Functional Test of the Differential Pressure Sensor (DPS) with the Bleed Test Set P/N 98L36103002000 and the Adaptor Kit P/N 98D36109004000

TASK 36-11-18-720-804-A
Functional Test of the Differential Pressure Sensor (DPS) with the Bleed Test Set P/N 98L36103002000 and the Adaptor Kit P/N 98D36109004000

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: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE IN POSITION BEFORE YOU START A TASK ON OR NEAR:

THE FLIGHT CONTROLS
THE FLIGHT CONTROL SURFACES
THE LANDING GEAR AND RELATED DOORS
COMPONENTS THAT MOVE.

MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

WARNING: BEFORE YOU INSTALL/REMOVE THE GSE TOOL, READ THE MANUFACTURER'S INSTRUCTIONS, AND, WHILE YOU OPERATE THIS TOOL, CAREFULLY OBEY THEM. IF YOU DO NOT DO THIS, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

WARNING: BEFORE YOU START WORK, YOU MUST PUT ON A SAFETY HARNESS AND ATTACH IT TO THE ACCESS PLATFORM. WITHOUT A SAFETY HARNESS, YOU CAN FALL. THIS CAN KILL YOU OR CAUSE YOU INJURY.

CAUTION: BE CAREFUL WHEN YOU CONNECT/DISCONNECT THE TEST SET TO/FROM THE EQUIPMENT. THE PRESSURE REGULATING VALVE AND THE PRESSURE GAGE ASSEMBLY OF THE TEST SET ARE HEAVY AND CAN CAUSE DAMAGE TO THE ENGINE.

FIN: 18HA1 ** ON A/C NOT FOR ALL
FIN: 18HA2 ** ON A/C NOT FOR ALL

1. Reason for the Job

NOTE: Two persons are necessary to do this task.

NOTE: To do this test, you need an TEST SET - ENGINE BLEED and a ADAPTORS KIT-BLEED. The ADAPTORS KIT-BLEED includes the adaptor to connect the TEST SET - ENGINE BLEED to the DPS.

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	1	AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY
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 )
98D27803000000	1	LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION
98D36109004000	1	ADAPTORS KIT - BLEED
98L36103002000	1	TEST SET - ENGINE BLEED

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
191DB
FOR [18HA1] (XDCR-BLEED DIFFERENTIAL PRESS, ENG1)
413AT
FOR [18HA2] (XDCR-BLEED DIFFERENTIAL PRESS, ENG2)
423AT

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 24-41-00-861-002-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 27-00-00-080-002-A	Removal of the Flap/Slat Control-Lever Locking Tool (98D27803000000)
TASK 27-00-00-480-002-A	Installation of the Flap/Slat Control-Lever Locking Tool (98D27803000000)
TASK 31-32-00-860-011-A	Procedure to Get Access to the SYSTEM REPORT/TEST/PNEU Page
TASK 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
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
TASK 78-30-00-040-805-A	Deactivation of the Thrust Reverser System for Ground Maintenance
TASK 78-30-00-440-805-A	Reactivation of the Thrust Reverser System after Ground Maintenance
DPS with the Bleed Test Set P/N 98L36103002000 and the Adaptor Kit P/N 98D36109004000
Status Page of the MCDU

3. Job Set-up
Subtask 36-11-18-861-059-A ** ON A/C NOT FOR ALL

A. Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).

Subtask 36-11-18-860-066-A ** ON A/C NOT FOR ALL

B. Aircraft Maintenance Configuration
(1) Do the EIS start procedure (only EWD and SD) (Ref. AMM TASK 31-60-00-860-001).

Subtask 36-11-18-941-059-A ** ON A/C NOT FOR ALL

C. Safety Precautions
(1) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(2) On the AIR COND section of 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) Put a WARNING NOTICE(S) in position to tell persons not to operate the pneumatic system.
(3) On the center pedestal, on the ENG section of 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) Put a WARNING NOTICE(S) in position to tell the 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) Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).
(5) On FLAPS panel 114VU:
(a) Put the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION in position on the flap/slat control lever (Ref. AMM TASK 27-00-00-480-002).
(6) Put a WARNING NOTICE(S) 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) Put a WARNING NOTICE(S) in position to tell persons not to pressurize the pneumatic system.

