W DOC AIRBUS | AMM A320F

Installation of the Mid Stage Tee Duct

TASK 36-11-49-400-043-A
Installation of the Mid Stage Tee Duct

1. Reason for the Job
Self explanatory
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
AR
ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE
No specific
AR
HAMMER - FIBER
No specific
AR
WARNING NOTICE(S)
No specific
Torque wrench: range to between 60 and 54 lbf.in (0.68 and 0.61 m.daN ) T
No specific
Torque wrench: range to between 90 and 75 lbf.in (1.02 and 0.85 m.daN ) T
No specific
Torque wrench: range to between 156.2 and 127.8 lbf.in (1.77 and 1.44 m.daN ) T
No specific
Torque wrench: range to between 150 and 135 lbf.in (1.70 and 1.53 m.daN ) T
 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
FOR [1000EM2] (ENGINE-2)
447AL, 448AR, 461AL, 462AR
 D. Expendable Parts
FIG.ITEM
DESIGNATION
IPC-CSN
15
E-SEALS
AIPC 36-11-41-02-025
15
E-SEALS
AIPC 36-11-51-02-025
15
SEALS
AIPC 36-11-52-02-040
 E. Referenced Information
REFERENCE
DESIGNATION
TASK 24-41-00-861-002-A
Energize the Aircraft Electrical Circuits from the External Power
TASK 24-41-00-861-002-A-01
Energize the Aircraft Electrical Circuits from the APU
TASK 24-41-00-862-002-A
De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 24-41-00-862-002-A-01
De-energize the Aircraft Electrical Circuits Supplied from the APU
TASK 36-12-00-860-001-A
Pressurization of the Bleed System with the APU
TASK 36-12-00-860-002-A
Pressurization of the Bleed System through the HP Ground Connector
TASK 49-00-00-860-006-A
APU Shutdown by External Power
TASK 49-00-00-860-006-A-01
APU Shutdown by Batteries
TASK 49-00-00-860-009-A
APU Shutdown by External Power (131-9(A))
TASK 49-00-00-860-009-A-01
APU Shutdown by Batteries (131-9(A))
TASK 71-13-00-010-040-B
Opening of the Fan Cowl Doors
TASK 71-13-00-410-040-B
Closing of the Fan Cowl Doors
TASK 78-30-00-081-041-B
Make the Thrust Reverser Serviceable after Maintenance
TASK 78-30-00-481-041-B
Make the Thrust Reverser Unserviceable for Maintenance
TASK 78-36-00-010-040-B
Opening of the Thrust Reverser Doors
TASK 78-36-00-410-040-B
Closing of the Thrust Reverser Doors
F Mid Stage Tee Duct
3. Job Set-up
Subtask 36-11-49-860-060-A ** ON A/C NOT FOR ALL
A. Aircraft Maintenance Configuration
   (1) Make sure that the aircraft electrical circuits are energized (Ref. AMM TASK 24-41-00-861-002) or (Ref. AMM TASK 24-41-00-861-002).
   (2) Make sure that engine 1(2) is shutdown for a minimum of 5 minutes before you do this procedure.
   (3) In the cockpit, on AIR COND panel 30VU:
     (a) Make sure that the ENG 1(2) BLEED pushbutton-switch is released (the OFF legend is on).
     (b) Make sure that the APU BLEED pushbutton-switch is released (the ON legend is off).
     (c) Make sure that the WARNING NOTICE(S) is(are) in position to tell persons not to operate the pneumatic system.
   (4) In the cockpit, on ENG panel 115VU:
     (a) Make sure that the WARNING NOTICE(S) is(are) in position to tell persons not to start engine 1(2).
   (5) On the HP ground connector:
     (a) Make sure that the WARNING NOTICE(S) is(are) in position to tell persons not to pressurize the pneumatic system.
   (6) On the ENG section of maintenance panel 50VU:
     (a) Make sure that the ON legend of the ENG/FADEC GND PWR 1(2) pushbutton-switch is off.
     (b) Make sure that the WARNING NOTICE(S) is(are) in position to tell persons not to energize FADEC 1(2).
   (7) Make sure that the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE is in position below the engine.
Subtask 36-11-49-010-075-A ** ON A/C NOT FOR ALL
B. Get Access
   (1) Make sure that the fan cowl doors are open (Ref. AMM TASK 71-13-00-010-040):
     (a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
     (b) FOR [1000EM2] (ENGINE-2)
447AL 448AR
   (2) Make sure that the thrust reverser doors are open (Ref. AMM TASK 78-36-00-010-040):
     (a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
     (b) FOR [1000EM2] (ENGINE-2)
461AL 462AR
Subtask 36-11-49-040-058-A ** ON A/C NOT FOR ALL
C. Make sure that the thrust reverser is unserviceable (Ref. AMM TASK 78-30-00-481-041).
Subtask 36-11-49-865-054-A ** ON A/C NOT FOR ALL
D. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUAIR BLEED/ENG 1/CTL3HA1D12
49VUAIR BLEED/ENG 1/MONG2HA1D11
122VUAIR BLEED/ENG 2/CTL3HA2Z23
122VUAIR BLEED/ENG 2/MONG2HA2Z22
4. Procedure
Subtask 36-11-49-420-051-A ** ON A/C NOT FOR ALL
A. Installation of the Mid Stage Tee Duct
   (1) If you use the APU to energize the electrical circuits, stop the APU:
   (2) In the cockpit, on the SD bleed page:
     (a) Make sure that the pressure and the temperature of the bleed-air duct system are in ambient conditions.
WARNING: MAKE SURE THAT THE PNEUMATIC SYSTEM IS DEPRESSURIZED BEFORE YOU START WORK. PRESSURIZED AIR CAN CAUSE INJURY TO PERSONNEL.
