard, Metal Stayed (Including Stay Material) Boxes, Setup Paperboard MILITARY MIL-P- 1 16 - Preservation, Methods of MIL-B- 12 1 - Barrier Material, Greaseproofed, Waterproofed, Flexible MIL-S-5000 - Steel, Chrome-Nickel-Molybdenum (E4340) Bars and Reforging Stock MIL-T-5544 -
6、 Thread Compound: Antiseize, Graphite-Petrolatum MIL-S-5626 - Steel, Chrome-Molybdenum (4140) Bars, Rods and Forging Stock (For Aircraft Applications) THE INITIAL RELEASE OF THIS DOCUMENT SUPERSEDES MIL-B-7838, REVISION C, AMENDMENT 1. 0 CANCELED AFTER JULY 3 1,2001 AND SUPERSEDED BY NAS4002 AND NAS
7、4003. SHEET I OF 16 FSC 5306 APPROVAL DATE Jan. 200 1 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 ORCLA
8、IM 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. (AIA NAS)Licensed by Information Handling ServicesSTD*AIA/NAS NASM783B-ENGL 2OOL 03l18
9、7Y3 0509261 698 NATIONAL AEROSPACE STANDARD O COPYRIOHT 1999 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIOHTS RESERVED NASM7838 SPECIFICATIONS (Continued) MIL-S-6049 MIL-S-6098 - MIL-H-6875 - MIL-S-7742 - MIL-S-8503 - MIL-S-8879 - MIL-L- 10547 - Steel, Chrome-Nickel-Molybdenum (8740) Bar
10、s and Forging Stock (For Aircraft Applications) Steel, Chrome-Nickel-Molybdenum (8735) Bars and Forging Stock (For haft Applications) Heat Treatment of Steels (Aircraft Practice), Process for Screw Threads, Standard, Optimum Selected Series, General Specification For Steel Bars: Chrome-Vauadium (615
11、0) Aircraft Quality Screw Threads, Controlled Radius Root with Increased Minor Diameter, Genual Specification for Liners, Case, Waterproof STANDARDS MILITARY MIL-STD-105 - MIL-STD-129 - MIL-STD-1186 - MIL-STD-1312 - MIL-STD-1949 - MS20004 thru MS20024 - Sampling Procedures and Tables for Inspection
12、by Attriiutes Marking for Shipment and Storage Cushioning, Anchoring, Bracing, Blocking and Waterproofing; With Appropriate Test Methods. Fastena Test Methods. Inspection, Magnetic Particle. Bolt, Internal Wrenching, 160 KSI. (Copies of specifications, standards and handbooks required by contractors
13、 in conuection with specific acquisition functions should be obtained fiom the contracting activity or as directed by the contracting activity.) 2.2 Other publications. The following documents(s) forms a part of this specification to the extent specified herein Unless otherwise specified, the issues
14、 of the documents which are DoD adopted shall be those listed m the issue of the DoDISS specified in the solicitation. Unless otherwise specified, the issues of the documents not listed in the DoDISS shall be the issue of the nongovernment documents which is curent on the date of the solicitation. A
15、MERICAN NATIONAL STANDARDS INSTITUTE ANSI B46.1 - Surface Texture (Surface Roughness, Waviness and Lay) (Application for copies should be addressed to the American National Standards Institute, 1430 Broadway, New York, NY 10018.) UNIFORM CLASSIFICATION COMMITTEE Uniform Freight Classification Rules
16、2 APPROVAL DATE JUNE 1999 REVISION USE OF OR TON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS WTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPLIERS OR CERTIFY CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTINO (1) THE SUITABILIIY OF IT
17、EMS FOR ANY PARTICULAR APPLICATION. OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO OF PATENT OR TRADEMARK RIOHTS COPYRIGHT Aerospace Industries Association of America, Inc. (AIA NAS)Licensed by Information Handling ServicesSTD.AIA/NAS NASM7838-ENGL 2OOL 0338743 05072b2 524 NATIONAL AEROSPACE STAND
18、ARD Q COPYRIGHT 1999 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL RIGHTS RESERVED NUM7838 (Application for copies should be addressed to the Uniform Classification Committee, 222 South Riverside Plaza, Chicago, IL 60606.) 2.3 Order of precedence. In the event of conflict between the text of
19、 this specification and the references cited herein (except for associated detail specifications, specification sheets or MS Standards), the text of this specification shall take precedence. Nothing in this specification, however, shall supersede applicable laws and regulations unless a specifc exem
