1、I INCH-POUND I NOTE: MIL-STD-l587C(USAF) has been redesignated as MIL-HDBK-I587(USAF) A handbook, and is to be used for guidance purposes only. 18 July 1996 This document is no longer to be cited as a requirement. For SUPERSEDING administrative expediency, the only physical change from MIL-STD-l587C
2、(USAF) MlL-STD-l587C(USAF) is this cover page. However, this 21 July 1992 document is no longer to be cited as a requirement. If cited as a requirement,contractors may disregard the requirements of this document and interpret its contents only as guidance. MILITARY HANDBOOK MATERIALS AND PROCESS REQ
3、UIREMENTS FOR AIR FORCE WEAPON SYSTEM AMSC NIA AREA MFFP DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-HDBK-L587 9979970 02bb277 hBT M m-sm- 1587C(USAF) FOREWORD
4、1. “us military standard is approved for use by all Departments and Agencies of the Department of Defense. 2. Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving ths document should be addressed to: WL/MLSA, Materials Directorate, Wrigh
5、t-Patterson AFB OH 45433-6533, by using the self-addressed Standardization Document Improvement Proposal (DD Form 1426) appeanng at the end of hs document or by letter. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-HDBK-L5B7 M 9999970 02bb278 5
6、Lb CONTENTS PARAGRAPH PAGE 1 . SCOPE . 1 1.1 1.2 Scope . 1 Applicability . 1 2 . REFERENCED DOCUMENTS . 2 2.1 Government documents 2 2.1.1 Specifications. standards. and handbooks 2 2.1.2 Other Government documents and publications 5 2.2 Otherpublications 6 2.3 Orderofprecedence . 7 3 . DEFINITIONS
7、8 3.1 Denitions . 8 4 . GENERAL REQUIREMENTS 9 4.1 4.2 4.3 4.4 4.5 Material selection . 9 Restricted materials . 9 Material propertiedfracture mechanics . 9 Disclosure of materials . 9 Contractor prepared specifications . 9 5 . DETAILED REQUIREMENTS 11 5.1 5.1.1 5.1.2 5.1.2.1 5.1.2.2 5.1.3 6.1.3.1 6
8、.1.3.2 6.1.3.3 6.1.3.4 5.1.3.5 5.1.3.6 6.1.3.7 5.1.3.8 Metals . 11 Minimum thicknesses . 11 Aluminum 12 Heattreatment 12 Forming and straightening 12 Steel . 12 Heat treatment 12 Shotpeening 12 Hardenability . 12 Forming or straightening of steel parts . 14 Decarburization . 14 Carburization . 14 Dr
9、illing of high strength steels . 14 Grinding of high strength steel . 15 iii Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-“Sm-1 587C(USAF) CONTENTS PARAGRAPH 5.1.3.9 5.1.3.9.1 5.1.3.9.2 5.1.4 5.1.4.1 5.1 -4.2 5.1.4.3 5.1.4.4 5.1.5 5.1.6 5.2 5.2.1
10、5.2.1.1 5.2.1.2 5.2.1.3 5.2.1.4 5.2.1.4.1 5.2.1.4.2 5.2.1.4.2.1 5.2.1.4.2.2 5.2.1.4.2.3 5.2.1.4.2.4 5.2.1.4.3 5.2.1.4.3.1 5.2.1.4.3.2 5.2.1.4.4 5.2.1.4.5 5.2.1.4.6 6.2.2 5.2.2.1 5.2.2.1.1 5.2.2.1.2 5.2.2.1.3 5.2.2.2 5.2.2.3 5.2.2.4 5.2.2.5 5.2.3 5.2.4 5.2.4.1 5.2.5 PAGE Corrosion resistant steels 15
11、 Austenitic stainless steels . 15 Precipitation hardening stainless steels 15 Titanium . 15 Forgin g3 15 Sheetandplate 15 Extrusions 15 Heattreatment 15 Beryllium . 15 Othermetals 15 Nonmetallic materials 16 Composites . 16 Organicresins . 16 Metal matrices 16 Conventional composites 16 Advanced com
12、posites . 16 Material property design allowables . 17 Specifications . 17 Material acquisition specification . 17 Material qualification specification 17 Process specification 17 Product fabrication specification 18 Joining and fastening . 18 Thermalexpansion . 18 Galvanic corrosion . 19 Repairabili
13、ty 19 Supportability . 19 ElectricaUelectromagnetic behavior 19 Elastomeric materials . 19 General requirements . 19 Cured elastomers 19 Noncured elastomers . 20 Silicone elastomers . 20 O-rings 20 Other molded parts, sheets, strips, and extruded shapes 21 Potting compounds . 21 Integral fuel tank s
