ATA 34 B1 Navigation - Issue 6 January 2023 PDF

BOMBARDIER DHC 8-400 (PWC PW150) ATA 34 - NAVIGATION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY B1 MAINTENANCE TRAINING MANUAL Issue 6 - January 2023 Page 1 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS INTRODUCTION The navigation system has different sub-systems to supply o...

BOMBARDIER DHC 8-400 (PWC PW150) ATA 34 - NAVIGATION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY B1 MAINTENANCE TRAINING MANUAL Issue 6 - January 2023 Page 1 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS INTRODUCTION The navigation system has different sub-systems to supply other systems with the data that follows: • • • • • • Pitot and static air pressures Pitch and bank attitude and stabilized heading Microwave Landing System (MLS) azimuth and elevation Weather, ground proximity, location and threat status of other aircraft, and Above Ground Level (AGL) altitude Radio navigation Flight management GENERAL DESCRIPTION The navigation system has the sub-systems that follow: • • • • • • • • • Flight Environment Data Attitude and Heading System External Protection System VHF Navigation Automatic Direction Finding (ADF) Distance Measuring Equipment (DME) Air Traffic Control Transponder Global Positioning System Flight Management System (FMS) TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 2 of 500 BOMBARDIER DHC 8-400 (PWC PW150) • NAVIGATION SYSTEMS Radio Altimeter GENERAL DESCRIPTION CONTINUED VERY HIGH FREQUENCY NAVIGATION FLIGHT ENVIRONMENT DATA The Very High Frequency Navigation (VHF NAV) system receives radio signals to give the navigation data that follows: The Air Data System (ADS) supplies air data for indication and to other aircraft systems. The air data that is shown to the pilots and used for flight guidance is critical data. Thus, the ADS have three air data systems that operate independently, two primary and one standby. ATTITUDE AND HEADING SYSTEM The Attitude and Heading System (AHRS) supplies attitude and heading data to the Electronic Instrument System (EIS) indication and to other aircraft systems. The attitude and heading data that are shown to the pilots and used for flight guidance is critical data. Thus, the AHRS has three isolated attitude and heading data systems that operate independently, two primary and one standby channel. EXTERNAL PROTECTION SYSTEM Weather Ground proximity Location and threat status of other aircraft Above Ground Level (AGL) altitude Weather Radar Systems Ground Proximity Warning System (GPWS) Traffic Alerting and Collision Avoidance System II (TCAS II) TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY VHF OMNI-RANGE (VOR) The Very High Frequency Omni-range (VOR) ground stations form part of the Victor airways navigation system. The VOR gives guidance on any track to or from the station. INSTRUMENT LANDING SYSTEM (ILS) The Instrument Landing System (ILS) is an integrated system that gives the approach flight path to landing on a runway. The Automatic Direction Finding (ADF) system shows the magnetic bearing to a fixed Non-Directional Beacon (NDB). DISTANCE MEASURING EQUIPMENT It also gives other aircraft and ground stations with data relating to the aircraft identification and location. The external protection system has the sub-systems that follow: • • • VHF Omni-range (VOR) Instrument Landing System (ILS) AUTOMATIC DIRECTION FINDING The External Protection System (EPS) has different sub-systems to give visual and aural indications that relate to the conditions that follow: • • • • • • The airborne Distance Measuring Equipment (DME) measures the line of sight slant range from the aircraft to the DME ground station. It uses the slant distance data to calculate the ground speed and the time-to-go data. MODE S TRANSPONDER The Mode S Transponder system transmits a signal to identify the aircraft and its altitude data to Air Traffic Control (ATC) ground stations and to other aircraft equipped with Traffic Alert and Collision Avoidance System (TCAS). ATA 34 - NAVIGATION Issue 6 - January 2023 Page 3 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS GENERAL DESCRIPTION CONTINUED GLOBAL POSITIONING SYSTEM The Flight Management System (FMS), Global Positioning System (GPS), and VORTAC Position Unit (VPU) are completely self-contained within a single MultiFunctional Control Display Unit (MCDU). It is located in the forward left side of the flight compartment console. FLIGHT MANAGEMENT SYSTEM (FMS) The FMS along with other interfacing equipment in the aircraft gives the following functions: • • • • • Calculating the aircraft position and velocity Guidance for the Automatic Flight Control System (AFCS) Managing the aircraft flight path from origin to destination Tuning communication and navigation radios Make fuel management computations The FMS assists the pilots by automating many routine tasks and manual computations. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 4 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - NAVIGATION SYSTEM BLOCK DIAGRAM TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 5 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS FLIGHT ENVIRONMENT DATA The flight environment data system supplies air data for indication and to other aircraft systems. GENERAL DESCRIPTION The flight environment data system has the sub-systems that follow: • • Two primary air data system Standby air data instruments The air data that is shown to the pilots and used for flight guidance is critical data. Thus, the ADS has the three air data systems that operate independently, two primary and one standby. AIR DATA SYSTEM The primary Air Data System (ADS) senses and changes static pressure, pitot impact, dynamic pressure, and static air temperature to electronic data for use by the systems that follow: • • • • • • • Cabin Pressure Control Flight Guidance Flight Controls Indication Vmo/Mmo-Warning Navigation Power-plant Operation STANDBY AIR DATA INSTRUMENTS The standby air data system senses static pressure and pitot pressure to give altitude and airspeed indication independently of the primary air data system. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 6 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - FLIGHT ENVIRONMENT DATA BLOCK DIAGRAM TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 7 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM INTRODUCTION The primary Air Data System (ADS) senses and changes static pressure, pitot (impact) pressure, and static air temperature to electronic data for use by other systems. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 8 of 500 BOMBARDIER DHC 8-400 (PWC PW150) • • • • NAVIGATION SYSTEMS AIR DATA SYSTEM Calibrated airspeed (CAS) True airspeed (TAS) Maximum velocity in operation (VMO) Static Air Temperature (SAT) GENERAL DESCRIPTION The primary Air Data Systems (ADS1, ADS2) has the units that follow: • • • • • Air data computer Pitot-static probes Static temperature probe Pitot-static isolation valve Pitot-static isolation valve panel Each Air Data System (ADS1, ADS2) senses the data that follow: • • • • Static and pitot pressures Outside air temperature Barometric correction Probe heater failure The primary ADS has two sub-systems that operate independently to calculate the data that follows: • • • • • • • Static and pitot pressures Temperature Barometric correction Altitude Altitude rate Airspeed Maximum velocity in operation The Electronic Instrument System (EIS) shows the Air Data System (ADS 1, ADS 2) data that follow: • • Barometric correction in Millibars and in In Hg (Bcor) Barometric altitude corrected by barometric correction (Hc) TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 9 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS A standard atmosphere, where the barometric pressure, density, and temperature is known, is used to calculate an altitude that is relative to sea level. During standard atmospheric conditions, the altitude calculation is accurate. But, during non-standard atmospheric conditions, an altitude with a noticeably large error is calculated. The amount of error depends on the difference between standard and actual atmosphere conditions. AIR DATA SYSTEM GENERAL DESCRIPTION CONTINUED The ADS senses static and pitot air pressure and temperature. All other data is calculated. Each Air Data Computer (ADC1, ADC2) senses the static and pitot pressures through holes in the related pitot-static probe. The static pressure from the other pitot-static probe is averaged to give a more accurate static pressure sensing. A bird strike at the right side of the forward fuselage section can cause damage to the No. 2 primary pitot-static probe and to the secondary pitot-static probe. All air data indications can possibly malfunction because the ADC1 static pressure sensing is connected to the No. 2 pitot-static probe. An electrically controlled shutoff valve is a used to isolate ADC1 and pitot-static probe No. 2 static pressure. The NORM/ISOL push-button switch on the pitot-static isolation control panel is pushed to close the usually open shutoff valve. The pitot-static probes have an encased heating element with a self regulating power consumption feature to prevent ice accumulation on the pressure probes and help eliminate erroneous pitot and static measurements. Each pitot-static probe heater is controlled by a PITOT STATIC toggle switch on the ice protection panel. Air temperature data is supplied by an air temperature probe that changes its electrical resistance as the temperature of the air changes. The resistance value is supplied to the two ADCs. The static temperature probe has two resistor sensors. Each sensor is connected to one ADC in order to supply the aircraft system with two independent temperature values. The Indicated Outside Air Temperature (IOAT) measured by the two sensors is affected by airspeed. A recovery factor is set in each ADC and is used to calculate and compare, using the IAOT, the Static Air Temperature (SAT) and Total Air Temperature (TAT). TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY Each Index Control Panel - ICP1, ICP2 - has a BARO SET knob to change the barometric correction data that is supplied to its related ADC to calculate the barometric altitude and barometric setting indication. The barometric correction value is shown as millibars (MIL) or Inches of Mercury (IN). On aircraft with the millibars (MB) barometric correction value 823SO00017: The millibar barometric correction indication is set by ADC pin programming logic. When the ADC is not energized, the barometric correction value is saved in ADC Non Volatile Memory (NVM). The Proximity Sensor Electronic Unit (PSEU) supplies on ground or airborne data to each ADC to make sure that the ADC operational test and the Power On Self Test (POST) is done only while the aircraft is on the ground. The Air Data Computers (ADC) calculate Non Computed Data (NCD) if a primary data, such as static pressure (ps), pitot pressure (dp), or Outside Air Temperature (OAT), is sensed out of range. NOTE: The Indicated Airspeed (IAS) and True Airspeed (TAS) indications are calculated as NCD when the airspeed is less than 30 kts and the aircraft is stationary and on the ground. A Weight-On-Wheels (WOW) signal from the PSEU will cause the Electronic Instruments System (EIS) to show 30 KIAS and 0 KTAS with these conditions. ATA 34 - NAVIGATION Issue 6 - January 2023 Page 10 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - AIR DATA SYSTEM BLOCK DIAGRAM, INPUTS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 11 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM GENERAL DESCRIPTION CONTINUED The Air Data Computers (ADC1, ADC2) supply data to the systems that follow: • • • • • • • • • • • • Cabin Pressure Controller (CPC) Cabin Indication Module (CIM) Flight Guidance Modules (FGM1, FGM2) Flight Controls Electronic Control Unit (FCECU1, FCECU2) Stall Protection Modules (SPM1, SPM2) Input/Output Processors (IOP1, IOP2) Primary Flight Displays (PFD1, PFD2) Multi-Functional Displays (MFD1, MFD2) Attitude and Heading Reference Units (AHRS1, AHRS2) ATC Transponders (ATC1, ATC2) Flight Management Systems (FMS1, FMS2) Full Authority Digital Engine Control (FADEC1, FADEC2) The trend of the altitude, calculated by the ADC, can be incorrect when the aircraft is dynamically pitched. For indication, the barometric corrected altitude data from the ADCs are dampened by the Attitude and Heading Reference Units (AHRS) to show barometric inertial altitude. If the AHRU malfunctions or an opposite EFIS ATT/HDG SOURCE reversion is set, barometric corrected altitude is shown on the related PFD. NOTE: The EIS has no indications to tell the pilots that barometric corrected altitude is shown. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 12 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - AIR DATA SYSTEM BLOCK DIAGRAM, OUTPUTS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 13 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM SYSTEM OPERATION The Air Data Computers (ADC1, ADC2) operate in the modes that follow: • • • • Power-On Self Test (POST) Operational Initiated Test Maintenance mode TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 14 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM SYSTEM OPERATION CONTINUED POWER-ON SELF TEST (POST) This mode automatically continues for 2 seconds after power up while the aircraft is on the ground. The ADC does the self-tests that follow: • • • • • CPU self-tests Memory check sum Test of peripheral circuits Test of I/O ports Indication of test in progress and successful completion The output air data is invalid during the power-up tests. The ADC calculates a failure warning if it senses a hardware failure. When the ADC POST mode is completed, all ADC data is available. