a320 - removal of the power plant

7/23/2019 A320 - Removal of the Power Plant

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Customer : A1LType : TF-NRev. Date : May 01, 2015

Manual : AMMSelected applicability : 005-005

71-00-00-000-042-A - Removal of the Power Plant

Print Date: August 25, 2015 Page 1 of 20

AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

** ON A/C ALL

TASK 71-00-00-000-042-ARemoval of the Power Plant

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING

GEAR.

WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU

START A TASK ON OR NEAR:

- THE FLIGHT CONTROLS

- THE FLIGHT CONTROL SURFACES

- THE LANDING GEAR AND THE RELATED DOORS

- COMPONENTS THAT MOVE.

MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CANCAUSE DAMAGE TO THE EQUIPMENT.

WARNING: MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU

SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL

MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

FIN : 1000EM1 , 1000EM2

1. Reason for the JobThis task gives the information for the removal of the Power Plant.The power plant can be removed in particular configuration. It is allowed to remove the power plant with orwithout the air intake cowl installed.

NOTE: Interferences between the LPTACC Inlet Airscoop assy and the Thrust reverser cowl have been ob-served in production on a limited number of A320 Family aircraft powered with CFM56-5B/3 engines.CFM has issued SB CFM56-5B S/B 75-0044. In order to recover the gap between the LPTACC scoopand the Thrust reverser cowl to avoid potential interference, Airbus recommends to incorporate this SBat the opportunity of Engine Removal/Installation.

2Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

REFERENCE QTY DESIGNATION

No specific AR ACCESS PLATFORM 1M(3 FT)

No specific AR CONTAINER 4 L (1 USGAL)

No specific AR COVER - PROTECTION

No specific AR PLIERS - NOSE, SOFT, LONG

No specific AR PLUG - BLANKING

No specific AR SAFETY CLIP - CIRCUIT BREAKER

No specific AR TAPE - ADHESIVE

No specific AR TIE WRAP

No specific AR WARNING NOTICE(S)


2/20






REFERENCE QTY DESIGNATION

No specific Torque wrench: range

to between 30.00 and 220.00 lbf.in (0.34 and 2.60 m.daN)No specific Torque wrench: range

to between 2.00 and 20.00 m.daN (15.00 and 150.00 lbf.ft)

(98D27803500001) 1 TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER

(98D71203500000) 1 BOOTSTRAP-SYSTEM

(98D71203501000) 1 BOOTSTRAP SYSTEM

(RSE1224) 2 SPLINT-ENGINE MOUNT AFT

(S487ETT2) 1 ENGINE TROLLEY

(S587-2BH0) 1 BRACE - HOLD OPEN COWLS

(S686CR56-5) 1 ENGINE CRADLE

(TMHBS10-10-00) 1 BRACE-HOLD OPEN COWLS

(TMHEC28-00-00) 1 CRADLE,CFM56-5 ENGINE

(TMHET06-00-00) 1 TRAILER,ENGINE GROUND HANDLING(CFM56-5 AND IAE V2500)

B. Consumable Materials

REFERENCE DESIGNATION

(Material No. CP8001) lockwire 0.032 in. (0.8 mm) dia

(Material No. CP8002) lockwire 0.032 in. (0.8 mm) dia

C. Work Zones and Access Panels

ZONE/ACCESS ZONE DESCRIPTION

FOR 1000EM1 (ENGINE-1)437AL, 438AR,451AL, 452AR,473AL, 473AR

FOR 1000EM2 (ENGINE-2)

447AL, 448AR,461AL, 462AR,483AL, 483AR

D. Referenced Information


(Ref. 05-57-00-200-001-A). Aircraft Stability

(Ref. 24-41-00-861-002-A). Energize the Aircraft Electrical Circuits from the External Power

(Ref. 24-41-00-861-002-A-01). Energize the Aircraft Electrical Circuits from the APU

(Ref. 24-41-00-861-002-A-02). Energize the Aircraft Electrical Circuits from Engine 1(2)

