ATA 31 Indicating and recording systems.pdf

For instruction only
Training Manual
ATA 31 - Indicating and recording systems H125
T1
31 - 1
Ed: 06-2016
Training Manual
ATA 31 - Indicating and recording systems
Ed: 06-2016
H125
T1

Training Manual
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List of effective pages
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Table Of Content
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1. General presentation........................................................ 5
1.1 Overview ................................................................... 5
2. Indicating systems ........................................................... 7
2.1 Overview ................................................................... 7
2.2 Description : instrument panel ................................... 9
2.3 Description : indicators ............................................ 11
2.4 Description : lights ................................................... 13
2.5 Architecture ............................................................. 15
2.6 Location................................................................... 17
2.7 Controls and displays : Caution and Warning Panel 19
2.8 Controls and displays : System Control Unit .......... 25
2.9 Controls and displays : Vehicle and Engine
Multifunction Display........................................................... 29
2.10 Normal functioning : warning information ............... 31
2.11 Normal functioning : Ancillary System Unit............. 33
2.12 Normal functioning : Caution and Warning Panel... 35
2.13 Normal functioning : audio alarm............................ 37
2.14 Normal functioning : test.......................................... 45
3. VEMD ............................................................................... 47
3.1 Overview ................................................................. 47
3.2 Introduction.............................................................. 49
3.3 Description .............................................................. 51
3.4 Architecture..............................................................53
3.5 Location ...................................................................55
3.6 Controls....................................................................57
3.7 Displays ...................................................................59
3.8 Limitation displays principle .....................................65
3.9 Status detection .......................................................67
3.10 Flight mode pages ...................................................69
3.10.1 3 infos page.......................................................69
3.10.2 "vehicle/engine" page .......................................71
3.10.3 Performances ....................................................73
3.10.4 First Limitation Indicator (FLI)............................75
3.10.5 ENGINE POWER CHECK...............................77
3.10.6 FLIGHT REPORT.............................................83
3.11 Messages places .....................................................85
3.12 EECU Messages......................................................87
3.13 Flight mode : degraded functioning..........................89
3.14 Configuration mode page.......................................103
3.15 Configuration mode operation................................105
3.16 Maintenance mode page........................................109
3.16.1 Pages dîsplayed..............................................109
3.16.2 Access to the Maintenance mode....................111
3.16.3 Flight report ....................................................113
3.16.4 Failure diagnosis .............................................115
3.16.5 Complete diagnosis.........................................117
3.16.6 Parameters type 1 ...........................................119

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3.16.7 Parameters type 2........................................... 121
3.16.8 Parameters type 3........................................... 123
3.16.9 Over limit......................................................... 125
3.16.10 Engine power check........................................ 127
3.16.11 Fonctional times.............................................. 129
3.16.12 EECU data..................................................... 131
3.16.13 Data loading................................................... 133

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1. General presentation
1.1 Overview
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1.1 Overview
The indicating and recording system is composed of the Indicating
system and the VEMD.

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1.1 Overview
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2. Indicating systems
2.1 Overview
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2.1 Overview
The purpose of the Indicating system is to inform the pilot, by
visual and aural alarms, when :
 during flight, a caution or warning situation occurs,
 after flight, some system needs a maintenance action.

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2.1 Overview
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2.2 Description : instrument panel
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On the instrument panel, the indicating system is composed
of:
 For the visual part , the Caution Warning Panel (CWP), the
NR/NF indicator, Airspeed indicator, the "LIGHT" status
indication and the VEMD,
 Audible warnings are produced via the CWP,VEMD the ASU
No.1 and the ICS system,
 The VEMD also has the capability to record specific indications.

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2.3 Description : indicators
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The indicating system generally indicates an abnormal
operating situation.
However, there are correct operation indicators which are
mainly used to test some systems. Two types of indicators are
used:
 The visual indicators,
 The aural warnings.
The visual indicators are activated by one of the following:
 Lighting via the closure of a contact providing a supply,
 Lighting via the closure of a contact providing a ground,
 Lighting via the opening of a contact.
The aural alarm can be a gong or a modulated signal heard
in the headset.
The aural alarm, which always reinforces a visual indicator, is
only used for VERY SERIOUS functional cases.

