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|  MIL-N-81604C(AS)
Para 3.5.2.2.2
(cont)
The mount shall be attached to the airframe by three 1/4-inch
bolts which shall have tensile properties of A286 stainless steel
or better.
3.5.2.2.3 Accuracy - The IMU mount shall have adequate provisions
for mechanically aligning the IMU in the aircraft about the three
major axes. Means shall be provided for an adjustment range of
at least 1 in each of the three axes and an adjustment accuracy
of 30 arcseconds. The 30-arcsecond accuracy shall include the
IMU inserted in the mount.
3.5.2.2.4 Adjustments - The coarse alignment of the mount is
afforded through the use of slotted airframe attachment holes.
The fine adjustment of the pitch, roll, or azimuth axis is
accomplished by shimming between the index pad and the steel
Increments of 0.002 to 0.524 shall be available in
sleeve.
accompanying shim kits.
3.5.2.2.5 Reinsertion Requirements - Provisions shall be made
for the removal and re-insertion of the IMU to an accuracy of
20 arcseconds.
3.5.3 Power Supply Unit (PSU)
3.5.3.1 Function - The function of the PSU shall be to convert
*
primary aircraft power to the required equipment d-c voltages
(refer to table XIX). Provisions shall be made to incorporate a. *
battery in the PSU. The battery shall provide power transient
protection for the equipment and shall maintain equipment opera-
tion for 10 seconds after a power dropout in flight and for 5 sec-
onds when the aircraft is on the ground or on a carrier deck.
3.5.3.2 Input Power - Input power shall conform to MIL-STD-704.
Maximum steady-state input required, exclusive of the CAU, shall be
545 watts with transient peak power requirements of 740 watts for
a duration of 30 seconds or less. In addition to steady-state
loading by the PSU, the following switched loads shall not exceed
the power as specified:
a.
Battery Charger - Three-phase, 20-watt balanced
resistive load. See table XX for the recharge-
interval required under different conditions:
103
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