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Description

TRAINING MANUAL CFM56-5B

FAULT DETECTION & ANNUNCIATION NOVEMBER 2002 CTC-232 Level 3

CFM56-5B

TRAINING MANUAL

FAULT DETECTION & ANNUNCIATION

Published by CFMI CFMI Customer Training Center Snecma Services

1936 77019

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

CFMI Customer Training Services GE Aircraft Engines Customer Technical Education Center 123 Merchant Street Mail Drop Y2 Cincinnati,

Ohio 45246 USA

GENERAL

Page 1 Nov 02

CFM56-5B

TRAINING MANUAL

THIS PAGE INTENTIONALLY LEFT BLANK

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

GENERAL

Page 2 Nov 02

CFM56-5B

TRAINING MANUAL

This CFMI publication is for Training Purposes Only

The information is accurate at the time of compilation

no update service will be furnished to maintain accuracy

For authorized maintenance practices and specifications,

consult pertinent maintenance publications

The information (including technical data) contained in this document is the property of CFM International (GE and SNECMA)

It is disclosed in confidence,

and the technical data therein is exported under a U

Government license

Therefore,

None of the information may be disclosed to other than the recipient

In addition,

the technical data therein and the direct product of those data,

re-exported or disclosed in any manner not provided for by the license without prior written approval of both the U

Government and CFM International

COPYRIGHT 1998 CFM INTERNATIONAL

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

GENERAL

Page 3 Nov 02

CFM56-5B

TRAINING MANUAL

THIS PAGE INTENTIONALLY LEFT BLANK

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

GENERAL

Page 4 Nov 02

CFM56-5B

TRAINING MANUAL

TABLE OF CONTENTS

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

CONTENTS FAULT DETECTION & ANNUNCIATION

Page 1 Nov 02

CFM56-5B

EFG Chapter

Table of Contents

1 to 10

Architecture

1 to 10

Interfaces

1 to 10

ECU Signals

Fault Detection

Warning Indications

1 to 28

Message Interrogation

CFDS Message Interrogation

1 to 46

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

TRAINING MANUAL

CONTENTS FAULT DETECTION & ANNUNCIATION

Page 2 Nov 02

CFM56-5B

TRAINING MANUAL

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

Page 1 Nov 02

CFM56-5B

A A/C AC ACARS ACMS ACS ADC ADEPT ADIRS ADIRU AGB AIDS ALF ALT ALTN AMB AMM AOG A/P APU ARINC ASM A/T ATA

AIRCRAFT ALTERNATING CURRENT AIRCRAFT COMMUNICATION ADRESSING and REPORTING SYSTEM AIRCRAFT CONDITION MONITORING SYSTEM AIRCRAFT CONTROL SYSTEM AIR DATA COMPUTER AIRLINE DATA ENGINE PERFORMANCE TREND AIR DATA AND INERTIAL REFERENCE SYSTEM AIR DATA AND INERTIAL REFERENCE UNIT ACCESSORY GEARBOX AIRCRAFT INTEGRATED DATA SYSTEM AFT LOOKING FORWARD ALTITUDE ALTERNATE AMBIENT AIRCRAFT MAINTENANCE MANUAL AIRCRAFT ON GROUND AIR PLANE AUXILIARY POWER UNIT AERONAUTICAL RADIO,

(SPECIFICATION) AUTOTHROTTLE SERVO MECHANISM AUTOTHROTTLE AIR TRANSPORT ASSOCIATION

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-320-321 CFMI PROPRIETARY INFORMATION

TRAINING MANUAL

ATC ATHR ATO AVM

AUTOTHROTTLE COMPUTER AUTO THRUST ABORTED TAKE OFF AIRCRAFT VIBRATION MONITORING

B BITE BMC BPRV BSI BSV BSV BVCS

BUILT IN TEST EQUIPMENT BLEED MANAGEMENT COMPUTER BLEED PRESSURE REGULATING VALVE BORESCOPE INSPECTION BURNER STAGING VALVE (SAC) BURNER SELECTION VALVE (DAC) BLEED VALVE CONTROL SOLENOID

C C CAS CBP CCDL CCFG CCU CCW CDP CDS CDU CFDIU CFDS

CELSIUS or CENTIGRADE CALIBRATED AIR SPEED (HP) COMPRESSOR BLEED PRESSURE CROSS CHANNEL DATA LINK COMPACT CONSTANT FREQUENCY GENERATOR COMPUTER CONTROL UNIT COUNTER CLOCKWISE (HP) COMPRESSOR DISCHARGE PRESSURE COMMON DISPLAY SYSTEM CONTROL DISPLAY UNIT CENTRALIZED FAULT DISPLAY INTERFACE UNIT CENTRALIZED FAULT DISPLAY SYSTEM

Page 2 Nov 02

CFM56-5B

JOINT GE/SNECMA COMPANY (CFM INTERNATIONAL) CENTER OF GRAVITY channel A channel B CHANNEL ACTIVE COMPRESSOR INLET PRESSURE COMPRESSOR INLET TEMPERATURE CENTIMETER X GRAMS CENTRALIZED MAINTENANCE COMPUTER COMPONENT MAINTENANCE MANUAL CENTRALIZED MAINTENANCE SYSTEM CENTRAL MAINTENANCE SYSTEM HIGH TEMPERATURE COATING CONTINUOUS CENTRAL PROCESSING UNIT CATHODE RAY TUBE CONSTANT SPEED DRIVE CYCLES SINCE INSTALLATION CYCLES SINCE NEW COWL THERMAL ANTI-ICING CUSTOMER TECHNICAL EDUCATION CENTER CONTROL COPPER

INDIUM CLOCKWISE

DOUBLE ANNULAR COMBUSTOR

CG Ch A Ch B CHATV CIP(HP) CIT(HP) cm

g CMC CMM CMS CMS CODEP CONT CPU CRT CSD CSI CSN CTAI CTEC

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

DAMV DAR DC DCU DCV DEU DFCS DFDAU DFDRS DISC DIU DMC DMD DMS DMU DOD DPU DRT E EAU EBU ECA ECAM ECS ECU EE EEC

TRAINING MANUAL DOUBLE ANNULAR MODULATED VALVE DIGITAL ACMS RECORDER DIRECT CURRENT DATA CONVERSION UNIT DIRECTIONAL CONTROL VALVE BOEING DISPLAY ELECTRONIC UNIT DIGITAL FLIGHT CONTROL SYSTEM DIGITAL FLIGHT DATA ACQUISITION UNIT DIGITAL FLIGHT DATA RECORDING SYSTEM DISCRETE DIGITAL INTERFACE UNIT DISPLAY MANAGEMENT COMPUTER DEMAND DEBRIS MONITORING SYSTEM DATA MANAGEMENT UNIT DOMESTIC OBJECT DAMAGE DIGITAL PROCESSING MODULE DE-RATED TAKE-OFF ENGINE ACCESSORY UNIT ENGINE BUILDUP UNIT ELECTRICAL CHASSIS ASSEMBLY ELECTRONIC CENTRALIZED AIRCRAFT MONITORING ENVIRONMENTAL CONTROL SYSTEM ELECTRONIC CONTROL UNIT ELECTRONIC EQUIPMENT ELECTRONIC ENGINE CONTROL

