-1- Cowling&EBU (CF6-80E1)

Created by Rafik Chabou ENGINE CF6-80E1 General Familiarization

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11 -- PP oo ww ee rr PP ll aa nn tt Nacelle

OverviewThe nacelle or cowling consists of the following components:

Air intake cowls Fan cowl doors Thrust reverser cowl doors Core cowl doors Exhaust nozzle

In this lesson, you will learn about thelocation, identification, and purpose ofthe nacelle, and the components of thenacelle.

The nacelle is located under the wing of the aircraft, and is hinged

to the pylon. The nacelle is divided into different components that

are listed below.

1. The air intake cowls are at the front of the nacelle, forward of thefan cowl doors.

2. The fan cowl doors are installed aft of the air intake cowls.3. The thrust reverser cowl doors are installed aft of the fan cowl

doors.4. The core cowl doors are installed aft of the thrust reverser cowl

doors.5. The exhaust nozzle is installed aft of the core cowl doors.

Nacelle purpose

The nacelle provides smooth airflow in and around the engine. In addition,

the nacelle provides access to the engine LRUs and cools the engine core.

The nacelle also protects the engine components and isolates the engine

from the airframe in case of an engine fire. Finally, the nacelle provides


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openings for the engine drains and contains some of the thrust reverser

components.

The air intake cowls

Location: The air intake cowls are at the front of the nacelle, forward of the

fan cowl doors.

Identification: The air intake cowls

are attached to the forward flange of

the engine fan case. The cowls

comprise the inlet lip and the forward

and aft bulkheads. The inlet lip forms a

smooth, cylindrical opening and is

lined with special material that reduces

the noise of air suction. The inlet lip also contains the anti-ice assembly.

Purpose:

Provides the engine fan with smooth airflow Directs the remaining airflow over the engine nacelle Prevents ice formation around the inlet lip Helps to reduce the noise of air suction

The fan cowl doors

Location: The fan cowl doors are installed

aft of the air intake cowls.

Identification: The two fan cowl doors are

hinged to the pylon. They are latched at

the bottom centerline with three pressure

relief latches that can be opened for accessing the engine components.


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Purpose: The fan cowl doors provide a smooth, aerodynamic surface for

unhindered airflow around the nacelle. They also provide access to various

engine components.

The thrust reverser cowl doors

Location: The thrust reverser cowl doors are installed aft of the fan cowl

doors.

Identification: The two thrust reverser cowl doors are hinged to the

pylon at the top and are latched together at the bottom split line. The

doors are designed to move along the pylon tracks. The thrust reverser

cowl doors also house the components of the thrust reverser system.

Purpose: The thrust reverser cowl

doors form part of the thrust

reverser system. When the thrust

reverser is in the stowed position,

the two thrust reverser cowl doors

provide a smooth, aerodynamic

surface for clean airflow around

the engine. However, when the thrust reverser is deployed, the doors

move aft along the pylon tracks thus providing space for the blocked

airflow to escape. The doors can be opened to provide access to the

engine and the thrust reverser components. A pressure relief door at the

6 o’clock position opens if the differential pressure between the nacelle

air and the ambient air becomes greater than 3.5 psid.


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The core cowl doors

Location: The core cowl doors are

installed aft of the thrust reverser

cowl doors.

Identification: There are two core

cowl doors, both of which are hinged to

the pylon.

Purpose: In the closed position, the core cowl doors provide a smooth

aerodynamic surface over the aft end of the engine core. In the open

position, the doors provide access to the engine components.

The exhaust nozzle

Location: The exhaust nozzle is installed aft of the core cowl doors.

Identification: The exhaust nozzle is a convergent-divergent type of

nozzle and consists of an exhaust sleeve and an exhaust plug.

Purpose:

Directs the engine exhaust gasesoverboard, thus providing the enginewith nearly 20 % of the thrust.

The exhaust sleeve releases lowpressure recoup air and the drainedfluids and vapors from the B and Csumps into the primary airflow stream.

