TRAINING MANUAL
CFM56-5B
BASIC ENGINE
JUNE 1999
CTC-063 Level 3
CFM56-5B
EF G
TRAINING MANUAL
BASIC ENGINE
Published by CFMI
CFMI Customer Training Center
Snecma (RXEF)
Direction de l’Après-Vente Civile
MELUN-MONTEREAU
Aérodrome de Villaroche B.P. 1936
77019 - MELUN-MONTEREAU Cedex
FRANCE
EFFECTIVITY
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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
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March 98
CFM56-5B
EF G
TRAINING MANUAL
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CFM56-5B
EF G
TRAINING MANUAL
This CFMI publication is for Training Purposes Only. The information is accurate at the time of compilation; however, 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.S. 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, may not be diverted, transferred, re-exported
or disclosed in any manner not provided for by the license without prior written approval of both the U.S. Government and
CFM International.
COPYRIGHT 1998 CFM INTERNATIONAL
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GENERAL
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CFM56-5B
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TRAINING MANUAL
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March 98
CFM56-5B
EFG
TRAINING MANUAL
TABLE OF CONTENTS
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Page 1
CONTENTS June
99
BASIC ENGINE
CFM56-5B
EFG
Chapter
Section
TRAINING MANUAL
Page
Table of Contents
1 to 2
Lexis
1 to 8
Intro
1 to 8
72-00-00
Engine General
1 to 10
72-20-00
Fan Section
1 to 22
72-30-00
High Pressure Compressor Section
1 to 6
72-40-00
Combustion Section
1 to 6
72-50-00
Turbine Section
1 to 14
72-60-00
Accessory Drive Section
1 to 12
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Page 2
CONTENTS June
99
BASIC ENGINE
CFM56-5B
EFG
TRAINING MANUAL
ABBREVIATIONS & ACRONYMS
TOC
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CFMI PROPRIETARY INFORMATION
LEXIS
Page 1
June 99
CFM56-5B
EFG
A
A/C
AC
ACARS
ACMS
ACS
ADC
ADEPT
ADIRS
AGB
AIDS
ALF
ALT
AMB
AMM
AOG
APU
ARINC
ATA
ATHR
ATO
AIRCRAFT
ALTERNATING CURRENT
AIRCRAFT COMMUNICATION
ADDRESSING and REPORTING SYSTEM
AIRCRAFT CONDITION MONITORING
SYSTEM
AIRCRAFT CONTROL SYSTEM
AIR DATA COMPUTER
AIRLINE DATA ENGINE PERFORMANCE
TREND
AIR DATA AND INERTIAL REFERENCE
SYSTEM
ACCESSORY GEARBOX
AIRCRAFT INTEGRATED DATA SYSTEM
AFT LOOKING FORWARD
ALTITUDE
AMBIENT
AIRCRAFT MAINTENANCE MANUAL
AIRCRAFT ON GROUND
AUXILIARY POWER UNIT
AERONAUTICAL RADIO, INC.
(SPECIFICATION)
AIR TRANSPORT ASSOCIATION
AUTO THRUST
ABORTED TAKE OFF
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CFMI PROPRIETARY INFORMATION
TOC
B
BITE
BMC
BSI
BSV
BVCS
C
CBP
CCDL
CCFG
CCU
CCW
CDP
CFDIU
CFDS
CFMI
Ch A
Ch B
CMC
CMM
CMS
CG
cm.g
CHATV
TRAINING MANUAL
BUILT IN TEST EQUIPMENT
BLEED MANAGEMENT COMPUTER
BORESCOPE INSPECTION
BURNER STAGING VALVE
BLEED VALVE CONTROL SOLENOID
(HP) COMPRESSOR BLEED PRESSURE
CROSS CHANNEL DATA LINK
COMPACT CONSTANT FREQUENCY
GENERATOR
COMPUTER CONTROL UNIT
COUNTER CLOCKWISE
(HP) COMPRESSOR DISCHARGE
PRESSURE
CENTRALIZED FAULT DISPLAY
INTERFACE UNIT
CENTRALIZED FAULT DISPLAY SYSTEM
JOINT GE/SNECMA COMPANY (CFM
INTERNATIONAL)
channel A
channel B
CENTRALIZED MAINTENANCE
COMPUTER
COMPONENT MAINTENANCE MANUAL
CENTRALIZED MAINTENANCE SYSTEM
CENTER OF GRAVITY
CENTIMETER x GRAMS
CHANNEL ACTIVE
LEXIS
Page 2
June 99
EFG
CIP(HP)
CIT(HP)
CODEP
CPU
CRT
CSD
CSI
CSN
Cu.Ni.In
CW
COMPRESSOR INLET PRESSURE
COMPRESSOR INLET TEMPERATURE
HIGH TEMPERATURE COATING
CENTRAL PROCESSING UNIT
CATHODE RAY TUBE
CONSTANT SPEED DRIVE
CYCLES SINCE INSTALLATION
CYCLES SINCE NEW
COPPER.NICKEL.INDIUM
CLOCKWISE
EFIS
D
DC
DCU
DISC
DIU
DMC
DMU
DPU
DIRECT CURRENT
DATA CONVERSION UNIT
DISCRETE
DIGITAL INTERFACE UNIT
DISPLAY MANAGEMENT COMPUTER
DATA MANAGEMENT UNIT
DIGITAL PROCESSING MODULE
ESN
EIU
E
EBU
ECAM
ECU
EFH
TOC
CFM56-5B
ENGINE BUILDUP UNIT
ELECTRONIC CENTRALIZED AIRCRAFT
MONITORING
ELECTRONIC CONTROL UNIT
ENGINE FLIGHT HOURS
EFFECTIVITY
