NASM 8831-2003 fasteners, alloy steel, 450 of externally threaded,180 ksi ftu, 108 ksi fsu, fatigue rated.pdf

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1、NASM 8831-2003 fasteners, alloy steel, 450 of externally threaded,180 ksi ftu, 108 ksi fsu, fatigue rated_Aerospace Industries NATIONAL AEROSPACE STANDARD Association O COPYRIGHT 2003 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA INC. ALL RIGHTS RESERVED CUSTODIAN NATIONAL AEROSPACE STANDARDS COMMITTE

2、E PROCUREMENT I TITLE FED. SUP CLASS 5306 1. SCOPE AND CLASSES THIRD ANGLE PROJECTION CLASSIFICATION 1.1 1.2 1.3 1.4 1.5 SPECIFICATION NONE This speafication defines the requirements for alloy steel externally threaded fatteners procured under patt numbers li on drawings which refer to this specific

3、ation. Typically these fasteners are used fa tension, shear, and tensiorbfatigue applications where 180 KSI mi and 108 KSI Fsu is desired with a serviceternperane capability to 450 F. Receiving contractors may reject any manwring iotwhitdoes notconform. STANDARD PRACTICE NASM8831 FASTENERS, ALLOY ST

4、EEL, 450 O F EXTERNALLY THREADED, 180 KSI Ftu, 108 KSI Fsu, FATIGUE RATED The cpecjfication indudes mechanical property requirements for hnro dacces of fastems as follows: Type I - Tension head (hex, double hex, 12 spline, etc. without an internal or recess drive) and Ws. Type II - 100 fuU flush hea

5、d and internal wrenching (pan, fillister, brazier, etc.) head cungutaon. Wokmanship of fastews shall conform with aircraft fastener manufacturing procesces. Recommendabons * for improvements or correcons to this specification should be direded to an NASC of a Using company or to the Exeadjve Secreta

6、ry of the National Aerospace Standard Committee. SpeciricatiOns listed herein, of the issue in em on date of inquiry, are a patt of this specification to extent indicated. In the case of conflict, the requirements herein shall take precedence. Unless othennrise specmed, part inventory manufactured b

7、 MIL-88831 or preVous reVicions ofthe applicable dMng or specification may be proai and used uniil stock is depleted. 2. APPLICABLE DOCUMENTS 2.1. Induslrystandanlc 2.1.1 Society of automotive Engineers AMs6322 Steel Bars, Forgings, and Rings, 0.5Cr4.55 Ni.25Mo (0.384.43C) (SAE8740) AMs6415 Steel Ba

8、rs, Forgings, and Tubing, 0.80Cr-1.8N-025Mo (0.380.43C) (SAE4340) AMS6484 Steel Bars, Forgings, and Tubing, 0.8ocr-1 .8Nd0.25Mo (0.384.43C) (SAE434) AMsH6875, HeatTreatrnentof Steel Raw Materials 2.1.2 American Society of Mechaniml Engineers ASME 846.1 Surface Texture (Surface Roughness, WavinesC, a

9、nd Lay) 2.1.3 American Society for Quality Control ASQC Z1.4 Sampling Procedures and Tables for Inspection Attributes o The initial release of this document suDercedes MIL-B-883 I, Revision B. Amendment 2 USE OF OR RELWJCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY A

10、IA DOES NOT CIUALIFY SUPPLIERS OR CERTIM 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 ESISTENCE OF OR APPLICABILITY THERETO OF PATENT OR TRADEMARKS RIGHTS Copyri

11、ght 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- CCOPYiGHT 2001 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA RIC ALL RIGHTS RESERV

12、ED c analysis Ncking. ysis for DIMENSIONS Per fastener part standard. SQUARENESSOF HEAD BEARING FIGURE 3. 2.1.4 American Society for Testing & Material ASTM E 112 Grain Size, Standard Test Methods for Determining Average ASTM E 140 Standard Hardness Conversion Tables for Metals ASTM E 340 Standard T

13、est Methods for Macroetching Metals & Alloys ASTM E 407, Standard Test Practice for Microetching Metals & Alloys ASTM E 1444, Standard Practice for Magnetic Particle Inspection NAS672 , Plating - High Strength Steels - Cadmium NAS1348, Fasteners - Recommended Tensile Stress Areas for Externally Thre

