1、 INCH-POUNDMIL-DTL-85061C 07 January 2009 SUPERSEDING MIL-C-85061B w/AMENDMENT 222 September 1986 DETAIL SPECIFICATION COUPLING, FUEL LINE, FLEXIBLE, 125 PSI Inactive for new design after 07 January 2009. For new design, use SAE-AS5356. This specification is approved for use by all Departments and A
2、gencies of the Department of Defense. 1. SCOPE 1.1 Scope. This specification covers flexible couplings for joining tubing with SAE-AS5131 style A beaded ends for use in aircraft fuel and vent systems (see 6.1). 1.2 Classification. Coupling materials and sizes are as specified in table I and table II
3、. 1.2.1 Part or Identifying number (PIN). The part or identifying number to be used for couplings acquired to this specification is identified as follows: M85061 -XX -X AMSC N/A FSC 4730 Material code letter (see 1.2.3 and table I) Size dash number (see table II) Military specification number Exampl
4、e: M85061-10-B = 0.625 tube coupling with CRES material 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 c
5、hange, you may want to verify the currency of this address information using the ASSIST online database at http:/assist.daps.dla.mil. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-85061C 21.2.2 Size. The size of couplings in dash numbers ar
6、e specified in table II. 1.2.3 Material. The basic material of the coupling is designated by the code letters as specified in table I. 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 docu
7、ments 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 4 o
8、f 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 to the extent specified herein. Unless otherwise specified, the issues of these documents
9、 are those cited in the solicitation or contract. FEDERAL STANDARD FED-STD-H28/2 - Screw-Thread Standards for Federal Services Section 2 Unified Inch Screw Threads- UN and UNR Thread Forms DEPARTMENT OF DEFENSE SPECIFICATIONS MIL-DTL-5624 - Turbine Fuel, Aviation, Grades JP-4 and JP-5 MIL-PRF-7024 -
10、 Calibrating Fluids, Aircraft Fuel System Components MIL-A-8625 - Anodic Coatings for Aluminum and Aluminum Alloys MIL-DTL-83133 - Turbine Fuel, Aviation, Kerosene Type, JP-8 (NATO F-34) and NATO F-35 and JP-8+100 (NATO F-37) DEPARTMENT OF DEFENSE STANDARDS MIL-STD-129 - Military Marking for Shipmen
11、t and Storage MIL-STD-130 - Identification Marking of U.S. Military Property MIL-STD-810 - Environmental Engineering Considerations and Laboratory Tests MIL-STD-889 - Dissimilar Metals Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-85061C 3D
12、EPARTMENT 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 Order Desk, 700 Robbins Avenue, Building 4D, Philadelphia,
13、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. SAE INTERNATIONAL SAE-AS5131 - Tubing End, Beaded, Design S
14、tandard (DoD Adopted) SAE-AS29512 - Packing, Preformed; Hydrocarbon Fuel Resistant, Tube Fittings, O-Ring (DoD Adopted) SAE-AS29513 - Packing, Preformed, Hydrocarbon Fuel Resistant, O-Ring (DoD Adopted) SAE-AMS-P-5315 - Butadiene-Acrylonitrile (NBR) Rubber for Fuel Resistant Seals 60 to 70 (DoD Adop
15、ted) (Copies of these documents are available online at http:/www.sae.org or from the SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001.) ASTM INTERNATIONAL ASTM-D3951 - Standard Practice for Commercial Packaging (DoD Adopted) (Copies of this document are available online at http:
16、/www.astm.org or from the ASTM International, P.O. Box C700, 100 Barr Harbor Drive, West Conshohocken, PA 19428-2959.) AEROSPACE INDUSTRIES ASSOCIATION (AIA) NASM 20995 - Wire, Safety or Lock (DoD Adopted) NASM 33540 - Safety Wiring, Safety Cabling, Cotter Pinning General Practices for (DoD Adopted)
17、 (Copies of these documents are available on line at http:/www.aia-aerospace.org or from the Aerospace Industries Association, 1000 Wilson Boulevard, Suite 1700, Arlington, VA 22209-3928.) Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-85061
18、C 4AMERICAN SOCIETY FOR QUALITY (ASQ) ANSI/ASQ Z1.4 - Sampling Procedures and Tables for Inspection by Attributes (DoD Adopted) (Copies of this document are available from American Society for Quality, 600 North Plankinton Ave., Milwaukee, WI 53203.) 2.4 Order of precedence. Unless otherwise noted h