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CFMI PROPRIETARY INFORMATION
EGT
EICAS
EIS
EIU
EMF
EMI
EMU
EPROM
F
FAA
FADEC
FAR
FDRS
FEIM
FFCCV
FI
FLA
TRAINING MANUAL
ELECTRONIC FLIGHT INSTRUMENT
SYSTEM
EXHAUST GAS TEMPERATURE
ENGINE INDICATING AND CREW
ALERTING SYSTEM
ELECTRONIC INSTRUMENT SYSTEM
ENGINE INTERFACE UNIT
ELECTROMOTIVE FORCE
ELECTRO MAGNETIC INTERFERENCE
ENGINE MAINTENANCE UNIT
ERASABLE PROGRAMMABLE READ
ONLY MEMORY
ENGINE SERIAL NUMBER
ENGINE INTERFACE UNIT
FEDERAL AVIATION AGENCY
FULL AUTHORITY DIGITAL
ENGINE CONTROL
FUEL/AIR RATIO
FLIGHT DATA RECORDING SYSTEM
FIELD ENGINEERING INVESTIGATION
MEMO
FAN FRAME/COMPRESSOR CASE
VERTICAL (VIBRATION SENSOR)
FLIGHT IDLE (F/I)
FORWARD LOOKING AFT
LEXIS
Page 3
June 99
EFG
FLX TO
FMGC
CFM56-5B
FRV
FWC
FWD
FLEXIBLE TAKE OFF
FLIGHT MANAGEMENT AND GUIDANCE
COMPUTER
FLIGHT MANAGEMENT SYSTEM
FUEL METERING VALVE
FOREIGN OBJECT DAMAGE
FRONT PANEL ASSEMBLY
FLUORESCENT PENETRANT
INSPECTION
FUEL RETURN VALVE
FAULT WARNING COMPUTER
FORWARD
G
GE
GEM
GI
g.in
GMT
GSE
GENERAL ELECTRIC
GROUND-BASED ENGINE MONITORING
GROUND IDLE (G/I)
GRAM x INCHES
GREENWICH MEAN TIME
GROUND SUPPORT EQUIPMENT
FMS
FMV
FOD
FPA
FPI
H
HCF
HMU
HP
HPC
HPCR
HPSOV
HPT
HIGH CYCLE FATIGUE
HYDROMECHANICAL UNIT
HIGH PRESSURE
HIGH PRESSURE COMPRESSOR
HIGH PRESSURE COMPRESSOR ROTOR
HIGH PRESSURE SHUTOFF VALVE
HIGH PRESSURE TURBINE
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CFMI PROPRIETARY INFORMATION
TOC
HPTC
HPT(A)CC
TRAINING MANUAL
HPTR
Hz
HIGH PRESSURE TURBINE CLEARANCE
HIGH PRESSURE TURBINE (ACTIVE)
CLEARANCE CONTROL
HIGH PRESSURE TURBINE CLEARANCE
CONTROL VALVE
HIGH PRESSURE TURBINE ROTOR
HERTZ (CYCLES PER SECOND)
I
IDG
ID PLUG
IFSD
IGB
IGN
IGV
in.
I/O
IOM
IR
INTEGRATED DRIVE GENERATOR
IDENTIFICATION PLUG
IN FLIGHT SHUT DOWN
INLET GEARBOX
IGNITION
INLET GUIDE VANE
INCH
INPUT/OUTPUT
INPUT OUTPUT MODULE
INFRA RED
K
K
1000 X
L
lbs.
LCF
LE (L/E)
L/H
POUNDS, WEIGHT
LOW CYCLE FATIGUE
LEADING EDGE
LEFT HAND
HPTCCV
LEXIS
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June 99
EFG
LP
LPC
LPT
LPTC
LPT(A)CC
LPTR
LRU
LVDT
M
MO
MCD
MCDU
MCL
MCT
MDDU
MEC
mm.
MMEL
MTBF
MTBR
TOC
CFM56-5B
LOW PRESSURE
LOW PRESSURE COMPRESSOR
LOW PRESSURE TURBINE
LOW PRESSURE TURBINE CLEARANCE
LOW PRESSURE TURBINE (ACTIVE)
CLEARANCE CONTROL
LOW PRESSURE TURBINE ROTOR
LINE REPLACEABLE UNIT
LINEAR VARIABLE DIFFERENTIAL
TRANSFORMER
N
N1 (NL)
AIRCRAFT SPEED MACH NUMBER
MAGNETIC CHIP DETECTOR
MULTIPURPOSE CONTROL AND
DISPLAY UNIT
MAXIMUM CLIMB
MAXIMUM CONTINUOUS
MULTIPURPOSE DISK DRIVE UNIT
MAIN ENGINE CONTROL
MILLIMETERS
MAIN MINIMUM EQUIPMENT LIST
MEAN TIME BETWEEN FAILURES
MEAN TIME BETWEEN REMOVALS
O
OAT
OGV
OSG
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TRAINING MANUAL
LOW PRESSURE ROTOR
ROTATIONAL SPEED
N1ACT
ACTUAL N1
N1DMD
DEMANDED N1
N1CMD
COMMANDED N1
N1TARGET TARGETED FAN SPEED
N2 (NH)
HIGH PRESSURE ROTOR ROTATIONAL
SPEED
N2ACT
ACTUAL N2
NVM
NON VOLATILE MEMORY
P
P0
P25
PCU
PLA
PMC
PMUX
PS12
PS13
OUTSIDE AIR TEMPERATURE
OUTLET GUIDE VANE
OVERSPEED GOVERNOR
AMBIENT STATIC PRESSURE
HP COMPRESSOR INLET TOTAL AIR
TEMPERATURE
PRESSURE CONVERTER UNIT
POWER LEVER ANGLE
POWER MANAGEMENT CONTROL
PROPULSION MULTIPLEXER
FAN INLET STATIC AIR PRESSURE
FAN OUTLET STATIC AIR PRESSURE
LEXIS
Page 5
June 99
EFG
PS3HP
psi
psia
psid
psig
PSM
PSS
PSU
PT
PT2
Q
QAD
QTY
R
RAC/SB
RACC
RAM
R/H
RPM
RTD
RTV
CFM56-5B
COMPRESSOR DISCHARGE STATIC AIR
PRESSURE
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)
QUICK ATTACH DETACH
QUANTITY
ROTOR ACTIVE CLEARANCE/START
BLEED
ROTOR ACTIVE CLEARANCE CONTROL
RANDOM ACCESS MEMORY
RIGHT HAND
REVOLUTIONS PER MINUTE
RESISTIVE THERMAL DEVICE
ROOM TEMPERATURE VULCANIZING
(MATERIAL)
EFFECTIVITY
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CFMI PROPRIETARY INFORMATION
TOC
RVDT
S
SAV
SB
SCU
SDI
SDU
SER
SFC
SG
SLS
SMM
SMP
S/N
SNECMA
SOL
S/R
S/V
SVR
SW
T
T12
T25
TRAINING MANUAL
ROTARY VARIABLE DIFFERENTIAL
TRANSFORMER
STARTER AIR VALVE
SERVICE BULLETIN
SIGNAL CONDITIONING UNIT
SOURCE/DESTINATION IDENTIFIER
