F2000EX EASY 02-45-00 ATA 45 – AIRLANE DIAGNOSTIC AND CODDE 1 PAGE 1 / 2 … · 2012. 6. 27. · cas messages . 02-45-00 f2000ex easy page 2 / 2 codde 1 issue 3 ata 45 – airlane

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ATA 45 – AIRLANE DIAGNOSTIC AND MAINTENANCE SYSTEM (ADMS)

TABLE OF CONTENTS ISSUE 3

DASSAULT AVIATION Proprietary Data

02-45 ATA 45 – AIRPLANE DIAGNOSTIC AND MAINTENANCE SYSTEM (ADMS)

02-45-00 TABLE OF CONTENTS

02-45-05 GENERAL

Introduction Elaboration and display of failure information for dispatch decision Central Maintenance Computer function Sources Access to the maintenance window on MDU Centralized Maintenance Computer (CMC) menus

02-45-10 DISPATCH DECISION

Introduction Airplane system computer fault code download with the fault code display device

02-45-15 MAINTENANCE

Introduction Processing and display of maintenance messages Parameter monitoring System tests Hardware architecture and components

02-45-20 PRINT (OPTION) OR DOWNLOAD OF MAINTENANCE REPORTS

Introduction Procedure

02-45-25 UPLOAD OF NAVIGATION DATA BASES

Introduction Procedure

02-45-30 ABNORMAL OPERATION

CAS messages

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GENERAL ISSUE 3


INTRODUCTION

The F2000EX EASy system enables the flight or maintenance crew to:

- obtain airplane system failure information requested for an optimized and safe dispatch decision,

- print or download maintenance reports,

- upload navigation files and data bases,

- obtain airplane failure and status information, perform additional ground tests, as requested for servicing, maintenance and troubleshooting operations.

The above listed capabilities rely on the F2000EX EASy Airplane Diagnostic and Maintenance System (ADMS) which includes first:

- the built-in test functions of the avionics, Head-up Guidance System (HGS), engine and airplane systems, which enable these systems to:

o detect and report failures to the EASy system in real time, in flight or on ground,

o perform on-ground additional tests on request,

- the EASy functions in charge of elaborating and displaying failure information for dispatch decision,

- the EASy Central Maintenance Computer Function (CMCF).

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Maintenance panel

Printer(optional)

Cursor ControlDevice (CCD)

Data ManagementUnit (DMU)

CAS messagewindows

DATA LOADERand LH DU BAT

breakers

Maintenancewindows location

MAU 2 CH Abreaker

Printer breaker(optional)

FIGURE 02-45-05-00 FLIGHT DECK OVERVIEW

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GENERAL ISSUE 3


ELABORATION AND DISPLAY OF FAILURE INFORMATION FOR DISPATCH DECISION

The EASy avionics system (Monitor Warning and Graphic Generation functions) processes the EASy input data, and, when a failure is detected, generates the proper cockpit indication for dispatch decision. This indication consists of one or several CAS messages, as well as abnormal status indication presented on PDU (gears, slats / flaps, airbrakes, …). When recommended by the Master Minimum Equipment List (MMEL), and in order to limit as much as possible dispatch restriction, detailed failure information can be obtained in the systems, STAT and TEST synoptics, or by a direct computer fault code readout performed on ground with the Fault Code Display (FCD) device.

CENTRAL MAINTENANCE COMPUTER FUNCTION

The EASy Central Maintenance Computer Function (CMCF) provides: - a single access to avionics, HGS, engines and airplane systems maintenance

messages, status information and initiated ground tests, requested for servicing, maintenance and troubleshooting purposes,

- a means of loading navigation files and data bases, and system software from the on-board Data Management Unit (DMU) located in the cockpit (LH console), or from a laptop acting as a Centralized Maintenance Computer (CMC) Remote Terminal (CMC RT),

- a means of downloading maintenance data to the on-board DMU, or to a laptop acting as a CMC RT,

- a means of printing data on the optional on-board printer located in the cockpit (RH console),

- a means of configuring the maintenance computer RS-232 port located in the cockpit maintenance panel, in order to connect the FCD device to one of the following airplane system computers: o Engine Diagnostic Units (EDU) 1 and 2, o Cabin Pressure Control (CPC), o Bleed Air Supply Computer (BASC) control and monitoring, o Fuel Quantity Management Computer (FQMC) channels 1 and 2, o Braking and Steering Control Units (BSCU) 1 and 2, o Temperature Control System (TCS crew, TCS pax, TCS man) of the air conditioning

computer.