Subtask 36-11-18-865-065-A ** ON A/C NOT FOR ALL

D. Make sure that this(these) circuit breaker(s) is(are) closed:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
FOR FIN: 18HA1 (XDCRBLEED DIFFERENTIAL PRESS, ENG1)
49VU	AIR BLEED/APU BLEED VLV CTL/BMC1 OVRD	11HV	D14
49VU	AIR BLEED/ENG 1/CTL	2HA1	D11
122VU	AIR BLEED/ENG 1/MONG	3HA1	Z23
122VU	AIR BLEED/X FEED VALVE/NORM	1HV	Z20
FOR FIN: 18HA2 (XDCRBLEED DIFFERENTIAL PRESS, ENG2)
49VU	AIR BLEED/X FEED/VALVE/BAT	2HV	D13
49VU	AIR BLEED/ENG 2/MONG	3HA2	D12
122VU	AIR BLEED/ENG 2/CTL	2HA2	Z22
122VU	AIR BLEED/APU BLEED VLV CTL/BMC2 OVRD	12HV	Z19

Subtask 36-11-18-040-054-A ** ON A/C NOT FOR ALL

E. Deactivation of the Thrust Reverser System

WARNING: MAKE SURE THAT THE THRUST REVERSER HYDRAULIC CONTROL UNIT (HCU) IS DEACTIVATED BEFORE YOU DO WORK ON OR AROUND THE THRUST REVERSER. IF THE HCU IS NOT DEACTIVATED, THERE IS A RISK OF UNWANTED THRUST REVERSER OPERATION WHICH CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

(1) Make the thrust reverser unserviceable for maintenance (Ref. AMM TASK 78-30-00-040-805).

Subtask 36-11-18-010-061-A ** ON A/C NOT FOR ALL

F. Get Access
(1) Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position below the pylon access panels.
(2) Remove the access panels (Ref. AMM TASK 54-52-11-000-805):
(a) FOR [18HA1] (XDCR-BLEED DIFFERENTIAL PRESS, ENG1)
413AT.
(b) FOR [18HA2] (XDCR-BLEED DIFFERENTIAL PRESS, ENG2)
423AT.

Subtask 36-11-18-020-058-A ** ON A/C NOT FOR ALL

G. Disconnection of the Sense Lines

DPS with the Bleed Test Set P/N 98L36103002000 and the Adaptor Kit P/N 98D36109004000 ** ON A/C NOT FOR ALL

CAUTION: USE A SECOND WRENCH TO APPLY COUNTER TORQUE TO THE UNIONS WHEN YOU DISCONNECT/CONNECT THE PNEUMATIC LINES FROM/TO THE UNIONS. IF YOU DO NOT OBEY THIS PRECAUTION, YOU CAN TWIST THE PNEUMATIC LINES AND CAUSE DAMAGE TO THEM.

(1) Disconnect the sense lines from the ports (1) and (2) of DPS 18HA1(18HA2).
(2) Put the blanking plug in each disconnected line end.

Subtask 36-11-18-860-062-A ** ON A/C NOT FOR ALL

H. Aircraft Maintenance Configuration

Status Page of the MCDU ** ON A/C NOT FOR ALL

(1) Adjust the brightness of the MCDU screen.
(2) On the MCDU, get access to the SYSTEM REPORT/TEST PNEU/SENSOR STATUS menu page (Ref. AMM TASK 31-32-00-860-011).

4. Procedure
Subtask 36-11-18-480-054-A ** ON A/C NOT FOR ALL

A. Connection of the Test Set
(1) Close the shutoff valve, the purge valve and the pressure regulator valve on the 98L36103002000 TEST SET - ENGINE BLEED.

