Download A320 ATA 31 L3 TECHNICAL TRAINING MANUAL PDF

TitleA320 ATA 31 L3 TECHNICAL TRAINING MANUAL
TagsAerospace Engineering Technology
File Size41.4 MB
Total Pages413
Table of Contents
                            INDICATING SYSTEM
	EIS ARCHITECTURE ENHANCED (2)
		EFIS-ECAM
		DMC
		FWC
		SDAC
		INPUTS
	ENGINE/WARNING DISPLAY PRESENTATION (2)
		GENERAL
			EWD INFORMATION
		ADVISORY AND STATUS INDICATION
			ADVISORY INDICATION
			STATUS INDICATION
			ARROW INDICATION
	ECAM ADVISORY & FAILURE RELATED MODES (3)
		ALERT CLASSIFICATION
			GENERAL
	LEVEL 3
		LEVEL 2
		LEVEL 1
		STATUS
		TYPE OF FAILURE
			GENERAL
			INDEPENDANT FAILURE
			PRIMARY FAILURE
			SECONDARY FAILURE
		ADVISORY
			ADVISORY MODE IN NORMAL DUAL DISPLAY
			ADVISORY MODE IN ECAM MONO DISPLAY
	ECAM WARNINGS PRESENTATION (2)
		ECAM DISPLAY WITH AIRCRAFT SYSTEM FAILURE
		CREW CORRECTIVE ACTIONS
			CORRECTIVE ACTIONS
			RESULTS
		CLEARING OF THE WARNINGS
		STATUS REMINDER AND RECALL FUNCTION
	ECAM DESCRIPTION/OPERATION (3)
		GENERAL PRESENTATION
		ECAM SYSTEM
			SDAC
			SDAC DATA PROCESSING
			FWC
			DMC
			ECP INTERFACE
	EFIS DESCRIPTION/OPERATION (3)
		GENERAL
		DMC
		DISPLAY UNIT (ND)
		DISPLAY UNIT (PFD)
	EIS ABNORMAL OPERATION (3)
		EIS ABNORMAL OPERATION
		SINGLE OR MULTIPLE FAILURE
			PFD DU FAILURE
			PFD DU FAILURE (PFD/ND XFR)
			ND DU FAILURE
			ND DU FAILURE (PFD/ND XFR)
			UPPER ECAM DU FAILURE
			UPPER ECAM DU FAILURE (SYSTEM PAGE RECOVERING)
			LOWER ECAM DU FAILURE
			BOTH ECAM DU FAILURE (ECAM ND XFR)
			BOTH ECAM DU FAILURE (SYSTEM PAGE RECOVERING)
			MULTIPLE DU FAILURE (SAME SIDE)
			ECAM CONTROL PANEL FAILURE
			SDAC FAILURE
			FWC FAILURE
			DMC FAILURE
		EXTERNAL SOURCE INFORMATION FAILURES
	DMC ARINC BUS RECONFIGURATION (3)
		GENERAL
		FWC
		SDAC
		DMC OUTPUT BUSES
		WEATHER RADAR
	EIS WARNINGS (3)
		FWC 1+2 FAULT
		FWC 1(2) FAULT
		SDAC 1+2 FAULT
		SDAC 1(2) FAULT
		DMC 1+2 FAULT
		DMC 1(2)+3 FAULT
		DMC 1(2) FAULT
		DMC 3 FAULT
		OPERATING LIMITATIONS
	INDICATING/RECORDING SYSTEM CLASSIC DIFFERENCES
		ELECTRONIC INSTRUMENT SYSTEM
			ECAM (CLASSIC SYSTEM)
		ECAM CONTROL AND INDICATING
	EIS ARCHITECTURE CLASSIC (2)
		EFIS-ECAM
		DMC
		FWC
		SDAC
		INPUTS
	ENGINE/WARNING DISPLAY PRESENTATION CLASSIC (2)
		GENERAL OVERVIEW