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2.4 Description : lights
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The “GREEN" lights indicate a normal or correct condition of
operation.
The “AMBER" lights indicate an abnormal operating
configuration or a degraded level of functionality.
The "Red" lights are WARNING lights, they require immediate
action by the pilot and because they are serious they are linked to
an aural alarm.

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2.5 Architecture
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2.5 Architecture
Architecture of the Indicating Systems for the AS350.

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2.5 Architecture
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2.6 Location
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2.6 Location
The VEMD is used to display engine and vehicle parameters. The
VEMD will transmit FLI warnings to the ASU for processing. The
CWP is used to display amber Cautions and Red warnings. In some
cases audible warnings are initiated directly from the CWP. The
W/LT TST is used to illuminate all the lights on the panel to verify
proper operation.

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2.6 Location
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2.7 Controls and displays : Caution and Warning Panel
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The CWP is divided in two parts:
 two vertical lines on the right hand side for the red warning
lights,
 six vertical lines on the left hand side for the amber
caution lights.
Her is an example of the CWP light to corresponding sensor.
For additional information as to the relationship between the
indicator light and the corresponding sensor refer to the Flight
Manual, chapter 3 (emergency procedures).

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The "HORN" switch on the multi block panel disables the audible
alarms associated with the RED warnings lights,FLI alarms and
rotor speed warnings.

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REMINDER:
All RED warning lights like this one will generate an audible alarm.
Note: the RED BATT TEMP light is associated with the installation
of the Nicad battery only.

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2.8 Controls and displays : System Control Unit
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Control Panel:
This control panel arrangement is the multi block configuration, with
the maximum switch options.

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This configuration is referred to as the System control Console
(SCU). The panel is shown with the maximum system switch
options.

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2.9 Controls and displays : Vehicle and Engine Multifunction Display
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2.9 Controls and displays : Vehicle and Engine
Multifunction Display
The VEMD color code is :
 White for Information,
 Blue for Units,
 Yellow for Caution,
 Red for Warning and fuel level.

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2.9 Controls and displays : Vehicle and Engine Multifunction Display
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2.10 Normal functioning : warning information
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Schematic diagram of the sound generation for the different
indicating systems.
Warning information can be initiated from:
 Switches or sensors directly linked to the CWP,
 Sensors or detectors that are linked to the ASU cards,
 FLI signals from the VEMD that are sent to the ASU,
 NR speed signals that are linked to the ASU for Min or Max rotor
warnings.

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2.11 Normal functioning : Ancillary System Unit
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The engine fire detection system is processed by the No 1 PCB of
the ASU and sent to the Caution Warning Panel, CWP.
The NR speed sensing signal is processed by the PCB No 1.
The PCB No 1 also processes the FLI warnings and the red
indicator light alarms.
"Each of these signals generates an aural alarm when the ""HORN"
switch is configured to allow audible.
The NR speed sensing signal is also processed by a frequency-
voltage converter on PCB No 2, and sent to the VEMD for recording
purposes.
The battery over temperature detection is processed by the PCB No
2, and sent to the CWP.
The PP12 bus bar voltage is converted by the PCB No 2 and sent
to the VEMD for display.
The generator output current is processed by a converter on PCB
No 2, and sent to the VEMD.
The optional exterior load-indicator signal is processed by a filter on
the PCB No 2, and sent to the VEMD.
A signal from the Electronic Engine Control Unit , EECU, is
processed by the PCB No 3, the Engine Backup Control Auxiliary
Unit, EBCAU.
The EBCAU, is dedicated to the engine back-up control and
connected to the CWP.

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2.12 Normal functioning : Caution and Warning Panel
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Each CWP light has six integrated LEDs each and is powered by a
dual power-supply in order to preserve the indicating system if one
power-supply or lamp is faulty.
By pressing the W/LT TST button, all the lights of the CWP will be
illuminated.
The brightness of the CWP lights are automatically decreased when
the light selector is switched to the “Night” position.

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2.13 Normal functioning : audio alarm
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When “Horn” is off:
There are no audio alarm and the “HORN” caution light
illuminates on the Caution and Warning Panel.