(Ref. 27-80-00-866-005-A). Retracting the Slats on the Ground

(Ref. 29-14-00-614-001-A). Depressurization of the Hydraulic Reservoirs

(Ref. 31-36-00-740-015-A). Printout of the Engine/APU Hours and Cycles Stored in the Flight DataInterface and Management Unit (FDIMU)

** ON A/C ALL

PRE SB 36-1055 for A/C 004-005

(Ref. 36-11-49-000-026-A). Removal of the Sense Line between the Bleed Pressure-RegulatorValve (PRV) and the Pylon Interface


3/20







** ON A/C ALL

(Ref. 71-13-00-010-040-B). Opening of the Fan Cowl Doors

(Ref. 71-13-00-410-040-B). Closing of the Fan Cowl Doors

(Ref. 71-73-49-000-025-A). Removal of the Fuel Overboard Drain Tube

(Ref. 78-30-00-481-041-B). Make the Thrust Reverser Unserviceable for Maintenance

(Ref. 78-36-00-010-040-B). Opening of the Thrust Reverser Doors

(Ref. 78-36-00-410-040-B). Closing of the Thrust Reverser Doors

Fan Duct Panels and Sealing Fitting Assy SHEET 1

Hold Open Cowl Braces - Installation SHEET 1

Thrust Reverser Electrical Connectors SHEET 1

Power Plant - Right Side SHEET 1

Power Plant - Left Side SHEET 1

Pneumatic System SHEET 1Forward Engine Mount SHEET 1

Bootstrap Installation

Aft Engine Mount SHEET 1

Figure 71(CFMB)-00-00-991-91000-06-A / SHEET 1 / 1 - Fan Duct Panels and Sealing Fitting Assyprinted at the end of the text

Figure 71(CFMB)-00-00-991-91100-06-A / SHEET 1 / 1 - Hold Open Cowl Braces - Installation printedat the end of the text

Figure 71(CFMB)-00-00-991-91200-06-A / SHEET 1 / 1 - Thrust Reverser Electrical Connectors printedat the end of the text

Figure 71(CFMB)-00-00-991-91300-06-B / SHEET 1 / 1 - Power Plant - Right Side printed at the end ofthe text

Figure 71(CFMB)-00-00-991-91400-06-A / SHEET 1 / 1 - Power Plant - Left Side printed at the end ofthe text

Figure 71(CFMB)-00-00-991-91500-06-A / SHEET 1 / 1 - Pneumatic System printed at the end of thetext

Figure 71(CFMB)-00-00-991-91600-06-A / SHEET 1 / 1 - Forward Engine Mount printed at the end ofthe text

Figure 71(CFMB)-00-00-991-91700-06-A / SHEET 1 / 2 - Bootstrap Installation printed at the end of thetext

Figure 71(CFMB)-00-00-991-91700-06-A / SHEET 2 / 2 - Bootstrap Installation printed at the end of the

textFigure 71(CFMB)-00-00-991-91800-06-A / SHEET 1 / 1 - Aft Engine Mount printed at the end of the

text

3. Job Set-up

Subtask 71-00-00-740-052-A

A. Do a print-out of the engine hours and cycles and keep the print with the engine for follow-up (Ref. AMM TASK 31-36-00-740-006) or (Ref. AMM TASK 31-36-00-740-007) or(Ref. AMM TASK 31-36-00-740-015) .

NOTE: Some tasks will possibly not be applicable depending on whether a DMU or an FDIMU is installedon the aircraft.

Subtask 71-00-00-941-066-A


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B. Safety Precautions

(1) Make sure that aircraft is stable (Ref. AMM TASK 05-57-00-200-001) .

NOTE: If the aircraft is on jacks, make sure that it is leveled before you remove the engine.

(2) On the center pedestal, on the ENG panel 115VU:

(a) Put a WARNING NOTICE(S) to tell persons not to start the engine.

