1、- 1. SCOPE MIL-D-8683C 5 February 1988 SUPERSEDING MIL-D-8683B 16 June 1980 MILITARY SPECIFICATION DESIGN AND INSTALLATION OF GASEOUS OXYGEN SYSTEMS IN AIRCRAFT, GENERAL SPECIFICATION FOR This specification is approved for use by al 1 Departments and Agencies of the Department of Defense. 1.1 Scope.
2、 This specification covers the general requirements for the design and installation of gaseous oxygen (450 and 1800 pounds per square inch gage (psig) (3.1 MPa and 12.4 MPa) systems in aircraft. 1.2 Classification, Aircraft oxygen systems shall be of the following types : Type I - High pressure syst
3、em 1800 psig (12.4 MPa) Type II - Low Pressure system 450 psig (3.1 MPa) 2. APPLICABLE DOCUMENTS 2.1 Government documents. 2.1.1 Specific-ation, standards, and handbooks. The following specifications, standards and handbooks form a part of this specification to the extent specified herein. Unless ot
4、herwise specified, the issues of these documents shall be those 1 isted in .Che Department of Defense Index of Specifications and Standards (DODISS) and supplement thereto, cited in the sol ici tation. Beneficial comments (recommendations, additions, deletions.) and any pertinent data which may be o
5、f use in improving this document should be addressed to: Systems Engineering and Standardization Department (Code 93) Naval Air Engineering Center, Lakehurst, NJ 08733-5100, by using the self-addressed Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this document
6、 or by letter. AMSC-NIA FSC 1660 DISTRIBUTION STATEMENT A. Approved for public release; distribution is un1 imi ted. Licensed by Information Handling ServicesProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SPECIFICATIONS MILITARY DOD-D- 1 O00 MIL-B-5
7、087 MIL-T-8506 MI L-A-8625 MIL-V-1 831 8 MI L-A-23 1 2 1 MIL-R-25410 MI L-L-25567 MIL-C-25969 MIL-T-26069 MI L-0-272 1 O MIL-0-27335 MIL-G-27617 MIL-T-27730 MIL-S-81018 MI L-C-8 1 302 MIL-T-81533 MI L-H-8 1 58 1 MI L-D-8683C Drawings, Engineering and Associated Lists Bonding, Electrical, and Lightin
8、g Protection, for Aerospace Systems. Tubing, Steel, Corrosion-Resistant, (304), Annealed, Seamless and We1 ded. Anodic Coatings, for Aluminum and Aluminum Al loys. Valve, Pressure Regulating, Oxygen System. Aircrew, Environmental, Escape and Survival Cockpit Capsule System; General Specification For
9、. Regulator, Oxygen, Di 1 uter-Demand, Automati c Pressure Breathing. Leak Detection Compound, Oxygen Systems. Capsule Emergency Escape Systems, General Specification For. Trai ler, Compressed Gas Cy1 i nder AF-M32R-3, High Pressure, 2 Wheel 6 Cy1 i nder Capac i ty . Oxygen, Aviators Breathing, Liqu
10、id and Gas. Oxygen System, Survi val Contai ner-Oxygen Kit, General Specification For. Grease, Aircraft and Instrument, Fuel and Oxidizer Resistant. Tape, Antiseize, Tetrafluoroethylene, With Di Spenser Survival Kit Container, Aircraft Seat With Oxygen, General Specification For C1 eani ng Compound,
11、 Sol vent, Trichlorotriflouroethane Trichloroethane 1, 1, 1, (Methyl Chloroform) - Hose Assembly, Breathing Oxyge and Air, General Specification For Inhibited, Vapor Degreasing. MIL-H-81581 15 - Hose Assembly; Breathing Oxygen, Low Pressure, Connector to Regulator. MIL-R-831 78 - Regulator Oxygen, D
12、i 1 uter-Demand, Automati c Pressure-Breathing, General Specification For. MIL-M-87163 - Mask, Oxygen, MBU-12/P MIL-H-87961 - Hose and Hose Assembl ies, Ai r Duct, Air Breathing Oxygen System, General Specification For. STANDARDS MILITARY MIL-STD-17-2 - Mechani cal Symbols For Aeronautical Aerospace
13、craft and Spacecraft Use. 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- e DOD-STD-1 O0 - MIL-STD-143 - MIL-STD-203 - MIL-STD-889 - MIL-STD-1247 - MIL-STD-1359 - MIL-STD-45662 - MS21211 - MS21227 - MS22012 - MS22032 - MS22035 - MS22055 - MS22059
14、- “22061 - MS22062 - MS26545 - MS27599 - MS33583 - MS33584 - MS33611 - MS90338 - Engineering Drawing Practices Specifications and Standards, Order of Precedence for the Selection of. Aircrew Station Controls and Di splays For Fi xed Ni ng Ai rcraf t . Dissimilar Metals. Marking, Functions and Hazard
15、 Designation of Hose, Pipe, and Tube Lines for Aircraft, Mi ss i 1 e, and Space Systems. Cleaning Methods and Procedures for Breathi ng Oxygen Equipment. Cal i bration System Requirements. Valve, Check, Aircraft Low Pressure Oxygen Sys terns. Cy1 i nder , Oxygen, Low Pressure. Valve, Hi gh-Pressure
16、Oxygen-Cy1 i nder, Automati c Open i ng . Recharger Assembly, Portable Oxygen. Valve, Check, Oxygen, High Pressure, Filler Connection. Hose Assemblies, Oxygen-Breathing Connector to Regul ator. Oxygen System, Portable, 295 Cu. In. High Pressure, Aircraft Oxygen System, Portable, 96 Cu. In. High Pres
17、sure, Aircraft. Regulator, Oxygen, Di 1 uter Demand, Automati c , Pressure Breathing. Cy1 i nder-Compressed Gas , Non-Shatterable. Regulator, Oxygen, Di 1 uter Demand. Tubing End, Double Flare, Standard Dimensions For. Tubing End, Standard Dimensions For Flared. Tube, .Bend Radi i. Valve, High Press