20、ption has been obtained. 3 REQUIREMENTS 3.1 Military Standards. The individual item requirements shall be as specified herein and in accordance with the applicable standards. In the event of any conflict between the requirements of this specification and the MS sheets, the latter shall govan. 3.2 Th
21、is paragraph left intentionally blank. 3.3 Materials. Qualification bolts shall be made from alloy steel conforming to specification MIL-S-5000 (UNS G43400 or UNS G43406), MIL-S-5626 (UNS G41400), MIL-S-6049 (UNS G87400), Mn-S-6098 (UNS G87350) or MIL-S-8503. Production bolts shall be made from mate
22、rial procured to the same nominal composition limits as that used for qualification. 3.4 Design and construction. The design and construction of the bolt shall be as specified herein and on the applicable standard. 3.4.1 Dimensions. Dimensions shall be in accordance with MS20004 thru MS 20024 or oth
23、er applicable specifications. 3.4.2 Threads. 3.4.2.1 Form and dimensions. The form and dimensions shall conform to MILS-8879 with the following exception: size 1-14 thread form and dimeslsions shall be per MIL-S-7742 and MS20016, except thread roots shall be round and minor diameter modified as spec
24、ified in Figure 1. 3.4.2.2 Rolling. Threads shall be llly formed by single rolling process after heat treatment. 3.4.2.3 Incomplete threads. Thread mout, consisting of not more than two incomplete threads, shall fair into shank, thereby eliminating an abrupt change in cross sectional area as illustr
25、ated in Figure 1. There shall be a thread runout of not less than one thread. Bottom and sides of threads in runout may deviate from true thread form, but shall be smooth and devoid of tool marks. Incomplete threads shall conform to Figure 1A. 3.4.2.4 Grain flow. The grain flow in the threads shall
26、be continuous and shall follow the general thread contour with the maximum density at the bottom of the root radius as shown in Figure 2. 3.4.3 Heads. Heads shall be forged. Sockets may be forged or machined. Flash or chip clearance in machined sockets shall not penetrate the head dimensional thickn
27、ess nor shall it be any larger than the hexagon width across flats. 3 APPROVAL DATE JUNE 1999 REVISION USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL. AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLTERS OR CERTIFY CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STA
28、NDARDS. AIA MAKES NO REPRESENTATION OR CWM 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. (AIA NAS)Licensed by Information Handling Serv
29、icesSTD.AIA/NAS NASM7838-ENGL 2001 0338743 05092b3 460 NATIONAL AEROSPACE STANDARD 0 COPYRIGm 1999 AEROSPACE INDUSTRIES ASSOCIATION OF -CA, INC. ALL RIGHTS RESERVED NASM7838 3.4.3.1 Bearing surface. The bearing surface ofbolt heads shall be at right angles to the shank within limits shown in Figure
30、3. The angular error of the underside of the head must be uniform around the shank within a tolerance of rtl0 minutes, as measured from the face of the head at length approximately equal to the diameter of the bolt. o,b) 2P MAX(INC0MPLETE (b)COMPLETE THDS. I .25P MIN 1 (APPLICABLE TO START OF THD MI
31、L-S-7742) RUNOUT END OF THD RUNOUT RUNOUT THREAD) (a.b) 2P MAX (INCOMPLETE LEAD THREAD PLUS CHAMFER) .5R (a) (MIN RAD FOR BUNK EXTRUDED FOR THD ROLLING) (APPLICABLE TO MIL-S-7742) CHAMFER NATURAL FLOW OF URAL FLOW OF ERIAL PERMITTED MIN RAD) FOR BLANK GROUND FOR THD ROLLING. (APPLICABLE TO MIL-S-774
32、2) MATERIAL PERMITTED (a) NOT APPLICABLE AFTER THREAD ROLLING. (APPLICABLE TO MIL-S-7742) The following table is applicable to MIL-S-7742 and MS20016 only. Thread li T R 2 P .25 P P size (Min root .5 R (Min mout (MW (Min) (pitch of - thread) radius) radius) - 21 1-14 .O08 .o12 .O25 .143 .O18 ,07143
33、- 1/ Maximum thread root radius limited by requirement that threads accept “GO” thread gage. - 2/ 1-14NS inactive for new design. FIGURE 1. Incomplete thread pitches, mout radius and root radius (optional design). 4 APPROVAL DATE JUNE 1999 REVISION USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATION
34、AL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY CONFORMANCE OF ITEMS PRODUCED UND= NATIONAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAM RESPECTING (1) THE SUITABILITY OF ITEMS FOR ANY PARTICULAR APPLICATION, OR (2) THE EXISTENCE OF OR APPLICABILITY