(BITS) (CF ARINC SPEC)
SOLENOID DRIVER UNIT
SERVICE EVALUATION REQUEST
SPECIFIC FUEL CONSUMPTION
SPECIFIC GRAVITY
SEA LEVEL STANDARD
(CONDITIONS : 29.92 in. Hg/59 F)
STATUS MATRIX
SOFTWARE MANAGEMENT PLAN
SERIAL NUMBER
SOCIETE NATIONALE D’ETUDE ET DE
CONSTRUCTION DE MOTEURS
D’AVIATION
SOLENOID
SERVICE REQUEST
SHOP VISIT
SHOP VISIT RATE
SOFTWARE
FAN INLET TOTAL AIR TEMPERATURE
HP COMPRESSOR INLET AIR
TEMPERATURE
LEXIS
Page 6
June 99
EFG
T3
T49.5
T5
TAT
TBD
TBV
T/E
T/C
TC
TCase
TCC
TCJ
TECU
TEO
TGB
Ti
TLA
TM
TMC
TO/GA
T/O
T oil
TPU
TOC
CFM56-5B
HP COMPRESSOR DISCHARGE AIR
TEMPERATURE
EXHAUST GAS TEMPERATURE
LOW PRESSURE TURBINE DISCHARGE
TOTAL AIR TEMPERATURE
TOTAL AIR TEMPERATURE
TO BE DETERMINED
TRANSIENT BLEED VALVE
TRAILING EDGE
THERMOCOUPLE
HP TURBINE CASE TEMPERATURE
HP TURBINE CASE TEMPERATURE
TURBINE CLEARANCE CONTROL
TEMPERATURE COLD JUNCTION
ELECTRONIC CONTROL UNIT INTERNAL
TEMPERATURE
ENGINE OIL TEMPERATURE
TRANSFER GEARBOX
TITANIUM
THROTTLE LEVER ANGLE
TORQUE MOTOR
TORQUE MOTOR CURRENT
TAKE OFF/GO AROUND
TAKE OFF
OIL TEMPERATURE
TRANSIENT PROTECTION UNIT
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
T/R
TRA
TRDV
TRAINING MANUAL
TSI
TSN
TTL
THRUST REVERSER
THROTTLE RESOLVER ANGLE
THRUST REVERSER DIRECTIONAL
VALVE
THRUST REVERSER PRESSURIZING
VALVE
TIME SINCE INSTALLATION (HOURS)
TIME SINCE NEW (HOURS)
TRANSISTOR TRANSISTOR LOGIC
U
UER
UNSCHEDULED ENGINE REMOVAL
TRPV
V
VAC
VBV
VDC
VDT
VRT
VSV
VOLTAGE, ALTERNATING CURRENT
VARIABLE BLEED VALVE
VOLTAGE, DIRECT CURRENT
VARIABLE DIFFERENTIAL
TRANSFORMER
VARIABLE RESISTANCE TRANSDUCER
VARIABLE STATOR VANE
W
WDM
WFM
WOW
WATCHDOG MONITOR
WEIGHT OF FUEL METERED
WEIGHT ON WHEEL
LEXIS
Page 7
June 99
CFM56-5B
EFG
TRAINING MANUAL
ENGLISH/METRIC CONVERSIONS
METRIC/ENGLISH CONVERSIONS
1 mile = 1.609 km
1 km = 0.621 mile
1 lb = 0.454 kg
1 kg =2.205 lbs
1 ft = 0.3048 m or 30.48 cm
1 m = 3.281 ft. or 39.37 in.
1 psi = 6.890 kPa or 6.89 x 10-2 bar
1 Pa = 1.45 x 10-4 psi
1 kPa = 0.145 psi or 0.01 bar
1 bar = 14.5 psi
1 in. = 0.0254 m or 2.54 cm
1 cm = 0.3937 in.
1 mil. = 25.4 10-6 m or 25.4mm
1 mm = 39.37 mils.
°F = 1.8 x °C + 32
°C = ( °F - 32 ) /1.8
1 in.2 = 6.45 cm²
1 m² = 10.76 sq. ft.
1 cm² = 0.155 sq.in.
1 USG = 3.785 l ( dm³ )
1 in.3 = 16.39 cm³
1 m³ = 35.31 cu. ft.
1 dm³ = 0.264 US gallon
1 cm³ = 0.061 cu.in.
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
TOC
LEXIS
Page 8
June 99
CFM56-5B
EF G
TRAINING MANUAL
INTRODUCTION TO THE CFM56 FAMILY
TOC
EFFECTIVITY
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CFMI PROPRIETARY INFORMATION
INTRO
BASIC ENGINE
Page 1
June 99
CFM56-5B
EF G
TRAINING MANUAL
INTRODUCTION TO THE CFM56 FAMILY
The CFM56 engine, a high by-pass, dual rotor, axial flow
advanced technology turbofan, was designed in the mid
70’s.
It is a product of CFMI. CFM International is a company
jointly owned by GENERAL ELECTRIC (GE) of the USA,
and SOCIETE NATIONALE D’ETUDE ET DE
CONSTRUCTION DE MOTEURS D’AVIATION
(SNECMA) of France.
CFMI, with the full backing of parent companies holding
equal shares, has a dual function :
- Overall program management, on behalf of both GE
and SNECMA
- Single interface with customers for marketing and
product support
EFFECTIVITY
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CFMI PROPRIETARY INFORMATION
TOC
INTRO
BASIC ENGINE
Page 2
June 99
CFM56-5B
EF G
TRAINING MANUAL
DESIGN
DEVELOPMENT
MANUFACTURING
ASSEMBLY
Jointly owned company
Uses all GENERAL ELECTRIC and
SNECMA resources...
...With work split 50/50
One program manager
One customer interface
MARKETING
PRODUCT SUPPORT
CUSTOMER SATISFACTION
CTC-063-001-01
TOC
CFM INTERNATIONAL ORGANIZATION
EFFECTIVITY
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INTRO
BASIC ENGINE
Page 3
June 99
CFM56-5B
EF G
TRAINING MANUAL
INTRODUCTION TO THE CFM56 FAMILY
Engine Applications
The following chart shows the various engine models for
the Airbus A319-A320-A321 aircraft.
The engine used on these aircraft is the CFM56-5B,
which has several different thrust ratings.
