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EC 130 B4 Initial Pilot Ground School Chapter 15 - Engine - Part 2

EC 130 B4 Initial Pilot Ground School Chapter 15 - Engine - Part 2 Engine Monitoring, Controls, Fuel System and Fire Detection. Chapter 15 - Engine Engine Monitoring Components ……………………….…………………….………….... 15.4 N1 Speed Sensing ……………..………………………….…………………………………. 15.5

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EC 130 B4 Initial Pilot Ground School Chapter 15 - Engine - Part 2

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  1. EC 130 B4 Initial Pilot Ground School Chapter 15 - Engine - Part 2 Engine Monitoring, Controls, Fuel System and Fire Detection

  2. Chapter 15 - Engine Engine Monitoring Components ……………………….…………………….………….... 15.4 N1 Speed Sensing ……………..………………………….…………………………………. 15.5 Ng / Ng Indicator Failure ………………………………………………………………….. 15.6 N2 Speed Sensing ………………………………...…………………………………………. 15.7 NR Indicator Failure …………………………………….…...………………………………. 15.8 Nf Indicator Failure ………………………………….……………………………………….. 15.9 Torque Monitoring ……………………………………..…………………………………….. 15.10 Torquemeter Failure ………………………………………………….…………………….. 15.11 Ng and Torquemeter Indicator Failure ………………………………………………… 15.12 T 4.5 Monitoring ………………………………...……………………………………………. 15.13 T4 Indicator Failure ………………………………………………………………………….. 15.14 Engine Oil Pressure Limitations …………………………………………………………… 15.15 Engine Oil Temperature Limitations ……………………………………………………… 15.16 First Limitation Indicator ……….…………………………………………………………… 15.17 Torque Limitations …………………………….…………………………………………….. 15.18 Main Rotor Limitations …………………………………………….………………………… 15.19 Nf Limitations ……………………….………………………………………………………… 15.20 Ng Limitations …………………………………..……………………………………………. 15.21 T4 Limitations …………………………...……………………...……………………………. 15.22 Engine Oil Temperature Limitations and Engine Oil Pressure Limitations ….……. 15.23 Engine Controls …………………...…………………………………………………………. 15.24 Twist Grips ………..…………………………………………………………………………… 15.26 15.2

  3. Chapter 15 - Engine FADEC …………………………………………………………………………….………….... 15.30 Tail Rotor Potentiometer Failure ….………………………………………………………. 15.32 EBCAU …………..…………………………………………………………………………….. 15.33 Governor Caution Light ………………………………….…………………………………. 15.41 Governor Warning Light ………………...…………………………………………15.45 & 15.48 Fire Detection ……………………………..………………………………………………….. 15.49 Engine Fire Warning Light …………….……………………………………….. …15.53 & 15.56 Engine Flame Out - Cruise Flight ……………………….………………………..15.57 & 15.58 Engine Flame Out - Autorotation Overwater …………………………….……………… 15.59 Engine Flame Out - InFlight Relighting ………………….………………………………. 15.60 Engine Flame Out - Hover In Ground Effect …………………………………………….. 15.61 Engine Flame Out - Hover Out of Ground Effect ……………………………………….. 15.62 Review Questions …………………………………………………………………………… 15.63 15.3

  4. Engine Monitoring Components 15.4

  5. N1 Speed Sensing 15.5

  6. NG / NG Indicator Failure 5 T4 820 0C 7 3 9 x100 -4 -8 -12 TQ 4 FLI FAILED Respect the maximum torque value and T4 below 8100 C. NOTE T4 limitations displayed are starting limitations. LAND AS SOON AS PRACTICABLE Flight Manual - Emergency Procedures - Page 3 - 10 15.6

  7. N2 Speed Sensing 15.7

  8. Collective ……… Maintain Tq >10%. NR reading is given by Nf pointer. NR Indication Failure LAND AS SOON AS PRACTICABLE [ Nf & NR are equivalent in POWER ON flight only. ] NOTE 1 The Nf value can be read on the VEMD screen. Press “SELECT” * , then “+” as many times as required to display the parameter in the rectangular window at the bottom of the FLI or 3-data screen. [ * The Flight Manual states “SCROLL” , which is incorrect. ] Flight Manual - Emergency Procedures - Page 3 - 8 15.8

