Initial Pilot Ground School Engine Monitoring, Controls, Fuel System 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 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

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

Engine Monitoring Components 15.4

N1 Speed Sensing 15.5

NG / NG Indicator Failure 5 3 7 9 x100 -8 -4 TQ -12 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

N2 Speed Sensing 15.7

NR Indication Failure Collective ……… Maintain Tq >10%. NR reading is given by Nf pointer. 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

NR gauge ……… CHECK in green range with Tq > 0. Nf Indication Failure NR gauge ……… CHECK in green range with Tq > 0. 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

Torque Monitoring 15.10

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

NG & Torquemeter Indications Failure 89.1 NG & Torquemeter Indications Failure T4 820 0C 5 3 7 9 x100 T4 limit of 8100 C. -8 -4 TQ -12 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. GOV GOV LAND AS SOON AS PRACTICABLE Flight Manual - Emergency Procedures - Page 3 - 10 15.12

T4.5 Monitoring 8 Double Probes 15.13

T4 Indicator Failure Respect Ng and Torque limitations 5 3 7 9 x100 -8 -4 TQ -12 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

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

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 ] Flight Manual - Limitations Section - Page 2 - 8 15.16

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. - “Gong!” Use of P2 air bleeds is forbidden above the engine maximum continuous rating (Ng or T4) 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. NOTE The values [shown] are given as examples. Flight Manual - Limitations Section - Page 2 - 6 15.17

Main Transmission Limitations TORQUE LIMITATIONS 6 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 (5 s) 10 4 x 10 2 TQ 99 % NOTE Use of Takeoff rating torque range has no time limit. 100% torque corresponds to 536 kW at 386 NR rpm. Flight Manual - Limitations Section - Page 2 - 6 15.18

Main Rotor Limitations It is prohibited to use the rotor brake prior to engine shutdown. Minimum time between two consecutive brakings: 5 minutes. 7 : 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 Flight Manual - Limitations Section - Page 2 - 5 15.19

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

Engine Limitations 99.1% Ng LIMITATIONS -5 -10 NG 5 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 -10 NG 99.1% 5 NOTE 100% Ng corresponds to 52,110 rpm. Flight Manual - Limitations Section - Page 2 - 7 15.21

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

Engine Limitations 900 C OIL TEMPERATURE LIMITATIONS 5 10 TEMP X10 : -100 C to 00 C Caution range : 1150 C Max. temperature 10 Minimum oil temperature before power application: 00 C (Oil 5 cSt). [ ‘power application’ means raising the collective ] TEMP 900 C X10 OIL PRESSURE LIMITATIONS 4 2 6 PRESS BAR 10 8 : 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

Engine Controls 15.24

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

Twist Grips To FADEC 15.26 Electrical unit Copilot twist grip Flight detent lock Pilot twist grip Copilot module rack and pinion gear Rack gear (pilot module) 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

(spring loaded to “Flight” position) Out of ‘Flight’ Position Switch 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 TWT GRIP Out of ‘Flight’ Position Switch 15.27

Engine Fuel System FADEC Electrical Twist Grip 15.28 ENGINE FUEL SYSTEM GENERAL 15.28

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

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

Engine Driven FADEC Alternator FADEC Computer 15.31

Failure of the Tail Rotor Potentiometer Neutral Left Pedal Right Pedal 104 103 102 101 100 99 98 400 NR NF % Zp > 15,000 ft 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

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

Engine Backup Control Ancillary Unit 15.34

EBCAU Schematic 15.35

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

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

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

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

LAND AS SOON AS PRACTICABLE 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. GOV Minor FADEC failure Flight Manual - Emergency Procedures - Page 3-12 15.40

LAND AS SOON AS PRACTICABLE 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. GOV Minor FADEC failure CONTINUE FLIGHT Flight Manual - Emergency Procedures - Page 3-12 15.41

Emergency mode engaged WARNING PANEL CORRECTIVE ACTIONS GOV Major gover nor failure Emergency mode engaged Flight Manual - Emergency Procedures - Page 3-12 15.42