EFFECTIVITY
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TOC
INTRO
BASIC ENGINE
Page 4
June 99
CFM56-5B
EF G
TRAINING MANUAL
CFM56-5B5 (22,000 lbs)
CFM56-5B6 (23,500 lbs)
CFM56-5B7 (27,000 lbs)
CFM56-5B4 (27,000 lbs)
CFM56-5B1 (30,000 lbs)
CFM56-5B2 (31,000 lbs)
CFM56-5B3 (33,000 lbs)
CTC-063-002-01
TOC
CFM56-5B FOR AIRBUS APPLICATIONS
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INTRO
BASIC ENGINE
Page 5
June 99
CFM56-5B
EF G
TRAINING MANUAL
CFM56-5B MAIN CHARACTERISTICS
Type of engine
Turbo fan
Arrangement
Two spool axial flow
Rotation
Clockwise (ALF)
Compressors
- Fan
- LP Compressor
- HP Compressor
Single stage
Five stages
Nine stages
Combustion chamber
Annular SAC (option DAC)
Turbines
- HP Turbine
- LP Turbine
Single stage
Four stages
Weight
2381 kg (5249 lbs)
Overall dimensions
- Length
- Height
- Width
2.94m (115.86 ins)
2.14m (83.65 ins)
1.97m (77.88 ins)
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
TOC
INTRO
BASIC ENGINE
Page 6
June 99
CFM56-5B
EF G
CFM56-5B
CTC-063-003-01
TOC
TRAINING MANUAL
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
INTRO
BASIC ENGINE
Page 7
June 99
CFM56-5B
EF G
TRAINING MANUAL
THIS PAGE INTENTIONALLY LEFT BLANK
EFFECTIVITY
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INTRO
BASIC ENGINE
Page 8
June 99
CFM56-5B
EF G
TRAINING MANUAL
ENGINE GENERAL
TOC
EFFECTIVITY
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CFMI PROPRIETARY INFORMATION
72-00-00
BASIC ENGINE
Page 1
June 99
CFM56-5B
EF G
TRAINING MANUAL
ENGINE GENERAL CONCEPT
The CFM56-5B engine is a high by-pass, dual rotor, axial
flow, advanced technology turbofan. It is supported by
the wing pylon and streamlined by cowlings.
Air is sucked into the intake by the fan blades and split
into two flow paths, the Primary and the Secondary.
The primary airflow passes through the inner portion of
the fan blades and is directed into a booster (LPC).
The airflow then enters a High Pressure Compressor
(HPC) and goes to a combustor. Mixed with fuel and
ignited, the gas flow provides energy to a High Pressure
Turbine (HPT) and a Low Pressure Turbine (LPT).
The secondary airflow passes through the outer portion
of the fan blades, the Outlet Guide Vanes (OGV’s) and
exits through the nacelle discharge duct, producing
approximately 80 % of the total thrust. It also plays a role
in the thrust reverser system.
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
TOC
72-00-00
BASIC ENGINE
Page 2
June 99
CFM56-5B
EF G
TRAINING MANUAL
SECONDARY FLOW
PRIMARY FLOW
THRUST
REVERSER
DESIGN AND OPERATION
CTC-063-005-00
TOC
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
72-00-00
BASIC ENGINE
Page 3
June 99
CFM56-5B
EF G
TRAINING MANUAL
ENGINE GENERAL CONCEPT
The CFM56-5B engine uses a maintenance concept
called ‘On Condition Maintenance’. This means that the
engine has no periodic overhaul schedules and can
remain installed under the wing until something important
occurs, or when lifetime limits of parts are reached.
For this reason, to monitor and maintain the health of the
engine, different tools are available, which are :
- Engine performance trend monitoring
- Borescope inspection
- Lubrication particles analysis
- Spectrometric oil analysis (S.O.A.P)
- Engine vibration monitoring system
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
TOC
72-00-00
BASIC ENGINE
Page 4
June 99
CFM56-5B
EF G
GAS PATH HEALTH
VIBRATION
MONITORING
BORESCOPE
INSPECTION
LUBE PARTICLE ANALYSIS
S.O.A.P. ANALYSIS
CONDITION MONITORING
CTC-063-009-01
TOC
TRAINING MANUAL
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
72-00-00
BASIC ENGINE
Page 5
June 99
CFM56-5B
EF G
TRAINING MANUAL
ENGINE GENERAL CONCEPT
The CFM56-5B engine consists of two independent
rotating systems :
- The low pressure system rotational speed is
designated N1.
- The high pressure system rotational speed is
designated N2.
The engine rotors are supported by 5 bearings, identified
in manuals as numbers 1 thru 5, where No. 1 is the most
forward and No. 5 the most aft. These bearings are
housed in 2 sump cavities provided by the fan and
turbine frames.
Engine structural rigidity is obtained with short lengths
and two main structures (frames).
The accessory drive system uses energy from the high
pressure compressor rotor to drive the engine and
aircraft accessories. It also plays a major role in starting.
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
TOC
72-00-00
BASIC ENGINE
Page 6
June 99
CFM56-5B
EF G
TRAINING MANUAL
5 BEARINGS
LP SYSTEM
ACCESSORY
DRIVE
2 FRAMES
HP SYSTEM
2 SUMPS
ENGINE GENERAL CONCEPT
CTC-063-006-00
TOC
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
72-00-00
BASIC ENGINE
Page 7
June 99
CFM56-5B
EF G
TRAINING MANUAL
ENGINE GENERAL CONCEPT
The CFM56-5B is a modular concept design engine. It
has 17 different modules that are enclosed within four
major modules.
The 4 Major Modules are :
- The Fan Major Module
- The Core Engine Major Module
- The Low Pressure Turbine Major Module
- The Accessory Drive Major Module
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June 99
CFM56-5B
EF G
TRAINING MANUAL
CORE ENGINE MAJOR MODULE
FAN MAJOR MODULE
LOW PRESSURE TURBINE
MAJOR MODULE
ACCESSORY DRIVE MAJOR MODULE
MODULAR DESIGN
CTC-063-008-01
TOC
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June 99
CFM56-5B
EF G
TRAINING MANUAL
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Page 10
June 99
CFM56-5B
EF G
TRAINING MANUAL
FAN SECTION
TOC
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June 99
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EF G
TRAINING MANUAL
FAN AND BOOSTER MODULE
The Fan and Booster module consists of :
- a spinner front cone
- a spinner rear cone
- a single stage fan rotor
- a four stage axial booster
The spinner front cone is designed to minimize ice buildup and is attached to the spinner rear cone.
The fan disk supports the mid-span shrouded fan blades
and a booster spool.
The booster spool accommodates booster blade stages,
numbers 2 thru 5.
The booster vane assembly stages, numbers 1 thru 5,
are stacked and mounted on the fan frame.
