cf34-10 compidmarchprint

CF34-10E TRAINING MANUAL COMPONENT IDENTIFICATION

EFFECTIVITY

Embraer 190/195 GENERAL GEAE PROPRIETARY INFORMATION Mar 06

Copyright 2005 GE Transportation

Published by: GE Aircraft Engines

Customer Training Services Customer Technical Education Center

123 Merchant Street Cincinnati, Ohio 45246

This publication is for TRAINING PURPOSES ONLY. This 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 Manual. This product is considered GE Aircraft Engines technical data information and therefore is exported under U.S. Government Export License Regulations. It is issued to the user under specific conditions that the data, or it’s product may not be resold, diverted, transferred, transshipped, reexported, or used in any other country without prior written approval of the U.S. Government. The information contained in this document is disclosed in confidence. It is the property of GE Aircraft Engines and shall not be used (except for evaluation), disclosed to others, or reproduced without the expressed written consent of GEAE. If consent is given for reproduction in whole or in part, this notice shall appear on any reproduction, in whole or in part. The foregoing is subjected to any rights the U.S. Government may have acquired as such information.


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COMPONENT IDENTIFICATION EXERCISE General Instructions Enter the item number in the left hand column that corresponds with the identification of the line, accessory or component shown in the picture. Then enter the item number in the right hand column that corresponds with the purpose for the line, accessory, or component shown in the picture. The arrow positioned around the clock is indicating from what angle the photograph was taken.


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ITEM NO.

IDENTIFY THE LINE, ACCESSORY OR COMPONENT

ITEM NO.

SELECT THE PURPOSE THAT MATCHES THE LINE ACCESSORY OR COMPONENT

5 Fan blade 3 Access for removing fan blades.

1 Outlet guide vane

1 Directs fan exhaust airflow.

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ENTER NUMBER

HERE

ENTER NUMBER

HERE

ARROW INDICATES CLOCK POSITION OF PHOTO (ALF)


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ITEM NO.


ITEM NO.


Fan Systems Drain Mast Assembly Produces an decelerating effect on the aircraft by forcing the fan airflow outward and forward

Fan Cowl Removes fluids and vapors from components on the engine aft fire zone.

Thrust Reverser Provides a means to open the starter valve in the event of a operational failure

Bullet Nose Removes fluids and vapors from components on the engine forward fire zone.

Starter Override Access Provides a smooth surface to maintain a clean airflow around the engine fan case

Core Systems Drain Mast Assembly Anti-iced from an engine air supply

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ITEM NO.


ITEM NO.


Primary Exhaust Nozzle Combined with the primary exhaust nozzle, provides a fixed area annulus for exhausting the core engine gas stream flow

Aft Core Cowl An integral component of the thrust reverser

Oil Servicing Access Door Provides access to oil tank

Inlet Cowl Combined with the exhaust center body, provides a fixed area annulus for exhausting the core engine gas stream flow

Aft Exhaust Center Body Directs air to the engine fan

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ITEM NO.


ITEM NO.


T12 Sensor Designed to help prevent ice and FOD damage in the core engine

Spinner Cone Flows cooling air through the discharge on the ground and from the inlet in flight

Fan Blades Provides engine inlet air temperature for use in FADEC control calculations.

FADEC Cooling Provides the majority of the engine thrust

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ITEM NO.


ITEM NO.


Anti Ice Swirl Nozzle Inspection Door Provides smooth flow path into the engine inlet

Bullet Nose Provides access to inspect or replace swirl nozzle

Nose Anti Ice Exhaust Provides overboard discharge for hot air

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ITEM NO.


ITEM NO.


IDG Harness Provides motive flow to aircraft fuel tanks

Hydraulic Return From A/C (pump supply) Supplies path for hydraulic fluid from the case drain

Hydraulic Case Drain Air source from ground power unit, APU or opposite engine to starter control valve

Fuel Flow to Aircraft Ejector Pump Supplies electrical path for power to operate aircraft systems

Starter Air Supply Fuel source for operation of all engine systems and combustion

Hydraulic Supply to A/C Supplies hydraulic fluid under pressure to various aircraft and engine systems

Aircraft Fuel Supply to Pump Flow path for return of hydraulic fluid from various engine and aircraft systems

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ITEM NO.


ITEM NO.


Permanent Magnet Alternator (PMA) Supplies cooled oil to the IDG

Oil Supply from Tank Transfers hot IDG oil to be cooled

Aft Scavenge Return Allows access for inspection of forward and aft scavenge screens

Nose Inlet Anti Ice Valve Supplies oil to pump after used in cooling of bearings #1,2 and 3

Forward Scavenge Return Provides electrical power for the FADEC at N2 speeds above 50 percent

Scavenge Screen Removal Ports Supplies oil to the pressurizing element of the pump

IDG Cooling Oil to Air/Oil HX Provides fifth stage air for anti icing of the nose inlet cowl

IDG Cooling Oil from Fuel/Oil HX Supplies oil to pump after used in cooling of bearings #4 and 5

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ITEM NO.