19、erein 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 exemption has been obtained. 3. REQUIREM
20、ENTS 3.1 First article. When specified (see 6.2d), a sample shall be subjected to first article inspection (see 6.3) in accordance with 4.2. 3.2 Materials. Materials shall conform to applicable specifications and shall be as specified in table I. Materials which are not covered by applicable specifi
21、cations or which are not specifically described herein shall be of the lightest practicable weight and compatible with aircraft fuel. All materials shall be resistant to fluids conforming to MIL-PRF-7024, MIL-DTL-5624, and MIL-DTL-83133 to ensure satisfactory operation. 3.2.1 Metals. Metals shall be
22、 of a corrosion resisting material or treated in a manner to render them adequately resistant to 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 extreme
23、s of climatic and environmental conditions shall be avoided. 3.2.1.1 Aluminum alloy parts. All aluminum alloy parts shall be anodized in accordance with MIL-A-8625, type II, class 1 or class 2. 3.2.1.2 Steel parts. All steel parts shall be corrosion-resistant steel. Non-corrosion parts shall not be
24、used. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-85061C 5TABLE I. Coupling materials. Material Code Aluminum A Corrosion Resistant Steel (CRES) B 3.2.2 Fungus proof materials. Materials that are not nutrients for fungi shall be used to t
25、he greatest extent practicable. In cases where materials that are nutrients for fungi must be used, such materials shall be treated with fungicidal agent as approved by the contracting activity. 3.2.3 Dissimilar metals. Combinations of tubing and all contacting coupling parts shall be compatible in
26、accordance with MIL-STD-889. 3.3 Design and construction. The coupling shall be designed for connection of AS5131 tubing style A beaded ends and shall meet the requirements of figure 1 and table II. 3.3.1 Threads. Screw threads shall conform to FED-STD-H28/2. All threaded parts shall be securely loc
27、ked in such a manner as to prevent loosening under test conditions specified herein and under normal service usage. Safety wire per NASM 20995 shall be installed in accordance with NASM 33540. Wrenching features shall conform to figure 1. Pipe threads shall not be used. 3.3.2 Angular misalignment. T
28、he coupling shall be capable of being installed with a maximum tubing installation misalignment of 3 degrees in any direction. 3.3.3 Flexure. The coupling shall provide for 1 degree flexure in any direction from any installed position. The coupling shall provide for a variation in space between tubi
29、ng ends of 0.062 to 0.188 inch. 3.3.4 Permanent deformation. Installation of the coupling on tubing ends under conditions specified herein shall not produce a permanent deformation of the coupling. 3.3.5 Tubing. The coupling shall be capable of connecting tubing having an outside diameter (OD) and w
30、all thickness as specified in table III. 3.4 O-ring seal. The seal, which is used for testing purposes only and is not furnished as part of the flexible coupling, shall be in accordance with SAE-AMS-P-5315, and SAE-AS29512 or SAE-AS29513 of the applicable size specified in table II. 3.5 Configuratio
31、n, dimensions, and weight. The configuration, dimensions and weight shall be in accordance with figure 1 and table II. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-85061C 63.6 Performance. The coupling when installed on tubing in any posit
32、ion (attitude) shall meet all the performance requirements when tested as specified in section 4 of this specification. 3.6.1 Visual examination. Each coupling shall be examined and inspected as specified in 4.5.1.1 and shall have no defects. All dimensions and weights shall conform to the requireme
33、nts of this specification. 3.6.2 Proof pressure. The coupling assembly shall be designed to withstand a proof pressure of 250 5 psi. A decrease in pressure when pressurized to proof pressure as specified in 4.5.2 or any leakage (see 6.4.4) shall be cause for rejection of the coupling. 3.6.3 Leakage.