(3) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do thisprocedure.

(4) On the overhead maintenance panel 50VU:

(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.

(b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).

(5) Make sure that the slats are retracted (Ref. AMM TASK 27-80-00-866-005) and install TOOL-ZEROLOCKING, FLAP SLAT CTL LEVER (98D27803500001) on the flap and slat control lever.

(6) On the panel 30VU make sure that the APU BLEED pushbutton switch is released (ON legend off)and install a WARNING NOTICE(S) to tell the persons not to use it.

(7) Put a WARNING NOTICE(S) on the HP ground connector to tell the persons not to pressurize thepneumatic system.

Subtask 71-00-00-861-089-A

C. Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

Subtask 71-00-00-865-087-A

WARNING: OPEN THE PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) AND5DA1(2,3) BEFORE ENG1(2)FADEC A AND EIU 1(2) C/B'S 2KS1 AND 2KS2. IF YOU DO

NOT OBEY THIS SEQUENCE:

- THE PROBES WILL BECOME TOO HOT.

- THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PER-

SONNEL.

D. Open, safety and tag this(these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION

49VU ENGINE/1 AND 2/IGN/SYS A 1JH A03

49VU ANTI ICE/PROBES/AOA/1 4DA1 D04

49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02

49VU ANTI ICE/RAIN/RPLNT/CAPT 1DB1 D01

49VU COM/CVR/SPLY 2RK E14

49VU COM/CVR/CTL 4RK E13

121VU RCDR/DFDR 7TU K16

121VU ENGINE/ENG1 AND 2 FIRE EX-TIG/BTL1/SQUIB/B

2WE1 Q44

121VU ENGINE/ENG1 AND 2 FIRE EX-TIG/BTL1/SQUIB/A

1WE1 Q43

121VU ENGINE/ENG1 AND 2 FIRE EX-TIG/BTL2/SQUIB/B

2WE2 Q42

121VU ENGINE/ENG1 AND 2 FIRE EX-TIG/BTL2/SQUIB/A

1WE2 Q41


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122VU ANTI ICE/WINDOWS/R 4DG2 W14

122VU ANTI ICE/RAIN/RPLNT/F/O 1DB2 W11122VU ANTI ICE/WINDOWS/L 4DG1 X14

122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15

122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14

122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13

122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11

122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16

122VU ANTI ICE/PROBES/3/AOA 4DA3 Z15

122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14

122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13

122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12

FOR FIN 1000EM1 (ENGINE-1)