Page 3 Nov 02

CFM56-5B

EFH EFIS

ENGINE FLIGHT HOURS ELECTRONIC FLIGHT INSTRUMENT SYSTEM EGT EXHAUST GAS TEMPERATURE EHSV ELECTRO-HYDRAULIC SERVO VALVE EICAS ENGINE INDICATING AND CREW ALERTING SYSTEM EIS ELECTRONIC INSTRUMENT SYSTEM EIU ENGINE INTERFACE UNIT EIVMU ENGINE INTERFACE AND VIBRATION MONITORING UNIT EMF ELECTROMOTIVE FORCE EMI ELECTRO MAGNETIC INTERFERENCE EMU ENGINE MAINTENANCE UNIT EPROM ERASABLE PROGRAMMABLE READ ONLY MEMORY (E)EPROM (ELECTRICALLY) ERASABLE PROGRAMMABLE READ ONLY MEMORY ESN ENGINE SERIAL NUMBER ETOPS EXTENDED TWIN OPERATION SYSTEMS EWD/SD ENGINE WARNING DISPLAY / SYSTEM DISPLAY F F FAA FADEC FAR FCC

FARENHEIT FEDERAL AVIATION AGENCY FULL AUTHORITY DIGITAL ENGINE CONTROL FUEL/AIR RATIO FLIGHT CONTROL COMPUTER

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-320-321 CFMI PROPRIETARY INFORMATION

FCU FDAMS FDIU FDRS FDU FEIM FF FFCCV FI FIM FIN FIT FLA FLX TO FMC FMCS FMGC FMGEC FMS FMV FOD FPA FPI FQIS

TRAINING MANUAL FLIGHT CONTROL UNIT FLIGHT DATA ACQUISITION & MANAGEMENT SYSTEM FLIGHT DATA INTERFACE UNIT FLIGHT DATA RECORDING SYSTEM FIRE DETECTION UNIT FIELD ENGINEERING INVESTIGATION MEMO FUEL FLOW (see Wf)

Page 4 Nov 02

CFM56-5B

FRV FWC FWD

FUEL RETURN VALVE FAULT WARNING COMPUTER FORWARD

in GE GEAE GEM GI GMM GMT GND GPH GPU GSE

GRAM X INCHES GENERAL ELECTRIC GENERAL ELECTRIC AIRCRAFT ENGINES GROUND-BASED ENGINE MONITORING GROUND IDLE (G/I) GROUND MAINTENANCE MODE GREENWICH MEAN TIME GROUND GALLON PER HOUR GROUND POWER UNIT GROUND SUPPORT EQUIPMENT

H HCF HCU HDS HMU HP HPC HPCR HPRV HPSOV HPT HPT(A)CC

HIGH CYCLE FATIGUE HYDRAULIC CONTROL UNIT HORIZONTAL DRIVE SHAFT HYDROMECHANICAL UNIT HIGH PRESSURE HIGH PRESSURE COMPRESSOR HIGH PRESSURE COMPRESSOR ROTOR HIGH PRESSURE REGULATING VALVE HIGH PRESSURE SHUT-OFF VALVE HIGH PRESSURE TURBINE HIGH PRESSURE TURBINE (ACTIVE) CLEARANCE CONTROL

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

TRAINING MANUAL

HPTC HIGH PRESSURE TURBINE CLEARANCE HPTCCV HIGH PRESSURE TURBINE CLEARANCE CONTROL VALVE HPTN HIGH PRESSURE TURBINE NOZZLE HPTR HIGH PRESSURE TURBINE ROTOR Hz HERTZ (CYCLES PER SECOND) I I/O IAS ID ID PLUG IDG IFSD IGB IGN IGV in

IOM IPB IPC IPCV IPS IR

INPUT/OUTPUT INDICATED AIR SPEED INSIDE DIAMETER IDENTIFICATION PLUG INTEGRATED DRIVE GENERATOR IN FLIGHT SHUT DOWN INLET GEARBOX IGNITION INLET GUIDE VANE INCH INPUT OUTPUT MODULE ILLUSTRATED PARTS BREAKDOWN ILLUSTRATED PARTS CATALOG INTERMEDIATE PRESSURE CHECK VALVE INCHES PER SECOND INFRA RED

K °K k KIAS kV

KELVIN X 1000 INDICATED AIR SPEED IN KNOTS KILOVOLTS

Page 5 Nov 02

CFM56-5B KILOGRAMS PER HOUR

L L'L/H lbs

LCD LCF LE (L/E) LGCIU

LEFT LEFT HAND POUNDS,

WEIGHT LIQUID CRYSTAL DISPLAY LOW CYCLE FATIGUE LEADING EDGE LANDING GEAR CONTROL INTERFACE UNIT LP LOW PRESSURE LPC LOW PRESSURE COMPRESSOR LPT LOW PRESSURE TURBINE LPT(A)CC LOW PRESSURE TURBINE (ACTIVE) CLEARANCE CONTROL LPTC LOW PRESSURE TURBINE CLEARANCE LPTN LOW PRESSURE TURBINE NOZZLE LPTR LOW PRESSURE TURBINE ROTOR LRU LINE REPLACEABLE UNIT LVDT LINEAR VARIABLE DIFFERENTIAL TRANSFORMER M mA MCD MCDU MCL MCR

MILLIAMPERES (CURRENT) MAGNETIC CHIP DETECTOR MULTIPURPOSE CONTROL AND DISPLAY UNIT MAXIMUM CLIMB MAXIMUM CRUISE

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-320-321 CFMI PROPRIETARY INFORMATION