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When the « HORN » switch is on, it’s possible to receive 4 types of
audio alarms.
The first type of audio alarm is a « GONG », generates by the CWP
when a red warning light comes on.

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The second type of audio alarm is a 650 Hz signal, generates by
the ASU card when a First Limitation Information, FLI, occurs.

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The two last type of audio alarm are linked to the rotor rate, NR:
 A 310 Hz modulate 3 Hz when NR is above NR max,
 A 310 Hz continues when NR is below NR min,
This two audio alarms are generated by the ASU card when NR
value is out of range.

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2.14 Normal functioning : test
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To do a test of the indicating system, the helicopter must be
electricaly supplied.
When the « W/L TST » test button is depressed, all the CWP lights
goes on and the VEMD displays on both screens a test pattern.
When the test button is released, the TRQ indicates 100% for 2
seconds, then decreases to 0.

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3. VEMD
3.1 Overview
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3. VEMD
3.1 Overview
The system is composed by the Vehicle and Engine Multifunction
Display (VEMD) and is used to display the engine and airframe
parameters.

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3. VEMD
3.1 Overview
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3. VEMD
3.2 Introduction
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3.2 Introduction
The VEMD displays all the necessary engine and vehicle
parameters and performs the following complementary function :
 Engine Power Check,
 maximun take-off weight in ground effect,IGE, and out of ground
effect, OGE,
 performance computation,
 NR datum computation,
 N1 and N2 cycles counting,
 Usage Counter,
 Overlimit recording,
 VEMD and associated sensors maintenance.

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3. VEMD
3.2 Introduction
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3. VEMD
3.3 Description
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3.3 Description
The VEMD is made of three modules:
two processor modules and a display module.
The display module includes two active liquid crystal matrix
and a control keys panel. The two processor modules receive
and process the same data and after, compare their
respective results. An error message is displayed if a
discrepancy is detected between the two processor results.
If one of the two module fails, the functions are still available
on the other one.

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3. VEMD
3.3 Description
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3. VEMD
3.4 Architecture
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3.4 Architecture
The VEMD is linked to :
 The ASU cards, to receive data like Voltage, Current or NR
values, and to send the FLI alarms,
 The lighting system and the OFF/DAY/NIGHT Switch, for
the lighting supply and the internal lighting control,
 The W/LT TST button, to do a test of the VEMD,
 The electrical essential and secondary bus bars, through
breakers, for the Power supply,
 The GPS, used for the failure datation,
 The P0 static port, used for the Zp altitude computing,
 The Temperature probe, used for the Outside Air
Temperature, OAT, computing,
 The Collective grip, equiped with a remote “SCROLL”
control,
 The Electronic Engine Control Unit, by a dual ARINC 429
line, for data exchange,
 The Fuel probe, to display the fuel quantity,
 In optional, the flowmeter and the sling load indicator, to
display this equipment informations. A Data download
connector links to the VEMD is used for the VEMD
memories data download.

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3. VEMD
3.4 Architecture
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3. VEMD
3.5 Location
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3.5 Location
Location for the AS 350 VEMD.

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3.5 Location
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3. VEMD
3.6 Controls
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3.6 Controls
Ten push-buttons are vertically layed on the right side of the
V.E.M.D front panel. They are divided in 3 functional assemblies :
1/ “OFF1" and "OFF2" push-buttons :
Pressing "OFF1" or "OFF2" push-buttons switch OFF or ON the
dedicated processor module and the associated screen (upper
screen for the lane 1 and lower screen for the lane 2).
2/ "SCROLL", "RESET", "SELECT", "ENTER", "+" and "–" push-
buttons :
These push-buttons are dedicated for the V.E.M.D. controls :
 "SCROLL“to select the desired page ("SCROLL" control is also
available on the collective sticks),
 "RESET" to return to the nominal page,
 "SELECT" to select a field,
 "+" and "–" to modify a value,
 "ENTER“ to validate a field.
3/ "BRT +" and "BRT –" push-buttons :
Pressing these push-buttons makes the brightness of the screens to
be progressively and simultaneously modified, "BRT +" to increase
the brightness and "BRT –“ to decrease it.

