Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
** ON A/C ALL
TASK 71-00-00-000-042-A
Removal 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 CAN
CAUSE 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 Job
This 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 or
without the air intake cowl installed.
NOTE: Interferences between the LPTACC Inlet Airscoop assy and the Thrust reverser cowl have been observed 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 scoop
and the Thrust reverser cowl to avoid potential interference, Airbus recommends to incorporate this SB
at the opportunity of Engine Removal/Installation.
2
Job Set-up Information
A.
Fixtures, Tools, Test and Support Equipment
REFERENCE
No specific
No specific
No specific
No specific
No specific
No specific
No specific
No specific
No specific
QTY
AR
AR
AR
AR
AR
AR
AR
AR
AR
DESIGNATION
ACCESS PLATFORM 1M(3 FT)
CONTAINER 4 L (1 USGAL)
COVER - PROTECTION
PLIERS - NOSE, SOFT, LONG
PLUG - BLANKING
SAFETY CLIP - CIRCUIT BREAKER
TAPE - ADHESIVE
TIE WRAP
WARNING NOTICE(S)
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 1 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
REFERENCE
No specific
No specific
(98D27803500001)
(98D71203500000)
(98D71203501000)
(RSE1224)
(S487ETT2)
(S587-2BH0)
(S686CR56-5)
(TMHBS10-10-00)
(TMHEC28-00-00)
(TMHET06-00-00)
B.
QTY DESIGNATION
Torque wrench: range
to between 30.00 and 220.00 lbf.in (0.34 and 2.60 m.daN)
Torque wrench: range
to between 2.00 and 20.00 m.daN (15.00 and 150.00 lbf.ft)
1
TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER
1
BOOTSTRAP-SYSTEM
1
BOOTSTRAP SYSTEM
2
SPLINT-ENGINE MOUNT AFT
1
ENGINE TROLLEY
1
BRACE - HOLD OPEN COWLS
1
ENGINE CRADLE
1
BRACE-HOLD OPEN COWLS
1
CRADLE,CFM56-5 ENGINE
1
TRAILER,ENGINE GROUND HANDLING(CFM56-5 AND IAE V2500)
Consumable Materials
REFERENCE
(Material No. CP8001)
(Material No. CP8002)
DESIGNATION
lockwire 0.032 in. (0.8 mm) dia
lockwire 0.032 in. (0.8 mm) dia
C. Work Zones and Access Panels
ZONE/ACCESS
FOR 1000EM1 (ENGINE-1)
437AL, 438AR,
451AL, 452AR,
473AL, 473AR
FOR 1000EM2 (ENGINE-2)
447AL, 448AR,
461AL, 462AR,
483AL, 483AR
ZONE DESCRIPTION
D. Referenced Information
REFERENCE
(Ref. 05-57-00-200-001-A).
(Ref. 24-41-00-861-002-A).
(Ref. 24-41-00-861-002-A-01).
(Ref. 24-41-00-861-002-A-02).
(Ref. 27-80-00-866-005-A).
(Ref. 29-14-00-614-001-A).
(Ref. 31-36-00-740-015-A).
DESIGNATION
Aircraft Stability
Energize the Aircraft Electrical Circuits from the External Power
Energize the Aircraft Electrical Circuits from the APU
Energize the Aircraft Electrical Circuits from Engine 1(2)
Retracting the Slats on the Ground
Depressurization of the Hydraulic Reservoirs
Printout of the Engine/APU Hours and Cycles Stored in the Flight Data
Interface 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-Regulator
Valve (PRV) and the Pylon Interface
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 2 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
REFERENCE
DESIGNATION
** 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 1
Forward 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 Assy
printed at the end of the text
Figure 71(CFMB)-00-00-991-91100-06-A / SHEET 1 / 1 - Hold Open Cowl Braces - Installation printed
at the end of the text
Figure 71(CFMB)-00-00-991-91200-06-A / SHEET 1 / 1 - Thrust Reverser Electrical Connectors printed
at 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 of
the text
Figure 71(CFMB)-00-00-991-91400-06-A / SHEET 1 / 1 - Power Plant - Left Side printed at the end of
the text
Figure 71(CFMB)-00-00-991-91500-06-A / SHEET 1 / 1 - Pneumatic System printed at the end of the
text
Figure 71(CFMB)-00-00-991-91600-06-A / SHEET 1 / 1 - Forward Engine Mount printed at the end of
the text
Figure 71(CFMB)-00-00-991-91700-06-A / SHEET 1 / 2 - Bootstrap Installation printed at the end of the
text
Figure 71(CFMB)-00-00-991-91700-06-A / SHEET 2 / 2 - Bootstrap Installation printed at the end of the
text
Figure 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 followup (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 installed
on the aircraft.
