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|  MIL-D-19326H
* 3.3.1.7 Systems utilizing capsules. The pressurization requirements and the
oxygen requirements shall be as specified in MIL-E-87235 or MIL-A-23121, as
applicable. The system to be installed shall be capable of meeting the specified
mission profile.
* 3.3.1.8 Portable oxygen systems. When crew mobility within the aircraft is
required, as is normally the case in bomber and transport aircraft, portable
oxygen systems shall be provided in a ratio not less than one system for two
crewmembers. At least one portable oxygen system shall be provided in each
compartment of the aircraft including lavatories. Smoke masks suitable for
respiratory and eye protection with communications capabilities shall be available
for use by the pilot and any other critical crewmembers and be usable with the
crew station regulators well as with the portable systems. Portable oxygen
systems shall be selected in accordance with 3.6.14. A critical crewmember is any
crewmember that performs flight duties, all flight crewmembers including any
crewmembers that operate flight essential equipment for navigation, even if
located in the passenger compartment, and any crewmembers that must move about tO
dispense oxygen-equipment and check on passengers.
3.3.1.9 Emergency oxygen. Aircraft equipped with a seat pan or back pack
emergency oxygen supply, as specified in MIL-O-27335 or MIL-S-81018, or an
equivalent emergency oxygen supply, shall have such system completely independent
of the aircraft oxygen supply system. Any emergency oxygen supply system will
normally remain with the crewmember during ejection 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 an altitude of 15,000 feet
(4,571 meters).
3.4 Oxyqen quantity determination.
3.4.1 Oxygen flow requirements.
3.4.1.1 Respiratory provisions. The oxygen supply requirement shall be based
on an inspiratory minute volume (volume of gas per minute) of 15 liters per minute
(imp) (250 cu.cm/ s) per crewmember determined at BTPS conditions; i.e., body
temperature 98.6 F (37C), body pressure (cabin altitude), and saturated with
water vapor, 47 mm Hg (6.27 kPa). At normal conditions (NTPD) of sea level
altitude, 760 mm Hg (101.3 kPa), 70F (21.1C), and dry, the baseline minute
volume per crewmember is 13.35 lpm (223 cu.cm/s) (NTPD). For oxygen system
design, the baseline oxygen requirements given in Table I shall apply to all
aircraft containing 6 or more aircrewmembers. For intermediate altitudes not
listed in Table I, the oxygen requirements may be calculated from Figure 9. For
aircraft which contain less than 6 aircrewmembers, the design oxygen quantity
shall be increased by the multipliers given in Table II, which is estimated to
cover the 90th percentile of normal aircrew populations.
3.4.1.2 Flight demand provisions. Where aircrew duties impose more than routine
flight demands on the crew, the baseline oxygen quantity, after adjustment for
aircrew size, shall be increased by applicable percentages extrapolated from those
given in Table III. Some of these situations will not exist throughout the design
mission and they shall be applied only to the crewmember or members directly
affected and only for that period during which the increased demand is anticipated.
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