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3.6 Controls
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3. VEMD
3.7 Displays
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3.7 Displays
The VEMD displays the following vehicle parameters :
 The Fuel quantity, FUEL QTY, with a analogic scale and a
numerical value,
 The Outside Air Temperature, OAT,
 The Fuel flow, FF, and remaining flight time, END,
estimated with the FUEL QTY and the FF values,
 The Starter/Generator current, I/GEN, used during starting
phase and provided during the flight,
 The Bus voltage, U/BUS, voltage value mesured on the
main bus bar,
 The Message places, used to display failure information.

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3.7 Displays
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3. VEMD
3.7 Displays
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The VEMD displays the following engine parameters :
 The Free Turbine Input Temperature, TOT (Gas Generator
Temperature Outside Turbine),
 The Gas Generator rate, N1 and the delta N1 (deviation in
respect to N1 at Maximum Take-Off Power),
 The Engine output Torque, TRQ,
 The Oil Temperature and Pressure, ENG OIL TEMP and
ENG OIL PRESS,
 The P2 indication, meanning than some P3 air is pickup
from the engine,
 The Bleed valve flag, indicating of the openning of the
bleed valve,
 The EECU Data, used to display current internal parameters
of the engine computer.

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3.7 Displays
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3. VEMD
3.7 Displays
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The FLI.

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The Red color is used to display the Safety limits or the Takeoff
Limitations.
The Amber or Yellow color is used to display the Caution range or
the Takeoff Rating range.
A Transcient Limit is displayed for the three main parameters, N1,
TOT and TRQ (also in FLI display mode).
This limit is indicated by a Red Triangle.
Note:
Values for each parameters are found in the Flight Manual,
Section2.

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Depending on both N1 and NR parameter values, the VEMD
manages three states of engine status : STOP, START and
FLIGHT.
The commutation threshold between these different status are :
- The STOP state is set when N1 is under 10% and NR under 70
Rpm.
- For N1 > 10% and NR > 70 Rpm, the engine status switches from
STOP to START state,
- When N1 reaches 60%, the engine switches into FLIGHT status
and, the First Limitation Indication, FLI, is automatically displayed
on the VEMD.
At the end of the flight, the pilot switches off the engine and when
N1 decrease under 50%, the engine status switches back to
START, or Re-START, state.
After, when N1 drop under 10% and NR under 70 RPM, the current
flight is completed and recorded in the VEMD memory while the
Flight Report page is displayed on the VEMD.
The flight number is increased for the beginning of the new flight
and the status of the engine is STOP.

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3.10.1 3 infos page
As saw before, the VEMD detects three operating engine
status: shutdown (STOP), starting (START) and FLIGHT
modes.
During STOP or START operations, the VEMD displays on the
upper screen, the ENGINE "3 infos" page comprising :
 an analog scale and a digital value of TOT with starting
limitations. The TOT parameter is sent from EECU to the
VEMD,
 an analog scale and a digital value of N1. The N1
parameter is sent by the EECU to the VEMD. The VEMD
computes the DELTA N1, yellow area of the N1 scale,
which is the deviation between the actual N1 and N1 at
maximal Take-off power,
 an analog scale and a digital value of Torque. The Torque
parameter is received from the EECU,
 an analog scale and a digital value of Fuel quantity. The
fuel quantity signal (DC Voltage 0-11,5V) is received from
the fuel probe (refer to fuel system chapter),
 a digital value of OAT. Computes by the VEMD with OAT
analog signal (100 Ohms at 0 °C platinium resistance)
received from the temperature probe,
 P2 pick up flag. If the sand filter system (optionnal
equipment) is operative a P2 flag is displayed on the 3
infos page(and FLI page). This discrete signal is received
from the SAND FILTER installation,
 Bleed Valve Flag. The flag is a green and white hatched
rectangle. Engine bleed valve in open state is displayed
with the flag on the 3 infos page(and FLI page). This
discrete signal is received from the EECU.