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GENERAL DGT94085


The CMCF is hosted by the CMC module. It can be controlled: - from the cockpit, on ground, with the Cursor Control Device (CCD) to navigate in the

menu of the CMC maintenance window displayed on one MDU, - from a standard laptop connected to the EASy Local Area Network (LAN) connector

located in the maintenance panel (with the LAN adapter connected into the MAINTENANCE OPERATION plug), and configured as a CMC RT by executing the dedicated software. The CMC RT can be used with the airplane being either on ground or in flight.

In this document, the CMC cockpit control mode will be the mode mainly described. For more information related to the CMC RT mode, refer to the Aircraft Maintenance Manual / ATA 45.

NOTE

The CMCF software does not comply with certification requirements applicable to functions generating and displaying information related to the safety of flights, as the Monitor Warning and Graphics Generation functions do. Consequently, failure and status information displayed on the CMC maintenance window cannot be considered as the only information used for dispatch decision: they are dedicated to servicing, maintenance and troubleshooting purposes.

LAN adapter in rest position

FIGURE 02-45-05-01 MAINTENANCE PANEL – NORMAL FLIGHT

LAN adapter

to CMC RT

Cockpit RHrear window

to FCDdevice

FIGURE 02-45-05-02 MAINTENANCE PANEL – MAINTENANCE OPERATION

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FIGURE 02-45-05-03 CENTRAL MAINTENANCE SYSTEM FUNCTIONAL ARCHITECTURE

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SOURCES

ELECTRICAL

The Centralized Maintenance Computer (CMC) is a module of a Modular Avionics Unit (MAU). It is installed in slot 2 of MAU 2 (MAU 2 is installed in the airplane nose cone). It is powered by channel A line through RH B2 bus when the RH AV MASTER switch is depressed, and is protected by the MAU 2 CH A circuit breaker. The CMC is consequently not powered in MINI LOAD mode. The CMC is alternately powered by the LH DU stand-by battery during avionics or airplane power-off in order to ensure a proper CMC shutdown.

FIGURE 02-45-05-04 OVERHEAD CIRCUIT BREAKER PANEL

DATA

The data available for processing and display of failure information requested for dispatch decision, and for the Central Maintenance Computer Function are all analog, discrete and digital data available to the avionics system. These include:

- all information received by the MAU(s) for flight management, - faults reported in real time by the system computers (avionics, HGS, engines, airplane

systems), on ground or in flight, through digital links (ARINC 429 or ASCB), - fault reports automatically downloaded on ground from air conditioning computer which

is not capable of sending its fault reports in real-time to the CMC.

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ACCESS TO THE MAINTENANCE WINDOW ON MDU

The CMC maintenance window can be displayed on the upper or lower MDU, or on the right PDU if configured as an MDU. It can be displayed as follows:

- put the CCD cursor in any 1/3 or 2/3 window of the selected MDU,

- call the menu by depressing the CCD MENU button,

- select the MAINT item of the menu. The CMC maintenance window will appear on the MDU as a 2/3 window.

"MENU"

"ENTER"

FIGURE 02-45-05-05 ACCESS TO THE MAINTENANCE WINDOW ON MDU

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CENTRALIZED MAINTENANCE COMPUTER (CMC) MENUS

The CMC maintenance window makes available a set of sub-functions through the various CMC menus, organization of which is described in the figure below.

DAILY SERVICINGMAINTENANCEDATA LOADER

DAILY SERVICING SCREEN(Engine Oil levels only)

MAINTENANCE MESSAGESPARAMETERS MONITORING

SYSTEM TESTSEXTENDED MAINTENANCE

STORAGE ON/OFFMEMBER SYSTEM STATUS

CONFIGURATIONREPORTS

RS 232 PORT MANAGEMENT

SELECT A TEST

SELECT A SCREEN

ACTIVECURRENT LEG

HISTORICAL BY DATEHISTORICAL BY ATA

CLEAR COMPUTER FAULT MEMORY

DATA LOADING SYSTEM SCREEN

FIGURE 02-45-05-06 CMC MENU ORGANIZATION

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INTRODUCTION

The elaboration and display of failure information requested for an optimized and safe dispatch decision is based on the following principles (see figure 02-45-10-01):

