NAVY MIL-DTL-6396 F-2008 TANKS FUEL OIL COOLING FLUIDS INTERNAL REMOVABLE NON-SELF-SEALING《可拆卸非自密封式内置冷却液的燃油箱》.pdf

《NAVY MIL-DTL-6396 F-2008 TANKS FUEL OIL COOLING FLUIDS INTERNAL REMOVABLE NON-SELF-SEALING《可拆卸非自密封式内置冷却液的燃油箱》.pdf》由会员分享，可在线阅读，更多相关《NAVY MIL-DTL-6396 F-2008 TANKS FUEL OIL COOLING FLUIDS INTERNAL REMOVABLE NON-SELF-SEALING《可拆卸非自密封式内置冷却液的燃油箱》.pdf（43页珍藏版）》请在麦多课文档分享上搜索。

1、 AMSC N/A FSC 1560 DETAIL SPECIFICATION TANKS, FUEL, OIL, COOLING FLUIDS, INTERNAL, REMOVABLE NON-SELF-SEALING This specification is approved for use by all Departments and Agencies of the Department of Defense. 1. SCOPE 1.1 Scope. This specification covers internal, removable, non-self-sealing tank

2、s, including tank fittings for use on aircraft. 1.2 Classification. The tanks are of the following general types, as specified (see 6.2). 1.2.1 Types. The types of tanks are as follows: Type I - Metallic. Type II Non-metallic, bladder, flexible cell construction. Class A Continuously supported. Clas

3、s B Continuously supported tear resistant. Class C Intermittently supported. Type III Non-metallic, rigid/non-flexible, self-supporting cell construction. INCH-POUND Comments, suggestions, or questions on this document should be addressed to: Commander, Naval Air Warfare Center Aircraft Division, Co

4、de 4L8000B120-3, Highway 547, Lakehurst, NJ 08733-5100 or emailed to michael.sikoranavy.mil. Since contact information can change, you may want to verify the currency of this address information using the ASSIST Online database at http:/assist.daps.dla.mil. MIL-DTL-6396F 28 July 2008 SUPERSEDING MIL

5、-T-6396E 30 August 1983 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-6396F 2 2. APPLICABLE DOCUMENTS 2.1 General. The documents listed in this section are specified in sections 3 and 4 of this specification. This section does not include d

6、ocuments cited in other sections of this specification or recommended for additional information or as examples. While every effort has been made to ensure the completeness of this list, document users are cautioned that they must meet all specified requirements of documents cited in sections 3 and

7、4 of this specification, whether or not they are listed. 2.2 Government documents. 2.2.1 Specifications, standards, and handbooks. The following specifications and standards form a part of this document to the extent specified herein. Unless otherwise specified, the issues of these documents are tho

8、se cited in the solicitation or contract. FEDERAL STANDARDS FED-STD-791 - Lubricants, Liquid Fuels, and Related Products; Methods Of Testing DEPARTMENT OF DEFENSE SPECIFICATIONS MIL-PRF-680 - Degreasing Solvent MIL-DTL-85470 - Inhibitor, Icing, Fuel System, High Flash, NATO Code S-1745 DEPARTMENT OF

9、 DEFENSE STANDARD MIL-STD-801 - Inspection and Acceptance Standards for Fuel Cells and Fittings (Copies of these documents are available online at http:/assist.daps.dla.mil/quicksearch or from the Standardization Document Order Desk, 700 Robbins Avenue, Building 4D, Philadelphia, PA 19111-5094.) 2.3

10、 Non-Government publications. The following documents form a part of this document to the extent specified herein. Unless otherwise specified, the issues of these documents are those cited in the solicitation or contract. Provided by IHSNot for ResaleNo reproduction or networking permitted without l

11、icense from IHS-,-,-MIL-DTL-6396F 3 AEROSPACE INDUSTRIES ASSOCIATION (AIA) NASM20470 - Rivet, Solid, Universal Head, Aluminum Alloy and Titanium Columbium Alloy (Copies of this document are available from the Aerospace Industries Association, 1000 Wilson Boulevard, Suite 1700, Arlington, VA 22209-39

12、01 or http:/www.aia-aerospace.org.) AMERICAN SOCIETY OF MECHANICAL ENGINEERS (ASME) ASME-Y14.100 - Engineering Drawing and Related Documentation Practices ASME-Y14.8 - Castings and Forgings (Copies of this document is available from the American Society of Mechanical Engineers, 22 Law Drive, P.O. Bo

13、x 2900, Fairfield, NJ 07007-2900 or http:/www.asme.org.) AMERICAN SOCIETY FOR TESTING AND MATERIALS (ASTM) INTERNATIONAL ASTM-B766 - Cadmium, Electrodeposited Coatings of ASTM-D381 - Fuels by Jet Evaporation, Gum Content in ASTM-D412 - Rubber, Vulcanized and Thermoplastic Elastomers - Tension ASTM-D