Emergency mode engaged WARNING PANEL CORRECTIVE ACTIONS IN FLIGHT: 1. Flight Parameters ………… CHECK Emergency mode automatically self-engages. [ also ] illuminates GOV Major gover nor failure Emergency mode engaged GOV Flight Manual - Emergency Procedures - Page 3-12 15.43

Emergency mode engaged 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 GOV Major gover nor failure Emergency mode engaged GOV Flight Manual - Emergency Procedures - Page 3-12 15.44

LAND AS SOON AS PRACTICABLE 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 GOV Major gover nor failure Emergency mode engaged GOV LAND AS SOON AS PRACTICABLE (Continued Flight Manual - Emergency Procedures - Page 3-12 15.45

Emergency mode engaged WARNING PANEL CORRECTIVE ACTIONS Approach and Landing : Make a powered approach. Avoid steep angle. GOV Major gover nor failure Emergency mode engaged Flight Manual - Emergency Procedures - Page 3-12 15.46

Emergency mode engaged 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 GOV Major gover nor failure Emergency mode engaged Flight Manual - Emergency Procedures - Page 3-12 15.47

Emergency mode engaged 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 GOV Major gover nor failure Emergency mode engaged Flight Manual - Emergency Procedures - Page 3-12 15.48

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

“Gong!” ENG FIRE ENG FIRE 15.50

ENG FIRE Fire in engine bay CORRECTIVE ACTIONS WARNING PANEL Flight Manual - Emergency Procedures - Page 3-11 15.51

ENG FIRE At start-up : 1. Starting selector ……… OFF position WARNING PANEL CORRECTIVE ACTIONS At start-up : 1. Starting selector ……… OFF position 2. Emergency fuel shut-off handle ……….. AFT 3. Booster pump ………… OFF 4. CRANK …………….…... DEPRESS (10 s) 5. MASTER SW ………….. OFF 6. Rotor brake ……………. Apply (< 170 rpm) 7. Evacuate aircraft and fight fire from outside. ENG FIRE Fire in engine bay Flight Manual - Emergency Procedures - Page 3-11 15.52

ENG FIRE At start-up : 1. Starting selector ……… OFF position WARNING PANEL CORRECTIVE ACTIONS At start-up : 1. Starting selector ……… OFF position 2. Emergency fuel shut-off handle ……….. AFT 3. Booster pump ………… OFF 4. CRANK …………….…... DEPRESS (10 s) 5. MASTER SW ………….. OFF 6. Rotor brake ……………. Apply (< 170 rpm) 7. Evacuate aircraft and fight fire from outside. Hover, Takeoff, Final : Carry out a no hover, powered landing then, once on ground, apply same procedure as above. ENG FIRE Fire in engine bay LAND IMMEDIATELY (Continued Flight Manual - Emergency Procedures - Page 3-11 15.53

ENG FIRE In Flight : LAND IMMEDIATELY Fire in engine bay WARNING PANEL CORRECTIVE ACTIONS In Flight : ENG FIRE LAND IMMEDIATELY Fire in engine bay Flight Manual - Emergency Procedures - Page 3-11 15.54

ENG FIRE In Flight : 1. Collective pitch ………..…. REDUCE WARNING PANEL CORRECTIVE ACTIONS In Flight : 1. Collective pitch ………..…. REDUCE 2. IAS ……………………..…… Vy 3. Autorotative procedure … Apply 4. Emergency fuel shut-off handle ………….. AFT 5. Starting selector ………… OFF position ENG FIRE LAND IMMEDIATELY Fire in engine bay Flight Manual - Emergency Procedures - Page 3-11 15.55

ENG FIRE In Flight : 1. Collective pitch ………..…. REDUCE WARNING PANEL CORRECTIVE ACTIONS In Flight : 1. Collective pitch ………..…. REDUCE 2. IAS ……………………..…… Vy 3. Autorotative procedure … Apply 4. Emergency fuel shut-off handle ………….. AFT 5. Starting selector ………… OFF position After landing : 6. MASTER SW ………… OFF 7. Rotor brake …………… APPLY (< 170 rpm) 8. Evacuate aircraft and fight fire from outside. ENG FIRE LAND IMMEDIATELY Fire in engine bay Flight Manual - Emergency Procedures - Page 3-11 15.56