Subtask 71-00-00-941-066-A
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 3 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
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 this
procedure.
(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-ZERO
LOCKING, 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 the
pneumatic 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:
D.
OPEN THE PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) AND
5DA1(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 PERSONNEL.
Open, safety and tag this(these) circuit breaker(s):
PANEL
49VU
49VU
49VU
49VU
49VU
49VU
121VU
121VU
121VU
121VU
121VU
DESIGNATION
ENGINE/1 AND 2/IGN/SYS A
ANTI ICE/PROBES/AOA/1
ANTI ICE/PROBES/PITOT/1
ANTI ICE/RAIN/RPLNT/CAPT
COM/CVR/SPLY
COM/CVR/CTL
RCDR/DFDR
ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B
ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A
ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B
ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A
FIN
1JH
4DA1
3DA1
1DB1
2RK
4RK
7TU
2WE1
A03
D04
D02
D01
E14
E13
K16
Q44
LOCATION
1WE1
Q43
2WE2
Q42
1WE2
Q41
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 4 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
PANEL
122VU
122VU
122VU
122VU
122VU
122VU
122VU
122VU
122VU
122VU
122VU
122VU
FOR FIN 1000EM1
49VU
49VU
49VU
121VU
121VU
121VU
121VU
121VU
122VU
122VU
FOR FIN 1000EM2
49VU
49VU
49VU
121VU
121VU
121VU
121VU
121VU
121VU
122VU
122VU
123VU
123VU
DESIGNATION
ANTI ICE/WINDOWS/R
ANTI ICE/RAIN/RPLNT/F/O
ANTI ICE/WINDOWS/L
ANTI ICE/PROBES/2/TAT
ANTI ICE/PROBES/2/PITOT
ANTI ICE/PROBES/2/AOA
ANTI ICE/PROBES/2/STATIC
ANTI ICE/PROBES/3/PITOT
ANTI ICE/PROBES/3/AOA
ANTI ICE/PROBES/3/STATIC
ANTI ICE/PROBES/1/STATIC
ANTI ICE/PROBES/1/TAT
(ENGINE-1)
FUEL/LP VALVE/MOT1/ENG1
ENGINE/1/FIRE DET/LOOP A
ENGINE/1/FADEC A/AND EIU 1
FUEL/LP VALVE/MOT2/ENG1
ENGINE/IGN/ENG1/SYS B
ENGINE/IGN/ENG1/SYS A BAT
ENGINE/ENG1/FIRE DET/LOOP B
ENGINE/ENG1/FADEC B/AND EIU 1
ELEC/GCU/1
ANTI ICE/ENG/1
(ENGINE-2)
FUEL/LP VALVE/MOT1/ENG2
ENGINE/2/FIRE DET/LOOP B
ENGINE/2/FADEC A/AND EIU 2
FUEL/LP VALVE/MOT2/ENG2
HYDRAULIC/HYD POWER/Y
ENGINE/IGN/ENG2/SYS B
ENGINE/IGN/ENG2/SYS A BAT
ENGINE/ENG2/FADEC B/AND EIU 2
ENGINE/ENG2/FIRE DET/LOOP A
ELEC/GCU/2
ANTI ICE/ENG/2
Y HYD/ELEC/PUMP
Y HYD/ELEC/ELEC PUMP/NORM
FIN
4DG2
1DB2
4DG1
1DA2
3DA2
4DA2
5DA2
3DA3
4DA3
5DA3
5DA1
1DA1
W14
W11
X14
Y15
Y14
Y13
Y11
Z16
Z15
Z14
Z13
Z12
LOCATION
1QG
7WD1
2KS1
3QG
3JH1
2JH1
8WD1
4KS1
2XU1
1DN1
A08
A06
A04
M25
P41
P39
Q38
R41
T26
X10
2QG
8WD2
2KS2
4QG
3803GX
3JH2
2JH2
4KS2
7WD2
2XU2
1DN2
3802GX
3801GX
A09
A07
A05
M26
N30
P42
P40
Q40
Q39
T27
W10
AB06
AB03
Subtask 71-00-00-865-158-A
WARNING:
E.
