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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 CONTROL DISPLAY UNIT (CDU) THAT PROVIDES AN INTERFACE TO THE FLIGHT MANAGEMENT COMPUTER SYSTEM (FMCS) WHICH HOLDS THE NAVIGATION DATABASE. THE FILGHT CREW USE THE CDU TO ENTER ROUTE AND PERFORMANCE DATA FOR THE FLIGHT. IT HAS THE ADDITIONAL CAPABILITY TO FUNCTION AS AN INDEPENDENT SOURCE OF NAVIGATION. IN THIS MODE THE CDU PROVIDES LATERAL NAVIGATION FROM THE FMC. THIS ALLOWS THE CREW TO MODIFY THE FLIGHT PLAN IN FLIGHT WHEN REQUIRED. THE INFORMATION IS SHOWN AS A DIGITAL DISPLAY.

PANEL CONTROL ASSEMBLY FOR BOEING 737 CIVIL AIRCRAFT. THE AUTOMATIC FLIGHT CONTROL SYSTEMS (AFCS) CONSIST OF THREE SYSTEMS: DIGITAL FLIGHT CONTROL SYSTEM (DFCS), YAW DAMPER SYSTEM & AUTOTHROTTLE SYSTEM. THE DFCS INCORPORATES TWO SPERATE CHANNELS. EACH CHANNEL CONTROLS THE PITCH AND ROLL AXES AND PROVIDES MACH TRIM AND SPEED TRIM CONTROL. THE MODE CONTROL PANEL IS MOUNTED ON THE GLARE SHIELD, ACCESSIBLE TO BOTH PILOTS. THE MCP CONSISTS OF A METAL HOUSING UNIT CONTAINING CONTROL SWITCHES, INDICATORS AND ELECTRONIC CIRCUITS ASSOCIATED WITH CONTROL FUNCTIONS GENERATED BY THE UNIT AND DISPLAYS OF STATUS AND MODES GENERATED BY THE FLIGHT CONTROL COMPUTER. THE FRONT PANEL OF THE UNIT IS EDGE LIGHTED. THE PANEL ALSO PROVIDES CONTROL OF PRESET HEADING, PRESET COURSE, ALTITUDE SELECT ENGAGE CONTROL, SPEED SELECTION AND VERTICAL SPEED SELECTION.

A VISUAL GUIDANCE SYSTEM (VGS). THE FUNCTION OF THE VGC IS TO PRESENT AIRCRAFT PERFORMANCE AND CONTROL INFORMATION TO THE PILOT WITHIN THE FORWARD FIELD OF VIEW. THIS IS DONE BY PROJECTING A CRT GENERATED IMAGE INTO THE FIELD OF VIEW VIA A REFLECTING COMBINER, SHEET OF GLASS. THE VGS CONSISTS OF A MODULAR AVIONICS UNIT (MAU), OVERHEAD UNIT AND COMBINER. THE MAU IS THE COMPUTER THAT RECEIVES AND PROCESSES AIRCRAFT SENSOR DATA, PILOT INPUT ETC TO THE OVERHEAD UNIT.

A CONTROL DISPLAY UNIT (CDU) THAT PROVIDES AN INTERFACE TO THE FLIGHT MANAGEMENT COMPUTER SYSTEM (FMCS) WHICH HOLDS THE NAVIGATION DATABASE. THE FILGHT CREW USE THE CDU TO ENTER ROUTE AND PERFORMANCE DATA FOR THE FLIGHT. IT HAS THE ADDITIONAL CAPABILITY TO FUNCTION AS AN INDEPENDENT SOURCE OF NAVIGATION. IN THIS MODE THE CDU PROVIDES LATERAL NAVIGATION FROM THE FMC. THIS ALLOWS THE CREW TO MODIFY THE FLIGHT PLAN IN FLIGHT WHEN REQUIRED. THE INFORMATION IS SHOWN AS A DIGITAL DISPLAY.