LEAP-1A Component Identification [PDF]

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Powerplant Line & Base Maintenance LEAP-1A Component Identification Answer Book

V0 - 611 - Level 1

This publication is for Training Purposes Only. It was developed based on the latest data available at the time of edition. This manual shall not be used as a reference for any maintenance practices and specifications and will not be updated. For authorized maintenance practices and specifications, consult the relevant maintenance publications. The contents of this manual is Snecma proprietary information. The manual is supplied in confidence and the commercial security of its contents must be maintained. Therefore, none of the information may be disclosed to other than the recipient. It shall not be used or reproduced without the express consent of Snecma, including, but without limitation, it shall not be used in the creation, manufacture, development or derivation of any repairs, modifications, spare parts, design or configuration changes or to obtain government or regulatory approval to do so. If consent is given for reproduction in whole or in part, this notice shall appear in any such reproduction in whole or in part. This manual must not be used for any purpose other than that for which it is provided. Copyright 2014 Snecma

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Powerplant Line & Base Maintenance LEAP-1A

Powerplant

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AIR INTAKE COWL

- OPTIMIZES ENGINE AIR INTAKE - HOUSES NACELLE ANTI ICE DUCT - PROVIDES ENGINE NOISE REDUCTION

2

FAN COWL DOOR (FCD)

- ENSURES AERODYNAMIC SHAPPING OVER THE FAN AERA - ENABLES ACCESS FOR MAINTEANCE AND SERVICING

3

LATCH DETECTION FLAG

SIGNALS INCORRECT LATCHING OF LATCH NO.1

5

INTEGRATED DRIVE GENERATOR (IDG) ACCESS DOOR

ENABLES IDG ACCESS FOR OIL LEVEL INSPECTION AND SERVICING

4

STARTER MANUAL OVERRIDE ACCESS

ENABLES ACCESS TO THE STARTER AIR VALVE (SAV)

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THRUST REVERSER (T/R) ACTUATOR

DEPLOYS T/R TRANSCOWL

1

PRIMARY LOCK PROXIMITY SENSORS

PROVIDE LINE OF DEFENSE AGAINST INADVERTENT T/R DEPLOYEMENT

4

TRANSCOWL PRESSURE SEALS

- PREVENT AIR INGRESSION INTO THE CAVITY - PREVENT LOSS OF AERODYNAMIC EFFICIENCY

3

DIRECTION CONTROL UNIT (DCU)

CONTROLS HYDRAULIC FLOW TO ACTUATORS

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THRUST REVERSER (T/R)

- DUCTS THE SECONDARY AIRFLOW - ALLOWS REVERSE THRUST - ENCLOSES THE ENGINE CORE

3

THRUST REVERSER (T/R) CASCADES

REDIRECT SECONDARY AIRFLOW DEFLECTED BY THE BLOCKER DOORS

4

EXHAUST NOZZLE

PROVIDES SURFACES TO GUIDE THE PRIMARY AND SECONDARY FLOWS

5

EXHAUST PLUG

GUIDES PRIMARY AIRFLOW

6

CENTRAL VENTILATION TUBE (CVT)

SUMP(A) VENT

1

FAN COWL STRAKES

PREVENT TURBULENT AIRFLOW ON WING

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AFT MOUNT

ALLOWS POSITIONING AND SUPPORT OF THE ENGINE REAR AREA

1

THRUST REVERSER (T/R) BLOCKER DOORS

DIVERT SECONDARY AIRFLOW

3

CORE DRAIN MAST

PORTS OVERBOARD ALL FLUID LEAKS FROM THE VARIOUS ACCESSORIES OR ENGINE SYSTEMS

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ENGINE LEFT HAND SIDE (LHS) DRAIN PIPE

PORT OVERBOARD FUEL LEAKS FROM: - HPTACC & LPTACC ACTUATORS - LEFT VBV, VSV, MTC ACUTATORS

2

ENGINE RIGHT HAND SIDE (RHS) DRAIN PIPE

PORTS OVERBOARD FUEL LEAKS FROM: - TBV & SB/BAI - RIGHT VBV, VSV, MTC ACUTATORS

3

PYLON LEFT HAND SIDE (LHS) DRAIN PIPE

PORTS OVERBOARD ALL FLUID LEAKS FROM THE PYLON LHS

4

PYLON RIGHT HAND SIDE (RHS) DRAIN PIPE

PORTS OVERBOARD ALL FLUID LEAKS FROM THE PYLON RHS

5

(B) SUMP DRAIN PIPE

PORTS OVERBOARD OIL LEAKS FROM THE (B) SUMP

6

(A) SUMP DRAIN PIPE

PORTS OVERBOARD OIL LEAKS FROM THE (A) SUMP

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ELECTRIC TERTIARY LOCK (ETL)

