 |
|||
|
Page Title:
Systems utilizing oxygen delivery equipment |
|
||
| ||||||||||
|
|  MIL-D-19326H
2.3 Order or precedence. In the event of a conflict between the text of this
document and the references cited herein (except for related associated detail
specifications, specification sheets or MS standards), the text of this document
shall take precedence. Nothing in this document, however, shall supersede
applicable laws and regulations unless a specific exemption has been obtained.
3.
REQUIREMENTS
3.1 Selection of specifications and standards. Specifications and standards
for necessary commodities and services not specified herein shall be selected in
accordance with MIL-STD-970.
* 3.2 Design. The installation of an aircraft liquid oxygen system shall
comprise, as required, liquid oxygen converters, tubing, fittings, filler valves,
build-up and vent valves, relief valves, check valves, quantity gauges,
regulators, portable units, adapters, mask to regulator hoses, brackets, shut-off
valves, and all other necessary items specified herein and required for a complete
installation. For permanently installed converters, the filler valve shall be
located such that filling from a portable servicing trailer can be easily
accomplished by servicing personnel standing on the ground outside of the
aircraft. Removable converters shall be capable of being removed and replaced in
the aircraft within a 5 minute time period. Sufficient access shall also be
provided for the removable converters to permit filling of the converter by
conventional means when they are installed in the aircraft. Components of the
oxygen system shall not be installed where they will be subjected to temperatures
in excess of that specified in the individual component specifications, and no
part of the system shall be installed in an area which will be subjected to a
temperature in excess of 260 F {126.6 C).
3.3 oxygen systems.
* 3.3.1 Systems utilizing oxygen delivery equipment. Aircraft having flight
ceilings over 10,000 feet (3,048 meters] shall have oxygen supply and the
necessary delivery and personal equipment to support the physiological needs of
all aircraft occupants.
3.3.1.1 Fighter and attack aircraft supply. These aircraft shall have an
oxygen system of sufficient capacity to supply the entire crew for the total
duration of any specified design mission. The oxygen supply system shall 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 due 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 total time the cabin altitude is above 8,000 feet (2,438 meters),
whichever condition establishes the larger amount. The oxygen supply system shall
be sized to ensure mission completion in the even of loss of cabin pressure
enroute to or at the target. If applicable, the oxygen system shall be sized to
include range extension due to auxiliary fuel stores and/or aerial refueling.
5
|
|
Privacy Statement - Press Release - Copyright Information. - Contact Us |
Click
here for thousands of PDF manuals