70 Power Plant (Cfm56-5b)

A318/A319/A320/A321 TECHNICAL TRAINING MANUAL M02 RAMP & SERVICING (CFM56)

POWER PLANT (CFM56-5B)

This document must be used for training purposes only

Under no circumstances should this document be used as a reference

It will not be updated.

All rights reservedNo part of this manual may be reproduced in any form,

by photostat, microfilm, retrieval system, or any other means,without the prior written permission of AIRBUS S.A.S.

POWER PLANT (CFM56-5B)Power Plant Level 2 (2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2Opening & Closing of Engine Cowl Doors (2) . . . . . . . . . . . . . . . . . 20Thrust Reverser Deactivation & Lockout(2) . . . . . . . . . . . . . . . . . . . 44

M02 RAMP & SERVICING (CFM56) 70 - POWER PLANT (CFM56-5B)

TABLE OF CONTENTS May 05, 2006Page 1

A318/A319/A320/A321 TECHNICAL TRAINING MANUALU

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POWER PLANT LEVEL 2 (2)

SYSTEM OVERVIEW

The CFM56-5B engine is a dual-rotor, variable stator, high bypass ratioturbo fan power plant. The CFM56-5B powers the complete single aislefamily of aircraft. CFM56-5B engines are available in several thrustratings.All the engines are basically the same. A programming plug on theElectronic Control Unit (ECU) changes the available thrust.The power plant installation includes the engine, the engine inlet, theexhaust, the fan cowls and the reverser assemblies. The pylon connectsthe engine to the wing structure. The engine is attached to the pylon byforward and aft mounts.


POWER PLANT LEVEL 2 (2) May 05, 2006Page 2


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SYSTEM OVERVIEW




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SYSTEM OVERVIEW (continued)

THRUST REVERSER SYSTEMReverse thrust is controlled by the ECU. Reverse is manually selectedby the flight crew by lifting the latching levers on the throttle controllevers. The reverse thrust command is sent to the ECU and the EngineInterface Unit (EIU). The signal from the ECU to the directional valveis fed to an inhibition relay controlled by the Engine Interface Unit(EIU) according to throttle control lever position.According to commands from the ECU, a Hydraulic Control Unit(HCU) supplies hydraulic power to operate the thrust reverser. Thethrust reverser uses 4 hydraulically actuated pivoting blocker doorsto redirect the engine fan airflow.




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SYSTEM OVERVIEW - THRUST REVERSER SYSTEM




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ENGINE OIL SERVICING

CAUTION: Caution: The engine should be shut down for at least 5minutes prior to oil servicing. This allows the residualpressure in the oil tank to decrease. If you open the fillercap when there is pressure in the tank the hot oil can sprayout and burn you.

- Open engine oil service door on left fan cowl,- Check oil level on the sight gage on the oil tank,- Raise filler cap handle to vertical (Unlocked position),- Push down and turn the oil filler cap counterclockwise to remove,- Add oil as necessary up to the FULL mark on the sight gage,- Install oil filler cap - make sure to LOCK the cap.

NOTE: Note: It is also possible to Pressure Fill the engine oil. Twoports are installed on the oil tank, one for pressure and one foroverflow. See AMM for procedure.




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ENGINE OIL SERVICING




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MASTER CHIP DETECTOR CHECK

There is a red pop-out indicator visible from the oil-servicing door. Ifextended, this indicates that the Electrical Master Chip Detector (EMCD)is contaminated and the probe should be checked. To reset red pop-outindicator, pushing in clogging indicator with thumb.The EMCD probe is located on the lubrication unit and is made up oftwo magnets separated by a gap. The probe will collect any magneticparticles in the oil system. If the particle contamination closes the gapbetween the magnets an electrical signal is generated to extend the pop-outindicator. To check for contamination, remove the probe as follows:- Open the left fan cowl,- At the same time, push and turn the EMCD plug ¼ turncounterclockwise,- Disengage the EMCD from its housing,- Check the AMM for examples of NORMAL and ABNORMALcontamination,- Clean the EMCD,- Replace o-ring if necessary and re-install - check that the RED marksare aligned.




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MASTER CHIP DETECTOR CHECK




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MEL/DEACTIVATION

FUEL FILTER CLOGGINGIn case of a failure of the FUEL CLOG warning on ECAM, the aircraftmay be dispatched per MEL as long as the fuel filter is changed onceeach day. The filter housing is part of the fuel pump assembly locatedon the accessory gearbox LH side. Procedure:- FADEC GND PWR selected OFF,- Open LH fan cowl,- Drain residual fuel using drain plug,- Open filter cover to remove and replace fuel filter element ando-rings,- Re-install filter cover; check AMM for correct torque value for filtercover bolts,- Perform minimum idle check for leaks,- Close fan cowl.