14、aded Alloy Steel NAS9800, Head Protrusion Gaging 1 OOo Flush Head Fastener Gage Block, Gage Diameters, and Stylus NASM1312 (MIL-STD-1312) Fastener Test Methods NASM1312-1 (MIL-STD-1312-1) Fastener Test Methods, Method 1, Salt Spray NASMl312-5 (MIL-STD-1312-5) Fastener Test Methods, Method 5, Stress

15、Durability NASMl312-6 (MIL-STD-1312-6) Fastener Test Methods, Method 6, Hardness NASM1312-8 (MIL-STO-1312-8) Fastener Test Methods, Method 8, Tension Test NASM1312-11 (MIL-STD-1312-11) Fastener Test Methods, Method 11, Fatigue Test NASM1312-12 (MIL-STD-1312-12) Fastener Test Methods, Method 12, Thic

16、kness of Metallic Coatings NASM1312-13 (MIL-STD-1312-13) Fastener Test Methods, Method 13, Double Shear Test NASM1312-20 (MIL-STD-312-20) Fastener Test Methods, Method 20, Single Shear Test NASM1312-25 (MIL-STD-1312-25) Fastener Test Methods, Method 25, Driving Recess Toque, Quality Conformance Test

17、 NASMl4191 Recess, Offset Cruciform, Ribbed, Dimensions of Recess, Gage and Driver for NACM33750 Recess, Dovetail and Conical Dovetail, Dimensions of Recess, Gage and Driver for NASM33781 Recess, Offset Cruciform, Dimensions of Recess, Gage and Driver for 2.1.5 Aerospace Industries Association of Am

18、erica, National Aerospace Standards Committee for 25% (or more) oi the parts used for metallurgical examination. Not mandatory. 2.2 Federal Specifications QQ-P-416 Plating, Cadmium (Electrodeposited) T SHANK DIA. Conventional measuring SHANK STRAIGHTNESS methods. TABLE Vil. No burrs or slivers. 2.3

19、Military Specifications MIL-$8879 Screw Threads, Controlled Root with Increased Minor Diameter, General Specification for TABLES XI and XII. TABLE I - BASIC REQUIREMENTS ENGINEERING TESTING REQUIREMENTS (SEE 3.1) TEST METHOD I SAMPLING PLAN Decification. ICheck material comDosition REQUIREMENTS CHAR

20、ACTERISTICS CORNERS & EDGES Break edges and comers .003 min. to .016 max. 0 COMPLETELY REVISED NASM8831 Lz -. - USE OF OR RELIANCE ON lHIS COCUMENT OR ANY NATDNAL AEROSPACE STANDARD IC ENTIRELY VOLUNTARY. AIA DOES NOT WMIN SUPPERS OR CERTIFY CONFORMANCE OF mMS PROCURED UNDER NATIONAL AEROSPACE STAND

21、ARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUllABlLiW OF ITEMS FOR ANY PmncuVvI AFRICATION, OR CL) THE WSENCE OF OR APPLICABILITY THERETO OF PAM OR TRADEMARK RIGHTS. rl O O CY h l-4 c, a o . z O - K 8 F O z li a n I- 2 s 2 a P a Copyright Aerospace Industries Association of Americ

22、a Inc. Provided by IHS under license with AIA/NASNot for ResaleNo reproduction or networking permitted without license from IHS-,-/:#:#$#:$*:$#:#Aerospace Industries Association 4 NATIONAL AEROSPACE STANDARD OCOPYRIGKT 2001 AEROSPACE NDUSTRIES ASSOCIATION OF AMWCA iNC ALL RIGHTS RESERVED TABLE I - B

23、ASIC REQUIREMENTS (CONTINUED) ENGINEERING TESTING REQUIREMENTS (SEE 3.1) TEST METHOD SAMPLING PLAN TABLES XI and XII. TABLE CHARACTERISTICS REQUIREMENTS -LUSH HEAD Per NAS9800. ?ECESS DRIVE Conventional measuring methods. Per ASME B46.1 by SURFACE TEXTURE DENTIFICATION THREADS HEAD TO SHANK ILLET AR

24、EA -EAT TREATMENT visual or fingernail ?er fastener drawing or comparison. In case of part standard. controversy, check accessible surface areas using a profilometer. Raised or depressed, measured by conventiona method(s), not to exceed min or max requirements. Visual check for legibility. Shall be

