FIRE PROTECTION

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 .. 1
5.14 Engine Oil Pressure Limitations
15.15 Engine Oil
Temperature Limitations 15.1
6 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 Govern
or Caution Light .. 15.4
1 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
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
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
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
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
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 gt 70)
• Caution range
• 1.1 to 2 bar
• Normal pressure
• 2 to 6 bar
• Caution range
• 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. -

Use of P2 air bleeds is forbidden above the
engine maximum continuous rating (Ng or T4)
NOTE The values shown are given as examples.
Flight Manual - Limitations Section - Page 2 - 6
15.17
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 (5 s)
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.
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.
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 lt 360 rpm High NR
aural warning gt 410 rpm
Flight Manual - Limitations Section - Page 2 - 5
15.19
20

• 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 (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
• 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.
Flight Manual - Limitations Section - Page 2 - 7
15.21
22

• 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 (10 s)
Flight Limitations
8490 C Max. continuous rating 8490 C to 9150
C Takeoff rating range 9150 C Max. takeoff
rating
Flight Manual - Limitations Section - Page 2 - 8
15.22
23

• Engine Limitations
• OIL TEMPERATURE LIMITATIONS

5
-100 C to 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 gt 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)
Friction adjustment
Copilot module rack and pinion gear
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
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 aircrafts 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 gt 15,000 ft
NF
Zp 10,000 ft
Zp 5000 ft
386 NR
Zp lt 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
WARNING PANEL
CORRECTIVE ACTIONS
Minor FADEC failure
Flight Manual - Emergency Procedures - Page 3-12
15.38
39
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
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
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
WARNING PANEL
CORRECTIVE ACTIONS
Major gover nor failure Emergency mode engaged
Flight Manual - Emergency Procedures - Page 3-12
15.42
43
WARNING PANEL
CORRECTIVE ACTIONS

• IN FLIGHT
• 1. Flight Parameters CHECK
• Emergency mode automatically self-engages.
• also
  illuminates

Major gover nor failure Emergency mode engaged
Flight Manual - Emergency Procedures - Page 3-12
15.43
44
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 gt 80 Hp lt 20,000
  ft
• Maintain Ng gt 85 Hp gt 20,000
  ft

Major gover nor failure Emergency mode engaged
Flight Manual - Emergency Procedures - Page 3-12
15.44
45
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 gt 80 Hp lt 20,000
  ft
• Maintain Ng gt 85 Hp gt 20,000
  ft

Major gover nor failure Emergency mode engaged
LAND AS SOON AS PRACTICABLE
Flight Manual - Emergency Procedures - Page 3-12
15.45
46
WARNING PANEL
CORRECTIVE ACTIONS
Approach and Landing Make a powered
approach. Avoid steep angle.
Major gover nor failure Emergency mode engaged
Flight Manual - Emergency Procedures - Page 3-12
15.46
47
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 gover nor failure Emergency mode engaged
Flight Manual - Emergency Procedures - Page 3-12
15.47
48
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 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
ENG FIRE
15.50
51
WARNING PANEL
CORRECTIVE ACTIONS
Fire in engine bay
Flight Manual - Emergency Procedures - Page 3-11
15.51
52
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 (lt 170 rpm)
• 7. Evacuate aircraft and fight fire from
  outside.

Fire in engine bay
Flight Manual - Emergency Procedures - Page 3-11
15.52
53
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 (lt 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.

Fire in engine bay
LAND IMMEDIATELY
Flight Manual - Emergency Procedures - Page 3-11
15.53
54
WARNING PANEL
CORRECTIVE ACTIONS

• In Flight

LAND IMMEDIATELY
Fire in engine bay
Flight Manual - Emergency Procedures - Page 3-11
15.54
55
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

LAND IMMEDIATELY
Fire in engine bay
Flight Manual - Emergency Procedures - Page 3-11
15.55
56
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 (lt 170 rpm)
• 8. Evacuate aircraft and fight fire from
  outside.

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 70 ft
• 5. Cyclic.... FLARE

15.57
Flight Manual - Emergency Procedures - Page 3-2
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 (lt 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.

15.58
Flight Manual - Emergency Procedures - Page 3-2
3-3
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 lt 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.

15.59
Flight Manual - Emergency Procedures - Page 3-3
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 lt 17.
• After relighting
• 4. Fuel pump . OFF
• At least 1000 ft are necessary to complete
  relighting
• procedure after flame-out.

15.60
Flight Manual - Emergency Procedures - Page 3-3
61
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
15.61
Flight Manual - Emergency Procedures - Page 3-4
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.
15.62
Flight Manual - Emergency Procedures - Page 3-4
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?
71
125. When may the EBCAU TEST switch be utilized
in flight?
D. NEVER!
72
EC 130 B4 Initial Pilot Ground School End of
Chapter 15 - Engine - Part 2 Engine Monitoring,
Controls, Fuel System and Fire Detection