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MEL/DEACTIVATION - FUEL FILTER CLOGGING




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MEL/DEACTIVATION (continued)

T/R DEACTIVATION AND LOCKOUTPer the MEL, one or both Thrust Reversers may be deactivated in theSTOWED position for dispatch. The deactivation procedure has twoparts. First, the Hydraulic Control Unit (HCU) is deactivated. Movingthe deactivation lever to the inhibit position prevents the pressurizingvalve from supplying hydraulic pressure to the reverser actuators. Inthe second part of the deactivation procedure each pivoting door issecured (bolted) to the reverser structure preventing any movement.




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MEL/DEACTIVATION - T/R DEACTIVATION AND LOCKOUT




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OIL FILTER CLOGGINGIn case of a failure of the OIL CLOG warning on ECAM, the aircraftmay be dispatched per MEL as long as the scavenge filter is changedonce each day. The filter housing lubrication unit located on theaccessory gearbox LH side. Procedure:- FADEC GND PWR selected OFF,- Open LH fan cowl,- Drain residual oil using drain plug,- Open filter cover to remove and replace oil filter element and o-rings,- Re-install filter cover, Check AMM/MEL for correct torque valuefor filter cover bolts,- Check ECMD for contamination,- Perform minimum idle check for leaks,- Close fan cowl.




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MEL/DEACTIVATION - OIL FILTER CLOGGING




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START VALVE MANUAL OPERATIONIn case of an electrical failure of the start valve, the valve may beoperated manually to start the engine. The aircraft may be dispatchedper the MEL with the valve INOP closed.

NOTE: Note: Do not operate the valve unless the starter system ispressurized. Damage to the valve can occur.

- Open the start valve access door on the RH cowl,- Establish communications with the cockpit (Interphone jack onengine inlet cowl),- On command from the cockpit, move start valve manual handle tothe OPEN position,

NOTE: Note: Make sure you maintain pressure against the springtension to keep the valve open.

- After engine start, on command from the cockpit, move start valvemanual handle to CLOSED. Make sure that the start valve is fullyclosed.




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MEL/DEACTIVATION - START VALVE MANUAL OPERATION




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MAINTENANCE TIPS

The engine and pylon drain system is designed to collect fuel, oil, waterand hydraulic fluid from engine systems and accessories and dischargethem overboard through the engine drain mast and the pylon drain tubes.For troubleshooting and leak isolation a drain collector is installed onthe accessory gearbox. The drain collector supplies the drain manifoldmodule, which supports the drain mast. The drain mast also has separatedrains for additional leak isolation. The pylon drain tubes collect fluidsfrom individual pylon chambers, also for leak isolation.If fluid leaks are found during transit operations, the AMM (ATA 70-00& ATA 29-00) lists maximum permitted leakage limits for the drainsystem. There are limits for STATIC (engine not running) and DYNAMIC(engine running) conditions. There is also a separate drain line at thedrain mast trailing edge for the Fuel Manifold Shroud drain. There is NOLEAKAGE PERMITTED from this drain. Here are some examples ofleakage limits for dispatch. See the AMM for complete list.

NOTE: In the case of extreme cold weather condition (Outside AirTemperature (OAT) <- 20 deg.C (- 4 deg.F), fuel leaks fromthe drain mast (other than fuel manifold drain) may occur on anon-running engine and during engine start. This leakage isexpected to stop after a 5 minute warm-up at minimum idle.




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MAINTENANCE TIPS




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OPENING & CLOSING OF ENGINE COWL DOORS (2)

INITIAL PRECAUTIONS

Opening and closing of the engine cowl doors.Before working on the engine, initial precautions have to be taken in thecockpit.On panel 115 VU, put a warning notice stating not to start the engine.Make sure that the engine has been shut down for at least 5 minutes andthat the corresponding master lever is in the OFF position.On panel 50 VU make sure that the ON legend of the engine FADECground power P/BSW is off and install a warning notice.Then make certain that the slats are retracted and install a warning noticeprohibiting use of the slats. If they are extended, retract them.


OPENING & CLOSING OF ENGINE COWL DOORS (2) May 05, 2006Page 20


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INITIAL PRECAUTIONS




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OPENING OF THE ENGINE FAN COWL DOORS

The fan cowl and the thrust reverser cowl doors can be opened formaintenance and inspection.Opening of the fan cowl door.

CAUTION: Caution: Do not attempt to open the fan cowl door if thewind speed is more than 65 knots or when the engine isrunning.

