ATA 77 Engine Indicating System - Issue 6 January 2023_Compress.pdf

BOMBARDIER DHC 8-400 (PWC PW150) ATA 77 - ENGINE INDICATING SYSTEM TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY B1/B2 MAINTENANCE TRAINING MANUAL Issue 6 - January 2023 Page 1 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING SYSTEM GENERAL DESCRIPTION The indicating system gives da...

BOMBARDIER DHC 8-400 (PWC PW150) ATA 77 - ENGINE INDICATING SYSTEM TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY B1/B2 MAINTENANCE TRAINING MANUAL Issue 6 - January 2023 Page 1 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING SYSTEM GENERAL DESCRIPTION The indicating system gives data on vital engine parameters for use by the flight crew and maintenance personnel to monitor engine health and performance. The parameters are: • • • • • • High Pressure Rotor Speed (NH) Low Pressure Rotor Speed (NL) Propeller Speed (NP) Torque (Q) Air Intake Temperature (T1.8) Inter-Turbine Temperature (ITT) The engine parameters from the sub-systems are shown on the Engine Display (ED). The parameters are also sent to the EMU for use by maintenance personnel. These parameters are accessed on the maintenance screen (ARCDU) or downloaded from the CDS to a computer. The function of the indicating system is done by the: • • • Power indicating sub-system Temperature indicating sub-system Analyzers TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 2 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING - ENGINE INDICATING BLOCK DIAGRAM TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 3 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING SYSTEM ENGINE POWER INDICATING GENERAL DESCRIPTION The power indicating system gives data on the speed of the major rotating assemblies and the torque output. These speeds and torque are monitored by magnetic pulse pickup probes at various locations on the engine. The power indicating system has: • • • • High Pressure Rotor Speed (NH) sensors Torque sensors (Q) Low Pressure Rotor Speed (NL) sensor Engine Controls Wiring Harness The speeds of the major rotating assemblies are monitored by magnetic pulse pick-up probes installed at various locations on the engine. These probes sense: • • • High pressure rotor speed (NH) Low pressure rotor speed (NL) Propeller speed (NP) Power turbine rotor speed (NPT) is sensed by the torque sensor and derived to propeller speed (NP). Electromagnetic pulses are generated when associated gear teeth or lugs pass through the magnetic field created by a permanent magnet at the probe or sensor tip. The pulse frequency is transmitted to the FADEC and then to the ED. The NPT/Q signals are also sent to Propeller Electronic Control (PEC) for autofeather and uptrim control. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 4 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING - ENGINE POWER INDICATING SCHEMATIC TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 5 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING SYSTEM ENGINE POWER INDICATING COMPONENT LOCATION AND DESCRIPTION HIGH PRESSURE ROTOR SPEED (NH) SENSOR The NH sensor gives high pressure compressor speed information to the FADEC and to the overspeed logic. There are two NH sensors located on top of the Accessory Gearbox (AGB). Each NH sensor is a sealed unit and has two coils. The sensors pick up high pressure rotor speed signals from the fuel pump/PMA gearshaft teeth. One coil provides a NH speed signal to the FADEC for use in the control and indication logic. The other provides a NH speed signal for the overspeed logic. There are two sensors on each engine. Control and overspeed functions are independent for channel A and B. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 6 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING - NH SENSORS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 7 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING SYSTEM ENGINE POWER INDICATING COMPONENT LOCATION AND DESCRIPTION TORQUE SENSOR (Q) The torque sensors send torque and power turbine speed information to the FADEC. There are two torque sensors located on the air inlet case. The two torque sensors take their signal from torque shafts in the reduction gearbox. Correction of torque shaft stiffness caused by temperature change is done by the FADEC and PEC. The Main Oil Temperature (MOT) probe on top of the front inlet case sends the temperature information for this computation. Each sensor has two coils which are used to sense Torque (Q) and Power Turbine Speed (NPT). Each sensor supplies a Torque and NPT speed signal to the FADEC, the ED and PEC using one coil for each. This means that there are independent Torque and NPT speed signals for channel A and B of both the FADEC and PEC. The Torque and NPT speed signals are used in the FADEC control logic. The FADEC provides processed Torque and NPT speed for flight compartment indication. The PEC uses these signals for Autofeather logic processing. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 8 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING - TORQUE SENSORS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 9 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING SYSTEM ENGINE POWER INDICATING COMPONENT LOCATION AND DESCRIPTION LOW PRESSURE ROTOR SPEED SENSOR (NL) The NL sensor sends low pressure compressor speed information to the FADEC. There is one Low Pressure Rotor Speed Sensor located on top of the front inlet case next to the MOT probe. The NL sensor is a sealed unit and has two coils. The sensor picks up low pressure rotor speed from a toothed sleeve against the No.2.5 bearing. Each coil sends a NL speed signal to channel A and B of the FADEC respectively. NL speed is used for: • • • Controlling the Interstage and Intercompressor bleed valves Flight compartment indication The FADEC NL speed limit logic and the NL decouple logic TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 10 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING - NL SENSOR TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 11 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING SYSTEM ENGINE POWER INDICATING COMPONENT LOCATION AND DESCRIPTION LOW PRESSURE ROTOR SPEED SENSOR (NL) CONTINUED These indications are displayed in both digital and analogue format on the ED as percentages: • • • High pressure compressor speed (NH) Torque (Q) Propeller speed (Np) Low pressure compressor speed (NL) is displayed in digital format only. FADEC sends rating power information to the rating display on the ED. Rated Power is indicated: • • • By a torque bug On the torque analogue display By digital display in the top left and right corners of the ED Selected Rating is indicated by a three letter acronym above the rated torque digital display. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 12 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING - ENGINE INDICATIONS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 13 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING SYSTEM ENGINE TEMPERATURE INDICATING COMPONENT LOCATION AND DESCRIPTION The Engine Temperature Indicating System monitors engine performance. The engine temperature indicating system supplies data on the Inter-Turbine Temperature (ITT). The system has: • Inter-turbine temperature probes The T6 (ITT) probes send signals to the FADEC by the controls electrical wiring harness and the T6 wiring harness. Each FADEC display channel - (channel not in control) - sends the signals on an ARINC 429 bus direct to the Engine Display. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 14 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING - ITT INDICATING SCHEMATIC TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 15 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING SYSTEM ENGINE TEMPERATURE INDICATING COMPONENT LOCATION AND DESCRIPTION INDICATED TURBINE TEMPERATURE (ITT) PROBE Eight probes consisting of three temperature sensing elements give 24 measurement points for comprehensive gas temperature measuring. The sensing elements are located to give sufficient coverage for an accurate ITT. The probes are equi-spaced, on right and left sides, with no probes at top or bottom around the circumference at station 6 of the engine downstream of the 2nd Power Turbine. ITT measurement is accomplished by 24 Chromel-Alumel thermocouples connected in parallel by the ITT wiring harness. The total signal is connected at a junction located at the rear of the engine. The junction is connected to a wiring harness which goes to the Main Oil Temperature/ Cold Junction sensor. Before being processed by the FADEC, the raw ITT is trimmed by a lug mounted resistor. The trimmed ITT and Main Oil Temperature (MOT) are processed by the FADEC and output to the flight compartment over an ARINC 429 bus. The ITT information is also sent to the EMU. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 16 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING - ITT PROBES TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 17 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING SYSTEM ENGINE TEMPERATURE INDICATING COMPONENT LOCATION AND DESCRIPTION ITT TRIM RESISTOR The ITT Trim Resistor is located on two stud terminals on the Main Oil Temperature/ Cold Junction Sensor. The ITT is produced from a system of 24 Chromel-Alumel thermocouples eight sensors with three thermocouples each arranged in parallel. The average signal (by virtue of parallel arrangement) is routed through the ITT Trim Resistor and the cold junction reference before being received and processed by the FADEC. The ITT Trim Resistor is used to provide compensation to the raw ITT signal. The value of the resistor is set during engine pass off testing by the manufacturer or at an approved overhaul facility. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 18 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING - MOT SENSOR AND ITT TRIM RESISTOR DETAIL TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 19 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING SYSTEM ENGINE TEMPERATURE INDICATING TRAINING INFORMATION POINTS Replace failed Lug Mounted Resistors before replacement of the FADEC. The new FADEC will immediately ignore a failed resistor and use the trim value stored in its memory. This value will not be the correct value for the engine. Engine performance will be compromised. Obey all the electrical/electronic, and electrostatic discharge safety precautions when handling the FADEC. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 20 of 36 BOMBARDIER DHC 8-400 (PWC PW150) INTENTIONALLY LEFT BLANK TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 21 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING SYSTEM ANALYZERS GENERAL DESCRIPTION The system displays most of the engine parameters, plus discrete indications, in the flight compartment. It also sends powerplant information to the engine monitoring system and to the digital flight data recorder. The analyzers record, display and download this information: • • • • • • FADEC and PEC fault and condition codes Engine Condition Trend Monitoring (ECTM) data Power assurance requirements and data Powerplant limit exceedance data Snapshot and transient powerplant and aircraft data to help troubleshooting Powerplant and aircraft flights, cycles and hours Primary fault code display is on the torque gauge and NH gauge. Channel A, FADEC and Lane A PEC fault codes are displayed on engine torque gauge. Channel B, FADEC and Lane B PEC fault codes are displayed on NH gauge. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 22 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING - EMS BLOCK DIAGRAM TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 23 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING SYSTEM ANALYZERS SYSTEM DESCRIPTION The function of the analyzers is done by the Engine Monitoring System (EMS) and the FADEC ARINC 429 System. Each FADEC display channel (channel not in control) sends signals on an ARINC 429 bus direct to the Engine Display (ED). The FADEC information is also sent to the Integrated Flight Cabinet (IFC) for processing and retransmission to the Digital Flight Data Recorder (DFDR). These parameters and discretes are sent to the Flight Compartment independent of the FADEC ARINC system: • • • FADEC Caution, Fail and PEC Caution as discretes are sent directly to the Caution and Warning Panel Propeller Ground Range as a discrete to the Advisory Display Unit (ADU) and then to the lights on the glare-shield panel Main Oil Pressure, Fuel Flow and Fuel Temperature from the engine mounted sensors as analogue signals to the IFC, and from there to the ED on an ARINC 429 DATA bus TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 24 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING - FADEC ARINC 429 INDICATING SYSTEM TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 25 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING SYSTEM ENGINE MONITORING SYSTEM GENERAL DESCRIPTION The Engine Monitoring System collects data on every significant event that occurs during the operation of the engine. The data collected by the EMS can be viewed in the aircraft on the Audio and Radio Control and Display Unit (ARCDU) screen. The data can also be downloaded to a PC based Ground Based System (GBS). The function of the Engine Monitoring System is performed by the: • • Engine Monitoring Unit (EMU) Ground Based System (GBS) The EMU is located in the flight compartment, on the side wall behind and below the copilot seat. The ARCDU is located in the Flight Compartment, one each side of the console behind the control quadrant. The Engine Monitoring System uses: • • • • The FADEC The Propeller Electronic Control (PEC) The Centralized Diagnostic System (CDS) The ARCDU TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 26 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING - ENGINE MONITORING SYSTEM SCHEMATIC TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 27 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING SYSTEM The position of any switch which provides an input to the FADEC or PEC will be displayed. This enables the circuit to be tested quickly and easily. ENGINE MONITORING SYSTEM Instructions to check the operation