NAVY MIL-V-81995-1980 VALVES STARTER CONTROL AIRCRAFT ENGINE GENERAL SPECIFICATION FOR《航空器引擎起动机控制阀的一般技术要求》.pdf

《NAVY MIL-V-81995-1980 VALVES STARTER CONTROL AIRCRAFT ENGINE GENERAL SPECIFICATION FOR《航空器引擎起动机控制阀的一般技术要求》.pdf》由会员分享，可在线阅读，更多相关《NAVY MIL-V-81995-1980 VALVES STARTER CONTROL AIRCRAFT ENGINE GENERAL SPECIFICATION FOR《航空器引擎起动机控制阀的一般技术要求》.pdf（39页珍藏版）》请在麦多课文档分享上搜索。

1、SPECIFICATIONS Federal PPP-T-60 MIL-V-81995(AS) 25 June 1980 MILITARY SPECIFICATION VALVES, STARTER CONTROL, AIRCRAFT ENGINE, GENERAL SPECIFICATION FOR This specification is approved for use by the Naval Air Systems Command, Department of the Navy, and is available for use by all Departments and Age

2、ncies of the Department of Defense. 1. SCOPE 1.1 Scope. This specification covers starter control valves for use with air turbine starters used on aircraft turbine engines. 2. APPLICABLE DOCUMENTS 2.1 Issues of documents. The following documents, of the issues in effect on the date of invitation for

3、 bids or request for proposals, forp a part of this specification to the extent specified herein: PPP-B-585 PPP-B- 601 PPP-B-621 Tape, Pressure Sensitive, Adhesive, Waterproof for Packaging and Sealing Boxes, Wood, Wirewound Boxes, Wood, Cleated-Plywood Boxes, Wood, Nailed and Lock-Co Beneficial com

4、ments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to: Engineering Specifications and Standards Department (Code 93) Naval Air Engineering Center, Lakehurst, NJ 08733, by using the self-addressed Standardization Doc

5、ument Improvement Proposal (DD Form 1426) appearing at the end of this document or by letter. ir US. GDVERNMENT PRINTING OFFICE: 1980-603-121/3008 THIS DOCUMENT CQNTAlMS L“34PAOES, Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SPECIFICATIONS (Conti

6、nued) Mi 1 it ary MIL-P- 11 6 MIL-B-121 Preservation-Packaging, Method of Barrier Material, Greaseproofed, Waterproofed, Flexible _- MIL-C-5015 Connectors, Electrical, Circular Threaded, AN - Type, General Specification for MIL-E-5400 Electronic Equipment, Airborne, General Specification for MIL-C-5

7、501 MIL-C-5541 Caps and Plugs, Protective, Dust and Moisture Seal Chemical Conversion Coatings on Aluminum and Aluminum Alloys MIL-C-6021 MIL-H- 6 O 8 8 MIL-H-6875 MIL-P-7 105 MIL-F-7179 Castfngs, Classification and Inspection of Heat Treatment of Aluminum Alloys Heat Treatment of Steels (Aircraft P

8、ractice), Process for Plpe Threads, Taper, Aeronautical National Form, Symbol ANPT, General Requirements for Finishings and Coatings; Protection of Aerospace Weapons Systems, Structures and Parts; General Specification for MIL-S-7742 Screw Threads, Standard, Optimum Selected Series; General Specific

9、ation for MIL-A-8625 MIL-S-8879 Anodic Coatings, for Aluminum and Aluminum Alloys Screw Threads, Controlled Radius Root with Increased Minor Diameter, General Specification for MIL-P- 9400 Plastic Laminate and Sandwich Construction Parts, Aircraft Structural, Process Specification Re qu ir-emen t s

10、2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-V-81995 29 W 979990b 0205402 9 W SPECIFICATIONS (Continued) - Mili t ay- (Continued) MIL-C- 1 1 7 9 6 Corrosion Preventative, Petrolatum, Hot Application MIL-C- 16 17 3 Corrosion Preventative Comp

11、ound, Solvent Cutback, Cold Application Aluminum Alloy Castings, High Strength MIL-A- 2 1 1 8 O MIL- G- 2 1 4 8 O Generator System, 400 Hertz Alternating Current, Aircraft , General Specification for MIL-E-25499 Electrical System, Aircraft, Design and Installation of, General Speciftcation for MIL-V

12、-81995fl Valve, Starter Control, Aircraft Engine, For T56 Engine MIL-V-8199512 Valve, Starter Control,.AIrcraft Engine, For TF30 Englne MIL-V-8199513 Valve, Starter Control, Aircraft Engine, For 552 Engine MIL-V-81995/4 Valve, Starter Control, Aircraft Engine, For TF 34 Engine STANDARDS Federal _- F