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 15 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM SYSTEM OPERATION CONTINUED OPERATIONAL The Air Data Computers (ADC1, ADC2) senses the data that follow: • • • • Static and pitot pressures Outside air temperature Barometric correction Probe heater failure data The Air Data Computers (ADC1, ADC2) calculate air data for flight compartment indication, and use by the air-conditioning, flight guidance, flight control, navigation, and engine systems that follow: • • • • • • • • • • Static pressure (ps) Pitot pressure (dp) Barometric correction in hPa and in In Hg (Bcor) Barometric altitude corrected by barometric correction (Hc) Altitude rate (Vz) Calibrated airspeed (CAS) True airspeed (TAS) Maximum velocity in operation (VMO) Mach number (M) Static Air Temperature (SAT) Averaged static pressure is supplied through tubing and a shutoff valve to the two ADCs and pitot pressure from each pitot-static probe is supplied through tubing to its related ADC. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 16 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM SYSTEM OPERATION CONTINUED INITIATED TEST MODE The ADC pre-flight test switch is used to check Vmo Warning Tone Generator (WTG) and the ADC outputs. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 17 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS Display Units (ARCDU) during maintenance operations. AIR DATA SYSTEM The ADC perform the tests when they receive a maintenance command from IOM1 while the air speed is less than 50 kts/93 km/h and the aircraft is on the ground. SYSTEM OPERATION CONTINUED MAINTENANCE MODE The Built In Test Equipment (BITE) uses the Central Diagnostic System (CDS) to give the condition of the unit. It saves faults in a Non Volatile Memory (NVM) for reporting to line and shop maintenance. The BITE allows aircraft maintenance personnel to: • • • • Do fault isolation Access failure reports from last or previous flight legs Get the avionics status report Get the part number of an LRU The BITE mode monitors the condition of the unit as follows: • • Power-On Self Test (POST) Continuous monitoring POWER-ON SELF TEST (POST) The POST checks the condition of the unit at power-up or after a long power interruption of more than 200 milliseconds. CONTINUOUS MONITORING The continuous monitoring checks the status of the unit in flight. It records faults in a Non Volatile Memory (NVM) for later troubleshooting using the Central Diagnostic System (CDS). The maintenance mode is selected from one or the other Audio and Radio Control TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 18 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - ADC MODES OF OPERATION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 19 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM AIR DATA COMPUTER The two ADC are installed in the flight compartment on the aft bulkhead using four mounting screws and have quick disconnect pitot and static pneumatic connectors. The pneumatic connectors oriented downwards to prevent entry of moisture into the units. The Air Data Computer (ADC) weighs 6.12 lbs/2.78 kgs. It has subassemblies mechanically packaged into a 2 in/51 mm high, 6 in/152 mm wide by 7.9 in/201 mm long case. The ADC measures static pressure (ps) and pitot pressure (pt) supplied from the primary pressure probes and compensates these pressures for probe position errors. The ADC also measures the temperature probe resistance to calculate Outside Air Temperature (OAT).With this data and and the barometric setting data supplied by the Index Control Panel (ICP), the ADC does the air data calculations. The ADC is a Line Replaceable Unit (LRU) that has the components that follow: • • Electrical board with two silicon pressure sensors P90, a CPU, analogue and discrete inputs/outputs, ARINC 429 interface, power supply and electrical interface with a connector and EMC protection Mechanical case that secures the pressure ports A test mode gives confirmation of correct interface of ADC with the flight compartment displays. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 20 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - AIR DATA COMPUTER LOCATOR TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 21 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM AIR DATA COMPUTER CONTINUED The ADC transmits the calculated air data on 5 ARINC 429 low speed busses to other units. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 22 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - AIR DATA COMPUTER INTERNAL BLOCK DIAGRAM TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 23 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS of each pipe to drain excessive moisture in the tubing. AIR DATA SYSTEM There are four drains are installed, two for each system. They are located under the flight compartment floor, under the left and right circuit breaker panels. PITOT-STATIC PROBES The two primary pitot-static probes are installed symmetrically to the left and right sides of the forward fuselage. The primary pitot-static probes are oriented 9° downward relative to the horizontal reference axis of the aircraft. The angle of the probe tube relative to the mast gives a 5° angle in or out between the tube line and the tangential plane of the fuselage skin. Locating pins on the base plate give an accurate angular orientation of the probe with the aircraft axis. An opening located at the nose of the pitot-static probe senses pitot pressure. The shape of the opening reduces the sensitivity because of the inclination of the tube axis to the different airflow angles. This results in a pitot pressure measurement that is the same through the entire AOA and sideslip area. The static pressure ports are located on the side of each probe tube and sense static pressure. The primary pitot-static probes have one pitot pressure connector and two static pressure connectors (for pneumatic connection with each ADC). To prevent ice accumulation, the primary pitot-static probes have a single coaxial-type electrical heating element that is self-regulating. The primary pitot-static probe has drain holes prevent to moisture accumulation in the pitot tube. The static pressure ports self-drain because of their location pitot-static