- a CAS message is displayed in case of any system failure identified by the EASy system, and which impacts the airplane dispatch capability,

- in order to limit the number of CAS messages, failures reported by braking, bleed air and anti-ice, fuel and air conditioning systems computers with a generic CAS message XXXX CMPTR FAULT CODE indicates to the crew that at least one fault code was received from the corresponding airplane system computer,

- these generic CAS messages are (refer to last subsection):

o A/I CMPTR MONIT/CONT FAULT CODE , when a fault code is received from the Bleed Air Supply Computer (BASC) Monitoring/Control,

o FUEL CMPTR FAULT CODE , when a fault code is received from the Fuel Quantity Management Computer (FQMC) channel 1 or 2,

o BRAKE CMPTR 1+2 FAULT CODE , when a fault code is received from the Braking and Steering Control Unit 1/2 (BSCU 1/2),

o COND CMPTR FAULT CODE , when a fault code is received from the Air Conditioning Computer (ACC)

- a table of CAS messages along with their references to enter in the MMEL item list is included in the MMEL preamble,

NOTE

Any CAS messages not listed in that MMEL preamble is to be considered as a NO GO.

- a MMEL item list reference is associated with any failure indication displayed on ground,

- the MMEL recommends getting additional information either in the STAT synoptic, or through a direct computer fault code download operation performed with the Fault Code Display (FCD) device, for an optimized dispatch decision.

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Some failures impacting the airplane dispatch can only be detected when the airplane is in a specific operational configuration (e.g.: engine running, anti-ice operating, braking with anti-skid operating, …). To keep the failure information displayed when the airplane is no longer in this operational configuration, the corresponding CAS message is latched until the CLR FAULT soft key on the TEST synoptic is activated for 5 sec at least.

FIGURE 02-45-10-00 CLR FAULT SOFT KEY

This allows the system to:

- make sure that the dispatch decision is taken with all CAS messages related to known airplane failures being displayed to the crew,

- inform the crew performing the Daily Servicing operation, thus providing with anticipation a remedy for any failure that was detected during the previous flights, and that could impact the next mission,

The CLR FAULT soft key shall consequently not be activated to confirm the failure, unless otherwise specified in the MMEL.

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(1) CAS message(s) orother failure indicationdisplayed in PDU, on

ground

DISPATCHDECISION

(2) MMEL preamble(reference table)

(3) MMEL Item list

Additionalinformation

requested foroptimal dispatch

decision ?

Airplane system fault codereading with Fault Code

Display (FCD) device

Additional informationfrom systems, STAT and

TEST synoptics

YES

e.g. fault code

NO

(4) MMEL [O]Procedure

(4) MMEL [M]ProcedureOR

FIGURE 02-45-10-01 DISPATCH DECISION - PRINCIPLE

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AIRPLANE SYSTEM COMPUTER FAULT CODE DOWNLOAD WITH THE FAULT CODE DISPLAY DEVICE

When recommended by the MMEL, an airplane system computer fault code download operation can be performed with the Fault Code Display (FCD) device in order to get detailed failure information at the origin of the XXXX CMPTR FAULT CODE CAS message.

The FCD device is a standard laptop configured with the Dassault AEGIS-EASy software.

The download operation is performed as follows:

- connect the FCD device to the "Maintenance Computer" RS-232 port located in the cockpit maintenance panel,

- configure the Maintenance Computer RS-232 port with the CMC, in order to connect it to the airplane system computer to be downloaded,

- download the selected computer with the AEGIS-EASy software.

CONNECTION OF THE FCD DEVICE TO THE MAINTENANCE COMPUTER RS-232 PORT

This connection is performed by using a standard Serial connection cable that will connect the FCD Serial port to the Maintenance Computer RS-232 port located in the cockpit maintenance panel.

"MAINTENANCE COMPUTER"RS-232 port

Standard serialcable

Fault Code Display (FCD) device

FIGURE 02-45-10-02 FAULT CODE DISPLAY DEVICE CONNECTION

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CONFIGURATION OF THE MAINTENANCE COMPUTER RS-232 PORT

The EASy Custom I/O modules integrate a configurable routing device to connect the Maintenance Computer RS-232 port to the airplane system computer to be downloaded. The configuration is performed by using the CMC as follows:

- display the CMC maintenance window on the upper or lower MDU (or on the RH PDU if re-configured as MDU),

- reach the CMC window named RS-232 PORT MANAGEMENT from the CMC MAIN MENU by selecting MAINTENANCE, then EXTENDED MAINTENANCE, then RS-232 PORT MANAGEMENT,

- click on the selected computer name through the CCD: when the selected name appears in the COMPUTER CONNECTED field, the connection is established.

