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_______ BE USED WHEN HANDLING THE UNIT. FAILURE TO OBSERVE ELECTROSTATIC DISCHARGE PRECAUTIONARY PROCEDURES WHEN HANDLING THE IRU MAY RESULT IN DEGRADATION OR FAILURE OF THE IRU. THE UNIT CONTAINS HIGH VOLTAGE DEVICES. THE UNIT COVER SHOULD NOT BE REMOVED EXCEPT IN THE OVERHAUL SHOP
 B.  The IRU weighs 42.4 lbs. It consists of 3 laser gyros, 3 accelerometers, 9 circuit cards, a power supply and a chassis assembly. The two IRU's are located in the main equipment center, E3-5.
 C.  The IRU is interfaced with airplane wiring through a triple section connector of which only the two lower sections are used. Two holddown hooks are used to secure the IRU on its mount.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
28V MEMORY 15V FAULTBALL
CONTROL
F
WATCHDOGTIMER
DECODERDRIVERS
G
FREQ/
ANALOG
CONV

DATA
BUS 3
XMTR

OUTPUTDRIVERS
DATA
BUS 2
XMTR

DATA
BUS 1
XMTR

CONINGCORRECTION
UP/DOWN
COUNTER CONT
D
A
CONT
CONT MUX
G
INTEGRATOR
INTEGRATOR
INTEGRATOR
BUFFER
UP/DOWN DIVIDER
COUNTER
GROUND SPEED
VERT SPEED
ALT RATE COMPUTE
WIND
INERTIALNAVIGATION TRUE HDGMAGNETICDEV. MAP
SOFTWAREHARDWARE

OUTPUT OUTPUT
REGISTER REGISTER

E
COMPENSATE COMPENSATE
ACCEL GYRO

ATT RATE ACCELLINEAR
COMPUTEATTITUDE
PITCH
ROLL YAW
E
OUTPUT & FORMATTING

ALONG TK HRZ ACCELBODY LATERAL ACCELBODY LONGIT ACCELBODY NORMAL ACCELBODY PITCH RATEBODY ROLL RATEBODY YAW RATECROSS TK HRZ ACCELDRIFT ANGLEE-W VELOCITYFLIGHT PATH ANGLEFLIGHT PATH ACCELGROUND SPEEDINERTIAL ALTITUDEINERTIAL VERTICAL SPDMAGNETIC HEADINGPRESENT POS-LAT/LONGROLL ANGLEROLL RATETRACK ANGLE RATETRACK ANGLE TRUETRACK ANGLE MAGVERTICAL ACCELWIND DIRECTION TRUEWIND SPEEDBUILT IN TESTLAT/LONG TRUE HEADINGDISCRETES MAG HDG
FAULT
F
TEST SW
28V 15VELAPSED TIME IND
BP
115V AC 1

RECT AC
5
CONTROL
11LEVELDETECT
28V DC 7 HIGH DC
8
VOLTAGE
MP
MODE 1

F1
MSU

MODE 2
F2 TEST SW DAA REMOTE TEST
ISDU E9
A2DISCRETE
MOUNTING
E

INTFC
A3
PROGRAM POSITION A4
PINS SDI A5
A1
DADC-1 K4 (IRU-1) K5
1
SYSTEMSELECT
RSV J13
DADC-2 J10 (IRU-2) J11
1
A8
A9
FMC  LATITUDE
LONGITUDEMAGNETIC HDGDATA SEL LOGICISDU C5
C6  (SELECTS THELASTINITIALIZATION
A13 DATA) A14
RSV INERTIAL REF UNIT (E3-5)
1
ONLY ONE DADC IS CONNECTEDTO EACH IRU
IRU SchematicFigure 10
DITHERDRIVE LASER
TEMP
ELAPSED

SENSOR
TIME IND

GYRO X
TEMPGYRO YE
SENSOR (SEE X)
TEMP GYRO Z SENSOR (SEE X)
TEMP X SENSOR ACCLRM
TEMP Y SENSOR ACCLRM
TEMPZ SENSOR ACCLRM
OSC
ALT/ALT RATE/TRUE AIRSPEED

MP
D1
D3
D2
E8
E13E11E12E10
G4
G5G6
C10C11
E5E6
G7G8

ISDURSV
ALIGNON DCDC FAIL MSU FAULT
RSV FMC,DAA,ISDU,FCC,A/T
FCC
DAA,HSI

A 737-300/400/500MAINTENANCE MANUAL
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
 D.

E.
F.
G.
H.
I.
A 737-300/400/500MAINTENANCE MANUAL
The front panel of the IRU has a fault ball indicator, an interface test switch, and a total time indicator.
 (1)  
The BITE fault ball indicator shows black for an operational IRU and yellow for a failed IRU. The fault ball indicates a failure that could cause erroneous outputs. Other failures detected by BITE, which do not affect the outputs are stored in BITE memory.

 (2)  
Pushing the test switch activates the ISDU annunciator discretes for 2 seconds, then IRU digital failure words for 8 seconds. After 10 seconds and until the switch is released, the IRU outputs canned test data for observation in the flight deck. The test may be performed in the NAV or ALIGN mode. The test is inhibited in the NAV mode whenever the ground speed is greater than 20 knots and in the ATT mode. Some displayed test outputs are:
　
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