49VU FUEL/LP VALVE/MOT1/ENG1 1QG A08

49VU ENGINE/1/FIRE DET/LOOP A 7WD1 A06

49VU ENGINE/1/FADEC A/AND EIU 1 2KS1 A04

121VU FUEL/LP VALVE/MOT2/ENG1 3QG M25

121VU ENGINE/IGN/ENG1/SYS B 3JH1 P41

121VU ENGINE/IGN/ENG1/SYS A BAT 2JH1 P39

121VU ENGINE/ENG1/FIRE DET/LOOP B 8WD1 Q38

121VU ENGINE/ENG1/FADEC B/AND EIU 1 4KS1 R41

122VU ELEC/GCU/1 2XU1 T26

122VU ANTI ICE/ENG/1 1DN1 X10


49VU FUEL/LP VALVE/MOT1/ENG2 2QG A0949VU ENGINE/2/FIRE DET/LOOP B 8WD2 A07

49VU ENGINE/2/FADEC A/AND EIU 2 2KS2 A05

121VU FUEL/LP VALVE/MOT2/ENG2 4QG M26

121VU HYDRAULIC/HYD POWER/Y 3803GX N30

121VU ENGINE/IGN/ENG2/SYS B 3JH2 P42

121VU ENGINE/IGN/ENG2/SYS A BAT 2JH2 P40

121VU ENGINE/ENG2/FADEC B/AND EIU 2 4KS2 Q40

121VU ENGINE/ENG2/FIRE DET/LOOP A 7WD2 Q39

122VU ELEC/GCU/2 2XU2 T27

122VU ANTI ICE/ENG/2 1DN2 W10

123VU Y HYD/ELEC/PUMP 3802GX AB06

123VU Y HYD/ELEC/ELEC PUMP/NORM 3801GX AB03

Subtask 71-00-00-865-158-A

WARNING: OPEN THE PROBE HEATER AND WINDOW HEATER CIRCUIT-BREAKERS BEFORE

YOU OPEN THE PHC AND WHC CIRCUIT BREAKERS. IF YOU DO NOT OBEY THIS SE-

QUENCE:

- THE PROBES WILL BECOME TOO HOT.

- THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PER-

SONNEL.

E. Open, safety and tag this(these) circuit breaker(s):


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49VU ANTI ICE/PROBES/PHC/1 2DA1 D03122VU ANTI ICE/WHC/2 5DG2 W13

122VU ANTI ICE/WHC/1 5DG1 X13

122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16

122VU ANTI ICE/PROBES/PHC/2 2DA2 Y12

Subtask 71-00-00-865-088-A

F. Make sure that this(these) circuit breaker(s) is(are) closed:



49VU ENGINE/1/HP FUEL SOV 1KC1 A01

FOR FIN 1000EM2 (ENGINE-2)49VU ENGINE/2/HP FUEL SOV 1KC2 A02

Subtask 71-00-00-941-067-A

G. Put a WARNING NOTICE(S) on the circuit breaker 1KC1(2) to tell the persons not to open it (them).

Subtask 71-00-00-864-051-A

H. Depressurize the hydraulic reservoir (Ref. AMM TASK 29-14-00-614-001) :

(1) FOR 1000EM1 (ENGINE-1)Depressurize the Green hydraulic reservoir.

(2) FOR 1000EM2 (ENGINE-2)Depressurize the Yellow hydraulic reservoir.

Subtask 71-00-00-010-093-A

J. Get Access

(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-040) :

(2) FOR 1000EM1 (ENGINE-1)437AL, 438AR


Subtask 71-00-00-040-069-A

K. Make the thrust reverser unserviceable (Ref. AMM TASK 78-30-00-481-041) .

Subtask 71-00-00-010-094-A

L. Get Access

CAUTION: BEFORE OPENING THE THRUST REVERSER DOORS TO THE 45 DEGREES POS-

ITION MAKE SURE THAT THE SLATS ARE RETRACTED. IF NOT THE SLATS CAN

TOUCH THE INBOARD THRUST REVERSER DOOR.

(1) Open the thrust reverser doors to the 45 degrees position (Ref. AMM TASK 78-36-00-010-040) :




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Subtask 71-00-00-941-068-A

M. Put the ACCESS PLATFORM 1M(3 FT) in position at the engine level.

(1) At the half upper part of the fan frame seal the fan duct panels with TAPE - ADHESIVE(Ref. Fig. Fan Duct Panels and Sealing Fitting Assy SHEET 1)

Subtask 71-00-00-480-059-A

N. Retract Fan and Thrust Hold Open Rods

(1) Install BRACE - HOLD OPEN COWLS (S587-2BH0) or BRACE-HOLD OPENCOWLS (TMHBS10-10-00) to support the fan and thrust reverser cowl doors.(Ref. Fig. Hold Open Cowl Braces - Installation SHEET 1)

(2) Retract the fan cowl hold open rods (Ref. AMM TASK 71-13-00-410-040) .

(3) Retract the thrust reverser doors hold open rods (Ref. AMM TASK 78-36-00-410-040) .

Subtask 71-00-00-680-051-AP. Drain the remaining fuel from the engine and the pylon fuel hose at the fuel filter as follows :

(Ref. Fig. Thrust Reverser Electrical Connectors SHEET 1)

(1) Put a CONTAINER 4 L (1 USGAL) under the fuel filter.