13、ED-STD-595 Mllitary - MIL-STD-100 MIL- S TD- 1 2 9 Colors Engineering Drawing Practices Marking of Shipments MIL-S TD-13 O MIL-S TD-454 MIL-STD-470 Identification Marking of U.S. Military Property Standard General Requirements for Electronic Equipment Ma in t ainab ili t y Pro gram Requirements ( fo

14、r Systems and Equipments) Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AMERICAN NATIONAL STANDARDS INSTITUTE (ANSI) B46.1-1962 Surface Texture (Appli

15、cation for copies should be addressed to the American Standards Institute, 1430 Broadway, New York, NY 10018.) 3. REQUIREMENTS s- 3.1 Specification sheets. The individual item requirements shall be as specified herein and in accordance with the applicable Specification sheets. of this specification

16、and the specification sheet, the latter shall govern. In the event of any conflict between requirements . 3.l. 1 Precedence. The contract shall have precedence over any specification. compliance with this specification or from subsidiary specifications or standards, for a qualified valve, are subjec

17、t to approval in writing by the qualifying activity (see 3.11.3). Any design or construction change that may effect 3.2 Qualification. The valve furnished under this specification shall be a product which has been qualified for listing on the applicable Qualified Products List at the time set for op

18、ening of sions shown on the specification sheet. Where only maximum or minimum dimensions are shown, the part need not have the shape shown, but the part, including all protrusions, shall be contained within the outline shown. are shown as examples and for information only; such details are optional

19、. Design details which are shown but are not specifically required 3.4 Data. Unless otherwise specified in the contract, data cited in this specification is only required as part of the qualifica- tion submittal. 3.5 Materials and parts. Materials arid parts used in construction of the valve shall b

20、e unaffected by aircraft engine oil while the valve is operating under any of the specified conditions. Materials, parts, and processes shall conform to applicable Government s,pecifications listed in MIL-BULL-544. may be used for materials or processes not covered by the documents listed in MIL-BUL

21、L-544, provided the specifications are approved by the qualifying activity and contain provisions for adequate kests. Contractor or industry specifications 3.5.1 Materials. 3.5.1.1 Toxic products. Materials which are toxic in themselves, or which become toxic when pulverized or vaporized, or which h

22、ave toxic Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3.5.1.2 Non-metals. Non-metallic materials used, including plastics, fabrics, and protective finishes shall be flame-resistant, shall not support combustion, shall be moisture resistant, and s

23、hall not be adversely affected by weather, temperature, and ambient conditions. 3.5.1.2.1 Fungus resistance. Materials that are nutrients for fungi shall not be used where it is practical to avoid them. Where used, all nutrient materials and associated fungicidal treatments used shall be specified o

24、n the valve manufacturing drawings. 3.5.1.2.2 Elastomers. Elastomeric components shall be fabricated from materials covered by applicable specifications and shall have maximum practicable ozone and aging resistance and hydrolytic stability consistent with performance requirements. All elastomeric ma

25、terials used shall be subject to the specific approval of the qualifying activity based upon the demonstrated suitability of the materials for the expected operating and storage environments. Age controls for synthetic rubber parts shall be in accordance with MIL-STD-1523. 3.5.1.3 Metals. All metals

26、 shall be compatible with the intended temperature, functional, service and storage conditions to which the valve will be exposed. corrosion by lubricating oil shall be of the corrosion-resisting type, or shall be suitably treated to resist corrosion in accordance with 3.5.1.4. Metals which are not

27、protected from 3.5.1.3.1 Steels (except corrosion-resistant). a. Aircraft quality, vacuum-melted steel shall be used for parts which are heat treated to an ultimate tensile strength 220,000 psi and above. approval by the qualifying activity. Such applications shall be subject to specific b. The ulti

28、mate tensile strength range in production parts shall not exceed the following limits: Minimum Ultimate Tensile Strength, P.S.I. Permissible Variation, P.S.1 220,000 260,000 270,000 280,000 6 -0 + 20,000 -0 + 20,000 -0 + 20,000 -0 + 20,000 Provided by IHSNot for ResaleNo reproduction or networking p

29、ermitted without license from IHS-,-,-carbon and low alloy steels, to compositions having the least hardenability which will insure through-hardening of the part concerned. d. Compositions shall be selected such that heat treatment to the required strength and service temperatures shall preclude tem

30、per embrittlement. i e. Steels shall be selected having ductile-brittle fracture transition temperatures as determined by impact test below the minimum operating temperature. . f. Steels whose mechanical properties are developed by cold deformation shall be so selected that the recovery temperature

31、will be at least 50F (lOC) above the maximum operating temperature range. g. Critical parts shall be designed and processed so as to result in no decarburization of highly stressed areas. Designs shall preclude use of as-forged surfaces unless specific approval is obtained from the qualifying activi