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Page 2
June 99
CFM56-5B
EF G
TRAINING MANUAL
FAN ROTOR
BOOSTER
SPINNER REAR
CONE
SPINNER FRONT
CONE
FAN AND BOOSTER DESIGN
CTC-063-011-01
TOC
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June 99
CFM56-5B
EF G
TRAINING MANUAL
FAN AND BOOSTER MODULE (CONTINUED)
Spinner front cone
Interference fit and single annular mounting positions are
characteristics of the installation of the front and rear
cone onto the fan disk.
The spinner front cone has an indent mark, which is
located next to an offset hole on its rear flange, to ensure
correct alignment for installation onto the rear cone front
flange.
The rear flange has 6 mounting screw locations and 3
threaded inserts, located every 120°, for installation of
jackscrews used in removal procedures.
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Page 4
June 99
CFM56-5B
EF G
6 MOUNTING
SCREW LOCATIONS
OFFSET HOLE
INDENT
MARK
TRAINING MANUAL
MOUNTING
SCREW
3 JACKSCREW
LOCATIONS
SPINNER FRONT CONE
CTC-063-012-01
TOC
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June 99
CFM56-5B
EF G
TRAINING MANUAL
FAN AND BOOSTER MODULE (CONTINUED)
Spinner rear cone
The front flange of the spinner rear cone has 6 line
replaceable, crimped, self-locking nuts.
The inner rear flange has 12 mounting screw holes, for
installation onto the fan disk, and there are a further 6
threaded holes for the installation of jackscrews used in
rear cone removal procedures.
Both front and rear flanges have an offset hole to ensure
correct installation and they are identified by indent
marks.
The rear cone also has an integrated air seal that is
glued to its inner rear flange.
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Page 6
June 99
CFM56-5B
EF G
TRAINING MANUAL
REAR FLANGE
GLUED
SEAL
CRIMPED
SELF - LOCKING NUTS
12 MOUNTING
SCREW HOLES
JACKSCREW HOLE
REAR CONE
CTC-063-013-01
TOC
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June 99
CFM56-5B
EF G
TRAINING MANUAL
FAN AND BOOSTER MODULE (CONTINUED)
Spinner rear cone (continued)
The rear cone prevents axial disengagement of spacers
used in the fan blade retention system.
It also supports a series of balancing screws that are
installed on its outer diameter. There are two sets of
balancing screws available and the screws in each set
are identified as either P01 to P07 or, P08 to P14. The
numbers, which are engraved on the screw heads, are
equivalent to various weights.
An indent mark is located in between two balancing
screws for correct installation of the rear cone onto the
fan disk and for identification of fan blade No.1.
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Page 8
June 99
CFM56-5B
EF G
TRAINING MANUAL
FAN BLADE
FAN BLADE
SPACER
FAN DISK
BALANCING SCREWS
BALANCE
SCREWS
SPACER
REAR CONE
CTC-063-014-01
TOC
INDENT MARK
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CFM56-5B
EF G
TRAINING MANUAL
FAN AND BOOSTER MODULE (CONTINUED)
Fan disk
The inner front flange has an imprint to identify an offset
hole for rear cone installation.
There are also two identification marks engraved on
either side of blade recesses No.1 and 5.
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Page 10
June 99
CFM56-5B
EF G
TRAINING MANUAL
SPHERICAL
IMPRINT
1
1
5
5
OFFSET HOLE
FAN DISK FRONT FLANGE
CTC-063-015-01
TOC
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June 99
CFM56-5B
EF G
TRAINING MANUAL
FAN AND BOOSTER MODULE (CONTINUED)
Fan blades
There are 36 titanium alloy, mid-span shrouded fan
blades.
Each blade has a dovetail base that slides into a recess
on the fan disk outer rim.
A retainer lug, machined at the rear end of the blade
root, engages the forward flange of the booster spool
and limits axial movements.
A spacer, installed underneath each blade, limits the
radial movement.
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Page 12
June 99
CFM56-5B
EF G
TRAINING MANUAL
36 FAN BLADES
RETAINER LUG
DISK
SPACER
FAN BLADES
CTC-063-016-01
TOC
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Page 13
June 99
CFM56-5B
EF G
TRAINING MANUAL
FAN AND BOOSTER MODULE (CONTINUED)
Fan blades (continued)
Each blade has specific indications engraved on the
bottom of the root :
- Part number
- Serial number
- Momentum weight
- Manufacturer code
The fan blade root pressure faces are sprayed with an
anti-friction plasma coating, and dry molybdenum base
film is applied to the blade roots.
The fan blade mid-span shroud contact surfaces have a
hard plasma coating, and a dry molybdenum base film is
then applied.
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Page 14
June 99
CFM56-5B
EF G
TRAINING MANUAL
MANUFACTURER CODE
PART NUMBER
MOMENTUM
WEIGHT
F0301 337-000-114-0
206740
F0491 J023493
TUNGSTEN CARBIDE COATING
AND MOLYBDENUM FILM
SERIAL NUMBER
SUB-CONTRACTOR
NUMBER
EXAMPLE SPECIFIC
INDICATIONS
FAN BLADE
TUNGSTEN CARBIDE COATING
AND MOLYBDENUM FILM
Cu-Ni-In COATING AND
MOLYBDENUM FILM
SPECIFIC
INDICATIONS
FAN BLADE ROOT
CTC-063-017-01
TOC
HARD COATING
SURFACE
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Page 15
June 99
CFM56-5B
EF G
TRAINING MANUAL
FAN FRAME MODULE
The fan frame module is the main forward structure for
mounting the engine onto the airframe. It supports the
fan and booster module, the HPC and cowls.
The fan frame module consists of the following 3 major
assemblies :
- The fan frame
- The downstream fan inlet case
- The upstream fan inlet case
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Page 16
June 99
CFM56-5B
EF G
TRAINING MANUAL
FAN FRAME
OUTER FLANGES
OUTER RIBS
MOUNTING FLANGE
FAN ABRADABLE
LINER
FAN INLET CASE ASSEMBLY
CTC-063-018-00
TOC
DOWNSTREAM
FAN INLET CASE
UPSTREAM FAN INLET CASE
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June 99
CFM56-5B
EF G
TRAINING MANUAL
FAN FRAME MODULE (CONTINUED)
Fan inlet case
The inner surface of the upstream fan inlet case is lined
with 6 forward acoustical panels, 6 mid acoustical panels
and provides an abradable shroud which faces the fan
blade tips.
The inner surface of the downstream fan inlet case is
lined with 12 aft acoustical panels.