(2) Cut and remove the lockwire or safety cable and remove the drain plug from the filter bowl. Drain thefuel into the container.

(3) Install the drain plug and TORQUE to between 45 and 55 lbf.in (0.51 and 0.62 m.daN). Safetywith lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001), or lockwire 0.032 in. (0.8 mm)dia (Material No. CP8002).

Subtask 71-00-00-010-095-B

Q. Remove the components:

(1) At the rear of the drain mast remove the drain tube (Ref. AMM TASK 71-73-49-000-025) .

(2) Remove the access panels :



(5) Remove these components from the right side of the engine :

(a) Disconnect the electrical connectors 450VCA, 452VCA, 454VCA, and 457VCA from the aft pylonjunction box.

(Ref. Fig. Thrust Reverser Electrical Connectors SHEET 1)

NOTE: If necessary, use the PLIERS - NOSE, SOFT, LONG to loosen the electrical connectors.

(b) Remove the two clamps which attach the core harness to the pylon and keep them attached tothe harness.

NOTE: Two clamp sizes can be found depending of the core harness diameter. To make surethat the correct clamps are installed, keep the clamps attached to the harness.

(c) Disconnect the generator harness connector 400VCA from the forward pylon junction box.(Ref. Fig. Power Plant - Right Side SHEET 1)

(d) Disconnect the thrust reverser harness connectors 4101KSB, 4101KSA and 4102KSA from thethrust reverser hydraulic control unit.


8/20






(Ref. Fig. Power Plant - Right Side SHEET 1)

(e) Remove the screw (15) and nut (20) that attach the clamps (10), (25) to the bracket on the HCU.

(f) Remove the clamp (10) from the harness for connector 4101KSB and remove the harness fromthe HCU.

NOTE: Loosely install the screw (15) and nut (20) on the clamp (25) and tighten with your hand.

(g) Disconnect the electrical connectors 401VCA, 402VCA, 403VCA, 404VCA, 405VCA, 406VCA,407VCA, 408VCA, 409VCA, 447VCA, and 448VCA from the forward pylon junction box.(Ref. Fig. Power Plant - Right Side SHEET 1)

(h) Remove the coupling (5) and disconnect the upper starter duct from the pylon duct.(Ref. Fig. Power Plant - Right Side SHEET 1)

(i) Install COVER - PROTECTION on the open ends of the ducts.

(j) Install PLUG - BLANKING on the electrical connectors.

(6) Remove these components from the left side of engine:

(a) Disconnect the thrust reverser harness connector 4100KSA and 4100KSB from the electricaljunction box.

(b) Disconnect the coupling half on the suction hose (60), the pressure hose (55), and the uppercase drain hose (50) from the fluid disconnect panel.(Ref. Fig. Power Plant - Left Side SHEET 1)

(c) Disconnect hose/tube (175) from the check valve restrictor pipe interface on the HCU.(Ref. Fig. Power Plant - Left Side SHEET 1)

(d) Remove the bolts (35), the washers (40) that attach the fuel/return by-pass hose (45), from the

fluid disconnect panel. Remove and discard the gasket (10).(Ref. Fig. Power Plant - Left Side SHEET 1)

(e) Remove the bolts (25), the washers (30) that attach the main fuel supply hose (20) to the fluiddisconnect panel. Remove and discard the gasket (15).(Ref. Fig. Power Plant - Left Side SHEET 1)

(f) Install the COVER - PROTECTION on the disconnected hoses and tubes.

(g) Disconnection of the tubes:

CAUTION: USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS:

- ONE WRENCH TO HOLD THE UNION, AND

- ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT.

THIS PREVENTS DAMAGE TO THE PARTS.

