aircrft engine

CFM56-7B TRAINING MANUAL

COMPONENT IDENTIFICATION

ALL GENERAL CFMI PROPRIETARY INFORMATION Mar 01

This CFMI publication is for Training Purpose 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 the 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. In addition, the technical data therein and the direct product of those data, may be diverted, transferred, exported or disclosed in any manner not provided for by the license without the prior written approval of both the U.S. Government and CFM International




ITEM NO.

IDENTIFY THE LINE, ACCESSORY OR COMPONENT

ITEM NO.

SELECT THE PURPOSE THAT MATCHES THE LINE ACCESSORY OR COMPONENT

Fan blade platform Supplies alignment of the spinner cones and fan blades to the #1 position for engine balancing.

Spinner rear cone Supplies a threaded hole to remove the spinner front cone.

Spinner front cone jack screw hole Supplies containment of the fan blades spacers and the retaining ring.

Balance screw Supplies an aerodynamic surface between the fan blades.

Spherical indent for fan blade #1 Balances engine if vibration limits are incorrect.




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Fan blade platform retention pins Lets extra weight to be added to the fan module for balancing at shop level only.

Fan blade dovetail slot Holds the fan blades and spacers.

Fan disk Holds and gives alignment of the platforms between the fan blades.

Balance weight for the fan disk Holds the fan blades.




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Splitter fairing Divides the secondary and primary airflow.

Stage 1 booster vanes Points the fan discharge airflow.

Outlet guides vanes (OGV’S) The primary airflow entry.




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Fan cowl hold open rod Supports the fan cowl for maintenance.

Spinner rear cone Supplies most of the thrust produced by the engine.

Fan blades Supplies a smooth, inner, aerodynamic flow path for air entering the engine.

Spinner front cone Prevents ice formation.

Fan abatable material Supplies axial retention of the fan blade spacers and location for balance weights.

Engine inlet cowl Keeps minimum clearance between the fan blades and fan case.

T12 sensor Monitors fan inlet temperature.




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Thrust reverser Holds the thrust reverser open for maintenance.

Thrust reverser blocker door Mechanically locks the thrust reverser actuator in the Open position.

Thrust reverser opening actuator

Connection for the hand pump on the thrust reverser opening actuator to open the thrust reverser.

Thrust reverser opening actuator inlet fitting A backup lock for the thrust reverser opening actuator in the Open position.

Thrust reverser opening actuator safety lock Changes the direction of secondary airflow to decrease aircraft speed after landing.

Thrust reverser opening actuator lock collar Changes the direction of secondary airflow.

Thrust reverser translating actuator Controls deploy/stow of thrust reverser.




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RH fan cowl Supplies access for maintenance of the RH side of the fan module.

T12 access panel Supplies an access for servicing the oil tank.

Oil tank filler door Supplies an access to the T12 sensor.




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N1 sensor Sends vibration data to the flight compartment.

Oil quantity transmitter Sends oil quantity data to the flight compartment.

Vibration sensor connector Gives remote pressure servicing (optional) of the oil tank.

Oil tank Releases pressure from the oil tank with the forward sump.

Balance pressure line Sends the oil back to the oil tank

Oil scavenge return line Sends N1 speed information to the EEC and flight compartment.

Fan case

Supplies the forward support structure for the engine core, fan module and forward engine mount.

Oil fill port and oil scupper Steel plate that indicates serial number, thrust ratings, etc.

Engine data plate Gives support for some LRUs and contains fan blade.

Fan frame Supplies a place for oil storage for the engine.

Remote oil filling ports Supplies the opening to fill the oil tank and a drain area if the oil is spilt.

Oil sight glass Supplies the external means of checking the oil quantity inside the oil tank.




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Flexible cooling duct for the EEC Supplies hot air flow in the engine inlet cowl.

Inlet cowl thermal anti-ice valve Sends cooling airflow to the Electronic Engine Control (EEC) Unit.




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EEC Supplies an interface for engine and aircraft systems.

EEC wiring connections harness Supplies the “brain” for engine control.




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EEC shock mount Supplies electronic data that gives information to the EEC for engine configuration.

EEC identification plug (P11) Holds the Electronic Engine Control (EEC) or (ECU)

Air sense line P25 Sends air pressure information to the EEC at station 13 and is optional.