PROVIDES THE THIRD LINE OF DEFENSE AGAINST INADVERTENT TRANSCOWL DEPLOYEMENT

3

TERTIARY LOCK HARNESSES

EXCHANGE DATA FROM BOTH PROXIMITY SENSORS AND ETL WITH ELECTRONIC ENGINE CONTROL (EEC) CHANNELS

2

TERTIARY LOCK PROXIMITY SENSORS

DETECT THE ETL STATUS (LOCKED/ UNLOCKED)

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THRUST REVERSER (T/R) COWL LATCHES

- SECURE THE T/R HALVES TOGETHER - ADJUST LATCH TENSION

3

LATCH ACCESS DOORS

PROVIDE ACCESS TO THE T/R COWL LATCHES

1

THERMAL BLANKET

PROVIDES THERMAL AND FIRE PROTECTION OF COWLS

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ENGINE FORWARD MOUNT & THRUST LINKS

- ALLOW POSITIONING AND SUPPORT OF THE ENGINE FRONT AREA - TRANSMIT THRUST FROM THE ENGINE TO THE PYLON

3

THRUST REVERSER (T/R) COWL OPENING ACTUATOR

OPENS T/R COWL DOOR

4

THRUST REVERSER (T/R) HOLD OPEN ROD (HOR)

ALLOWS EACH T/R COWL DOOR TO BE SECURED IN AN OPEN POSITION

2

ENGINE KIT

- ENSURES AN AERODYNAMICAL CONTINUITY OF THE SECONDARY FLOWPATH - SUPPORTS VARIABLE BLEED VALVE (VBV) DUCTS - SUPPORTS ACTIVE CLEARANCE CONTROL AIR PICKING

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FAN COWL LATCHES

SECURE THE TWO FAN COWL DOOR HALVES TOGETHER

4

FAN COWL DOOR (FCD) HOLD OPEN ROD (HOR)

ALLOWS EACH FCD TO BE HELD IN AN OPEN POSITION

6

NACELLE ANTI-ICE (NAI) ACCESS DOOR

PROVIDES ACCESS TO NAI DUCTS

2

T12 ACCESS DOOR

PROVIDES ACCESS TO THE T12 PROBE FOR MAINTENANCE TASKS

3

AIR SCOOP

PROVIDES COLD AIR INTO THE FAN AERA

7

FAN DRAIN MAST

PORTS OVERBOARD ALL FLUID LEAKS FROM THE VARIOUS ACCESSORIES OR ENGINE SYSTEMS

1

OIL TANK ACCESS DOOR

PROVIDES ACCESS TO THE OIL TANK FOR MAINTENANCE TASKS

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OIL TANK OVERFILL DRAIN PIPE