DOWNLOAD OF THE SELECTED AIRPLANE COMPUTER WITH AEGIS-EASy SOFTWARE

As soon as the Fault Code Display (FCD) device is connected to the RS-232 port, and the RS-232 port is configured for the selected computer, the download operation can be launched by using the AEGIS-EASy software. The download operation is performed as follows:

- start the laptop and execute the AEGIS-EASy software, - select the proper A/C S/N in the Aircraft menu bar, - select the computer to be downloaded in the computers list, by checking the

corresponding checkbox, - launch the download operation by clicking on the Download soft key, - read the downloaded fault codes in the Code area.

NOTE

If the selected computer does not correspond to the computer for which the RS-232 port is configured, the download operation will terminate with a COMPUTER NOT RESPONDING failure indication. In this case, select the correct computer and launch again the download operation.

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FIGURE 02-45-10-03 RS-232 PORT MANAGEMENT WITH THE CMC

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Airplanemenu bar

Computercheckbox

Downloadsoft key

FIGURE 02-45-10-04 AEGIS-EASy DOWNLOAD WINDOW

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MAINTENANCE ISSUE 3


INTRODUCTION

The Central Maintenance Computer Function provides the maintenance crew with a set of sub-functions in order to facilitate the whole airplane troubleshooting and maintenance. These main sub-functions are:

- processing and display of maintenance messages,

- parameter monitoring,

- system tests (ground tests, on request).

PROCESSING AND DISPLAY OF MAINTENANCE MESSAGES

Maintenance messages are elaborated by the CMCF based on any failure information or flight data made available to EASy. Fault processing equations are defined in order to provide the mechanics with only the maintenance message identifying the initial cause. These fault processing equations combine the various available information to isolate the failure and to eliminate as much as possible the cascade effects.

They result in maintenance messages which mainly contain the following information:

- maintenance message name,

- list of possible defective Line Replaceable Units (LRUs), ordered from the most to the less probable,

- symptoms, as visible by the flight or maintenance crew,

- reference of the Fault Isolation Procedure of the Aircraft Maintenance Manual detailing the maintenance actions to be performed if the message occurs,

- flight phase and time stamp of all identified transition of the message from the Inactive to Active or Active to Inactive status.

The maintenance messages are stored in the Fault History Data Base (FHDB). The CMC Maintenance Message menu allows the operator to display messages being in the Active status at the time of the display, or messages which were stored in the FHDB during the current or previous legs.

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PARAMETER MONITORING

The CMCF is capable of displaying and refreshing in real time screens of parameters (e.g. screen containing landing gear proximity sensors status presented in figure ). These parameter monitoring screens are defined to ease the troubleshooting and maintenance operations by reducing the external test equipment requirements.

FIGURE 02-45-15-00 EXAMPLE OF PARAMETER MONITORING SCREEN

SYSTEM TESTS

The CMCF is capable of initiating ground tests of equipped systems. These ground tests are mainly defined to simplify the return-to-service operational tests to be performed after a system component replacement.

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HARDWARE ARCHITECTURE AND COMPONENTS

The following schematics present the hardware components and links involved in the Airplane Diagnostic and Maintenance System (ADMS). MAINTENANCE INHIBIT is a guarded switch which allows ground maintenance operation with inhibition of overhead panel automatic sequences.

Maintenance Panel

Modular Avionics Units (MAU)

I/O Modules

Maintenance MUX

CMC Module (MAU2A)

Monitor Warning function

Processor Modules

Databases- Loadable Diagnostic Information- Fault History Database

Advanced Graphics Modules (2 to 4)

°RS-232 TO RS-422

° °°°°° ° °°

Central Maintenance Function- Fault Processing- Tests & Parameter Monitoring- RS-232 Port management- Data & Software Load

ARINC 429

RS 232

RS 422 System computers with RS 422 link(EDU, BASC, FQMC, BSCU, ACC, CPC)

