1. 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

2. Chapter 15 - Engine
Engine Monitoring Components ……………………….…………………….…………
N1 Speed Sensing ……………..………………………….…………………………………. 15.5
Ng / Ng Indicator Failure …………………………………………………………………
N2 Speed Sensing ………………………………...…………………………………………. 15.7
NR Indicator Failure …………………………………….…...………………………………. 15.8
Nf Indicator Failure ………………………………….………………………………………
Torque Monitoring ……………………………………..……………………………………
Torquemeter Failure ………………………………………………….……………………
Ng and Torquemeter Indicator Failure ………………………………………………… 15.12
T 4.5 Monitoring ………………………………...……………………………………………
T4 Indicator Failure …………………………………………………………………………
Engine Oil Pressure Limitations …………………………………………………………… 15.15
Engine Oil Temperature Limitations ……………………………………………………… 15.16
First Limitation Indicator ……….…………………………………………………………… 15.17
Torque Limitations …………………………….……………………………………………
Main Rotor Limitations …………………………………………….………………………… 15.19
Nf Limitations ……………………….………………………………………………………… 15.20
Ng Limitations …………………………………..……………………………………………
T4 Limitations …………………………...……………………...……………………………
Engine Oil Temperature Limitations and Engine Oil Pressure Limitations ….……
Engine Controls …………………...…………………………………………………………
Twist Grips ………..…………………………………………………………………………… 15.26
15.2

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

4. Engine Monitoring Components
15.4

5. N1 Speed Sensing
15.5

6. NG / NG Indicator Failure5 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
15.6

7. N2 Speed Sensing
15.7

8. 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

9. 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

10. Torque Monitoring
15.10

11. 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
15.11

12. 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
15.12

13. T4.5 Monitoring
8 Double Probes
15.13

14. T4 Indicator Failure Respect Ng and Torque limitations5 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

15. 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

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

17. 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

18. 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

19. 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

20. 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

21. 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 = %, 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

22. 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

23. 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

24. Engine Controls
15.24

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

26. 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

27. (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

28. Engine Fuel System FADEC Electrical Twist Grip 15.28
ENGINE FUEL SYSTEM GENERAL
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
NF %
Zp > 15,000 ft
Zp = 10,000 ft
Zp = 5000 ft
386 NR
Zp < 1000 ft
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 Minor FADEC failure CORRECTIVE ACTIONS WARNING PANEL
Flight Manual - Emergency Procedures - Page 3-12
15.38

39. 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

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.
GOV
Minor FADEC failure
Flight Manual - Emergency Procedures - Page 3-12
15.40

41. 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

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

43. 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

44. 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

45. 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

46. 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

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

48. 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

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!”
ENG FIRE
ENG FIRE
15.50

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

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.
ENG FIRE
Fire in engine bay
Flight Manual - Emergency Procedures - Page 3-11
15.52

53. 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

54. 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

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
ENG FIRE
LAND IMMEDIATELY
Fire in engine bay
Flight Manual - Emergency Procedures - Page 3-11
15.55

56. 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

57. 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 ft
5. Cyclic………………….... FLARE = ~
(Continued
Flight Manual - Emergency Procedures - Page 3-2
15.57

58. 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

59. 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

60. 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

61. 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

62. 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

63. Review
Questions
15.63

64. 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.

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

66. 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.

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

68. 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.

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

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

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

72. 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