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AIR DATA INERTIAL REFERENCE UNIT (ADIRU) FOR AIRBUS A340 CIVIL AIRCRAFT. THE ADIRU IS A KEY COMPONENT OF THE INTEGRATED AIR DATA INERTIAL REFERENCE SYSTEM, WHICH SUPPLIES AIR DATA (AIRSPEED, ANGLE OF ATTACK AND ALTITUDE) AND INERTIAL REFERENCE (POSITION AND ALTITUDE) INFORMATION TO THE PILOTS ELECTRONIC FLIGHT INSTRUMENT SYSTEM DISPLAYS, AS WELL AS OTHER SYSTEMS ON THE AIRCRAFT, SUCH AS THE ENGINES, AUTOPILOT, AIRCRAFT FLIGHT CONTROL SYSTEM AND LANDING GEAR SYSTEMS. AN ADIRU ACTS AS A SINGLE, FAULT TOLERANT SOURCE OF NAVIGATIONAL DATA FOR BOTH PILOTS OF AN AIRCRAFT. MANUFACTURED BY HONEYWELL INC IN THE USA.

A VERTICAL GYROSCOPE THAT IS AN ELECTRICALLY DRIVEN GYRO THAT SPINS ABOUT A VERTICAL AXIS. IT SUPPLIES THE REFERENCE FOR THE AUTOMATIC FLIGHT CONTROL AND FLIGHT INSTRUMENTS OF AN AIRCRAFT ABOUT THE ROLL (AILERON) AND PITCH (ELEVATOR) AXIS. THE ELECTRICALLY DRIVEN GYRO HAS FULL FREEDOM IN ROLL. IT HAS -85 TO +85 DEGREES FREEDOM OF PITCH. THERE IS AN ERECTION SYSTEM TO KEEP THE ROTOR SPIN AXIS VERTICAL. THE VERTICAL GYRO HAS TWO SYNCHROS TO DETECT THE MOVEMENT OF THE AIRCRAFT ABOUT THE ROLL AND PITCH AXES. THE GYRO ALSO HAS CIRCUITS THAT MONITOR THE FUNCTIONAL OPERATION OF THE INTERNAL COMPONENTS.

A PRIMARY FLIGHT DISPLAY THAT DISPLAYS AIRSPEED, ALTITUDE AND INFORMATION TO THE PILOT ON AN AIRCRAFT. THE DISPLAY UTILIZES FIVE PUSH BUTTONS AND TWO SCROLL KNOBS FOR CONTROL OF THE UNIT. THERE IS NO ON/OFF BUTTON AND POWER IS SUPPLIED THROUGH THE AIRCRAFTS DC BUSSING SYSTEM. THE SYSTEM INCLUDES THREE ACCELEROMETERS, THREE RATE SENSORS AND A PILOT/STATIC SYSTEM.

AN AIRCRAFT DISPLAY UNIT, USED TO SUPPLY FORMATS FOR FLIGHT, NAVIGATION AND ENGINE INFORMATION. IT IS A FULL COLOUR FLAT-PANEL DISPLAY LOCATED IN THE AIRCRAFT COCKPIT.. THE UNIT COMPRISES OF A FRONT ELECTRONIC ASSEMBLY AND A REAR ELECTRONIC ASSEMBLY AND IS RACK MOUNTED. THREE CONNECTORS ON THE REAR ELECTRONIC ASSEMBLY MATE TO CONNECTORS IN THE RACK. THE FUNCTION OF THE REAR ELECTRONIC ASSEMBLY IS TO COLLECT AND CONVERT SIGNALS FROM THE WEATHER RADAR, ENGINE AND OTHER INTO DIGITAL SIGNALS WHICH ARE DISPLAYED ON THE FRONT ELECTRONIC ASSEMBLY. THE DISPLAY DATA IS SHOWN ON AN AMLCD IN FRONT OF A FLUORESCENT LAMP. DIMENSIONS: 302 MM L X 196 MM W X 259 MM H. WEIGHT (MAXIMUM): 9.3 KG.

AN ACCELEROMETER WHICH IS USED FOR TACTICAL NAVIGATION APPLICATIONS INCLUDING TACTICAL MISSILE AND SMART BOMB PROGRAMS. THE ACCELERATION IS MEASURED AS A FUNCTION OF THE FREQUENCY DIFFERENCE BETWEEN TWO VIBRATING QUARTZ BEAMS. FREQUENCY OUTPUT FOR THE DIRECT INTERFACE TO DIGITAL ELECTRONICS. INTEGRAL TWO MOUNTING FLANGE. HERMETICALLY SEALED CASE. INTERNAL TEMPERATURE SENSOR FOR THERMAL COMPENSATION. CASE MATERIAL OF STAINLESS STEEL. WEIGHT 12 GRAMS, SIZE 0.8 INCH DIAMETER AND 0.42 INCHES HIGH.