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3.10.2 "vehicle/engine" page
During STOP, START or FLIGHT operations the VEMD
displays, on the lower screen, the "vehicle/engine" page
comprising :
 two analog scale linked with a digital value of engine oil
pressure and temperature. The engine oil pressure and
temperature parameters and their limitations are received by
the VEMD from the EECU,
 a digital value of starter/generator current , I/GEN,
corresponding to the current used by the starter (negative
value) or to the current provided by the generator (positive
value).This analog signal is measured on a shunt and
adapted by the ASU board,
 a digital value of the main bus bar voltage, U/BUS. The
bus voltage analog signal is measured on the main bus
bar and adapted by the ASU board,
 a digital value of fuel flow, FF. The fuel flow parameter is
received from the EECU,
 a digital value of remaining flight time. Using FF and Fuel
Quantity values, the VEMD computes the remaining flight
time (END).

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3.10.3 Performances
The Performance weight function allows knowing the maximum
weight which can be carried up by the helicopter in ground
effect and out ground effect. Pressing "SCROLL" twice
displays the "Performance" page. The pilot then uses the "+",
"–" and "ENTER" keys to record the payload carried.
EEW: Equipped Empty Weight, pilot input data, set to the last
pilot input value at power ON,
CREW: pilot input data, set to 80Kg at power ON,
PAY LOAD: pilot input data, set at power ON to the value
wich leads to a AUW value equal to 2250kg (2800 with
SLING) for AS350 B3e or 2500Kg (3050 with SLING) for
EC130 T2,
USABLE FUEL: present measured value,
SLING LOAD: present measured value if the sling is selected
as installed in configuration page for AS350 B3 or powered
for EC130T2.
The All Up Weight , AUW, is the sum of:
EEW + CREW + PAY LOAD + USABLE FUEL + SLING
LOAD (if installed).
AUW is displayed in yellow if > 2250kg (2800 with SLING) for
AS350 B3e or 2500Kg (3050 with SLING) for EC130 T2.
The Maximum take off weight IGE and OGE is computed as
function of Zp and T0 displayed on the performance page
(measured or pilot input values).
IGE and/ OGE are displayed in yellow if its lower than AUW
value.

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3.10.4 First Limitation Indicator (FLI)
During flight operation, N1 exeeds 60%, the VEMD switches
over automatically to the "FLIGHT" display. The upper LCD
shows then all the engine limitation data on the FLI, the First
Limitation Indicator.
Engine parameters are displayed with FLI (First Limitation
Indicator) symbology on the upper screen if following
conditions are fulfilled:
 Flight state (N1 exeeds 60%),
 No parameter failure or inconsistency,
 No pilot request for 3 info page display.
The FLI page shows also the fuel quantity, the outside air
temperature "OAT", the value of the "P2" air pick-off, the
status of the bleed valve and a message area.
FLI computation: The three parameters N1, TOT and Torque
are converted in a common scale which is the parameter FLI
value.
For the three parameters:
 0% corresponds to zero power,
 96% corresponds to Maximum Continuous Power (MCP),
 100% corresponds to Maximum Take-Off Power (MTOP),
 104% corresponds to Maximum Transient Power (MTP).
The VEMD generates an aural warning when:
 at least one of the N1, TOT or TRQ parameters exceeds
its value at maximum take-off power (MTOP) for longer
than 1,5 seconds,
 at least one of the N1, TOT or TRQ paramaters, summed
with a constant, exceeds the Maximum Transient Power
(MTP).

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3.10.5 ENGINE POWER CHECK
In compliance with the Flight Manual, the pilot can perform an
engine health check by selecting "Engine Power Check".
In conjunction with the Electronic Engine Control Unit (EECU),
the VEMD records the parameters N1, TOT and Torque, and
displays the torque margins / TOT and torque margins / N1.
ENGINE POWER CHECK, first page:
The VEMD checks:
 Sand filter not active (if active, message SWITCH OFF
SAND FILTER is displayed),
 Generator electrical power lower than a recorded value in
the VEMD (message REDUCE ELEC POWER
CONSUMPTION, if not),
 N1 and Torque value lower than TOP value (message
DECREASE N1, if not),
 TRQ and N1 higher than a minimum value (if not message
INCREASE N1).
When all the conditions are satisfied, the EPC is conducted
automatically.

