Functional Test of the Bleed Differential Pressure-Transducer with the Test Set P/N 98D36109001000

TASK 36-11-18-720-802-A
Functional Test of the Bleed Differential Pressure-Transducer with the Test Set P/N 98D36109001000

WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE AFTER SHUTDOWN. THE ENGINE CAN STAY HOT FOR A LONG TIME. IF YOU DO NOT OBEY THIS INSTRUCTION, INJURY CAN OCCUR.

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.

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
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 5M (16 FT)- ADJUSTABLE
No specific	1	AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY
No specific	AR	PLUG - BLANKING
No specific	AR	WARNING NOTICE(S)
No specific	Torque wrench: range to between 0.84 and 0.83 m.daN (74.34 and 73.45 lbf.in )
98D36109001000	1	TEST SET - ENGINE BLEED

B. Work Zones and Access Panels

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

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 24-41-00-861-002-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 31-32-00-860-011-A	Procedure to Get Access to the SYSTEM REPORT/TEST/PNEU Page
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
TASK 78-30-00-040-807-A	Deactivation of the Thrust Reverser System for Nacelle Maintenance (ICU)
TASK 78-30-00-440-807-A	Reactivation of the Thrust Reverser System after Nacelle Maintenance (ICU)
Status Page of the MCDU
Functional Test of the Bleed Differential Pressure Sensor with the Test Set P/N 98D36109001000

3. Job Set-up
Subtask 36-11-18-861-053-A

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

Subtask 36-11-18-941-053-A

B. Safety Precautions
(1) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(2) On AIR COND panel 30VU:

Make sure that ENG 1(2) BLEED pushbutton switch is released (OFF legend is on).
Make sure that the APU BLEED pushbutton switch is released (ON legend is off).
Put a WARNING NOTICE(S) in position to tell persons not to operate the pneumatic system.

(3) On ENG panel 115VU:

Put a WARNING NOTICE(S) in position to tell the persons not to start engine 1(2).

(4) On the HP ground connector:

Put a WARNING NOTICE(S) in position to tell persons not to pressurize the pneumatic system.

(5) On the ENG section of maintenance panel 50VU:

Make sure that the ON legend of ENG/FADEC GND PWR 1(2) pushbutton switch is off.
Put a WARNING NOTICE(S) in position to tell persons not to energize FADEC 1(2).

Subtask 36-11-18-865-056-A

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
49VU	AIR BLEED/APU BLEED VLV CTL/BMC1 OVRD	11HV	D14
49VU	AIR BLEED/X FEED/VALVE/BAT	2HV	D13
49VU	AIR BLEED/ENG 2/MONG	3HA2	D12
49VU	AIR BLEED/ENG 1/CTL	2HA1	D11
122VU	AIR BLEED/ENG 1/MONG	3HA1	Z23
122VU	AIR BLEED/ENG 2/CTL	2HA2	Z22
122VU	AIR BLEED/X FEED VALVE/NORM	1HV	Z20
122VU	AIR BLEED/APU BLEED VLV CTL/BMC2 OVRD	12HV	Z19

Subtask 36-11-18-010-053-A

D. Get Access
(1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at the pylon access.
(2) Remove the access panels (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.

Subtask 36-11-18-040-050-A

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 78-30-00-040-807).

Subtask 36-11-18-020-052-A

F. Disconnection of the Sense Lines

WARNING: DO NOT TOUCH THE BLEED VALVE COMPONENTS FOR A SHORT TIME AFTER THE ENGINE IS SHUTDOWN. THE ENGINE COMPONENTS STAY HOT FOR SOME TIME AND CAN CAUSE INJURY.

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

(1) Disconnect the sense lines from the ports (1) and (2) of bleed differential pressure-transducer 18HA1 (18HA2).
(2) Put the PLUG-BLANKING in each disconnected line end.

Subtask 36-11-18-860-054-A

G. Aircraft Maintenance Configuration

Status Page of the MCDU

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

4. Procedure
Subtask 36-11-18-720-051-A

A. Functional Test of the Bleed Differential Pressure-Transducer 18HA1(18HA2)
(1) Close the shutoff valve, the purge valve and the pressure regulator valve on the 98D36109001000 TEST SET - ENGINE BLEED.

NOTE: For a better access to install the adaptor assembly, you can remove the collars on the bleed differential pressure-transducer 18HA1 (18HA2).

(2) Connect an AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY to the 98D36109001000 TEST SET-EBAS,BLEED.