14、413 - Rubber Property-Adhesion to Flexible Substrate ASTM-D471 - Rubber Property - Effect of Liquids (Copies of these documents are available from ASTM International, 100 Barr Harbor Drive, West Conshohocken, PA 19428-2959 or http:/www.astm.org.) RADIO TECHNICAL COMMISSION FOR AERONAUTICS (RTCA) RTC

15、A/DO-160 - Environmental Conditions and Test Procedures for Airborne Equipment (Application for copies should be addressed to the Radio Technical Commission for Aeronautics, 1828 L Street, NW, Suite 805, Washington, DC 20036 or http:/www.rtca.org.) Provided by IHSNot for ResaleNo reproduction or net

16、working permitted without license from IHS-,-,-MIL-DTL-6396F 4 SOCIETY OF AUTOMOTIVE ENGINEERS (SAE) INTERNATIONAL SAE-AMS2175 - Casting, Classification and Inspection of SAE-AS8879 - Screw Threads, UNJ Profile, Inch Controlled Radius Root With Increased Minor Diameter (Copies of these documents are

17、 available from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001 or http:/www.sae.org.) 2.4 Order of precedence. In the event of a conflict between the text of this document and the references cited herein, the text of this document takes precedence. Nothing in this document, how

18、ever, supersedes applicable laws and regulations unless a specific exemption has been obtained. 3. REQUIREMENTS 3.1 Tank performance. The tank(s) shall be capable of performing, without failure, during all phases and environments of aircraft use as specified by the procuring activity. 3.2 First arti

19、cle. When specified (see 6.2), a sample shall be subjected to first article inspection in accordance with 4.2. 3.3 Tank components. 3.3.1 Type I and III tanks. These tanks shall consist of a fluid reservoir, typically referred to in this specification as a cell or bladder, complete with all fittings

20、 and attachments. 3.3.2 Type II tanks. A tank shall consist of a cell or a group of interconnected cells to form a complete tank or reservoir, complete with all fittings and attachments. 3.4 Materials. The materials used in the manufacture of non-self-sealing tanks shall be for the purpose intended.

21、 The use of magnesium is prohibited. 3.4.1 Metals. Metals shall be of the corrosion-resistant type or treated to resist corrosion due to fuels, salt fog, or atmospheric conditions likely to be met in storage or normal service. 3.4.1.1 Dissimilar metals. Unless protected against electrolytic corrosio

22、n, dissimilar metals shall not be used in intimate contact with each other. 3.4.2 Metallic castings. Castings shall be in accordance with ASME-Y14.8. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-6396F 5 3.5 Design. 3.5.1 General. Tanks sha

23、ll be compatible with the fuel for which they are intended and shall perform in conjunction with the containing structure to avoid load concentration on splices, seams, fittings, or concentrated flexure locations. The tank assembly and aircraft structure in which it is mounted shall possess the nece

24、ssary strength to provide for the stresses caused by the following: a. Flexing resulting from vibration. b. Impact loads incident to take-off, taxiing, and landing (including catapulting and aresting). c. Positive and negative pressures associated with fluid surge incident to all dynamic conditions

25、of flight, including catapult and arrested landing, if applicable. d. Pressure loads imposed by: 1. Hydrostatic head of fluids during level flight or maneuvers. 2. Pressurizing or inerting gases. 3. Proof and ultimate pressures as designated by the procuring activity. 4. Fluid surge incident to gunf

26、ire, where type II, class B, tank constructions are used. e. Handling loads associated with removal, transportation and installation. 3.5.2 Capacity. The capacity of the tank(s) shall be such that the aircraft is capable of completing the requirements as specified by the procuring activity. The capa

27、city of types I and III cells shall be within 1.5 percent of the total volume of the average capacity of the first 10 production cells manufactured after design approval of the cells. For cells in production, the fuel level versus volume curve shall be within 1.5 percent of the calibrated fuel level

28、 versus volume curve. 3.5.3 Weight. Emphasis shall be placed on creating the lowest weight cell that will meet the requirements of this specification. The weight of production cells shall be within the following percentages of the average weight of the first 10 production cells manufactured after de

29、sign approval of the cell: a. Type I cells: 2 percent b. Types II and III cells: 5 percent Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-6396F 6 If, during the production of cells, the weight is consistently greater than the tolerance on on

30、e side of the production weight, the procuring activity shall be informed, and all pertinent data shall be supplied including a recommendation for a new production weight, the reason for exceeding the weight tolerances, and a log of the tank or cell weight for review and establishment of a new produ

31、ction weight. 3.6 Construction. 3.6.1 Installation mountings. Provisions shall be made for installation mounting of the tank(s) with the following interfaces: 3.6.1.1 Bosses. Fittings shall conform to best commercial practices consistent with meeting design requirements of the tank. Tanks shall not

32、leak. 3.6.1.2 Sealing torque. The fitting(s) shall provide a fluid tight seal with application of the appropriate tightening torque as specified in table I. 3.6.1.3 Threaded holes. All threaded bolt holes shall be blind and shall incorporate replaceable or repairable self-locking steel inserts. 3.6.

