ATA 31 Indicating & Recording System PDF

BOMBARDIER DHC 8-400 (PWC PW150) ATA 31 - INDICATING & RECORDING SYSTEM TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY B1/B2 MAINTENANCE TRAINING MANUAL Issue 6 - January 2023 Page 1 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING PURPOSE The indicating and recording system...

BOMBARDIER DHC 8-400 (PWC PW150) ATA 31 - INDICATING & RECORDING SYSTEM TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY B1/B2 MAINTENANCE TRAINING MANUAL Issue 6 - January 2023 Page 1 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING PURPOSE The indicating and recording system has different sub-systems to do the functions that follow: • • • • • • • • Showtime Records aircraft parameter data Receive data from sensors and avionics systems and supply it to other systems Calculate warning and caution conditions and make the related warning tones Show caution and warning lights Show advisory messages Take-off warning calculation Show navigation, engine, and system parameters TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 2 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING GENERAL DESCRIPTION The indicating and recording system has the sub-systems that follow: • • • • • Clocks Flight Data Recorder System (FDR) Central computer, Flight Data Processing System (FDPS) Central warning system Electronic Instruments System (EIS) TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 3 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING CAUTION AND WARNING LIGHTS GENERAL DESCRIPTION The caution and warning lights system shows system malfunctions and other conditions that require a corrective action. CLOCKS ADVISORY LIGHTS The electronic clock has a quartz time base that supplies a continuous display of Greenwich Mean Time (GMT) or Local Time (LOC). The electronic clock can also to show the Elapsed Time (ET), the date or set to the chronometer function (CHR). FLIGHT DATA RECORDER SYSTEM (FDR) The advisory lights show malfunctions and safe and normal system operation. Some advisory lights require a corrective action. The take-off warning system supplies an aural warning when a take-off is attempted with the aircraft not in the correct take-off configuration. ELECTRONIC INSTRUMENTS SYSTEM The Solid State Flight Data Recorder (SSFDR) records aircraft parameter data and stores it in crash-protected memory for future retrieval purposes. CENTRAL COMPUTER The Electronic Instrument System (EIS) shows navigation, engine, and system parameters. It interfaces with other systems to calculate, make, and show their indications. The central computer has a Flight Data Processing System (FDPS) to receive data from sensors and avionics systems and supplies it to other systems. The Flight Data Processing System (FDPS) also supplies warning tones that alert the crew to specific events or system failures. The Electronic Instrument System (EIS) also monitors its calculations to prevent misleading information from being shown. CENTRAL WARNING SYSTEM The central warning system is divided into the two parts that follow: • • Caution and Warning Lights Take-off Warning The caution and warning light system is divided into the two parts that follow: • • Caution and warning lights Advisory lights TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 4 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - INDICATING AND RECORDING BLOCK DIAGRAM TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 5 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING GMT is supplied to the CVR and Flight Data Processing System (FDPS) in the Integrated Flight Cabinet (IFC). CLOCKS PURPOSE The electronic clock has a quartz time base that supplies a continuous display of Greenwich Mean Time (GMT) or Local Time (LOC). The electronic clock can also be set to show the Elapsed Time (ET), the date or set to the chronometer function (CHR). GENERAL DESCRIPTION The clock system includes the unit that follows: • Clock, Electronic The electronic clock has a quartz time base which operates a special function Large Scale Integrated (LSI) circuit and supplies the functions that follow: • • • • Continuous digital display of Greenwich Mean Time (GMT) or Local Time (LOC) Digital display of Elapsed Time (ET) Display of the chronometer (CHR) function. In this mode, the display of seconds is analogue (sweep-hand) and that of minutes is digital Display of date and year, when set There are two clocks located in the flight compartment one on each side of the glareshield. The pilots set the type of data to be shown on the display. A four-position switch, located on the lower left corner of the clock face, controls the clock functions. Each clock is energized by its related essential bus and the battery power bus located in the right circuit breaker panel. The battery power bus is used to keep time when the essential bus is not energized. The Proximity Sensor Electronics Unit (PSEU) supplies a Weight On Wheels (WOW) signal to start and stop the Elapsed Time (ET) function. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 6 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - CLOCK SYSTEM BLOCK DIAGRAM TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 7 of 308 BOMBARDIER DHC 8-400 (PWC PW150) • • • • • • • INDICATING AND RECORDING CLOCKS DETAILED DESCRIPTION CONTINUED The clocks have dichroic Liquid Crystal Displays (LCD) that show white digits against a grey background. The five time base functions that are available are as follows: • • • • • Greenwich Mean Time (GMT) Local Time (LOC) Elapsed Time (ET) Date Chronometer function (stopwatch) with a seconds sweep-hand Equipment Part Number Equipment Serial Number Date of Manufacture Manufacturer Inspection Stamp Administration Inspection Stamp Power Requirements Backlighting Requirements The electronic clock weighs 1.04 ± 0.031 lbs/0.475 ± 0.01 kgs. It measures 2.4 in/61 mm high by 2.4 in/61 mm wide by 6.24 in/156 mm long including front controls and the rear connector. The clocks are attached to the glare-shield panel with two mounting screws. ELECTRONIC CLOCK Two clocks are installed on the left and right sides of the glare-shield panel assembly. Dichroic liquid crystal decimal indicators (7-segment) display white digits against a black background. Digits, graduations and GMT, LOC, DATE, SET, ET, CHR markings are shown in light grey on a black background. Four labels are attached to each clock that include the information that follows: • • • • An Identification label A Modification Status label A NO HIGH VOLTAGE TEST label A CAUTION label regarding the handling of electrostatic-sensitive devices The identification label contains the information that follows: • • • Manufacturer logo Manufacturer code Name of equipment TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 8 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - ELECTRONIC CLOCK LOCATOR TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 9 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING CLOCKS CONTROLS AND INDICATIONS Each clock is independently operated from the switches located on the bezel, and has instrument glass which is coated with an anti-reflection treatment on both sides. The function selector positions are labelled DATE, LOC, GMT and SET. The selector is pushed to exit the SET mode. When the function selector is placed in the SET position, the Elapsed Time (ET) switch is pushed to cycle through the modes that follow: • • • • • • • GMT minutes displayed immediately when SET is selected GMT hours LOC minutes LOC hours Days Months Years default on power-up is 90 TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 10 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING When primary electrical power is removed, the time base is maintained by the aircraft battery bus, all displays are blanked, and the sweep hand, if active, stops. Current parameters continue to increment with the exception of the Chronometer and Elapsed Time functions. When primary power is restored, the upper LCD display shows the original function data and the lower display indicates 00 00. The Chronometer sweephand returns to zero and can be re-enabled if set to start from zero. CLOCKS CONTROLS AND INDICATIONS CONTINUED At each momentary activation of the ET switch, the applicable area of the display flashes and the data is then entered using the CHR switch. The CHR switch may either be pushed steadily to cause the target display to increment automatically at a rate of 1 unit per 0.5 seconds, or may be activated by the operator in discrete steps. The Elapsed Time (ET) switch located in the lower left area of the clock face gives 3-state and 2-state sequences dependent on the Weight On Wheels (WOW) status of the aircraft. On the ground: • • • First activation: Display of Elapsed Time Second Activation: Elapsed Time is reset to zero Third activation: Display of Chronometer minutes Airborne: • • First Activation: Display of Elapsed Time Second Activation: Display of Chronometer minutes The Chronometer function switch (CHR) located in the top right corner of the clock face supplies the three states, in order, that follow: First activation: START Temporary removal of the Elapsed Time hour display Return to zero Chronometer minute count start Chronometer sweep-hand start Second activation: STOP Maintains the display of the current indication Third activation: RESET Sweep-hand returns to zero Elapsed Time display returns TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 11 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING CLOCKS CONTROLS AND INDICATIONS CONTINUED The ARINC 429 output bus is not active during standby power operation. Greenwich Mean Time (GMT) is shown in the top 4-digit readout area of the clock face from 00:00 to 23:59 minutes when the function selector is in the GMT position. A single dot is displayed above the GMT legend. Local time (from 00:00 to 23:59) is shown in the same location as GMT when the selector switch is in the LOC position. A single dot appears above the LOC legend, to give an alternative means of distinguishing local time from GMT, additional to switch position. When the selector switch is set to DATE, the month and day are shown in the top 4-digit area of the clock face. The two left digits 01 to 12 identify the month and the two right digits identifies the day 01 to 31 and the year 0 to 99. As the day and year occupy the same area, the display alternates each second between the two parameters. To aid interpretation while displaying the year, the left digits are blank. Leap years are programmed into clock operation. Elapsed Time (ET) is indicated from 0 to 99:59 in the lower digital display area of the clock face and gives an indication of aircraft flight time. The mode is automatically enabled by a discrete Weight-Off-Wheels discrete input from the Proximity Switch Electronics Unit (PSEU) when the aircraft becomes airborne and can only be reset during a Weight-On-Wheels (WOW) condition. A colon separates the hours and minutes. Minutes are indicated from 0 to 59 by the two right digits in the lower display area of the clock face with the left digits blanked. Seconds are shown against the round dial of the clock face by a sweep-hand activated by a stepper motor. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 12 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - ELECTRONIC CLOCK TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 13 of 308 BOMBARDIER DHC 8-400 (PWC PW150) • • • INDICATING AND RECORDING CLOCKS Remote Control Audio Unit (RCAU) Audio and Radio Management System (ARMS) Engine Monitoring Unit (EMU) The clocks send data to the CVR and FDPS through an ARINC 429 data bus. INTERFACES The clock installations interface with the aircraft systems that follow: The left essential and battery power busses supply 28V DC electrical power through two 1 ampere circuit breakers to the CLOCK 1. The circuit breakers are located in positions E9 on the avionics circuit breaker panel and F3 on the right circuit breaker panel. • • • IOP1, located in IFC 1, for input to the CDS and FDR PSEU for Weight-Off-Wheels discrete to activate the Elapsed Time function CVR for recording of real time and synchronization with the FDR The right main and battery power busses supply 28V DC electrical power through two 1 ampere circuit breakers to the CLOCK 2. The circuit breakers are located in positions E6 on the avionics circuit breaker panel and G3 on the right circuit breaker panel. Primary power is supplied from the left essential and right main 28V DC busses for CLOCK1 and CLOCK2 with a keep-alive voltage automatically supplied by the battery power bus when the primary electrical power is removed. The clocks are also supplied with variable 5V DC from the aircraft dimming bus to 4 display backlighting bulb. Each clock operates independently. The CLOCK1 is interfaced directly with the Cockpit Voice Recorder and both clocks are interfaced with the Flight Data Recorder (FDR) through the Flight Data Processing System (FDPS). The FDR normally records time from the CLOCK1 but will switch to CLOCK2 if the CLOCK1 malfunctions. Real time is recorded on both the Cockpit Voice Recorder (CVR) and Flight Data Recorder (FDR) to establish synchronization between the two recording systems. The date is also supplied to the Flight Data Processing System (FDPS) located in the Integrated Flight Cabinet (IFC1) to show when the Type 1 systems malfunctioned for events in Central Diagnostics System (CDS) BITE reports. Type 1 systems