The fan inlet case also houses the Outlet Guide Vane
(OGV) assembly.
The rear face of the fan frame mid section provides the
front mounts for the engine and the front flange for the
High Pressure Compressor (HPC) section.
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Page 18
June 99
CFM56-5B
EF G
FAN AFT
FAN
ACOUSTICAL FRAME
PANELS
CASING
ABRADABLE
LINER
FAN
FORWARD
ACOUSTICAL
PANELS
TRAINING MANUAL
FAN MID
ACOUSTICAL
PANELS
OUTLET
GUIDE
VANE
FRONT ENGINE
MOUNT
FAN INLET CASE DESIGN
CTC-063-019-01
TOC
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June 99
CFM56-5B
EF G
TRAINING MANUAL
FAN FRAME MODULE (CONTINUED)
The Outlet Guide Vane (OGV) assembly
The fan OGV assembly consists of the inner shroud and
35 twin vanes.
The inner shroud rear flange is bolted to the fan frame
and has 35 apertures to allow passage of the vane inner
platforms.
The vane inner platforms are axially retained by the inner
face of the fan OGV inner shroud.
The vane outer platforms are bolted to the downstream
fan inlet case.
A splitter fairing, which separates the primary and
secondary airflows, is bolted onto the fan OGV inner
shroud forward flange.
There are 2 unplugged holes on the inner shroud,
between the 3 and 4 o’clock positions, to enable
borescope inspection of the booster vane assemblies.
One is located between the OGV’s at the stage 3 vane
assembly and the other at the stage 5 vane assembly.
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Page 20
June 99
CFM56-5B
EF G
OUTLET
GUIDE
VANE
TRAINING MANUAL
OGV
INNER
SHROUD
OUTER
PLATFORM
UNPLUGGED
BORESCOPE
HOLES
OGV
SPLITTER
FAIRING
INNER
PLATFORM
FAN OUTLET GUIDE VANES
CTC-063-020-01
TOC
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June 99
CFM56-5B
EF G
TRAINING MANUAL
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Page 22
June 99
CFM56-5B
EFG
TRAINING MANUAL
HIGH PRESSURE COMPRESSOR SECTION
TOC
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June 99
CFM56-5B
EFG
TRAINING MANUAL
THE HIGH PRESSURE COMPRESSOR (HPC)
The High Pressure Compressor (HPC) is mounted
between the fan frame module and the combustion case.
The HPC, which has 9 stages, increases the pressure of
the air as it passes from stage to stage, to supply the
combustor section.
It consists of the following modules :
- The compressor rotor
- The compressor stator
The compressor stator is made up of two parts and the
front is supported by the fan frame and the rear is
attached to the combustion case.
The HPC has pipe connections that duct bleed air for
both engine and aircraft use.
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Page 2
June 99
CFM56-5B
EFG
TRAINING MANUAL
HIGH PRESSURE
COMPRESSOR FRONT STATOR
HIGH PRESSURE COMPRESSOR
REAR STATOR
HIGH PRESSURE
COMPRESSOR ROTOR
4th. STAGE
BLEED AIR
9th. STAGE
BLEED AIR
HP COMPRESSOR SECTION
CTC-063-021-01
TOC
5th. STAGE
BLEED AIR
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CFM56-5B
EFG
TRAINING MANUAL
THE HIGH PRESSURE COMPRESSOR (HPC)
Borescope ports
The lower stator case has a series of plugged ports to
allow for borescope inspection of the rotor and stator
vanes.
There are 9 borescope inspection ports located at
approximately the 5 o’clock position and they are
numbered S1 thru S9, where S1 is the most forward.
S7, S8 and S9 plugs are double plugs connected by a
shaft. A spring-loaded system enables the outer plug to
drive the inner plug.
Both inner and outer plugs have specific torque values.
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Page 4
June 99
CFM56-5B
EFG
TRAINING MANUAL
TOP VERTICAL
FWD
S1 TO S9
AFT LOOKING FORWARD
CAP
RETAINING
RING
S1 TO S6
BORESCOPE PLUGS
S6 S5 S4 S3S2
S9 S8S7
SHAFT
S1
S7, S8, S9 BORESCOPE
PLUG ASSEMBLY
HPC BORESCOPE PORTS
CTC-063-031-00
TOC
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June 99
CFM56-5B
EFG
TRAINING MANUAL
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Page 6
June 99
CFM56-5B
EFG
TRAINING MANUAL
COMBUSTION SECTION
TOC
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June 99
CFM56-5B
EFG
TRAINING MANUAL
THE COMBUSTION SECTION
The combustion section is located between the High
Pressure Compressor (HPC) and the Low Pressure
Turbine (LPT).
Air from the HPC is mixed with fuel, supplied by 20 fuel
nozzles.
The mixture is ignited by 2 igniter plugs that are located
at the 4 and 8 o’ clock positions.
The front face of the combustor is attached to the rear of
the compressor module.
The rear section of the combustion case houses the HPT
module.
The combustion section also supplies HPC 9th stage
bleed air for both aircraft and engine use.
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Page 2
June 99
CFM56-5B
EFG
TRAINING MANUAL
FUEL NOZZLE x20
IGNITER PLUGS x2
9TH STAGE BLEED AIR
ENERGY
COMPRESSOR
TURBINE
COMBUSTOR DESIGN
CTC-063-022-01
TOC
ANNULAR
COMBUSTION
CHAMBER
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June 99
CFM56-5B
EFG
TRAINING MANUAL
THE COMBUSTION SECTION (CONTINUED)
Borescope ports
There are 4 plugged ports (S12, S13, S14, S15) around
the combustion case, which enable borescope inspection
of the combustion chamber.
Two other ports are available, using the spark igniter
ports S10 and S11, which can also be used to inspect
the High Pressure Turbine (HPT) blades.
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Page 4
June 99
CFM56-5B
EFG
TRAINING MANUAL
BORESCOPE PORT
LOCATIONS
S12
S15
S13
S10
S11
IGNITER
S14
AFT LOOKING
FORWARD
S12
FWD
FWD
S13
S15
S11 IGNITER S10
S14
CTC-063-032-00
TOC
COMBUSTION CASE BORESCOPE PORTS
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June 99
CFM56-5B
EFG
TRAINING MANUAL
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Page 6
June 99
CFM56-5B
EFG
TRAINING MANUAL
TURBINE SECTION
TOC
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June 99
CFM56-5B
EFG
TRAINING MANUAL
TURBINE SECTION
The turbine section provides the necessary power to
drive the compressor rotors. It consists of the :
- High Pressure Turbine (HPT)
- Low Pressure Turbine (LPT)
Engine cooling
Air from the 4th stage of the HPC is ducted through 4
pipes, to cool down the 1st stage of the LPT and the front
cavity.