1 Disconnect the sense tubes (75) and (80) from the pylon interface tubes.(Ref. Fig. Pneumatic System SHEET 1)

2 Disconnect the pressure tube (70) from the union installed in the upper high-pressuremanifold duct (engine 1 only).(Ref. Fig. Pneumatic System SHEET 1)

3 Remove the coupling (65) and disconnect the pylon interface duct from the pylon duct.(Ref. Fig. Pneumatic System SHEET 1)

** ON A/C ALL

PRE SB 36-1055 for A/C 004-005

Subtask 71-00-00-020-078-A


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R. Removal of the Pressure Regulator Valve (PRV) Sense Line

(1) Remove the sense line between the bleed pressure regulator valve (PRV) and the pylon interface(Ref. AMM TASK 36-11-49-000-026) .

** ON A/C ALL

Subtask 71-00-00-020-060-A

S. Loosen the forward engine mount bolts.

(1) Remove the bolts (100), the washers (105) and (115), and nuts (110) that attach the nut retainers(125).(Ref. Fig. Forward Engine Mount SHEET 1)

(2) Cut and remove the lockwire or safety cable and loosen the bolts (85) as follows:

(a) Loosen one bolt. TORQUE again the bolt

to between 12 and 18 m.daN (88.50 and 132.74 lbf.ft)or to the maximum load that a mechaniccan apply with a standard wrench.

(b) Apply this procedure on the three remaining bolts one by one.

Subtask 71-00-00-480-060-A

T. Installation of the booststrap system:

(1) Install BOOTSTRAP-SYSTEM (98D71203500000) or BOOTSTRAP SYSTEM (98D71203501000)(Ref. Fig. Bootstrap Installation)

(a) Install the rear beam (9) on the lower part of the pylon and attach with the pins (8).

(b) Install the spacer and the center hinge clamp (6) on the pyramid. Attach the spacer to thepyramid with the right and left clamps (7).

(c) Install the forward hinge arms (4) and (5) with the pins (3).

(d) Install the link (2) at the upper part of the hinge arms (4) and (5) with the pins (1).

(e) Install the dynamometers and the chain pulley blocks.

(2) Install the engine cradle:

CAUTION: BE CAREFUL WHEN YOU INSTALL THE CRADLE ON, OR REMOVE IT FROM, THE

ENGINE. IF NOT, YOU CAN CAUSE DAMAGE TO THE VIBRATION SENSOR CON-

NECTOR. THE VIBRATION SENSOR CONNECTOR IS IN FRONT OF THE FOR-

WARD HANDLING POINT ON THE RIGHT SIDE.

(a) Put the ENGINE TROLLEY (S487ETT2) or TRAILER,ENGINE GROUNDHANDLING(CFM56-5 AND IAE V2500) (TMHET06-00-00) together with the ENGINECRADLE (S686CR56-5) or CRADLE,CFM56-5 ENGINE (TMHEC28-00-00) , in position belowthe engine.

(3) Attach the chain hooks to the engine cradle.

(4) Release the pins that attach the engine cradle to the trolley and lift the engine cradle to the engine.

NOTE: Make the engine cradle level. To do this use the chain pulleys.

(5) Put the pins of the front fixtures into the engine handling points and then install the rear support onthe left side. Attach to the engine with a pin.

NOTE: The pin of the rear support on the left side must be put in the lower hole of the engine bracket.


10/20






(6) Put the pins into each fixture. Then, at the same time, adjust the tension of the handling hoists sothat you can read these values on the dynamometers : 1975 daN (4440 lbf) (2015 kg) for the forward

dynamometers and 400 daN (900 lbf) (408 kg) for the aft dynamometers.4. Procedure

Subtask 71-00-00-020-061-A

A. Remove the bolts of the engine mounts

WARNING: DEATH OR SERIOUS INJURY MAY RESULT IF THE POWER PLANT FALLS ON

THE PERSONNEL. THE POWER PLANT WEIGHS APPROXIMATELY 6280 POUNDS

(2850KG). MAKE SURE THAT ALL PERSONNEL IS AWAY FROM THE AIRCRAFT

WHEN THE POWER PLANT IS REMOVED.