		ENGINE/WARNING DISPLAY AREAS
			UPPER AREA
			LEFT MEMO AREA
			RIGHT MEMO AREA
		ADVISORY AND STATUS INDICATION
			ADVISORY INDICATION
			STATUS AND ARROW INDICATION
	ECAM DESCRIPTION/OPERATION CLASSIC (3)
		GENERAL ARCHITECTURE
		SDAC
		FWC
		DMC
		INTERFACE
	EFIS DESCRIPTION/OPERATION CLASSIC (3)
		GENERAL
		DMC
		EFIS CONTROL PANEL
		DISPLAY UNIT
	EIS ABNORMAL OPERATION CLASSIC (3)
		FAILURE OF ONE EFIS DISPLAY UNIT
		FAILURE OF THE ENGINE/WARNING DISPLAY UNIT
		FAILURE OF BOTH ECAM DISPLAY UNITS
		FAILURE OF ONE DMC
		FAILURE OF DMC 1+3
		ECAM CONTROL PANEL FAILURE
		FAILURE OF ONE SDAC
		FAILURE OF SDAC 1+2
		FAILURE OF ONE FWC
		FAILURE OF FWC 1+2
		EXTERNAL SOURCE INFORMATION FAILURES
	DMC ARINC BUS RECONFIGURATION CLASSIC (3)
		GENERAL
		FWC
		SDAC
		DMC OUTPUT BUSES
		WEATHER RADAR
	EIS WARNINGS CLASSIC (3)
		FWC 1+2 FAULT
		FWC 1(2) FAULT
		SDAC 1+2 FAULT
		SDAC 1(2) FAULT
		DMC 1+2 FAULT
		DMC 1(2)+3 FAULT
		DMC 1(2) FAULT
		DMC 3 FAULT
		OPERATING LIMITATIONS
	ELECTRICAL CLOCK D/O (2)
		AIR PRECISION CLOCK
			TEST
			UTC AND DATE
			UTC SETTING
			DATE SETTING
			CHRONOMETER
			ELAPSED TIME
			FAILURE
		SMITH CLOCK
			TEST
			UTC AND DATE
			UTC SETTING
			DATE SETTING
			CHRONOMETER
			ELAPSED TIME
			FAILURE
		SEXTANT CLOCK
			TEST
			UTC AND DATE
			UTC AND DATE SETTING
			CHRONOMETER
			ELAPSED TIME
			FAILURE
	CFDS FAULT PROCESSING (3)
		BITE
		MEMORIZATION
		CFDIU
		CFDS MODES
			NORMAL MODE
			MENU MODE
		REPORTS
			LAST/CURRENT LEG REPORT
			LAST/CURRENT LEG ECAM REPORT
			POST FLIGHT REPORT
		INTERNAL/EXTERNAL FAILURES
		FAILURE GRAVITY
	CFDS AIRCRAFT SYSTEM TYPES (2)
		TYPE 1 SYSTEMS
			SINGLE COMPUTER
			MULTI COMPUTER
			DUPLICATED SYSTEM
			TYPE 2 SYSTEM
			TYPE 3 SYSTEM
	CFDS FAILURE CLASSIFICATION (2)
		CLASS 1
	CLASS 2
		CLASS 3
		SYNTHESIS
	CFDS REPORTS (2)
		GENERAL
		LAST/CURRENT LEG REPORT
		LAST/CURRENT LEG ECAM REPORT
		PREVIOUS LEGS REPORT
		AVIONICS STATUS
		SYSTEM REPORT/TEST
		SYSTEM REPORT/TEST-BSCU A (TYPE 1 SYSTEM)
			LAST LEG REPORT
			PREVIOUS LEGS REPORT
			LRU IDENTIFICATION
			TROUBLE SHOOTING DATA
			CLASS 3 FAULTS
			TEST
			GROUND SCANNING
		SYSTEM REPORT/TEST-AEVC (TYPE 2 SYSTEM)
		SYSTEM REPORT/TEST-GCU EMER (TYPE 3 SYSTEM)
		POST FLIGHT REPORT
		GMT/DATE INIT