  9. NR gauge ……… CHECK in green range with Tq > 0. Nf Indication Failure CONTINUE FLIGHT [ Nf & NR are equivalent in POWER ON flight only. ] NOTE 1 The Nf value can be read on the VEMD screen. Press “SELECT” * , then “+” as many times as required to display the parameter in the rectangular window at the bottom of the FLI or 3-data screen. [ * The Flight Manual states “SCROLL” , which is incorrect. ] NOTE 2 In case of Nf indication failure, the EBCAU may not be available. Flight Manual - Emergency Procedures - Page 3 - 8 15.9

  10. Torque Monitoring 15.10

  11. Ng = minus 4 5 T4 820 0C 7 3 9 Torquemeter Failure x100 -4 -8 -12 TQ 4 FLI FAILED Respect the Ng given in the following table: LAND AS SOON AS PRACTICABLE Flight Manual - Emergency Procedures - Page 3 - 10 15.11

  12. NG & Torquemeter Indications Failure GOV 89.1 GOV T4 limit of 8100C. 5 T4 820 0C 7 3 9 x100 -4 -8 -12 TQ 4 FLI FAILED warning can also cause loss of Ng and torque indications. The VEMD switches to 3-data symbology with only T4 and numeric Ng as valid parameter. Comply with Ng limitations in the above table, substituting the Ng = minus 4 limit by a T4 limit of 8100 C. LAND AS SOON AS PRACTICABLE Flight Manual - Emergency Procedures - Page 3 - 10 15.12

  13. T4.5 Monitoring 8 Double Probes 15.13

  14. T4 Indicator Failure 5 T4 820 0C 7 3 9 x100 -4 -8 -12 TQ 4 FLI FAILED Respect Ng and Torque limitations On ground: do not try to start the engine. LAND AS SOON AS PRACTICABLE Flight Manual - Emergency Procedures - Page 3 -10 15.14

  15. Engine Oil Pressure Limitations • Minimum pressure 1.1 bar(Ng > 70%) • Caution range 1.1 to 2 bar • Normal pressure 2 to 6bar • Caution range 6 to 9.8 bar • Maximum pressure 9.8 bar 15.15 Flight Manual - Limitations Section - Page 2 - 8

  16. Engine Oil Temperature Limitations • Caution range - 100 C to 00 C • Maximum temperature 1150 C • Minimum oil temperature before power application 00 C (Oil 5 cSt) [ ‘power application’ means raising the collective ] 15.16 Flight Manual - Limitations Section - Page 2 - 8

  17. “Gong!” Failure of NG - Torque - T4 Indicators: In the event of failure of a first limitation calculation parameter, the FLI is no longer displayed. The NG / NG, Torque, and T4 indicators are displayed instead. First Limitation Indicator • Maximum continuous: 9.6 • Take-off rating range: 9.6 to 10 • [ 5 sec Ng limit ] • Maximum take-off rating: 10 • Maximum transient: 10.4 (5 s) • [ Power alarm above 10 for 1.5 sec. - Use of P2 air bleeds is forbidden above the engine maximum continuous rating (Ng or T4) NOTE The values [shown] are given as examples. 15.17 Flight Manual - Limitations Section - Page 2 - 6

  18. Main Transmission Limitations • TORQUE LIMITATIONS 8 : 92.7 % Maximum continuous rating : 92.7 % to 100 % Takeoff rating torque range from 0 to 40 kt : 100 % Max. takeoff rating torque : 104 % Max. transient rating (5s) 6 10 4 x 10 2 TQ 99 % 0 NOTE Use of Takeoff rating torque range has no time limit. 100% torque corresponds to 536 kW at 386 NR rpm. 15.18 Flight Manual - Limitations Section - Page 2 - 6

  19. 7 Main Rotor Limitations It is prohibited to use the rotor brake prior to engine shutdown. Minimum time between two consecutive brakings: 5 minutes. : 170 rpm Rotor brake operation max. speed : 320 rpm Minimum power-off : 320 to 375 rpm Caution range : 375 to 405 Normal operating range : 405 to 430 rpm Caution range : 430 rpm Maximum power-off NOTE: Low NR aural warning < 360 rpm High NR aural warning > 410 rpm 15.19 Flight Manual - Limitations Section - Page 2 - 5

  20. 7 • Engine Limitations • Nf LIMITATIONS Use of takeoff rating range MTOP, is limited to 5 minutes. : 349 rpm Mini : 349 to 418 rpm Normal operating range : 418 rpm Max. continuous : 450 rpm Max. transient limit (5s) NOTE A NR rotor speed of 386 rpm corresponds to a Nf speed of 39,158 rpm. 15.20 Flight Manual - Limitations Section - Page 2 - 7