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ENGINE POWER CHECK, second page:
During the check the pilot have to maintain more steady flight
condition (3 phases), the symbology represents the check
evolution.

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ENGINE POWER CHECK, third page:
Parameters used for the EPC : N1, N2, TOT, Zp, TRQ and
OAT.
At the end of the test, the result is displayed with :
 TRQ iso TOT margin with a pourcentage value and a «
GOOD » (positive margin) or « BAD » (negative margin)
indication,
 TRQ iso N1 margin with a pourcentage value and a
"GOOD" (positive margin) or "BAD" (negative margin)
indication.

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3.10.6 FLIGHT REPORT
At the end of the flight, N1 < 10% and NR < 70 rpm, the
flight report symbology is automatically displayed on the lower
screen.
The flight report symbology presents the following data:
 Flight number: incremented when, at the end of a "flight"
status, the N1 drops below 10 % and NR is lower than 70
rpm,
 Duration of the flight: correspond to the time of the flight
status. When N1 value rises above 60 %, the flight time
counter starts. It stops when the N1 value decreases and
drops below 50%,
The flight duration ignores the take-off and landing phase of
aircraft.
 Usage: Creep damage counter, sent by the EECU on Arinc
line 429. The maximum value displayed could be 400 %
but when 261 % is reached, the Engine Module M03 must
be removed,
 CYCLE N1: Number of N1 cycles during the flight and total
number of N1 cycles.,
 CYCLE N2: Number of N2 cycles during the flight and total
number of N2 cycles,
 Indication "OVERLIMIT DETECTED" if parameter limits have
been exceeded during the flight,
 Indication "FAILURE DETECTED" if failure have been
detected on VEMD associated sensors during the flight. All
the recorded data can be accessed in the maintenance
mode.

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In case of a failure detected by the VEMD, two message area, one
for each screen, are used to display information concerning this
failure or action to be done by the pilot.

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3.12 EECU Messages
During flight, the crew members can use the SELECT button
in order to get EECU messages.
The parameters available are the following (in the order of
apparition when + button pushed):
 N2,
 T0,
 P0,
 P3,
 XPC,
 XPA,
 Fuel Pressure,
 Fuel Temperature,
 N2 datum used by EECU (only displayed when in flight
mode,
 Logical word (Failure & Maintenance words; Discrete output
states words).

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Displays in case of failure of the VEMD’s LANE 1:
When the LANE 1 is in failure, the upper screen is also in failure.
The pilot must switch off the LANE 1 and the upper screen by
depressing « OFF 1» as indicates in the lower message area.

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The FLI is lost but the engine parameters are still available and
displayed on the lower screen, in « 3 info » mode only.
Using « SCROLL », pushbutton on the VEMD or switch on the
collective, the pilot can switch between the engine « 3 info » page
and the vehicle page.
The Performance page and the Engine Power Check are not
available in this degraded mode.

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Displays in case of failure of the VEMD’s LANE 2:
When the VEMD’s LANE 2 is in failure, the lower screen is also in
failure.
The pilot must switch off the LANE 2 and the lower screen by
depressing « OFF 2» as indicates in the lower message area.

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In this case, the FLI is not lost and can continue to be displayed.
Using « SCROLL », pushbutton on the VEMD or switch on the
collective, the pilot can switch between the FLI page, the engine « 3
info » page and the vehicle page.
The Performance page and the Engine Power Check are also not
available in this degraded mode.

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Displays in case of failure of a FLI parameter (example TRQ).
In the event of an invalid FLI parameter (N1, TOT or TRQ),
the FLI is lost and the engine page switch to the « 3 info »
display.
The invalid parameter is then still displayed in yellow but
without value indication.

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Displays in case of failure of a FLI parameter (example TOT).
display.

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Displays in case of failure of a FLI parameter (example N1).
display.