PORTS OVERBOARD OVERFILLED OIL FROM THE OIL TANK

3

ENGINE DRIVEN PUMP (EDP) DRAIN PIPE

PORTS OVERBOARD HYDRAULIC FLUID LEAKS FROM THE EDP

5

MAIN FUEL PUMP (MFP) DRAIN PIPE

PORTS OVERBOARD FUEL LEAKS FROM THE MFP

4

MANUAL CONTROL COVER DRAIN PIPE

PORTS OVERBOARD OIL LEAKS FROM THE MANUAL CONTROL COVER

2

INTEGRATED DRIVE GENERATOR (IDG) DRAIN PIPE

PORTS OVERBOARD OIL LEAKS FROM THE IDG

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T12 SENSOR

TRANSMITS FAN INLET AIR TEMPERATURE TO ELECTRONIC ENGINE CONTROL (EEC) UNITS

2

FAN BLADES

INCREASE AIR PRESSURE FOR PRIMARY AND SECONDARY AIRFLOW

5

FRONT SPINNER

PROVIDES A SMOOTH AERODYNAMIC AIRFLOW TO THE ENGINE

4

ACOUSTIC SHROUDS

REDUCE NOISE

3

ABRADABLE LINER

PROVIDES A WEAR SURFACE BETWEEN THE FAN CASE AND THE FAN BLADE TIPS

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PLATFORM FRONT SHROUD

- SECURES FAN BLADE PLATEFORMS POSITION - RECEIVES THE FAN BLADE BALANCE WEIGHT

3

FLOW SPLITTER

SEPARATES THE PRIMARY AND SECONDARY AIRFLOW

2

FAN BLADE PLATFORMS

PROVIDE A SMOOTH AERODYNAMIC AIRFLOW

4

AFT ACOUSTICAL PANELS

REDUCE NOISE

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FAN COMPARTMENT TEMPERATURE SENSOR

MEASURES FAN COMPARTMENT OVERHEAT FOR AIR DUCT LEAK DETECTION

1

FAN FIRE DETECTOR SENSOR

DETECTS THE PRESENCE OF FIRE AROUND THE FAN

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MANUAL CONTROL COVER

GIVES ACCESS TO THE MANUAL CONTROL TO ROTATE OR LOCK HP ROTOR

2

INTEGRATED DRIVE GENERATOR (IDG)

SUPPLIES THE AIRCRAFT WITH ELECTRICAL POWER

1

FAN CASE

- PROVIDES FAN BLADE CONTAINEMENT - DUCTS AIRFLOW

4

ACCESSORY GEARBOX (AGB) ASSEMBLY

SUPPORTS AND DRIVES BOTH A/C AND ENGINE ACCESSORIES

5

TRANSFER GEARBOX (TGB) ASSEMBLY

REDIRECTS THE TORQUE FROM INLET GEARBOX (IGB) TO AGB

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PNEUMATIC AIR STARTER (PAS)

CONVERTS PRESSURIZED AIR INTO TORQUE TO ROTATE CORE ENGINE

4

STARTER AIR VALVE (SAV)

SUPPLIES THE PAS WITH AIRFLOW

6

PNEUMATIC AIR STARTER (PAS) MAGNETIC PLUG

ALLOWS MAINTENANCE INSPECTION

3

ENGINE DRIVEN PUMP

DELIVERS HIGH PRESSURED HYDRAULIC FLUID TO THE AIRCRACFT

2

OIL PRESSURE AND TEMPERATURE SENSOR (OPTS)

TRANSMITS ENGINE OIL TEMPERATURE AND PRESSURE TO THE EECs

1

ENGINE OIL LOW PRESSURE SWITCH AND HARNESS

INDICATES A LOW PRESSURE IN THE ENGINE OIL SYSTEM

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SERVO FUEL HEATER (SFH)

HEATS FUEL WITH SUPPLY OIL

4

MAIN HEAT EXCHANGER (MHX)

COOLS THE ENGINE SUPPLY OIL WITH FUEL

1

FAN COMPARTMENT TEMPERATURE SENSOR

MEASURES FAN COMPARTMENT TEMPERATURE FOR AIR DUCT LEAK DETECTION

3

FUEL RETURN VALVE

CONTROLS INTEGRATED DRIVE GENERATOR (IDG) OIL TEMPERATURE

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MAIN FUEL FILTER HOUSING

HOUSES THE FUEL FILTER CARTRIDGE

4

FUEL FILTER CARTRIDGE

FILTERS AND COLLECTS CONTAMINANTS FROM FUEL

5

FUEL FILTER DIFFERENTIAL PRESSURE TRANSDUCER

TRANSMITS FUEL FILTER BYPASS INDICATIONS TO THE EECs

1

INTEGRATED DRIVE GENERATOR (IDG) OIL COOLER

COOLS OIL FROM THE IDG

3

FUEL METERING UNIT (FMU)

METERS FUEL FLOW TO THE COMBUSTION CHAMBER

2

FUEL METERING UNIT (FMU) DIFFERENTIAL PRESSURE TRANDUCER

TRANSMITS FMU STRAINER BYPASS INDICATIONS TO THE EECs

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PERMANENT MAGNET ALTERNATOR (PMA)

PROVIDES ELECTRICAL POWER AND N2 SPEED SIGNAL TO THE EECs

5

LUBRICATION UNIT

PRESSURIZES, FILTERS AND DELIVERS/SCAVENGES OIL TO/FROM THE ENGINE

1

MAIN FUEL PUMP (MFP)

