NAVY MIL-DTL-22263 C-2009 COUPLING FUEL LINE FLEXIBLE 125 PSI GENERAL SPECIFICATION FOR《125 PSI 柔性联接燃料管线一般规范》.pdf

《NAVY MIL-DTL-22263 C-2009 COUPLING FUEL LINE FLEXIBLE 125 PSI GENERAL SPECIFICATION FOR《125 PSI 柔性联接燃料管线一般规范》.pdf》由会员分享，可在线阅读，更多相关《NAVY MIL-DTL-22263 C-2009 COUPLING FUEL LINE FLEXIBLE 125 PSI GENERAL SPECIFICATION FOR《125 PSI 柔性联接燃料管线一般规范》.pdf（24页珍藏版）》请在麦多课文档分享上搜索。

1、 MIL-DTL-22263C 11 September 2009 SUPERSEDING MIL-C-2263B 28 June 1972 DETAIL SPECIFICATION COUPLING FUEL LINE, FLEXIBLE, 125 PSI GENERAL SPECIFICATION FOR This specification is approved for use by all Departments and Agencies of the Department of Defense. 1. SCOPE 1.1 Scope. This specification cove

2、rs flexible couplings for joining variable ferrule type tubing in military aircraft fuel systems. 1.2 Couplings. The coupling materials and sizes are as specified in table I and table II respectively. TABLE I. Material and code. Material Code All aluminum A Aluminum body and nut, CRES steel retainer

3、 B All CRES C All titanium T AMSC N/A FSC 4730 Comments, suggestions, or questions on this document should be addressed to the Naval Air Systems Command, Attention: Code 4L8000B120-3, Highway 547, Lakehurst, NJ 08733-5100 or emailed to michael.sikoranavy.mil. Since contact information can change, yo

4、u may want to verify the currency of this address information using the ASSIST online database at http:/assist.daps.dla.mil. INACTIVE FOR NEW DESIGN AFTER 18 MARCH 1997 INCH-POUND Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-22263C 21.2.1

5、Part or identifying number (PIN). The part or identifying number to be used for couplings acquired to this specification is identified as follows: M 22263 -XX -X Example: M22263-10-C = 0.625 tube coupling with CRES material 2. APPLICABLE DOCUMENTS 2.1 General. The documents listed in this section ar

6、e specified in sections 3 and 4 of this specification. This section does not include documents 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 cautione

7、d that they must meet all specified requirements of documents cited in sections 3 and 4 of this specification, whether or not they are listed. 2.2 Government documents. 2.2.1 Specifications, standards, and handbooks. The following specifications, standards, and handbook form a part of this document

8、to the extent specified herein. Unless otherwise specified, the issues of these documents are those cited in the solicitation or contract. DEPARTMENT OF DEFENSE SPECIFICATIONS MIL-DTL-5624 - Turbine Fuel, Aviation, Grades JP-4 and JP-5 MIL-PRF-7024 - Calibrated Fluids, Aircraft Fuel System Component

9、s MIL-A-8625 - Anodic Coatings for Aluminum and Aluminum Alloys MIL-DTL-25988 - Rubber, Fluorosilicone Elastomer, Oil and Fuel Resistant, Sheets, Strips, Molded Parts, and Extruded Shapes MIL-R-25988/1 - Rubber, Fluorosilicone Elastomer, Oil- and Fuel Resistant, O-Rings, Class 1, Grade 70 Specificat

10、ion number Material code (see table I) Size in dash number (see table II) M prefix Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-22263C 3MIL-DTL-83133 - Turbine Fuel, Aviation, Kerosene Type, JP-8 (NATO-F34), NATO F-35 and JP-8+100 (NATO F-

11、37) DEPARTMENT OF DEFENSE STANDARDS MIL-STD-129 - Military Marking for Shipment and Storage MIL-STD-130 - Identification Marking of US Military Property MIL-STD-810 - Environmental Engineering Considerations and Laboratory Tests MIL-STD-889 - Dissimilar Metals MS33784 - Wrenching Features for Cylind