33、1.4 Inserts. Each insert shall be provided with a locking device. The locking device shall not damage the fastener or insert. The insert and locking device shall be capable of a minimum of 50 installation and removal cycles before replacement is required. The fitting and insert shall be designed so

34、that damage beyond repair to the fitting or insert shall not occur when the maximum allowable torque as specified in table I is applied on a bolt that is bottomed out against the bottom of the bolt clearance hole or tapped hole or when applied against a bolt that is shanked out against the top threa

35、d of the bolt. 3.6.2 Screw threads. Screw threads shall be in accordance with SAE-AS8879. 3.6.2.1 Pipe threads. The use of pipe threads is prohibited. 3.6.2.2 Locking of threaded parts. All threaded parts shall employ self-locking features. Staking and the use of lock washers shall not be permitted.

36、 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE I. Torque values (inch pounds). Locking Device Free Spinning Prevailing torque Breakaway torque Maximum allowable bolt torque Thread size Tightening torque Minimum Maximum Maximum Installation Mi

37、nimum Breakaway 0.2500-28_ 100 60 30 90 30 3.5 0.3125-24_ 225 120 60 180 60 6.5 0.3750-24_ 390 175 85 260 80 9.5 0.4375-20_ 840 475 240 715 100 14.0 0.5000-20_ 1,100 585 290 875 150 18.0 7MIL-DTL-6396F Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-

38、MIL-DTL-6396F 8 3.7 Interchangeability. All parts having the same manufacturers part number shall be physically and functionally interchangeable without the need for modification of such parts. 3.8 Finish. 3.8.1 External surfaces. The external surfaces of type II and III tanks shall be ozone and ult

39、raviolet light resistant or protected against the action of ozone, ultraviolet light and the fluid for which the tanks are intended. 3.8.2 Steel parts. Exposed steel parts shall be of corrosion resistant steel or shall be protected to satisfy a 120-hour salt fog test conducted in accordance with RTC

40、A/DO-160, Section 14. For parts not exposed to fuel in normal use, cadmium plating in accordance with ASTM-B766 may be used. Parts exposed to fuel in normal use shall not be cadmium plated. 3.8.3 Aluminum-alloy parts. Aluminum-alloy parts shall meet a 120-hour salt fog test conducted in accordance w

41、ith RTCA/DO-160, Section 14. If required for electrical bonding, the protection may be removed locally. 3.9 Temperature range. Tanks shall operate throughout an ambient temperature range of -65 to +160 F (-54 to +71 C) and fuel temperature ranges of -65 to +135 F (-54 to +57 C) unless otherwise dire

42、cted by the procuring activity. 3.10 Installation torque. As specified by the procuring activity, the proper torque values for installing the tank in the aircraft and for attachment of fuel lines, interconnects, vent lines, fuel pumps, valves, access doors, and other fuel system components shall be

43、durably and legibly marked on or adjacent to each fitting or fuel system component involved, on the side to which the torque wrench is applied. In tanks where all torque values are the same, the proper torque value shall be stenciled in a conspicuous space. 3.11 Age. Cells shall be not greater than

44、2 years old from date of initial cure to delivery to the procuring activity. 3.12 Cleaning. No cell shall contain rubber particles, dirt, sand, metal chips, welding flux, or any other foreign material prior to shipment. 3.13 Markings. Each assembly part shall be marked with its part number which sha

45、ll be the same as the drawing number of that part or assembly. (An assembly consists of parts that are permanently fastened together.) Exceptions to this marking requirement are those parts that do not have a suitable or sufficient surface for a part number. 3.13.1 Location of part numbers. The part

46、 number shall be visible to read after assembly of the complete unit and legible during the life of the part. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-6396F 9 3.13.2 Identification of product. Each cell assembly shall be marked for ide

47、ntification and shall include: a. Re-order by part number (insert current aircraft contractor part number). b. Federal stock number. c. Aircraft model(s) and cell location. d. Cure date (month and year). e. Construction number. f. Cell manufacturer and CAGE code. g. Cell manufacturer part number. h.

48、 Weight, empty (actual). i. MIL-DTL-6396F, Type, Class (if applicable). j. Contract or order number. 3.13.2.1 Identification. Identification (e.g., nameplate, stencil, etc.) shall be located on the cell in such a position that when the cell is installed in the aircraft, identification is visible with the minimum possible disruption of the cell installation. Identification shall be durably and legibly marked onto the tank. 3.13.3 Access door covers. Unless otherwise specified, the exterior surface of all access door covers shall be durably and legibly marked “OUTSIDE”. 4. VERIFICATION