NAVY MIL-S-85419-1981 STARTER AUXILIARY POWER UNIT AIRCRAFT ENGINE GAS TURBINE TYPE DETAILED SPECIFICATION FOR《燃气轮机类航空发动机起动 辅助动力装置的详细规格》.pdf

《NAVY MIL-S-85419-1981 STARTER AUXILIARY POWER UNIT AIRCRAFT ENGINE GAS TURBINE TYPE DETAILED SPECIFICATION FOR《燃气轮机类航空发动机起动 辅助动力装置的详细规格》.pdf》由会员分享，可在线阅读，更多相关《NAVY MIL-S-85419-1981 STARTER AUXILIARY POWER UNIT AIRCRAFT ENGINE GAS TURBINE TYPE DETAILED SPECIFICATION FOR《燃气轮机类航空发动机起动 辅助动力装置的详细规格》.pdf（82页珍藏版）》请在麦多课文档分享上搜索。

1、MIL-S-85419 (AS) 1 October 1981 MILITARY SPECIFICATION STARTER/AUXILIARY POWER UNIT, AIRCRAFT ENGINE, GAS TURBINE TYPE, DETAILED 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 Agencies

2、 of the Department of Defense. 1. SCOPE This specification covers a gas turbine starter/APU for starting the main aircraft engine and providing emergency electrical power on the AV-8B aircraft. establishes the content and format to be used by the supplier for the preparation of the gas turbine start

3、er/APU model specification. 2. APPLICABLE DOCUMENTS This specification also 2.1 Issues of Documents. The following documents, of the issues in effect on the date of invitation for bids or request for proposals, are a part of this specification to the extent specified herein: SPECIFICATIONS Federal P

4、PP-B-585 Boxes, Wood Shipment) Wirewound (For Domestic PPP-B-601 Boxes, Wood, Cleated-Plywood Beneficial comments (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

5、(Code 93) Naval Air Engineering Center, Lakehurst, NJ 08733, by using the self-addressed Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this document or by letter. L I i Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IH

6、S-,-,-MIL-S-85419 (AS) 2 PPP-B-621 PPP-T-60 Mi 1 i tarv MIL-P-116 MIL-B-121 MIL-En5400 MIL-C-5501 MIL-C-5541 MIL-T-5624 MIL-C-6021 MIL-H-6088 MIL-1-6866 MIL-H-6875 MIL-P-7105 MIL-F-7179 MIL-S-7742 MIL-L-7808G MIL-A-8625 MIL-S-8879 Boxes, Wood, Nailed and Lock-Corner Packaging, Waterproof Preservatio

7、n, Packaging, Method of Barrier Material, Greaseproofed, Waterproofed, Flexible Electronic Equipment, Airborne, General Specification for Caps and Plugs, Protective, Dust and Moisture Seal Chemical Conversion Coatings on Aluminum and Aluminum Alloys Turbine Fuel, Aviation Grades JP-4 and JP-5 Castin

8、g, Classification and Inspection of Heat Treatment of Aluminum Alloys Inspection, Pentrant Method of Heat Treatment of Steels (Aircraft Practice), Process or Pipe Threads, Taper, Aeronautical National Form, Symbol AMPT, General Requirements for Firiishes and Coatings; Protection of Aerospace Weapons

9、 Systems, Structures and Parts Screw Threads, Standard, Optimum Selected Series, General Specification for Lubricating Oil, Aircraft Turbine Engine, Synthetic Base Anodic Coatings, for Aluminum and Aluminum Alloys Screw Threads, Controlled Radius Root with Increased Minor Diameter, General Specifica

10、tion for Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-S-5417 27 = 7777706 0206639 6 a t a a MIL-P-9400 MIL-C-11796 . MIL-C-16173 MIL-A-21 180 MIL-L-23699 MIL-E-25499 MIL-C-38999 STANDARDS Mi 1 i tarv DOD-STD-1 O0 MIL-STD-129 MIL-STD-130 MIL-ST

11、D-453 MIL-STD-454 MIL-STD-461 M IL-STD-4 6 2 MIL-STD-470 DOD-STD-480 MIL-S-85419 (AS) Plastic Laminate and Sandwich Construction, Aircraft Structural Process Parts Specification Requirements Corrosion Preventative Compound, Petrolatum, Hot Application Corrosion Preventative Compound, Solvent Cutback

12、, Cold Application Aluminum Alloy Castings, High Strength Lubricating Oil, Aircraft Turbine Engines, Synthetic Base Electrical System, Aircraft, Design and Installation of, General Specification for Connectors, Electrical, Circular, Miniature, High Density, Quick Disconnect, Environment Resistant, R

