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|  MIL-R-70503A(AR)
3.5.2.2.1.3 Distribution of weight. The distribution of
weight between right and left launchers shall not be out of
balance by more than five rockets except for asymmetrical loading
resulting from damage outboard of the operations units. The
firing order of each type of rocket within a launcher shall be
controlled to minimize lateral center of gravity shifts within the
launcher.
3.5.2.2.1.4 Malfunction indication. An equipment status
indicator shall be provided on each LRU. The equipment status
indicator shall be a go/no go device and shall be such as to hold
the last result if power is interrupted or removed, and shall be
on the surface of the OU/RMS, visible to the mechanic when the
equipment is installed in the aircraft. The equipment status
indicator on the DU/RMS shall be located on the back of the DU/RMS
and is visible only when the DU/RMS is removed from the aircraft.
The BIT provisions shall also provide for driving a remote
indicator. This output shall be such that a signal of 28 4 Vdc
indicates a go condition and a signal of 0.5 Vdc indicates a
no-go condition.
3.6 Environmental conditions. The system shall operate and
meet the performance requirements of 3.5.2 under any of the
environmental conditions, or reasonable combination of these
conditions, as specified below:
3.6.1 Natural environments. The components of the RMS
subsystem shall be capable of operation and storage in the
worldwide environments as specified below:
0-20,000 feet;
Operating:
3.6.1.1 Temperature-Altitude.
nonoperating and storage: 0-50 ,000 feet.
3.6.1.2 Temperature.
a. Operating.
(1) Display Unit: -65 to +125F
(2) Operations Unit: -65 to +160F
b.
Nonoperating and storage.
(1) Display Unit: -65 to +160F
(2) operations Unit: -65 to +160F
3.6.1.3 Humidity. Operation after exposure to 149F and
relative humidity to 95 percent.
3.6.1.4 Sand and dust. Operation after internal and external
exposure to sand and dust test.
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