MCT MDDU MEC milsD

MMEL MO MPA MPH MTBF MTBR mV Mvdc

TRAINING MANUAL MAXIMUM CONTINUOUS MULTIPURPOSE DISK DRIVE UNIT MAIN ENGINE CONTROL Mils DOUBLE AMPLITUDE MILLIMETERS MAIN MINIMUM EQUIPMENT LIST AIRCRAFT SPEED MACH NUMBER MAXIMUM POWER ASSURANCE MILES PER HOUR MEAN TIME BETWEEN FAILURES MEAN TIME BETWEEN REMOVALS MILLIVOLTS MILLIVOLTS DIRECT CURRENT

N N1 (NL)

LOW PRESSURE ROTOR ROTATIONAL SPEED N1* DESIRED N1 N1ACT ACTUAL N1 N1CMD COMMANDED N1 N1DMD DEMANDED N1 N1K CORRECTED FAN SPEED N1TARGET TARGETED FAN SPEED N2 (NH) HIGH PRESSURE ROTOR ROTATIONAL SPEED N2* DESIRED N2 N2ACT ACTUAL N2 N2K CORRECTED CORE SPEED N/C NORMALLY CLOSED N/O NORMALLY OPEN

Page 6 Nov 02

CFM56-5B

NAC NVM

NACELLE NON VOLATILE MEMORY

O OAT OD OGV OSG OVBD OVHT

OUTSIDE AIR TEMPERATURE OUTLET DIAMETER OUTLET GUIDE VANE OVERSPEED GOVERNOR OVERBOARD OVERHEAT

P Pb Pc Pcr Pf P/T25 P/N P0 P25 PCU PLA PMC PMUX PPH PRSOV Ps PS12

BYPASS PRESSURE REGULATED SERVO PRESSURE CASE REGULATED PRESSURE HEATED SERVO PRESSURE HP COMPRESSOR INLET TOTAL AIR PRESSURE/TEMPERATURE PART NUMBER AMBIENT STATIC PRESSURE HP COMPRESSOR INLET TOTAL AIR TEMPERATURE PRESSURE CONVERTER UNIT POWER LEVER ANGLE POWER MANAGEMENT CONTROL PROPULSION MULTIPLEXER POUNDS PER HOUR PRESSURE REGULATING SERVO VALVE PUMP SUPPLY PRESSURE FAN INLET STATIC AIR PRESSURE

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

PS13 PS3HP

TRAINING MANUAL

FAN OUTLET STATIC AIR PRESSURE COMPRESSOR DISCHARGE STATIC AIR PRESSURE (CDP) POUNDS PER SQUARE INCH POUNDS PER SQUARE INCH ABSOLUTE POUNDS PER SQUARE INCH DIFFERENTIAL POUNDS PER SQUARE INCH GAGE POWER SUPPLY MODULE (ECU) PRESSURE SUB-SYSTEM POWER SUPPLY UNIT TOTAL PRESSURE FAN INLET TOTAL AIR PRESSURE (PRIMARY FLOW) HPC TOTAL INLET PRESSURE

Q QAD QEC QTY QWR

QUICK ATTACH DETACH QUICK ENGINE CHANGE QUANTITY QUICK WINDMILL RELIGHT

PSI PSIA PSID psig PSM PSS PSU PT PT2

R R/H RAC/SB RACC RAM RCC RDS

RIGHT HAND ROTOR ACTIVE CLEARANCE/START BLEED ROTOR ACTIVE CLEARANCE CONTROL RANDOM ACCESS MEMORY REMOTE CHARGE CONVERTER RADIAL DRIVE SHAFT

Page 7 Nov 02

RPM RTD RTO RTV

RVDT S S/N S/R S/V SAC SAR SAV SB SCU SDAC SDI SDU SER SFC SFCC SG SLS SLSD

CFM56-5B REVOLUTIONS PER MINUTE RESISTIVE THERMAL DEVICE REFUSED TAKE OFF ROOM TEMPERATURE VULCANIZING (MATERIAL) ROTARY VARIABLE DIFFERENTIAL TRANSFORMER SERIAL NUMBER SERVICE REQUEST SHOP VISIT SINGLE ANNULAR COMBUSTOR SMART ACMS RECORDER STARTER AIR VALVE SERVICE BULLETIN SIGNAL CONDITIONING UNIT SYSTEM DATA ACQUISITION CONCENTRATOR SOURCE/DESTINATION IDENTIFIER (BITS) (CF ARINC SPEC) SOLENOID DRIVER UNIT SERVICE EVALUATION REQUEST SPECIFIC FUEL CONSUMPTION SLAT FLAP CONTROL COMPUTER SPECIFIC GRAVITY SEA LEVEL STANDARD (CONDITIONS : 29

Hg / 59°F) SEA LEVEL STANDARD DAY (CONDITIONS : 29

Hg / 59°F)

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-320-321 CFMI PROPRIETARY INFORMATION

SMM SMP SN SNECMA SOL SOV STP SVR SW SYS T T oil T/C T/E T/O T/R T12 T25 T3 T49

TRAINING MANUAL STATUS MATRIX SOFTWARE MANAGEMENT PLAN SERIAL NUMBER SOCIETE NATIONALE D’ETUDE ET DE CONSTRUCTION DE MOTEURS D’AVIATION SOLENOID SHUT-OFF VALVE STANDARD TEMPERATURE AND PRESSURE SHOP VISIT RATE SWITCH BOEING SYSTEM OIL TEMPERATURE THERMOCOUPLE TRAILING EDGE TAKE OFF THRUST REVERSER FAN INLET TOTAL AIR TEMPERATURE HP COMPRESSOR INLET AIR TEMPERATURE HP COMPRESSOR DISCHARGE AIR TEMPERATURE EXHAUST GAS TEMPERATURE LOW PRESSURE TURBINE DISCHARGE TOTAL AIR TEMPERATURE THERMAL ANTI ICE TOTAL AIR TEMPERATURE