(3) Connect the adaptor assembly on the high pressure port (1) and on the low pressure port (2).
(4) Tighten the adaptor assembly.
(5) Connect the 98D36109001000 TEST SET-EBAS,BLEED with the short hose to the adaptor assembly on the low pressure port (2) of bleed differential pressure-transducer 18HA1 (18HA2).
(6) Set the digital pressure gage back to zero.
(7) Make sure that the regulator valve of the 98D36109001000 TEST SET-EBAS,BLEED is closed before you pressurize the system.
(8) Do the test that follows:

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 98D36109001000 TEST SET-EBAS,BLEED: If there is a manometer on the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY, installation of the primary regulator valve is not necessary. Use the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY shutoff valve and the manometer to slowly pressurize the 98D36109001000 TEST SET-EBAS,BLEED to 14.5 psi (1.00 bar). If there is no manometer in the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY, installation of primary regulator valve is mandatory. In this case the primary regulator valve will limit the pressure in the 98D36109001000 TEST SET-EBAS,BLEED to 14.5 psi (1.00 bar).
3.On the 98D36109001000 TEST SET-EBAS,BLEED: Open the shutoff valve. Use the regulator valve of the 98D36109001000 TEST SET-EBAS,BLEED to slowly pressurize the system to 4 psi (0.2758 bar).	On the 98D36109001000 TEST SET-EBAS,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 98D36109001000 TEST SET-EBAS,BLEED: Use the regulator valve of the 98D36109001000 TEST SET-EBAS,BLEED to depressurize the system.	On the 98D36109001000 TEST SET-EBAS,BLEED: The digital pressure gage shows 0 psi (0.00 bar).
5.On the AIR SOURCE - REGULATED, FILTERED, DRY: Close the shutoff valve.
6.Disconnect the short hose from the adaptor assembly on the low pressure port (2) of the bleed differential pressure-transducer 18HA1(18HA2).
7.Connect the short hose to the adaptor assembly on the high pressure port (1) of the bleed differential pressure-transducer 18HA1(18HA2).
8.Pressurize the 98D36109001000 TEST SET-EBAS,BLEED: If there is a manometer on the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY, installation of the primary regulator valve is not necessary. Use the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY shut off valve and the manometer to slowly pressurize the 98D36109001000 TEST SET-EBAS,BLEED to 14.5 psi (1.00 bar). If there is no manometer in the AIR SOURCE - REGULATED, FILTERED, DRY, installation of primary regulator valve is mandatory. In this case the primary regulator valve will limit the pressure in the 98D36109001000 TEST SET-EBAS,BLEED to 14.5 psi (1.00 bar).
9.On the 98D36109001000 TEST SET-EBAS,BLEED: Open the shutoff valve. Use the regulator valve of the 98D36109001000 TEST SET-EBAS,BLEED to slowly pressurize the system to between 4 psi (0.28 bar) and 10 psi (0.69 bar).	On the 98D36109001000 TEST SET-EBAS,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 98D36109001000 TEST SET-EBAS,BLEED: Use the regulator valve of the 98D36109001000 TEST SET-EBAS,BLEED to depressurize the system.	On the 98D36109001000 TEST SET-EBAS,BLEED: The digital pressure gage shows 0 psi (0.00 bar).

(9) Close the shutoff valve of the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY.
(10) Slowly open the purge valve to depressurize the 98D36109001000 TEST SET-EBAS,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.

(11) Disconnect the short hose from the adaptor assembly on the high pressure port (1) of the bleed differential pressure-transducer 18HA1(18HA2).

5. Close-up
Subtask 36-11-18-860-055-A

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

Subtask 36-11-18-420-052-A

B. Connection of the sense lines:
(1) Remove the PLUG-BLANKING from each disconnected line end.
(2) Connect the sense lines to the bleed differential pressure-transducer ports (1) and (2).

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

(3) TORQUE the nut of the sense lines to between 0.84 and 0.83 m.daN (74.34 and 73.45 lbf.in )

Subtask 36-11-18-440-050-A

C. Reactivation of the Thrust Reverser System
(1) Make the thrust reverser serviceable (Ref. AMM TASK 78-30-00-440-807).

Subtask 36-11-18-410-052-A

D. 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 54-52-11-400-807).
(a) FOR [18HA1] (XDCR-BLEED DIFFERENTIAL PRESS, ENG1)
414BR
(b) FOR [18HA2] (XDCR-BLEED DIFFERENTIAL PRESS, ENG2)
424BR.
(3) Remove the access platform(s).
(4) Remove the WARNING NOTICE(S).

Subtask 36-11-18-862-052-A

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

[Rev.10 from 2021] 2026.04.01 01:08:55 UTC