Air sense line PS13 Sends ambient air pressure information to the EEC from station 0.

Air sense line PS3 Sends air pressure information to the EEC from station 25 and is optional.

Air sense line PO Sends air pressure information to the EEC from station 3.




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Upper exciter box Supplies the exciter boxes with aircraft electrical power.

Lower exciter box Supplies the RH igniter plug with electrical power to start combustion.

RH ignition lead Supplies the LH igniter plug with electrical power to start combustion.

LH ignition lead Supplies a path for the electrical energy to reach the RH igniter plug to cause a spark.

115 Vac power supply connection Supplies a path for the electrical energy to reach the LH igniter plug to cause a spark.




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LH fan cowl Mechanical fastener to hold the fan cowls.

LH fan cowl latches Gives access to service the IDG.

IDG access door Supplies protection and aerodynamic airflow over the engine LH fan module area.

EEC air inlet duct Discharge hot airflow from the engine inlet cowl.

Outlet for the inlet anti-ice system Air discharge for the starter.

Fan cowl airflow outlet Supplies cooling air to the EEC.




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Integrated drive generator (IDG) Points air into the engine.

Low pressure turbine major module Supplies electricity for the aircraft.

Inlet cowl Supplies the energy to operate the engine.

Core major module Changes the energy to turn the fan and LPC.

Fan major module Supplies 80% of the thrust to operate the engine.




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QAD ring Supplies an electrical connection for the cockpit oil pressure signal.

Oil level sight glass Gives access to service the IDG oil filter.

IDG Supplies cool oil from the IDG oil coolers to IDG for lubrication.

Phase lead terminal Mechanical fastener to hold the IDG

Disconnect reset ring Supplies the electrical connections for the aircraft electrical systems from the engines.

Electrical connector Lets servicing of the IDG be done from a remote oil supply system.

Charge filter Disconnects and resets the IDG shaft after maintenance.

Pressure fill adapter Supplies access to check oil quantity in the IDG.

IDG oil inlet port Supplies the primary electrical energy for the aircraft electrical systems from the engine.




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IDG fuel/oil cooler

Electrical connection for the differential pressure switch for the engine scavenge oil filter.

IDG fuel/oil cooler IN line Decreases the temperature of the IDG hot oil with fuel from the LP side of the pump.

IDG fuel/oil cooler OUT line Sends cool oil back to the IDG.

Fan frame Sends hot oil to the IDG oil coolers to decrease the temperature.

Differential pressure switch electrical connector Lets the AGB alignment be adjusted.

AGB turnbuckle The support structure for the forward engine mount and the engine.




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IDG air/oil cooler Decreases engine noise.

Aft acoustical panels Uses fan air in a heat exchanger to supply cool air for the IDG oil




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Hydraulic pump Supplies hydraulic fluid to the hydraulic pump.

Hydraulic pump IN line Supplies hydraulic fluid pressure to the airplane systems.

Hydraulic pump OUT line Supplies hydraulic pump operation electrical information to the airplane.

Hydraulic pump electrical connection Sends hydraulic fluid from the hydraulic pump.




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Starter Uses air pressure during engine start to supply N2 rotation

Starter air supply duct Supplies core speed to the EEC and to the airplane systems.

N2 speed sensor Supplies electrical power to the electronic engine control box.

Hand cranking pad Supplies air pressure to the starter.

EEC alternator Supplies N2 rotation by the manual method.




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Starter air valve manual drive Supplies normal supply air pressure to the starter.

Starter air valve Lets the starter air valve be opened manually.




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Hydraulic connector for the pressure line Supplies fuel to the engine fuel pump.

Fuel supply line to the engine Supplies hydraulic fluid to the hydraulic pump.

Electrical connector for the thrust reversers Supplies hydraulic fluid to the airplane.

Hydraulic connector for the supply line Supplies hydraulic fluid to the hydraulic filter.

Thrust reverser actuator Operates the thrust reverser to deploy and stow.

Hydraulic connector for the hydraulic fluid filter. Supplies electrical feedback information about the thrust reversers position.




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Thrust reverser hold open actuator Opens/closes the T/R doors for maintenance.

Thrust reverser opening actuator safety lock collar

Supplies electrical information path to the airplane for fuel flow indication, etc.

