W DOC AIRBUS | AMM A320F

Installation of the Bleed Differential Pressure-Transducer

TASK 36-11-18-400-801-A
Installation of the Bleed Differential Pressure-Transducer

WARNING: MAKE SURE THAT THE PNEUMATIC SYSTEM IS DEPRESSURIZED BEFORE YOU START WORK. PRESSURIZED AIR CAN CAUSE INJURY TO PERSONNEL.
ZONE: 413
ZONE: 423
FIN: 18HA1 ** ON A/C NOT FOR ALL
FIN: 18HA2 ** ON A/C NOT FOR ALL
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 4M (13 FT)-ADJUSTABLE
No specific
AR
PLUG - BLANKING
No specific
AR
WARNING NOTICE(S)
No specific
Torque wrench: range to between 8.5 and 7.3 m.N (75.22 and 64.60 lbf.in ) T
No specific
Torque wrench: range to between 0.85 and 0.73 m.daN (75.22 and 64.60 lbf.in ) T
 B. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
413
UPPER FWD PYLON
423
UPPER FWD PYLON
FOR [18HA1] (XDCR-BLEED DIFFERENTIAL PRESS, ENG1)
413AT
FOR [18HA2] (XDCR-BLEED DIFFERENTIAL PRESS, ENG2)
423AT
 C. 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 36-11-00-740-802-A
BITE Test of the Engine Bleed Air System (EBAS) (System Test)
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 71-00-00-860-833-A
Procedure to Prevent Engine Motoring
F Bleed-Differential Pressure Transducer ** ON A/C NOT FOR ALL
F Bleed Differential Pressure-Transducer ** ON A/C NOT FOR ALL
FOR [18HA1] (XDCR-BLEED DIFFERENTIAL PRESS, ENG1)
TASK 54-52-11-000-805-A
Removal of the Access Skin Panels
TASK 54-52-11-400-805-A
Installation of the Access Skin Panels
FOR [18HA2] (XDCR-BLEED DIFFERENTIAL PRESS, ENG2)
TASK 54-52-11-000-805-A
Removal of the Access Skin Panels
TASK 54-52-11-400-805-A
Installation of the Access Skin Panels
3. Job Set-up
Subtask 36-11-18-861-051-A ** ON A/C NOT FOR ALL
A. 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).
Subtask 36-11-18-860-050-A ** ON A/C NOT FOR ALL
B. Safety Precautions
   (1) Make sure that the engine 1(2) shutdown occurred for a minimum of 5 minutes before you do this procedure.
   (2) In the cockpit, on AIR COND panel 30VU:
     (a) Make sure that the ENG 1(2) BLEED pushbutton switch is released (OFF legend on).
     (b) Make sure that the APU BLEED pushbutton switch is released (ON legend off).
     (c) Make sure that the WARNING NOTICE(S) is in position to tell persons not to operate the pneumatic system.
   (3) In the cockpit, 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 in position to tell persons not to energize FADEC 1(2).
   (4) Make sure that you did the procedure to prevent engine motoring
(Ref. AMM TASK 71-00-00-860-833).
Subtask 36-11-18-865-051-A ** ON A/C NOT FOR ALL
C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
FOR FIN: 18HA1 (XDCRBLEED DIFFERENTIAL PRESS, ENG1)
49VUAIR BLEED/ENG 1/CTL2HA1D11
122VUAIR BLEED/ENG 1/MONG3HA1Z23
FOR FIN: 18HA2 (XDCRBLEED DIFFERENTIAL PRESS, ENG2)
49VUAIR BLEED/ENG 2/MONG3HA2D12
122VUAIR BLEED/ENG 2/CTL2HA2Z22
Subtask 36-11-18-010-051-A ** ON A/C NOT FOR ALL
D. Get Access
   (1) Make sure that the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE is in position at the pylon access panels.
   (2) Make sure that these access panels are removed:
     (a) FOR [18HA1] (XDCR-BLEED DIFFERENTIAL PRESS, ENG1)
413AT (Ref. AMM TASK 54-52-11-000-805).
     (b) FOR [18HA2] (XDCR-BLEED DIFFERENTIAL PRESS, ENG2)
423AT (Ref. AMM TASK 54-52-11-000-805).
4. Procedure
Subtask 36-11-18-420-050-A ** ON A/C NOT FOR ALL
A. Installation of the Bleed Differential Pressure-Transducer
   (1) If you use the APU to energize the electrical circuits, stop the APU:
WARNING: MAKE SURE THAT THE PNEUMATIC SYSTEM IS DEPRESSURIZED BEFORE YOU START WORK. PRESSURIZED AIR CAN CAUSE INJURY TO PERSONNEL.
   (2) Make sure that you wait for a minimum of 5 minutes until there is no pressure in the bleed-air duct system.
WARNING: DO NOT TOUCH THE UNIT UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS WHEN YOU DO THE MAINTENANCE TASK(S).
   (3) Make sure that the temperature of the bleed-air duct system is in the ambient condition.
   (4) Do a visual inspection and clean the component interface and/or the adjacent area.
   (5) Install the transducer (6) in the clamps (7).
   (6) Put the transducer (6) with the clamps (7) in position on the bracket (8).