include: • Electronic Indication System (EIS) TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 14 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INTENTIONALLY LEFT BLANK TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 15 of 308 BOMBARDIER DHC 8-400 (PWC PW150) • • INDICATING AND RECORDING FLIGHT DATA RECORDER SYSTEM (FDR) • PURPOSE The Solid State Flight Data Recorder (SSFDR) records aircraft parameter data and stores it in crash-protected memory for future retrieval purposes. GENERAL DESCRIPTION The Flight Data Recorder System (FDR) has the units that follow: • • • • The flight data recorder system interfaces with the units that follow: • • When a high impact is sensed, the impact switch opens the circuit to the SSFDR to remove electrical power. This makes sure that the recorded data before the impact is not overwritten. While the aircraft is on the ground, a signal from the Proximity Sensor Electronics Unit (PSEU) to the IOMs causes relay K5 to open and de-energize the SSFDR during the conditions that follow: • • • Flight Data Recorder Impact Switch Test Switch Anti-collision Switch Anti-collision lights toggle switch is set to the RED or WHITE position Both engines are operating engine-operating oil pressure is sensed from both engines Weight-Off-Wheels is sensed from the Proximity Sensor Electronics Unit (PSEU) Engines are not operating Anti-collision lights toggle switch is set to the OFF position FLIGHT DATA RCDR toggle switch is set to the NORM position If the SSFDR is not operating or not operating correctly, the FLT DATA RECORDER caution light comes on. An Underwater Locator Beacon (ULB) is attached to the Solid State Flight Data Recorder (SSFDR) handle. When immersed in water, the ULB transmits an acoustic signal to help locate the SSFDR. Flight Data Processing System (FDPS) Caution and warning panel The Solid State Flight Data Recorder (SSFDR) is a crash survivable unit that can record up to 25 hours of aircraft parameters and clock data in a continuous loop. Different aircraft systems supply related data through the Input-Output Modules (IOM1, IOM2), Input-Output Processors (IOP1, IOP2), to the Flight Data Concentrator (FDC). The FDC is located in IOP1 and it changes ARINC 429 data to ARINC 717 and sent to the Solid State Flight Data Recorder (SSFDR). Electrical power is supplied through relay K5 and impact switch to the SSFDR. The IOMs causes relay K5 to close and energize the SSFDR when they sense a condition that follows: • FLIGHT DATA RCDR toggle switch is set to the NORM position TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 16 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - FLIGHT DATA RECORDER BLOCK DIAGRAM TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 17 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING FLIGHT DATA RECORDER SYSTEM (FDR) DETAILED DESCRIPTION The SSFDR system receives mandatory and non-mandatory parameters and discretes from aircraft systems at 128 words per second through an ARINC 717 data bus. The SSFDR unit records up to 25 hours of data in a crash-survivable memory for subsequent retrieval and analysis. Ground-Based Equipment (GBE) and an RS422 interface are used to download the recorded data. The GBE does the functions that follow: • • • • Real-time monitoring of aircraft parameters and discretes Shows the internal status of the SSFDR Downloads data from the Crash Survivable Memory Unit (CSMU) Test of the SSFDR The GBE interface connector with protective cover is installed in the front panel of the SSFDR and is used for download, test and maintenance functions without removing the LRU from the aircraft. SSFDR system operations are controlled by a microprocessor which supplies the logical processing and data flow necessary to do all system functions. The SSFDR operates in the modes that follow: • • • • • • • Power off mode Initialization mode Record mode Continuous monitor mode Test mode Download mode Power down mode TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 18 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING It operates in the record mode within 500 millisecond of applying power. The SSFDR stops recording if it does not receive data for more than five seconds, causing the FLT DATA RECORDER caution light to come on. FLIGHT DATA RECORDER SYSTEM (FDR) The SSFDR stays in the record mode until it is connected to the Ground Based Equipment (GBE). The type of GBE selects what mode the SSFDR will enter next. POWER OFF MODE The SSFDR operates when power is removed for more than 200 milliseconds. No functions are available. Applying power exits the power off mode. INITIALIZATION MODE The SSFDR operates in the initialization mode immediately upon receiving power. It initializes and performs 95% of the Built-In-Test (BIT) within 500 millisecond. It determines the SSFDR status on power-up in addition to normal recorder operations. A history of the BIT status is maintained within the CSMU and can be downloaded with the GBE. During initialization, the system records the unit configuration that follows: • • • Memory size Rate of transfer Address of next available memory location to be recorded If the BIT fails, the external BIT light on the front panel of the SSFDR comes on. The SSFDR transmits the received data back to the Input/Output Processor (IOP1). This makes sure that the SSFDR is properly receiving the input data. If the status discrete senses a failure, the loop-back data is not present. The FLT DATA RECORDER caution light on the caution and warning panel will come on. The conditions that follow exit the SSFDR from the record mode: • • • Removing power Detection of the download mode Command from the IOP MONITOR MODE The monitor mode supplies aircraft installation diagnostics and troubleshooting. The SSFDR continuously does the following: • • Background tests on system hardware Monitors data inputs The SSFDR exits the initialization mode of operation if it cannot record data due to a critical failure. It transmits a signal to the continuous monitor mode to stop it from recording, and the FLT DATA RECORDER annunciator on the Caution Warning Panel comes on. In the monitor mode, the SSFDR records normal flight data in parallel with the data bus to the GBE. The GBE commands the SSFDR to operate in the monitor mode and to output a data frame, once per second, that shows the status of the recorder, and the record data, 8 times per second. The Central Diagnostics System (CDS) receives and records an equivalent maintenance output through the Integrated Flight Cabinet (IFC 1). TEST MODE RECORD MODE Recording data begins immediately following the initialization and self-test mode. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY The test mode supplies Return to Service testing of the SSFDR. The external Automated Test Unit (ATU) commands the SSFDR to operate in the test mode. The normal record mode stops when the unit is operating in the test mode. The ATU controls the exit from the test mode. ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 19 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING FLIGHT DATA RECORDER SYSTEM (FDR) DOWN LOAD MODE The SSFDR starts the down load mode when initiated by the external Down Load Unit (DLU). A DLU is a PC-based device that has the necessary software to download the contents of the CSMU and monitor the data parameters as they are received. The data can be downloaded through the front connector of the SSFDR. When the information is downloaded, the SSFDR record mode stops and the status discrete will show a failure. A full 25-hour download of data recorded at 128 words per minute can last approximately 10 minutes dependent upon PC speed. POWER DOWN MODE The SSFDR power supply maintains internal voltages to continue normal operation during a power interruption lasting less than 200 milliseconds. For power interruptions greater than 200 milliseconds: • • The data in the RAM is lost The initialization mode starts In the power down mode, the SSFDR continues to receive data. It records data in the volatile Random Access Memory (RAM) rather than the non-volatile CSMU. If the power restores within 200 millisecond, the data in the RAM is transferred to the CSMU. The normal recording process then continues. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 20 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING The power supply uses the 28V DC input from the rear connector through the controller CCA, then filters and regulates the power to create the necessary voltages for system operation. FLIGHT DATA RECORDER SYSTEM (FDR) The power supply circuitry also monitors input and output power characteristics. FLIGHT DATA RECORDER The SSFDR is installed in the empennage of the aircraft between station points X942.57 and X958.23 at Z134.46 and to the left of aircraft centreline. The unit weighs less than 16 pounds/7.26 kilograms. Voltages used by the SSFDR are +5V DC, +12V DC, and -12V DC. Additional functions of the power supply are the generation of system reset and power-down interrupt signals. The reset signal is triggered when the +5V DC regulated signal drops to approximately 4.75V DC. The SSFDR is installed to the tray with corrosion resistant steel fasteners. The unit is located adjacent to the Solid-State Cockpit Voice Recorder (SSCVR). The Power-Down Interrupt occurs for a primary power input drop of approximately 13V DC. The SSFDR has the components that follow: The SSFDR has an identification label that includes the information that follows: • • • • • • • • • • • Circuit Card Assemblies (CCA) Controller Memory Power supply regulator Power supply filter The CCA are interfaced with each other or to external devices through a series of connectors. The Controller CCA performs the main SSFDR control functions. The CCA controls the reception and transmission of all aircraft parameter and discrete data. The data inputs flow through the controller and are presented at the CSMU for storage. All circuit card assemblies are conformally coated for protection from the effects of moisture, humidity and vibration. Unit part number Weight Serial number Manufacturing date TSO certified number DO-160C environmental certification categories A modification status label hardware/software is also attached. The memory functional block includes 18 flash Electrically Erasable Programmable Read Only Memory (EEPROM) memory chips, each capable of 8 megabits (1 megabyte) storage capacity and powered by 5V DC. The unit can store the last 25 hours of recorded data. An additional EEPROM chip is installed for BITE messages generated during BIT operations. An Elapsed Time Indication (ETI), repair history, bad memory locations and pointers to the most recent ARINC 717 data are also stored. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 21 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING The ULB is self-powered by a battery with a typical service life of six years from the date of manufacture. A label that shows the battery expiry date is attached to the ULB. FLIGHT DATA RECORDER SYSTEM (FDR) FLIGHT DATA RECORDER CONTINUED The SSFDR chassis is painted a bright international orange and is marked with the black letters FLIGHT RECORDER DO NOT OPEN and ENREGISTREUR DE VOL NE PAS OUVRIR. Reflective tape is attached to the SSFDR external surface to further help recover it. The SSFDR has two flex print assemblies; one between the controller CCA and the LRU rear connector and the other between the controller CCA and the CSMU. This latter assembly is constructed such that in the event of a crash, should the flex print be torn, corruption of the FLASH memory will not occur. The housing is designed such that the crash-survivable enclosure is installed on top and towards the front of a thin-walled chassis. The recorder housing has been designed to be Electro-Magnetic Interference (EMI) tolerant. The SSFDR front fasteners are electrically bonded to the chassis ground. The rear interface connector shell includes bonding surfaces which maintain good ground continuity between the recorder chassis and the recorder mounting frame. The SSFDR is designed to operate in extreme environmental conditions with no forced air cooling. When installed, air can flow around the unit and supply cooling. An Underwater Locator Beacon (ULB) is attached to the front of the SSFDR to easily access it for servicing and to read its battery expiratory date. It may also be used as a carrying handle. The ULB is automatically activated when immersed in either fresh water or salt water at depths from 0.5 to 20,000 feet (0.15 to 6096 meters). When activated, the ULB will transmit a 37.5 kHz ± 1 kHz frequency for a duration longer than thirty days. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 22 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - FLIGHT DATA RECORDER LOCATOR TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 23 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING FLIGHT DATA RECORDER SYSTEM (FDR) IMPACT SWITCH The impact switches attached to a bracket located below the cabin floor at station point X195.8, Y0, Z88.9. The unit is installed at 45° with the reset switch pointing towards ground and the front of the aircraft to sense upward and downward acceleration. The impact switch supplies the SSFDR system with the capability to remove power from the system if an acceleration of greater than 5.5g is applied to the switch as a consequence of high impact landing. This makes sure that SSFDR recorded data prior to the impact is stored and cannot be overwritten. The normally-closed impact switch has an impact activated double pole latching switch; one pole of which is connected in series with the 28V DC aircraft supply to the SSFDR. The second pole is connected to the Solid-State Cockpit Voice Recorder. The switch latches to an open state when activated. A manually operated RESET toggle switch, located on the side of the impact switch is used to re-arm the switch. The current rating of each pole of the switch is 5A at 28V DC. The maximum DC current of the SSFDR is less than 500 mA. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 24 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - FLIGHT DATA RECORDER IMPACT SWITCH LOCATOR TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 25 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING FLIGHT DATA RECORDER SYSTEM (FDR) TEST SWITCH The FLIGHT DATA RCDR toggle switch is located in the flight compartment on the overhead panel. When the FLIGHT DATA RCDR switch is set to the GND TEST position, the normal on ground power removal circuits are bypassed. The pre-flight GND TEST switch located in the flight compartment on the overhead panel, supplies power to the SSFDR for the duration that the switch is held. If the SSFDR BITE indicates satisfactory system operation, the caution panel FLT DATA RECORDER light goes out. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 26 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - FLIGHT DATA RECORDER PANEL LOCATOR TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 27 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING FLIGHT DATA RECORDER SYSTEM (FDR) ANTI-COLLISION SWITCH The RED-OFF-WHITE A/COL switch is located in the flight compartment on the overhead EXTERIOR LIGHTS panel. When the anti-collision lights switch is set to the RED or WHITE position, the normal on ground power removal circuits are bypassed. The anti-collision lights switch is located in the flight compartment on the overhead panel. If the SSFDR BITE indicates satisfactory system operation, the caution panel FLT DATA RECORDER light goes out. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 28 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - RECORDERS, EXTERIOR LIGHTS PANEL LOCATION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 29 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING FLIGHT DATA RECORDER SYSTEM (FDR) CONTROLS AND INDICATIONS The RED-OFF-WHITE A/COL toggle switch on the Exterior Lights Panel is set to the WHITE or RED position to power the SSFDR. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 30 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - ANTI-COLLISION LIGHT SWITCH TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 31 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING FLIGHT DATA RECORDER SYSTEM (FDR) CONTROLS AND INDICATIONS CONTINUED The FLT DATA RECORDER caution light comes for the conditions that follow: • • • • • • • SSFDR is not energized Data rate mis-compare Memory malfunction cannot record 25 hours of data Micro-controller malfunction Software malfunction Download mode Test TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 32 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - CAUTION AND WARNING PANEL, FDR CAUTION INDICATION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 33 of 308 BOMBARDIER DHC 8-400 (PWC PW150) • • INDICATING AND RECORDING FLIGHT DATA RECORDER SYSTEM (FDR) Caution panel status flag Impact switch removes power for accelerations more than of 5.5g The SSFDR operates in the modes that follow depending on its interface as described in the following table: INTERFACES The left main bus supplies 28V DC electrical power through a 1 A circuit breaker to the Solid State Flight Data Recorder (SSFDR). The circuit breaker is located in position F3 on the avionics circuit breaker panel. Two digital clocks supply the SSFDR and Solid State Cockpit Voice Recorder (SSCVR) with time data. The clocks synchronize the aircraft data with audio information recorded by the SSCVR. The SSCVR receives ARINC 429 time information directly from digital clock No.1 and digital clock No.2 supplies time information to the SSFDR through the Input/Output Processor (IOP1). The IOP1 converts ARINC 429 data to ARINC 717. MODE INTERFACE Record IOP1 using ARINC 717 data bus Monitor and Test Automated Test Unit using RS422 data bus Download Download Unit using RS-422 data bus The flight data recorder parameters that are described in the follow tables are controlled using ARINC 429 low speed busses 12.0 to 14.5 kilobits per second: The Flight Data Processing System (FDPS) includes the Flight Data Concentrator which is located in the IFC1 in the IOP1 module. The acquisition of discretes and analogue signals is done by the Input Output Module 1 (IOM1) while IOP1 receives digital data. The flight data concentrator receives, samples, conditions and digitizes the received flight data and transmits it to the SSFDR through an ARINC 573/717 bus generated within IOP1. The output of the flight data concentrator is organized into frames which are repeated every four seconds. Each frame has four sub-frames of 1 second that consists of 128 twelve-bit words each. Discrete data are packed into discrete words. The data transmission rate is therefore 128 words per second. The SSFDR system interfaces with the aircraft systems/busses that follow: • • • • • • Left Main 28V DC bus through 1 A circuit breaker F3 Avionics circuit breaker panel IOM1 located in IFC1 for input to the Centralized Diagnostic System (CDS) maintenance flag IOP1 located in IFC1 for input ARINC 573/717 data and loop-back data Overhead anti-collision lights red and white switch for power interlock Proximity Sensor Electronic Unit (PSEU) for WOW input part of power interlock Overhead test switch TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 34 of 308 BOMBARDIER DHC 8-400 (PWC PW150) PARAMETER SOURCE Barometric Corrected Altitude ADU1, ADU2 Computed Air Speed ADU1, ADU2 Static Air Temperature ADU1, ADU2 Pilot’s Barometric Setting ADU1 AFCS engagement FGM1, FGM2 YD engagement FGM1, FGM2 AFCS Mode Selection FGM1, FGM2 AFCS Selected Speed FGM1, FGM2 AFCS Selected Vertical Speed FGM1, FGM2 Tactile Control Steering Status FGM1, FGM2 HSI selection IOP1, IOP2 Heading Selection IOP1, IOP2 Altitude Selection IOP1, IOP2 DU Health Status IOP1, IOP2 Course Selection IOP1, IOP2 DH Selection IOP1, IOP2 Recorder Elapse Time IOP1 Terrain caution alert EGPWC Terrain warning alert EGPWC EGPWS system status EGPWC EGPWS Terrain Inhibit Selection TERRAIN INHIBIT Switch Pitch Angle AHRS1, AHRS2 Roll Angle AHRS1, AHRS2 Magnetic Heading AHRS1, AHRS2 INDICATING AND RECORDING - FLIGHT DATA RECORDER PARAMETERS CONTROLLED USING ARINC 429 