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 D.  Each IRU contains three laser gyros and three accelerometers. These sense angular rates and linear accelerations, respectively. The sensed data is resolved to local vertical coordinates and combined with air data inputs to compute the following:
 (1)
position (latitude, longitude)

 (2)
attitude (pitch, roll, yaw)

 (3)
true and magnetic heading

 (4)
windspeed and direction

 (5)
velocity

 (6)
accelerations

 (7)
angular rate data

 (8)
altitude

 E.  The IRS outputs are displayed on the flight instrument system displays. They are also displayed on the flight management computer system control display unit (FMCS-CDU) (Ref 34-62-01). Preselected parameters are also displayed on the inertial system display unit (ISDU).
 2.  IRS Theory of Operation
_______________________
 A.  General (Fig. 3)
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A 737-300/400/500MAINTENANCE MANUAL
AFT OVERHEAD PANEL 
SEE  G  H  FORWARD OVERHEAD 
PANEL 
PILOTS'  SEE  C 
LIGHTSHIELD 
SEE  J 
CAPTAIN'S PANEL  INERTIAL REFERENCE 
SEE  D  E  FIRST OFFICER'S PANEL  UNIT 1 AND 2 
SEE  D  E  SEE  A 
FORWARD 
ELECTRONICS  P10 PANEL 
PANEL  SEE  I 
SEE  F 
E1 RACK 
FLIGHT COMPARTMENT 
DIGITAL/ANALOG 
ADAPTER 1 AND 2  E3 
SEE  B  E2 RACK  RACK 
MAIN EQUIPMENT CENTER 

FAULT INDICATOR

TOTAL TIME YELLOW = FAULT
INDICATOR BLACK = OK
1
TEST SWITCH

INERTIAL REFERENCE UNIT
(IRU)

A DIGITAL/ANALOG ADAPTER (DAA)
AIRPLANES WITH -110 IRU's AND SUBSEQUENT;
1
NO FAULT BALL INDICATOR IS INSTALLED. THE B
CHASSIS INDICATOR HOLE CONTAINS A PLUG.
Inertial Reference System - Component Location Figure 1 (Sheet 1)
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NORMAL IRS TRANSFER SWITCH

Inertial Reference System - Component Location
Figure 1 (Sheet 2)

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A 737-300/400/500MAINTENANCE MANUAL

CONTROL DISPLAY UNIT
(CDU)

 

 

IRS MODE SELECT UNIT
(MSU)

FLT CONT  ELEC 
IRS  APU 
FUEL  OVHT/DET 

IRS MASTER CAUTION UNIT IRS MASTER CAUTION LIGHT

 

Inertial Reference System - Component Location
Figure 1 (Sheet 3)

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IRS Block Diagram
Figure 2

A96121
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