probes. The primary pitot-static probes are connected to aluminium tubing with flexible hoses. Two T-pipes, located approximately the same distance from the two primary pitotstatic probes, gives the pneumatic averaging of left and right static pressures supplied to each ADC. The slope of the tubing is always more than 3.5° to the drains holes at the lowest point TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 24 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - PITOT-STATIC PROBE LOCATOR TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 25 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM STATIC TEMPERATURE PROBE The static temperature probe is attached flush to an access panel in the wing to fuselage fairing below the left wing root with four mounting screws. It weighs 0.25 pounds. The probe has two isolated platinum temperature sensing elements that have a 0°C base resistance of 500 ohms, and a thermal coefficient of resistance of 0.00385 ohms/degree C. The accuracy of the resistance over the -50°C to +50°C range is ± 1 ohm. This resistance error is equivalent to a temperature accuracy of 0.52°C within this range. The static temperature probe measures the surrounding aircraft Indicated Outside Air Temperature (IOAT). It is a flush-attached electrical resistance transmitter with temperature resistance properties. The IOAT measured by the sensors are affected by airspeed. A recovery factor, a value programmed in the ADC to change IOAT data to SAT is stored in each ADC and is used to calculate from IOAT the Static Air Temperature (SAT) and the True Air Temperature (TAT). TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 26 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - STATIC TEMPERATURE PROBE LOCATOR TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 27 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM PITOT-STATIC ISOLATION VALVE PANEL The pitot-static isolation valve panel is attached to the bottom left part of the instrument panel with two mounting screws. A bonding wire connected to the chassis makes a ground continuity connection between the control panel and the aircraft structure. The NORM/ISOL annunciator switch is a guarded annunciator switch. A transparent switch cover prevents accidental selection of the switch. The pitot-static isolation valve panel has a NORM/ISOL annunciator switch. It pushed to energize the shutoff valve. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 28 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - PITOT-STATIC ISOLATION VALVE PANEL LOCATOR TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 29 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM PITOT-STATIC ISOLATION VALVE PANEL CONTINUED An electrically controlled solenoid shutoff valve is used to isolate ADC1 from the pitotstatic probe No. 2 static source. An annunciator switch located near the pilot in the flight compartment gives manual control of the shutoff valve. Electrical power is supplied from the 28V DC left essential bus through a flight compartment annunciator switch and relay to let the same electrical power source energize the shutoff valve. When the NORM/ISOL annunciator switch is pushed, the 28V DC left essential bus energizes a relay to let the 28V DC left essential bus supply electrical power through relay contacts to the shutoff valve. The shutoff valve is stays closed while it is energized. When the solenoid valve is in the open position, it supplies different signals through the Advisory Control Unit (ACU) to make the NORM lights in the annunciator switch come on and the ISOL lights go out. If the solenoid valve is in the closed position, it supplies different signals through the ACU to make the ISOL lights in the annunciator switch come on and the NORM lights go out. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 30 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - SOLENOID SHUTOFF VALVE SIMPLIFIED SCHEMATIC TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 31 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS The EFIS ADC SOURCE reversion selector on the ESID Control Panel (ESCP) is set to the NORM position to show ADC data on the related Primary Flight Displays (PFD1, PFD2). NOTE: The ADC data is supplied through its related AHRU. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 32 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - ESCP EFIS ADC SOURCE REVERSION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 33 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED The Electronic Instrument System (EIS) shows the Air Data Computer (ADC1, ADC2) data that follow: • • • • • Indicated Air Speed (IAS1, IAS2) Altitude (ALT1, ALT2) True Airspeed (TAS1, TAS2) Minimum Descent Altitude (MDA) Static Air Temperature (SAT) TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 34 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - ELECTRONIC INSTRUMENT SYSTEM (EIS) INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 35 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS The IAS digital readout has white numbers that change to red when the IAS is more than the Maximum Operating Speed (VMO). The display changes back to white when the IAS decreases 2 at less than the VIM. The numbers also change to red when the IAS is less than the low speed cue. The display changes back to white when the IAS increases 2 kts, more than the low speed cue. AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED IAS REFERENCE LINE INDICATED AIR SPEED (IAS) The IAS indicator has a white line adjacent to the window to point to the current IAS. The Indicated Air Speed (IAS) indicator, shows the IAS of the set Air Data Computer (ADC1, ADC2). It has a vertical scale with an IAS reference line and digital readout. The IAS vertical scale and reference line give an analogue indication. The Primary Flight Display shows the Indicated Air Speed (IAS) indicator indications that follow: • • • • • • • VMO SPEED CUE The VMO speed cue gives indication of the Maximum Operating Speed (VMO) along the IAS scale from 30 to 400 kts. It is a red and black band that starts with a red edge at the VMO value and extends to the top of the scale. IAS scale IAS digital readout IAS reference line VMO speed cue Predicted airspeed trend IAS mismatch flag IAS failure flag The VMO speed cue is out of view when the IAS is 42 kts. less than VMO. PREDICTED AIRSPEED TREND The predicted airspeed trend, gives an analogue indication of the predicted airspeed in 10 seconds while the aircraft is airborne. IAS SCALE The IAS scale has a speed range from 30 to 500 kts. It is a black filled rectangular vertical tape with scale with marks every 10 kts and numbers every 20 kts. The tape moves up for decreasing airspeeds and down for increasing airspeeds to show the IAS value. It is a white vertical line with an arrow that starts at IAS reference line and points to the predicted airspeed. If the airspeed trend is more than the shown IAS scale, part of the indication goes out of view. When the difference between the actual IAS and the predicted airspeed value is less than 1 kts or when the IAS data is not correct, the indication goes out of view. IAS DIGITAL READOUT The IAS value is shown through a window in the middle of the IAS indicator. The IAS indicator also shows range of values 42 kts. more or less than the value shown in the window. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 36 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - PFD INDICATED AIR SPEED INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 37 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED IAS MISMATCH FLAG The Flight Data Processing System (FDPS) senses signal differences between the IAS1 and the IAS2. The two IAS indicators show a yellow IAS flag above its IAS digital readout and the two Flight Mode Annunciators (FMA) show a yellow IAS MISMATCH message in the centre row of the centre column. The indications flash for five seconds when they come into view and then go steady. The airspeed mismatch threshold is equal to 10 kts. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 38 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - PFD INDICATED AIR SPEED MISMATCH INDICATION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 39 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED IAS FAILURE FLAG When the airspeed data malfunctions an IAS failure flag comes into view as a red IAS FAIL message in a white rectangle. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 40 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - PFD INDICATED AIR SPEED FAILURE FLAG TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 41 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED SPEED BUGS Speed bugs are shown along the edge of the IAS scale to reference difference speeds. The SPEED BUG SEL push-button switch located on the Index Control Panel (ICP1, ICP2) is pushed while the aircraft is on the ground to set the speed bugs that follow: • • • • • V1, take off decision speed VR, rotation speed V2, take off safety speed No.1 (Solid) No.2 (Outline) The SPEED BUGS SEL push-button switch is pushed to change speed bug V1. It is pushed again to set speed bug V1 and to change VR. The SPEED BUGS SEL pushbutton switch is pushed again to set V2 and change speed bug No.1. It is pushed again to set No.1 and change No.2. Each speed bug is also set five seconds after the last SPEED BUGS SEL push-button switch or SPEED BUGS rotary selection. The SPEED BUGS rotary selector is turned to change the speed bug value. NOTE: Speed bugs V1, VR, and V2 go out of view shortly after the aircraft is airborne when the KIAS is more than 20 kts for V1 and VR, and more than 40 kts for V2. Only speed bugs No.1 and No.2 values can be changed while the aircraft is airborne. When the aircraft is back on the ground, the SPEED BUGS SEL pushbutton switch is pushed to show 49 KTS for speed bugs V1, VR, and V2. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 42 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - INDEX CONTROL PANEL (ICP), SPEED BUG SELECTION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 43 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED SPEED BUGS CONTINUED The cyan bug moves along the IAS scale from minimum 50 kts value to 400 kts, and is parked at this position for higher values. When the index value is lower than 50 kts or when not correct, it is removed from the indication. Each index bug has a digital readout shown in cyan numbers to give a digital value for the Index Control Panel (ICP1, ICP2) selection. It shows the selection in 1 kts increments from 50 kts to 400 kts. The indication is out of view when the selection is less than 50 kts. Each digital value has a bug indication. NOTE: The speed bug is not an autopilot target and is only used as an advisory indication. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 44 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - PFD SPEED BUG INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 45 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED BAROMETRIC SETTING The BARO SET knob located on the Index Control Panel (ICP1, ICP2) is turned to supply the related Air Data Computers (ADC1, ADC2) with a barometric correction. When the aircraft is at the standard pressure altitude, or transition altitude, the PUSH TO STD switch in the BARO SET knob is pushed to use standard barometric pressure. At this altitude, the atmospheric changes are not important because all nearby aircraft set their barometric correction to 29.92 inches of mercury/1013 millibars. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 46 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - INDEX CONTROL PANEL (ICP), BAROMETRIC CORRECTION SELECTION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 47 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED BAROMETRIC SETTING CONTINUED The barometric correction range is 745 to 1050 mbar 22 to 31 In Hg. The related Primary Flight Displays (PFD1 and PFD2) show the barometric correction indication below the altitude indicator with four numbers shown in cyan followed by a Millibars (MB) label in white letters. It is shown in Millibars (MB) or in InHg, as set by pin programming logic on the ADC. If a power interruption occurs, the barometric selection value is saved by the ADC for use when restarting. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 48 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - PFD BAROMETRIC CORRECTION INDICATION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 49 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS ALTITUDE REFERENCE LINE AIR DATA SYSTEM The altitude indicator has a white line adjacent to the window to point to the current altitude. CONTROLS AND INDICATIONS CONTINUED ALTITUDE INDICATOR The altitude indicator shows the barometric altitude of the selected Air Data Computer (ADC1, ADC2). It has a vertical scale with an altitude reference line and digital readout. The altitude vertical scale and reference line give an analogue indication. The Primary Flight Display shows the altitude indicator data that follow: • • • • • Altitude scale Altitude digital readout Altitude reference line Altitude mismatch flag Altitude failure flag ALTITUDE SCALE The altitude scale has a range from -990 ft to 50000 ft. It is a black filled rectangular vertical tape with scale with marks every 100 ft and numbers every 500 ft. The tape moves up for decreasing altitudes and down for increasing altitudes. For negative altitudes, A white NEG label is shown vertically between the 0 ft and -500 ft, -500 and -1000 ft, and -1000 ft and -1500 ft marks. ALTITUDE DIGITAL READOUT The altitude value is shown through a T shaped window in the middle of the altitude indicator as a rolling drum indication in 20 ft increments. The altitude indicator also shows a range of values 550 ft more and less than the value shown in the window. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 50 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - PFD ALTITUDE INDICATOR INDICATION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 51 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED ALTITUDE INDICATOR CONTINUED ALTITUDE MISMATCH FLAG The Flight Data Processing System (FDPS) senses signal differences between the ALT1 and the ALT2. The two altitude indicators show a yellow ALT flag above its altitude digital readout and the two Flight Mode Annunciators (FMA) show a yellow ALT MISMATCH message in the centre row of the centre column. The indications flash for five seconds when they come into view and then go steady. The altitude mismatch threshold increases from 60 ft/18.3 m on the ground to 180 ft/55 m at 27,000 ft/8230 m. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 52 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - PFD ALTITUDE INDICATOR MISMATCH INDICATION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 53 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED ALTITUDE INDICATOR CONTINUED ALTITUDE FAILURE FLAG When the altitude indicator data malfunctions, an altitude indicator failure flag comes into view as a red ALT FAIL message in a white rectangle. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 54 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - PFD ALTITUDE INDICATOR FAILURE FLAG TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 55 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED ALTITUDE INDICATOR CONTINUED METRIC ALTITUDE SELECTION On aircraft with the metric secondary altitude indications (839CH00016): When the PFD ALTIMETER UNITS toggle on the PFD altimeter unit control panel is set to the FT+M position, the altitude indicator will continue to show altitude in feet and it will also show a metric indication in meters. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 56 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - (839CH00016): PFD METRIC SECONDARY ALTITUDE INDICATION SELECTION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 57 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED ALTITUDE INDICATOR CONTINUED METRIC ALTITUDE SELECTION CONTINUED The metric indication shows the aircraft current altitude in 5 m increments from negative 500 m to 15900 m. It has white numbers in white box with an M label. When the metric altitude indication malfunctions, the 5 numbers are replaced with 5 white dashes. The metric altitude indication is supplied through its related IOP. If it malfunctions, the indication is supplied through the opposite (IOP). When the metric altitude indication is in view, the pre-selected altitude readout is also shown in meters. The range of the altitude readout is between 0 and 30500 m. NOTE: The metric altitude readout indication changes in 100 ft increments but is rounded up to match the 5 m metric altitude indication. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 58 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - (839CH00016): PFD METRIC ALTITUDE INDICATION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 59 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED ALTITUDE INDICATOR CONTINUED MINIMUM DESCENT ALTITUDE (MDA) The MDA is a specified altitude that is referenced to sea level for non-precision approaches. A descent below the MDA cannot be made until a visual reference to continue the approach to land is made. The DH/MDA rotary switch on the Index Control Panel - ICP1, ICP2 - is set to MDA to let the DH/MDA knob change the MDA value. The DH/MDA knob is then turned to set a MDA for minimum descent altitude calculations. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 60 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - ICP MDA SELECTION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 61 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS A Weight On Wheels (WOW) condition causes the indication to disarm to make sure that the MDA alert annunciation is out of view during take off and after landing. AIR DATA SYSTEM When the MDA alert annunciation is armed and the aircraft altitude is less than the set MDA value, a yellow MDA alert annunciation that flashes for the first 3 seconds then goes steady is shown in the attitude sphere. The indication stays in view while the barometric corrected altitude is less than 100 ft above the set MDA and ground to keep the MDA alert annunciation in view during a flight level hold at the set MDA. CONTROLS AND INDICATIONS CONTINUED ALTITUDE INDICATOR CONTINUED MINIMUM DESCENT ALTITUDE (MDA) CONTINUED Five white dashes replace the numbers and the MDA alert annunciation goes out of view when a Primary Flight Display (PFD1, PFD2) does not receive valid data from its related Input/Output Processor (IOP1, IOP2). The MDA has the indications that follow: • • • Digital readouts Index bug Alert annunciation MDA DIGITAL READOUTS The bottom right part of the attitude indicator shows the selection as cyan numbers followed by a white MDA label. It shows the altitude selection in ten-feet increments from 0 through 19990 ft. When MDA setting is less than 0 ft, all of the indication goes out of view. MDA INDEX BUG When the MDA is set to a value more than zero, a cyan analogue MDA index bug on the altitude indicator also comes into view to show the selected MDA value. When aircraft is at the selected MDA, the MDA index bug changes to a yellow indication that flashes for the first 3 seconds then goes steady. MDA ALERT ANNUNCIATION An MDA alert annunciation shows that the aircraft is going down to the Minimum Descent Altitude (MDA). This indication is armed until the aircraft barometric corrected altitude is 100 ft more than the set MDA. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 62 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - EIS MDA INDICATION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 63 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED EFIS SOURCE SELECTION When the EFIS ADC SOURCE reversion selector on the ESID Control Panel (ESCP) is set to the 1 or 2 position, the two Primary Flight Displays (PFD1, PFD2) will show barometric inertial altitude from the selected Air Data Computer (ADC1 or ADC2) through its related AHRU (AHRU1 and AHRU2). Note: When the EFIS ATT/HDG SOURCE reversion selector on the ESID Control Panel (ESCP) is set to the 1 or 2 position, the one PFD will show barometric inertial altitude from the selected ADC and AHRU and the other PFD will show barometric corrected altitude data from its related ADC. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 64 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - ESCP EFIS ADC SOURCE REVERSION SELECTION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 65 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED EFIS SOURCE SELECTION CONTINUED When the two Primary Flight Displays (PFD1, PFD2) are showing the same air data source, an air data source annunciator is shown in yellow letters. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 66 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - PFD EFIS ADC SOURCE REVERSION INDICATION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 67 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED EFIS SOURCE SELECTION CONTINUED The MFD1 and MFD2 reversion switches located on the ESID Control Panel (ESCP) are used to show the navigation page on the multi-functional displays. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 68 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - ESCP MFD REVERSION SELECTION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 69 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED TAS DATA DISPLAY The navigation page is usually shown on the upper part of MFD1 and permanent data is shown on the bottom. The navigation page shows the TAS digital value in white numbers from 0 to 999 kts in 1 kts increments with a TAS label. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 70 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - MFD TRUE AIR SPEED (TAS) INDICATION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 71 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED TAS DATA DISPLAY CONTINUED When the TAS data malfunctions, the 3 numbers are replaced by 3 white dashes. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 72 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - PFD TRUE AIR SPEED (TAS) MALFUNCTION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 73 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED SAT DATA DISPLAY The Engine Display (ED) shows the Static Air Temperature (SAT) digital display in white numbers with a + or - symbol and a °C label to the right of the numbers. The ED shows SAT from ADC1. When an EFIS ADC SOURCE reversion selector is set to the 2 position, the ED will show the SAT data from ADC2. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 74 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - ED STATIC AIR TEMPERATURE (SAT) INDICATION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 75 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED SAT DATA DISPLAY CONTINUED When the SAT data malfunctions, the 2 numbers are replaced by 2 white dashes. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 76 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - ED STATIC AIR TEMPERATURE (SAT) MALFUNCTION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 77 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM CONTROLS AND INDICATIONS CONTINUED PITOT/STATIC ISOLATION CONTROL The NORM/ISOL annunciator switch on the pitot-static isolation control panel is pushed to isolate ADC1 from the pitot-static probe No.2 static source. The green NORM indication goes out and the amber ISOL comes on to show that the shutoff valve has moved to the closed position. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 78 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - PITOT-STATIC ISOLATION SELECTION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 79 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS The following tables describle the air data information that is received via ARINC 429 low speed busses 12.0 to 14.5 kilobytes per second: AIR DATA SYSTEM INTERFACES The aircraft left essential and right main busses supply 28V DC electrical power through 2 A circuit breakers to the Air Data Computers (ADC1, ADC2). The circuit breakers are located on the 28V DC avionics circuit breaker panel in position A7 and A6. The temperature probe has 2 sensing elements. Each element receives an excitation current from its related ADC to measure its resistance. It is less than 0.5 mA to limit the self-heating error. Each ADC receives pitot pressure (pt) supplied by its related pitot-static probe and a static pressure (ps) value obtained as a pneumatic average between static pressures from the two pitot-static probes. In addition to the data received from the pneumatic interfaces, each ADC receives discrete data from the systems that follow: • • • • • • • An electrical signal from its related temperature sensor to calculate the Indicated Outside Air Temperature (IOAT) Barometric correction data from the related Index Control Panel (ICP) Test discrete command from a 3 position ADC TEST switch on the pilot side console Initiated Built-In-Test (IBIT) discrete command from the Centralized Diagnostic System (CDS) Pitot-static probe heating failure discrete from the Ice and Rain Protection System (IRPS) Air data source manual reversion command from the ESID Control Panel (ESCP) Weight-On-Wheels discrete from the Proximity Sensor Electronics Unit (PSEU) TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 80 of 500 BOMBARDIER DHC 8-400 (PWC PW150) DATA INTERFACE Static Pressure FADEC1, FADEC2 Pitot Pressure FADEC1, FADEC2 Pressure Altitude FGM1, FGM2 - IOP1, IOP2 - ATC1, ATC2 - FMS - CPC - CIM Barometric Correction PFD1, PFD2 - MFD1, MFD2 - FDR - CPC Barometric Corrected Altitude PFD1, PFD2 - MFD1, MFD2 - FGM1, FGM2 - AHRS1, AHRS2 - ATC1, ATC2 - FMS Altitude Rate FMS - CPC - CIM Calibrated Air Speed PFD1, PFD2 - MFD1, MFD2 - FGM1, FGM2 - SPM1, SPM2 - IOP1, IOP2 - FMS - FADEC1, FADEC2 - FCECU1, FCECU2 Maximum Velocity in Operation PFD1, PFD2 MFD1, MFD2 FGM1, FGM2 FMS VMO Warning IOP1, IOP2 Barometric Correction PFD1, PFD2 - MFD1, MFD2 - FDR - CPC Barometric Corrected Altitude PFD1, PFD2 - MFD1, MFD2 - FGM1, FGM2 - AHRS1, AHRS2 - ATC1, ATC2 - FMS Altitude Rate FMS - CPC - CIM Calibrated Air Speed PFD1, PFD2 - MFD1, MFD2 - FGM1, FGM2 - SPM1, SPM2 - IOP1, IOP2 - FMS - FADEC1, FADEC2 - FCECU1, FCECU2 Maximum Velocity in Operation PFD1, PFD2 - MFD1, MFD2 - FGM1, FGM2 - FMS VMO Warning IOP1, IOP2 NAVIGATION SYSTEMS - ADC DIGITAL INPUTS (ARINC 429) TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 81 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS AIR