13、emovable Crimp Contacts Engineering Drawing Practices Marking for Shipment and Storage Identification Marking of U.S. Military Property Inspection, Radiographic Standard General Requirements for Electronic Equ ipmen t Electromagnet i c Interference Character ist ics Requirements for Equipment Electr

14、omagnetic Interference Characteristics, Measurement of Maintainability Program Requirements (For Systems and Equipment) 5 Configuration Control, Engineering Changes, Deviations and Waivers 3 i Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-S-854

15、19- (AS) MIL-STD-704 MIL-STD-721 MIL-STD-785 MIL-STD-810 MIL-STD-831 MIL-STD-889 MIL-STD-1523 MIL-STD-2076 MIL-STD-2077 MS33666 MS3 3 66 8 Aircraft Electric Power, Characteristics Definition of Effectiveness Terms for Reliability, Maintainability, Human Factors, and Safety Reliability Program for Sy

16、stems and Equipment Development and Production Environmental Test Method Test Reports, Preparation of Dissimilar Metals Age Control of Age Sensitive Elastomeric Mater i al Unit Under Test Compatibility With Automatic Test Equipment; General Requirements For Test Program Sets; General Requirements Fo

17、r Packing, Preformed - Aeronautical, Elastomeric, Range of Sizes Packing, Preformed - Tube, Fitting Elastomeric, Range of Sizes PUBLICATIONS (Air Force-Navy Aeronautical Bulletins) MIL-BULL-343 MIL-BULL-544 List of Specifications and Standards (Book Documents Applicable to Aircraft Engines and Prope

18、llers - Use of Form) Approved by the Naval Air Systems Command PUBLICATIONS (NAVAIR Requirements) AR-1 o Maintainability of Avionics Requirements and Systems, General Requirements for (When requesting applicable documents, refer to both title and number, from the Commanding Officer, Naval Publicatio

19、ns and Forms Center, 5801 Tabor Avenue, Philadelphia, Pennsylvania 19120. Request for copies of classified documents should be addressed to the Naval representative,) Copies of unclassified documents may be obtained . Publications and Forms Center, via the cognizant Government 4 Provided by IHSNot f

20、or ResaleNo reproduction or networking permitted without license from IHS-,-,-a 1 a a MIL-S-85419 (AS) 2.2 Other Publications. The following documents form a part of this mecification to the extent specified herein, Unless otherwise indicated, the issue in effect on date of invitation for bids or re

21、quest for proposal shall apply. AMERICAN NATIONAL STANDARDS INSTITUTE (ANSI) B46; 1-1962 Surface Texture (Application for copies should be addressed to the American Standards Institute, 1430 Broadway, New York, NY 10018.) SOCIETY OF BRITISH AEROSPACE COMPANIES, LTD. RS263 Accessory Drives and Mounti

22、ng Pads (Taper Flange and Involute Splines 1 (Application for copies should be addressed to the Society of British Aerospace Companies, LTD., Technical Section, 29 King Street, London SW1Y 6RD, England, U.K.) 3. REQUIREMENTS 3.1 Precedence. The contract shall have precedence over any mecification. A

23、ny deviation from this specification or from sbsidiary specifications or standards, where applicable, is subject to approval in writing by the procuring activity. 3.2 First Article. The parts furnished under this specification shall be a product which has been inspected and passed the first article

24、inspection specified herein (see 4.2). The Naval Air Propulsion Center (PE611, Trenton, New Jersey 08628, is the activity responsible for approving equipment submitted under this specification. 3.3 Dimensions. The aircraft engine gas turbine starter/APU components defined in 3.6.3 shall conform to t

25、he dimensions shown in Figures 1A through 9. Where only maximum or minimum dimensions are shown, the starter need not have the shape shown, but the starter, including all protrusions, shall be contained within the outline shown. not specifically required are shown as exemples and for information onl

26、y; such details are optional. Design details which are shown but are 3.4 Data. Unless otherwise specified in the contract, data cited in this specification is only required as part of the first article submittal. 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license

27、from IHS-,-,-MIL-S-85419 (AS) 3.4.1 Model Specification. A model specif ication in accordance with 6.3 shall be prepared by the supplier and submitted to NAVAIR (AIR-536) for approval. 0 3.5 Materials and Parts. The limitations and restrictions placed on the use of materials and components by MIL-BU

28、LL-544 shall pertain. Materials, parts, and processes shall conform to applicable Government specifications listed in MIL-BULL-544. Contractor or industry specifications may be used for materials or procesces not listed in MIL-BULL-544, provided the specifications are approved by the approving activ

29、ity and contain provisions or adequate tests. . 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 have toxic products of combustion, shall be used only upon written permission of the approving activity. 3,5,

30、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 shall not be adversely affected by weather, temperature, and ambient conditions. where it is practical to avoid t