  21. Engine Limitations • Ng LIMITATIONS Use of takeoff rating range MTOP, is limited to 5 minutes. Ng 67 % : Mini stabilized speed Ng = - 4 % Max. continuous rating (Ng = 97.1 %, Hp = 0, ISA) : Ng = - 4 %to Ng 0 % Takeoff rating range : Ng = 0 % Max. takeoff rating (Ng = 101.1%, Hp = 0, ISA) : Ng = + 1 % Max. transient rating (5 s) (Ng = 102.3 %, Hp = 0, ISA) -5 0 -10 NG 99.1% 5 NOTE 100% Ng corresponds to 52,110 rpm. 15.21 Flight Manual - Limitations Section - Page 2 - 7

  22. 7 5 9 3 X100 0 T4 8200 C 7 5 9 3 X100 0 T4 6500 C • Engine Limitations • T4 LIMITATIONS Use of takeoff rating range MTOP, is limited to 5 minutes. Starting Limitations : 7500 C Maximum continuous : 8650 C Max. transient (10s) Flight Limitations : 8490 C Max. continuous rating : 8490 C to 9150 C Takeoff rating range : 9150 C Max. takeoff rating 15.22 Flight Manual - Limitations Section - Page 2 - 8

  23. 4 6 2 8 PRESS 6 10 0 BAR • Engine Limitations • OIL TEMPERATURE LIMITATIONS 5 : -100 Cto 00 C Caution range : 1150 C Max. temperature 10 0 Minimum oil temperature before power application: 00 C (Oil 5 cSt). [ ‘power application’ means raising the collective ] TEMP 900 C X10 • OIL PRESSURE LIMITATIONS : 1.1 bar Mini pressure (Ng > 70% ) : 1.1 to 2 bar Caution range : 6 to 9.8 bar Caution range : 9.8 bar Max. pressure 15.23 Flight Manual - Limitations Section - Page 2 - 8

  24. Engine Controls 15.24

  25. Engine Controls Anticipator - Prevents static droop and reduces governor response time 15.25

  26. Electrical unit Twist Grips Copilot twist grip Flight detent lock Pilot twist grip Rack gear (pilot module) Copilot module rack and pinion gear Friction adjustment Ball-end rod Input pinion (pilot module) Cam Torque tube between collective pitch levers ‘Flight’ Position “TWIST GRIP” warning light microswitch Idle detection microswitch To FADEC 15.26

  27. TWTGRIP Twist Grip Components The total ‘throw’ between the idle position and the flight position is approximately 800 of travel. There are no mechanical linkages between the throttle and the fuel control, only microswitches. Idle Detection Ramp Return Coil Spring (spring loaded to “Flight” position) Idle Switch Out of ‘Flight’ Position Switch 15.27

  28. Engine Fuel System FADEC Electrical Twist Grip 15.28

  29. What is the purpose of a governor? To maintain a constant rotor speed without the tendency to overspeed or droop. This is done, depending upon power application and pedal positioning, by metering the amount of fuel going into the engine. The metering authority in the EC130 B4 is the FADEC computer. 15.29

  30. FADEC - Full Authority Digital Engine Control The FADEC is a computer, which receives information from several sources (PA, OAT, TQ, T4, N1, N2, etc.) to schedule fuel, via actuators and valves, which allow the rotor rpm to function as needed. The FADEC is a dual channel computer located in the rear cargo area, mounted on the forward wall structure. Should any information going to the primary channel fail, the back-up channel will become the primary source for the information required. The back-up for the FADEC is the EBCAU - Engine Back-Up Control Ancillary Unit. The FADEC is powered during start-up by the aircraft 28 VDC bus bar. The engine driven alternator provides primary voltage to the FADEC above 65% NG. If the FADEC alternator fails, power is then provided by the aircraft’s 28 VDC system . 15.30

  31. Engine Driven FADEC Alternator FADEC Computer 15.31

  32. Failure of the Tail Rotor Potentiometer Neutral Left Pedal Right Pedal 104 103 102 101 100 99 98 400 NR Zp > 15,000 ft NF % Zp = 10,000 ft Zp = 5000 ft 386 NR Zp < 1000 ft 0 10 20 30 40 50 60 70 80 90 100 Pedal Position (DDN) % The FADEC will automatically default to 400 NR with a loss of the T/R Potentiometer signal. 15.32

  33. Engine Control Panel EBCAU Test Switch Start Switch EBCAU switch cover is safety wire closed. It is tested ONLY as a maintenance function and is NEVER used by the pilot in flight under any circumstance! 15.33