18、ure Oxygen Check, Flareless Ends. AIR FORCE-NAVY AERONAUTICAL AN780 AN806 AN929 AN6009 AN601 1 AN601 2 AN601 4 AN601 5 AN601 6 AN601 7 AN601 8 AN602 1 AN6024 AND10089 Nipple - Union. Plug - Flared Tube. Cap Assembly, Tube, Pressure Seal. Coup1 i ng - Automatic Oxygen. Gage-Panel Mounting, High Press
19、ure Oxygen. Valve, High Pressure Oxygen Line. Valve-High Pressure Oxygen Check, Style A. Valve-High Pressure Oxygen Check, Style B. Valve-High Pressure Oxygen Check, Style C. Valve-High Pressure Oxygen Check, Style D. Valve-High Pressure Oxygen Check, Style E. Gage-Panel Mounting, Low Pressure Oxyge
20、n. Val ve-Low Pressure Oxygen Fi 11 er. Fitting End, Standard Dimensions For Cone Connect i on. 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-D-8683C 2.1.2 Other Government documents, drawings and publications. The fol lowing other Government
21、 documents, drawings and publ ications, form a part of thi s specffication to the extent specified herein. Unless otherwise speclfied, the issues shall be those in effect on the date of the solici tation. DRAWINGS AIR FORCE 44A25450 - S1 eeve, Oxygen Coup1 i ng. 46A16236 - Clip-Recharger, Low Pressu
22、re Oxygen System. 53c3794 d Cy1 i nder and Regulator, Breathi ng Oxygen, Portable. 5303970 I Mask-Cy1 i nder-Regul ator, Oxygen, Portable, Aircraft, Firefighters. 5583878 - Dustcap-High Pressure Oxygen Fi 1 ler Valve-Assembly. 6003570 - Cy1 Inder and Regulator, Breathing Oxygen, Portable A/U26S-3, A
23、ssembly of (Copies of specifications, standards, handbooks, drawings, publications and other Government documents required by contractors In connection with specific acquisition functions should be obtained from the contracting activity or as directed by the contracting officer.) 2.2 Other publ i ca
24、tions. The fol lowing document forms a part of this specification to the extent specified herein. Unless otherwise specified, the issues of the documents which are DOD adopted shall be those 1 isted In the Issue of the DoDISS specified in the solicitation. Unless otherwise specified, the issues of d
25、ocuments not listed in the DODISS shall be the issue of the nongovernment documents which is current on the date of sol ici tation. SOCIETY OF AUTOMOTIVE ENGINEERS AM! 4071 d Aluminum Alloy Tubing, Hydraulic, Seamless, Drawn, Round 2-5Mg-0 25 Cr (5052-01 Anneal ed . (Applications for copies should b
26、e addressed to the Society of Automotive Engineers, Inc., 400 Commonweal th Drive, Warrendale, PA 15096.) (Nongovernment standards and other publ ications are normally available from the Organizations which prepare or which distribute the documents. These documents al so may be available in or throu
27、gh 1 i braries or other informational servl ces. 1 2.3 Order of precedence. In the event of a conflict between the text of this specification and the references cited herein (except for associated detail specifications, specification sheets or MS standards), the text of this specification shall take
28、 precedence. Nothing in this specification, however, shall supersede applicable laws and regulatlons unless a specific exemption has been obtained. 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MI L-D-8683C 3; REQUIREMENTS 3.1 Selection of specif
29、ications and standards. Specifications and standards for necessary commodities and services not specified herein shall be selected in accordance- with MIL-STD-143. 3.2 Design. The insallation of an aircraft gaseous oxygen system shall comprise, as required: cylinders, tubing, fittings, filler valves
30、, relief valves, check valves, gages, regulators, portable units, adapters, mask to regulator hoses, brackets, shutoff valves, and al 1 other necessary i tems specified herein and required for a complete installation. The installation shall provide for replenishing the oxygen supply by connecting an
31、 external filling source directly to the filTing valve which shall be located such that fi 11 ing from a portable servicing trai ler can easily be accomplished by servicing personnel standing on the gr0un.d outside of the aircraft, 3.3 Oxygen systems. 3.3.1 Systems utilizing oxygen delivery equipmen
32、t. Aircraft having flight ceilings over 10,000 feet (3048 metres), but not over 50,000 feet (15,240 metres) of al ti tude and aircraft that have the capabi 1 i ty of descending from altitudes above 50,000 feet (15,240 metres) to 4Zi0O0 feet (12,801 metres) or lower immediately fol lowing a decrompre
33、ssion shall be provided with an installed oxygen system. This oxygen system shall have supply, necessary delivery, and crew station equipment to support all aircraft occupants. 3.3.1.1 Fighter and attack aircraft supply. Fighter and attack aircraft shall have an oxygen system of sufficient Capacity
