Pitot/Static System. Avionics. Single ADC LEFT PITOT TUBE AIR DATA COMPUTER RIGHT PITOT TUBE COPILOT ASI PILOT COPILOT ASI VSI PILOT

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1 Pitot/Static System Single ADC Avionics LEFT PITOT TUBE CO ASI RIGHT PITOT TUBE ASI TRANSPONDER FLIGHT RECORDER FLIGHT DIRECTOR AUTO CO CO VSI CABIN AIR PRESSURE VSI AURAL WARNING UNIT (MACH WARNING) AURAL WARNING UNIT (MACH WARNING) CABIN DIFFERENTIAL PRESSURE INDICATOR LEFT FORWARD RIGHT FORWARD LEFT UPPER RIGHT UPPER LEFT LOWER RIGHT LOWER Citation III/VI For training only 4A-

2 Pitot/Static System Dual ADC LEFT PITOT TUBE LEFT AURAL WARNING UNIT (MACH WARNING) RIGHT RIGHT PITOT TUBE ASI VSI BACKUP AIRSPEED INDICATOR OPTIONAL BACKUP IMETER CO VSI CO ASI CABIN AIR PRESSURE CABIN DIFFERENTIAL PRESSURE INDICATOR CO LEFT FORWARD RIGHT FORWARD LEFT UPPER RIGHT UPPER LEFT LOWER RIGHT LOWER 'S IMETER OPERATES PNEUMATICALLY IF ELECTRICAL MODE FAILS. 4A-2 For training only Citation III/VI

3 Avionics SPZ-8000 System ED-800 MFD SI-225S MACH AIRSPEED IND. ED-800 EADI ED-800 EHSI AL-80 CONTROL/DISPLAY WU-650 WEATHER RADAR R/T/A SI-225S MACH AIRSPEED IND. NAV DATA ED-800 EADI ED-800 EHSI RT-300 RADIO IMETER RECEIVER/ TRANSMITTER 2 RI-206S INSTRUMENT REMOTE DME VS-200 VERTICAL SPEED INDICATOR DC-80 DISPLAY WC-650 MG-86 MSD SYMBOL GENERATOR MC-800 MFD DC-80 DISPLAY VS-200 VERTICAL SPEED INDICATOR DME WC-650 WX NAV RECEIVER SG-68 SYMBOL GENERATOR NZ-8XX/9XX CD-800/80 CD-800/80 NZ-8XX/9XX SG-86 SYMBOL GENERATOR NAV RECEIVER AT-300 ANTENNA AT-300 ANTENNA PART OF CS-42 DUAL REMOTE COMPENSATOR AH-600 STRAPDOWN AHRU AH-600 STRAPDOWN AHRU PART OF CS-42 DUAL REMOTE COMPENSATOR OZ-800 OMEGA OZ-800 OMEGA FX-600 THIN FLUX VALVE OPTIONAL FX-600 THIN FLUX VALVE AZ-80 DIGITAL FZ-800 FLIGHT GUIDANCE ASCB GC-80 FLIGHT GUIDANCE FZ-800 FLIGHT GUIDANCE AZ-80 DIGITAL WU-870 WEATHER RADAR R/T/A WC-650 ELEVATOR AILERON RUDDER AIRCRAFT TRIM SYSTEM NOTES: NOT REQUIRED WITH -36 GENERATORS ARE INSTALLED 2 IF INSTALLED Citation III/VI For training only 4A-3

4 4A-4 For training only Citation III/VI

5 Avionics SPZ-650 Automatic Flight Control System SI-225S AIRSPEED INDICATOR EADI EHSI BACKUP BA-4 IMETER WU-650 ANTENNA AND RECEIVER/ TRANSMITTER DS-25A TAS/SAT/TAT INDICATOR ED-600 ELECTRONIC DISPLAY (MFD) EADI EHSI RMI MC-800 MFD RMI DC-8 DISPLAY CONTROL WX/MAP OZ-800 OMEGA SENSOR RIGHT SIDE SENSORS MG-605 MFD SYMBOL GENERATOR LEFT SIDE SENSORS BACKUP CONTROL WX/MAP DC-8 DISPLAY ASCB SG-605 SYMBOL GENERATOR SG-605 SYMBOL GENERATOR AZ-80 2 NZ-8XX/9XX FMS NAVIGATION CD-800 CONTROL DISPLAY UNIT 2 PC-500 AUTO RI-206S INSTRUMENT REMOTE SP-650 AUTO DL-800 DATA LOADER VN-800 VNAV FZ-500 FLIGHT DIRECTOR MD-500A MODE SELECTOR FD/FD2 2 FZ-500 FLIGHT DIRECTOR MS-500A MODE SELECTOR FLUX VALVE DUAL REMOTE COMPENSATOR FLUX VALVE 2 NOTES: OPTIONAL RAD SRN ATT 2 HDG HDG 2 ATT THROTTLE GO-AROUND TCS, DISENGAGE 2 CAN BE SINGLE OR DUAL SRN 2 MARKER BEACON RATE LRN GYRO ADF AOA MARKER BEACON ELEVATOR AILERON RUDDER RATE GYRO AOA ADF 2 Citation III/VI For training only 4A-5