WARNING: DO NOT TOUCH THE UNIT UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS WHEN YOU DO THE MAINTENANCE TASK(S).
   (3) Remove the blanking plugs from the mid stage tee duct (20), the bleed PRV (5), the High Pressure (HP) bleed valve (40), and the Intermediate Pressure (IP) bleed check valve (45).
   (4) Put the mid stage tee duct (20) in position between the bleed PRV (5), the HP bleed valve (40), and the IP bleed check valve (45).
   (5) Use serviceable AIPC 36-11-52-02-040 SEALS (15), AIPC 36-11-41-02-025 E-SEALS (15), AIPC 36-11-51-02-025 E-SEALS (15)
and the couplings (10) to connect the duct to the valves
CAUTION: MAKE SURE THE SMOOTH CIRCULAR SURFACE OF THE COUPLING IS RADIALLY OUTBOARD FROM THE ENGINE. DO NOT LET THE COUPLING TOUCH ENGINE COMPONENTS OR STRUCTURE. DAMAGE TO THE COMPONENTS OR STRUCTURE COULD OCCUR.
   (6) Tighten the nuts of the couplings (10) sufficiently to hold the mid stage tee duct (20) in position. Do not torque the coupling nuts at this time.
   (7) If required, adjust the support links (50), (52) so they do not put a load on the mid stage tee duct (20) as follows:
     (a) Adjust the support link (50) to approximately 8.2 IN. (208.2796 MM) between hole centers.
     (b) Adjust the support link (52) to approximately 3.86 IN. (98.0438 MM) between hole centers.
   (8) TORQUE the nuts on the support links to between 60 and 54 lbf.in (0.68 and 0.61 m.daN ) T.
WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
   (9) Safety the nuts with CP8001lockwire 0.032 in. (0.8 mm) dia. or CP8002lockwire 0.032 in. (0.8 mm) dia.
   (10) Put the support links (50) in the brackets on the mid stage tee duct (20).
   (11) Attach the links with the bolts (25), the washers (30), and the nuts (35).
NOTE: The washer must installed with the countersunk against the bolt heads.
   (12) Tighten the nuts sufficiently to hold the mid stage tee duct (20) in position. Do not torque the nuts at this time.
   (13) Make sure that the mid stage tee duct (20) is in the correct position.
   (14) TORQUE the nuts (35) to between 90 and 75 lbf.in (1.02 and 0.85 m.daN ) T.
   (15) TORQUE the coupling nuts as follows:
     (a) TORQUE the coupling nut to the value shown on the coupling.
     (b) Tap the perimeter of the coupling with a HAMMER - FIBER, then torque the coupling nut again.
     (c) Do the torque procedure two times, then torque the coupling nut again.
   (16) Remove the protective covers from the HP sense tube and the boss on the mid stage tee duct (20).
NOTE: The tapered side of the union must face the mid stage tee duct.
   (17) Install the union (55) in the boss on the mid stage tee duct (20).
NOTE: The tapered side of the union must face the mid stage tee duct (20).
   (18) TORQUE the union (55) to between 150 and 135 lbf.in (1.70 and 1.53 m.daN ) T.
   (19) Connect the HP sense tube to the union (55).
   (20) Make sure that the tube is in the correct position.
CAUTION: USE TWO 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.
   (21) TORQUE the coupling nut on the tube to between 156.2 and 127.8 lbf.in (1.77 and 1.44 m.daN ) T.
Subtask 36-11-49-720-056-A ** ON A/C NOT FOR ALL
B. Do this test:
   (1) Pressurize the bleed system through the HP ground connector (Ref. AMM TASK 36-12-00-860-002) or with the APU (Ref. AMM TASK 36-12-00-860-001).
   (2) 0n the panel 30VU, put the X-BLEED selector switch in the OPEN position.
   (3) If you pressurize the bleed system through the HP ground connector, the supplied pressure 30 psi (2.07 bar) must be stable.
   (4) Make sure that there are no leaks at the junctions of the installed duct.
5. Close-up
Subtask 36-11-49-865-055-A ** ON A/C NOT FOR ALL
A. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUAIR BLEED/ENG 1/CTL3HA1D12
49VUAIR BLEED/ENG 1/MONG2HA1D11
122VUAIR BLEED/ENG 2/CTL3HA2Z23
122VUAIR BLEED/ENG 2/MONG2HA2Z22
Subtask 36-11-49-410-051-A ** ON A/C NOT FOR ALL
B. Close Access
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) Close the thrust reverser cowl doors (Ref. AMM TASK 78-36-00-410-040):
     (a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
     (b) FOR [1000EM2] (ENGINE-2)
461AL 462AR
   (3) Remove the access platform(s).
Subtask 36-11-49-440-060-A ** ON A/C NOT FOR ALL
C. Make the thrust reverser serviceable (Ref. AMM TASK 78-30-00-081-041).
Subtask 36-11-49-410-083-A ** ON A/C NOT FOR ALL
D. Close Access
   (1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-040):
     (a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
     (b) FOR [1000EM2] (ENGINE-2)
447AL 448AR
   (2) Remove the WARNING NOTICE(S).
Subtask 36-11-49-862-056-A ** ON A/C NOT FOR ALL
E. De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002) or (Ref. AMM TASK 24-41-00-862-002).
[Rev.10 from 2021] 2026.04.01 01:10:28 UTC
"Aviabrain" 2025