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M’ARMS EC 225 - EC725
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SUMMARY
Introduction p3 - p4
Presentation p5 - p10
Acronyms p11
1. Equipment and Description p13 - p55
2. Communication p56 - p66
3. Operating with the system p67 - p86
4. Usage Analysis p87 - p1045. System Analysis p105 - p109
6. Health Domain p110 - p118
7. Health Monitoring p119 - p133
8. Ground-Station Computer p134 - p173
9. Ground Tools p174 - p220
10. Quick Health p221 - p230
11. Multibase Principle p231 - p232
12. Health Indicators p233 - p257
Appendix p258 - p262
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M’ARMS : Modular Aircraft Recording Monitoring System HUMS system on EC 225 has been built for the following purpose:
- Satisfy to JAR OPS3’s compliances relative to flight data parameters
- Automation of flights and their analysis
- Provide a maintenance report and optimise help for maintenance
- Deliver a diagnostic for the main mechanical “critical parts”.
Airborne architecture has been developed on EC155 experience.
In the same way M ’Arms architecture on EC 225 is built following 3 concepts:
CVFDR for the flight data recording parameters (crash recorder)
UMS
HUMS defining the ARMS system
M’ARMS installed on EC225 is a full M’ARMS configuration. It will integrate the Ums
function and HUMS function. It has been developed using Euroarms MKII
experience and EC 155 architecture (M ’Arms).
Introduction
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1. CVFDR : Combined Voice and Flight Data recorder
The first purpose of this recorder is to save any time the last historical data : mandatory parameters and recommended
will be used for expertise in case of crash or investigation.
CVFDR will be downloaded by maintenance team for data validation and for investigation on overshooting.
2. UMS: Usage monitoring
Way of aircraft utilisation in flight. Monitoring flight data condition on every flight.
UMS function will integrate the historic of counting hours for maintenance job: mechanical main parts following.
The customer will have to provide data to keep his data base updated by downloading flight data daily.
3. HUMS : Health monitoring
Indicators qualified as “Health indicators” extraction from vibration spectrum will allow the identification of any degradation
of performance
This function will provide an important help for following mechanic trends
The M’ARMS system has been defined in 3 parts :
- An airborne segment to collect flight data acquisitions on board. - A ground Segment will assist the treatment, the analysis, the historic management and data coming from UMS and HUMS
This is called GSC or Ground station
- A PCMCIA card will collect all data under a file name. These files will be called under the word of “sessions”.
At the end of each session, after the last engine shut down, Arms data will be transfer automatically o
PCMCIA card . This card will be downloaded daily on GSC
Introduction
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1. CVFDR Purpose : Crash recorder storing in memory FDR data and audio signals for CVR function.
Compliance with CAA authorities.
FDRS= CVR+FDR
FDR : Data collected on helicopter. These data coming from the frame, engines, navigation, systems installed.
At power on, ”mandatory ” and recommended will be recorded under frame and subframe
CVR : 3 “audio“ signals insure the CVR function:
“Pilot“ et “copilot” audio signals collected on audio and mike issued from P and CP jacks
An ambiance mike will care about audio recorded in cabin.
Recording parameters will start at battery switched on. Supplied on battery (essential network).
CVFDR Objectives
Main goal on data recording is:
a) To confirm overshooting parameters exceeded during the flight detected by the Arms le system ARMS :Overtorque, NR and Engines
b) to deliver a real diagnostic : after downloading data in case of accident
Nota: SSCVFDR will not deliver any message after flight in case of exceedance.
Download operation will be realized by an operator to check and confirm data stored inside the equipment.
For this purpose a computer Kontron called AHMU will be used for investigation.
Presentation
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2. Function UMS or Usage
Monitoring Counters associated to component to inform maintenance about time reached and alarms displayed
in flight:
- Time in operation
- Flying time
- Landings
- NR cycles
- Engines cycles N1(NG) et N2 (NF).
Exceedances monitoring on usage threshold in order to generate overshooting message in caseof overshooting with flight manual:
- TQ1+TQ2 for Overtorque detection (damaging on MGB),
- Engines exceedances (limitation on these 3 modes T4, NG, NF )
- NR exceedance NR max (MRP damaging)
- Engine Power check basic function on EC 225 will be done from VMS. M’ARMS system will record datafor trend following.
All these functions will be automatically linked with operator after downloading data in he flight reportThey will be saved inside GSC
UMS Objectives
Deliver useful parameters to maintenance in order to mention all exceedance about overshoot about enginesand frame.
Provide information about the flight helpful for maintenance purpose
Presentation
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3. HUMS Function or Health
Provide vibration data on main mechanical parts.
Generate maintenance message when threshold will be overshooted.
Analyse monitoring will be displayed on the following components:
- MGB: input shafts 23000, left & right ancillary gearbox, ….
- TDS : shafts and bearings on tail transmission
- IGB : Shafts and pinions
- TGB: input shaft and pinions
- ROTORS : vibration level in n
All the acquisitions are realised on these components in a predefined order automatically on board.This function will be automatic and doesn’t need any pilot action. (less of load for operator)
HUMS function will realise also the « Rotor Tuning » function.
These specific acquisitions will be launch manually by the crew and will request a specific flightconfiguration in accordance with flight manual.
HUMS Objectives:Safety
Improve safety on board by detection abnormal vibration level Anticipate detection on cracks, misalignment , unbalance, corrosion.
In-condition benefits
Improve comfort on board
Help and anticipate maintenance workload
Maintenance benefits
Adjust rotors : doesn’t request a specific technical flight
Help monitoring : daily spectrum on all mechanical components
Presentation
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+ AircraftSensors +
MFDAU SSCVFDR
AHMU
= CVFDR function
= UMS function
= HUMS function
+
DTU
VPU
GSC
GROUND
SEGMENT
CVFDR
USAGE
HEALTH
FD
R
S
+
I.H.M
+
P
C
M
C
I
AU
M
S
H
U
M
S
ACMS HUMS
MFDAU
Sensors
ACMS FDR
Magnetic Top
+
AIRBORNE
SGEMENT
Presentation
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Airborne Segment is composed of:
For CVFDR function
- A recorder (voice and parameters)- A module MFDAU (Miscellaneous Flight Data Acquisition Unit) used to concentrate data to the flight recorder.
it will be called MFDAU_ FDRS.
For ACMS function (Arms)
- A second module MFDAU ; heart of HUMS system will be called MFDAU_ ACMS.
Both MFDAU are identical (same P/N). They will be loaded with the same software but with different configuration tables
(ICT and DFS) introduced by Eurocopter.
These module are not interchangeable.Each MFDAU will receive a different pin code (recognised at installation).
A single control unit including CVFDR et ACMS functions called IHM will insure
- failure monitoring
- Access to ARMS menu displayed on the screen pad
Flight Data : Acknowledgement about flight data
Data Transfer: Data Transfer at engine shut down
Rotor Tuning : acquisitions requested on rotors
A DTU called also MDR (Data transfer Unit) will receive flight data on PCMCIA card (link RS 422)
A VPU (Vibration Processing unit) will acquire HUMS the vibration data base on specific accelerometers.
These accelerometers are mandatory to collect vibration monitoring on aircraft.
Two magnetic pick-up used to deliver rotor speed and phase balancing
A set of magnetic electric plugs will monitor for the ACMS any alarm coming from gearboxes on A/C.
Presentation
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EC 155, EC 135, AS 365 N3, EC145,EC225
M’ARMS
AS 365 N3
EC 155 EC 135
EC 145
EC 225
Presentation
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N O T E S
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1. Equipment Description
CVFDR
CVFDR ARCHITECTURE
SUMMING AMPLIFIER
AMBIANCE MIKE
IMMERSION UNIT
INERTIA CONTACT
CVR FUNCTION
CVR LISTENINGCVFDR INTERFACE WITH AHMU
IHM CONTROL UNIT
DTU CONTROL UNIT
DTU CONNECTION
PCMCIA CARD
HEALTH ARCHITECTURE
VPU
MAGNETIC PICKUP ON MRH & TRH
ACCELEROMETERS
MGB SINGLE AXIS ACCELEROMETERS
TGB SINGLE AXIS ACCELEROMETERS
TDS SINGLE AXIS ACCELEROMETERS
ENGINES ACCELEROMETERS
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1
BITE
A
A 3
4
2
3
5
1. Equipment Description
CVFDR
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Definition
Recorder Unit Solid State technology
HONEYWELL (ALLIED Signals) called Black Box
Function
Recording data parameters mandatory representative of theflight (engine configuration, altitude, airspeed) and audio signalpilot, copilot and cabin.