NOTE: You can remove the collars from the DPS for an easier installation of the 98D36109004000 ADAPTORS KIT - BLEED.

(2) Connect the 98L36103002000 TEST SET - ENGINE BLEED with the 98D36109004000 ADAPTORS KIT - BLEED to the low pressure port (2) of the DPS.
(3) Set the digital pressure gage back to zero.
(4) Connect an AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY to the 98L36103002000 TEST SET - ENGINE BLEED.
(5) Make sure that the regulator valve of the 98L36103002000 TEST SET - ENGINE BLEED is closed before you pressurize the system.

Subtask 36-11-18-720-057-A ** ON A/C NOT FOR ALL

B. Functional Test of DPS 18HA1(18HA2)

WARNING: WHEN YOU USE COMPRESSED AIR:

USE THE CORRECT PROTECTION (FACE SHIELD OR GOGGLES)
DO NOT POINT THE AIRFLOW AT YOURSELF OR OTHER PERSONS.

LOOSE PARTICLES AND/OR HIGH PRESSURE AIR CAN CAUSE INJURY.

WARNING: WHEN YOU USE COMPRESSED AIR:

USE THE CORRECT PROTECTION (FACE SHIELD OR GOGGLES)
DO NOT POINT THE AIRFLOW AT YOURSELF OR OTHER PERSONS.

LOOSE PARTICLES AND/OR HIGH PRESSURE AIR CAN CAUSE INJURY.

(1) Do the test(s):

ACTION	RESULT
1.On the MCDU control panel: Push the SENSOR STATUS key.	On the MCDU: The SENSOR STATUS page comes into view and shows the bleed pressure.
2.Pressurize the 98L36103002000 TEST SET - ENGINE BLEED: A.If the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY, has a manometer: Do not install the primary regulator valve. Slowly pressurize the 98L36103002000 TEST SET - ENGINE BLEED to 14.5 psi (1.00 bar) with the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY shutoff valve and the manometer. B.If the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY, has no manometer: Install the primary regulator valve. NOTE: The primary regulator valve will keep the pressure in limit in the 98L36103002000 TEST SET - ENGINE BLEED to 14.5 psi (1.00 bar).
3.On the 98L36103002000 TEST SET - ENGINE BLEED: Open the shutoff valve. Slowly pressurize the system to 4 psi (0.28 bar) with the regulator valve of the 98L36103002000 TEST SET - ENGINE BLEED.	On the 98L36103002000 TEST SET - ENGINE BLEED: The digital pressure gage shows the pressure. On the SD: The BLEED page shows a value between -0.5 +0.05 psi or -0.05 psi (-0.0345 +0.0034 bar or -0.0034 bar) and 0 +0.05 psi or -0.05 psi (0.0000 +0.0034 bar or -0.0034 bar).
4.On the 98L36103002000 TEST SET - ENGINE BLEED: Depressurize the system with the regulator valve of the 98L36103002000 TEST SET - ENGINE BLEED.	On the 98L36103002000 TEST SET - ENGINE BLEED: The digital pressure gage shows 0 psi (0.00 bar).
5.On the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY: Close the shutoff valve.
6.Disconnect the 98D36109004000 ADAPTORS KIT - BLEED from the low pressure port (2) of DPS 18HA1(18HA2).
7.Connect the 98D36109004000 ADAPTORS KIT - BLEED to the high pressure port (1) of DPS 18HA1(18HA2).
8.Pressurize the 98L36103002000 TEST SET - ENGINE BLEED: A.If the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY, has a manometer: Do not install the primary regulator valve. Slowly pressurize the 98L36103002000 TEST SET - ENGINE BLEED to 14.5 psi (1.00 bar) with the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY shutoff valve and the manometer. B.If the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY, has no manometer: Install the primary regulator valve. NOTE: The primary regulator valve will keep the pressure in limit in the 98L36103002000 TEST SET - ENGINE BLEED to 14.5 psi (1.00 bar).
9.On the 98L36103002000 TEST SET - ENGINE BLEED: Open the shutoff valve. Slowly pressurize the system from 4 psi (0.28 bar) to 10 psi (0.69 bar) with the regulator valve of the 98L36103002000 TEST SET - ENGINE BLEED.	On the 98L36103002000 TEST SET - ENGINE BLEED: The digital pressure gage shows the pressure. On the SD: The BLEED page shows the saturation pressure value +4 +0.05 psi or -0.05 psi (0.2758 +0.0034 bar or -0.0034 bar).
10.On the 98L36103002000 TEST SET - ENGINE BLEED: Depressurize the system with the regulator valve of the 98L36103002000 TEST SET - ENGINE BLEED.	On the 98L36103002000 TEST SET - ENGINE BLEED: The digital pressure gage shows 0 psi (0.00 bar).