34、 3.6.3.1 Vacuum leakage. The coupling assembly shall be subjected to the negative proof pressure specified in 4.5.3.1. A decrease in pressure exceeding 0.5 Hg shall be cause for rejection of the test sample. 3.6.3.2 Pneumatic leakage. The coupling assembly shall be tested with pneumatic pressure equ
35、al to proof pressure as specified in 4.5.3.2 for 3 minutes at room temperature. The test sample shall be rejected if there is any evidence of leakage during the test. 3.6.4 Fuel resistance. The coupling assembly shall not leak (sufficient to form a drop) nor show evidence of damage when subjected to
36、 high temperature fuel aging at 200 F, low temperature fuel aging at -65 F and air dry out at 200 F when tested as specified in 4.5.4. 3.6.5 Vibration. The coupling assembly shall show no evidence of malfunction or structural failure (see 6.4.3) and shall pass the proof pressure test after exposure
37、to vibration levels as specified in 4.5.5. 3.6.6 Repeated assembly. There shall be no evidence of deformation, damage or degradation in the connecting ability of the coupling after 25 repeated assembly and disassembly operations specified in 4.5.6. After repeated assembly and disassembly, the test c
38、oupling shall pass the proof pressure test without fuel leakage (see 6.4.3). 3.6.7 Salt fog. The coupling assembly shall pass the salt fog test specified in 4.5.7 without any evidence of excessive corrosion, peeling, blistering of the finish or exposure of base metal. Threads, connecting surfaces, a
39、nd sealing surfaces shall be free of corrosion. 3.6.8 Flexure. The coupling assembly, when tested as specified in 4.5.8 with a 3 degree tubing misalignment and flexure at 0.5 degree for 28,800 cycles followed by the proof pressure test shall show no evidence of leakage, rupture, permanent set, perma
40、nent deformation or damage. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-85061C 73.6.9 Surge pressure. The coupling assembly shall withstand 50,000 pressure surge cycles without evidence of malfunction or leakage when tested at room temper
41、ature as specified in 4.5.9. 3.6.10 Burst pressure. The coupling assembly shall be designed to meet the burst pressure requirements at room and extreme temperatures and shall pass the tests specified in 4.5.10.1 and 4.5.10.2. Provided by IHSNot for ResaleNo reproduction or networking permitted witho
42、ut license from IHS-,-,-MIL-DTL-85061C 8TABLE II. Coupling dimensions and weights. Dash No. O.D. Tube (inch) A B (MIN) D (MAX)G (MIN) L (MAX) No. of lugs U O-ring Seal 3/ -04 .250 3.390 1.810 .890 1.220 1.794 - -010 -06 .375 1.100 1.289 -110 -08 .500 1.230 -112 -10 .625 3.610 1.360 1.291 1.954 -114
43、-12 .750 3.840 2.620 1.480 1.300 2.230 4 -210 -16 1.000 1.730 -214 -20 1.250 4.010 2.840 1.980 1.430 2.350 -218 -24 1.500 2.470 -325 -28 1.750 2.720 -327 -32 2.000 2.970 8 -329 -40 2.500 3.470 -333 -48 3.000 4.500 3.130 3.970 2.600 12 -337 -56 3.500 4.600 -341 -64 4.000 4.610 5.100 1.580 -345 -72 4.
44、500 4.740 3.190 5.660 1.710 2.650 -349 -80 5.000 6.231 -429 -88 5.500 5.270 3.470 6.680 1.800 2.930 -433 -96 6.000 5.980 3.700 7.230 1.920 3.160 16 -437 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-85061C 9TABLE II. Coupling dimensions and
45、 weights- Continued. Weight lbs (max) Dash No. W (min) T +.016 Aluminum CRES -04 - - 0.030 0.106 -06 0.038 0.114 -08 0.046 0.138 -10 0.180 0.093 0.056 0.168 -12 0.078 0.265 -16 0.130 0.320 -20 0.187 0.142 0.334 -24 0.242 0.550 -28 0.255 0.720 -32 0.135 0.294 0.741 -40 0.350 1.051 -48 0.145 0.438 1.3
46、10 -56 0.563 1.780 -64 0.160 0.782 2.030 -72 0.875 2.680 -80 1.140 3.200 -88 1.268 3.380 -96 0.250 0.175 1.900 3.600 NOTES: 1/ Dimensions are in inches 2/ Unless otherwise specified tolerances .010 3/ See detail dimensions on SAE-AS29513 and SAE-AS29512 for O-ring dimensions 4/ Dimensions W and T ar
47、e for nut only Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-85061C 10TABLE III. Tubing size and wall thickness. Nominal Wall Thickness Minimum (inches) Nominal Wall Thickness Minimum (inches) Tube O.D (inches) AL CRES Tube O.D (inches) AL
48、CRES .250 .028 .020 2.000 .035 .035 .375 .028 .020 2.500 .042 .035 .500 .035 .020 3.000 .042 .035 .625 .035 .020 3.500 .049 .049 .750 .035 .020 4.000 .049 .049 1.000 .035 .020 4.500 .065 .049 1.250 .035 .025 5.000 .065 .049 1.500 .035 .025 5.500 .065 .049 1.750 .035 .035 6.000 .065 .049 3.6.10.1 Bur
49、st pressure at temperature extremes. The coupling assembly shall not rupture nor show evidence of leakage at any pressure when tested as specified in 4.5.10.1. 3.6.10.2 Burst pressure at room temperature. The coupling assembly shall not rupture nor show evidence of leakage at any pressure when tested as specifie