12、rical Nut, Design Standard for (Inactive for new design) DEPARTMENT OF DEFENSE HANDBOOK MIL-HDBK-470 - Designing and Developing Maintainable Products and Systems, Volume 1 (Copies of these documents are available online at http:/assist.daps.dla.mil/quicksearch/ or from the Standardization Document O

13、rder Desk, 700 Robbins Avenue, Building 4D, Philadelphia, PA 19111-5094.) 2.3 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. S

14、AE INTERNATIONAL SAE-AMS2700 - Steels, Passivation of Corrosion Resistant (DoD adopted) SAE-AS8879 - Screw Threads, UNJ Profile, Inch Controlled Radius Root With Increased Minor Diameter (DoD adopted) (Copies of these documents are available online at http:/www.sae.org or from the SAE International,

15、 400 Commonwealth Drive, Warrendale, PA 15096-0001.) ASTM INTERNATIONAL ASTM-D3951 - Commercial Packaging (DoD adopted) (Copies of these documents are available online at http:/www.astm.org or from the ASTM International, P.O. Box C700, 100 Barr Harbor Drive, West Conshohocken, PA 19428-2959.) Provi

16、ded by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-22263C 4AEROSPACE INDUSTRIES ASSOCIATION (AIA) NASM20995 - Wire, Safety or Lock (DoD adopted) NASM33540 - Safety Wiring and Cotter Pinning (DoD adopted) (Copies of these documents are available onlin

17、e at http:/www.aia-aerospace.org or from the Aerospace Industries Association, 1000 Wilson Boulevard, Suite 1700, Arlington, VA 22209-3928.) ANSI INTERNATIONAL ANSI/ASQ Z1.4 - Sampling Procedures and Tables for Inspection by Attributes (Copies of these documents are available online at http:/www.ans

18、i.org or from ANSI, 25 West 43rd Street, New York, NY 10036-8002.) ASME INTERNATIONAL ASME B46.1 - Surface Texture (Surface Roughness, Waviness, and Lay) (Copies of this document are available online at http:/www.asme.org or from ASME, 22 Law Drive, P.O Box 2900, Fairfield, NJ 07007-2900.) 2.4 Order

19、 of precedence. Unless otherwise noted herein or in the contract, 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, however, supersedes applicable laws and regulations unless a specific

20、exemption has been obtained. 3. REQUIREMENTS 3.1 First article. The couplings furnished under this specification shall be products that have been inspected and have passed the first article inspection specified herein. 3.2 Materials. Materials shall conform to applicable specifications and shall be

21、as specified herein. Materials that are not covered by applicable specifications or that are not specifically described herein shall be compatible with aviation fuel conforming to MIL-DTL-5624, MIL-PRF-7024 and MIL-DTL-83133 and shall have the lightest practicable weight as possible. 3.2.1 Metals. M

22、etals shall be of a corrosion-resisting type or shall be suitably treated to resist corrosion when exposed to climatic and environmental conditions encountered during the service life of the equipment. The use of any protective coating that will crack, chip, or scale with age or extremes of climatic

23、 and environmental conditions shall be avoided. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-22263C 53.2.2 Fungus-proof materials. Materials that are not nutrients for fungi shall be used to the greatest extent practicable. In cases where

24、materials that are nutrients for fungi must be used, such materials shall be treated with a fungicidal agent as approved by the procuring activity. 3.3 Finish. 3.3.1 Aluminum alloy parts. Where practicable, all aluminum alloy parts shall be anodized in accordance with MIL-A-8625. 3.3.2 Steel parts.