Fuel flow transmitter Secures and safeties the actuator.

Fuel flow transmitter electrical connector Gives downstream protection to fuel nozzles.

In-line fuel filter Gives fuel flow information to the airplane for indication.




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Oil temperature sensor electrical connection Supplies electrical path to the aircraft for engine oil temperature indication.

Oil temperature sensor Supplies electrical path to the aircraft for engine oil pressure indication.

Oil pressure sensor electrical connection Supplies electrical information to the aircraft for engine oil temperature indication.

Oil pressure sensor Supplies electrical information to the aircraft for engine pressure indication.

Fan case Supplies fan blade containment and holds some LRUs.




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Accessory Gearbox (AGB) Supplies fuel to the fuel pump.

Transfer Gearbox (TGB) Holds and turns the accessories for the engine.

Main fuel/oil heat exchanger Supplies the N2 drive for the AGB.

Engine fuel supply line (port) Decreases temperature of the engine oil.

Servo fuel heater Increases the temperature of the engine fuel to prevent ice particles entering the engine servo systems.




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Channel B Supplies fuel from the LP fuel pump to the IDG oil cooler.

Channel A Attaches the fuel pump to AGB.

Airframe shutoff (HPSOV) feedback Supplies the fuel to the engine fuel systems.

Hydromechanical Unit (HMU) Supplies the hydraulic muscle to operate the servo systems.

Fuel pump Transmits an HPSOV position signal to the EEC, then to the ENGINE CLOSED light.

Fuel line Electrical connection for EEC channel B.

QAD ring Electrical connection for EEC channel A.

Low pressure stage fuel pump inspection plug LP stage pump impeller inspection access




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Oil scavenge filter Filters fuel from the LP pump.

Oil scavenge filter lock release Locks the oil filter and prevents rotation.

Fuel filter Gives pressure information to signal oil filter clogging.

Fuel filter drain plug Supplies pressure information to signal fuel filter clogging.

Fuel filter differential pressure switch Filters oil from the engine oil return.

Oil filter differential pressure switch Lets the AGB alignment be adjusted.

AGB turnbuckle Lets the engine fuel filter be drained.




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Lubrication unit Filters the oil.

Magnetic chip detector bayonet slot Gives access to inspect for sumps debris

Magnetic chip detector Gives a clogging indication by a red pin that pops out if the supply oil filter clogs.

Supply oil filter pop-out indicator Supplies alignment for proper installation.

Pressure oil supply filter Supplies the oil for the engine AGB.

AGB oil supply line Gives the oil supply and return for the engine oil system.

Scavenge oil filter unlocking lugs Lets the scavenge oil filter be removed with a tool




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Engine oil supply line Sends oil from the engine aft sump.

Rear sump scavenge oil line Sends oil from the engine forward sump.

Forward sump scavenge oil line Sends oil from the engine AGB and TGB.

AGB TGB scavenge oil line Supplies the oil to the engine sumps and accessories.




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Debris monitoring system chip detector Supplies the CDU information on oil system contamination in the AGB, TGB, forward and aft sumps.

Debris monitoring system chip detector lead Supplies the electrical path to the junction box then to the airplane CDU.




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Debris monitoring system junction box (optional) Oil tank scupper drain.

Debris monitoring system chip detector lead Sends the CDU data on oil system contamination in the AGB, TGB, forward and aft sumps.

Drain line The electrical path to the junction box then to the airplane CDU.




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Anti-leakage valve Supplies the lubrication unit with oil.

Oil supply line Lets removal of the lubrication unit occur without draining the oil tank.

Oil pressure line Supplies pressurized oil to keep the anti-leakage valve open.




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RH VBV actuator drain line

LH VBV actuator drain line

RH VSV actuator drain line

LH VSV actuator drain line

Transient bleed valve drain line

HPTACC valve drain line

LPTACC valve drain line




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VBV open line Supplies the fuel pressure to operate the TBV.

VBV close line Supplies the fuel pressure to close the VBV doors.

VSV rod line Holds the forward part of the engine.

VSV head line Supplies the fuel pressure to operate the LPTACC valve.

Transient bleed valve line Supplies the fuel pressure to operate the HPTACC valve.

HPTACC valve line Supplies the fuel pressure to open the VSV’.