(1) Remove the bolts (85), washers (90), nuts (120) that attach the forward engine mount (95) to the

pylon.(Ref. Fig. Forward Engine Mount SHEET 1)

(2) Remove the bolts (135) and washers (140) that attach the aft engine mount (145) to the pylon.(Ref. Fig. Aft Engine Mount SHEET 1)

Subtask 71-00-00-869-177-A

B. Make sure that no lines or unions stay connected to the pylon.

Subtask 71-00-00-480-061-A

CAUTION: MAKE SURE THAT THE PYLON FORWARD MOUNT DOES NOT TOUCH THE UPPER

STRUT OR THE UPPER SEAL ASSY WHEN YOU LOWER THE ENGINE OR DAMAGE CAN

OCCUR.

C. Installation of the support equipment(Ref. Fig. Fan Duct Panels and Sealing Fitting Assy SHEET 1)

(1) Put the pulley locking levers in down position then lower the engine with the four chain pulley blocks.

NOTE: Use the level indicators on the forward hinge arms of the bootstrap to keep this hinge arms asnear as possible to the horizontal position.

NOTE: Be careful not to cause dynamic effects while you lower the engine.

(2) Put first the aft section of the engine cradle in position on the trolley then the forward section.

(3) Lock the engine cradle to the trolley with pins.(4) Remove the four chain hooks from the engine cradle stirrups and remove the four chain pulley blocks

from the bootstrap system.

Subtask 71-00-00-020-059-A

CAUTION: OBEY THESE PRECAUTIONS WHEN YOU TOW OR MOVE THE AIRCRAFT ON THE

GROUND WITH THE ENGINE REMOVED AND THE THRUST REVERSER INSTALLED:

- THE THRUST REVERSER MUST BE CLOSED AND LATCHED.

- THE FAN COWLS MUST BE REMOVED.

- THE SPEED OF THE AIRCRAFT MUST BE 2 KM/H OR SLOWER.

- PREVENT SUDDEN MOVEMENTS OF THE THRUST REVERSER.

IF YOU DO NOT OBEY THESE INSTRUCTIONS, YOU CAN CAUSE DAMAGE TO THE NA-

CELLE STRUCTURE.


11/20






D. Remove the engine.

NOTE: When you lower the engine, check that the assembly is level and never in a nose down attitude.

Subtask 71-00-00-480-082-A

E. Installation of the Aft Engine Mount Anti Gouge Splints

(1) Put the top splint assemblies (larger) on the outside of the aft engine mount links.

NOTE: The end of the splint assembly marked TOP must touch the beam assembly. The other endmarked BOTTOM must touch the links.

(2) Put the bottom splint (smaller) on the inside of the aft engine mount links.

(3) Attach the SPLINT-ENGINE MOUNT AFT (RSE1224) to the engine mount two places with TIE

WRAP.(a) Wind the TIE WRAP around the splints and the aft mount where the splint touches the beam

assembly.

(b) Wind the TIE WRAP around the splints and the aft mount where the splint touches the link.

(c) Make sure that the TIE WRAP is wound very tight and that the splints can not move.

FAN FRAME CASING

FAN DUCT PANEL

UPPER SEALASSY FITTING

UPPERSTRUT

N_MM_710000_4_RAM0_01_00

Figure 71(CFMB)-00-00-991-91000-A / SHEET 1/1 - Fan Duct Panels and Sealing Fitting Assy** ON A/C ALL


12/20






N_MM_710000_4_RBM0_01_00

Figure 71(CFMB)-00-00-991-91100-A / SHEET 1/1 - Hold Open Cowl Braces - Installation** ON A/C ALL


13/20






PLUG

FLANGESTA 191 (B6)

FLANGESTA 199 (A2)

FUEL

DRAIN

PYLON

JUNCTIONPYLON

BOX

454VC-A

450VC-A

452VC-A

457VC-A

CORE

C1M-245-00

FILTER

ELECTRICALHARNESS

A

B A

B

N_MM_710000_4_RCM0_01_00

Figure 71(CFMB)-00-00-991-91200-A / SHEET 1/1 - Thrust Reverser Electrical Connectors** ON A/C ALL