  34. Engine Backup Control Ancillary Unit 15.34

  35. EBCAU Schematic 15.35

  36. EBCAU Back-Up Governing The EBCAU monitors NF speed and controls the fuel flow to maintain the NF between 100.5% and 103.5%. This provides surge protection. You should maintain your Torque above 10%. 15.36

  37. Back-Up Stepper Actuator Metering Unit Main Stepper Motor MAIN STEPPER ACTUATOR Resolver 15.37

  38. GOV WARNING PANEL CORRECTIVE ACTIONS Minor FADEC failure Flight Manual - Emergency Procedures - Page 3-12 15.38

  39. GOV WARNING PANEL CORRECTIVE ACTIONS • Permanently lighted : • Governing function degraded. • 1. Collective ………… AVOID abrupt power • changes. Minor FADEC failure Flight Manual - Emergency Procedures - Page 3-12 15.39

  40. GOV WARNING PANEL CORRECTIVE ACTIONS • Permanently lighted : • Governing function degraded. • 1. Collective ………… AVOID abrupt power • changes. • 2. IAS ………………… MAINTAIN below VNE • power off • LAND AS SOON AS PRACTICABLE • On ground : do not start engine. Minor FADEC failure Flight Manual - Emergency Procedures - Page 3-12 15.40

  41. GOV WARNING PANEL CORRECTIVE ACTIONS • Permanently lighted : • Governing function degraded. • 1. Collective ………… AVOID abrupt power • changes. • 2. IAS ………………… MAINTAIN below VNE • power off • LAND AS SOON AS PRACTICABLE • On ground : do not start engine. • Flashing at idle or during starting or shut • down : • Governor redundancy failure. Minor FADEC failure CONTINUE FLIGHT Flight Manual - Emergency Procedures - Page 3-12 15.41

  42. GOV WARNING PANEL CORRECTIVE ACTIONS Major governor failure Emergency mode engaged Flight Manual - Emergency Procedures - Page 3-12 15.42

  43. GOV GOV WARNING PANEL CORRECTIVE ACTIONS • IN FLIGHT: • 1. Flight Parameters ………… CHECK • Emergency mode automatically self-engages. • [ also ] illuminates Major governor failure Emergency mode engaged Flight Manual - Emergency Procedures - Page 3-12 15.43

  44. GOV GOV WARNING PANEL CORRECTIVE ACTIONS • IN FLIGHT: • 1. Flight Parameters ………… CHECK • Emergency mode automatically self-engages. • [ also ] illuminates • 2. Collective Pitch … Avoid abrupt changes • Maintain Ng > 80% Hp < 20,000 ft • Maintain Ng > 85% Hp > 20,000 ft Major governor failure Emergency mode engaged Flight Manual - Emergency Procedures - Page 3-12 15.44

  45. GOV GOV (Continued WARNING PANEL CORRECTIVE ACTIONS • IN FLIGHT: • 1. Flight Parameters ………… CHECK • Emergency mode automatically self-engages. • [ also ] illuminates • 2. Collective Pitch … Avoid abrupt changes • Maintain Ng > 80% Hp < 20,000 ft • Maintain Ng > 85% Hp > 20,000 ft Major governor failure Emergency mode engaged LAND AS SOON AS PRACTICABLE Flight Manual - Emergency Procedures - Page 3-12 15.45

  46. GOV WARNING PANEL CORRECTIVE ACTIONS Approach and Landing : Make a powered approach. Avoid steep angle. Major governor failure Emergency mode engaged Flight Manual - Emergency Procedures - Page 3-12 15.46

  47. GOV WARNING PANEL CORRECTIVE ACTIONS Approach and Landing : Make a powered approach. Avoid steep angle. After touchdown, shut-down : Collective pitch…. SLOWLY down to low pitch Starting selector ……OFF NOTE This failure can also results in loss of Ng and torque parameters on the VEMD Major governor failure Emergency mode engaged Flight Manual - Emergency Procedures - Page 3-12 15.47

  48. GOV WARNING PANEL CORRECTIVE ACTIONS • Approach and Landing : • Make a powered approach. • Avoid steep angle. • After touchdown, shut-down : • Collective pitch…. SLOWLY down to low pitch • Starting selector ……OFF • NOTE • This failure can also results in loss of Ng and torque parameters on the VEMD • DURING ENGINE STARTING : • Starting selector ………. OFF position • immediately Major governor failure Emergency mode engaged Flight Manual - Emergency Procedures - Page 3-12 15.48

  49. Engine Fire Detection There are 3 bimetallic sensors on the engine which are fully enclosed, (not open as in the 350 Series). 15.49

  50. “Gong!” ENGFIRE ENG FIRE 15.50

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