ITEM NO.


Starter Valve Allows for the manual opening of the starter valve in the event of a failure.

Starter Valve Override Provides a source of air required for the operation of the anti-ice valve

Muscle Supply Air to Nose Anti Ice Valve Allows pressurized air from either a Ground Power Unit, Auxiliary Power Unit, or the AMS to enter the starter

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ITEM NO.


ITEM NO.


Transfer Gearbox Drives the mechanical accessories needed to supply the engine with fuel, lubrication, and electrical power

Engine Driven Hydraulic Pump Provides electrical power needed by the aircraft.

Air Supply to Nose Anti Ice Transfers power from the inlet gearbox to the Accessory Gearbox

AGB Provides the hydraulic pressure to operate the aircraft systems

Oil Filter Housing Uses pressurized air to accelerate the engine to speed a where combustion light off and self-sustaining RPM occur

Turbine Air Starter Provides support for the oil filter and filter bypass indicator

Fuel Pump Contains three elements supplying fuel pressure to operate different engine and aircraft systems

IDG Supplies 5th stage air for anti icing

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ITEM NO.


ITEM NO.


Oil Pressure Transmitter Maintains oil circulation in the engine and returns scavenged oil to the oil tank

Lube and Scavenge Pump Calculates the differential between oil supply pressure and internal AGB to display a caution on EICAS

Oil Filter impending Bypass Sensor Monitors the differential pressure between the lube filter inlet and the lube filter discharge.

Scavenge oil return line to oil tank. Provides a differential oil pressure of filter downstream and gearbox pressure for system pressure readout on EICAS.

Chip Detector Path of forward sump, aft sump and gearbox return oil to the oil tank.

Oil Filter Module Provides mounting for the filter, filter impending bypass sensor and bypass valve.

Low Oil Pressure Switch Traps magnetic particles suspended in the scavenge oil to warn of impending bearing failure.

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ITEM NO.


ITEM NO.


Pressure Regulating & Shut Off Valve (PRSOV) Provides simultaneous movement of the IGV

and stage 1-3 variable guide vanes

VSV Actuating Shaft Stage 9 pressure which is used to give an indication of bleed flow to the FADEC through the Delta P3 sensor

High Pressure Regulating & Shut Off Valve (HPSOV) Prevents high pressure air from back flowing

into fifth stage

Ninth Stage Bleed Air source for nose anti-ice

Low Stage Bleeed Check Valve Low pressure/temperature air source for aircraft systems operation

4th Stage Air Supply to LPT Modulates high pressure air into bleed system

Stage 9 Bleed Flow Sense Line to Delta P3 Sensor (Low Side) Isolates aircraft bleed system

TAI Air Supply Line Source of cooling air for the LPT stage one nozzle

Stage 9 Bleed Pressure Line to Delta P3 Sensor (High Side) High pressure/temperature air source for

aircraft systems operation

Fifth Stage Bleed Venturi throat pressure to the Delta P3 sensor

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ITEM NO.


ITEM NO.


Fire Detection Loop Collects fuel or oil leakage and vents safely overboard

Forward Drain mast A pneumatic sensing device which provides for fire detection due to gas expansion and electrical pressure switch closure.

OVG Torque Box Latch Primary pull latch for mating the thrust reverser cowls

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ITEM NO.


ITEM NO.


OGV’s Carries high voltage capacitance discharge power to 4:00 igniter

Ignition Lead Carries high voltage capacitance discharge power to 8:00 igniter

Fan Cooling Air Source of cooling air used for LPT active clearance control

Ignition Lead Straightens fan discharge air into core flow path

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ITEM NO.


ITEM NO.


Fourth stage cooling air Directs mixed temperature air to HPT shrouds

Turbine Rear Frame Supports the LPT rotor and structural stator loads and transmits the loads to the engine mount system

LPT Cooling Manifold Source of cooling air for the LPT stage one nozzle

Inter Turbine Temperature Assembly (ITT) Distributes fan air evenly over LPT case

HPTCC Manifold

Output signal is sent to the FADEC where the signal is processed and sent digitally to a cockpit indicator for monitoring engine temperature

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ITEM NO.


ITEM NO.