System computers with ARINC 429 link

Printer

CCD

LAN

Avionics components with ASCB linkNetwork Interface ControllersASCB

Analog and discrete data

DMU

Video Control I/O Module (MAU1A)RIB

LANVirtual backplane network

FIGURE 02-45-15-01 CENTRAL MAINTENANCE SYSTEM HARDWARE ARCHITECTURE

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MAINTENANCE DGT94085



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PRINT (OPTION) OR DOWNLOAD OF MAINTENANCE REPORTS ISSUE 3


INTRODUCTION

Printing or downloading of maintenance reports can be performed to provide the maintenance crew with detailed information in case of a problem encountered during the flight. The maintenance report can be:

- printed on the optional cockpit printer,

- downloaded on a PCMCIA memory PC-CARD inserted in the PCMCIA slot 2 of the on-board Data Management Unit (DMU),

- downloaded on the hard drive of a laptop connected to the LAN as a CMC RT.

The most interesting and informative CMC REPORTS are:

- CURRENT LEG FDE / MAINT MSG, which contains:

o all the maintenance messages logged during the current flight leg,

o Flight Deck Effects (FDE), i.e. CAS messages.

NOTE

A new flight leg is initiated at the first engine start following a MAU 2 electrical off/on sequence.

- ACTIVE FDE / MAINT MSG, which contains the maintenance messages and CAS messages still active at the time of the download or print operation. It must be noted that some failures to be fixed by the maintenance technicians might not appear in this report (intermittent failures, failures only detected in specific operating conditions such as engines running, …).

Other available CMC reports are detailed in the Aircraft Maintenance Manual / ATA 45.

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PRINT (OPTION) OR DOWNLOAD OF MAINTENANCE REPORTS DGT94085


PROCEDURE

Printing or downloading of a maintenance report is performed as follows:

- display the CMC maintenance window on a MDU,

- reach the CMC window named CMC REPORTS from the CMC MAIN MENU by selecting MAINTENANCE, then EXTENDED MAINTENANCE, then REPORTS,

- move the cursor in the list of available reports with the CCD knob, to select the report to be printed or downloaded,

- click on the selected report name through the CCD. This opens the list of available devices for printing or downloading:

o COCKPIT PRINTER,

o LOCAL STORAGE: To be selected to download the file on a laptop hard drive. This is only possible when the operation is performed with a laptop connected to the LAN as a CMC RT,

o DMU PCMCIA : To be selected to download the file on a PCMCIA PC-CARD inserted in the DMU slot,

- select one of the above listed devices with the CCD knob,

- launch the print or download operation by clicking on the CCD enter key. When the operation is complete, a completion status will appear at the bottom of the screen.

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FIGURE 02-45-20-00 PRINT OR DOWNLOAD OF MAINTENANCE REPORT

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UPLOAD OF NAVIGATION DATA BASES ISSUE 3


INTRODUCTION

Upload of files and data bases are requested to:

- periodically update navigation and terrain data bases requested for the INAV and FMS EASy functions, and Jeppesen electronic charts (if the option was selected by the operator),

- load a flight plan prepared on an external computer and stored on a CD-ROM or on a PCMCIA memory PC-CARD.

The navigation and terrain data bases and the Jeppesen electronic charts are distributed to the operator by the Integrated Navigation Data Service (INDS) which was developed through an alliance of Honeywell and Jeppesen, to provide state-of-the-art data service for the new EASy cockpit.

These data are provided under the format of CD-ROM:

- INDS CD-ROM #1 (Blue), updated every 14 days, containing Jeppesen e-Charts (if the option was selected by the operator), Obstacles, Geopolitical Information, Airport Information,

- INDS CD-ROM #2 (Red), updated every 28 days, containing Navigation Data and Airspace and Communications Data,

- INDS CD-ROM #3 (Green), updated every 6 to 12 months, containing Terrain Data.

The upload of navigation files and data bases can be performed:

- either from the cockpit by inserting the INDS CD-ROM or the PCMCIA memory PC-CARD containing the flight plan to be uploaded in the DMU drive, and controlling the loading process with the CMC,

- or from a laptop connected to the LAN as a CMC Remote Terminal, by inserting the INDS CD-ROM or the PCMCIA memory PC-CARD containing the flight plan to be uploaded in the corresponding laptop drive.