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The configuration mode, selected in ground condition only, allows
the selection of the following aircraft options:
 Limit I/Gene: 150A or 180A or 200A,
 Flow meter installed or not installed: I or N/I,
 Sling installed or not installed: I or N/I,G
 PS installed or not installed: I or N/I,
 Fuel unit:(Kg, Kg/h or lb, lb/h)*; (l, l/h); (US Gal, US Gal/h); (Imp
Gal, Imp Gal/h),
 System unit selection: IS ; Imp IS (EOP, P0 = bar, OAT °C) ;
Imperial ( EOP, P0 = PSI, OAT = °F),
 Altitude unit selection : m / ft.
At the end of the selection select "VALID" and depress "ENTER" to
memorize the selection.
*note: Function of the system unit selection:
 "SI " = Kg and Kg/h
 "Imp" = lb and lb/h

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To display the configuration menu, switch off both screens.
Simultaneously press and hold down the two "SELECT" and
"ENTER" keys.
Press the "OFF 1" and "OFF 2" keys to switch on the
V.E.M.D.

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The "AIRCRAFT CONFIGURATION" page appears.

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3.16.1 Pages dîsplayed
This mode gives access to the different pages necessary for
maintenance of the V.E.M.D. and associated avionic system. It
can be activated only if the V.EM.D detects an "engine stop"
status. The first page displayed, is a menu page which
allows the selection ("SELECT“ and "ENTER") of the different
maintenance functions.

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3.16.2 Access to the Maintenance mode
Access to the Maintenance mode is done, after switching OFF the
two lanes by press and hold the "SCROLL" and “RESET"
pushbuttons while press "OFF1" and "OFF2" push-buttons to switch
ON both lanes of the V.E.M.D.
Release the "SCROLL" and "RESET" pushbuttons when
“RELEASE KEY” is displayed on screens to get access in the
Maintenance mode.

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3.16.3 Flight report
This mode allows to display the last 31 flight reports.
On the right side of the page the symbology indicates which
flight report within the list of 31 is displayed.
The "+" and the "–" push-buttons allow to navigate in the list.
When the "FLIGHT REPORT" function is activated, the
displayed page corresponds to the last flight report.
The informations contained in the "FLIGHT REPORT" pages of
the "MAINT" mode are identical of those of the "FLIGHT"
mode.
Note : the 32th flight is not finished.

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3.16.4 Failure diagnosis
This function provides help for detection of failed items (VEMD
module or sensors linked to the VEMD).
The last 256 failures are recorded (with 4 identical failures
maximum by flight).
The failures are displayed on three successive pages:
1/ The failure diagnosis page:
This page gives the last flight number, on the upper right side, the
flight number with failure detected associated to its position in the
list and the number of failure in this flight ("+/-“ push buttons allows
the navigation in the list of flight report with failure).
Depress "RESET" to go back to the maintenance menu page.
Depress “ENTER” to go to the complete diagnosis page of the flight
selected.

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3.16.5 Complete diagnosis
The complete diagnosis page:
 gives the flight number, selected in the previous page,
 gives the time elapsed from the beginning of the flight
before detection of the selected failure,
 gives the number and the identification of the test reference
linked to the failure,
 Indicates by "R" or "L", the lane of the VEMD which has
detected and memorized the failure,
 gives the list of LRU, Line Replaceable Unit, incriminated
for the failure,
 gives the name of the faulty parameter, it's type ("P",
permanent or "I" Intermittent) and it's rate (1 to 4),
 gives, on the right side of the display, the selection of the
fails detected during this flight.
A color code, Red/Amber/White, indicates the decreasing
probability of the faulty element.
The message "to see param press ENTER" means that it
possible to get access to a parameters list page
linked to the failure.

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3.16.6 Parameters type 1
The third one gives parameters list values when the failure
occurred.
The list type is a function of the failure number. All failures
are not linked to a parameter list.
(Depress "ENTER" to go to the page 2)
Depress "RESET" to go back to the "FAILURE DIAGNOSIS"
page.
The "PARAMETER 1" page displays the following parameters:
 "N1" (engine rating),
 "TRQ" (engine torque),
 "TOT" (engine temperature),
 "NRd" (rotor rpm limitation),
 "P0" (static pressure measured by VEMD),
 "OAT" (outside air temperature),
 "IGEN" (current intensity supplied by the generator),
 "UBUS" (voltage supplied by the generator),
 "N2" (free turbine rpm),
 "NR" (rotor rpm),
 "START" (current intensity supplied by the battery),
 "B/P2-PM" (status of the "P2" air bleed discrete signals).
The VEMD delivers the value of those parameters measured
and recorded before failure detection and upon failure
detection as well as their unit.
Press “ENTER” to go to next parameter page or “RESET” to
go back to the previous page.