Page 8 Nov 02

CFM56-5B

TBC THERMAL BARRIER COATING TBD TO BE DETERMINED TBO TIME BETWEEN OVERHAUL TBV TRANSIENT BLEED VALVE TC(TCase) HP TURBINE CASE TEMPERATURE TCC TURBINE CLEARANCE CONTROL TCCV TURBINE CLEARANCE CONTROL VALVE TCJ TEMPERATURE COLD JUNCTION T/E TRAILING EDGE TECU ELECTRONIC CONTROL UNIT INTERNAL TEMPERATURE TEO ENGINE OIL TEMPERATURE TGB TRANSFER GEARBOX Ti TITANIUM TLA THROTTLE LEVER ANGLE AIRBUS TLA THRUST LEVER ANGLE BOEING TM TORQUE MOTOR TMC TORQUE MOTOR CURRENT T/O TAKE OFF TO/GA TAKE OFF/GO AROUND T/P TEMPERATURE/PRESSURE SENSOR TPU TRANSIENT PROTECTION UNIT TR TRANSFORMER RECTIFIER TRA THROTTLE RESOLVER ANGLE AIRBUS TRA THRUST RESOLVER ANGLE BOEING TRDV THRUST REVERSER DIRECTIONAL VALVE TRF TURBINE REAR FRAME TRPV THRUST REVERSER PRESSURIZING VALVE TSI TIME SINCE INSTALLATION (HOURS) EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

TRAINING MANUAL

TSN TTL

TIME SINCE NEW (HOURS) TRANSISTOR TRANSISTOR LOGIC

U UER UTC

UNSCHEDULED ENGINE REMOVAL UNIVERSAL TIME CONSTANT

V VAC VBV VDC VDT VIB VLV VRT VSV

VOLTAGE,

ALTERNATING CURRENT VARIABLE BLEED VALVE VOLTAGE,

DIRECT CURRENT VARIABLE DIFFERENTIAL TRANSFORMER VIBRATION VALVE VARIABLE RESISTANCE TRANSDUCER VARIABLE STATOR VANE

W WDM Wf WFM WOW WTAI

WATCHDOG MONITOR WEIGHT OF FUEL OR FUEL FLOW WEIGHT OF FUEL METERED WEIGHT ON WHEELS WING THERMAL ANTI-ICING

Page 9 Nov 02

CFM56-5B

IMPERIAL / METRIC CONVERSIONS

METRIC / IMPERIAL CONVERSIONS

3937 in

37 mils

1 USG 1 cu

39 cm³

205 lbs

890 kPa

- 32 ) /1

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-320-321 CFMI PROPRIETARY INFORMATION

TRAINING MANUAL

Page 10 Nov 02

CFM56-5B

TRAINING MANUAL

ARCHITECTURE

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

ARCHITECTURE FAULT DETECTION & ANNUNCIATION

Page 1 Nov 02

CFM56-5B

TRAINING MANUAL

ENGINE CONTROL SYSTEM System components

Electronic Control Unit (ECU)

The CFM56-5B engine incorporates a computer-based Full Authority Digital Engine Control (FADEC) system

The ECU is the prime component of the engine control system

The engine control system is composed of the following elements :

containing two identical computers,

which converts electrical signals from the ECU into hydraulic pressures to drive the engine’s valves and actuators

The ECU governs the engine in response to thrust command inputs from the airplane and provides information to the airplane for flight compartment indication,

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

Control system maintenance is assisted by extensive ECU internal software called Built-In-Test-Equipment (BITE),

which monitors engine data and ECU status flags to detect engine failures

ARCHITECTURE FAULT DETECTION & ANNUNCIATION

Page 2 Nov 02

CFM56-5B

TRAINING MANUAL

CONTROL SIGNALS T12

ANALOG DISCRETE SIGNALS

FEEDBACK SIGNALS 115V 400Hz

ARINC DATABUSES

IGNITION

REVERSER SOLENOIDS + SWITCHES

VBV VSV TBV

BSV HPT LPT CCV CCV

FUEL HYDROMECHANICAL UNIT

ALTERNATOR

FUEL FLOW

STARTER AIR VALVE STARTER

FADEC COMPONENTS

CTC-232-001-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

ARCHITECTURE FAULT DETECTION & ANNUNCIATION

Page 3 Nov 02

CFM56-5B

TRAINING MANUAL

ECU INPUTS AND OUTPUTS

Electrical interfaces

The following chart is a summary of the ECU electrical interfaces to show which connectors interface with channel A and which interface with channel B

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

ARCHITECTURE FAULT DETECTION & ANNUNCIATION

Page 4 Nov 02

CFM56-5B

5J J1 J J3

J 11 J9

J6 J8 5 1 J

CHANNEL A CONNECTOR (ODD)

CHANNEL B CONNECTOR (EVEN)

FUNCTION

J1 J3 J5 J7 J9 J11 SHARED J13 J15

J2 J4 J6 J8 J10 J12 J14 SHARED SHARED

A/C POWER (28V) AND IGNITER POWER (115V) A/C INPUT/OUTPUT AND TLA THRUST REVERSER SOLENOIDS,

TORQUE MOTORS,

RESOLVERS,

N2 ALTERNATOR,

N1 AND T12 LVDT'S,

RVDT'S,

BSV POSITION SWITCH ENGINE IDENTIFICATION PLUG WF METER,

THERMOCOUPLES TEST INTERFACE

ELECTRICAL CONNECTORS

CTC-232-002-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

TRAINING MANUAL

CFMI PROPRIETARY INFORMATION

ARCHITECTURE FAULT DETECTION & ANNUNCIATION

Page 5 Nov 02

CFM56-5B

TRAINING MANUAL

ENGINE TESTS ECU initialization

Built-In-Tests

If the engine is not running,

the ECU becomes fully operational within a maximum of three seconds after application of airplane power,

Built-In-Test-Equipment (BITE) monitors the system and memorizes failures

If the core speed is greater than 10% N2,

the ECU performs a short initialization and is fully functional in less than 750ms after application of airplane power

Each ECU channel performs a reset initialization sequence in response to aircraft-generated resets,

An aircraft-commanded reset occurs when the master lever is toggled from ON to OFF

During reset initialization,

all RAM variables are initialized,

except for a special reserved area

This area of RAM is not initialized as it is allocated to parameters critical to engine operation and which must maintain their values prior to the reset operation

The BITE detects and isolates failures,

in order to determine the health status of the channels and to transmit maintenance data to the aircraft

There are two types of Built-In-Test : Initialization test and Periodic test

The Initialization tests cover functions which cannot be continually tested without disturbing the ECU system operation

The typical tasks of an Initialization test are processor test,

memories test and output driver disconnect tests

The Periodic tests cover functions which can be continually tested

These tests are similar to the Initialization tests,

but are run in background as time permits

Specific tests are available to verify certain engine functions

These tests are the FADEC test (Non-motoring & motoring),

ignition test and thrust reverser test

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

ARCHITECTURE FAULT DETECTION & ANNUNCIATION

Page 6 Nov 02

CFM56-5B

TRAINING MANUAL

POWER UP

POWER UP TEST

OPERATIONAL FUNCTION

BUILT-IN TESTS PERMANENT MONITORING

ENGINE RUN

SPECIFIC TESTS

FADEC TEST THRUST REVERSER TEST IGNITION TEST

CTC-232-003-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

ARCHITECTURE FAULT DETECTION & ANNUNCIATION

Page 7 Nov 02

CFM56-5B

TRAINING MANUAL

ENGINE CONTROL SYSTEM Electronic Control Unit (ECU)