35、 THERETO OF PATENT OR TRADEMARK RICSHTS COPYRIGHT Aerospace Industries Association of America, Inc. (AIA NAS)Licensed by Information Handling ServicesSTD.AIA/NAS NASM7838-ENGL 2onL G3i8743 0509264 377 NATIONAL AEROSPACE STANDARD 0 COPYRIGHT 1999 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALL
36、RIcmTs RESERVED NASM7838 SHANK 7 - RUNOUT THREADS - MAX 2P L 1- MAX 2P LEAD THREADS .5 MAJOR DIA. TDL + H/8 (H/8=. 1 0825P) - CHAMFER 45 APPROX. I L 5/24 H OR .18042 P I SHADOW PROFILE OF THREADS FIGURE 1A. Determination of incomplete threads. MAJOR DIAMETER PITCH DIAMETER MINOR DIAMETER FIGURE 2. T
37、hread Grain Flow. FIGURE 3. Head Angularity. -1- MIN. THREAD HEIGHT -f 5 APPROVAL DATE JUNE 1999 REVISION USE OF OR REWCE 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 STAN
38、DARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF ITEM FOR ANY PARTICULAR APPLICATION, OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO OF PATENT OR TRADEMARK RIaHTS COPYRIGHT Aerospace Industries Association of America, Inc. (AIA NAS)Licensed by Information Handling Serv
39、icesSTD.AIA/NAS NASM7838-ENGL 2OOL 0318743 05092b5 233 NATIONAL AEROSPACE STANDARD 0 COpyRIc1HT 1999 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. ALLRIGHTS RESERVED NUM7838 show grain-flow lines substantially as shown in Figure 4. The grain-flow lines may be slightly broken by the finish machin
40、ing or grinding. 3.4.3.2 Head structure and grain flow. A section of the head shall show no detrimental defects and shall 3.4.4 Fillet (head-to-shank). The fillet shall be cold-worked in such a manner as to produce the fatigue strength requirements specified herein. Fillet shall be finished to radiu
41、s specified on the applicable drawing. Cold working of fillet radius shall be accomplished subsequent to heat treatment of bolt. Fillet shall show no evidence of seams or inclusions. 3.4.4.1 Distortion radius. Cold working of head-to-shank fillet may cause distortion of fillet area Distortion shall
42、not exceed 0.002-inch above A or below B contour shown on Figure 5. Distorted area shall not extend beyond C as illustrated in Figure 5. 3.5 Surface roughness. The surface roughness of the bolt, after plating, shall be not greater than the values shown in Table I. The surface roughness shall be meas
43、ured in accordance with ANSI B46.1. TABLE I. Roughness height rating (Ra). Maximum Microinches Shank and undersize of head Head-to-shank met Sides of thread and root area other dses 125 3.6 Straightness. The straightness of the bolt shank shall be within the values specified in Table II when the bol
44、t is rolled on a surface plate and the point of greatest deviation is measured with a feeler gage. TABLE II. Straightness of shank Deviation of Bolt Shank Bolt size of Bolt Len&) IMaxjmum) From Plate (Inch PH Inch .250 and .3 13 .375 and .438 0.0030 o. 0020 SOO and larger O. 0025 3.7 Heat treatment.
45、 Heat eeatment shall be m accordance with MIL-H-6875 to develop the mechanical properties specified herein. 3.8 Finish. AU surfaces shall be cadmium plated in accordance with QQ-P-416, Type II, Class 2. The bolts shall be heated to a temperature of 190 f 14C (375 f 25F) within 4 hours after plating
46、and before magnetic particle inspection, and held at this temperature for 23 hours, after which the bolts shall be allowed to cool normally at room temperature. 6 APPROVAL DATE JUNE 1999 REVISION USE OF OR RELIANCE UPON THIS WCUMENT OR ANY NATIONAL AEROSPACE STANDm IS ENTIRELY VOLUNTARY. AIA WES NOT
47、 QUALEY 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 OF PATENT OR TRADEMARK RIOHTS COPYRIGHT Aerospa
48、ce Industries Association of America, Inc. (AIA NAS)Licensed by Information Handling ServicesSTD.AIA/NAS NASM3838-ENGL 2001 MB 0338743 05092bb L7T NATIONAL AEROSPACE STANDARD O COPYRIGHT 1999 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, MC. ALL. RIGHTS RESERVED NASM7838 SOCKET-MACHINED HEAD-UPSET SOCKET-IMPACTED HEAD-UPSET FIGURE 4. Head structnre and grain flow. Nominal 0.188 O. 156 O. 125 0.094 0.062 C Max over 1 .750 .438 ,313 Under Size Through 1 Through.625 and
