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MIL-N-81497A(AS)
(Continued)
3.5.2.8
Function
Type
Designation
Cable to
MS3112-E-24-61PX
3J1
Aircraft
Cable to Computer,
MS3112-E-24-61PY
3J2
Navigation.
Edge Lighting - Edge lighting shall be supplied to
3.5.2.9
the Control, Gyroscope Assembly from external sources. Edge lighting
shall be 5 to 28V, variable, 400 Hz, single phase.
Advisory Lamp Excitation - All advisory lamps shall
3.5.2.10
be energized with +18 V DC, however, the TEST, SYSTEM FAIL< ALIGN and
BTRY IN USE lamps shall be energized by a +28V DC non-power interrupt
supply generated within the Power Supply Unit.
Lamp Check Function -  The Control, Gyroscope Assembly
3.5.2.11
shall contain diode isolated clrcultry, to check all advisory lamps when
the equipment is operating upon application of an external +28V DC test
signal.
3.5.2.12
Control, Gyroscope Assembly Color - The Control,
Gyroscope Assembly iincludlng shell, front panel and controls shall
be lusterles gray No. 36231 as specified in FED-STD-595.
Control, Gyroscope Assembly Mounting - Mounting
3.5.2.13
shall be in accordance with MIL-C-6181.
Indicator, Position ID-1542/ASN-84 - The Indicator,
3.5.3
Position shall meet the followlng requirements.
Function -  The Indicator, Position shall be used to
3.5.3.1
display and manually update computer present position data for the INS.
It shall also be used to insert auxiliary data into the Computer,
Navigation,  as required.
Form Factor - Form factor of the equipment shall
3.5.3.2
conform to EI-554. Maximum envelope dimensions shall be 5.78 inches
by 5.75 inches by 6.0 inches,
3.5.3.3
Weight - The weight of the Indicator, Position
shall not exceed 4.85 pounds.
35

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