31、hem. Where used, all nutrient materials and associated fungicidal treatments used shall be specified on the starter/APU manufacturing drawings. covered by applicable specifications and shall have maximum practicable ozone and aging resistance and hydrolytic stability consistent with performance requ

32、irements. All elastomeric materials used shall be subject to the specific acceptance by approving 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 Materials that are n

33、utrients for fungi shall not be used Elastomeric components shall be fabricated from materials with MIL-STD-1523. O Process specifications for adhesive-bonded construction including reinforced plastic, sandwich, and foamed-in-place core construction shall be prepared in accordance with MIL-P-9400. A

34、ll sandwich construction shall be sealed or otherwise designed . to preclude entrance or entrapment of water and other contaminants. Perforated metallic core shall not be used. When metallic core is used, it shall be corrosion resistant, ,. 6 Provided by IHSNot for ResaleNo reproduction or networkin

35、g permitted without license from IHS-,-,-MIL-S-85427 27 W 7777706 0206623 B W MIL-S-85419 (AS) All reinforced plastic constructign shall be in conformance with the contractors process specifications, prepared in accordance with MIL-P-9400 and accepted by the approving activity. 3.5.1.3 Metals. All m

36、etals shall be compatible with the intended temperature, functional, service and storage conditions to which the starter/APU will be exposed. Metals which are not protected from corrosion by lubricating oil shall be of the corrosion-resisting type, or shall be suitably treated to resist corrosion in

37、 accordance with 3.5.1.4, 3.5.1.3.1 Steels (except corrosion-resistant). parts which are heat treated to an ultimate tensile strength 220,000 psi and above. specific acceptance by the approving activity. shall not exceed the fallowing limits: a. Aircraft quality, vacuum-melted steel shall be used fo

38、r Such applications shall be subject to b, The ultimate tensile strength range in production parts Minimum Ultimate Tensile Strength - P.S.I. 220,000 260,000 270,000 280,000 Permissible Variation, P.S.1. -0 + 20,000 -0 + 20,000 -0 + 20,000 -0 + 20,000 c. Preference shall be given, in se ection of ca

39、rbon and low alloy steels, to compositions having the least hardenability which will insure thorough-hardening of the part concerned. to the required strength and service temperatures shall preclude temper embrittlement. e. Steels shall be selected having ductile-brittle fracture transition temperat

40、ures as determined by impact test below the minimum operating temperature. deformation shall be so selected that the recovery temperature will be at least 500F (28OC) above the expected operating temperature range. Critical parts shall be designed and processed so as to result in no decarburization

41、of highly .stressed areas. Designs d. Compositions shall be selected such that heat treatment f. Steels whose mechanical properties are developed by cold . g. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-S-85419 (AS) shall preclude use of as-f

42、orged surfaces unless specific acceptance is obtained from the approving activity. h, The mechanical drilling of holes in martensitic steels after hardening to strength levels of 180,000 psi and above shall be avoided whenever practicable. When such drilling is unavoidable, detailed information conc

43、erning the processes to be used shall be submitted to the approving activity for acceptance. to at: i, Any necessary straightening of parts after heat treatment strength levels of 180,000 psi and above shall be accomplished the tempering temperature, plus OOF (OW) minus 500F (28OC), or the parts sha

44、ll receive a stress-relieving treatment at this temperature immediately after straightening, Parts shall be inspected for cracks after straightening. 3. Free-machining grades of steel shall be subject to acceptance by the approving activity. 3.5,1,3,2 Corrosion-resistant Steels, The following limita

45、tions shall be observed in the selection and application of corrosion resistant steels, a, Unstabilized austenitic steels shall not be fusion welded, b. Precipitation hardening semi-austenitic grades shall not be used in applications which require extended exposure to -. temperatures in the 7500-900

46、0F (3990-4820C) range. subject to acceptance by the approving activity, c, The use of heat treated 431 or 19-9DL steel shall be d, The use of 17-4PH stainless steel aged below H1025 shall be subject to acceptance by the approving activity. 3,5.1,3,3 Maunesium Allov. Magnesium or its alloy shall not

47、be used 3.5,1,3,4 Castinas, 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 accordance with MIL-A-21180. Defects not materially affecting the suitability of the castings may be repaired at the foundry or during

48、machining by peening, impregnation, welding, or other methods acceptable to the procuring activity, governed by quality control techniques subject to the acceptance by the approving activity, Inspection of repaired castings shall be 8 Provided by IHSNot for ResaleNo reproduction or networking permit

49、ted without license from IHS-,-,- MIL-S-85419 27 m 7799906 O206625 I li MIL-S-85419 (AS) 3.5.1.3.5 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 above 220,000 psi or of bare high strength aluminum alloys and the techniques by which they are