PRESSURIZES FUEL FROM A/C AND DELIVERS IT TO FUEL DISTRIBUTION AND CONTROL COMPONENTS

2

NON RETURN VALVE

PREVENTS THE ENGINE HEAT EXCHANGERS FROM SIPHONING AT ENGINE SHUT DOWN

3

N2 SENSOR

TRANSMITS HP ROTOR SPEED TO THE EECs

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OIL FILTER CARTRIDGE

COLLECTS DEBRIS AND CONTAMINANTS FROM THE SUPPLY OIL

4

SCAVENGE SCREEN PLUGS

COLLECT DEBRIS IN THE SCAVENGE OIL

3

MAGNETIC BARS

COLLECT MAGNETIC PARTICLES IN THE SCAVENGE OIL FOR TROUBLESHOOTING

1

OIL FILTER DELTA PRESSURE (OFDP) SENSOR

TRANSMITS OIL FILTER BYPASS INDICATIONS TO THE EECs

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OUTER OUTLET GUIDE VANE (OGV) PLATEFORMS

PROVIDES AN AERODYNAMIC AND SMOOTH SURFACE FOR THE SECONDARY AIRFLOW

2

OUTLET GUIDE VANES (OGVs)

DIRECT THE SECONDARY AIRFLOW AND PROVIDE A REDUNDANT RADIAL SUPPORT

3

OUTLET GUIDE VANE (OGV) STRUTS

- PROVIDE A REDUNDANT RADIAL SUPPORT AND GUIDE INSIDE EQUIPMENT - DIRECT THE SECONDARY AIRFLOW,

6

SEGMENT SHROUDS

- PROVIDE EXHAUST FOR VARIABLE BLEED VALVE (VBV) FLOW - GUIDE SECONDARY AIRFLOW

4

STRUTS

- HOUSE TUBINGS - DIRECT THE SECONDARY AIRFLOW

1

ENGINE SURFACE AIR COOLING OIL COOLER (SACOC)

COOLS THE ENGINE SUPPLY OIL WITH SECONDARY AIRFLOW

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HIGH PRESSURE TURBINE ACTIVE CLEARANCE CONTROL (HPTACC) VALVE

REGULATES COOLING AIR AROUND THE HPT CASE

2

LOW PRESSURE TURBINE ACTIVE CLEARANCE CONTROL (LPTACC) VALVE

REGULATES COOLING AIR AROUND THE LPT CASE

3

ACTIVE CLEARANCE CONTROL (ACC) DUCTS

SUPPLY ACC MANIFOLDS WITH REGULATED SECONDARY AIRFLOW

4

EDUCTOR VALVE

CONTROLS PRESSURIZATION OF (A) SUMP

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SPLIT CONTROL UNIT/ SERVO VALVE ASSEMBLY (SCU/SVA)

MODULATES FUEL TO THE COMBUSTION CHAMBER AND SUPPLIES FUEL TO ACTUATORS AND VALVES

4

FUEL MANIFOLD PRESSURE TRANSDUCER

TRANSMITS FUEL OUTPUT PRESSURE TO THE EECs

1

T3 SENSOR

TRANSMITS HIGH PRESSURE COMPRESSOR (HPC) AIR OUTLET TEMPERATURE TO THE EECs

2

LEFT VARIABLE STATOR VANE (VSV) ACTUATOR

MOVES THE VSV MECHANISM

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IGNITION LEADS

TRANSMIT ELECTRICAL POWER FROM THE EXCITERS TO THE IGNITERS

1

IGNITERS

PRODUCE SPARKS WITHIN THE COMBUSTION CHAMBER

3

IGNITION EXCITERS

PROVIDE ELECTRICAL ENERGY TO IGNITERS

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EXHAUST GAS TEMPERATURE (EGT) HARNESSES

CONNECT THE EGT SENSORS WITH THE EECs

4

EXHAUST GAS TEMPERATURE (EGT) SENSORS

TRANSMIT THE EGT SIGNAL TO THE EECs

2

TRANSIENT BLEED VALVE (TBV)

RELEASES THE COMPRESSOR TO INCREASE STALL MARGIN AND FLAME OUT MARGIN

1

TRANSIENT BLEED VALVE (TBV) DUCT

DUCTS HPC AIR TROUGH THE TBV OVERBOARD

5

LOW PRESSURE TURBINE (LPT) BORESCOPE PLUGS

PROVIDE ACCESS TO THE LPT FOR INSPECTION

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TURBINE CENTRAL FRAME (TCF) ACCELEROMETER