OPEN THE PROBE HEATER AND WINDOW HEATER CIRCUIT-BREAKERS BEFORE
YOU OPEN THE PHC AND WHC CIRCUIT BREAKERS. IF YOU DO NOT OBEY THIS SEQUENCE:
- THE PROBES WILL BECOME TOO HOT.
- THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL.
Open, safety and tag this(these) circuit breaker(s):
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 5 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
PANEL
49VU
122VU
122VU
122VU
122VU
DESIGNATION
ANTI ICE/PROBES/PHC/1
ANTI ICE/WHC/2
ANTI ICE/WHC/1
ANTI ICE/PROBES/PHC/3
ANTI ICE/PROBES/PHC/2
FIN
2DA1
5DG2
5DG1
2DA3
2DA2
LOCATION
D03
W13
X13
Y16
Y12
Subtask 71-00-00-865-088-A
F.
Make sure that this(these) circuit breaker(s) is(are) closed:
PANEL
FOR FIN 1000EM1
49VU
FOR FIN 1000EM2
49VU
DESIGNATION
(ENGINE-1)
ENGINE/1/HP FUEL SOV
(ENGINE-2)
ENGINE/2/HP FUEL SOV
FIN
LOCATION
1KC1
A01
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
(3) FOR 1000EM2 (ENGINE-2)
447AL, 448AR
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 POSITION 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) :
(2) FOR 1000EM1 (ENGINE-1)
451AL, 452AR
(3) FOR 1000EM2 (ENGINE-2)
461AL, 462AR
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 6 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
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 OPEN
COWLS (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-A
P.
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 the
fuel into the container.
(3) Install the drain plug and TORQUE to between 45 and 55 lbf.in (0.51 and 0.62 m.daN). Safety
with 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 :
(3) FOR 1000EM1 (ENGINE-1)
473AL, 473AR
(4) FOR 1000EM2 (ENGINE-2)
483AL, 483AR
(5) Remove these components from the right side of the engine :
(a) Disconnect the electrical connectors 450VCA, 452VCA, 454VCA, and 457VCA from the aft pylon
junction 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 to
the harness.
NOTE: Two clamp sizes can be found depending of the core harness diameter. To make sure
that 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 the
thrust reverser hydraulic control unit.
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 7 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
(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 from
the 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 electrical
junction box.
(b) Disconnect the coupling half on the suction hose (60), the pressure hose (55), and the upper
case 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 fluid
disconnect 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-pressure
manifold 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
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 8 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
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 mechanic
can 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 the
pyramid 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 CONNECTOR. THE VIBRATION SENSOR CONNECTOR IS IN FRONT OF THE FORWARD HANDLING POINT ON THE RIGHT SIDE.
(a) Put the ENGINE TROLLEY (S487ETT2) or TRAILER,ENGINE GROUND
HANDLING(CFM56-5 AND IAE V2500) (TMHET06-00-00) together with the ENGINE
CRADLE (S686CR56-5) or CRADLE,CFM56-5 ENGINE (TMHEC28-00-00) , in position below
the 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 on
the 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.
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 9 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
(6) Put the pins into each fixture. Then, at the same time, adjust the tension of the handling hoists so
that 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:
C.