32、ty. h. The mechanical drilling of holes in martensitic steels after hardening to strength levels of 180,000 psi and above shall i. Any necessary straightening of parts afer heat treatment to strength levels of 180,000 psi and above shall be accomplished at the tempering temperature, plus OOF (-18OC)

33、 minus 500F (lOC), or the parts shall receive a st-ress-relieving treatment at this temperature immediately after straightening. Parts shall be inspected for cracks after straightening. j. Free-machining grades of steel shall be subject 9 to approval by the qualifying activity. 3.5.1.3.2 Corrosion-r

34、esistant steels. The following limitations shall be observed in the selection and application of corrosion resistant steels. a. Unstabilized austenitic steels shall not be fusion welded. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-b. Precipitatio

35、n hardening semi-austenitic grades shall not be used in applications which require extended exposure to temperatures in the 750 -900F (399 -482OC) range. c. The use of heat treated 431 or 19-9DL steel shall be subject to approval by the qualifying activity. d. The use of 17-4PH stainless steel aged

36、below H1025 shall be subject to approval by the qualifying activity. 3.5.1.3.3 Magnesium alloy. Magnesium or its alloy shall not be used. 3.5.1.3.4 Castings. Castings shall be in accordance with MIL- - C-6021 and shall be classified Class lB, grade C or higher. Aluminum alloy castings shall be in ac

37、cordance with MIL-A-21180. Defects not materially affecting the suitability of the castings may be repaired at the foundry or during machining by peening, impregnation, welding, or other methos acceptable to the procuring activity. Inspection of repaired castings shall be governed by quality control

38、 techniques subject to the approval of the qualifying activity. 35.1.3.5 Stress corrosion embrittlement factors. To prevent premature failures caused by stress corrosion or hydrogen embrittlement, the design and method of manufacture of parts of titanium and steel heat-treated to tensile strengths a

39、bove 220,000 psi or of bare high strength aluminum alloys and the techniques by which they are assembled and installed shall be such that sustained or residual surface tensile stresses and stress concentrations are minimized. Practices, such as: the use of press or shrink fits; taper pins, clevis jo

40、ints in which tightening of the bolt imposes a bending load on the female lugs; and straightening or assembly operations; which result in sustained or residual surface tensile stresses shall be avoided. In cases where such practices cannot be avoided, corrective practices such as stress relief heat

41、treatment, optimum grain flow orientation, peening (shot or rotary flat) or similar surface working shall be used to minimize the hazard of stress corrosion or hydrogen embrittlement damage. In no case shall sustained or residual surface tensile stresses in these materials exceed Provided by IHSNot

42、for ResaleNo reproduction or networking permitted without license from IHS-,-,-alloy, such stresses may be as high at 75% of the minimum yield strength in any grain flow direction. These limits for stresses represent the algebraic sum of all the continuous tension and compression surface stresses re

43、sulting from any source such as quenching, forming and assembly. The use of cadmium in contact with or plated on titanium shall not be permitted. 3.5.1.3.6 Fatigue factors. To prevent premature failures caused by repeated loads, the design and method of manufacture, including consideration of the da

44、maging effect of decarburization and certain metallic coatings, of all critical parts and the techniques by which they are assembled and installed shall be such that sustained or residual e tensile stresses and stress concentrations are minimized. Practices such as cold straightening, cold forming,

45、and the assembly of mismatched surfaces, which result in sustained or residual surface tensile stresses shall be avoided. In cases where such practices cannot be avoided, corrective practices such as stress relief heat treatment, optimum gain flow orientation, peening (shot or rotary flat) or simila

46、r surface working shall be used to minimize premature fatigue failure. In no case shall parts of nonuniform section be cold formed unless the contractor can demonstrate with test results that required fatigue resistance is obtained . fatigue life of the parts in the planned operating environment. ro

47、ughness limits and limiting criteria for allowable flaws shall be established for approval by the qualifying activity. Alternately the surface roughness shall not exceed 63 RHS and there shall be no flaws such as tool marks deeper than 0,0002 inch. Such limits for parts critical in low cycle fatigue

48、 shall be separately identified. Surface 3.5.1.3.7 Heat treatment. Heat treatment of aluminum alloys shall be in accordance with the material specification and MIL-H-6088. Steels shall be heat treated in accordance with the material specification and MIL-H-6875. Precautions shall be taken to minimiz

49、e warpage during heat treatment. to 200,000 psi or below may be cold straightened provided a stress relieving heat treatment is subsequently applied. Steel parts which require straightening after hardening , O Straightening of parts hardened to tensile strengths above 200,000 psi shall b (b) a mating plug for each electric connector, used on each of the three units; (c) the test report described in 4.2.6; (d)