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Engine Controls T55-GA-714A

Terminal Learning Objective. Action: Describe components, operational characteristics, functions, limitations, malfunctions, and emergency procedures of the CH-47D T55-GA-714A Engine Controls System.Conditions: Given a student handout and TM 1-1520-240-10.Standards: Correctly answer in writing, without reference, four of six questions pertaining to components, operational characteristics, limitations, functions, malfunctions, and emergency procedures of the CH-47D T55-GA-714A Power Plant,25

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Engine Controls T55-GA-714A

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    1. Engine Controls T55-GA-714A 1

    2. 2

    3. Safety Requirements: None Risk Assessment Level: Low Environmental Considerations: None Evaluation: Each student will be evaluated on this block of instruction during the second written examination. This will be a criterion type examination requiring a GO on each scored unit. You will have 90 minutes for the exam. Terminal Learning Objective 3

    4. Class Outline Description of the FADEC FADEC Operation Malfunction Indications and Emergency Procedures 4

    5. Learning Step/Activity #1 Provide a system description of the Full Authority Digital Electronic Control (FADEC) 5

    6. FADEC Overview The Full Authority Digital Electronic Control (FADEC) system replaces the Hydro-Mechanical engine control system. The FADEC system is designated model EMC-32T-2. The DECU includes a microcomputer-based primary control channel with an independent microcomputer-based electronic reversionary back-up channel. The DECU tracks the primary channel operation allowing a smooth switch-over when the reversionary channel is selected, or the primary channel fails. The FADEC system utilizes many of the existing engine and aircraft sensors and controls (i.e., PTIT, P3, start fuel solenoid, bleed band actuator, and engine condition levers (ECLs). 6

    7. Components of the FADEC System 7

    8. FADEC Features Automatic start scheduling. No. 1 and No. 2 engine load sharing. Power turbine speed governing. Transient load anticipation (using rotor speed and collective pitch rates). Transient torque smoothing (using N2 rates). Contingency power capability to meet aircraft demands. Acceleration and deceleration control. Engine temperature limiting throughout the operating range. Surge avoidance. Compressor bleed band scheduling. 8

    9. FADEC Features (cont) Fuel flow limiting. Engine fail detection Power assurance test. Engine history, start/component cycle and limit exceedence recording. Engine-to-engine communication (via data bus). Automatic switch-over to an independent back-up control system Control system self-test, self-diagnosis and fault identification. Accurate torque matching. No field level, system adjustments. On-condition maintenance. 9

    10. Learning Step/Activity #2 Describe components and operational characteristics of the Full Authority Digital Electronic Control (FADEC) 10

    11. Hydro Mechanical Metering Assembly (HMA) 11

    12. Primary Channel 12

    13. Primary Stepper Motor 13

    14. Metering Valve 14

    15. Metering Head Regulator 15

    16. Pressurizing and Shutoff valve 16

    17. Reversionary Channel 17

    18. Reversionary Stepper Motor 18

    19. Power Lever Angle (PLA) feedback Potentiometer 19

    20. Primary/Reversionary Change-Over Solenoid 20

    21. Magnetic N1 Speed Sensors 21

    22. Power Supply 22

    23. Alternator 23

    24. Bleed Solenoid Valve 24

    25. Fuel Pump Unit (FPU) 25

    26. Digital Electronic Control Unit (DECU) 26

    27. DECU Fault Codes F Fluid controller (HMU). A Airframe sensor. D, 1, or B DECU fault. E Engine sensor. C Communications between the DECUs. 27

    28. Faults Soft Faults A Failure that does not impact the normal control of the engine. Soft faults are not indicated in the cockpit. Pilot action is not required. Hard Faults Faults that could cause unacceptable engine and/or aircraft performance. Hard faults are detected through software fault limit monitoring or if the primary channel fails. FADEC 1/2 or REV 1/2 lights will be displayed based on what system's failed. 28

    29. DECU Connections 29

    30. P3 Condensation Drain 30

    31. Master Caution/Advisory Panel 31

    32. Engine Condition Levers (ECL) 32

    33. Thrust Controls 33

    34. FADEC Control Panel 34

    35. FADEC Control Panel NR% Selector 1 and 2 PRI/REV Select Switches ENG Start Switch Load Share Switch B/U Power Switch OSPD (Overspeed) Test Switch 35

    36. Power Assurance Test (PAT) Switch 36

    37. Adjustments to PACN 37

    38. Power Assurance Test Log 38

    39. Power Turbine Speed Sensors 39

    40. Twin Engine Load Sharing In non FADEC controlled aircraft the pilots adjust the engines through a process called beeping. With the FADEC system torque, PTIT can be selected to automatically control the engine load sharing requirements. If the selected system fails the system is designed to default to N1 load sharing. If the selected load share signal is loss between the DECUs or one of the two FADEC systems is in the reversionary mode, load sharing is disabled. Load sharing is accomplished by bringing up the low performing engine. The load sharing circuits are by design slow acting so as not to create an unstable engine condition. 40

    41. Engine Starting Set the ECL to the GND position. Hold start switch until N1 > 10% Primary channel will automatically control the start sequencing of the: Starter. Fuel flow to start fuel nozzles. Ignition. Fuel flow to main nozzles. 41

    42. Engine Temperature Limiting Temperature limiting (After light off PTIT > 760C). Reduces fuel flow to 100 PPH minimum. Over temperature during start (Abort start) Fuel shutoff if PTIT > 816C. Associated ENG 1/2 FAIL indication. 42