25、Steel parts shall be corrosion proof or resist to corrosion shall be passivated per SAE-AMS2700. Non-corrosion-resistant steel parts shall not be used. 3.3.3 Titanium parts. Finish shall not be required for titanium parts. 3.4 Dissimilar metals. Connecting tubing with coupling parts shall be compati

26、ble and shall meet the requirements of MIL-STD-889. 3.5 Design and construction. The coupling shall be designed for connecting variable ferrule type tubing end when used in aircraft power plant fuel systems. Typical couplings installation shall be as shown in figure 1. The coupling dimensions and we

27、ights without O-ring shall be in accordance with table II. The design and construction of the coupling shall be such that it shall withstand the strains, jars, vibrations and other conditions incident to aircraft installations and service usage. 3.5.1 Threads. Machine screw threads shall conform to

28、SAE-AS8879. All external or internal threaded parts shall be securely locked in such a manner as to prevent loosening under test conditions specified herein and under normal service usage. Provisions for safety wiring shall be provided. Safety wires shall be installed in accordance with NASM33540 an

29、d shall conform to NASM20995. Wrenching features shall conform to MS33784. Tools shall not be required for torquing. 3.5.2 Angular misalignment. The coupling shall be capable of being installed with a maximum tubing or ferrule installation misalignment of 3 degrees in any direction (see figure 3 and

30、 figure 4). 3.5.3 Flexure. The coupling shall provide for one degree flexure in any direction from any installed position. The connector shall maintain a space between tubing and ferrules of 0.062 inch minimum to 0.188 inch maximum. 3.5.4 Permanent deformation. Installation of the coupling on tubing

31、 ends under conditions specified herein shall not produce a permanent deformation of the tubing or fitting. 3.5.5 Tubing. The couplings shall be designed for connecting tubing ends conforming to figure 2. The tubing end dimensions shall be in accordance with table III. Provided by IHSNot for ResaleN

32、o reproduction or networking permitted without license from IHS-,-,-MIL-DTL-22263C 63.6 O-ring seal. The O-ring seal used for testing purposes shall be in accordance with MIL-DTL-25988 of the applicable size specified in table II. The seals shall be easily replaceable without damage to the coupling

33、parts and with a minimum of disturbance or displacement of the installed tubing or fitting. The O-ring seals shall not be subjected to axial loads of tubing under pressure. FIGURE 1. Coupling installation connecting two swaged ferrule fuel lines. Provided by IHSNot for ResaleNo reproduction or netwo

34、rking permitted without license from IHS-,-,-MIL-DTL-22263C 7TABLE II. Coupling dimensions and weights. 1/ Weight lb (max) Dash No Tube OD A B D (max) G L (max) O-ring Size (Ref) 2/ Al Steel Ti -12 0.75 2.51 1.68 1.532 1.31 1.29 -212 0.057 0.163 0.092 -16 1.00 2.57 1.84 1.782 -216 0.075 0.215 0.120

35、-20 1.25 2.57 1.84 2.032 1.37 1.35 -220 0.086 0.240 0.144 -24 1.50 2.90 2.407 -326 0.128 0.358 0.214 -28 1.75 2.90 2.657 1.63 -328 0.176 0.492 0.294 -32 2.00 2.95 3.052 -330 0.212 0.593 0.354 -40 2.50 2.95 3.427 -334 0.225 0.630 0.376 -48 3.00 2.95 2.07 3.927 1.65 1.54 -338 0.285 0.798 0.476 -56 3.5

36、0 3.06 2.17 4.427 1,63 -342 0.375 1.050 0.627 -64 4.00 3.06 2.18 4.928 1.76 1.64 -346 0.399 1.117 0.667 -72 4.50 3.35 2.30 5.678 1.99 1.76 -426 0.654 1.730 0.842 -80 5.00 3.58 2.52 6.178 2.21 1.98 -430 0.762 2.066 1.233 -88 5.50 3.60 2.56 6.553 2.19 2.02 -434 0.777 2.131 1.298 -96 6.00 3.64 2.60 7.0

37、53 2.24 2.06 -437 0.932 2.015 1.557 1/ Dimensions are in inches 2/ O-ring sizes conform to MIL-R-25988/1 3.7 Performance. The coupling, when installed in any position (attitude), shall meet all the following performance requirements when tested as specified in section 4 of this specification. 3.7.1

38、Examination of product. The couplings shall be examined and inspected as specified in 4.7.1 and shall have no defects. All dimensions and weights shall conform to table II. 3.7.2 Proof pressure. The coupling assembly shall be designed to withstand a proof pressure of 250 5 psi. A decrease in pressur