14、ealing 21 Foamed plastics . 21 Flexible and semiflexible materials for manned airCr Flash, Carbon and Alloy Steel Forging, Steel, for AircrxWAerospace Equipment and Special Ordnance Applications Rubber, Synthetic, Solid, Sheet, Strip and Fabricated Parts, Synthetic Oil Resistant Core Material, Alumi
15、num, for Sandwich Construction Brazing of Steels, Copper, Copper Alloys, Nickel Alloys, Aluminum and Aluminum Alloys Core Material, P1asti.c Honeycomb, Laminated Glass Fabric Base, for Aircraft Structural and Electronic Applications Core Material, Foamed-in-Place, Urethane Type Sealing Compound, Pol
16、ysulfide Rubber, Electric Connectors and Electric Systems, Chemically Cured Sealing Compound, TemperatureResistant Integral Fuel Tanks and Fuel Cell Cavities, High-Adhesion Sandwich Construction; Plastic Resin, Glass Fabric Base, Laminated Facings and Honeycomb Core for Aircraft Structural and Elect
17、ronic Applications 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-HDBK-LSB7 - 9997770 0266284 BLT E MIL-T-9046 MIL-T-9047 MIGS-13165 “1-16923 “A-211 80 MIL-A-22771 MIGS-23586 MIL-M-24041 “S-25392 MIL-P-25732 MEL-R-25988 MIL-R-259884 MIGR-2598
18、8/2 MIGR-25988/3 MIGR-25988/4 MIM-27725 MIGA-46106 MIL-A-46146 1ML-US231 MIL-H41 200 MIL-1-81 550 MILT-81 5 5 6 “S-81732 MIL-F43142 “83248 MJLR-83248/1 MIL-R-8324812 “83285 MIL-STD-l587C(USAF) Titanium and Titanium Alloy, Sheet, Strip, and Plate Titanium and Titanium Alloy Bars (Rolled or Forged) an
19、d Reforging Stock, Aircraft Quality Shot Peening of Metal Parts Insulating Compound, Electrical, Embedding Aluminum-Alloy Castings, High Strength Aluminum Alloy Forgings, Heat Treated Sealing Compound, Electrical, Silicone Rubber, Accelerator Required Molding and Potting Compound, Chemically Cured,
20、Polyurethane Sandwich Construction, Plastic Resin, Glass Fabric Base, Laminated Facings and Urethane Foamed-in-Place Core, for Structural Applications Packing, Preformed, Petroleum Hydraulic Fluid Resistant, Limited Service at 275 F (132“ C) Rubber, Fluorosilicone Elastomer Oil- and Fuel-Resistant,
21、Sheets, Strips, Molded Parts, and Extruded Shapes Rubber, Fluorosilicone Elastomer, Oil- and Fuel-Resistant, O-Rings, Class 1, Grade 70 Rubber, Fluorosilicone Elastomer, Oil- and Fuel-Resistant, O-Rings, Class 3 Rubber, Fluorosilicone Elastomer, Oil- and Fuel-Resistant, O-Rings, Class 1, Grade 60 Ru
22、bber, Fluorosilicone Elastomer, Oil- and Fuel-Resistant, O-Rings, Class 1, Grade 80 Coating, Corrosion Preventive, for Aircraft Integral Fuel Tanks Adhesivesealants, Silicone, RTV, One Component AdhesivesSealants, Silicone, RTV, Noncorrosive (for Use with Sensitive Metals and Equipment) Electrical C
23、omponents, Potting of Heat Treatment of Titanium and Titanium Alloys Insulating Compound, Electrical, Embedding, Reversion Resistant Silicone Titanium and Titanium Alloys, Extruded Bars and Shapes, Aircraft Quality Sealing Compound, Electrical High Strength, Accelerator Required Forging, Titanium Al
24、loys, Premium Quality Rubber, Fluorocarbon Elastomer, High Temperature, Fluid, and Compression Set Resistant Rubber, Fluorocarbon Elastomer, High Temperature, Fluid, and Compression Set Resistant (O-Rings, Class 1,75 Hardness) Rubber, Fluorocarbon Elastomer, High Temperature, Fluid, and Compression
25、Set Resistant (O-Rings, Class 2, 90 Hardness) Rubber, Ethylene-Propylene General Puzpose 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-HDBK-3587 7999970 02bb285 75b = “83377 “83397 MILS-83430 MIL-P433461 “83461/1 “83483 MIL-R43485 AFGS-87221
