Installation of the Bleed Differential Pressure-Transducer

TASK 36-11-18-400-802-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.

WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.

WARNING: YOU MUST NOT TOUCH HOT PARTS WITHOUT APPLICABLE GLOVES. HOT PARTS CAN CAUSE AN INJURY.

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.

ZONE: 414
ZONE: 424
FIN: 18HA1
FIN: 18HA2

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	WARNING NOTICE(S)
No specific	Torque wrench: range to between 0.85 and 0.73 m.daN (75.22 and 64.60 lbf.in )

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
414	UPPER FWD PYLON
424	UPPER FWD PYLON
191DB
FOR [18HA1] (XDCR-BLEED DIFFERENTIAL PRESS, ENG1)
414BR
FOR [18HA2] (XDCR-BLEED DIFFERENTIAL PRESS, ENG2)
424BR

C. Referenced Information

REFERENCE	DESIGNATION
TASK 20-23-22-910-001-A	Marking of the Unions after Application of Standard or Specific Tightening Torque
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 27-00-00-480-002-A	Installation of the Flap/Slat Control-Lever Locking Tool (98D27803000000)
TASK 36-11-00-740-804-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 54-52-11-000-807-A	Removal of the Access Skin Panels
TASK 54-52-11-400-807-A	Installation of the Access Skin Panels
Bleed Differential Pressure-Transducer

3. Job Set-up
Subtask 36-11-18-861-055-A

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 36-11-18-941-055-A

B. Safety Precautions
(1) Make sure that the engine 1(2) shutdown occurred not less than five minutes before you do this procedure.
(2) 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) On the center pedestal, on ENG panel 115VU:
(a) Make sure that the ENG/MODE selector switch is in the NORM position.
(b) Make sure that the ENG/MASTER 1(2) control switch was in the OFF position not less than five minutes before you do this procedure.
(c) Make sure that the WARNING NOTICE(S) are in position to tell persons not to operate:

The ENG/MODE selector switch, and
The ENG/MASTER 1(2) control switch.

(4) 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).
(5) On FLAPS panel 114VU:
(a) Make sure that the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION is in position on the flap/slat control lever (Ref. AMM TASK 27-00-00-480-002).
(6) Make sure that the WARNING NOTICE(S) is in position on the flap/slat control lever to tell persons not to operate the flap/slat controls.
(7) On the access door 191DB, on the HP ground connector:
(a) Make sure that the WARNING NOTICE(S) is in position to tell persons not to pressurize the pneumatic system.

Subtask 36-11-18-865-058-A

C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
FOR FIN: 18HA1 (XDCRBLEED DIFFERENTIAL PRESS, ENG1)
49VU	AIR BLEED/ENG 1/CTL	2HA1	D11
122VU	AIR BLEED/ENG 1/MONG	3HA1	Z23
FOR FIN: 18HA2 (XDCRBLEED DIFFERENTIAL PRESS, ENG2)
49VU	AIR BLEED/ENG 2/MONG	3HA2	D12
122VU	AIR BLEED/ENG 2/CTL	2HA2	Z22

Subtask 36-11-18-010-055-A

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 (Ref. AMM TASK 54-52-11-000-807):
(a) FOR [18HA1] (XDCR-BLEED DIFFERENTIAL PRESS, ENG1)
414BR
(b) FOR [18HA2] (XDCR-BLEED DIFFERENTIAL PRESS, ENG2)
424BR

4. Procedure
Subtask 36-11-18-420-053-A

A. Installation of the Bleed Differential Pressure-Transducer
(1) If you use the APU to energize the electrical circuits, stop the APU:

For GTCP 36-300 APU (Ref. AMM D/O 49-00-00-86)
For APS 3200 APU (Ref. AMM D/O 49-00-00-86)
For 131-9(A) APU (Ref. AMM TASK 49-00-00-860-009).

(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).

CAUTION: USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT THE PNEUMATIC LINES ON UNIONS.

(3) Do a visual inspection and clean the component interface and/or the adjacent area.
(4) Install the transducer (6) in the clamps (4).
(5) Remove the PLUG-BLANKING from each disconnected line end.
(6) Remove the blanking plugs from the transducer (6).
(7) Put the transducer (6) in position on the bracket (7).
(8) Install the bolts (5).
(9) Tighten the bolts (5).
(10) Connect the duct (2) to the transducer (6).
(11) Connect the duct (3) to the transducer (6).
(12) 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 )

.
(13) Identify the tightened union nuts of the duct (2) and (3) with a red line (Ref. AMM TASK 20-23-22-910-001).
(14) Remove the CAP-BLANKING from each electrical connector and receptacle.
(15) Make sure that the electrical connector(s) is (are) clean and in the correct condition.
(16) Connect the electrical connector (1) to the transducer (6).

Subtask 36-11-18-865-059-A

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
FOR FIN: 18HA1 (XDCRBLEED DIFFERENTIAL PRESS, ENG1)
49VU	AIR BLEED/ENG 1/CTL	2HA1	D11
122VU	AIR BLEED/ENG 1/MONG	3HA1	Z23
FOR FIN: 18HA2 (XDCRBLEED DIFFERENTIAL PRESS, ENG2)
49VU	AIR BLEED/ENG 2/MONG	3HA2	D12
122VU	AIR BLEED/ENG 2/CTL	2HA2	Z22

Subtask 36-11-18-740-050-A

C. Do the BITE test of the Engine Bleed Air System-Application (Ref. AMM TASK 36-11-00-740-804).

5. Close-up
Subtask 36-11-18-410-053-A

A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Install these access panels (Ref. AMM TASK 54-52-11-400-807):
(a) FOR [18HA1] (XDCR-BLEED DIFFERENTIAL PRESS, ENG1)
414BR
(b) FOR [18HA2] (XDCR-BLEED DIFFERENTIAL PRESS, ENG2)
424BR
(3) On FLAPS panel 114VU:

Remove the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION from the flap/slat control lever.

(4) Remove the access platform(s).
(5) Remove the WARNING NOTICE(S).

Subtask 36-11-18-862-053-A

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 12:38:03 UTC