		ACARS/PRINT PROGRAM
		PFR FILTER PROGRAM
			FILTER ACTIVATED
			PRINT FILTER CONTENT
	CFDS PHASES (2)
		GROUND/FLIGHT TRANSITION
		IN FLIGHT PHASE
		FLIGHT/GROUND TRANSITION
		ON GROUND PHASE
	CFDIU FUNCTIONS (3)
		MAIN FUNCTIONS
			MEMORY
			MANAGEMENT
			CORRELATION
			MONITORING
			DETECTION
		INTERFACES
			CLOCK
			FAC
			FDIMU
			FWC
			DMC
			ATSU
			EVMU
		ABNORMAL OPERATION
			CLOCK BACKUP
			CFDIU FAILURE
		COCKPIT EFFECT
		PFR
		TROUBLE SHOOTING PROCESS
			[email protected] ENTRY
			ECAM WARNING SELECTION
			CORRELATION
		FAULT ISOLATION PROCEDURE
	POST FLIGHT REPORT FILTERING FUNCTION (3)
		PURPOSE
		FILTER DATA BASE CUSTOMIZATION AND LOADING
		FILTER DATA BASE IDENTIFICATION
		ACTIVATION
		EXAMPLES
	PRINTER PRESENTATION (2)
		GENERAL
		PAPER
		MONITORING
	PRINTER DESCRIPTION/OPERATION (3)
		PRINTER CAPABILITY
		USERS
		MANUAL PRINT
		AUTOMATIC PRINT
	PRINTER SYSTEM INTERFACES (3)
		INPUTS
		OUTPUTS
		MONITORING
	PRINTER PAPER LOADING (2)
		JOB SET-UP
		PROCEDURE
		CLOSE-UP
	COMPUTER REMOVAL AND INSTALLATION (3)
	PUSHBUTTON REMOVAL AND INSTALLATION (3)
	E-LOGBOOK DESCRIPTION (OPTION) (2)
		ELOGBOOK PURPOSE
			ELECTRONIC / PAPER LOGBOOK COMPARISON
			E-LOGBOOK FUNCTIONS
		ELOGBOOK COCKPIT LOCATION AND STOWAGE
		ELECTRONIC AND CABIN LOGBOOK
		E-LOGBOOK - PILOT DEDICATED FUNCTIONS
			FLIGHT DATA REPORTING
		E-LOGBOOK - MAINTENANCE DEDICATED FUNCTIONS
			LOGBOOK DATA STATUS
			SERVICED ITEMS REPORT
			LOGBOOK ENTRIES FUNCTION
			LOGBOOK DEFECT ENTRY
			ACCESS TO MEL
			MAINTENANCE ACTION REPORT
			CERTIFICATE OF RELEASE TO SERVICE
		LOGBOOK DATA LINK CAPABILITIES
		ELOGBOOK SYNCHRONIZATION WITH AIRMAN
			E-LOGBOOK SENT DATA
			E-LOGBOOK RECEIVED DATA
	AIRMAN GATE OPERATION DESCRIPTION (OPTION) (2)
		WHAT IS AIRMAN
		FUNCTIONAL OVERVIEW
		MAINTENANCE PHILOSOPHY
		AIRMAN DATA SOURCES
			AIRMAN LINKS
			DOWNLINK DATA
			AIRLINE DATA
			AIRBUS DATA
		AIRMAN GATE FUNCTION
		REAL TIME FLEET MONITORING
			LAST A/C STATUS
			FLIGHT LIST
		FLIGHT BOXES DESCRIPTION
			FLIGHT BOXES BASIC INFORMATION
			FLIGHT BOXES COLOR CODE INFORMATION
		PFR/LOG FOR AIRCRAFT
			CURRENT / POST FLIGHT REPORT
			LAST LEG REPORT
			DEFECT ADVISOR
			PREVIOUS FLIGHT ITEMS
		LOGBOOK
			LOGBOOK REPORT
			MAINTENANCE ACTION REPORT