Air from the HPTCC valve is ducted through 2 pipes, to
cool down the cavity that surrounds the HPT shroud.
High Pressure Turbine (HPT)
The HPT module is housed in the combustion case and
consists of a single stage nozzle that directs the gas flow
from the combustion chamber to the HPT rotor blades that
drive the HPC rotor.
The LPT stage 1 nozzle is also housed in the combustion
case.
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Page 2
June 99
CFM56-5B
EFG
HPC 4th / 9th STAGE
COOLING AIR
TRAINING MANUAL
HPC 4th STAGE
COOLING AIR
LPT STATOR
COMBUSTOR CASE
STAGE 1
LPT NOZZLE
HPT ROTOR
HPT NOZZLE
HPT SHROUD
CTC-063-023-01
TOC
HPT & STAGE 1 LPT NOZZLE ASSY.
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June 99
CFM56-5B
EFG
TRAINING MANUAL
TURBINE SECTION (CONTINUED)
HPT borescope ports
Igniter ports S10 and S11 are used to inspect the HPT
front sections and combustor with a borescope.
Borescope ports S16 and S17, at the aft of the
combustion case at approximately the 5 and 8 o’clock
positions, are used to inspect the trailing edge of the HPT
blades.
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Page 4
June 99
CFM56-5B
EFG
TRAINING MANUAL
S10
S16
FWD
FWD
S17
S11
FWD
S16,S17
HPT BORESCOPE PORTS
CTC-063-033-00
TOC
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Page 5
June 99
CFM56-5B
EFG
TRAINING MANUAL
TURBINE SECTION (CONTINUED)
Low Pressure Turbine (LPT)
The LPT module converts the energy of gasses from the
HPT into the necessary torque to drive the fan and
booster rotor.
The LPT is a 4 stage axial flow turbine that consists of a
rotor and stator assembly.
The LPT module front flange is mounted onto the rear
flange of the combustor module. Its rear flange is
attached onto the LPT frame and its inner flange is
secured onto the LPT shaft.
Fan discharge air is ducted through manifolds that are
provided with orifices, to direct cooling air onto the LPT
outer case.
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Page 6
June 99
CFM56-5B
EFG
TRAINING MANUAL
TURBINE FRAME
LPT ROTOR /
STATOR
ASSEMBLY
UPPER
COOLING
MANIFOLD
TUBE
SUPPORT
AIR MANIFOLD
LPT SHAFT
LOWER
COOLING
MANIFOLD
CTC-063-034-00
TOC
LOW PRESSURE TURBINE MODULE
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June 99
CFM56-5B
EFG
TRAINING MANUAL
TURBINE SECTION (CONTINUED)
There are 5 borescope ports for inspection of the LPT
blades.
Ports S16 and S17, which are located at the 5 and 8
o’clock positions respectively, are used to examine the
LPT stage 1 blade leading edge.
Ports 18, 19 and 20, at the 5 o’clock position, are located
between stages 1, 2 and 3.
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Page 8
June 99
CFM56-5B
EFG
TRAINING MANUAL
BORESCOPE PORT
LOCATIONS
S16,S17
BORESCOPE
PLUGS
S17
S16, S18, S19, S20
AFT LOOKING
FORWARD
FWD
S18, S19, S20
BORESCOPE
PLUGS
S20 S19 S18 S16
CTC-063-035-00
TOC
LOW PRESSURE TURBINE BORESCOPE PORTS
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June 99
CFM56-5B
EFG
TRAINING MANUAL
THE LPT SHAFT MODULE
The LPT shaft located concentrically inside the high
pressure rotor system, connects the fan shaft with the LPT
rotor.
It provides support for the rear of the LPT rotor through the
No.5 bearing, which holds the LPT rotor inside the turbine
frame.
It also vents the engine forward and aft sumps, through
the center vent tube.
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
TOC
72-50-00
BASIC ENGINE
Page 10
June 99
CFM56-5B
EFG
TRAINING MANUAL
TURBINE FRAME
LPT ROTOR
FAN ROTOR
CENTER VENT
TUBE
FAN SHAFT
LPT SHAFT
No.4 BEARING
No.5 BEARING
THE LPT SHAFT MODULE
CTC-063-036-00
TOC
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
72-50-00
BASIC ENGINE
Page 11
June 99
CFM56-5B
EFG
TRAINING MANUAL
THE TURBINE FRAME MODULE
The turbine frame module is one of the engine major
structural assemblies, and is located at the rear of the
engine.It is made up of a hub and an outer casing.
Bolted on the rear flange of the LPT case, the turbine
frame module supports the rear end of the LPT rotor and
the No. 5 oil damp bearing. Its rear flange provides
attachment for the exhaust nozzle and exhaust plug. The
outer casing is equipped with mounts for rear engine
installation on the airframe.
The hub forward side provides support and attachment
for :
- the No. 5 bearing support
- the aft oil sump assembly
The hub aft side provides support and attachment for :
- the flange assembly and, at its center, the flame
arrestor
- the exhaust plug
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
TOC
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BASIC ENGINE
Page 12
June 99
CFM56-5B
EFG
AFT OIL SUMP
ASSEMBLY
TRAINING MANUAL
STRUT
EXHAUST PLUG
(NOT SHOWN)
STUD
OIL INLET
COVER
OIL SUPPLY TUBE
FLAME
ARRESTOR
OIL SUPPLY
TUBE
FLANGE
ASSEMBLY
OIL INLET
COVER
DAMPING
OIL TUBE
SCAVENGE
TUBE
OVERBOARD
SEAL DRAIN
TUBE
FLANGE ASSEMBLY
FLAME ARRESTOR
No.5 BEARING SUPPORT
TURBINE FRAME MODULE
CTC-063-037-00
TOC
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
72-50-00
BASIC ENGINE
Page 13
June 99
CFM56-5B
EFG
TRAINING MANUAL
THIS PAGE INTENTIONALLY LEFT BLANK
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
TOC
72-50-00
BASIC ENGINE
Page 14
June 99
CFM56-5B
EFG
TRAINING MANUAL
ACCESSORY DRIVE SECTION
TOC
EFFECTIVITY
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CFMI PROPRIETARY INFORMATION
72-60-00
BASIC ENGINE
Page 1
June 99
CFM56-5B
EFG
TRAINING MANUAL
ACCESSORY DRIVE SECTION
The accessory drive system is located at the 6 o’clock
position and is accessible when both fan cowlings are
open.