Passive system which doesn’t modify aircraft input parameters.
Description
- An orange unit including the static memory (1)
- A logic circuit including power supply and control commands(2).
- An acoustic beacon ULB (4) supplied by an internal battery isfitted in its front face: low frequency transmission to localize theunit.
Front face a connector to download data for laboratoryoperation (3).
An amber light (5) “BIT” on unit will display an internal failure .This light is associated to FDR light on IHM control unit
Power supply: +28v essential (pin 55 )
Supplied through inertia contact and logic immersion unit.
Localisation
Inside tail boom to minimize damaging in case of crash.
Characteristics
Choc Résistance : 15 g
Resistance temperature: 1100°C/ 1 hour
Immersion : 1 month /20 000 ft.
No fan installed
24 hours recording data (FDR function)
2 hours recording for CVR each mike
Maintenance
Before flight: manual Test on IHM (check list)Periodicity : Battery on ULB. (SLL 6ans)
Data Downloading every 18 months.
IHM/ CDU
FDR
Synoptique de la fonction
CVR/FDR
1. Equipment Description
CVFDR
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Start Recording
SSCVFDR is recording as soon as power on.
Mandatory for >2730 kg.
Operative after BIT done (few ms after initialization test)
CVR et FDR flashing on IHM at power on
List of parameters mandatory and recommended coming fromMFDAU_FDRS are captured under Arinc 573 format.
Parameters are recorded under frames and subframestransmitted under 12 bits at speed of 128 word/s.
One frame is fitted with four subframes. Each subframe will besampled every 4 seconds.
Stop of record:- At battery switched off or In Case of crash or immersion:
- an inertia switch
- a logic unit associated with an immersion probe
On of these condition will cut SSCVFDR line.
At this level; data cannot be overwritten. CVR light is coming onIHM control unit.
Input
FDR Data : transit par MFDAU-FDR
CVR Data : signaux audio pilot , co-pilot, ambiance mike.
IHM Functions dedicated to CVFDR
TEST Manuel:
During test no light will come onOnly an audio signal : “800 Hz” is generated through CVFDRheadset.
ERASE:2 Pushbuttons should be set to initialise Erase function Audiosignal is cancelled from recording data.
(private flight)
Helicopter on ground with rotor brake applied and action on:
1. Erase on IHM2. Erase on switch Erase in luggage compartment.
(2 operators required)
3. EVENT : Provide a mark on the CVFDR graph to investigate after anabnormal configuration
Analyse cannot be done alone and request a download operationon CVFDR
1. Equipment Description
CVFDR
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Inertia Contact ambiance MikeSumming Amplifier
Immersion Probe
Immersion Logic Unit
CVFDR
A.H.M.U
MFDAU/ FDRS
I.H.M
VMS
Airborne Segment
Ground Segment
(PGS: Software used to download CVFDR data and analyse in real time )
AHRS
1. Equipment Description
CVFDR
ARCHITECTURE
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1. Equipment Description
SUMMING
AMPLIFIER
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Micro Out +
Micro Out -
39
38
Ambiance mike
Area Micro signal -
16
15
Summing Amplifier
Channel B Audio Copilote24
Channel A Audio Pilote279
8
Copilote Audio In -
Pilote Audio In +
Pilote Audio In -
+ 28 V dc46
Ground47
0 Vdc45
A
J1
37
45
5 VDC
Return 5 V
GND
S10 +
S10 -
PWR +
PWR -
49
54
-12 dB
31
46Rouge
Noir
Blanc
Vert+ 5 VDC
Return 5 VDCGround
+ 28VDC 55
Return 28 VDC 53
GROUND
- 6 dB 48 Attenuation ambiance mike
Commun Attenuation
3839
Mike signal+ Mike signal -
audio Copilot IN +
audio Copilot IN -
Pilot audio IN +
+Pilot audio IN -
Mike Out +
Mike Out -
CoPilot Mike
Pilot Mike +
Audio Pilot +
Audio CoPilot +
4
1
9 Audio Co-Pilot -38
Audio Pilot -
17
33
21
11
SSCVFDR
1. Equipment Description
SUMMING
AMPLIFIER
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Definition
Channels summing amplifier
FunctionDedicated Equipment dedicated for CVR function : amplifier
Audio signals+ Mike are directly linked from from jacks P and CP
Description
Mixing Amplifier for the signals Mike and audio coming from channels pilot et copilot.
Location
Inside Cargo
Characteristics
Weight : 500 g
Operation
Test equipment CVR will be realized through a special headset impedance 600 ohms.
Connexion
input = Audio Pilot et Copilot
output = to flight recorder unit
Power supply
Double supply with a +28 V Battery / protection par breaker 3 A
1. Equipment Description
SUMMING
AMPLIFIER
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1. Equipment Description
SUMMING
AMPLIFIER
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Definition
Ambiance Mike
Function
Monitoring noises and frequencies coming from cabin to identify rotor regime for adding information for analyze purpose.
Location
On the overhead panel between pilot et copilot seats.
Characteristics
Frequency band:150 -6000 Hz.
Operation
Audio issued from ambiance mike can be checked :
1. in real time (PGS software) To test ambiance mike will be tested through a specific headset (real time audio check)
2. after downloading CVR function (PGS software) through AHMU
Connection
INPUT = signals audio and micro
OUTPUT = CVR recording
Power supply
Ambiance mike receives a 5volts input to supply its internal amplifier provided by CVFDR unit
1. Equipment Description
AMBIANCE
MIKE
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Immersion Probe
Logic Immersion Unit
1. Equipment Description
IMMERSION
UNIT
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Definition
Electronic Immersion logic
Function
Detection following a major incident (A/C ditched).
Logic unit is linked with an external probe
Cut the main power supply of the CVFDR unit keeping in memory the last hours recorded on board.
Description
An immersion probe fitted with two resistors, one hot and one cold.
When immerged probe resistors become equal unbalancing logic unit input : “CVR” light is coming on IHM control unit.
Location
Immersion probe is fitted inside right side.
immersion logic unit fitted rear cargo side (close to BTP)
Characteristics
Weight : 80 g.Periodic check : Maintenance every 18 months.
Power Supply
+28 V / 3 A
1. Equipment Description
IMMERSION
UNIT
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Logic unit Immersion
+ 28 V dc power supplyA
0 VdcB
Immersion probe
A
D
B
C
Thermo probe 1
Thermo probe 2
J
M
K
L
Hot Probe
Cold probe
Output 28v to SSCVFDRF
Input 28v controlC
B
C
Inertia contactA
A
+ 28 V Battery
V Ground
1. Equipment Description
INERTIA
CONTACT
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Definition
Ball contact compressed through a spring.
FunctionStop recording CVR and FDR following a hard landing
Cut the line over an acceleration of 6,5g.
This detection (open contact) will cut the CVFDR power supply. CVR light will come on on IHM.
Description
Electrical Contact.
This equipment will be replaced after release.
When it is new, it is delivered with a cutter pin to avoid any activation.
Localisation
Back MGB on top.
Characteristics
Weight :105 g
Operation
Contact is closed between pin B and C
1. Equipment Description
INERTIA
CONTACT
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Erase : to cancel audio data
IHM
Hydraulic switch on rotor brake
“Erase”
switch 2
“Erase”
switch 1
Ambiance mike SSCVFDR
summing Ampli
« Erase » Operation : “400 Hz” Tone is generated in
CVFDR headset (transmission signal 3s, blanc 1s)
1. Equipment Description
CVR
FUNCTION
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CVR in real time
Luggage Compartment
Inside tail boom
1. Equipment Description
CVR
LISTENING
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Download processing and real time analysis
Download is possible from plug 552Vc
552Vc
552VC
SSCVFDR ALLIED
TX -
TX +
ATE Présent
RX -
RX +
CTS +
CTS -
FDR Data + IN
FDR Data - OUT
FDR Data+ OUT
RTS -
RTS +
7
1
2
3
33
41
3442
21
22
6
14
13
B
A
N
K
J
ML
C
H
G
D
E
F
TEST et
déchargeme
nt CV/FDR.