			LOGBOOK ENTRIES
RECORDING SYSTEM
	UP & DOWN DATA LOADING SYSTEM PRESENTATION (2)
		GENERAL
		UP LOADING
		DOWN LOADING
	UP & DOWN DATA LOADING SYSTEM UTILIZATION (2)
		GENERAL
		UP LOADING PROCEDURE
		DOWN LOADING PROCEDURE
		ABNORMAL OPERATION
	DFDRS DESCRIPTION/OPERATION (3)
		FDIMU
		DFDR
		QAR
		LINEAR ACCELEROMETER
	DFDRS WARNINGS (3)
		DFDR FAULT
		FDIU FAULT
	FDIMU INTERFACES (3)
		ARINC 429 INPUTS
		ARINC 429 OUTPUTS
		DISCRETE INPUTS
		DISCRETE OUTPUT
		HARVARD BIPHASE OUTPUT
		HARVARD BIPHASE INPUT
		BIPOLAR RETURN TO ZERO OUTPUT
		PCMCIA INTERFACE
		RS 232
	PRINT REPORT STD HEADER DESCRIPTION (3)
		GENERAL
		REPORT VALUE PRESENTATION
		REPORT INFORMATION
		AIRCRAFT AND FLIGHT INFORMATION
		GENERAL DATA
			TRIGGER CONDITION CODE
			BLEED STATUS
	INDIVIDUAL PRINT REPORT DESCRIPTION (3)
		GENERAL
		ENGINE CRUISE REPORT <01>
		CRUISE PERFORMANCE REPORT <02>
		ENGINE TAKE OFF REPORT <04>
			GENERAL
			"T/O DELTA N1 SUMMARY" DATA
		ENGINE REPORT ON REQUEST <05>
		ENGINE GAS PATH ADVISORY REPORT <06>
			GENERAL
			LIMIT EXCEEDANCE SUMMARY
		ENGINE MECHANICAL ADVISORY REPORT <07>
		ENGINE DIVERGENCE REPORT <09>
		ENGINE START REPORT <10>
		ENGINE RUN UP REPORT <11>
		APU MAIN ENGINE START/IDLE REPORT <13>
		APU SHUTDOWN REPORT <14>
		LOAD REPORT <15>
		ENVIRONMENTAL CONTROL SYSTEM REPORT <19>
	AIDS PROGRAMMING (3)
		GENERAL
		GSE
		MCDU PROGRAMMING MENU
			REPORT INHIBIT
			REPORT LIMITS
			REPORT COUNTERS
			STATISTIC COUNTERS
	PRINT REPORT STD HEADER DESCRIPTION (3)
		GENERAL
		FREE PROGRAMMABLE LINES
		REPORT NAME
		AIRCRAFT AND FLIGHT INFORMATION
		GENERAL DATA
			TRIGGER CONDITION CODE
			BLEED STATUS
	INDIVIDUAL PRINT REPORT DESCRIPTION (3)
		GENERAL
		ENGINE CRUISE REPORT <01>
		CRUISE PERFORMANCE REPORT <02>
		ENGINE TAKE OFF REPORT <04>
		ENGINE ON REQUEST REPORT <05>
		ENGINE GAS PATH ADVISORY REPORT <06>
		ENGINE MECHANICAL ADVISORY REPORT <07>
		ENGINE DIVERGENCE REPORT <09>
		ENGINE START REPORT <10>
		ENGINE RUN UP REPORT <11>
		APU MES/IDLE REPORT <13>
		APU SHUTDOWN REPORT <14>
		LOAD REPORT <15>
		FREE PROGRAMMABLE REPORTS <16,17 AND 18>
		ECS REPORT <19>
	AIDS INTERFACES (3)
		GENERAL INTERFACES
		DAR INTERFACE
		FDIU INTERFACE
		SYSTEM INTERFACE
		PARAMETER CALL-UP
                        