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"PARAMETER 2" page displays the value of the following
parameters measured and recorded upon failure detection as
well as their unit :
 "EOP" (engine oil pressure),
 "EOT" (engine oil temperature),
 "FQ" (Fuel quantity),
 "FT" (Fuel temperature),
 "FF" (Fuel Flow rate),
 OAT (Outside Air Temperature),
 "NRd" (rotor rpm limitation).
Press “ENTER” to go to next parameter page or “RESET” to
go back to the previous page.

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The "PARAMETER 3" page displays the value of the following
parameters:
 "N1" (engine rating),
 "FAIL1A" (FADEC password),
 "FAIL2A" (FADEC password),
 "FAIL1B" (FADEC password),
 "FAIL2B" (FADEC password),
 "FAIL1C" (FADEC password),
 "FAIL2C" (FADEC password),
 "LOG OUT" (FADEC output discrete values),
 "LOG IN" (FADEC status input discrete values),
 "LOG ST" (EECU status logic word),
 "LOG ID" (EECU indication logic word).
Refer to the FADEC documentation to find the composition of
the various FADEC messages.
Press “RESET” to go back to the previous page.

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3.16.9 Over limit
The "OVER LIMIT" page : The function displays the 31 last
flight Overlimit pages (the 32th flight is not finished).
An Overlimit page is recorded for each flight even if there are
no overlimit detected during the flight.
When a "OVERLIMIT DETECTED" message appears in the
Flight Report page, an access to the "OVER LIMIT" page will
displays for this flight :
 the flight number in the tittle of the view,
 for TRQ, TOT, N1 and N2 parameters, the passed times in
"OVER LIMIT" for each limit ranges and the maximale
value recorded,
 the 5 maximal over limit values for NR parameter.
Navigation between the different “OVERLIMIT” pages is
possible by using the “+” and “-” keys. Depress "RESET " to
go back to the maintenance menu page.

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3.16.10 Engine power check
The "ENGINE POWER CHECK" page
This function allows displaying the last 8 engine power checks
as well as the parameters used for the computation.
The "+" and the "–" push-buttons allow to navigate in the list.
The symbology on the right side indicates the position in the
list of the EPC recorded.
Note : In duplex mode or in simplex mode on lane1, the
messages "MODE NOT AVAILABLE" and "CHECK LANE 2"
are displayed.
The content of the "ENGINE POWER CHECK" page of the
"MAINT" mode is identical to the "ENGINE POWER CHECK
RESULT" page of the "FLIGHT" mode.

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3.16.11 Fonctional times
The "FONCT.TIMES" page
For each computation lane, this function displays :
 the total functioning time at "flight" status (FLIGHT)
 the total functioning time from the first power up (FONCT.)
This page displays also accumulated operating time of the
EECU(ENGINE FONCT. TIMES).
Depress "RESET " to go to the maintenance menu page.

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3.16.12 EECU data
This function displays the parameters sent by EECU on the
ARINC 429 line.
Depress "RESET " to go to the maintenance menu page.

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3.16.13 Data loading
When this function is selected it is possible using two
software tools (which are implemented on a "ground PC tool")
to perform the following functions:
Using the "ANCT-DUT" software tool:
 Dowloading of maintenance memory data (failures, EPC,
Flight reports, Overlimits) from the VEMD to a "tool PC".
Reset of the VEMD maintenance memory (this function is
available only on specific EC version of "ANCT-DUT").
Using the "UMCARD" software tool:
 Validation flight by flight of the maintenance data received
from the "ANCT-DUT" tool.
 Presentation of the VEMD maintenance data flight by flight
and computation of cumul on selected flights (cumulated
flight time; cumulated engines cycles; cumulated overlimit
times).

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