6 4A-6 For training only Citation III/VI

7 Pitot/Static System Avionics On aircraft with a single air data computer (ADC), the left pitot tube supplies the ADC and the right pitot tube supplies the copilot s airspeed indicator. The aircraft has three independent static systems: pilot s, copilot s, and standby. Each system has a static port on the left and right forward fuselage. The pilot s system supplies static pressure to the ADC, while the copilot s system supplies the copilot s airspeed indicator, vertical speed indicator (VSI), the cabin air pressure controller, and the cabin differential pressure indicator. The standby system supplies the copilot s altimeter. On aircraft with dual ADCs, the left pitot tube supplies the No. ADC and the right pitot tube supplies the No. 2 ADC and the standby airspeed indicator. The three independent static systems each has a static port on the left and right forward fuselage. The pilot s system supplies the No. ADC, the copilot s system supplies the No. 2 ADC, cabin air pressure controller, and cabin differential pressure indicator. The standby system supplies the pilot s dual mode altimeter. On all aircraft, water drains in the static lines allow removal of accumulated water from the system. Water in the pitot lines drains through the pitot tubes. Electrically powered heating elements in the pitot tubes and static ports prevents ice accumulation (see Ice and Rain Protection). Citation III/VI For training only 4A-7

8 Air Data Computer The air data computer (ADC) receives pitot pressure (P T ) and static pressure (P S ) inputs from the pitot/static system and temperature data from a probe on the lower forward fuselage. The ADC converts and processes these inputs and provides as electrical signals: indicated airspeed (IAS) true airspeed (TAS) Mach number true air temperature (TAT) static air temperature (SAT) pressure altitude. The ADC provides these inputs to: airspeed indicator overspeed warning system altimeter altitude alerting system vertical speed indicator (dual ADC equipped) vertical navigation (VNAV) controller optional electronic flight instrument system (EFIS) symbol generator TAS/SAT/TAT indicator ATC transponder flight director computer autopilot computer optional flight data recorder. 4A-8 For training only Citation III/VI

9 Avionics Digital air data computers (DADCs) provide the same outputs as the ADCs. DADCs are microprocessor-based units that accept analog and digital inputs from the pitot/static system and TAT probe. They then provide analog and digital outputs to the flight instruments, navigation systems, flight director and autopilot, and flight data recorder. SPZ-650 The Honeywell SPZ-650 automatic flight control system (AFCS) combines the functions of an autopilot, flight director, yaw damper, and elevator trim system to provide automatic flight path and attitude control through the pitch, roll, and yaw axes. Various subsystems of the SPZ-650 AFCS include: air data system autopilot flight director system flight instrumentation (mechanical or optional EFIS) vertical and directional gyros radio altimeter weather radar. The flight control system receives aircraft attitude, position, and heading data from various sensors and navigation equipment. These data sources include: air data system airspeed, vertical speed, altitude directional gyro heading vertical gyro attitude (pitch, roll, and yaw) accelerometer acceleration navigation radios position in relation to navaids. Citation III/VI For training only 4A-9

10 Supplied with these inputs, the AFCS generates the appropriate pitch, roll, and yaw commands or cues to fly the aircraft from its actual attitude to a desired attitude. Flight instrumentation can be mechanical instruments that consists of conventional attitude director indicators (ADIs) and horizontal situation indicators (HSIs) or electronic flight instrumentation (EFIS) that uses cathode ray tubes (CRTs) and symbol generators (SGs) to displays the same information. SPZ-8000 The Honeywell SPZ-8000 is a fail-operational digital automatic flight control system (AFCS) that provides autopilot, yaw damper, flight director guidance, and trim functions. The complete system consists of: air data system dual flight guidance system (FGS) electronic flight instrument system (EFIS) optional multifunction display (MFD) optional flight management system (FMS) attitude and heading reference system (AHRS) weather radar system radio altimeter system. A bi-directional, high-speed avionics standard communications bus (ASCB) and private-line paths interface with the various subsystems and components to provide rapid data transfer. Supplied with the necessary inputs from the air data system, navigation sensors, and AHRS, the SPZ-8000 AFCS generates the appropriate commands and cues to automatically or manually fly the aircraft from its present attitude to a desired attitude. 4A-0 For training only Citation III/VI