Document Text Contents
Page 1

AIRBUS A318/319/320/321

CFM 56 / Level 3
Austrian Technical Training

School Notes - For Training Purposes Only







INDICATING/RECORDING



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Page 2

AIRBUS A318/319/320/321

CFM 56 / Level 3
Austrian Technical Training

School Notes - For Training Purposes Only







TTHHIISS PPAAGGEE IINNTTEENNTTIIOONNAALLLLYY LLEEFFTT BBLLAANNKK



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Page 206

AIRBUS A318/319/320/321

CFM 56 / Level 3
Austrian Technical Training

School Notes - For Training Purposes Only







CFDIU FUNCTIONS (3)

MAIN FUNCTIONS

MEMORY
The Centralized Fault Display Interface Unit (CFDIU) stores the failure
messages and the Electronic Centralized Aircraft Monitoring (ECAM)
warning messages in a Non Volatile Memory (NVM).

MANAGEMENT
The CFDIU manages failure information and adds data such as
Universal Time Coordinated (UTC), DATE, ATA chapter, LEG, FLIGHT
PHASE to elaborate reports.

CORRELATION
If a computer internal failure is detected, the CFDIU achieves a
correlation function that means it isolates or ignores the malfunctions
of systems relating to this failure. Example: ADC FAILURE causes NO
DATA FROM ADC in other computers. The Centralized Fault Display
System (CFDS) will present only the initial failure in the last leg report.
The function IDENT will then present the systems affected by this
failure.

MONITORING
The CFDIU scans permanently all input buses in order to detect a
transmitted failure message. The CFDIU detects intermittent operation
of the systems and adds INTM to the failure message.

DETECTION
The CFDIU can detect the nature of the failure by reading the ARINC
words. Nature of failures:

internal (i.e. SDAC FAULT)

external (i.e. FWC 1: NO DATA FROM ADIRU1)

intermittent; (INTM) added

class 3; (CLASS 3) added.

INTERFACES

CLOCK
The CFDIU permanently receives the UTC and the date from the
aircraft clock and then sends these two parameters to all type 1
systems. The UTC and date are used by the system Built-in Test
Equipments (BITEs) as well as the CFDIU for the various maintenance
reports.

FAC
The CFDIU receives the flight number and city pair from the Flight
Augmentation Computer (FAC). The city pair (FROM/TO airport) is sent
to the Air Traffic Service Unit (ATSU) and to the Data Management
Unit (DMU)-part of the Flight Data Interface and Management Unit
(FDIMU). The CFDIU counts the number (maximum 8) of identical and
consecutive ECAM warning messages and records in the LAST LEG
ECAM REPORT.



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AIRBUS A318/319/320/321

CFM 56 / Level 3
Austrian Technical Training

School Notes - For Training Purposes Only









MMAAIINN FFUUNNCCTTIIOONNSS ...... AABBNNOORRMMAALL OOPPEERRAATTIIOONN



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Page 412

AIRBUS A318/319/320/321

CFM 56 / Level 3
Austrian Technical Training

School Notes - For Training Purposes Only







SYSTEM INTERFACE
The FDIMU (DMU-part) receives approximately 13.000 parameters
from various A/C systems through ARINC 429 data lines. These
parameters can be recorded by the DAR.

NNOOTTEE:: IINN AADDDDIITTIIOONN,, SSPPAARREESS IINNPPUUTTSS AARREE PPRROOVVIIDDEEDD..
AAMMOONNGG TTHHEESSEE AARRIINNCC 442299 IINNPPUUTTSS DDAATTAA LLIINNEESS,, SSOOMMEE OOFF
TTHHEEMM AARREE SSEELLEECCTTAABBLLEE FFOORR HHIIGGHH OORR LLOOWW SSPPEEEEDD FFRROOMM
SSYYSSTTEEMM CCOOMMPPUUTTEERRSS..

PARAMETER CALL-UP
Parameters transmitted on the connected data buses can be shown on
the MCDU in binary code with the label call-up function. At FDIMU
delivery, 200 parameters are already defined with alpha call-up code
and can be shown on the MCDU in engineering units. Approximately
1.500 parameters can be added to the initial alpha call-up list by
programming.



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AIRBUS A318/319/320/321

CFM 56 / Level 3
Austrian Technical Training

School Notes - For Training Purposes Only









SSYYSSTTEEMM IINNTTEERRFFAACCEE && PPAARRAAMMEETTEERR CCAALLLL--UUPP



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