of Engine Health Discretes. SYSTEM DESCRIPTION Confirmation of powerplant trims: Torque Gain and Bias, ITT, configuration, BETA Feedback and Power Lever Angle (PLA) Feedback. The EMS has these functions: Snapshot and/or Trace recording (in response to an engine significant event). A snapshot is a recording taken at the instant of the event and consists of approximately 79 parameters generated by the FADEC/PEC. A Trace is a recording initiated at the instant of the event and consists of approximately 49 parameters generated by the FADEC/PEC (going back two minutes prior to the event and one minute after the event). Resolution is one set of parameters every 80 msec near either side of the event and 800 msec everywhere else. A snapshot and trace can be initiated by pushing the EVENT MARKER switch on the ENGINE CONTROL PANEL. Review of data stored in EMU memory. This feature allows the operator to view the date/time of each recording in memory, type of recording, and Flight Deck parameters at the time of the recording. Summary of aircraft and FADEC configuration. Aircraft Registration, Owner and Operator can be uploaded manually. Aircraft S/N is automatically uploaded from the CMS, FADEC, PEC, and EMU S/N are logged automatically. Hours and cycles accumulated on the above is available. EMU memory usage is available Logging of Fault Codes generated by the FADEC and PEC. Recording of Engine Condition Trend Monitoring (ECTM) conditions automatically. Averaging of ECTM conditions for the previous Flight Hours and alert to Maintenance if the trend deviates from the norm. Recording of time to spool down for high and low pressure spools. Alert to Maintenance if the spool down time reduces below a minimum value significantly. Monitoring of Engine parameters and logging any exceedance beyond operating limitations. These parameters include: ITT, Torque, NH/NL/NP, Oil Pressure, Oil Temperature. Monitoring of Engine Health discretes, and logging any change in state. These discretes include: Chip Detectors, Low Oil Pressure, Oil Filter Impending Bypass, Low Fuel Pressure, and Fuel Filter Impending Bypass. Step by step Power Assurance procedure. Detailed results are available following successful completion. Live feedback of Flight Deck engine switch state. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 28 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING - ENGINE MONITORING SYSTEM SCHEMATIC TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 29 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING SYSTEM ENGINE MONITORING SYSTEM CONTROLS AND INDICATIONS ARCDUs EMU functions can be viewed in the flight compartment on the ARCDU. The normal mode for the ARCDU is to allow the crew to manage radio communications functions. In Maintenance Mode, the ARCDU becomes a display screen for the CDS. These conditions must be met to access the Maintenance Mode on the ARCDU: • • • • The aircraft is static airspeed <50 knots (93 km/h) Weight is on wheels ARCDU GND MAINT on Central Maintenance Panel in wardrobe is selected MAINT key on either or both ARCDU screens selected When in Maintenance Mode, the fault codes for FADEC channel A and PEC lane A are displayed on the Torque gauges. The fault codes for FADEC channel B and PEC lane B are displayed on the NH gauges. When Maintenance Mode is selected, the CMS Main Menu is displayed. The ARCDU screen has eight soft keys and three navigation keys which can be used to select menu items. To select the Engine Monitoring Unit, press the key adjacent to EMU on the screen. When EMU is selected, the main menu is displayed and any EMU function can be accessed. NOTE: Where there is an active message waiting, the menu item colour is amber rather than white. This convention is carried through the sub-menus, the sub-sub-menus, and so on. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 30 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING - ENGINE MONITORING SYSTEM, ARCDU TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 31 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING - POWERPLANT MENU LAYOUT (1) TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 32 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING - POWERPLANT MENU LAYOUT (2) TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 33 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING - POWERPLANT MENU LAYOUT (3) TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 34 of 36 BOMBARDIER DHC 8-400 (PWC PW150) ENGINE INDICATING - POWERPLANT MENU LAYOUT (4 ) TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 35 of 36 BOMBARDIER DHC 8-400 (PWC PW150) INTENTIONALLY LEFT BLANK TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 77 - ENGINE INDICATING SYSTEM Issue 6 - January 2023 Page 36 of 36