26、“87244 STANDARDS FEDERAL FED-STD-191 MILITARY “STD-129 MIhsTD-454 “STD-810 “STD-838 “STD-866 “STD-889 “D-970 “STD-1523 “STD-1530 “STD-1568 MIL“)-1 595 “STD-1 783 MIGSTD-17 98 “STD-1807 “STD-2000 “D-21 75 “STD-2219 MS28775 Adhesive Bonding (Structural) for Aerospace and Other Systems, Requirements fo
27、r Rubber, Polyurethane, Castable, Humidity Resistant Sealing Compound, Integral Fuel Tanks and Fuel Cell Cavities, Intermittent Use to 360 OF Packings, Preformed, Petroleum Hydraulic Fluid Resistant, Improved Performance at 276 “F (135 “C) Packing, Preformed, Petroleum Hydraulic Fluid Resistant Impr
28、oved Performance at 275 “F (135 “C) Sizes and Tolerances Thread Compound, Antiseize, Molybdenum DisulfidePetrolatum Rubber, Fluorocarbon Elastomer, Improved Performance at Low Temperatures Aircraft Structures, General Specification for Avionifllectronic Integrity Program Requirements (AVIP) Textile
29、Test Methods Marking for Shipment and Storage Standard General Requirements for Electronic Equipment Environmental Test Methods and Engineering Guidelines Lubrication of Military Equipment Grinding of Chrome Plated Steel and Steel Parts Heat Treated to 180,000 psi or Over Dissimilar Metals Standards
30、 and Specifications, Order of Preference for the Selection of Age Controls of Age-Sensitive Elastomeric Material (for Aerospace Applications) Aircraft Structural Integrity Program, Airplane Requirements Materials and Processes for Corrosion Prevention and Control in Aerospace Weapons Systems Qualaca
31、tion of Aircraft, Missile and Aerospace Fusion Welders Engine Structural Integrity Program (ENSIP) Mechanical Equipment and Subsystems Integrity Program Crash Survivability of Aircraft Personnel Standard Requirements for Soldered Electrical and Electronic Assemblies Castings, ClassScation and Inspec
32、tion of Fusion Welding for Aerospace Applications Packing, Preformed, Hydraulic, +275 “F ( inaccessible areas of holes; pneumatic or hydraulic seat contact areas; and thin sections or parts which, after shot peening, violate engineering and functional configuration. Areas requiring lapped, honed, or
33、 polished surfaces shall be shot peened prior to such finishing. Surface removal of up to 0.0038 cm (0.0015 inches) based on pre-shot peened dimensions shall be permissible. 5.1.3.3 Hardenability. Hardenability shall be sufficient to ensure transformation during quenching to not less than 90 percent
34、 martensite at the center of the maximum cross section. 12 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-HDBK-1587 7799970 02bb294 7b7 1414 mm O0 lo* O0 14* I -U 1 A I ! l , I i I I l I m al N rn .- 2 L Li al 5 4 O a h m rl * e 10 O hl r 5 a n
35、o bo C 13 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-5.1.3.4 Forming or straightening of steel parts. All reasonable precautions shall be taken to minimize warping during heat treatment of steel parts. ND1 shall be performed on parts after room
36、temperature straightening. Steel parts shall be formed or straightened unless otherwise noted in accordance with the following: a. Parts hardened up to 165 ksi (1138 MPa) UTS may be room temperature straightened. b. Parts hardened from 165 to 200 ksi (1138 to 1379 MPa) may be straightened at room te
37、mperature providing they are given a stress relieving heat treatment subsequent to straightening. c. Parts hardened over 200 ksi (1379 MPa) UTS shall be hot formed or straightened within a temperature range from the tempering temperature to 128 “C (50 “F) below the tempering temperature. 5.1.3.5 Dec
