W DOC AIRBUS | AMM A320F

Installation of the P2/T2 Sensor [IAE]

TASK 73-22-11-400-010-A
Installation of the P2/T2 Sensor

FIN: 4014KS ** 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 2M (6 FT)
No specific
AR
WARNING NOTICE(S)
No specific
Torque wrench: range to between 38.5 and 31.5 lbf.in (0.44 and 0.36 m.daN ) T
No specific
Torque wrench: range to between 44 and 36 lbf.in (0.50 and 0.41 m.daN ) T
No specific
Torque wrench: range to between 49.5 and 40.5 lbf.in (0.56 and 0.46 m.daN ) T
No specific
Torque wrench: range to between 110 and 90 lbf.in (1.24 and 1.02 m.daN ) T
No specific
Torque wrench: range to between 105 and 95 lbf.in (1.19 and 1.07 m.daN ) T
No specific
Torque wrench: range to between 145 and 135 lbf.in (1.64 and 1.53 m.daN ) T
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.V02-126)
lockwire
 C. Expendable Parts
FIG.ITEM
DESIGNATION
IPC-CSN
11
PACKING
AIPC 73-22-48-80-050
 D. 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 24-41-00-861-002-A-02
Energize the Aircraft Electrical Circuits from Engine 1(2)
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 24-41-00-862-002-A-02
De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)
TASK 31-60-00-860-001-A
EIS Start Procedure
TASK 31-60-00-860-002-A
EIS Stop Procedure
TASK 70-23-11-911-013-A
General Torque Tightening Techniques
TASK 70-23-13-911-010-A
Procedures for the Installation of Preformed Packings
TASK 70-23-15-912-010-A
Connection of Electrical Connectors
TASK 71-11-11-300-014-A
Repair the Aerodynamic Sealant on the Air Intake Cowl or the P2/T2 Sensor
TASK 73-22-11-710-040-A
Operational Test of the P2/T2 Probe Heater
F P2/T2 Sensor
3. Job Set-up
Subtask 73-22-11-860-050-A ** ON A/C NOT FOR ALL
A. Aircraft Maintenance Configuration
   (1) On the center pedestal, on the ENG panel 115VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the engine.
   (2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a WARNING NOTICE(S) is in position to tell persons not to energize the FADEC 1(2).
   (3) Make sure that the ACCESS PLATFORM 2M (6 FT) is in position.
Subtask 73-22-11-140-050-A ** ON A/C NOT FOR ALL
B. Remove the sealant from the P2/T2 probe installation area (Ref. AMM TASK 71-11-11-300-014).
Subtask 73-22-11-630-050-A ** ON A/C NOT FOR ALL
C. Remove all the applicable covers/caps/plugs from the openings.
Subtask 73-22-11-410-050-A ** ON A/C NOT FOR ALL
D. Preparation of the replacement P2/T2 sensor
   (1) Install the union (10):
     (a) Install the AIPC 73-22-48-80-050 PACKING (11) to the union (10) (Ref. AMM TASK 70-23-13-911-010).
     (b) Install the union (10) to the sensor (8).
     (c) TORQUE the union to between 105 and 95 lbf.in (1.19 and 1.07 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
4. Procedure
Subtask 73-22-11-420-050-A ** ON A/C NOT FOR ALL
A. Install the P2/T2 sensor
   (1) Install the sensor (8) so that the two openings on the airfoil section point forwards.
   (2) Install the clip mounting bracket (9) and the sensor to the mounting bracket with the four washers (1) and the six bolts (2).
   (3) TORQUE the bolts to between 110 and 90 lbf.in (1.24 and 1.02 m.daN ) T (Ref. AMM TASK 70-23-11-911-013)
   (4) Safety the bolts in two groups of three with the lockwire (Material No.V02-126)
   (5) Install the bonding clamp (4) to the P2/T2 sensor (8). Set the bonding clamp (4) to the position noted on removal.
   (6) Safety the bonding clamp (4) with the bolt (5) and the nut (3). TORQUE the nut (3) to between 49.5 and 40.5 lbf.in (0.56 and 0.46 m.daN ) T.
   (7) Apply the aerodynamic sealant around the P2/T2 probe (Ref. AMM TASK 71-11-11-300-014).
NOTE: If time is not sufficient to meet cure requirements, it is permitted to postpone the application of the aerodynamic sealant. Aerodynamic sealant must be applied within 14 days.
Subtask 73-22-11-420-051-A ** ON A/C NOT FOR ALL
B. Connect the electrical connectors to the sensor
   (1) Attach the electrical connectors 4014KS-A (15) and 4014KS-B (14) to the sensor and tighten them by hand (Ref. AMM TASK 70-23-15-912-010).
   (2) TORQUE the coupling nuts of the 4014KS-A (15) and 4014KS-B (14) electrical connectors to between 44 and 36 lbf.in (0.50 and 0.41 m.daN ) T (Ref. AMM TASK 70-23-15-912-010).
   (3) Install the P2 tube
     (a) Attach the P2 tube (12) with the end connectors.
     (b) TORQUE the tube end connectors to between 145 and 135 lbf.in (1.64 and 1.53 m.daN ) T (Ref. AMM TASK 70-23-11-911-013)
   (4) Install the access panel
     (a) Attach the access panel (6) to the air intake cowl with the 18 bolts (7).
     (b) TORQUE the bolts to between 38.5 and 31.5 lbf.in (0.44 and 0.36 m.daN ) T (Ref. AMM TASK 70-23-11-911-013)
Subtask 73-22-11-861-050-A ** ON A/C NOT FOR ALL
C. Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).
Subtask 73-22-11-869-050-A ** ON A/C NOT FOR ALL
D. Do an EIS Start Procedure (ECAM display unit only) (Ref. AMM TASK 31-60-00-860-001)
Subtask 73-22-11-710-050-B ** ON A/C NOT FOR ALL
E. Do the following test
ACTION
RESULT
1.On the MAINTENANCE PNL 50VU, release the FADEC GND PWR ENG ENG1(2) pushbutton switch.
  • On the pushbutton switch, the ON legend comes on.
  • On the upper ECAM DU, the engine parameters EPR, EGT and Fuel Flow come into view.
2.On the upper display unit of the ECAM system, make sure that the EPR indication is not crossed (EPR=1)

3.On the MAINTENANCE PNL 50VU, push the FADEC GND PWR ENG ENG1(2) pushbutton switch.
  • On the pushbutton switch, the ON legend goes off.
  • On the upper ECAM DU, the engine parameters EPR, EGT and Fuel Flow go out of view.
   (1) Do the operational test of the P2/T2 (Ref. AMM TASK 73-22-11-710-040).
Subtask 73-22-11-862-050-A ** ON A/C NOT FOR ALL
F. De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002).
Subtask 73-22-11-860-051-A ** ON A/C NOT FOR ALL
G. Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002)
5. Close-up
Subtask 73-22-11-942-050-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) Remove the access platform(s).
   (3) Remove the WARNING NOTICE(S).
[Rev.10 from 2021] 2026.04.01 03:00:46 UTC
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