25、rolled subsequent to thermal treatment except for bake requirements after plating or coating see Grain Flow and FIGURE 21. Conventional measuring Unless otherwise specified, methods. dimensions and form per See FIGURES 7 and 8. MIL-S-8879 except major diameter may be limited by part standard. Incomp

26、lete threads per Figures 7 and 8. Parts .1900 Dia. and larger shall be cold worked subsequent to all thermal TABLE XII, 1 .O% AQL. TABLES XI and XII. treatment except bake after plating or coating. The fillet radius shall conform to the part standard but may be Measurement by use of a comparator in

27、a TABLES XIII. of two I I distorted per FIGURE 4. Parts threaded to the head do not require cold working. I I Per AMs-H-6875. Shall I Idevelop mechanical properties as defined herein without effect On metallurgical properties as Test Of mechanical and metallurgical requirement. verifies heat treatme

28、nt. As indicated for each test !defined herein. I llndividual hardness 0 COMPLETELY REVISED I NASM8831 I SHEET 3 - USE OF OR RWNCE ON MIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS MRELY VOLUNTARY. AIA WES NOT QUALIFY SUPPLIERS OR CmFY CONFORMANCE OF mMS PROCURED UNDER NAiIONAL AEROSPACE STANDAR

29、DS. AIA MAKES NO REPRESENTATION OR CWM RESPKSnNG (1) THE SUITABILITY OF mMS FOR ANY PARTICULAR APPLICATION, OR (2) THE WSENCE OF OR APPUCABILmNTHEf?ETO OF PATENTORTRADEMARK RIGHTS. Copyright Aerospace Industries Association of America Inc. Provided by IHS under license with AIA/NASNot for ResaleNo r

30、eproduction or networking permitted without license from IHS-,-/:#:#$#:$*:$#:#Aerospace Industries NATIONAL AEROSPACE STANDARD Association O COPYRIGHT 2003AEROSPACE INDUSTRIES ASSOCIATION OFAMERCA INC. ALL RIGHTS RESERVED TABLE 1 - BASIC REQUIREMENTS (CONTINUED) CHARACTERISTICS SHEAR STRENGTH FATIGU

31、E TEST RECESS TORQUE METALLURGICAL UNTEMPERED MARTENSITE GRINDING BURNS ENGINEERING REQUIREMENTS Minimum strength per TABLE 111. Limitations per note (d) under TABLE 111. Fasteners shall pass the fatigue cyde requirements per TABLE XVI when subjected to loads per TABLE IV. Fasteners with MS14191, MS

32、33750,8 MS33781 recesses shall be capable of developing the recess torque values specified in TABLE V. No cracks permitted in any location. A crack is a clean crystalline break passing through the grain or grain boundary. Other discontinuities permitted only as described in TABLES II and IX. Untempe

33、red martensite (or transformed structure) is an acceptable condition only when: (1) condition is not found in root of threads or head of shank fillet, (2) condition does not produce discontinuities or burrs which result in oui of tolerance dimensions, (3) does not exceed depth allowed for laps or th

34、read crest discontinuities per TABLE IX, and (4) a crack(s) is not found in any location. None permitted on shank, head to shank fillet, threads, or bearing surface of head. TESTING RE TEST METHOD Double shear test per fastener is too short for double shear test, use HRC value per TABLE 111, Note (d

35、) or single shear test per MIL-STD- MIL-STD-1312-13. If 131 2-20 MIL-STD-1312-11 Recess torque test per requirements of TABLE V, Notes (a), (b), (c) and (d). Test in both installation and removal directions By longitudinal & circular method per ASTM E 1444. Perorn magnetic inspection after cadmium p

36、lating. Magnetic inspection is not required on fasteners with thread size smaller than .190. MI L-STDI 31 2-25 to Metallurgical examination. See 3.3 Strip plating and etch in 2% to 5% Nital solution. Examine at 1 OX to 1 oox. IUIREMENTS SAMPLING PIAN TABLE XV TABLE XVI TABLE XII1 100% INSPECTION TAB

37、LE XIV Use samples from metallurgical examination and untempered martensite NAS M 88 3 1 SHEET 4 USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY NATIONAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA DOES NOT UALIFY SUPPLIERS OR CERTIFY CONFORMANCE OF ITEMS PRODUCED UNDER NATIONAL AEROSPACE STANDARDS.