38、arburization. Unless otherwise specifed, completed decarburization shall not be present in a finished machined surface. On steels heat treated below 200 ksi (1379 MPa) UTS partial decarburization to a maximum depth of 0.0127 cm (0.005 inches) may be present. On steels heat treated above 200 ksi (137
39、9 MPa) UTS, partial decarburization to a maximum depth of 0.0076 cm (0.003 inches) may be present. The difference in hardness from the surface to any point below the surface shall not exceed 30 points Knoop microhardness or equivalent. 5.1.3.6 Carburization. Minimum carburization of fully hardened s
40、teel parts shall be a prime objective. Furnace atmospheres which increase the carbon content of surface zones above the maximum for the respective composition are not acceptable. Surface of steel parts shall show no evidence of carbon increase as a result of heat treating. 5.1.3.7 Drilling of high s
41、trength steels. The drilling of holes, including chamfering and spot facing, in martensitic steels subsequent to hardening to strength levels of 180 ksi (1241 MPa) UTS and above shall be avoided whenever practicable. When such drilling and reaming is unavoidable because of manufacturing sequence, to
42、oling and techniques necessary to avoid formation of any untempered martensite shall be used. Al1 holes, straight or tapered, shall be reamed with sharp, carbide reamers having a sufficient number of flutes to avoid chattering. The documents controlling such techniques shall specify a final sizing p
43、ass with minimum radial loads, speed and feed rates, coolant flow rates, tool life limits, inspection techniques, and other requirements necessary to assure the production of holes of high quality, smooth bore surfaces, and free from “hard spots“ and microcracks. Tooling and processes used shall be
44、qualified by demonstration. Microhardness and metallurgical examinations of test specimens shall be used to determine the depth of disturbed metal and possible untempered martensitic areas resulting from drilling. The surface roughness of the finished hole, including any countersink or spot faced su
45、rfaces, shall not be greater than RHR 63. Both ends of the holes shall be deburred by a method which has been demonstrated not to cause untempered martensite except where the materials stackups or assemblies preclude accessibility of both ends of the holes in each layer of the stackups. Cobalt high
46、speed steel or carbide reamers shall be used in steel heat treated at 200-260 ksi (1517-1793 MPa) WS. Carbide reamers shall be used in steel heat treated to 260 ksi (1793 MPa) UTS and above. For tapered holes, reamers having not less than 12 flutes shall be used. 14 Provided by IHSNot for ResaleNo r
47、eproduction or networking permitted without license from IHS-,-,-5.1.3.8 Grinding of high strength steel. Grinding of martensitic steels hardened to 180 ksi (1241 MPa) UTS and above shd be performed in accordance with “Sm-866. Grinding of chromium plated martensitic steels hardened to 180 ksi (1241
48、MPa) UTS and above shall also be performed in accordance with “STD-866. 5.1.3.9 Corrosion resistant steels 5.1.3.9.1 Austenitic stainless steels. Free machining stainless steels intended for fatigue critical applications shall be avoided. Sulfur or selenium additions improve machinability but lower
49、fatigue life. 5.1.3.9.2 Precipitation hardening stainless steels. These steels shall be aged at temperatures not less than 538 “C (1000 “F). Exception is made for castings which may be aged at 501.5 * 9.4 “C (935 f 15 “F), for fasteners whch may be used in the H950 condition, and for springs which have optimum properties at the CH 900 condition. H950 is not permitted for 17-4 PH or 15-5 PH alloys. 5.1.4 Titanium 5.1.4.1 Forg