   (7) Install the washers (5), the bolts (4) and the nuts (9).
   (8) Tighten the bolts (4).
   (9) Remove the PLUG-BLANKING from each disconnected line end.
   (10) Remove the PLUG - BLANKING from the transducer (6).
CAUTION: USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT THE PNEUMATIC LINES ON UNIONS.
   (11) Connect the senseline (2) to the transducer (6) and tighten it.
CAUTION: USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT THE PNEUMATIC LINES ON UNIONS.
   (12) Connect the senseline (3) to the transducer (6) and tighten it.
   (13) TORQUE the nuts of the ducts (2) and (3) to between 0.85 and 0.73 m.daN (75.22 and 64.60 lbf.in ) T.
   (14) Apply a new red line on the senselines (2) and (3).
   (15) Remove the CAP-BLANKING from each electrical connector and receptacle.
   (16) Make sure that the electrical connector(s) is (are) clean and in the correct condition.
   (17) Connect the electrical connector (1) to the transducer (6).
Subtask 36-11-18-420-050-B ** ON A/C NOT FOR ALL
A. Installation of the Bleed Differential Pressure-Transducer
   (1) If you use the APU to energize the electrical circuits, stop the APU:
WARNING: MAKE SURE THAT THE PNEUMATIC SYSTEM IS DEPRESSURIZED BEFORE YOU START WORK. PRESSURIZED AIR CAN CAUSE INJURY TO PERSONNEL.
   (2) Make sure that you wait for a minimum of 5 minutes until there is no pressure in the bleed-air duct system.
WARNING: DO NOT TOUCH THE UNIT UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS WHEN YOU DO THE MAINTENANCE TASK(S).
   (3) Make sure that the temperature of the bleed-air duct system is in the ambient condition.
   (4) Do a visual inspection and clean the component interface and/or the adjacent area.
   (5) Install the transducer (6) in the clamps (7).
   (6) Put the transducer (6) with the clamps (7) in position on the bracket (8).
   (7) Make sure that the angle between the transducer (6) and the horizontal is -20 deg (-20 deg), see view C of the figure.
NOTE: The "minus" symbol shows that the angle is in the clockwise direction.
   (8) Install the washers (5), the bolts (4) and the nuts (9).
   (9) Tighten the bolts (4).
   (10) Remove the PLUG-BLANKING from each disconnected line end.
   (11) Remove the PLUG - BLANKING from the transducer (6).
   (12) Connect the senseline (1) to the transducer (6).
CAUTION: USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT THE PNEUMATIC LINES ON UNIONS.
   (13) TORQUE the union of the senseline (1) to between 8.5 and 7.3 m.N (75.22 and 64.60 lbf.in ) T.
   (14) Connect the senseline (2) to the transducer (6).
CAUTION: USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT THE PNEUMATIC LINES ON UNIONS.
   (15) TORQUE the union of the senseline (2) to between 8.5 and 7.3 m.N (75.22 and 64.60 lbf.in ) T.
   (16) Apply a new red line on the senselines (1) and (2).
   (17) Remove the CAP-BLANKING from each electrical connector and receptacle.
   (18) Make sure that the electrical connector(s) is (are) clean and in the correct condition.
   (19) Connect the electrical connector (3) to the transducer (6).
Subtask 36-11-18-865-052-A ** ON A/C NOT FOR ALL
B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
FOR FIN: 18HA1 (XDCRBLEED DIFFERENTIAL PRESS, ENG1)
49VUAIR BLEED/ENG 1/CTL2HA1D11
122VUAIR BLEED/ENG 1/MONG3HA1Z23
FOR FIN: 18HA2 (XDCRBLEED DIFFERENTIAL PRESS, ENG2)
49VUAIR BLEED/ENG 2/MONG3HA2D12
122VUAIR BLEED/ENG 2/CTL2HA2Z22
Subtask 36-11-18-710-050-A ** ON A/C NOT FOR ALL
C. Do the BITE test of the Engine Bleed Air System (EBAS) (Ref. AMM TASK 36-11-00-740-802).
5. Close-up
Subtask 36-11-18-410-050-A ** ON A/C NOT FOR ALL
A. Close Access
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) Install these access panels:
     (a) FOR [18HA1] (XDCR-BLEED DIFFERENTIAL PRESS, ENG1)
413AT (Ref. AMM TASK 54-52-11-400-805).
     (b) FOR [18HA2] (XDCR-BLEED DIFFERENTIAL PRESS, ENG2)
423AT (Ref. AMM TASK 54-52-11-400-805).
   (3) Remove the access platform(s).
   (4) Remove the WARNING NOTICE(S).
Subtask 36-11-18-862-050-A ** ON A/C NOT FOR ALL
B. 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 01:08:48 UTC
"Aviabrain" 2025