39、e when pressurized to proof pressure as specified in 4.7.2 or any leakage from the coupling or joint shall be cause for rejection of the coupling. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-22263C 8FIGURE 2. Tubing swaged end ferrule dim

40、ensions and configuration. 1/ TABLE III. Tubing end, swage end ferrule, variable cavity dimensions. 1/ Dash No Tube OD A +.000 -.005 B + .005 - .000 C +.000 -.005 D + .005 E + .005 F + .005 G -12 0.75 0.730 0.755 0.891 0.984 0.545 -16 1.00 0.980 1.005 1.142 1.265 -20 1.25 1.230 1.256 1.392 1.515 0.6

41、69 -24 1.50 1.480 1.506 1.642 1.785 0.040 -28 1.75 1.730 1.756 1.892 2.035 0.675 -32 2.00 1.980 2.006 2.142 2.308 -40 2.50 2.480 2.507 2.642 2.808 -48 3.00 2.930 3.007 3.145 3.308 0.682 -56 3.50 3.455 3.507 3.650 3.819 -64 4.00 3.980 4.008 4.154 4.329 5 -72 4.50 4.480 4.508 4.655 4.825 0.712 0.055 -

42、80 5.00 4.980 5.009 5.155 5.300 -88 5.50 5.480 5.509 5.660 5.825 .956 -96 6.00 5.980 6.010 6.165 6.340 1.001 0.075 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-22263C 91/ NOTES: 1. Materials: 2024 T4 aluminum, CRES, or Ti 2. Dimensions s

43、hown are in inches, unless otherwise specified, tolerance: Decimal + .005, angle + 0.5o3. Unless otherwise specified, break all sharp edges .003 - .015 4. Surface texture in accordance with ASME B46.1 TABLE IV. Tubing sizes and wall thickness. Wall thickness (min) Coupling sizes Tube O.D AL CRES Ti

44、-12 0.75 .035 .020 .020 -16 1.00 .035 .020 .020 -20 1.25 .035 .025 .022 -24 1.50 .035 .025 .022 -28 1.75 .035 .035 .032 -32 2.00 .042 .035 .032 -40 2.50 .042 .035 .032 -48 3.00 .042 .035 .041 -56 3.50 .065 .049 .041 -64 4.00 .065 .049 .041 -72 4.50 .065 .049 .041 -80 5.00 .065 .049 .041 -88 5.50 .06

45、5 .049 .041 -96 6.00 .065 .049 .041 3.7.3 Leakage. 3.7.3.1 Vacuum leakage. The coupling assembly shall be subjected to the negative proof pressure specified in 4.7.3.1. A decrease in pressure exceeding 0.5 Hg (0.25 psi) shall be cause for rejection of the test sample. 3.7.3.2 Pneumatic leakage. The

46、coupling shall be tested with pneumatic pressure equal to proof pressure as specified in 4.7.3.2 for 3 minutes at room temperature. Any leakage or evidence of leakage during the test shall be cause for rejection of the test sample. Provided by IHSNot for ResaleNo reproduction or networking permitted

47、 without license from IHS-,-,-MIL-DTL-22263C 103.7.4 Fuel resistance. The coupling assembly shall not leak (sufficient to form a drop) nor show evidence of damage when subjected to high temperature fuel aging at 200 F, low temperature fuel aging at -65 F and air dry out at 200 F when tested as speci

48、fied in 4.7.4. 3.7.5 Salt fog. The coupling assembly shall pass the salt fog test specified in 4.7.5 without any evidence of excessive corrosion, peeling, blistering of the finish or exposure of base metal. Threads and connecting surfaces and sealing surfaces shall be free of corrosion. 3.7.6 Repeat

49、ed assembly. There shall be no evidence of deformation, damage or degradation in the connection of the coupling halves after 25 repeated assembly and disassembly test specified in 4.7.6 follow by the proof pressure test without leakage. 3.7.7 Flexure. The coupling assembly, when tested as specified in 4.7.7