Lignes
Arinc 573
FDR Data - IN
Test Plug
maintenance 7
1
2
3
33
41
34
42
21
22
6
14
13
552 VC
1. Equipment Description
CVFDR INTERFACE
WITH AHMU
CVFDR INTERFACE
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1. Equipment Description
CVFDR INTERFACE
WITH AHMU
IHM CONTROL
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Definition
I.H.M : Interface Helicopter Monitoring
Description
Control unit fitted with :
- A screen pad displaying :
- HUMS menu (function used by crew)
- status PCMCIA card (ARMS+ CVFDR)
- An alarm system status indicating:
- alarms on CVR, FDR and HUMS
Function
Permanent Check on : CVFDR, MFDAU and ACMS
CVFDR : CVR, FDR
ACMS : HUMS light to detect
- inconsistency between software MFDAU/ACMS
(configuration files ) and pin code
- Missing signals NR, NG or NF or not updated over
than 10‘’- dialogue loss between equipments
Location
On pedestal control unit
Characteristics
Weight: 600g
Consumption = 30 w
CVFDR Functions – Test
– Event
– Erase
HUMS Functions
- Rotor Tuning
- Flight Data
- Data transfer
Operation
Following initialization sequence (few seconds after power
on) main menu will take place
Connexion
input : MFDAU ACMS / MFDAU FDR
output : CVFDR and HUMS purpose
Alimentation
+28v Essential network / 3 A
1. Equipment Description
IHM CONTROL
UNIT
DTU CONTROL
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TARGA
Magnetic Detector
1. Equipment Description
DTU CONTROL
UNIT
DTU CONTROL
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Definition
Data transfer unit.
Allow to read files fitted on PCMCIA card.
Function
PCMCIA should have to be inserted inside DTU before flight
Interface between MFDAU and PCMCIA card. Flight data issue from MFDAU are transferred under RS 422 format.
Block of raw data 4Kb capacity will be transferred every 4 seconds.
File .225 (ACMS) file will be transferred at the end of flight
At the end of transfer a message ” transfer Done” will be displayed. Card can be removed
Description2 types of DTU
- One on the GSC which request an external power supply 15v
- One on aircraft 28v fitted with a cover
Opening front cover on airborne DTU will affect the message “No card” on IHM.
Location
Rear side of Cargo bay
Characteristics
Weight : 750g
Power supply
+28 V / 3 A
1. Equipment Description
DTU CONTROL
UNIT
DTU
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MFDAU HUMS
C2DTU
19
+ 28 V
+ 28 V
12
13
A
DTU/MFDAU +
DTU/MFDAU -
10
9
MFDAU/DTU +8
MFDAU/DTU -18
27
28
GND7
GND
RTS + (RS 422)11
CTS + (RS 422)14
RTS - (RS 422)20
CTS - (RS 422)21
RTS (RS 232)22
CTS (RS 232)17
Ground1
DTU présent
29
30
26
C1
6
DTU IN +
DTU OUT -
DTU OUT +
DTU IN -
ACTIVATION ACMS 5
RS 422
1. Equipment Description
DTU
CONNECTION
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File format:
The card will contain files created on board. Each session will get 2 files:- One file with extension “.225” where HUMS data will be
recorded (Usage and Health data).
- The other one with extension “.raw” which contains the
defined list of FDR data used for FDM.
PCMCIA card is not affected to a special aircraft. It can be installed on any
helicopter fitted with M’ARMS system
Possibility to record files coming from different helicopter
2 types of Messages relative to card status:
”No Card ” : missing card
“Full Card” : memory available < 8Mb
PCMCIA description:
High capacity : 256 MB solid state (non volatile memory)
PCMCIA characteristics:
MTBF> 1000 000 Hours / Temp -40 à +85° C« .raw » file « .225 » file
Session
FDM data HUMS data
1. Equipment Description
PCMCIA CARD
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File Format:
Each file will be identified as below:
- software version helicopter
- pin program (family, S/N)
- session number
File format and session number will be displayed in
hexadecimal.
At session starting MFDAU /ACMS memorise time and dateof the session.
Every start, airborne segment will generate a new session.
This session will be recorded and displayed in GSC
computer.
ACMS data coming from different cards and helicopters will
be recorded inside GSC.
1FF41 02d
Pin code in Hexadecimal
File List displayed under Windows Explorer
Extension file
Session number
in Hexadecimal
1FF41 02d
(Decim al = 130881)
225
raw
(Decimal = 45)
FDM
HUMS
1. Equipment Description
PCMCIA CARD
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Such file is the result of 128 parameters recorded on configurable input defined on MFDAU DFS table. This file
created at each starting will generate raw data for a maintenance help.
This is to provide « replay » of the flight and analyse the exceedance limitation.
A « .raw » file will integrate pin helicopter code and session number. It will be displayed on GSC through PGS
software.
Input data are read by blocks of data and recorded on DTU every 4 seconds without coding under format A429.
Frequency of each data identified is 2 Hz.
MFDAU time will be a parameter user can select on parameters list
SSQAR function « downloading in continuous flight data » is a part of module MFDAU/ ACMS and will
be closed correctly if a «watchdog is deactivating the system.
If during continuous data recording DTU front cover is opened or card removed, data will be lost temporally .
1. Equipment Description
PCMCIA CARD
« .RAW » File Definition:
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Parameters list fitted in. Raw files
Provided by VMS
Date
TimeNr
P0
OAT
Airspeed (IAS)
Trq 1
Trq 2
Dng 1Dng 2
N11
N12
N21
N22
TOT 1 (Eng 1 temperature)
TOT 2 (Eng 2 temperature)
Engine configuration (Training,OEI ou AEO)
Flight/ground Logic
Altitude ZB
MGB Oil Pressure
MGB Oil Temperature
Weight
FLI 1 (first limitation)
FLI 2
Provided by FDRS
Vertical Acceleration (Gama Z) GAM Z
TR Position TR_Pos
Collective pitch
Altitude Radio altitude ZRS
Pitch Position Pitch
Roll Position Roll
Heading Hdg
Pitch Attitude Pitch attitudeRoll Attitude Roll attitude
Pitch rate Pitch rate
Roll rate Roll rate
Yaw rate Yaw rate
1. Equipment Description
PCMCIA CARD
HEALTH
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GSC M ’ARMS AHMU
PCMCIA
I.H.M
D.T.U
Pickup TR
MGB
MR1
TR
TDSTGB Engines
MR2
MR3VPU
2 M.F.D.A.U++
+
Airborne SEGMENT
Ground
SEGMENT
Load
AmplifiersIGB Fan
(5) (1) (8) (2)(1)(1) (4)
1. Equipment Description
HEALTH
ARCHITECTURE
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Vibration Processing Unit
Health interface for the HUMS function.
- Realize Health monitoring for all the components
monitored
- Compute the results for rotors adjustment
VPU is a generic equipment loaded with a software to beinstalled on a EC 225. It can be installed on any ECF family
Software downloading will be done before installation.
MFDAU_ACMS will pilot VPU for acquisitions processing.
For each demand requested by VPU, VPU sends back a
message “correct acquisition” or “incorrect acquisition”.
Acquisitions correct: MFDAU_ACMS asks VPU to send back
its results before to pass to next acquisition.
During the session VPU is used for the following check :
-rotors monitoring
-gears on MGB, IGB,TGB-TDS monitoring shafts and bearings
- Bearings monitoring on MGB, IGB and TGB
- Engines vibration monitoring in stabilized mode and at starting
- Rotors adjustment MR and TR
Acquisitions are executed following a predefined cycle
This determine VPU cycle from beginning to end of session
Some acquisitions called priority can be requested any time
interrupting the normal cycle, time to realize the acquisition.
On ground In flight
priority 2: rotor monitoring priority 2:eng vib stabilized
priority 1: engine start monitoring priority 1: rotor monitoring
priority 0: Rotors adjustment priority 0: rotor adjustment
1. Equipment Description
VPU
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VPU Characteristics
Integration of a new software on VPU could be done with AHMU using CMT software ( uploading process)
MFDAU_ACMS and VPU will be linked through an RS
422 line.
VPU defect
At power on
VPU generates its “BIT” and elaborates its status. ACMS (MFDAU) sends a status command “status” and
receive in return VPU status “Go” or “No Go”
If VPU doesn’t answer or sending a bad result (No Go)
(checksum error ) in Status mode a VPU failure will be
recorded. This code (result of Status) coded under 8 bits.
If pin code is not recognized health acquisitions will be
inhibited
If the status is “Go” then the MFDAU reads the ACMS version
addressed to VPU and the one waited by the S/W downloaded
onto the VPU. If it is not compliant, “ACMS/VPU
inconsistency” is recorded.