14/20






PYLON

DUCT

UPPERSTARTERDUCT

PYLON

JUNCTIONBOX

FLANGE STA.199 (A2)

FLANGE STA.158 (B1)

FLANGE STA.167 (B4)

CHECK VALVERESTRICTORPIPE

A

C1M-290-01

A

N_MM_710000_4_RDN0_01_01

5

HYDRAULICCONTROLUNIT

25

101520

-A

-A

-A

-A

-A

-A

-A

-A

-A

-A

-A

-A

404VC

403VC

402VC

447VC

448VC

406VC

407VC

408VC

405VC

401VC

409VC400VC

-A

-B

-A

4101KS

4101KS

4102KS

Figure 71(CFMB)-00-00-991-91300-B / SHEET 1/1 - Power Plant - Right Side** ON A/C ALL


15/20






FLANGE

STA 199 (A2)

THRUST

REVERSER

JUNCTION

BOX

175

FLANGESTA 185 (B5)

FLANGESTA 176 (B4)

FLUIDDISCONNECTPANEL

COUPLINGHALF

10

15

2030(4 PLCS)

25(4 PLCS)

35(4 PLCS)

40(4 PLCS)

45

60

TO CHECK

VALVE

RESTRICTOR

PIPE ON HCU

50

55

A

A

C1M-247-05

4100KS-B

-A4100KS

N_MM_710000_4_REM0_01_01

Figure 71(CFMB)-00-00-991-91400-A / SHEET 1/1 - Power Plant - Left Side** ON A/C ALL


16/20






75

PYLON

DUCTINTERFACE

HIGH PRESSURE

80

INTERFACE

BLEED PRESSURE

DUCTPYLON

65

UNION

(SEE NOTE)

PYLON

NOTE: ENGINE 1 ONLYCAPPED ON ENGINE 2

C1M-349-00

70

MANIFOLD DUCT

REGULATOR VALVE

TUBES

A

A

N_MM_710000_4_RFM0_01_00

Figure 71(CFMB)-00-00-991-91500-A / SHEET 1/1 - Pneumatic System** ON A/C ALL


17/20






85(4 PLCS)

90

PYLON

95

100

(4 PLCS)

105

(4 PLCS)

120

(4 PLCS)

115

(4 PLCS)

110

(4 PLCS)

(4 PLCS)125

C1M-249-03

(4 PLCS)

A

B

A

N_MM_710000_4_RGM0_01_00

Figure 71(CFMB)-00-00-991-91600-A / SHEET 1/1 - Forward Engine Mount** ON A/C ALL


18/20






3

4

6

3

5

1 2 1

4

7

5

2

A

B

A

B

N_MM_710000_4_RHM0_01_00

Figure 71(CFMB)-00-00-991-91700-A / SHEET 1/2 - Bootstrap Installation** ON A/C ALL


19/20






8

8

9

C

C

N_MM_710000_4_RHM0_02_00

Figure 71(CFMB)-00-00-991-91700-A / SHEET 2/2 - Bootstrap Installation** ON A/C ALL


20/20




Print Date: August 25 2015 Page 20 of 20

U

P

135

( 4 l o c a t i o n s )

140

( 4 l o c a t i o n s )

C

1M

-250-

03

150

( 4 l o c a t i o n s )

155

( 4 l o c a t i o n s )

BARREL

N U T 1 5 5

SHEAR PIN

PYLON

CAUTION

145

RETAINER 150

BARREL NUT MUST BE

INSTALLED WITH THE

ROUNDED SIDE UP,

AS SHOWN.

A

B

A

B

N_MM_710000_4_RJM0_01_00

Figure 71(CFMB)-00-00-991-91800-A / SHEET 1/1 - Aft Engine Mount** ON A/C ALL

End of document

a320 - removal of the power plant

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