In order to drive the engine and aircraft accessories, part
of the core engine power is extracted through the Inlet
Gearbox (IGB) and transmitted through the following
gearboxes and shafts :
- Radial Drive Shaft (RDS)
- Transfer Gearbox (TGB)
- Horizontal Drive Shaft (HDS)
- Accessory Gearbox (AGB)
At engine start, the accessory drive system transmits
external power from the engine air starter to drive the core
engine.
For maintenance tasks, there is a hand-cranking pad on
the AGB that is used to manually turn the core engine.
EFFECTIVITY
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CFMI PROPRIETARY INFORMATION
TOC
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BASIC ENGINE
Page 2
June 99
CFM56-5B
EFG
TRAINING MANUAL
INLET GEARBOX
(IGB)
RADIAL DRIVE
SHAFT (RDS)
HORIZONTAL
DRIVE SHAFT
(HDS)
ACCESSORY GEARBOX
(AGB)
TRANSFER GEARBOX
(TGB)
CTC-063-026-01
TOC
ACCESSORY DRIVE SECTION DESIGN
EFFECTIVITY
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CFMI PROPRIETARY INFORMATION
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Page 3
June 99
CFM56-5B
EFG
TRAINING MANUAL
THE ACCESSORY GEARBOX (AGB)
The AGB assembly is mounted under the fan inlet case at
the 6 o’clock position and is secured by 2 clevis mounts.
The AGB consists of a gear train that reduces and
increases the rotational speed to drive various engine
and aircraft accessories.
The AGB’s rear face connects with the Horizontal Drive
Shaft (HDS) coupling tube and provides mounting pads
for :
- The fuel pump
- The starter
- The N2 speed sensor
The AGB’s front face has mounting pads for the following
equipment :
Some of the accessories are installed on the AGB
through Quick Attach/Detach (QAD) rings.
- Lube unit
- Hydraulic pump
- Hand-cranking drive
- Control alternator
- Integrated Drive Generator (IDG)
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
TOC
72-60-00
BASIC ENGINE
Page 4
June 99
CFM56-5B
EFG
TRAINING MANUAL
CLEVIS MOUNT
FUEL PUMP/HMU PAD
N2 SPEED SENSOR
MOUNTING PAD
LUBRICATION
UNIT PAD
HORIZONTAL
DRIVE COUPLING
TUBE
STARTER PAD
HYDRAULIC PUMP PAD
FWD
HANDCRANKING PAD
CLEVIS MOUNT
CONTROL ALTERNATOR PAD
IDG PAD
ACCESSORY GEARBOX HOUSING
CTC-063-027-00
TOC
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
72-60-00
BASIC ENGINE
Page 5
June 99
CFM56-5B
EFG
TRAINING MANUAL
THE ACCESSORY GEARBOX (CONTINUED)
Sealing
Sealing of the AGB is provided by 2 configurations of
carbon-contact seals :
- Magnetic type
- Spring-loaded type
Magnetic seals
The magnetic-type seal consists of :
- a non-magnetic housing, which contains a
magnetized mating ring with a polished face and a
retaining ring.
- a rotating seal with carbon material held in a rotating
ring.
This type of seal can be used on the following pads :
- Integrated Drive Generator (IDG)
- Hydraulic pump
- Fuel pump
EFFECTIVITY
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CFMI PROPRIETARY INFORMATION
TOC
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BASIC ENGINE
Page 6
June 99
CFM56-5B
EFG
(ASSEMBLED)
TRAINING MANUAL
(DISASSEMBLED)
NON MAGNETIC
SEAL HOUSING
MAGNETIZED RING
RETAINING
RING
O-RING
SEALS
STATIC PART
ROTATING
PART
CARBON CONTACT
FACE
O-RING SEAL
MAGNETIC SEAL
CTC-068-028-01
TOC
LAPPED OR POLISHED
CONTACT FACE
EFFECTIVITY
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BASIC ENGINE
Page 7
June 99
CFM56-5B
EFG
TRAINING MANUAL
THE ACCESSORY GEARBOX (CONTINUED)
Starter drive pad seal
On the starter drive pad only, a different configuration of
magnetic seal is used.
It has a thrust ring, which also acts as a thermal
exchanger, installed in between the mating ring and
retaining ring.
EFFECTIVITY
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CFMI PROPRIETARY INFORMATION
TOC
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BASIC ENGINE
Page 8
June 99
CFM56-5B
EFG
TRAINING MANUAL
(ASSEMBLED)
STATIC PART
O-RING SEAL
THRUST THERMAL
EXCHANGER
OIL DRAINING
HOLES
ROTATING PART
O-RING SEAL
(DISASSEMBLED)
STATIC PART
NON MAGNETIC
SEAL HOUSING
RETAINING RING
THRUST RING
CARBON
CONTACT FACE
MAGNETIZED
RING
LAPPED OR POLISHED
CONTACT FACE
CTC-063-029-01
TOC
MAGNETIC SEAL (STARTER DRIVE ONLY)
EFFECTIVITY
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CFMI PROPRIETARY INFORMATION
72-60-00
BASIC ENGINE
Page 9
June 99
CFM56-5B
EFG
TRAINING MANUAL
THE ACCESSORY GEARBOX (CONTINUED)
Spring-loaded seals
Spring-loaded seals have a rotating mating ring with 4
lugs that engage in corresponding slots machined in the
gear shaft bearing.
A housing, which contains the spring-loaded seal,
ensures constant contact between the polished face and
the carbon seal element.
This type of seal can be used on the following drive pads:
- Integrated Drive Generator (IDG)
- Hydraulic pump
- Starter
- Fuel pump
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
TOC
72-60-00
BASIC ENGINE
Page 10
June 99
CFM56-5B
EFG
TRAINING MANUAL
CARBON CONTACT FACE
(DISASSEMBLED)
(ASSEMBLED)
O-RING
SEAL
O-RING
SEALS
STATIC PART
MATING
RING
ROTATING
PART
LUGS
LAPPED OR POLISHED
CONTACT FACE
SPRING LOADED SEAL
CTC-063-030-01
TOC
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
72-60-00
BASIC ENGINE
Page 11
June 99
CFM56-5B
EFG
TRAINING MANUAL
THIS PAGE INTENTIONALLY LEFT BLANK
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
TOC
72-60-00
BASIC ENGINE
Page 12
June 99