LOW SPEED BUSSES TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 35 of 308 BOMBARDIER DHC 8-400 (PWC PW150) PARAMETER SOURCE Normal Body Acceleration AHRS1, AHRS2 Lateral Body Acceleration AHRS1, AHRS2 Longitudinal Body Acceleration AHRS1, AHRS2 Time Clock 1, Clock 2 Condition Lever Angle FADEC1, FADEC2 Power Lever Angle FADEC1, FADEC2 ECS Bleed Valve Position FADEC1, FADEC2 NH FADEC1, FADEC2 NP FADEC1, FADEC2 Torque Command (QPLA) FADEC1, FADEC2 Torque Target FADEC1, FADEC2 TQ FADEC1, FADEC2 ITT FADEC1, FADEC2 Thrust Reverse Status FADEC1, FADEC2 Autofeather Event Marker FADEC1, FADEC2 Autofeather Armed Indication PEC DU on or off status EIS MFD Reversions EIS ADU Reversions EIS AHRS Reversions EIS Mono Mode EIS DU Indication Selections EIS MFD1 Images EIS EGPWS Terrain Selections EIS INDICATING AND RECORDING - FLIGHT DATA RECORDER PARAMETERS CONTROLLED USING ARINC 429 LOW SPEED BUSSES TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 36 of 308 BOMBARDIER DHC 8-400 (PWC PW150) PARAMETER SOURCE Glideslope Deviation NAV1, NAV2 Localizer Deviation NAV1, NAV2 VOR Bearing NAV1, NAV2 APU Bleed Valve Position APU FADEC VHF Communications PTT RCAU HF Communications PTT RCAU Standby Battery Hot CWP No.3 Standby Hydraulic Pump CWP Cabin Pressure CWP Touched Runway CWP AC Busses CWP TRU CWP DC Generators CWP AC Generators CWP DC Busses CWP FADEC Malfunctions CWP Doors CWP Check Fire Detection CWP Smoke CWP Main Battery Hot CWP Auxiliary Battery Hot CWP Engine Oil Pressure CWP Engine Hydraulic Pumps CWP INDICATING AND RECORDING - FLIGHT DATA RECORDER PARAMETERS CONTROLLED USING ARINC 429 LOW SPEED BUSSES TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 37 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING FLIGHT DATA RECORDER SYSTEM (FDR) TESTS The FLIGHT DATA RCDR toggle switch on the flight data recorder panel is set to the GND TEST position to test the SSFDR while the aircraft is on the ground. If the SSFDR BITE senses satisfactory operation, the FLT DATA RECORDER amber caution light on the caution and warning panel will go out. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 38 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - FLIGHT DATA RCDR TEST SWITCH TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 39 of 308 BOMBARDIER DHC 8-400 (PWC PW150) • INDICATING AND RECORDING Aircraft Configuration Module (ACM) The modules are located in two Integrated Flight Cabinets - IFC 1, IFC 2 - installed in the Avionics rack. CENTRAL COMPUTER PURPOSE The central computer has a Flight Data Processing System (FDPS) to receive data from sensors and avionics systems and supplies it to other systems. The FDPS also causes different warning tones to sound it shows messages if an important system has malfunctioned or if the aircraft is in a dangerous condition. GENERAL DESCRIPTION The two Flight Data Processing Systems (FDPS1, FDPS2) do the functions that follow: • • • • • • • • • • Receive and calculate aircraft and avionics parameters for the Flight Data Recorder (FDR) Receive data from different avionics and aircraft systems and routes their parameters to other systems through one output Receive analogue, discrete, and digital data from other systems and changes it to ARINC 429 format Mismatch message calculations Monitors the Electronic Instrument System (EIS) Advisory message calculation Aircraft configuration management with Aircraft Configuration Modules (ACM) Calculates and supplies Warning Tones (WTG 1, WTG 2) and controls their priority Maintenance tests Software teleloading Each Flight Data Processing System (FDPS 1, FDPS 2) has the modules that follow: • • • • Integrated Flight Cabinet (IFC) Input/Output Processor (IOP) Input/Output Module (IOM Prime Power Supply Module (PPSM) TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 40 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - FLIGHT DATA PROCESS SYSTEM BLOCK DIAGRAM TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 41 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING CENTRAL COMPUTER GENERAL DESCRIPTION Electrical power is supplied through the Prime Power Supply Modules (PPSM1, PPSM2) to the units in the related Integrated Flight Cabinet - IFC1, IFC2. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 42 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - FLIGHT DATA PROCESS SYSTEM BLOCK DIAGRAM, POWER TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 43 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING CENTRAL COMPUTER OPERATIONAL MODES The Flight Data Processing System - FDPS 1, FDPS 2 - functions in the modes that follow: • • • • • Initialization (INIT) Power-On Self Test (POST) Operational (OPER) Maintenance Teleloading TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 44 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING CENTRAL COMPUTER OPERATIONAL MODES CONTINUED INITIALIZATION (INIT) STATE The FDPS functions in the initialization mode after an electrical power interruption. It initializes the hardware and software when it is on the ground. If the FDPS does not receive a maintenance or teleloading request, it will then function in the Power-On Self Test (POST) mode. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 45 of 308 BOMBARDIER DHC 8-400 (PWC PW150) • • • INDICATING AND RECORDING CENTRAL COMPUTER IO1, IO2 board validity Analogue inputs and outputs Discrete inputs and outputs They do not cause a FDPS malfunction. The POST sequence continues for 25 seconds. OPERATIONAL MODES CONTINUED POWER-ON SELF TEST (POST) The FDPS does a (POST) to make sure the hardware operates correctly before starting the operational mode. The FDPS does a POST when the aircraft is on the ground and there is a long electrical power interruption that continues for more than 200 milliseconds. The FDPS tests the interfaces that follow: • • • Input/Output Processor (IOP 1, IOP 2) Input/Output Module (IOM 1, IOM 2) Ground Proximity Warning System Converter The result of the POST is stored in the Built In Test Equipment (BITE) and sent to the Central Diagnostic System (CDS). The POST checks the parameters that follows: • • • • • • • Programme memory Data memory Watch dog Power supplies Hardware (HW) monitoring Module Validity HW and Software (SW) logic Memory partitioning HW monitoring Time partitioning HW monitoring If a parameter malfunctions, it will causes the FDPS to malfunction. The POST also checks the parameters that follow: • • • • ARINC 429 inputs and outputs ARINC 422 inputs and outputs ARINC 717 inputs and outputs Discrete inputs and outputs TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 46 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING CENTRAL COMPUTER OPERATIONAL MODES CONTINUED OPERATIONAL STATE The FDPS does the functions that follow: • • • • • • • • Flight Data Concentrator (FDC) Data Hub Concentrator (DHC) Data Control (DCO) Mismatch calculations Electronic Instrument System (EIS) essential monitoring Message generation Aircraft configuration management Warning Tone Generator (WTG 1, WTG 2) TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 47 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING DATA CONTROL (DCO) CENTRAL COMPUTER The Data Control (DCO) makes calculations for the parameters before concentration. OPERATIONAL MODES CONTINUED MISMATCH CALCULATIONS OPERATIONAL STATE CONTINUED The FDPS monitors important Primary Flight Display (PFD) indications. A mismatch condition is calculated if an IOP senses a difference between its related system value and the value it receives from the other system. A related mismatch flag and mismatch message is shown by opposite Primary Flight Display (PFD). FLIGHT DATA CONCENTRATOR (FDC) The FDC is located in IOP1. It receives data in different formats from the avionics and other aircraft systems and supplies digital data to the Solid State Flight Data Recorder (SSFDR) through an ARINC 717 bus. The calculations are only done when the parameters are valid. For localizer and glideslope mismatch messages, the two navigation receiver outputs must be valid and tuned to the same frequency. DATA HUB CONCENTRATOR (DHC) The FDPS receives non-critical data from avionics and other aircraft systems and supplies their parameters to other systems through a single output. The FDPS supplies the concentrated parameters through ARINC 429 data buses to the avionics systems that follow: • • • • • • • • Electronic Instruments System (EIS) Flight Guidance Module (FGM 1, FGM 2) Stall Protection Module (SPM 1, SPM 2) Audio and Radio Control Display Units (ARCDU 1, ARCDU 2) Traffic Collision Avoidance System (TCAS) Ground Proximity Warning System (GPWS) Weather Radar (WXR) Flight Management System (FMS 1, FMS 2) Two specific external non-avionics General Purpose Data Buses (GPDB 1, GPDB 2) are used to transmit data to systems that are not part of the avionics suite. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 48 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - FDPS MISMATCH CALCULATION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 49 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING CENTRAL COMPUTER OPERATIONAL MODES CONTINUED OPERATIONAL STATE CONTINUED MISMATCH CALCULATIONS CONTINUED If a mismatch condition is sensed, the PFDs will show the most important mismatch message in its Flight Mode Annunciators (FMA) and a mismatch flag in the related indicators: • • • • • • • • PITCH MISMATCH ROLL MISMATCH HEADING MISMATCH IAS MISMATCH ALT MISMATCH RAD ALT MISMATCH GS MISMATCH LOC MISMATCH TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 50 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - FDPS MISMATCH INDICATION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 51 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING CENTRAL COMPUTER OPERATIONAL MODES CONTINUED OPERATIONAL STATE CONTINUED (EIS) ESSENTIAL MONITORING The IOP monitors the difference between a parameter received directly and same parameter received from the opposite PFD and IOP. If the difference is more than the predetermined value, the FDPS causes to the PFD to show a malfunction condition for that parameter. The FDPS does essential monitoring for the systems that follow: • • • Radio Altimeter Localizer deviation Glideslope deviation The essential monitoring parameter thresholds are shown in the table that follows: PARAMETER AGL altitude, less than 1000 ft DIFFERENCE 20 ft LOC deviation, between 50 and 1000 ft AGL 2/3 of Expanded LOC Scale G/S deviation, between 50 and 1000 ft AGL 1/6 of G/S Scale TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 52 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - EIS ESSENTIAL MONITORING TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 53 of 308 BOMBARDIER DHC 8-400 (PWC PW150) • INDICATING AND RECORDING ICE DETECTED CENTRAL COMPUTER BALANCE MESSAGE OPERATIONAL MODES CONTINUED The [BALANCE] message comes into view flashing for five seconds then stays on steady when a fuel imbalance condition is sensed by the left or right fuel gauging computers. OPERATIONAL STATE CONTINUED INCR REF SPEEDS MESSAGE MESSAGE GENERATION The message generation system has the indications that follow: • • ICE DETECTED MESSAGE Advisory Flight Mode Annunciator (FMA) The ICE DETECTED message comes into view when one ice detector probe or the other senses ice accumulation. ADVISORY The advisory messages are shown in white letters on the Engine Display (ED). Each message has a location and is shown while the condition is present. There are two kinds of advisory messages as follows: • • The INCR REF SPEEDS message comes into view when the Stall Protection System (SPS) stall sensing is changed for icing conditions. The FDPS sends a discrete data signal to Electronic Instruments System (EIS) from one or the other SPM. First Family Second Family FIRST FAMILY SECOND FAMILY Second family messages relate to minor malfunctions and are located at the bottom of the ED. The messages relate to malfunctions that do not affect a continued safe flight. The FDPS causes the ED to show the second family advisory messages that follow: • • IFC messages Display messages avionic cooling fans related only The first family messages relate to a condition that needs pilot awareness and an action may be necessary. These messages are located near its related indication. The FDPS causes the ED to show the first family advisory messages that follow: • • NOTE: The power-plant messages are supplied by the Full Authority Digital Engine Control (FADEC) for indication. BALANCE INCR REF SPEEDS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 54 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING CENTRAL COMPUTER OPERATIONAL MODES CONTINUED OPERATIONAL STATE CONTINUED MESSAGE GENERATION CONTINUED IFC MESSAGES The most important IFC message is shown at the bottom left part of the ED. It shows the messages that follow: • • • • • • • • IOP1 FAIL, IOP2 FAIL, IOPS FAIL IOP BAD CONF IOM1 FAIL, IOM2 FAIL, IOMS FAIL WTG1 FAIL, WTG2 FAIL, WTGS FAIL GPWSC I/F FAIL WOW/IOP1 FAIL, WOW/IOP2 FAIL, WOW/IOPS FAIL IFC ACM1 FAIL, IFC ACM2 FAIL, IFC ACMS FAIL RA1 FAIL, RA2 FAIL, RAS FAIL TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 55 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING GPWSC I/F FAIL CENTRAL COMPUTER The GPWSC I/F FAIL messages are shown when the IFC1 makes the GPWS inoperative when it malfunctions. The message is when the malfunction is sensed. OPERATIONAL MODES CONTINUED WOW/IOP1 FAIL,WOW/IOP2 FAIL, WOW/IOPS FAIL OPERATIONAL STATE CONTINUED The WOW/IOP FAIL