Channel selection and fault strategy

The ECU has two channels,

A and B,

and both channels are capable of controlling the engine

Active and Standby channel selection is performed at ECU power-up and during operation

The two channels are identical and permanently operational,

but they operate independently from each other

Each channel has a full complement of sensors,

interfaces to the engine and aircraft,

central processor and output drivers

Active and Standby selection is based upon the health of the channels and each channel determines its own health status

The healthiest is selected as the Active channel

As well as continuously checking and processing their own inputs,

the channels compare each others data over a Cross Channel Data Link (CCDL),

to ensure that there are no anomalies

When both channels have an equal health status,

active/ standby channel selection alternates with every engine start,

if N2 was greater than 11,000 RPM during the last run

The two ECU channels operate their output drivers on an active/standby principle

Both channels always receive inputs and process them,

but only the channel in control,

delivers control outputs (solenoids/torque motors)

The other is called the Standby channel

The purpose of the dual-redundant architecture is to minimize the effects of control system faults on the engine operation

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

ARCHITECTURE FAULT DETECTION & ANNUNCIATION

Page 8 Nov 02

CFM56-5B

TRAINING MANUAL

ECU INPUTS

CHANNEL A

CHANNEL B

ECU DESIGN

CTC-232-004-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

STAND BY

CFMI PROPRIETARY INFORMATION

ARCHITECTURE FAULT DETECTION & ANNUNCIATION

Page 9 Nov 02

CFM56-5B

TRAINING MANUAL

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ARCHITECTURE FAULT DETECTION & ANNUNCIATION

Page 10 Nov 02

CFM56-5B

TRAINING MANUAL

INTERFACES

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

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Page 1 Nov 02

CFM56-5B

TRAINING MANUAL

FADEC INTERFACES There are many aircraft computers and systems that interface directly,

or indirectly with the engine FADEC system

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

INTERFACES FAULT DETECTION & ANNUNCIATION

Page 2 Nov 02

CFM56-5B

TRAINING MANUAL

ENGINE INTERFACE UNIT (EIU) AIR DATA & INERTIAL REFERENCE SYSTEM (ADIRS) FLIGHT MANAGEMENT & GUIDANCE COMPUTER (FMGC) FLIGHT CONTROL UNIT (FCU) DIGITAL FLIGHT DATA RECORDING SYSTEM (DFDRS) CENTRALIZED FAULT DISPLAY INTERFACE UNIT (CFDIU) ENGINE VIBRATION MONITORING UNIT (EVMU) DATA MANAGEMENT UNIT (DMU) ELECTRONIC CENTRALIZED MONITORING SYSTEM (ECAM) MULTIPURPOSE CONTROL & DISPLAY UNIT (MCDU) SYSTEM DATA ACQUISITION CONCENTRATOR (SDAC) FADEC SYSTEM

FLIGHT WARNING COMPUTER (FWC) DISPLAY MANAGEMENT COMPUTER (DMC) SLAT FLAP CONTROL COMPUTER (SFCC) LANDING GEAR CONTROL INTERFACE UNIT (LGCIU) ENVIRONMENTAL CONTROL SYSTEM (ECS)

AIRCRAFT

CTC-232-005-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

INTERFACES FAULT DETECTION & ANNUNCIATION

Page 3 Nov 02

CFM56-5B

TRAINING MANUAL

FADEC INTERFACES Each ECU interfaces with the aircraft systems,

Each EIU is an interface concentrator,

which collects information to be used by the ECU from various aircraft systems and also sends information from the engines to the aircraft systems

The EVMU receives analog signals from the engine speed and vibration sensors for vibration monitoring and recording

The ECU entirely supervises the thrust reverser operation

In case of malfunction,

the reverser doors are commanded stowed (LGCIU,

The ADIRS sends air data parameters to the ECU for power management and engine control

The ECU manages power according to 2 thrust modes :

depending on Throttle Lever Angle

according to the autothrust function generated by the Auto-Flight System (AFS)

The FMGC computes the autothrust order and sends it to the ECU,

The FCU is the interface for transmission of engine data from the FMGC to the EIU

Thrust limit computation is performed by the ECU,

except if the alpha floor protection is activated

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

The ECU provides idle mode selection :

when flaps are extended (SFCC),

or landing gear is down (LGCIU)

modulated up to approach idle,

depending on oil temperature (IDG cooling),

air conditioning and anti-ice demand (zone & pack controller)

Primary parameters (N1,

Fuel Flow) are sent by the ECU directly to the ECAM,

Secondary parameters are sent to the ECAM,

through different aircraft computers (EIU,

The DFDRS includes a Flight Data Interface Unit (FDIU) and a Flight Data Recorder (FDR)

The FDIU collects various engine and A/C system parameters and processes them internally

The FDR stores data collected over the last 25 hours

The DMU collects,

stores and processes various A/C system data and generates condition reports

The CFDIU memorizes warnings generated by the FWC and failure information produced by the BITE function integrated in the computers

Maintenance personnel can read out BITE memory information,

INTERFACES FAULT DETECTION & ANNUNCIATION

Page 4 Nov 02

CFM56-5B

TRAINING MANUAL

CONTROL / MONITOR SENSORS

PACK CONTROLLER COCKPIT SWITCHES

LGCIU SFCC

FMGC ZONE CONTROLLER

115 VAC

EIU HCU

FWC OIL QTY

CFDIU OIL TEMP

OIL PRESS TX

OIL/FUEL FLTR CLOG

OIL LO PRESS SW

FADEC INTERFACES

CTC-232-006-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

INTERFACES FAULT DETECTION & ANNUNCIATION

Page 5 Nov 02

CFM56-5B

TRAINING MANUAL

FADEC INTERFACES The FADEC system is closely integrated into the aircraft ECAM system to provide cockpit fault indication and warnings

Propulsion system survey parameters are directly displayed on dedicated Engine Warning and System Displays

Information contained on the ECU output buses includes:

This data is sent to :

The ECAM monitors operational data in order to display warnings and system information

