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MIL-O-87226 (USAF) 30 April 1985 MILITARY SPECIFICATION

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MIL-O-87226 (USAF) 30 April 1985 MILITARY SPECIFICATION Downloaded from http://www.everyspec.com MIL-O-87226 (USAF) 30 April 1985 MILITARY SPECIFICATION OXYGEN SYSTEMS, AIRCRAFT, GENERAL SPECIFICATION FOR This specification is approved for use by the Department of the Air Force and is available for use by all Departments and Agencies of the Department of Defense 1. SCOPE 1.1 Scope. This specification establishes the development requirements and verifications for an aircraft oxygen system and its components. 1.2 Use. This specification cannot be used for contractual purposea without supplemental information relating to the unique requirements included herein. The supplemental information relates to system design around the normal and emergency mission profiles. 1.2.1 Structure. The required supplemental information is identified by blanks within the specification. Only those paragraphs applicable to the aircraft system under consideration shall be selected. Verification method(s) must be added to each selected requirement. For more effective designs, the oxygen systems are discussed in terms of aircraft missions. 1.2.2 Instructional handbook. The instructional handbook contained in Appendix A herein provides for this technical area the rationale for require- ments, guidance on document usage, and a lessons learned repository. The need for this information is identified by blanks within the generic requirements and verifications. 1.2.3 Physiological handbook. The use of oxygen on an aircraft supports the physiological requirements of crew member(s) and passenger (if applicable) for the intended missions (altitudes, air speeds and ranges). For these reasons physiological criteria is included in Appendix B for background information. 1.2.4 Existing military oxygen equipment. Existing oxygen equipment design information is provided in Appendix C. A future oxygen system or a modified existing system will usually be a composite of existing oxygen equipment and some newly developed equipment. Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to: ASD/ENES, Wright-Patterson AFB, OH 45433-6503 by using the self-addressed Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this document or by letter. FSC 1660 Downloaded from http://www.everyspec.com MIL-O-87226 (USAF) 1.3 Deviation. Any projected design for a given application which will result in improved system performance, reduced life cycle cost, or reduced development cost through deviation from this specification, or where the requirements of this specification result in compromise in operational capability, shall be brought to the attention of the procuring activity for consideration of change. 2. APPLICABLE DOCUMENTS 2.1 Government documents 2.1.1 Specifications, standards, and handbooks. Unless otherwise specified, the followlng speclflcatlons, standards, and handbooks of the issue listed in the current Department of Defense Index of Specifications and standards “ (DODISS) and the supplement thereto (if applicable) form a part of this speci- fication to the extent specified herein. SPECIFICATIONS (Specifications called out in the final specification shall be referenced here.) STANDARDS (Standards called out in the final specification shall be referenced here.) HANDBOOKS (Handbooks called out in the final specification shall be referenced here.) 2.1.2 Other Government publications. The following other Government publica- tions form a part of this specification to the extent specified herein. PUBLICATIONS (Other publications called out in the final specification shall be referenced here. ) (COpie8 of specifications, standards, handbooks, drawings, and publications required by manufacturers in connection with specific acquisition functions should be obtained from the contracting activity or as directed by the contracting officer.) Downloaded from http://www.everyspec.com MIL-O-87226 (USAF) 2.2 Other publications. The follow;.ngdocuments form a part of this speci- fication to the extent specified herein. The issues of the documents which are indicated as DOD adopted shall be the issue in the current DODISS and the supplemer[t thereto, if applicable. (Other publications called out in the final specification shall be referenced here. ) (Technical society and technical association specifications and standards are generally available for reference from libraries. They are also distributed among technical groups and using Federal agencies.) 2.3 Order of precedence. In the event of a conflict between the text of this specification and the references cited herein, the text of this specification shall take precedence. 