Defects on VPU:
In normal operation
For each acquisition , VPU sends back a message to MFDAU
about the result acquisition.
If OK: Result is sent to MFDAU/ACMS
If no OK:
1/ No response from VPU or response unclear: major failure
recorded on VPU, interruption of acquisition cycle (major
defect)
2/ acquisition not acquired :out of range: minor failure
1. Equipment Description
VPU
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Tachometers:Capacity: 8 channels available
4 used for phonic wheel as N11,N12, N21,N22.
2 used for magnetic pick up MR and TR.
2 not used
Accelerometers
Capacity: 36 input axis
Capacity:12 discrete input
8 discrete available to identify aircraft pin coding
4 discrete available for maintenance (VPU reconfiguration) (Reset,
Reprog, flight/ground position, presence computer RS232)
“Discrete Input”
1. Equipment Description
VPU
MAGNETIC PICKUP
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TRH
+
Interruptor on MGB
target
MRH
1. Equipment Description
MAGNETIC PICKUP
ON MRH & TRH
MAGNETIC PICKUP
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Function
Determine airspeed and phase rotor position.
Mandatory to validate acquisition RTB on VPU
Description
Magnetic pick up is fitted in face of a target in order to generate the speed signal.
Process
Used to tune rotor AR (software Steady Control Rotor) to define track and balance and determine unbalance
phase position.
This information is required to optimize level of vibration on aircraft.
Characteristics
Distance between sensor and target: 1.25 mm -/+0.25.
1. Equipment Description
MAGNETIC PICKUP
ON MRH & TRH
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Z
Function
Provide vibration data on VPU for health acquisitions
Description3 type accelerometers (Mono-axis, Bi-axis, Tri-axis)
Fitted at different places they are monitoring:
- Bi-axis is monitoring Health on MR an TR
(automatic acquisitions ground and flight )
- Rotor tuning (specific function for rotors) MR and TR
Characteristics
Rotor Tuning
3 Accelerometers with amplifier integrated
Tri-axis
Vertical/ Lateral /Longitudinal
Y
ZX
Y
Z
Rotor Tuning
Bi-axis : Measures vertical acceleration (interchangeable
between main and tail rotor)
Y
Z
Health monitoring on components
Pinions/Shafts/Bearings
Type: Single with internal amplifier
Engines
Specific single axis on engine resisting to high temperature. Two
amplifiers by engine associated to 2 accelerometers.
+
Y
Bi-axis Vertical /Lateralsingle Vertical MR
TR
1. Equipment Description
ACCELEROMETERS
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Main Rotor and Tail Rotor
4 accelerometers dedicated on adjustment : 3 MR;1TR
Vibrations acquisitions are necessary for the following configurations (FPOG, Hover, Cruise 100 knts, MCP)
to obtain the correct adjustment will be requested by a crew member
Result on balancing will be displayed on IHM control unit
1. Equipment Description
ACCELEROMETERS
Tail Rotor Bi-axis on tail
Main rotor
Accelerometer
Single axis under
pilot seat
Main rotor
Tri-axis under cabin floor
Main rotor Accelerometer Bi-axis under
copilot seat
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MGB Health monitoring
1. Equipment Description
ACCELEROMETERS
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TDS Health monitoring
1. Equipment Description
ACCELEROMETERS
MGB SINGLES AXIS
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1. Equipment Description
MGB SINGLES AXIS
ACCELEROMETERS
MGB SINGLES AXIS
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Interchangeable Single axis on MGB monitoring components on MGB :
Input Monitoring 23 000 rpm Epicyclic module monitoring
1. Equipment Description
ACCELEROMETERS
MGB SINGLES AXIS
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MGB
Left Ancillary Box
1. Equipment Description
ACCELEROMETERS
TGB SINGLES AXIS
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Monitoring
Input TGB
1. Equipment Description
ACCELEROMETERS
TDS SINGLES AXIS
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A single axis fitted on transmission for shaft and engine monitoring
1. Equipment Description
ACCELEROMETERS
ENGINES
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Engine accelerometer ( 2 per engine interchangeable)
Accelerometer linked with load amplifier
4 Amplifiers in cabin
1. Equipment Description
ACCELEROMETERS
N O T E S
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N O T E S
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2. Communication
ARCHITECTURE FDRS/HUMS
INTERCONNECTION
SYSTEM
MFDAU MODULE
ARCHITECTURE
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CVFDR
There are 2 MFDAU modules fitted on the aircraft and powered up by direct battery:
- One for CVFDR data
- The other for HUMS & FDM data
HUMS & FDM MFDAU modules pow ered up by directbattery
MFDAU CVFDR MFDAU HUMS & FDM
DTU
2. Communication
FDRS/HUMS
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VMS - MFD- FADEC- APM
M’ARMS GSC
ARINC 429
ARINC 573
RS 485
RS 422
VPU
RS422
Vibration sensors
MFDAU
FDRS
CVFDR HMI - CP
Ground segment
Flight segment
NR,N1, N2
out
in MFDAU
ACMS
DTU
INTERCONNECTION2. Communication
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The system stores in memory all data recorded as soon as
one engine start .
The session will be linked to one helicopter only and
identified as Helicopter Type _ serial number_ session
number
A session = A flight or a ground run
A/C S/N and A/C type are identified through a pin code. This
pin code is made by straps rear side on MFDAU
Each file will be identified on the airborne segment and a
packed session will be generated if the last flight was
not transferred correctly.
How to define a session?
First engine start
Start engine 1: N11>5% or N12> 5 %
Last engine Stop : N11
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The number of session is automatically increased after each use and re-initialise after each MFDAU replacement or
download of a new ACMS S/W version onto MFDAU.
This number is recorded at file transfer on PCMCIA and compared with the last MARMS number session recorded onto
GSC for the associated aircraft. This makes the operator aware about any missing or non downloaded sessions.
In case of, the user is able to create missing flight on GSC and so update the usage cycles counters.
Regarding the on-board, before engine start, it is necessary to check the system status.
If the last flight has been correctly downloaded, it will be deleted from the memory of the MFDAU.
On contrary, if the session has not been correctly downloaded, the message « transfer » will be displayed on IHM
requiring a manual download through the command « Data Transfer ». At this step, if the transfer is not done, an
abbreviated session will be generated and saved on MFDAU memory. Such session contains only usage information. A
maximum of last 20 files could be saved like this.
SYSTEM2. Communication
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A 2
Miscellaneous Flight Data Acquisition unit
Module fitted with a lock handle
PACKAGING EQUIPMENT LINE CONCEPT « AVIONIQUE NOUVELLE »
MFDAU-ACMSMFDAU-FDRS
PELICAN Rack
MFDAU MODULE2. Communication
2. Communication
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Fitted with internal memory (RAM) in order to save ACMS dataon the last flight. Keep on memory for 5O hours throughcapacitor. If the flight has been downloaded correctly data on RAMwill be erased.
To operate MFDAU_ACMS and FDRS will receive a software.
One version only will be provided on both MFDAU++ fitted on EC
225.
On MFDAU FDRS the software will be grounded (software
inhibited)
2 tables ICT and DFS will be loaded on equipment : un code
707A…..will be set.
These tables will be different according to the module functionFDRS or ACMS : two pin program different.
Pin code linked with (helicopter family, configuration system, DTU
presence...). Their position on the rack are essential.
They are not interchangeable.
Pin code is defined by jumpers rear side of the connectors.
18 bits recognising :
Position: discrete
Type : coding on 5 bits : EC 225 (family)
Configuration :coding on 7 bits (engines, Fadec)
Serial Number :coding on 6 bits
System configuration is identified at power on through theconfiguration file but also through pin code which is different oneach helicopter.
Definition FDR et ACMS
Function
MFDAU is an acquisition unit which convert flightparameters format under different format.
Flight data are coming from different sensors withdifferent input data entrée
- analog (NR,NG,NF)
- digital (APM, VEMD, FCDM, FADEC)
- discrete (Alternat Radio, logic input)
Process is to record flight data in order to compute ACMS function on board. This will insure HUMS function
through VPU to provide health purpose.
Dialog with different interface working with VPU,IHM,
CVFDR.
A link between MFDAU Arinc 429 checks the
consistency between acquired signals
Description
MFDAU++ ACMS is fitted with a lithium battery to maintain
date and time on board generating starting session time
(OTL : 5ans)
MFDAU MODULE
O2. Communication
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Pin code type + configuration defined on EC225
APIRS will be used to provide accelerations under three axis . No adding accelerometers will be fitted for this
function
Difference between MFDAU modules
MFDAU_ACMS & MFDAU_FDRS realize a status process and auto validate the processing.