LPTACC valve line Supplies the fuel pressure to close the VSVs.

HMU Supplies the reference pressure to operate some valve.

PCR line Supplies the fuel pressure to close the BSV.

Burner staging valve line Supplies the fuel pressure to open the VBV doors.

HPSOV electrical connector Supplies servo system fuel input to operate engine components and regulates fuel for nozzles.

Fan frame Supplies the electrical input to operate the HPSOV.




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Forward sump vent line Supplies the housing for the 9 o’clock tube bundle.

Transfer Gearbox Supplies the air signal to operate the engine oil pressure indicator.

Fan frame strut fairing Relays the N2 drive for the AGB.




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Engine high pressure bleed air regulator Supplies the high pressure customer bleed air control.

LH VBV actuator Supplies the mechanical drive power to operate the VBVs.




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Fan duct panel Supplies the attachment support for the thrust reverser system and core cowl air sealing.

Outlet guide vanes Supplies the cover over the VBV and the air outlet when they are open.

Internal V-groove panel Changes the direction of the air out of the fan.

Fan frame strut Holds and gives rigidity to the fan frame.




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Variable bleed valve door Supplies the booster air control into the core to prevent a stall.

Variable bleed valve actuator connecting rod Fuel pressure to open the VBVs.

Variable bleed valve actuator drain line Fuel pressure to close the VBVs.

VBV actuator LVDT position feedback connector

Changes the hydraulic actuator movement into a mechanical movement, to open and close the VBVs.

VBV actuator rod line (close)

Changes the hydraulic actuator movement into an electrical position feedback signal to the EEC.

VBV actuator head line (open) Drains the fuel in case of actuator seal leakage.

LH VBV actuator One of the muscles to open the VBV doors.




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Variable stator vane bellcrank

Changes the hydraulic actuator movement into a mechanical movement, to open and close the VSVs.

Variable stator vane actuator Changes the hydraulic fluid to a mechanical force to move the bellcrank assembly.

High pressure compressor forward stator case. Shows the dimension of the core for modular maintenance.

Metal core measurement placard Supports the HPC stators.




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Variable stator vane stage 1 Prevent HPCR core stalls and improves efficiency of the engine.



Inlet guide vanes Prevent HPCR core stalls and improves efficiency of the engine.




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Variable bleed valve door Supplies air to keep the LPT turbine stator case cool.

Fan duct panel (removed) Supplies the booster air control into the core to prevent a stall.

LPT air inlet scoop Supplies the cover over the VBV and an air outlet when VBVs are open.




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HPT shroud support Supplies stages 4 and 9 cooling air to the HP turbine shroud support.

HPT air duct Supplies structural strength to the HPT shroud.

HPTACC valve Controls the clearance inside the engine between the HPT rotor and HPT shroud.




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HPTACC valve 9th stage bleed air duct Supplies low pressure bleed air for HPT rotor and HPT shroud clearance control.

HPTACC valve 4th stage bleed air duct Supplies high pressure bleed air for HPT rotor and HPT shroud clearance control.

HPTACC electrical connection Supplies the hydraulic pressure to move the HPTACC valve.

HPTACC valve fuel manifold Supplies the valve position feedback to the EEC.

FFCCV electrical connection Supplies vibration monitoring data to the AVM.




FUEL, CONFIGURATION 1 (BSV)

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Fuel spray shield Supplies the fuel flow in the combustion chamber.

(SAC) fuel manifold Supplies protection from fuel going all over the engine if a leak occurs.

(SAC) fuel manifold Fuel manifold

(SAC) Fuel nozzle Deactivated staging valve.

(SAC) Burner staging valve (deactivated) Fuel manifold




FUEL, CONFIGURATION 2 (NO BSV)

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(SAC) fuel nozzle Sensor line for stage 9 air called compressor discharge pressure (CDP)

PS3 line (also called CDP) Sends fuel in a spray into the combustor.

(SAC) fuel supply manifolds Prevents leakage if the B nut comes loose.

Fuel nozzle drain shroud Supplies fuel into the staged and unstaged manifolds.





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LH ignition lead Supplies the electrical path for the spark in the combustion chamber.

RH ignition lead Supplies access to the combustion chamber to be inspected.

Combustor borescope plug Supplies the electrical path for the spark in the combustion chamber.