HPTCC valve Distributes and atomizes the metered fuel from the FMU and directs it into the combustor

Ninth Stage Bleed for HPTCC Provides the FADEC with compressor discharge (PS3) airflow temperature

Fourth Stage Bleed for HPTCC Modulates the supply of 4th and 9th-stage compressor bleed air to the engine’s high-pressure turbine case

HPTCC Manifold Provides the electrical spark needed to start or maintain combustion

Fuel Injector Source of hot air used to maintain a optimum clearance between the HPT blades and shrouds

Igintor Plug Distributes fuel flow evenly to all fuel injectors

Fuel Manifold Source of cool air used to maintain a optimum clearance between the HPT blades and shrouds

T3.0 Measures HPT case shroud temperature and is an input to the HPT clearance control algorithm

TCase Directs mixed temperature air to HPT shrouds

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ITEM NO.


ITEM NO.


Fuel Filter Maintains a positive pressure in the oil tank to help prevent oil foaming and ensure a positive feed to the lube pump at all altitudes

Oil Tank Pressurizing Valve Provides electrical indication to the aircraft that the filter element is contaminated

Fuel Filter Impending Bypass Switch Removes contaminants from the engine fuel before used by the FMU

Fuel to Fuel metering Unit Filtered fuel supplied to the FMU for combustion and IDG cooling

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ITEM NO.


ITEM NO.


P3.0 Input Supplies a source of atmospheric pressure for use in the FADEC

FADEC Mates to the fan cowl as a source/discharge for FADEC cooling air

FADEC Cooling Air Supply /Discharge(cowl) Allows for water to escape from the FADEC cooling plenum

P0 Input Supplies a source of combustor inlet pressure for use in the FADEC

FADEC Cooling Air Supply/Discharge (fan) Inlet air routed as a source/discharge for FADEC cooling air

Drain Hole Monitors and controls fuel, VSV and VBV actuators, TBV and HPTCC Valve position, engine starting, and ignition

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ITEM NO.


ITEM NO.


Oil From IDG Air/Oil HX Maintains IDG oil temperature within an acceptable range

FMU Interface to FADEC and Air System Valves Cooled oil to IDG that has passed through

both the air/oil and fuel/oil Hx

Servo Fuel Supply to FMU Unmetered fuel from the FMU that is used for IDG cooling and returned to the main fuel/oil HX

IDG Fuel/Oil HX

Receives input and feedback signals from the FADEC and actuators and sends position demand signals to air system actuators

Cooling Fuel to Main Fuel/Oil HX Cooled oil that has passed through the Air/Oil HX

Oil to IDG Heated fuel from the servo fuel/oil HX for operation of the electro-hydraulic servo valves within the FMU

Bypass Fuel From FMU Bypass fuel returned to the main fuel/oil HX inlet

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ITEM NO.


ITEM NO.


Engine Identification Plug Provides DC voltage to the left igniter at the rate of one pulse per second

Left Ignition Exciter Provides key engine information to the FADEC to allow proper identification and operation of the engine

Right Ignition Exciter Provides DC voltage to the right igniter at the rate of one pulse per second

Fuel Metering Unit (FMU) Meters fuel for combustion and provides servo fuel pressure for positioning of air system actuators.

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ITEM NO.


ITEM NO.


Core Cowl Provides support for the thrust reverser and separates fan and core fire zones

Synchronizing Locking Actuator Actuates the transcowl and gives stowed position indication to the FADEC

Torque Box Establishes an inner flow path for the bypass air

Power Door Opener (PDO) Provides a means to hydraulically open and close the thrust reverser doors

Synchronizing Feedback Actuator Actuates the transcowl, mechanically locks it in the stowed position, and gives a locked indication to the FADEC

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ITEM NO.


ITEM NO.


Manual Disconnect Provides a locked indication to the FADEC

Synchronizing Locking Actuator Must be pinned to allow manual movement of the transcowls

Lock Switch Moves the transcowl, mechanically lock it in the stowed position

Manual Drive Deploys and stows the thrust reverser translating cowl during maintenance

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ITEM NO.


ITEM NO.


Actuator Position feedback Actuates the transcowl and gives stowed position indication to the FADEC

Synchronizing Shaft Provides indication of transcowl position

Synchronizing Feedback Actuator Synchronizes movement of the locking and feedback actuators

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ITEM NO.


ITEM NO.


Core Cowl An integral component of the thrust reverser inner flow path

Transcowl Provides protection in the event of an over pressure condition in the LPT area

Aft Core Cowl Blowout Door When removed, provides access to the cowl lock

Primary Exhaust Nozzle Provides support and forms an inner flow path for bypass airflow

Aft Core Cowl Blocks fan discharge air and directs it forward

Left Translating Cowl Beavertail Combined with the exhaust center body, provides a fixed area annulus for exhausting the core engine gas stream flow

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