First unlock the 3 latches on the engine centerline.For each latch, push the latch snap to release the handle.Pull the latch handle until the latch hook releases from its keeper.Manually elevate and support the door at the lower edge.Two hold-open rods are located inside the fan cowl door.Release the hold-open rods from their brackets and connect them to theirsupports on the fan case.The two hold-open rods must be unlocked to open the fan cowl door.Open the fan cowl door sufficiently to extend the hold-open rods.Manually check the correct engagement of the hold-open rods.Open the second fan cowl door. The other fan cowl door is opened in thesame way.Each time check that the locking devices are properly engaged on thehold-open rods.With the fan cowl door opened, the accessories mounted on the fan caseand on the accessory gearbox are accessible.There are two opening positions, one at 40 degrees for routinemaintenance, and the second at 55 degrees for increased access.




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OPENING OF THE ENGINE FAN COWL DOORS




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OPENING OF THE ENGINE THRUST REVERSER COWLDOORS

Opening of the thrust reverser doors.

CAUTION: Caution: do not attempt to open the thrust reverser door ifthe wind speed is more than 40 knots.

First, deactive the thrust reverser system. Push and hold the hydrauliccontrol unit lever to the forward frame and then install the safety pin. Onthe engine centerline, release the four latches.Push the snap to free the latch handle. Then pull down on the latch handleto disengage the latch hook from its attachment point.Before connecting the hydraulic hand pump, read the instructions writtenon the red plate located beside the quick disconnect of each thrust reverserhalf.Remove the dust cover from the quick disconnect and connect the handpump. Make sure that the quick disconnect tube is correctly connected.Operate the hand pump to pressurize the opening actuator until thereverser half reaches the fully open 45 degrees position.When the door is open, unstow the hold-open rod from the fan case, thenattach and secure it to each bracket on the thrust reverser door.Unload the hydraulic pump and disconnect it from the hydraulic manifold.Replace the cap on the quick disconnect.The hand pump is used to open the other thrust reverser door.Once all doors are opened the engine accessories mounted on the fancase and engine cowl are accessible.




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OPENING OF THE ENGINE THRUST REVERSER COWL DOORS




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CLOSING OF THE ENGINE THRUST REVERSER COWLDOORS

The cowl closing sequence is exactly opposite to the opening sequence.Make sure that the working area is clean and clear of tools and otheritems.The thrust reverser doors are closed first.To close the thrust reverser door, pressurize the hydraulic opening actuatorto release the load from the hold-open rod.Disengage the hold-open rod from its bracket, stow and secure it to itsattachment support on the fan case.Slowly open the hand pump relief valve.The actual rate of door closing should be control by the hand pump.However, as a safety device, the actuator has a metering valve whichensures a minimum door closing time.When the door is fully closed, disconnect the hand pump from thehydraulic manifold, and replace the cap on the quick disconnect.Complete door closing by securing the latches. Engage and lock the fourtension latches.Remove the inhibition pin from the hydraulic control unit lever, to putthe thrust reverser system back to the operational condition.




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CLOSING OF THE ENGINE THRUST REVERSER COWL DOORS




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CLOSING OF THE ENGINE FAN COWL DOORS

Now, close the fan cowl doors.Remove the aft and the forward hold-open rods from the retention bracketson the fan case and stow them on the fan cowl door.The door can now be closed.Make sure that the hooks are released from the latch handles.Push the doors together and engage latch hooks with their keepers. Firstclose the front latch then the center, and then the rear one.To finish this operation, check that the fan cowl doors are flush with thethrust reverser door and the inlet cowl.Finally, in the cockpit, remove the warning notices from panels 50 VU,115 VU, and the slats control lever.




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CLOSING OF THE ENGINE FAN COWL DOORS




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FAN COWL LATCHES

The fan cowl door is latched by three adjustable tension latches.Each latch assembly consists of a snap, a handle and a hook.




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FAN COWL LATCHES




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FAN COWL HOLD OPEN RODS

Two hold open rods, stored on the fan cowl doors, are extended thenattached to the fan case to hold the doors.




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FAN COWL HOLD OPEN RODS




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THRUST REVERSER COWL LATCHES

Four adjustable tension latches are provided on the thrust reverser cowlingassembly.Each latch is unlocked by pushing a snap on its handle to disengage thecorresponding hook from its bracket.




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THRUST REVERSER COWL LATCHES




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INSTRUCTION PLATE

Beside each quick disconnect for the hand pump, an instruction plate isinstalled to warn against extension of slats during thrust reverser cowldoor opening.