DAC CONFIGURATION

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S 9 borescope plug Controls the fuel flow between the staged and unstaged DAC fuel nozzles.

S8 borescope plug Supplies the electrical path to the EEC for position of the BMV.

S7 borescope plug Supplies access to the HPC for inspection.



(DAC) burner modulating valve Supplies access to the HPC for inspection.

(DAC) burner modulating valve electrical connection

Supplies access to the HPC for inspection.




DAC CONFIGURATION

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LPT air duct Controls the fan air to the LPT case.

LPTACC valve Ducts cooling air to the HPT shroud support.

LPT nozzle cooling manifold 1 of 4 tubes that cool the LPT nozzles with stage 4 air.

HPT air duct Supplies the fan air path to the LPT case.




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High stage bleed air valve Supplies cooling air to the ignition leads.

LH ignition lead Supplies stage 9 bleed air to the airplane systems.

RH ignition lead Supplies the path for electricity to the LH igniter plug.

Ignition lead cooling manifold Supplies the path for electricity to the RH igniter plug.

T25 sensor lead Transmits HPC inlet temperature data for the control logic.




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Transient bleed valve actuator Cools the ignition leads.

Ignition lead cooling manifold Controls stage 9 air bleed to ease engine acceleration.

TBV electrical connection Supplies the electrical path to the EEC for position of the TBV.

Transient bleed valve Operates the TBV butterfly.




DAC CONFIGURATION

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High stage bleed air valve Controls stage 9 bleed air to the airplane.

Stage 5 bleed air check valve Fuel nozzle with a gold band (DAC).

(DAC) cooling fuel nozzle Fuel nozzle with a blue band (DAC).

(DAC) bleed fuel nozzle Prevents stage 9 bleed air reverse flow into the HPC.

(DAC) fuel manifolds Supplies access to the HPT rotor trailing edge.

Borescope plug Holds the HPT shroud.

HPT shroud support Supplies fuel into three manifolds the pilot, main 1, and main 2 (DAC).




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Fire loop detection sensor Supplies data to the EEC on the HPT shroud support temperature.

HPTCC sensor Senses engine fires and sends the data to the flight compartment.





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Combustion case Supplies data to the EEC on the CDP temperature.

T3 sensor Supports the combustion chamber.

Fuel manifold Supplies fuel flow in the combustion chamber.

Fuel nozzle Sends fuel in a spray into the combustor.




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Turbine rear frame Sends information to the EEC on LPT exhaust temperature.

T5 sensor (optional) Supplies location for tooling attachment.

Turbine rear frame support Supports the LPT case and attaches to the rear engine mount.




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Oil supply line Supplies oil to the rear sump.

Oil scavenge line Scavenges the oil from the rear sump.

LPT case drain Drains the LPT case.




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LPT cooling tubes manifold Sends fire data to the flight compartment.

EGT harness and probes Monitors the T49.5 station and sends the data to the EEC and flight compartment.

Fire loop detection sensors

Supplies cooling air to the LPT manifold impingement holes to control clearance between the LPTR blades and case shrouds.




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Precooler air valve Puts out engine fires.

Thrust bar Controls the quantity of fan air directed to be precooler.

Fire bottle discharge distribution tubes Transmits the torque between the engine and aircraft.




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Precooler Transmits the precooler pressure to the A/C systems.

Precooler downstream pressure sense line Transmits the precooler temperature to the A/C systems.

Precooler 450 degree F temperature sense line Decreases the temperature of the bleed air for the airplane systems.




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Primary exhaust nozzle Contains the engine fires.

Rear engine mount Directs the primary airflow.

Labyrinth seals Supports the engine.




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Primary exhaust nozzle Primary airflow inner duct and sumps venting.

Exhaust plug Makes sure the primary airflow is smooth.

Thrust reverser Transmits thrust from engine to aircraft.

Thrust link Decreases A/C speed after landing.




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Primary exhaust Keeps fire out of the engine center vent tube.

Flame arrestor Removes primary air exhaust.

Thrust reverser

Points the secondary airflow forward and outboard to decrease the speed of the airplane with up to 80% of fan air.




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aircrft engine

Documents

component item

component fan cowl

fan module

fan blades spacers

line accessory

training purpose

fan disk holds

fan discharge airflow