Memory inside MFDAU_ACMS will not be saved over 50 h.
MFDAU MODULE
MFDAU MODULE2. Communication
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code Pin module MFDAU power supply
MFDAU MODULE
MFDAU MODULE2. Communication
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Operation
ICT /DFS tables are loaded inside MFDAU EEPROM.
(Electrical Erasable Programmable Read only Memory)
At power on: each MFDAU is sending a “BIT” (Built in test)and elaborate a status validity following its function and itsposition.
MFDAU -FDRS can generate two status failure introducing
FDR alarm :-failure type “incompatibility” between helicopter type(pin code) and version table configuration.- Failure type “logic” internal to MFDAU module or CVFDR.
Nota: A MFDAU module failure will not interrupt the ACMSsoftware
MFDAU -ACMS can generate HUMS alarm on IHM :
lost of validity or invalidity NR, NG1 or NG2 mandatory to
define data status of the system
On ground : no starting session
During flight : 10s disconnection of ACMS (watchdog)
A429 to dialog between modules
.
Power Supply
Double power supply 28 v (pin 34 and 35 connector C)
Essential Network and direct battery
Consumption : 25 w each
Input
VMS: data coming from vehicle and engines (alarms and flight
parameters.).
APM modules
PU: EID/MFD navigation parameters navigation control
RCU: Reconfiguration system unit
FADEC 1 and 2: digital computers managing both engines
block of data coming from analog sensors (NR), (NF), PA settings,
discrete).
Output
Interfaces aux formats:
A 573 for SSCVFDR treatment of parameters
(Solid State Cockpit Voice and Flight Data Recorder)
RS 422 data link DTU and VPU
RS 485 interface with IHM control unit
MFDAU MODULE
N O T E S
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3. Operating With The System
PROCESS
IHM CONTROL UNIT
IHM MENU
FLIGHT DATA ACCESSFLIGHT DATA ACKNOWLEDGEMENT
ROTOR TUNING
DATA TRANSFER
MARMS GSC
MARMS GSC DOWNLOADING
FLIGHT REPORT
MAINTENANCE REPORT
DISCREPANCY REPORT
DIAGNOSTIC REPORT
3. Operating With The System
PROCESS
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PROCESS OPERATOR
STEP1: PRE-FLIGHT
STEP2: IN FLIGHT
STEP3: POST FLIGHT
STEP4: TRANSFER to GSC PILOT/ENGINEER
STEP6: MAINTENANCE
ACTION
MAINTENANCE
EXPERT
ENGINEER /
HUMS EXPERTSTEP5: ANALYSIS AND
DIAGNOSTIC
PILOT/ENGINEER
FDM data
HUMS data
SESSION
File stored on GSC Hard Disk to be used later on…
… PGS s/w
or other.AMM
EC SUPPORT
GSC M’ARMS
DATABASE
« .raw » file
« .225 » file
MAINTREPORT
-------------
---------
PRINTER
PROCESS
IHM CONTROL
UNIT3. Operating With The System
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BACK ENTER TEST
ERASE
EVENT
1 2 3 4 6
7 8 9 10 12 13 11
CVR
FDR
HUMS
5
No . DESCRIPTIO N FUNCT ION
1 SCREEN
3 rows of information 19 al hanumeric charactersmaximum)displayed :
Menu selection and scratchpad zone Page Number displayed on right hand bottom area.
2 MENU zone
Selection of Menu options: Flight data / Data Transfer / Engine check/ Rotor Tuning View status and results of acquisition (Run,Done,Fail…)
3 EVENT Marker Create a marker on CVFDR to take note of fli ht dataarameters in event of an unusual incident encountered b
the pilot/ crew during flight.
4 ERASE buttonTo erase audio tracks recorded in CVFDR on ground only. Activation of this erase button is associated with eraseswitch located in the luggage compartment. (2 persons)
5 TEST pushbutton Initialize the CVFDR built-in test.
6 CVR indicator light Indicates an audio recording fault.
7 FDR indicator lightIndicates a flight data recording failure or a MFDAU modulefailure.
8 HUMS warning light Indicates a major failure of the ACMS.C.
9 ENTER key
It is used: To activate a selected command To reach a sub-menu . To manage the option type field in flight data menu (Y/N)
10 SCRATCH PAD zoneDisplays on ground only with engines and rotor stopped. “Full Card” or “No Card” message : PCMCIA status“Transfer “ message in case of last flight not downloaded
11UP arrow keyDOWN arrow key
Provide Initialisation of IHM self-test rocedure bsimultaneously pressing both arrow keys for more than
5 seconds Scrolling through the menu.
12 Dashed line Permanently displayed on the screen.
13 BACK key Return to previous selection o f menu option.
UNIT
IHM MENU3. Operating With The System
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A. At power on (engines stopped) B. Rotor running
. “HUMS” Alarm Software Pb MFDAU/ACMS or helicopter pin code not recognised (No Data from Hums)
Inconsistency between MFDAU/ACMS and tables configuration
NR ,NG or NF parameters invalid
• Alarm “FDR”
FDR alarm or module MFDAU failure or FDR function not operating
• Alarm “CVR”
CVR function not operative or power supply missing on SSCVFDR unit.
PCMCIA not installed
Flight DataFlight Data
Full Card
Data Transfer Data Transfer
No Card
Rotor Tuning
2/21/2
Not enough Memory
1/2
IHM MENU
FLIGHT DATA
ACCESS3. Operating With The System
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After flight: Possibility to display the last flight data
Once automatic data transfer has been realised, crew member can get access to “ Usage” data contained on last session.
(engines shut down , main battery on)
1. Get access to ”Flight Data” menu then Press “Enter “
2. Use index “Down “or “Up” to access to the different pagesIn case of exceedance it will be shown : the type; max value reached ;duration ; and date of it.
Cycles NG / mot 1
Airborne 1 H 43
Landing 2
N11 Cycle
N21 Cycle 1.0
1.20
Oat at take off
OAT +18.0 C
ENG 2
N12 CYCLE
N22 CYCLE 0.9
1.20
Cycles NF/ mot 1
Cycles NG/mot 2
Cycles NF/mot 2
NR None TORQUE None ENG 1 None None
NR exceedance Torque exceedance Eng 1 exceedance Eng 2 Exceedance
Wow 9500Kg
ACCESS
FLIGHT DATA
ACKNOWLEDGEMENT3. Operating With The System
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“Acknowledge” (last page of the menu FLIGHT DATA)
Objective: check & acknowledge flight data
Crew member can provide data validation about each parameter mentioned of the flight (command Y/N ) then confirm by
pressing « Enter » inside the “Acknowledge” menu. Acknowledgement flag is then sent to the file already transferred in
PCMCIA.
It’s the way on board to process the “Lock” of the file. Then file locked cannot be modified any more
Eurocopter advise to do it on board after every session.
If the process is not done on board it should be done by the maintenance operator in front of the GSC during flight
downloading.
data Validation under processing Validation done
Acknowledge Done Acknowledge Run Acknowledge Fail
Validation fail
ACKNOWLEDGEMENT
ROTOR TUNING3. Operating With The System
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• Rotor Tuning on MR Determine main rotor adjustment to optimise vibration level in 1, 2 , 5 for processing adjustment on weight,
pitch rods, tabs angles
MAIN.R-100KT Main R-FPOG RUN
MAIN.R-HOVER MAIN.R-MCP
Main R-FPOG DONE
• Flight Configurations in MR tuning
FPOG: low pitch with NR>245 rpm and Delta NR< 5rpm
HOVER ground effect: Flight logic - ZRS < 50 ft - IAS hover < 50 kts
CRUISE 100kts: 90 kts < IAS < 110 kts
CRUISE PMC: IAS>130 kts
Minimum on rotor acquisition: One engine running
1. Highlight « ROTOR Tuning » . Select Main Rotor then
Enter.2. Select configuration FPOG, then valid by pressing
« Enter », acquisition will be displayed few seconds later
Main Rotor
Tail Rotor
Result Acquisition
FAIL
Acquisition in process
ROTOR TUNING
ROTOR TUNING
ROTOR TUNING3. Operating With The System
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Tail rotor
Tail.R- FPOG DONE
Main Rotor
Tail Rotor
Tail.R-FPOG RUN
• Rotor Tuning on TR
Determine tail rotor adjustment to optimise vibration level in 1 and realise the weight adjustment for each blade on TR
One configuration possible : on ground
Regime : FPOG flat pitch on ground with NR > 245 rpm and Delta NR< 5rpm + Top validity presence
FAIL
Acquisition in process Result on acquisition
TAIL.R FPOG
ROTOR TUNING
Minimum on acquisition: One engine running
1. Highlight menu « ROTOR Tuning » press « Tail Rotor »
then press « Enter ».