messages are shown when the IOP senses a difference between the main and nose WOW signals from the PSEU. The IOP will not be able to do a POST after a power interruption. The message is shown when the aircraft is on the ground and engines are not running. MESSAGE GENERATION CONTINUED IFC MESSAGES CONTINUED IFC ACM1 FAIL, IFC ACM2 FAIL, IFC ACMS FAIL IOP1 FAIL, IOP2 FAIL, IOPS FAIL The IOP FAIL messages are shown when the IOP1 or IOP2 or the interface to the ED has malfunctioned. The IFC ACM FAIL messages are shown when a ACM malfunction is detected. A single ACM malfunction has no effect on the aircraft. When the two ACM malfunction, a bad DU BAD CONF messages is shown. RA1 FAIL,RA2 FAIL,RAS FAIL IOP BAD CONF The IOP BAD CONF message is shown when a bad aircraft configuration condition is sensed by one IOP or the other. The RA FAIL message is shown when a dual Radar Altimeter system is installed and the RA malfunction is sensed for more that ten seconds by the EIS ED. The message is displayed any time the malfunction is sensed. The message comes into view when the aircraft is on the ground. IOM1 FAIL, IOM2 FAIL, IOMS FAIL The IOM FAIL messages are shown when IOM malfunctions are sensed. WTG1 FAIL, WTG2 FAIL, WTGS FAIL The WTG FAIL messages are shown when the WTG malfunctions. The message is shown when the aircraft is on the ground and engines are not running. A Remote Control Audio Unit (RCAU) malfunction also causes a WTG FAIL indication. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 56 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING CENTRAL COMPUTER OPERATIONAL MODES CONTINUED OPERATIONAL STATE CONTINUED MESSAGE GENERATION CONTINUED DISPLAY MESSAGES The most important display message is shown at the bottom right part of the ED. The FANS FAIL message is the only FDPS related display message indication. It comes into view when 2 or more avionics cooling fans do not operate. The FANS FAIL display message also comes into view when 2 or more avionics cooling fans do not operate and they are not inhibited by their related thermal switch while the aircraft is on the ground. The temperature switch 1 supplies data to IOP1 and temperature switch 2 supplies data to IOP2. NOTE: The advisory messages are shown in order of decreasing importance. The most important IFC message is shown at the bottom left part of the ED and the most important display message is shown at the bottom right part of the ED. An IFC or display advisory message also causes the AVIONICS caution light to come on 2 minutes after the aircraft is on the ground and the air speed is less than 50 kts. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 57 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING CENTRAL COMPUTER OPERATIONAL MODES CONTINUED OPERATIONAL STATE CONTINUED MESSAGE GENERATION CONTINUED FLIGHT MODE ANNUNCIATOR (FMA) The top part of the PFD have a FMA to show different Automatic Flight Control System (AFCS) and FDPS mismatch messages. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 58 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - FDPS ADVISORY MESSAGE GENERATION TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 59 of 308 BOMBARDIER DHC 8-400 (PWC PW150) • INDICATING AND RECORDING CRC MSB indication CENTRAL COMPUTER OPERATIONAL MODES CONTINUED OPERATIONAL STATE CONTINUED AIRCRAFT CONFIGURATION MANAGEMENT The Aircraft Configuration Module stores configuration information for the systems that follow: • • • • • • • • • • • • • • • • • • • • • • • TCAS ACARS SELCAL MLS FMS VHF COM HF SPM ADF DME ATC RA IRS Aircraft type Engine type Temperatures Quantities Fuel used Ground mapping Aircraft serial numbers AOA correction WTG outputs CRC LSB indications TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 60 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - FDPS AIRCRAFT CONFIGURATION MANAGEMENT TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 61 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING CENTRAL COMPUTER OPERATIONAL MODES CONTINUED OPERATIONAL STATE CONTINUED WARNING TONE GENERATORS (WTG 1, WTG 2) The Warning Tone Generators (WTG 1, WTG 2) sound different tones to tell the pilots of dangerous conditions or system malfunctions. NOTE: The WTG make the tones and control the priority of the voice sounds from the GPWS and TCAS. The tone that sounds depends on its priority. The most important tone always sounds as follows: TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 62 of 308 BOMBARDIER DHC 8-400 (PWC PW150) PRIORITY TONE DESCRIPTION SIGNAL TYPE LEVEL VOLTS 1 GPWS Voice N/A N/A 2 TCAS, RA Voice N/A N/A 3 Fire Continuous chime until manually cancelled A 4.8 4 Incorrect take off configuration 1000 Hz intermittent tone until cause of condition is removed C 3.5 5 Autopilot disengage 250 Hz Intermittent tone for 1.5 seconds (manual) or until manually cancelled (automatic) F 3.8 6 Pitch trim in motion Continuous clicking until cause of condition is removed D 4.2 7 Overspeed 1000 Hz intermittent tone until speed decreased C 3.1 8 Incorrect landing gear configuration Continuous 800 Hz tone until cause of condition is removed B 1.8 9 Altitude alert 2900 Hz tone for 1 seconds B 2.9 10 Beta lockout warning Continuous 1900 Hz to 2900 tone until cause of condition is removed G 5.2 11 Warning annunciation 3 x 1000 Hz chimes E 3.8 12 Caution annunciation 1 x 1000 Hz chime E 5.0 13 TCAS, TA Voice N/A N/A 14 SELCAL 1200 Hz tone for 3 seconds N/A 2.7 INDICATING AND RECORDING - WARNING TONE PRIORITIES TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 63 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING CENTRAL COMPUTER OPERATIONAL MODES CONTINUED OPERATIONAL STATE CONTINUED WARNING TONE GENERATORS (WTG 1, WTG 2) CONTINUED Each type of warning type signal modulation, is described in the following diagrams: TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 64 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - WTG AURAL WARNING TYPE A TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 65 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - WTG AURAL WARNING TYPE B TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 66 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - WTG AURAL WARNING TYPE C TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 67 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - WTG AURAL WARNING TYPE D TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 68 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - WTG AURAL WARNING TYPE E TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING & RECORDING SYSTEM Issue 6 - January 2023 Page 69 of 308 BOMBARDIER DHC 8-400 (PWC PW150) INDICATING AND RECORDING - WTG AURAL WARNING TYPE F TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 31 - INDICATING