Dimensions (maximum):
Length ...................................... 12.76 in. (324.1 mm)
Width ....................................... 12.70 in. (322.6 mm)
Height
....................................... 7.62 in. (193.5 mm)
Weight (maximum) ..
................................
45.0 lb (21.1 kg)
Power Requirements:
IRU on AC
................................
115 V, 400 Hz, 135 W Max
DC required when operating on AC ...............
28Vdc, 1.1 WMax
IRUonDC ......................................
28 V dc, 116W Max
Mating Connector ............................. Cannon BKAD2-313-30001
Mounting ................................... Mounting Rack, Honeywell
Part No. 10088502-1OX
Inertial Reference Unit
Leading Particulars
Table 2-1
The IRU microprocessors perform computations required for:
● Primary attitude
. Present position
. Inertial velocity vectors
. Magnetic and true north reference
. Sensor systematic error compensation
The power supplies receive ac and dc power from the aircraft and backup
battery, supply power to the IRS, and provide switching to primary ac,
primary dc, or backup battery power.
The aircraft electronic interfaces convert ARINC and ASCB inputs for use
by the IRS. The electronic interfaces also provide IRS outputs in ARINC
and ASCB formats for use by the associated aircraft equipment.
A fault ball indicator and a manual INTERFACE TEST switch are mounted on
the front of the IRU and are visible when the IRU is mounted in an
avionics rack.
In a triple-IRS installation, IRU 3 provides IRS comparison monitoring
for the flight guidance system and also provides the FMS with a third
long range sensor.
The input and output information provided by the IRU is listed in
Table 2-2.
22-14-00
Page 103
Apr 15/93
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