34、to supply the entire crew for the total duration of any specified design mission The oxygen supply system shaTl be sized to ensure mission completion in the event of loss of cabin pressure enroute to or at the combat zone. If applicable, the oxygen system shall be sized to include range extension du
35、e to auxiliary fuel stores and/or aerial refueling. 3.3.1.2 Bomber aircraft supply. Bomber aircraft shall have an oxygen system of sufficient capacity to supply breathing oxygen to the entire crew for 75 percent of the duration of the longest specified design mission, or to the entire crew for the t
36、otal time the cabin altitude is above 10,000 feet (3048 metres), whichever condition establishes the largest amount. The oxygen supply system shall be sized to ensure mission completion in the event of loss of cabin pressure enroute to or at the target. If applicable, the oxygen system shall be size
37、d to include range extension due to auxiliary fuel stores and/or aerial refueling. 3.3.1.3 Transport aircraft supply. Transport aircraft shall have an oxygen system of sufficient capacity to supply all the primary crew members and al 1 of the passengers with breathing oxygen whenever the cabin al ti
38、 tude exceeds 10,000 feet (3048 metres). In the event of loss of cabin pressure, the oxygen system shall provide the full primary aircrew with breathing oxygen for at least 50 percent of the design mission duration. The passenger oxygen supply shall be dispensed from a continuous flow system and sha
39、ll have sufficient capacity to provide breathing oxygen to a full passenger load for 50 percent of the design mission duration or for a shorter period if so specified by the acquiring activity, but in no case for less than 15 minutes. 5 Provided by IHSNot for ResaleNo reproduction or networking perm
40、itted without license from IHS-,-,-MI L-D-8683C When therapeutic oxygen capability is specified, a supplemental quantity shall be included within the passenger oxygen supply. Therapeutic oxygen usage shall be independent from passenger oxygen usage and the quantity shall be adequate for 100 percent
41、of the design mission duration plus two hours to allow for patlent loading and unloading. * 3.3.1.4 Mission specialist and training aircraft supply. Mission specialist and training aircraft shall have an oxygen system of sufficient capacity to supply the entire flight crew, mission specialist traine
42、es, and any passengers (if appl icable) with breathing oxygen whenever the cabin altitude exceeds 10,000 feet (3048 metres). The flight crew may need additional oxygen supply for flight above 35,000 feet (10,668 metres), inflight refueling, and night flight. The oxygen system shall support all aircr
43、aft occupants during depressurization at cabin al ti tudes and durations as specified by the acquisition activity. 3.3.2 High altitude aircraft supply. Aircraft having a sustained flight capability above 50,000 feet (15,240 metres), or the requirement to remain above 42,000 (12,801 metres) for a per
44、iod over 5 minutes, but not equipped with emergency pressurization capsule provisions, shall be provided with an installed oxygen system design to support high altitude pressure suits and helmets, or pressure breathing masks and counter pressure garments, as appropriate. The quantity shall be adequa
45、te to provide for 100 percent oxygen for the entire mission, including, if appropriate, a period of oxygen breathing at ground level prior to flight. In addition, provisions shall be made for the use of preisure breathing masks during flight operations at lower al ti tudes r 3.3.3 Systems utilizing
46、capsules. The pressurization requirements and the oxygen requirements shall be as specified in MIL-C-25969 or MIL-A-23121, as applicable. The system to be installed shall be capable of meeting the specified mission profile. 3.3.4 Portable oxygen systems. When crew mobility within the aircraft is req
47、uired, as is normally the case in bomber and cargo aircraft, portable oxygen systems shall be provided in a ratio not less than one system for two crew- members. In those aircraft, at least one portable oxygen system shall be provlded in each compartment of the aircraft, including lavatories. Smoke
48、masks suitable for respiratory and eye protection shall be available for use by the pilot and any other cri tical crew member and be usable with the crew station regulator as well as with the portable systems. Portable oxygen systems shall be selected in accordance with 3.6.13. 3.3,5 Emergency oxyge
49、n. Aircraft equipped with a seat pan or back pack emergency oxygen supply, as specified in MIL-0-27335 or MIL-S-81018 or an equivalent emergency oxygen supply, shall be completely independent of the aircraft .oxygen supply system. The emergency oxygen supply system will normally remain with the crewmember in the event of departure from the aircraft and subsequent descent via parachute. When the emergency oxygen is attached to the seat, separation from the seat shall not occur above
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