3. REQUIREMENTS 3.1 System description. The oxygen system shall support crewmembers and type personnel for the normal and emergency intended missions of the aircraft. The oxygen system consists of the following functional sub- systems as applicable: oa. Crew oxygen system (3.2.2.1) ob. Paratroop oxygen system (3.2.2.2) OC. Mission specialist oxygen system (3.2.2.3) od. Aeromedical oxygen system (3.2.2.4) oe. HALO oxygen subsystem (3.2.2.5) of. Passenger oxygen (3.2.2.6) og. Ejection seat bailout oxygen subsystem (3.2.2.7) oh. Manual bailout oxygen (3.2.2.8) oi. Walk-around oxygen assemblies (3.2.2.9) ojo Aircraft firefighter portable assembly (3.2.2,10.1) ok. Chemical defense protective breathing assemblies (3.2.2.10.2) 01. Aircraft pressure suit provisions (3.2.2.11) Downloaded from http://www.everyspec.com MIL-O-87226 (USAF) 3.2 Performance requirements 3.2.1 System characteristics. In the design and installation of the func- tional subsystems and equipment groups of the entire aircraft oxygen system, the following system characteristics apply as requirements throughout: . 3.2.1.1 Physical characteristics. The physical characteristics of the aircraft oxygen system are oxygen supply source with associated aircraft interfaces, oxygen SUpply delivery plumbing lines with associated valves, regulators as required for proper delivery of oxygen to on-board personnel, plumbing, hoses, and face masks to provide physiological protection to on-board personnel, portable oxygen equipment for special purposes and emergencies, and . 3.2.1.2 Operational characteristics. The aircraft oxygen system must provide effective operational characteristics that are , 3.2.1.3 Electrical characteristics. The aircraft oxygen system electrical characteristics shall effectively interface with the aircraft electrical subsystem and shall consist of ● 3.2.1.4 Environmental conditions. The aircraft oxygen system shall be designed such that it is qualified to the environmental extremes as follows: . 3.2.1.5 Transportability. Certain transportability features are desired in the design of the oxygen system components. The oxygen system components are . The transportability features should consist of ● 3.2.2 Functional subsystem characteristics. In the design and installation of the functional subsystems and equipment groups of the entire aircraft oxygen system, the following oxygen subsystems and equipment shall be used: ● 3.2.2.1 Crew oxygen system. A crew oxygen system shall be provided that is regulated to the cockpit or cabin pressure altitude and which consists of the following delivery features . A warning shall be provided detectable by all crewmembers that functions when ● The pri- mary oxygen supply for crewmembers who operate and monitor the aircraft and its subsystems shall be from a separate supply source than for other personnel (if applicable) and shall have features . The crew oxygen system supply shall be sized to provide pressure demand regulated oxYgen for all crewmembers at an average flow rate of litres/hour per crewmember for a minimum of hours. The oxygen system distribution lines shall operate under an ‘al pressure range of psi and shall allow a maximum gaseoue flow rate throughout of , 3.2,2.1.1 Crew controls and displays. Each crewmember shall have oxygen system displays conaistlng of and controls consisting of . Emergency quick-donning mask assemblies shall incorporate the intercommunication microphone and headset open to all crewmembers, Test controls shall be provided to check for the proper functioning of all lighted displays, indicators, instruments, and ● The controls and — 4 Downloaded from http://www.everyspec.com MIL-O-87226 (USAF) displays provided shall be functionally compatible with the crew oxygen system, Emergency oxygen system controls and displays consisting of shall be provided to alert the appropriate personnel of . 3.2.2.1.2 Physiological features. The crewmember respiratory provisions at normal conditions (NTPD) of sea level altitude, 760 mmHg, 70”F and dry shall be a minimum baseline minute volume per crewmember of litres/minute (NTPD). The crewmember respiratory provisions at high demand flow for breath- ing while under high workloads and/or stress levels shall be Iitresl minute (NTPD) per crewmember. The crewmember respiratory pr=ions for instantaneous peak demand flow for very high stress or workload shall be litres/minute (NTPD) per crewmember. A pressure of in the face- piece and a pressure range of in the inlet delivery tubing shall acti- vate inhalation and exhalation features. 3.2.2.1.3 Oxygen delivery features. The oxygen concentration for air dilu- tion shall be provided to each crewmember within the following limits: . Positive mask pressure is required above ~eet cabin altitude and for . To provide user comfort and to m-e the possi- bility of hyperventilation due to the
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