38、AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF ITEMS FOR ANY PARTICULAR APPLICATION OR (2) THE ESISTENCE OF OR APPLICABILITY THERETO OF PATENT OR TRADEMARKS RIGHTS. Copyright Aerospace Industries Association of America Inc. Provided by IHS under license with AIA/NASNot for Re

39、saleNo reproduction or networking permitted without license from IHS-,-/:#:#$#:$*:$#:#Aerospace Industries Association CHARACTERISTICS AICRoSTRUCTURE NATIONAL AEROSPACE STANDARD OCOPYIUGHT 2001 AEROSPACE INDUSTIUES ASSOCIATION OF AMERICA MC. Au. RIGHTS RESF.RED ENGINEERING TESTING REQUI TEST METHOD

40、REQUIREMENTS be free from Specimens shall be cut voids, and oveheating. per Figure 1, etched per Alloy segregation which ASTM E 340 and ASTM E 407 and adversely effects the mechanical or physical examined 3.3. properties is not acceptable. Parts plated per QQ-P-416, MIL-STD-1312-5, WDROGEN iMBRITnEM

41、ENT stress-durabiiity test of each extemal load method. manufacturing lot per the Load shall be maintained loads as stated in QQ-P-416. for 23 hours. :ARBUREATIoN OR )ECARBUREATIoN Metallurgical examination None On head See 3.3. Strip plating and shank fillet area, shank, or solution. Examine at thr

42、eads. All other areas lox to Referee method per Note (c). per TABLE II. Grain size in vicinity of head surface* head to etch in 2% to 5% Nital ;RAIN GROVVTH iEADS or threads shall notdiffer Metallurgical from grain size in shank by more than one size (as See 3.3. Irepresented by FIGURE 2. I IHeads s

43、hall be forged. I ;RAIN FLOW READ defined in ASTM E 112). Grain flow indicative of thread forming subsequent Metallurgical examination to thermal treatment as See 3.3. Grain flow lines may vary depending upon head configuration. However any metallurgical condition which adversely affects the mechani

44、cal moperties of :INISH Metallurgical examination See 3.3. NAS672 cadmium plating is specified in the part standard, the test methods shall be as stated herein. shall be as stated herein. the part is not acceptable. As specified in the part standard. If QQ-P416 or COMPLETELY REVISED Salt spray, adhe

45、sion and plating thickness per QQ-P-416. The referee test method for plating thickness shall be MIL-STD-1312-12, and plating thickness per NAS672. The referee test method for plating thickness shall be MIL-STPI 312-12, EMENTS (SEE 3.1) SAMPLING PIAN ABLE XIV. 2Q-P-416. WS672. I NASM8831 I SHEET 5 US

46、E OF OR RELIANCE ON MIS DOCUMENT OR ANY NATK)NAL AEROSPACE STANDARD IS ENTIRELY VOLUNTARY. AIA WES NOT QUAUM CUPPERS OR CERTIFY CONFORMANCE OF ITEMS PROCURED UNDER wnoNAL AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATIMJ OR CLAIM RESPECTING (1) THE SUITABILITY OF ITEMS FOR ANY PARTEULAR APWCATDN, OR

47、(2) ME EUSIENCE OF OR APPUCABILIV MERETO OF PATENT OR TRADEMARK RIGHTS. FI O O N h rl 9 a . z O - K 8 v O z w I- s s a -I a o. U Copyright Aerospace Industries Association of America Inc. Provided by IHS under license with AIA/NASNot for ResaleNo reproduction or networking permitted without license

48、from IHS-,-/:#:#$#:$*:$#:#Aerospace Industries Association CHARACTERISTICS NATIONAL AEROSPACE STANDARD OOXYRIGHT 2001 A!ZROSPACE IMuSTRIEs ASSOCIATION OF AMERICA INC W RIGHIS RESERVED ENGINEERING REQUIREMENTS Package to prevent nicking, PACKAGING MARKING scratching of threads or - ground surfaces, o

49、r other damage during handling, transportation or storage. Unit packages must contain fasteners of one part number from one manufacturing lot. An assortment of unit packages may be in larger packages. Packaging must allow for economical transportation. Fasteners shall be identified in accordance with the applicable part standard. Shipping pack