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UPLOAD OF NAVIGATION DATA BASES DGT94085


PROCEDURE

The upload of data bases from the cockpit is controlled from the CMC as follows:

- power on the avionics system by depressing MINI LOAD MASTER, LH AV MASTER and RH AV MASTER switches, in order to make sure that MAU modules to be loaded are powered,

- insert the appropriate INDS CD-ROM in the corresponding DMU drive,

- display the CMC Maintenance Window on a MDU,

- activate the Data Loading System (DLS) by selecting DATA LOADER in the CMC MAIN MENU,

- click on the FULL LOAD button located on the RH button bar for an automatic loading of the appropriate MAU modules with the files located on the CD-ROM. The list of drives available for the upload operation will appear,

- move the cursor in the list using the CCD knob, and select the appropriate DMU drive (CD-ROM or PCMCIA Slot 2) by clicking on the CCD Enter key. This expands the list of files '_DR' available for upload,

- move the cursor in the list of '_DR' files using the CCD knob, and select the file to be uploaded by clicking on the CCD Enter key (Refer to the INDS CD-ROM installation letter as needed for identification of the '_DR' file to be selected). A text description of the content of the selected '_DR' file will appear at the bottom of the screen,

- click on the SELECT FILE button located on the RH button bar, to initiate the configuration check of the modules to be loaded. During the configuration check, the " xx% complete" indication and a list of errors will be displayed as needed to reflect status of modules checked in the system. On completion of the configuration check, the estimated load time will be displayed, and the START LOAD button will appear on the RH button bar,

- click on the START LOAD button to launch the selected file loading. On Load completion, error codes, if any, will be displayed, along with the indication that the load is 100% complete.

NOTE

Refer to the Aircraft Maintenance Manual – ATA 45 for additional information related to error codes which might be displayed during the last two phases (configuration check and loading).

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ABNORMAL OPERATION ISSUE 3


CAS MESSAGES

CAS MESSAGE DEFINITION

PARKING

ENG 1+2: NO DISPATCH Fault detected by FADEC thus leading to no dispatch

PRESSURE CMPTR FAULT CODE Cabin Pressure Computer (CPC) fault (activated also during taxiing)

APU CMPTR FAULT CODE APU ECU fault

A/I CMPTR MONIT FAULT CODE Fault code from the Bleed Air Supply Computer (BASC) Monitoring

A/I CMPTR CONT FAULT CODE Fault code from the Bleed Air Supply Computer (BASC) Control

FUEL CMPTR FAULT CODE Fault code from the Fuel Quantity Management Computer (FQMC), channel 1 or 2

BRAKE CMPTR 1+2 FAULT CODE Fault code from a Braking and Steering Control Unit (BSCU) 1/2

SERVO ACCU LEFT TEST FAIL Test of flight control servo accumulator LH monitoring failed

SERVO ACCU RIGHT TEST FAIL Test of flight control servo accumulator RH monitoring failed

COND CMPTR FAULT CODE Fault code from the Air Conditioning Computer (ACC), TCS crew, TCS pax or TCS man

ENG 1+2: SHORT DISPATCH Short term dispatch

ENG 1+2: LONG DISPATCH Long term dispatch

MAINT CMPTR FAIL Maintenance computer failed

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ABNORMAL OPERATION DGT94085


CAS MESSAGE DEFINITION

IN-FLIGHT

ENG 1+2: NO DISPATCH Failure detected by FADEC

PRESSURE CMPTR FAULT CODE Cabin Pressure Computer (CPC) fault

APU CMPTR FAULT CODE APU ECU fault

A/I CMPTR MONIT FAULT CODE Fault code from the Bleed Air Supply Computer (BASC) Monitoring

A/I CMPTR CONT FAULT CODE Fault code from the Bleed Air Supply Computer (BASC) Control

FUEL CMPTR FAULT CODE Fault code from the Fuel Quantity Management Computer (FQMC), channel 1 or 2

BRAKE CMPTR 1+2 FAULT CODE Fault code from a Braking and Steering Control Unit (BSCU) 1/2

SERVO ACCU LEFT TEST FAIL Test of flight control servo accumulator LH monitoring failed

SERVO ACCU RIGHT TEST FAIL Test of flight control servo accumulator RH monitoring failed

COND CMPTR FAULT CODE Fault code from the Air Conditioning Computer (ACC), TCS crew, TCS pax or TCS man

Documents

F2000EX EASY 02-45-00 ATA 45 – AIRLANE DIAGNOSTIC AND CODDE 1 PAGE 1 / 2 … · 2012. 6. 27. · cas messages . 02-45-00 f2000ex easy page 2 / 2 codde 1 issue 3 ata 45 – airlane