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.
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 as
near 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 NACELLE STRUCTURE.
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 10 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
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 end
marked 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
UPPER
STRUT
FAN DUCT PANEL
UPPER SEAL
ASSY FITTING
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
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 11 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
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
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 12 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
B
A
FLANGE
STA 191 (B6)
FLANGE
STA 199 (A2)
A
B
PYLON
JUNCTION
BOX
FUEL
FILTER
DRAIN
PLUG
454VC-A
450VC-A
452VC-A
457VC-A
PYLON
CORE
ELECTRICAL
HARNESS
C1M-245-00
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
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 13 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
A
A
404VC -A
403VC -A
402VC -A
447VC -A
448VC -A
406VC -A
407VC -A
PYLON
JUNCTION
BOX
408VC -A
FLANGE STA.
158 (B1)
405VC -A
401VC-A
409VC-A
400VC-A
PYLON
DUCT
10
15 5
CHECK VALVE 20
RESTRICTOR
PIPE
25
FLANGE STA.
167 (B4)
4102KS-A
HYDRAULIC
CONTROL
UNIT
4101KS-B
C1M-290-01
4101KS-A
FLANGE STA.
199 (A2)
UPPER
STARTER
DUCT
N_MM_710000_4_RDN0_01_01
Figure 71(CFMB)-00-00-991-91300-B / SHEET 1/1 - Power Plant - Right Side
** ON A/C ALL
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 14 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
A
FLANGE
STA 176 (B4)
A
FLUID
DISCONNECT
PANEL
10
COUPLING
HALF
TO CHECK
VALVE
RESTRICTOR
PIPE ON HCU
FLANGE
STA 185 (B5)
60
175
FLANGE
STA 199 (A2)
55
50
40
(4 PLCS)
45
4100KS-A
15
30
(4 PLCS)
4100KS-B
35
(4 PLCS)
C1M-247-05
20
THRUST
REVERSER
JUNCTION
BOX
25
(4 PLCS)
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
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 15 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
A
A
PYLON
PYLON
DUCT
65
70
(SEE NOTE)
UNION
HIGH PRESSURE
MANIFOLD DUCT
PYLON
INTERFACE
DUCT
INTERFACE
TUBES
75
80
BLEED PRESSURE
REGULATOR VALVE
NOTE: ENGINE 1 ONLY
CAPPED ON ENGINE 2
C1M-349-00
N_MM_710000_4_RFM0_01_00
Figure 71(CFMB)-00-00-991-91500-A / SHEET 1/1 - Pneumatic System
** ON A/C ALL
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 16 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
A
A
85
(4 PLCS)
90
(4 PLCS)
B
PYLON
95
100
(4 PLCS)
105
(4 PLCS)
125
(4 PLCS)
120
(4 PLCS)
115
(4 PLCS)
110
(4 PLCS)
C1M-249-03
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
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 17 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
B
A
A
1
2 1
6
3
3
5
4
B
2
4
5
7
N_MM_710000_4_RHM0_01_00
Figure 71(CFMB)-00-00-991-91700-A / SHEET 1/2 - Bootstrap Installation
** ON A/C ALL
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 18 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
C
C
8
8
9
N_MM_710000_4_RHM0_02_00
Figure 71(CFMB)-00-00-991-91700-A / SHEET 2/2 - Bootstrap Installation
** ON A/C ALL
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 19 of 20
Customer : A1L
Manual : AMM
Type : TF-N
Selected applicability : 005-005
Rev. Date : May 01, 2015
71-00-00-000-042-A - Removal of the Power Plant
A
A
135
(4 locations)
140
(4 locations)
PYLON
SHEAR PIN
B
145
CAUTION
BARREL NUT MUST BE
INSTALLED WITH THE
ROUNDED SIDE UP,
AS SHOWN.
155
(4 locations)
BARREL
NUT 155
RETAINER 150
C1M-250-03
150
(4 locations)
U
P
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
Print Date: August 25, 2015
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Page 20 of 20