DATA SYSTEM INTERFACES CONTINUED Each ADC supplies air data through 5 identical ARINC 429 low speed busses for use by critical systems and other avionics subsystems. For non-avionics non-critical systems, air data is available on two General Purpose Data Busses (GPDB) from the IOP modules. Each ADC also transmits to each IOM a Vmo/Mmo warning discrete. The units interfaced with ADC ARINC 429 outputs are described in the following tables: TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 82 of 500 BOMBARDIER DHC 8-400 (PWC PW150) ADC1 ARINC 1 ARINC 2 ARINC 3 ARINC 4 ARINC 5 MFD1 FGM1 FCECU1 MFD2 IOP2 PFD1 SPM1 Channel A PFD2 ATC1 FCECU1 FCECU2 FGM2 ATC2 AHRS1 Channel A SPM2 CPC AHRS2 CIM IOP1 ADC2 ARINC 1 ARINC 2 ARINC 3 ARINC 4 ARINC 5 MFD2 FGM2 FCECU1 MFD1 IOP1 PFD2 SPM2 Channel B PFD1 ATC1 AHRS2 FCECU2 FGM1 ATC2 FCECU2 Channel B SPM1 CPC AHRS2 CIM IOP2 The Input/Output Processor (IOP1, IOP2), Stall Protection Modules (SPM1, SPM2), and Flight Guidance Modules (FGM1, FGM2) are located inside its related Integrated Flight Cabinet (IFC1, IFC2). NAVIGATION SYSTEMS - ADC DIGITAL OUTPUTS (ARINC 429) TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 83 of 500 BOMBARDIER DHC 8-400 (PWC PW150) • NAVIGATION SYSTEMS The bottom part of Engine Display (ED) shows an opposite WTG FAIL advisory message AIR DATA SYSTEM NOTE: TESTS The ADC toggle switch on the pilot side console is set to TEST 1 or TEST 2 (with the EFIS ADC SOURCE switch set to NORM) to check the Vmo Warning Tone Generator (WTG) and related ADC interfaces. When the engines are operating, the RUD CTRL and SPLR OUTBD caution lights also come on. To view the the SAT from ADC2, the EFIS ADC SOURCE reversion selector on the ESID Control Panel (ESCP) is set to the 2 position. The Vmo warning sounds 5 seconds after the ADC test selection. The ADC test values are shown in the table that follows: DATA OUTPUT VALUES Static Pressure 571.8125 mbar Pitot Pressure 137.875 mbar Standard Altitude 15,000 ft Baro correction 990 mbar, 29.23 In Hg Baro corrected altitude 14360 ft (4377 m) Vertical speed 0 ft/min Calibrated Airspeed 285 KIAS (528 km/h) Mach 0.564 True Air Speed 353.125 kt VMO 284 KIAS (519 km/h) Static Air Temp -15°C Total Air Temp +1.5°C Other operational test indications are shown as follows: • • The PITCH TRIM and ELEVATOR FEEL caution lights come on Each Primary Flight Display (PFD1, PFD2) shows an IAS and ALT mismatch flag and a Flight Mode Annunciator (FMA) ALT MISMATCH message TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 84 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - ADC TEST SELECTION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 85 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS The forward part of the probe is an open tube with a knife edge around a circular opening. The standby pitot-static probe has a location with minimal distorted airflow and is pointed directly into the air-stream. STANDBY AIR DATA INSTRUMENTS INTRODUCTION The standby air data system senses and changes static pressure and pitot pressure to give altitude and airspeed indication independently of the primary air data system. The standby altitude and airspeed indicators are connected to the standby pitot-static probe. It has an integral electrical heating element to prevent ice accumulation that causes irregular measurements. The electrical power to the heater is controlled by the Timer Monitor Unit (TMU) of ice and rain protection system. GENERAL DESCRIPTION The standby air data instruments function independently of the primary channel Air Data Computers (ADC1, ADC2) to show the data that follows: • • • Altitude Airspeed Barometric correction settings The standby air data system has the units that follow: • • • Standby altitude indicator Standby airspeed Indicator Standby pitot-static probe The standby pitot-static probe has one pitot pressure port and two static pressure port to supply air data to the standby air data instruments. The standby altitude indicator receives air data from one static port and the standby airspeed indicator receives air data from the pitot and static ports. The standby altitude indicator and the standby airspeed indicator are mechanical devices. The standby altitude indicator uses static air pressure to calculate altitude and the standby airspeed indicator uses the difference between pitot and static pressures to calculate airspeed. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 86 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - STANDBY AIR DATA INSTRUMENTS BLOCK DIAGRAM TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 87 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS STANDBY AIR DATA INSTRUMENTS SYSTEM OPERATION STANDBY ALTITUDE INDICATOR The standby altitude indicator is located in the instrument panel between the pilot Multi-Function Display (MFD1) and the Engine Display (ED) below the standby airspeed indicator in view of the two pilots. It weighs 2.2 lbs/1 kgs. The standby altitude indicator has a high-precision aneroid capsule that expands or compresses with changes in atmospheric pressure to show altitude. A multiplying gear train mechanism is used to change the capsule variations into angular movements of the altitude pointer. A vibrator in the indicator shakes the mechanism to decrease the friction and to prevent the needle pointer from sticking. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 88 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS - STANDBY ALTITUDE INDICATOR LOCATOR TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 34 - NAVIGATION Issue 6 - January 2023 Page 89 of 500 BOMBARDIER DHC 8-400 (PWC PW150) NAVIGATION SYSTEMS turned to set the barometric correction. STANDBY AIR DATA INSTRUMENTS BAROMETRIC CORRECTION INDICATION STANDBY ALTITUDE INDICATOR CONTINUED The standby altitude indicator shows the barometric set knob selection. The left part of the indication shows the barometric selection from 0749 to 1051 millibars and the right part shows the same value in inches of mercury from 22.01 to 31.03. The standby altitude indicator shows the altitude data that follow: • • • • • • FAILURE FLAG Dial scale and needle pointer Digital readout Barometric set knob Barometric correction indication, millibars Barometric correction indication, inches of mercury Failure flag When the vibrator malfunctions, an orange flag comes into view. DIAL SCALE AND NEEDLE POINTER The dial scale with a needle pointer gives analogue indicated barometric corrected altitude. The scale has a circle with short markings shown every 20 ft and long markings every 100. The dial scale shows thousands of feet per turn with each 100 ft. mark shown with a digital value. DIGITAL READOUT The digita