2. Select FPOG, then valid by pressing « Enter », Done
will appear few seconds later
Selection
ROTOR TUNING
ROTOR TUNING3. Operating With The System
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File transfer on
floppy
Value on acquisition
No threshold : use AHMU for adjustment process
ROTOR TUNING
ROTOR TUNING3. Operating With The System
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Function
Optimise rotor adjustment to obtain comfort on board without
any additional installation (maintenance job)
Washers added on tail rotor
Input Parameters 1 accelerometer bi-axis 41RK2
Ground/Flight Logic sol
NR 245trs
Top RA
Configuration :
1 acquisition recognised under IHM control menu : FPOG
Inside ACMS:
Identification
NR and ground configuration valid
Number of revolution to take to catch one acquisition on MR:
24 rpm
Acquisition will be done 5 times in a row before to provide the
result. Priority on VPU cycle
Inside VPU
Acquisition realised on accelerometers 41Rk2 synchronised on
TR pick up
If instability during acquisition: a message will be sent and
acquisition aborted
« acquisition impossible » or « fail »
If acquisition OK: VPU will compute amplitudes and phases
issued from signals accelerometer, a flag validity on phonic
wheel and MR magnetic pick up
Inside ACMS
One acquisition stored only : the last one
On ground
Results will be identified after a manual transfer without shutting
down the engines.
For any correction to be applied use Steady Control Rotor
application
Rotor tuning /Main Rotor
On IHM, a message “Run “then ”Done” or “Fail” will followacquisition result
Ground Station
Rotor Tuning/ Main rotor.
Y and Z amplitude levels monitored.
Amplitude in “ips”
No threshold , no adjustment proposal under GSC application
Possibility to transfer rotor data afterwards on floppy disk
ROTOR TUNING
ROTOR TUNING3. Operating With The System
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acquisition Value
No threshold : use AHMU for rotor adjustment
ROTOR TUNING
3. Operating With The System
DATA TRANSFER
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Data transfer monitoring
Transferring data remains an automatic operation. A« manual transfer » can be done by the operator through IHM control unit.
In automatic : when Ng and NR parameters pass under the defined threshold. All data are transferred to PCMCIA card
During transfer phase « Data Transfer » will be displayed to the crew until done is done.
Following messages can be displayed on IHM
For any reason a session not downloaded automatically can be done manuallyIf this operation is not done, a packed flight will be recorded on board at next start
If fail message appear after transfer operation:
Get in menu « Data Transfer” and activate « ENTER »
Transfer activated Transfer realised
Transfer Done Transfer Run
Failure during transfert
Transfer Fail Or
DATA TRANSFER
3. Operating With The System
MARMS GSC
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M‘ARMS Ground Station Computer : GSC
GSC software is working under Windows Server 2003 associated to SQL server 2000 software
PCMCIA unit to download data
DAT driver to make back-up and restore database
GSC purpose is to collect data from flight to save them on mirroring drive
Software GSC version V 5.1 called “Groundstation” has been defined by ECF . Its purpose is- to give access to different groups of work (crew, maintenance, expert, administrator)
- Store data coming from one aircraft or fleet of aircrafts
- Display flight report (where all usage data will be displayed: alarms, exceedance in flight domain)
- Inform operator on health acquisitions overshooted on main mechanical components
- Print and keep history flight report and maintenance message
- Provide rights to administrator to modify settings inside GSC (threshold modification, new users, new
groups creation )
MARMS GSC
3. Operating With The System
MARMS GSC
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M‘ARMS Menu
MARMS GSC
3. Operating With The System
MARMS GSC
DOWNLOADING
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At downloading .225 and raw present on PCMCIA card a consistency : A/C identification, compliance session date & GSC date,
PIN code identification.
• Files not acknowledged on board will be locked on GSC
• A flight report will be delivered.
Flying time, operating time and landings, engines cycles, exceedances, alarms detected during flight and engines power
check .
Any exceedance detected by ARMS will be compared to raw file
To update usage and health counters on the different parts monitored it’s necessary to pass by flight analysis .
After analysis operator will be driven by maintenance message:
Apply work cards MMA chap.45
Confirm overshoot by using raw file
Use communication form with ECF technical support
DOWNLOADING
3. Operating With The System
FLIGHT REPORT
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A/C Family A/C Reference Date and starting session
Engines Airframe
FLIGHT REPORT
3. Operating With The System
MAINTENANCE
REPORT
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MAINTENANCE ACTION
Maintenance report will be the result of the flight analysis.
Each message monitored will be linked with a work card associated.Each message identified by session date are classified in 3 categories: usage, system and health
Purpose: Produce to maintenance operator the work card reference
Messages can be acknowledged after checking
maintenance Messages
Maintenance
Report
3. Operating With The System
DISCREPANCY
REPORT
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System : MARMS Customer :
Fault repor t-DR Customer ref. :
Page : 1 / 1
Modification request EC ref.:
Report / Request : Test site :
A/C tail number :
ACMS-C S/N & S/W version :
GSC S/N & S/W version :
EMU S/N S/W version :
DSP S/N & S/W version :
FDAU S/N & S/W version :
Date & Flight report # :
Problem description :
Writer : Approved by :
Visa : Visa :
Transmitted to EC the : By FAX :
EC answer : Evolution decided? Yes No
Units involved :
Evolution description :
S/W evolution :
Availability :
Writer : Approved by :
Visa : Visa :
Transmitted to Customer the : By FAX :
Concerning a problem: airborne orsoftware, equipment module as
MFDAU, VPU, EMU, GSC ...
Official Link: DR
3. Operating With The System
DIAGNOSTIC
REPORT
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Usage or Health overshooting on a red or
amber threshold, abnormal Trend
detected on a component
Official Health form: EDR
Tel : 04.42.85.99.25Tel : 04.42.85.17.04
N O T E S
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4. Usage Analysis
OPERATING TIME
FLYING TIME
FLYING TIME & LANDINGS
NR CYCLES
TORQUE CYCLES
ENGINE EXCEEDANCE
NR EXCEEDANCE
TORQUE LIMIT MONITORING
ENGINE POWER ASSURANCE CHECK
4. Usage Analysis
OPERATING TIME
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Function
- accurate time for maintenance calculation
- Consistency check with flying time computation
- Provide low temperature flag information for special flightconditions
Input Parameters Signal source
OAT A429 APM
N11 et N12 Arinc Fadec
NR Phonic wheel
Operation
Take in account time at first engine starting :Tf0
Take in account temperature at take off: OAT
Take in account time at last engine shut down: Tff
Time in operation = Tff_- Tf0
Invalidity on OAT if flight condition not activated (ground run).Message « invalidity » on this parameter will be recorded on thissession
Pilot Confirmation
yes
Flight Report
Duration in operating Time
OAT at take off ( ***** ex: PF or after crank or engine washing)
Maintenance Message
In case of pilot disagreement > 3° “System message”
Ground Station Affect operating time counters to parts.
Cumulated operating time since beginning.
4. Usage Analysis
OPERATING TIME
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N11 and N12 < 5%
Start of Session End of Session
N1_1
N1_2
NR
N11 or N12 > 5%
with NR < 85 rpm
T running = Tf end - Tf init
Session will start: at first engine starting (NG < 5%) and close at last engine shut down (NG < 5% et NR
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Function
Helpful for TBO and SLL
Accurate time computation
Record the number of landings
Input Parameters Signal sourceFlight/ground Logic Discrete train
Weight A 429
Operation
Computation flying time by storing starting flying time and
end flying time :
Flying Time = (Tf take off – Tf landing)
On each take off it will be stored max weight to estimatetime in overload
Implement landing counters after each landing
Pilot Confirmation : yes
Flight Report
Duration
Landing Number
Maintenance Report
In case of pilot disagreement “System message “
”Airborne time has been declared faulty” if t >5mn.
“Landing count has been declared faulty” if =+/-1
«Flight in overweight: duration xxx »
Ground Station
Displayed time and landings
Under « Usage »/ Airframe/Time : Counters Access to total« Flying time » and « Landings » monitored.