FADEC system data is processed by the SDAC’s,

FWC’s and DMC’s before being presented on the ECAM Engine Warning Display (EWD) and System Display (SD)

The EWD is dedicated to the primary engine parameters and engine warning messages

The SD is dedicated to the propulsion system parameters when the engine system page is called either automatically,

The SDAC’s digitalize systems data and transmit it to the DMC’s

The SDAC’s receive systems information concerning amber cautions and transmit it to the FWC’s

The FWC’s receive systems data concerning red warnings and memos,

generate messages and activate attention getters

Both FWC’s have the same engine monitoring capability

The DMC’s use outputs from the FWC’s to display information on the lower part of the EWD

The EVMU provides vibration information to the SDAC’s for real time monitoring on the ECAM and to the DMU for condition monitoring

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

INTERFACES FAULT DETECTION & ANNUNCIATION

Page 6 Nov 02

CFM56-5B

TRAINING MANUAL

DMU (AIDS)

VIB SENSORS EWD

OIL TEMP OIL/FUEL FILTER CLOG

OIL QUANTITY OIL PRESS TRANSMITTER

OIL LO PRESS SWITCH

CTC-232-007-00

ENGINE DATA DISPLAY PROCESSING

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

INTERFACES FAULT DETECTION & ANNUNCIATION

Page 7 Nov 02

CFM56-5B

TRAINING MANUAL

ON-BOARD MAINTENANCE SYSTEM Acquisition of aircraft system data is performed by the Centralized Fault Display System (CFDS)

This includes the ECAM to display warnings and system information,

which is an obligatory recording system,

which is the main component of the Aircraft Integrated Data System (AIDS)

In each aircraft system computer,

a BITE monitors the system and memorizes the failures

After failure detection,

the BITE is able to identify the possible failed LRU’s and give a ‘snapshot’ of the system environment when the failure occurred

All information necessary for maintenance and troubleshooting is memorized in NVM

The ECU is able to distinguish between faults external and internal to the FADEC system

External faults are defined as those detected on aircraft interfaces not dedicated to the FADEC system

External functions include the ADIRU’s,

the EIU and aircraft power supplies

All other faults in the system (ECU,

) are considered internal faults

The main components of the CFDS are the CFDIU,

which has a main channel and a standby channel,

The CFDIU continuously scans the buses from the aircraft systems and if a failure message from a system BITE is present on a bus,

the CFDIU copies and stores it

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

The CFDIU also stores the ECAM messages generated by the FWC’s and acts as an interface for some class 2 failures,

and used for the ECAM maintenance status

The aircraft systems are divided into types 1,

2 and 3,

depending on their capabilities and connection to the CFDIU

Most systems are type 1 and these can memorize failures which have occurred in the last 64 flights

The engine (FADEC) is a type 1 system

The MCDU is the operators interface with the CFDIU

The DMU records significant operational parameters in order to monitor the engines,

the aircraft performance and to analyze specific aircraft problems

A Portable Data Loader (PDL) can be connected to the DMU for up and down loading

An optional Digital AIDS Recorder (DAR) enables data to be stored on a replaceable cassette

Most reports may be printed and data can also be transmitted to the ground,

Data may also be loaded into the maintenance computers,

through the Multi-purpose Disk Drive unit (MDDU)

INTERFACES FAULT DETECTION & ANNUNCIATION

Page 8 Nov 02

CFM56-5B

TRAINING MANUAL

FWC ECU

PRINTER

DMU (AIDS)

ON-BOARD MAINTENANCE

CTC-232-008-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

INTERFACES FAULT DETECTION & ANNUNCIATION

Page 9 Nov 02

CFM56-5B

TRAINING MANUAL

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INTERFACES FAULT DETECTION & ANNUNCIATION

Page 10 Nov 02

CFM56-5B

TRAINING MANUAL

ECU SIGNALS

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

ECU SIGNALS FAULT DETECTION & ANNUNCIATION

Page 1 Nov 02

CFM56-5B

TRAINING MANUAL

ECU INPUTS Each ECU channel receives critical engine signal inputs from separate sources

When the signal is less critical,

only one source sends a signal,

which is connected to both channels

Dual inputs : LVDT/RVDT and resolver :

Valve position switches :

N1 and N2 signals

Shared inputs : EGT

Fuel flowmeter

HMU OSG switch

ID plug inputs

Non-critical control inputs are only sent to one channel

Single inputs : PS13 to channel A (PMUX option)

T5 to channel A (PMUX option)

P25 to channel B (PMUX option)

Dual power : Engine alternator

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

ECU SIGNALS FAULT DETECTION & ANNUNCIATION

Page 2 Nov 02

CFM56-5B

TRAINING MANUAL

SINGLE PS13 (PMUX) T5 (PMUX)

DUAL LVDT/RVDT/RESOLVER SOL POSITION SW (e

SAV) PS12 PS3 P0 T25 T12 T3 TEO TECU N1 N2

CHANNEL A SHARED EGT TC FUEL FLOWMETER HMU OSG SW ID PLUG

CHANNEL B

ENGINE ALTERNATOR

SINGLE P25 (PMUX)

ENGINE INPUTS TO THE ECU

CTC-232-009-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

ECU SIGNALS FAULT DETECTION & ANNUNCIATION

Page 3 Nov 02

CFM56-5B

TRAINING MANUAL

AIRCRAFT TO ECU INPUTS The aircraft provides the electrical power supplies for the ECU and also the ignition system

The aircraft normal and emergency buses supply the ECU with 28Vdc,

The 115Vac,

through the EIU and then the ECU,

where it is switched on and off to control the operation of the exciters

The ARINC429 databuses and some aircraft discretes are wired to the engine as simplex connections and split into duplex connections on the engine

The actual split is implemented within the ECU

The aircraft provides the ECU with :

- Altitude

From the ADC’s,

From the EIU,

via an ARINC429 serial databus

The resolver is mechanically linked to the throttle levers in the cockpit

Selected hardwired discrete signals

which are used by the ECU to assign the SDI on ARINC outputs

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

ECU SIGNALS FAULT DETECTION & ANNUNCIATION

Page 4 Nov 02

CFM56-5B

TRAINING MANUAL

CHANNEL A MASTER LEVER/RESET ECU

CHANNEL A

AUTOTHRUST ENGAGEMENT/DISCONNECT ENGINE POSITION

CHANNEL B

CHANNEL B MASTER LEVER/RESET

AIRCRAFT INPUTS TO THE ECU

CTC-232-010-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

ECU SIGNALS FAULT DETECTION & ANNUNCIATION

Page 5 Nov 02

CFM56-5B

TRAINING MANUAL

ECU OUTPUTS Each ECU channel has 2 independent ARINC429 serial databuses,

which interface with the aircraft

There are no differences in the bus outputs,

but data which is specific to a channel,

such as fault and maintenance data,

may differ from channel to channel

Sensor values that are output by the two separate ECU channels will also be slightly different,

but within signal tolerance requirements

Cockpit indication data is output to the aircraft to keep the flight crew informed of the operational status of system components and FADEC system controlled engine parameters