Subtask 36-11-18-020-059-A ** ON A/C NOT FOR ALL

C. Disconnection of the Test Set
(1) Close the shutoff valve of the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY.
(2) Slowly open the purge valve to depressurize the 98L36103002000 TEST SET - ENGINE BLEED to 0 psi (0.00 bar).

WARNING: BEFORE YOU START TO REMOVE THE TOOLING, MAKE SURE THAT THERE IS NO PRESSURIZED GAS LEFT INSIDE THE DUCTS. IT CAN CAUSE AN INJURY TO PERSONNEL AND/OR DAMAGE TO EQUIPMENT.

(3) Disconnect the 98D36109004000 ADAPTORS KIT - BLEED from the high pressure port (1) of DPS 18HA1(18HA2).
(4) Disconnect the 98D36109004000 ADAPTORS KIT - BLEED from the 98L36103002000 TEST SET - ENGINE BLEED.
(5) Disconnect the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY from the 98L36103002000 TEST SET - ENGINE BLEED.

5. Close-up
Subtask 36-11-18-860-063-A ** ON A/C NOT FOR ALL

A. Aircraft Maintenance Configuration
(1) Close the MCDU session.
(2) Fully decrease the brightness of the MCDU screen (display off).

Subtask 36-11-18-420-057-A ** ON A/C NOT FOR ALL

B. Connection of the sense Lines

DPS with the Bleed Test Set P/N 98L36103002000 and the Adaptor Kit P/N 98D36109004000 ** ON A/C NOT FOR ALL

(1) Remove the blanking plug from each disconnected line end.
(2) Connect the sense lines to the ports (1) and (2) of the DPS.

(3) TORQUE the nuts of the sense lines to between 0.85 and 0.73 m.daN (75.22 and 64.60 lbf.in )

.
(4) Put a red line between the nut of the sense line and the test port of the DPS (Ref. AMM TASK 20-23-22-910-001).

Subtask 36-11-18-410-059-A ** ON A/C NOT FOR ALL

C. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Install the access panels (Ref. AMM TASK 54-52-11-400-805):
(a) FOR [18HA1] (XDCR-BLEED DIFFERENTIAL PRESS, ENG1)
413AT.
(b) FOR [18HA2] (XDCR-BLEED DIFFERENTIAL PRESS, ENG2)
423AT.
(3) On FLAPS panel 114VU:
(a) Remove the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION from the flap/slat control lever (Ref. AMM TASK 27-00-00-080-002).
(4) Remove the access platform(s).
(5) Remove the WARNING NOTICE(S).

Subtask 36-11-18-440-053-A ** ON A/C NOT FOR ALL

D. Reactivation of the Thrust Reverser System
(1) Make the thrust reverser serviceable after maintenance (Ref. AMM TASK 78-30-00-440-805).

Subtask 36-11-18-860-065-A ** ON A/C NOT FOR ALL

E. Aircraft Maintenance Configuration
(1) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).

Subtask 36-11-18-862-057-A ** ON A/C NOT FOR ALL

F. De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).

[Rev.10 from 2021] 2026.04.01 01:08:53 UTC