Flying time cumulated or by session
Landing numbers cumulated or per session
4. Usage Analysis
FLYING TIME &
LANDINGS
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Time spent in flight
By session
Counter cumulated
Landings session
and cumulated
4. Usage Analysis
NR CYCLES
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Function
Recording NR cycles to determine spectrum domain.
Can be used for manufacturer for mechanical parts
expertise
Input Parameters Signal Source
Phonic wheel NR
Operation
Detect NR regime to compute NR cycles
NR cycle=1 when NR pass over a threshold max andpass lower a threshold min
Compute and store session cycles
Flight Report : none
Maintenance Report
“Reasonableness check failure, NR cycle
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0
50
100
150
200
250
300
350
400
Time
R P M
NR_cycle_max = 245 rpm
NR_cycle_min = 220 rpm
NR cycle = 1
4. Usage Analysis
TORQUE CYCLES
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Function
Recording TQ cycles to determine spectrum domain.
Can be used for manufacturer for mechanical parts expertise
Input Parameters Signal Source
TQ1, TQ2: Engine Torque A429 VMS
Operation
Detect TQ regime to compute TQ cycles
One torque cycle is defined when pass over a threshold max
and pass lower a threshold min
Compute and store session cycles
Flight Report : none
Maintenance Report :
“Reasonableness check failure, NR cycle
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Torque
0
20
40
60
80
100
120
Time
E n g i n e T o r q
u e
( % )
TQ_cycle_min = 30 %
TQ_cycle_max = 70 %
Torque cycle = 1 FPOG
HOVER
CRUISE
4. Usage Analysis
ENGINE
EXCEEDANCE
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Function
Automate cycle counting on NG and NF cycle:
getting accurate counting
evaluate next inspection on
Input Parameters Signal Source
N11/N12 (NG) cycle A429 Fadec
N21/N22 (NF) cycle A429 Fadec
Operation
N1 and N2 cycles taken from Fadec computers:
4 counters per engineN1 cycle session = N1 cycle end - N1 cycle end N2 cycle session = N2 cycle end - N2 cycle start
Flight Report
N1/ session
N2/ session
Maintenance Report
Maintenance Message if pilot disagreement
“Eng N° xx N1cycle count has been declared faulty” or
“Eng N° xx N2cycle count has been declared faulty”
Ground Station
USAGE/ Engine1or 2 /Engine damage
cycles counters N1 and N2 displayed session/cumulated
By session Cumulated
4. Usage Analysis
ENGINE
EXCEEDANCE
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4. Usage Analysis
NR EXCEEDANCE
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Function
Detect and measure NR exceedance to determine
maintenance operation.
This value can be acknowledged by the crew
Input Parameters Signal Source
NR NR phonic wheel
System in operation
Each NR exceedance duration will be identified and stored
following NR max conditions
- NR max value for NR>310 rpm
- NR min value for NR
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310
400
Time
N R (
r p m )
NR low = 290 rpm
NR high = 310 rpm
NR exceedance duration
200
0
290
4. Usage Analysis
TORQUE LIMIT
MONITORING
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Function
Detect and measure TQ exceedance to introduce maintenance
actions following flight configuration and power transmitted on the
mechanic (MRP et TR)
Input Parameters (Arinc line VMS) Value
Torque threshold in OEI 95 %
Torque threshold in MTP 104,6 %
Torque threshold in climb 1 103,6 %
Torque threshold in climb 2 102,7 %
Torque threshold in Cruise 100,5 %
IAS Threshold in MTP 45 knts
IAS Threshold in climb 1 57 knts
IAS Threshold in climb 2 70 knts
TR position for torque limitation 80 %
Operation
Store exceedance under 4 ranges in OEI and 11 in AEO and
for each exceedance (OEI, MTP, Spot Turn, CLIMB, CRUISE)
IAS , TR position, TRQ max value and duration
Maintenance Report :
Case of exceedance: « Overtorque has been detected”
In case of pilot disagreement on TQ value:
” TQ exceedance max value has been declared faulty ”
“TQ exceedance duration has been declared faulty ”
Ground station: «Usage/airframe/ TQ exc
Flight Report : yes
Time, configuration Type, Max Value reached/duration
4. Usage Analysis
TORQUE LIMIT
MONITORING
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REGIME DEFINITION
MTP Tq > 104,6 % IAS < 45 kts TR position < 80 %
SPOT TURN Tq > 104,6 % IAS < 45 kts TR position > 80 %
CRUISE Tq > 100,5 % IAS > 70 kts
Torque limit in AEO
85
90
95
100
105
110
0 20 40 60 80 100
IAS (kts)
T O R Q U E ( % )
MTP
CRUISE
CLIMB 1
CLIMB 2
CLIMB 1 Tq > 103,6 % 45 knts 102,7 % 57knts
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EPC Function (engine power check)
Provided by VMS.
ACMS module collect results and output parameters from
VMS and Fadec
Acquisition Parameters Source
N1 Fadec
N2
TRQ 1+TRQ2
OAT
Marg TOT 1/2 Fadec
Marg TRQ 1/2 Fadec
TOT 1 + TOT 2IAS
ZB
Parameters provid ed by VMS
Marg TOT1 corrected T4 margin1
Marg _TRQ1 corrected TQ margin 1
EPC1_STAT status EPC eng1
EPC2_STAT status EPC eng2
Marg TOT2 corrected T4 margin 2
Marg _TRQ2 corrected TQ margin 2
Aircraft Configuration Air intake closed
VMS is checking that EPC conditions are required before to sendthe command to Fadec to compute engine margins
Once the computation is done each Fadec sends back a
transmission status message 5 times in a row
- If one engine doesn’t mix VMS conditions a message « EPCinvalid » will be displayed .
- If one parameter is not valid a message « EPC not available »
will be displayed.
- If a EPC is requested with Air intake opened; a message bleed
valve opened will be displayed
During acquisition phase MFDAU/ACMS is monitoring the status
messages « EPC STAT_VMS » and « EPC Trans FADEC» .
Both engines are monitored independently
20 EPC (2 X10) per session max
S
VMS
Demande
CSM
VMS/ Fadec
0 60
Margin computation
by Fadec
80
Computation Margin
by VMS
90
Status VMS
(EPC_Stat_VMS
Status VMS
(EPC_TRANS)
paramètres calcul + marges
Fadec 5X
Margins computation VMS
5X
Stab Phase VMS
CSM request
APM
4. Usage Analysis
ENGINE POWER
ASSURANCE CHECK
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1
2
Display in flight report
TOT Margins
TQ Margins
Trend in TOT and TRQ
EPC Eng 1 under Health
N O T E S
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5. System Analysis
ALARMS
SYSTEM STATUS
5. System Analysis
ALARMS
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Function
Stores and displays alarms displayed in flight to:
- Identify failures to analyse discrepancies
- Help for maintenance- Confirm Pb appear during the flight
Input Parameters Source
Chip detection discrete
Red Alarms MFDAU
Logic ground /flight discrete
Activation Condition
Starting Activation start /end session for chip detection for a
discret status >5s (logic Flight/ground not taken into account)
Activation for all the others failures only in flight configuration
Each failure can be record no more than 3 times.
Each one will be identified (date start , date end)
Maintenance Report
Yes if chip detection on MGB /TGB /IGB / Engines
Message : «Oil debris has been detected on P/N ..S/N… »
Ground Station
Aircraft Status (Warning /failure) for alarms appeared during
flight.
- Duration
- Occurrence
System Status ( minor/major defects) for any equipment failure
Flight Report : yes
Number of alarms and occurrences appeared in flight
5. System Analysis
ALARMS
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Maintenance report
(ex: chip detection)
Click« Aircraft status » alarms displayed
« Failures » and « Warnings »
WARNINGS
FAILURES
5. System Analysis
SYSTEM STATUS
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Minor defects will be stored over 30’ flight
Minor defects
Major defects
Displayed major and minor defects appeared in flight
N O T E S
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6. Health Domain
HEALTH GENERALITY
SIGNAL TREATMENT
6. Health Domain
HEALTH GENERALITY
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VIBRATION
MONITORING
TGB ENGINES MGB TDS ROTORS
LEFT RIGHT GEARS / BEARINGS / SHAFTS
Engine Power up
Engine Stabilized Engine Power Up
Engine Stabilized
MAIN TAIL
- Balance
- Tuning
- Balance
- Tuning
6. Health Domain
HEALTH GENERALITY
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An accelerometer delivers a signal representative of all vibrations registered in the vicinity of its attachment. This signal contains
information from gears, shafts and bearings in close proximity: this will define the ACCELEROMETER RAW vibration signal.