Maintenance data is output,

via the ARINC429 buses to the aircraft maintenance computer

This data provides information to help the ground crew identify system faults and isolate the faults to the correct LRU,

Channels A and B deliver constant outputs,

irrespective of which channel is in control

Channel switch-over does not affect the output data of the ECU,

except for the status indication for the channel in control,

items specific to the channel in control and whatever faults caused the switch-over

Both ECU channels are able to control torque motor and solenoid output loads,

but only the active channel supplies control outputs during normal operation and the standby outputs are not used

The ECU turns the two engine igniters on,

using relay-controlled switches,

Each channel of the ECU also provides excitation voltages for the throttle control system resolvers

Engine condition monitoring parameters are output to the aircraft,

as digital equivalents of all sensor inputs to the ECU

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

ECU SIGNALS FAULT DETECTION & ANNUNCIATION

Page 6 Nov 02

CFM56-5B

TRAINING MANUAL

AIRCRAFT TRA EXCITATION T/R DIRECT VALVE T/R PRESSURE VALVE

CHANNEL A

ENGINE ACTIVE

OUTPUT DATABUS 2A OUTPUT DATABUS 1A OUTPUT DATABUS 1B

STAND-BY

OUTPUT DATABUS 2B T/R PRESSURE VALVE T/R DIRECT VALVE

STAND-BY

CHANNEL B

FMV HPTC LPTC VSV VBV TBV BSV SAV FRV 1 IGNITERS

STAND-BY

TRA EXCITATION

ECU OUTPUTS

CTC-232-011-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

ECU SIGNALS FAULT DETECTION & ANNUNCIATION

Page 7 Nov 02

CFM56-5B

TRAINING MANUAL

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EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

ECU SIGNALS FAULT DETECTION & ANNUNCIATION

Page 8 Nov 02

CFM56-5B

TRAINING MANUAL

FAULT DETECTION

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

FAULT DETECTION FAULT DETECTION & ANNUNCIATION

Page 1 Nov 02

CFM56-5B

TRAINING MANUAL

FAULT DETECTION Signal processing

Within the ECU,

the various inputs from sensors,

switches and the aircraft pass through several stages of checks before the values received are finally selected to be used in the control law calculations

Both ECU channels validate their inputs,

process the data and check their outputs identically

After they have been converted to a digital format,

the parametric/discrete values and the ARINC datawords must first pass through a signal and range check logic

The values are then compared across the CCDL before being selected for control low calculations

The control laws are entirely managed by the ECU software and will not be described here as they have no impact on fault detection

After the values have been calculated and processed in the control law logic,

they pass through to the output stage for transmission to engine,

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

FAULT DETECTION FAULT DETECTION & ANNUNCIATION

Page 2 Nov 02

CFM56-5B

TRAINING MANUAL

LOCAL CHANNEL PARAMETRIC

SIGNAL CHECK

DISCRETE

PARAMETER SELECTION RANGE CHECK

CONTROL LAW CALCULATIONS

OUTPUT CONTROL

CCDL CROSS CHANNEL PARAMETRIC DISCRETE ARINC

AS ABOVE

AS ABOVE

S/TM ARINC

SIGNAL PROCESSING

CTC-232-012-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

AS ABOVE

AS ABOVE

CFMI PROPRIETARY INFORMATION

FAULT DETECTION FAULT DETECTION & ANNUNCIATION

Page 3 Nov 02

CFM56-5B

TRAINING MANUAL

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EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

FAULT DETECTION FAULT DETECTION & ANNUNCIATION

Page 4 Nov 02

CFM56-5B

TRAINING MANUAL

WARNING INDICATIONS

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 1 Nov 02

CFM56-5B

TRAINING MANUAL

WARNING INDICATIONS Depending on the data transmitted from the engine,

messages are generated on the :

These messages are used to run the engine under normal conditions throughout the operating range,

or to provide warning messages to the crew and maintenance personnel

The aircraft computers that impact the engine are :

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 2 Nov 02

CFM56-5B

EFG ACCELEROMETER 1 ACCELEROMETER 2 N1 SPEED N2 SPEED

TRAINING MANUAL

EVMU SDAC 2

OIL QUANTITY OIL PRESSURE FUEL FILTER CLOG OIL FILTER CLOG N1 SPEED N2 SPEED EGT FUEL FLOW T/R SWITCHES SAV SWITCHES IGNITION

ECU DMC 2 DMC 3

NACELLE TEMP

OIL TEMP

OIL QUANTITY OIL PRESSURE SWITCH

LOWER ECAM

ENGINE INDICATING SYSTEM

CTC-232-013-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

UPPER ECAM

CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 3 Nov 02

CFM56-5B

TRAINING MANUAL

WARNING INDICATIONS Upper display

The N1 needle and N1 digital indication are normally green

The needle pulses amber when the actual N1 is above the N1 Max

Both needle and digital indication pulse red when the actual N1 is above the N1 red line (104%)

After an exceedance,

a red mark appears at the maximum value achieved

It disappears after a new engine start on ground,

of after maintenance action through the MCDU

If N1 is degraded (N1 dual sensor failure),

the last digit of the digital display is amber and dashed

A blue arc symbolizes the difference between the N1 command and the actual N1

This is not displayed if the A/THR is off

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 4 Nov 02

CFM56-5B

EGT 0 C N2 %

F K KG/H G G/H /H

TRAINING MANUAL

REDLINE : 104%

FOB:16300 1 16300 6 6300 300K KG G S

ENG 1 THR LEVER LE DISAGREE

N1 INDICATIONS

CTC-232-014-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

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WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 5 Nov 02

CFM56-5B

TRAINING MANUAL

WARNING INDICATIONS Upper display

The actual EGT indications are normally green The index pulses amber above 915°C (or above 725°C during the start sequence)