3.2 ENGINE FLAME-OUT 3.2.1 CRUISE FLIGHT ~ = AUTOROTATION PROCEDURE OVER LAND 1. Collective pitch ……… REDUCE to maintain NR in green arc. 2. IAS …………………….. Vy If relighting impossible or after tail rotor control failure 3. Twist Grip …………….. IDLE position 4. Maneuver the aircraft into the wind on final approach. At height 70 ft 5. Cyclic………………….... FLARE = ~ (Continued Flight Manual - Emergency Procedures - Page 3-2 15.57

At 20 / 25 ft and at constant attitude 6. Collective pitch ……. GRADUALLY INCREASE to reduce the rate of descent and forward speed. 7. Cyclic …………...….. FORWARD to adopt a slightly nose-up landing attitude (< 100 ). 8. Pedal ……………….. ADJUST to cancel any sideslip tendency. 9. Collective pitch ……. INCREASE to cushion touch-down. After touch-down 10. Cyclic, collective, pedal … ADJUST to control ground run. Once the aircraft has stopped 11. Collective pitch …….….. FULL DOWN 12. Rotor brake………….…. APPLY below 170 rotor rpm. Flight Manual - Emergency Procedures - Page 3-2 & 3-3 15.58

3.2.1 CRUISE FLIGHT (continued) AUTOROTATION PROCEDURE OVER WATER Apply same procedure as over land, except items 10, 11, and 12, but maneuver to head the aircraft equally between the wind and wave direction on final approach. Ditch with minimum forward (IAS < 30 kt) and vertical speed. Then apply following check list for items 10, 11, and 12. After touch-down 10. Collective pitch …………………….. MAINTAIN 11. Door emergency handles ………… PULL-UP 12. Rotor brake ………………………… APPLY Abandon aircraft once the rotor has stopped. Flight Manual - Emergency Procedures - Page 3-3 15.59

3.2.1 CRUISE FLIGHT (continued) IN FLIGHT RELIGHTING According to available height and cause of flame-out : 1. Starting selector ………………. OFF position 2. Fuel pump ……………………… ON 3. Starting selector ………….…… ON position The relighting sequence will therefore be automatically carried out as soon as Ng < 17%. After relighting 4. Fuel pump ………………………. OFF At least 1000 ft are necessary to complete relighting procedure after flame-out. Flight Manual - Emergency Procedures - Page 3-3 15.60

3.2 ENGINE FLAME-OUT 3.2.2 HOVER-IGE 1. Collective ………………. MAINTAIN 2. Pedals ……………………CONTROL YAW 3. Collective ………………. INCREASE as needed to cushion touch-down. 3.2 ENGINE FLAME-OUT Flight Manual - Emergency Procedures - Page 3-4 15.61

3.2 ENGINE FLAME-OUT 3.2.3 HOVER-OGE 1. Collective pitch …..…… FULLY DOWN When NR stops decreasing 2. Cyclic…………………….. FORWARD to gain airspeed according to available height. 3. Autorotation procedure…. APPLY WARNING SAFE AUTOROTATIVE LANDING CAN NOT BE WARRANTED IN CASE OF A FAILURE IN HOGE BELOW THE TOP POINT OF THE HV DIAGRAM (REFER TO SECTION 5) OR IN A CONFINED AREA. Flight Manual - Emergency Procedures - Page 3-4 15.62

Review Questions 15.63

118. What is the function of the anticipator? B. To decrease governor response time and eliminate static droop by sending a collective command to the governor.

119. What is the procedure for a failed torque meter indication? B. Limit the NG speed according to the Flight Manual.

120. What does the term “Delta NG” refer to? C. The difference between the actual (indicated) take-off power and the maximum computed take-off power.

121. What component(s) monitor torque? D. Reference shaft and associated sensor.

122. What will occur on the VEMD when it loses a required FLI parameter? A. The triple indication page will appear with the lost parameter displaying an amber arc.

123. How many engine fire detectors are on the EC130 B4? C. Three

124. If any one of the engine fire detectors senses an abnormal temperature rise, what cockpit indications are given? Gong! B. ENG FIRE

125. When may the EBCAU TEST switch be utilized in flight? D. NEVER!

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