TRANSMITS ENGINE VIBRATION SIGNALS TO THE EEC CHANNEL A

4

TURBINE CENTER FRAME (TCF) LEFT COOLING MANIFOLD

BLEEDS HIGH PRESSURE COMPRESSOR AIR TO COOL THE TCF

3

COMBUSTOR CASE BORESCOPE PLUG

PROVIDES ACCESS TO THE COMBUSTION CHAMBER FOR INSPECTION

5

CORE FIRE DETECTOR SENSOR

DETECTS THE PRESENCE OF FIRE AROUND THE CORE

2

FUEL NOZZLES

ATOMIZE METERED FUEL INTO COMBUSTION CHAMBER

1

FUEL NOZZLE MANIFOLDS

SUPPLY FUEL NOZZLES WITH METERED FUEL

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RIGHT MODULATED TURBINE COOLING (MTC) VALVE

MODULATES COOLING AIR INTO HPT STAGE 1 BLADES

1

RIGHT MODULATED TURBINE COOLING (MTC) ACTUATOR

MOVES THE RIGHT MTC VALVE

4

START BLEED VALVE - BOOSTER ANTI ICE VALVE (SBV/BAI)

PROVIDES HIGH PRESSURE COMPRESSOR (HPC) AIR TO BOOSTER FOR DE-ICING, AND DECREASES COMPRESSOR PRESSURE DURING STARTING

3

BOOSTER ANTI ICE MANIFOLD TUBING

SUPPLIES THE FLOW SPLITTER WITH HPC AIR

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T25 SENSOR

TRANSMITS HPC AIR INLET TEMPERATURE TO THE EECs

3

N1 SENSOR

TRANSMITS LP ROTOR SPEED TO THE EECs

2

RIGHT VARIABLE BLEED VALVE (VBV) ACTUATOR

MOVES VBV MECHANISM

4

FUEL FLOW TRANSMITTER

TRANSMITS FUEL FLOW MASS RATE TO THE EECs (FLIGHT DECK INDICATING)

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RIGHT VARIABLE STATOR VANE (VSV) ACTUATOR

MOVES THE VSV MECHANISM

2

CORE COMPARTMENT TEMPERATURE (CCT) SENSOR

MEASURES CORE COMPARTMENT OVERHEAT FOR AIR DUCT LEAK DETECTION

3

FUEL TEMPERATURE TRANSDUCER

TRANSMITS FUEL TEMPERATURE TO THE EECs

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ELECTRONIC ENGINE CONTROL (EEC) UNITS

CONTROL THE ENGINE, TRANSMIT FLIGHT DECK INDICATIONS AND MAINTENANCE DATA TO THE AIRCRAFT

4

ENGINE WIRING HARNESSES

TRANSMIT ELECTRICAL SIGNALS

1

ELECTRONIC ENGINE CONTROL (EEC) COOLING BLOWERS

PROVIDE COOLED AIR TO THE EECs

2

COOLING DUCTS

DUCT AMBIENT AIR TO THE EECs

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RATING PLUG

SUPPLIES THE EECs WITH : - ENGINE RATED THRUST - FAN SPEED MODIFIER - HARDWARE CONFIGURATION DATA - HPT DETERIORATION STATE

1

PRESSURE SUB SYSTEM (PSS) BOX AND SENSOR

TRANSMITS AIR PRESSURE INDICATIONS TO THE EECs

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OIL TANK

STORES THE ENGINE OIL

4

OIL LEVEL SENSOR

MEASURES THE QUANTITY OF OIL IN THE TANK

6

OIL DEBRIS MONITORING SYSTEM (ODMS) UNIT

CONDITIONS SIGNAL BEFORE SENDING IT TO THE EECs

2

AIR/ OIL SEPARATOR

REMOVES AIR FROM THE SCAVENGE OIL

3

OIL DEBRIS MONITORING SYSTEM (ODMS) SENSOR

RETAINS MAGNETIC PARTICLES AND SENDS SIGNAL TO THE ODMS UNIT

1

OIL DEBRIS MONITORING SYSTEM (ODMS) HARNESS

CONNECTS THE ODMS SENSOR TO THE ODMS UNITS

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