The index and the numerical value pulse red above 950°C

If 950°C is exceeded,

a red mark appears at the maximum value achieved

It disappears after a new take off,

or after maintenance action through the MCDU

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 6 Nov 02

CFM56-5B

EGT 0 C N2 %

F K KG/H G G/H /H

TRAINING MANUAL

AMBER LINE : 725°C DURING START

FOB:16300 1 16300 6 6300 300K KG G S

AMBER LINE : 915°C AFTER START RED LINE : 950°C

ENG 1 THR LEVER LE DISAGREE

EGT INDICATIONS

CTC-232-015-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 7 Nov 02

CFM56-5B

TRAINING MANUAL

WARNING INDICATIONS Upper display

The HP rotor speed digital indication is normally green

During the start sequence,

the indication is green on a grey background

When N2 is above 105%,

the indication becomes red and a red + appears next to the digital indication

It disappears after a new take off,

or after a maintenance action through the MCDU

If the N2 value is degraded (N2 dual sensor failure),

the last digit is amber and dashed

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 8 Nov 02

CFM56-5B

EGT 0 C N2 %

F K KG/H G G/H /H

TRAINING MANUAL

FOB:16300 1 16300 6 6300 300K KG G S

RED LINE : 105%

ENG 1 THR LEVER LE DISAGREE

N2 INDICATIONS

CTC-232-016-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 9 Nov 02

CFM56-5B

TRAINING MANUAL

WARNING INDICATIONS EGT N1 or N2 overlimit

This warning appears when there are primary parameter limit exceedances

The over limit for :

- N2 105%

The master caution comes on and the aural warning (single chime) sounds

The indication is shown in red and the failure message appears in amber on the upper ECAM display

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 10 Nov 02

CFM56-5B

EGT 0 C N2 %

F K KG/H G G/H /H

TRAINING MANUAL

FOB:16300 1 16300 6 6300 300K KG G S

THIS WARNING APPEARS WHEN EGT EXCEEDS 950°C

THE OVERLIMIT FOR :

ENG 1 EGT OVERLIMIT

N1 OR N2 OVERLIMIT

CTC-232-017-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 11 Nov 02

CFM56-5B

TRAINING MANUAL

WARNING INDICATIONS Upper display

The fuel flow indications are displayed in green

In case of invalid fuel flow information,

the digital indication is replaced by two amber crosses

This lack of valid data happens when the ECU power is off

This is the case on the ground,

five minutes after the last engine shut down

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 12 Nov 02

CFM56-5B

EGT 0 C

TRAINING MANUAL

KG G FOB:16300 1 16300 6 6300 300K

ENG 1 THR LEVER LE DISAGREE

FUEL FLOW INDICATIONS

CTC-232-018-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

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WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 13 Nov 02

CFM56-5B

TRAINING MANUAL

WARNING INDICATIONS Lower display

The fuel used value,

It is reset at the next engine start (Master switch ON) on ground

It is frozen at its last value at engine shut down until the next engine start

The two last digits are dashed if the fuel used indication is inaccurate due to a loss of fuel flow information for more than 1 minute

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 14 Nov 02

CFM56-5B

USED 1432 KG

VIB (N2) 1

VIB (N1 N1) 0

TRAINING MANUAL

PSI 35 35

TAT AT +10 SAT +10

GNB AIGN C C

34 3 4 PSI

GW 54700 KG

FUEL USED INDICATIONS

CTC-232-019-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 15 Nov 02

CFM56-5B

TRAINING MANUAL

WARNING INDICATIONS Lower display

The needle and the digital indication are normally green

The indication pulses below 3 quarts decreasing,

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 16 Nov 02

CFM56-5B

USED 1432 KG

VIB (N2) 1

NORMAL INDICATION PULSES IF :

VIB (N1 N1) 0

TRAINING MANUAL

PSI 35 35

TAT AT +10 SAT +10

GNB AIGN C C

3 34 4 PSI

OIL QUANTITY INDICATIONS

CTC-232-020-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

GW 54700 KG

CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 17 Nov 02

CFM56-5B

TRAINING MANUAL

WARNING INDICATIONS Lower display

The needle and digital indication are normally in green

The normal indication pulses if :

The indication is red associated with an ECAM warning if the oil pressure drops below 13 psi

In case of oil low pressure warning,

the master warning flashes and the aural warning (continuous chime) sounds

The failure message is shown in red on the upper ECAM display

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 18 Nov 02

CFM56-5B

USED 1432 KG

VIB (N2) 1

VIB (N1 N1) 0

PSI 35 35

TAT AT +10 SAT +10

GNB AIGN C C

WILL CONTINUE TO PULSE UNTIL PRESSURE DROPS BELOW 85 PSI

INDICATION RED IF PRESSURE DROPS BELOW 13 PSI

3 34 4 PSI

GW 54700 KG

OIL PRESSURE INDICATIONS

CTC-232-021-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

INDICATION PULSES IF :

WILL CONTINUE TO PULSE UNTIL PRESSURE EXCEEDS 20 PSI

TRAINING MANUAL

CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 19 Nov 02

CFM56-5B

TRAINING MANUAL

WARNING INDICATIONS Lower display

The oil temperature indication is normally green

The indication pulses above 140°C increasing and continues to pulse until the temperature drops below 135°C

The indication becomes amber associated,

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321 CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 20 Nov 02

CFM56-5B

USED 1432 KG

VIB (N2) 1

VIB (N1 N1) 0

PSI 35 35

TAT AT +10 SAT +10

GNB AIGN C C

3 34 4 PSI

GW 54700 KG

OIL TEMPERATURE INDICATIONS

CTC-232-022-00

EFFECTIVITY ALL CFM56-5B ENGINES FOR A319-A320-A321

INDICATION PULSES ABOVE 140°C INCREASING,

WILL CONTINUE TO PULSE UNTIL TEMPERATURE DROPS BELOW 135°C

INDICATION AMBER IF TEMPERATURE EXCEEDS :

TRAINING MANUAL

CFMI PROPRIETARY INFORMATION

WARNING INDICATIONS FAULT DETECTION & ANNUNCIATION

Page 21 Nov 02

CFM56-5B

TRAINING MANUAL

WARNING INDICATIONS Lower display

Lower display

IGN is displayed in white during the start sequence

This indication is displayed,

except during the start sequence,

when the nacelle temperature is above 240°C (advisory threshold)

The selected ignitors ‘A’,

or ‘AB’ are displayed in green when supplied during start,

The start valve position is green and displayed only during the start sequence

The bleed pressure,

is displayed normally in green

It becomes amber b