The exhaust plug vents the air/oilmixture from the sumps into theprimary airflow stream.


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Engine Build Unit (EBU)ObjectivesGiven an objective exercise, you will be able to:

Identify the location of the components of the engine build unit(EBU)

Identify the components of the engine build unit (EBU) Identify the purpose of the components of the engine build unit

(EBU)

OverviewThe engine build unit (EBU) consists of the following systems andcomponents:

Engine fire detection system Engine bleed-air supply system Hydraulic pumps Integrated drive generator (IDG) Engine air intake ice protection

In this lesson, you will learn about the location, identification, and purposeof the systems, and components of the EBU.

Location Left Side ViewThe CF6-80E1 engine build unit (EBU) consists of systems and components

that are listed below.

The engine fire detection system is installed around the outer

surfaces of the AGB and the upper and lower turbine areas in the core

module.

The hydraulic pumps are installed on the forward side of the AGB.

The integrated drive generator (IDG) is installed on the aft side of

the AGB.

The engine air intake ice protection system consists of components

that are installed near the 11th compressor stage and in the lip

assembly of the air intake cowls.


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Location Right Side View

The CF6-80E1 engine build unit (EBU) consists of systems and componentsthat are listed below. The engine bleed-air supply system components are installed in the

nacelle and pylon of each engine.


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Engine Fire Detection SystemLocation: The engine fire detection system is installed around the outer

surfaces of the AGB and the upper and lower turbine areas in the core

module.

Identification: The engine fire detection system has two continuous loops

connected in parallel. Each loop has three fire detector assemblies and

the necessary wiring. The fire detector assembly consists of a sensor and

a responder.

Purpose: The engine fire detection system helps to detect and

transmit information about an engine fire to the flight deck.

Engine Bleed-Air Supply System

Location: The engine bleed-air supply system components are installed in

the nacelle and pylon of each engine.

Identification: The engine supply system consists

of the following components:

Ducts Intermediate pressure check (IPC) valve High pressure valve (HPV) Pressure regulating valve (PRV)

Purpose: The engine bleed-air supply system routes

the air through a series of ducts for use by other

aircraft systems. The ducting also allows bleed air

from one engine to be routed to the other engine

to aid in ground or air starting.


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Hydraulic PumpsLocation: The hydraulic pumps are installed

on the forward side of the AGB.

Identification: Each hydraulic pump is an

engine-driven, variable displacement type unit.

Purpose: The hydraulic pump supplies

hydraulic pressure to operate the different

hydraulic systems of the aircraft.

Integrated Drive GeneratorLocation: The integrated drive generator (IDG)

is installed on the aft side of the AGB.

Identification: The IDG has a constant speed

drive (CSD) and an AC generator installed side by

side in a single housing. The generator is a three-

phase and brushless rotating rectifier unit that is spray-oil cooled.

Purpose: The IDG supplies 115-kva electrical power to the aircraft.

Engine Air Intake Ice ProtectionLocation: The engine air intake ice protection system

consists of components that are installed near the 11th

HPC stage and in the lip assembly of the air intake cowls.

Identification: The system consists of an anti-ice duct

that gets bleed air from stage 11 of the HPC through the

anti-ice valve.

Purpose: The system sends hot air to the air intake

cowls to prevent ice buildup on the lip assembly.


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Engine Build Unit Lesson SummaryThe engine build unit (EBU) consists of the following systems andcomponents:

Engine fire detection system Engine bleed-air supply system Hydraulic pumps Integrated drive generator (IDG) Engine air intake ice protection

The engine fire detection system helps in detecting engine fires. The

engine bleed air-supply system supplies high-pressure bleed air to the

aircraft. The hydraulic pumps supply hydraulic pressure for the operation

of different aircraft systems and components. The IDG supplies electrical

power to the aircraft. The engine air intake ice protection system makes

sure that there is no ice formation around the air intake cowls.

-1- Cowling&EBU (CF6-80E1)

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