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INSTRUCTION PLATE




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THRUST REVERSER COWL QUICK DISCONNECT

Each thrust reverser cowl door is fitted with a quick disconnect to connecta hand pump.




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THRUST REVERSER COWL QUICK DISCONNECT




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THRUST REVERSER COWL OPENING ACTUATOR

To open each thrust reverser cowl door, an actuator is extended byhydraulic pressure from the hand pump.




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THRUST REVERSER COWL OPENING ACTUATOR




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THRUST REVERSER COWL HOLD OPEN ROD

Only one hold open rod keeps each thrust reverser cowl door in the openposition.The hold open rod is stored on the fan case then extended and attachedto the thrust reverser cowl door.




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THRUST REVERSER COWL HOLD OPEN ROD




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THRUST REVERSER DEACTIVATION & LOCKOUT(2)

THRUST REVERSER DEACTIVATION AND LOCKOUT

This procedure is accomplished when a fault occurs on the thrust reversersystem which can not be repaired for the next flight.De-activation and lockout devices are therefore provided to secure thepivoting doors in the stowed position when an A/C has to be dispatchedwith an inoperative thrust reverser.In the cockpit first put a warning notice on the engine panel 115VU toprevent engine start.Make sure that the engine has been shutdown for at least 5 minutes andthat the corresponding MASTER control switch is set to the OFF position.On the engine maintenance panel 50VU make sure that the ON legendof the ENG FADEC GND PWR 1 (2) P/BSW is off and install a warningnotice.Open the fan cowl doors.On the right hand side install the access platform in position to get accessto the Hydraulic Control Unit (HCU) located on the upper part of thethrust reverser door.Deactivate the thrust reverser system as follows:Move the HCU deactivation lever to the INHIBIT position.Remove the safety pin from its storage support and install it to hold thedeactivation lever in the INHIBIT position.Disconnect the connectors of the pressurizing valve and directional valve.Install blanking caps on the electrical connectors and secure them.For lockout operation:On the lower forward face of the right thrust reverser half, lockout boltswill be removed from the storage bracket.On each pivoting door remove the lockout fairing and its screw.Then remove the red lock plates and the lockout bolts.Now install in each pivoting door a lockout bolt and tighten it to attachthe door to the frame structure of the thrust reverser cowl door.Cover and secure each lockout bolt with a red lock plate and its retainingbolt.

Replace the lockout fairings and the screws on the storage bracket insteadof the red lock plates and the lockout bolts.Close the fan cowl doors and make sure that the working area is cleanand clear of tools and other items.When all the lock plates are installed they indicate that the four pivotingdoors and the thrust reverser are locked out.Finally, in the cockpit remove the warning notices from panels 50VUand 115VU.Install a warning notice indicating that the corresponding reverser isinoperative and note it in the logbook.


THRUST REVERSER DEACTIVATION & LOCKOUT(2) May 05, 2006Page 44


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THRUST REVERSER DEACTIVATION AND LOCKOUT




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THRUST REVERSER DEACTIVATION LEVER

To deactivate the thrust reverser system, the safety pin is installed to holdthe deactivation lever in the inhibition position.




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THRUST REVERSER DEACTIVATION LEVER




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HYDRAULIC CONTROL UNIT (HCU) CONNECTIONS

For safety reasons the solenoid valve connections of the HCU aredisconnected.




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HYDRAULIC CONTROL UNIT (HCU) CONNECTIONS




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THRUST REVERSER LOCKOUT BOLTS STORAGE

To lockout the pivoting doors, special lockout bolts and red lock platesare stored on a storage bracket located on the lower forward face of theright thrust reverser cowl door.




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THRUST REVERSER LOCKOUT BOLTS STORAGE




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THRUST REVERSER LOCKOUT FAIRING

On each pivoting door a lockout fairing is removed to install lockoutbolts in the lockout position.




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THRUST REVERSER LOCKOUT FAIRING




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THRUST REVERSER LOCKOUT BOLTS INSTALLATION

The lockout bolts are installed and secured by lock plates to attach thepivoting doors to the structure of the thrust reverser cowl doors.The lockout fairing plates and screws are stored on the storage bracketinstead of the lockout bolts and red lock plates.




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THRUST REVERSER LOCKOUT BOLTS INSTALLATION




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AIRBUS S.A.S.31707 BLAGNAC cedex, FRANCE

STMREFERENCE U3Q06181

MAY 2006PRINTED IN FRANCEAIRBUS S.A.S. 2006

ALL RIGHTS RESERVED

AN EADS JOINT COMPANYWITH BAE SYSTEMS

Documents

70 Power Plant (Cfm56-5b)