To identify the vibration signal of each element, a signal from phonic wheels (toothed wheel associated with a sensor delivering a
pulse with each passage of tooth) is used to obtain its own rotation speed. With this information, the vibration signal of each
element could be extracted from the raw signal and will elaborate the vibratory SIGNATURE.
6. Health Domain
SIGNAL TREATMENT
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Signal Treatment
The Signal issued from the accelerometer will be sampled to obtain a number of points constant per shaft revolution and thiswhatever the variation speed : This is called synchronous sampling average
NF phonic wheel (1or 2) will be the reference for the synchronous sampling: For each Rpm we will take a number constant of
points.
This reference should be in phase with the different reduction rate of the train drive shaft.
The synchronous average
Synchronous average is composed of: signature of the shaft monitored + signals issued from the other shafts around
Sampling will be done following a number of revolution known by the system. Noise will be erased from the shaft signatures
Mesh frequency is not a perfect multiplier of the shaft period.
Conclusion: Synchronous average will allow to filter the signal in order to obtain a revolution of a shaft removed from its noise
around
6. Health Domain
SIGNAL TREATMENT
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Signal Interpolation
0
1
2
3
4
5
0 100 200 300 400 500 600 700 800
0
1
2
3
4
5
0 100 200 300 400 500 600 700 800
-1
-0.5
0
0.5
1
0 100 200 300 400 500 600 700 800
Signal of the phonic wheel
Multiplier
Accelerometer signal
points
sampling
Phonic wheel NF
The signal is multiplied to obtain a number of tops equal to
numbers of points requested
Superimpose to the accelerometer signal to the multiplier
of tops.
This is called signal interpolation
6. Health Domain
SIGNAL TREATMENT
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Synchronous average
N signaux/ N
6. Health Domain
SIGNAL TREATMENT
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Fast Fourier Transform
Fast Fourier Transform FFT is a treatment of the signal : Breakdown of the signal in sinusoids amplitude and frequencies different
in order to identify the frequencies of a part monitored
It’s the graphic representation in harmonics in the frequencial domain.
One revolution
of the part monitored
FFT Spectrum
Fundamental
Harmonic 2
Harmonic 3
(Harmonic 1)
6. Health Domain
HEALTH GENERALITY
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0 5 10 15 20 25 30 35 40 45 500
0.2
0.4
0.6
0.8
1
0 10 20 30 40 50 60 70 80 90 100-1.5
-1
-0.5
0
0.5
1
1.5
OM-1
OM-5
0 10 20 30 40 50 60 70 80 90 100-1
-0.8
-0.6
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
Temporal Signal FFT Spectrum
N O T E S
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7. Health Monitoring
MAIN ROTOR
TAIL ROTOR
GEARS
SHAFTS & TRANSMISSIONS
BEARINGS
ENGINES
Function Inside ACMS
7. Health Monitoring
MAIN ROTOR
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Function
Detect and anticipate defects on MR by monitoring indicators
to check daily health on rotor and its harmonics.
Input Parameters Source Magnetic pickup 1 top per rev MR
NR rotor threshold >245 rpm
IAS cruise threshold >125 knts
ZB altitude ZB245 rpm with NR< 5trs
CRUISE: stabilized with IAS 125knts and IAS245, NR< 5trs and ZB 30mn
“Check accelerometer MR04/MR05 and Main Rotor Top” in
minor defect
7. Health Monitoring
MAIN ROTOR
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Numbers of acquisitions par session: 5 max
Health /MR/ Balance Monitoring in ground and flight configuration
Health Graphic extraction
(ips en Y et Z harmonics in OM1,OM2,OM5,OM10)
Fixed threshold on indicators OM1(red and amber) and OM2
(amber)
Start acquisition NR average
flight configuration
Ground configuration
Function Inside VPU
7. Health Monitoring
TAIL ROTOR
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Detect and anticipate defects on TR by monitoring indicators
to check daily health on TR and its harmonics
Input Parameters
Magnetic pickup 1 top per rev TRNR rotor Threshold >245 rpm
IAS cruise >125 knts
ZB altitude ZB 245 rpm with NR< 5trs
CRUISE: stabilized at IAS 125knts and IAS245 and NR< 5trs ( ZB30mn
« Check accelerometer TR and tail rotor top » in minor
defect
7. Health Monitoring
TAIL ROTOR
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GSC:
Health /MR/ Balance Monitoring in ground and flightconfiguration
Health graphic extraction des signaux MR en indicateurs santé
(ips in Y and Z in harmonics 1, 2,4)
-Threshold monitoring in learning period
Numbers, start time and NR average on acquisition
TR monitoring in flight
TR monitoring on ground
Function
7. Health Monitoring
GEARS
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Anticipate on gears deteriorations MGB,IGB,TGB
No acquisition on ground
Parameters
For VPU
identify sensor validity for acquisition
Phonic wheel NF1or 2
Ratio between phonic wheel and gear monitored
10 accelerometers valid (8 on BTP, 1 on BTI, 1 on BTA)
For ACMS:
TR position
TRQ1+TRQ2
flight/ground logic
Operation
Included in VPU cycle
2 conditions requested
For IGB and TGB gears: flight and TR position> 70%For MGB gear: flight and TRQ1+TRQ2> 45%
-Acquisitions are realised based on 10 accelerometers tours
Following gears number of rpm could be different
(48rpm, 100rpm or 200 rpm )
If acquisition rejected: VPU follows up next one
-5 acquisitions max stored in MFDAU.
(Acquisition recorded with 30 mn interval)
If flight logic is lost interruption on acquisition.
Maintenance Report
Exceedance on a health indicator for a gear monitored.
“ indicator “XX” has exceed its amber threshold on LH
first reduction pinion”
No data over 5 hours
“LH double pinion is not monitored for > 5hours““Check accelerometer xx and the corresponding VPU treatment”
GSC
date
Time for each acquisition
signal accelerometer for the gear monitored
Average (TRQ1+2) or Tr position displayed
Indicators affected:OM1, OM2,nOM, MOD,RMS,RMSR, Km, Kr, Kg
.
7. Health Monitoring
GEARS
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Signal issued from computation
Convertion in FFT
(harmonics)
Function
7. Health Monitoring
SHAFTS &TRANSMISSIONS
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Anticipate on gears deteriorations shafts and bearings on TDS No acquisition on ground
Parameters
For VPU
Identify validity of the sensor requested to acquire acquisition
Phonic wheel NF1 or 2
Numbers of revolution 200trs
Ratio between phonic wheel and shaft monitored
6 accelerometers valid (1 per shaft)
For ACMS:
TR position
Flight /ground logic
Operation
Including in VPU cycle
Condition: flight/ground = flight and TR pos >70%
Acquisition on 200 rpm on the shaft monitored.
If acquisition rejected, VPU follows up next one
-5 acquisitions max stored inside MFDAU.
(Acquisition recorded every 30 mn interval )
If flight logic is lost interruption on acquisition
Maintenance Report “ indicator “XX” has exceed its amber threshold on
TRD forward shaft element”
If no data from more than 5 hours, following message sent :
“TRD center shaft 3 is not monitored for >5hours “
“Check accelerometer xx ”
Ground Station
-harmonic monitoring in OM1 and OM2
Time on Acquisition
Accelerometer signal on 200 rpm
TR position during acquisition
7. Health Monitoring
SHAFTS &TRANSMISSIONS
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OM1 monitoring
Shaft n°3 health monitoring
Health SPECTRUM
Function Inside VPU
7. Health Monitoring
BEARINGS
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Ground Station:
Associated indicators : FI, FE, M6, RMS, H2FE.
Control and Anticipate on bearings problems to avoid bigger
damage on the mechanic around
Parameters
For VPU
identify validity of the sensor requested to acquire acquisition
Phonic wheel NF1 or 2
Numbers of revolution 200trs
Ratio between phonic wheel and shaft monitored 128/256pts rpm
17 accelerometers
For MFDAU/ACMS:TRQ1+TRQ2
TR position
Flight/ground logic
Operation
Belong to VPU cycle
Recognising configuration:
For IGB and TGB bearings: flight and Tr pos> 70%For MGB: Flight and TQ1+TQ2> 45%
For MRH bearings : Flight and IAS> 125 knts
Inside ACMS
Acquisition identification to be done according VPU cycle. If
TRQ1+TRQ2 or RA pos or Vi a