    43. Engine Shutdown ECL moved to GND to allow normal engine cool down. ECL moved to STOP. Primary system closes the metering valve to the 40 PPH position. Reversionary mode will affect complete shutoff of fuel when ECL is moved to STOP. The shutoff feature is the only function of the reversionary mode that impacts the primary mode. 43

    44. Rate of Change Acceleration (Thrust CPT). Deceleration (Thrust CPT). Temperature Limiting (Abort Start). Power turbine speed (N2 Overspeed). 44

    45. Learning Step/Activity #3 Describe malfunctions and emergency procedures for the 714 Engine. 45

    46. Emergency Engine Shutdown ENG COND lever STOP. FIRE PULL handle PULL (Engine fire only). AGENT DISCH switch As required. (Engine fire only) Perform single-engine failure procedure. 46

    47. Abort Start ENG COND lever STOP. ENG START switch 1 or 2 as appropriate (If high PTIT is indicated). 47

    48. Dual Engine Failure AUTOROTATE. External cargo Jettison. ALT switch Disengage. 48

    49. Single Engine Failure Eng 1 or 2 Fail Light Power turbine shaft failure. N2 is greater than RRPM by more than 3%. N1 underspeed. Engine flameout. Over temperature start abort (Primary mode only). Primary system fail freeze (Primary and Reversionary mode hard faults, FADEC caution is illuminated). During normal shutdown as the N1 RPM goes below 48% the ENG 1 FAIL or ENG 2 FAIL caution is illuminated and then turned off 12 seconds after the N1 RPM drops below 40%. 49

    50. Single Engine Failure Low Altitude/Low Airspeed and Cruise Thrust control Adjust as necessary to maintain RRPM. External cargo Jettison (If required). ALT switch Disengage. Continued flight is not possible: Land as soon as possible. EMER ENG SHUTDOWN (When conditions permit). Continued flight is possible: Land as soon as practicable. EMER ENG SHUTDOWN (when conditions permit). 50

    51. Engine Restart During Flight APU Start. ENG COND lever (inoperative engine) STOP, then GND. FIRE PULL handle In. All FUEL PUMP switches ON. XFEED switch As required. Starting engine Perform. APU OFF 51

    52. Engine Oil Low or Engine Chip If engine power is required for flight: Land as soon as possible. If engine power is not required for flight: EMER ENGINE SHUTDOWN (Affected Engine) Refer to single-engine failure emergency procedure. 52

    53. Engine Shutdown ECL Failure FIRE PULL handle (affected engine) Pull. Normal shutdown Perform. 53

    54. Torque Measuring System Malfunctions N1(NG) and PTIT indicators Check. N1(NG)s and PTITs are not matched. 1. LOAD SHARE switch PTIT. PTIT indicators Check. N1 (NG)s PTITs are not matched. Land as soon as practicable. N1(NG)s and PTITs are matched. 1. AC and DC Torque and Engine circuit breakers IN. 2. Fuel flow indicator Monitor for matched fuel flow. 54

    55. Fires Engine Hot Start A hot start will be detected by a rapid and abnormal rise in PTIT and/or by observing flames and black smoke coming from the engine tail cone. ABORT START Residual Fire During Shutdown A residual engine fire may occur during shutdown. It is caused by residual fuel igniting in the combustion chamber. ABORT START. FIRE PULL handle (affected engine) Pull. 55

    56. Engine or Fuselage Fire Engine or Fuselage Fire Flight Visible flames, smoke coming from the engine or the lighting of the respective FIRE PULL handle: Land as soon as possible. Confirm Fire. (Flight Engineer). EMER ENG SHUTDOWN (affected engine). After landing: EMER ENG SHUTDOWN. 56

    57. FADEC 1 or 2 Caution FADEC INC-DEC beep switches (affected engine) Adjust as required. Reduce rate of Thrust CONT lever changes. 57

    58. FADEC 1 and 2 Caution FADEC ENG 1 and ENG 2 INC-DEC beep switches Beep to 100 percent, match TQs. Reduce rate of THRUST CONT lever changes. Land as soon as practicable. 58

    59. Eng Fluctuations W/O FADEC 1/2 Lights Caution Load share switch Select PTIT. If engine power flucations are not corrected. Load share switch TQ. No. 1 engine FADEC switch REV. If engine power flucations are not corrected. No. 1 engine FADEC switch PRI. No. 2 engine FADEC switch REV. If engine power flucations are not corrected. No. 2 engine FADEC Switch PRI. Land as soon as practicable. 59

    60. Rev 1 and/or Rev 2 (No FADEC) Do not Manually Select Reversionary Mode 60

    61. Rev 1 or Rev 2 (with) Associated FADEC Light ON If engine power is required for flight: Land as soon as possible. After landing: EMER ENG SHUTDOWN (AFFECTED ENGINE). If engine power is not required for flight: EMER ENG SHUTDOWN (AFFECTED ENGINE). FIRE PULL HANDLE (AFFECTED ENGINE) Pull. REFER TO SINGLE-ENGINE FAILURE EMERGENCY PROCEDURES. 61

    62. Rev 1 and Rev 2 (with) Associated FADEC Lights On Land as soon as possible. EMER ENG SHUTDOWN As required. 62

    63. QUESTIONS? 63

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