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

TASK 36-11-00-790-810-A
Leak Test of the Differential Pressure Sensor (DPS) Sense Lines with the Bleed Test Set P/N 98L36103002000 and the Adaptor Kit P/N 98D36109004000

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: 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: MAKE SURE THAT THE PNEUMATIC SYSTEM IS DEPRESSURIZED BEFORE YOU START WORK. PRESSURIZED AIR CAN CAUSE INJURY TO PERSONNEL.

WARNING: ALWAYS USE APPLICABLE GLOVES TO TOUCH HOT PARTS. HOT PARTS CAN CAUSE INJURY TO PERSONS.

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.

ZONE: 410
ZONE: 420

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	1	AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY
No specific	AR	WARNING NOTICE(S)
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
410	ENG 1 PYLON BOX AND FORWARD FAIRING
420	ENG 2 PYLON BOX AND FORWARD FAIRING
191DB
FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
413CT, 413ET, 414BR, 472AR
FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
423CT, 423ET, 424BR, 424CR

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 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 36-11-18-000-802-A	Removal of the Bleed Differential Pressure-Transducer
TASK 36-11-18-400-802-A	Installation of the Bleed Differential Pressure-Transducer
TASK 36-11-49-000-833-A	Removal of the Sense Line between the Bleed-Air Precooler Exchanger (Upstream) and the Bleed Differential Pressure-Transducer
TASK 36-11-49-000-834-A	Removal of the Sense Line between the Bleed-Air Precooler Exchanger (Downstream) and the Bleed Differential Pressure-Transducer
TASK 36-11-49-400-833-A	Installation of the Sense Line between the Bleed-Air Precooler Exchanger (Upstream) and the Bleed Differential Pressure-Transducer
TASK 36-11-49-400-834-A	Installation of the Sense Line between the Bleed-Air Precooler Exchanger (Downstream) and the Bleed Differential Pressure-Transducer
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 54-53-11-000-806-A	Removal of the Pylon-to-Wing Access Panels and Doors
TASK 54-53-11-400-806-A	Installation of the Pylon-to-Wing Access Panels and Doors
TASK 78-30-00-040-809-A	Deactivation of the Thrust Reverser System for Ground Maintenance
TASK 78-30-00-440-809-A	Reactivation of the Thrust Reverser System after Ground Maintenance
DPS Sense Lines with the Bleed Test Set P/N 98L36103002000 and the Adaptor Kit P/N 98D36109004000

3. Job Set-up
Subtask 36-11-00-861-177-A

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

Subtask 36-11-00-941-165-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 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 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).
(4) 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).
(5) Put a WARNING NOTICE(S) in position on the flap/slat control lever to tell persons not to operate the flap/slat controls.
(6) On 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 36-11-00-865-175-A

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
FOR FIN: 4020KM1 (POWER PLANTDEMOUNTABLE, ENGINE 1)
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: 4020KM2 (POWER PLANTDEMOUNTABLE, ENGINE 2)
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 36-11-00-040-149-A

D. Deactivation of the Thrust Reverser System

WARNING: YOU MUST DEACTIVATE THE THRUST REVERSER BEFORE YOU DO WORK ON OR AROUND IT. IF YOU DO NOT, THE THRUST REVERSER CAN OPERATE ACCIDENTALLY AND CAUSE AN INJURY AND/OR DAMAGE.

(1) Make the thrust reverser unserviceable for maintenance (Ref. AMM TASK 78-30-00-040-809).

Subtask 36-11-00-010-219-A

E. Get Access
(1) Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position below the pylon access panels.
(2) Remove these access panels (Ref. AMM TASK 54-52-11-000-807) and (Ref. AMM TASK 54-53-11-000-806):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
413CT, 414BR, 413ET and 472AR.
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
423CT, 424BR, 423ET and 424CR.

Subtask 36-11-00-020-067-A

F. Disconnection of the Sense Lines

DPS Sense Lines with the Bleed Test Set P/N 98L36103002000 and the Adaptor Kit P/N 98D36109004000

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 DPS sense-line end (6) from the port (5) of the DPS (Ref. AMM TASK 36-11-18-000-802).
(2) Disconnect the DPS sense-line end (7) from the port (8) of the DPS (Ref. AMM TASK 36-11-18-000-802).
(3) Put the blanking plug on the sense line ports (5) and (8) of the the DPS.
(4) Put the blanking plug on the DPS sense-line ends (6) and (7).
(5) Disconnect the DPS sense-line end (1) from the port (2) of the bleed-air precooler exchanger (upstream) (Ref. AMM TASK 36-11-49-000-833).
(6) Disconnect the DPS sense-line end (4) from the port (3) of the bleed-air precooler exchanger (downstream) (Ref. AMM TASK 36-11-49-000-834).
(7) Put the blanking plug on the sense line ports (2) and (3) of the bleed-air precooler exchanger.

4. Procedure
Subtask 36-11-00-480-129-A

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.
(2) Connect the 98L36103002000 TEST SET - ENGINE BLEED with the 98D36109004000 ADAPTORS KIT-BLEED to the end of the DPS sense line (4).
(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 36-11-00-790-069-A

B. Leak Test of DPS Sense Lines

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.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 psig (1.00 bar rel.) 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 psig (1.00 bar rel.).
2.On the 98L36103002000 TEST SET - ENGINE BLEED: Open the shutoff valve. Slowly pressurize the system to 4 psig (0.28 bar rel.) with the regulator valve of the 98L36103002000 TEST SET - ENGINE BLEED.	On the 98L36103002000 TEST SET - ENGINE BLEED: The digital pressure gage shows the saturation pressure value +4 +0.05 -0. psig (+0.2758 +0.0034 -0.0034 bar rel.).
3.On the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY: Close the shutoff valve.	On the digital pressure gauge: Make sure that the indication shown does not decrease to 0 psig (0.00 bar rel.) in less than 20 seconds. If the pressure decreases to 0 psig (0.00 bar rel.) in less than 20 seconds, replace the damaged DPS sense line.
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 psig (0.00 bar rel.).
5.Disconnect the 98D36109004000 ADAPTORS KIT-BLEED from the DPS sense line (1).
6.Connect the 98D36109004000 ADAPTORS KIT-BLEED to the end of the DPS sense line (4).
7.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 psig (1.00 bar rel.) 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 psig (1.00 bar rel.).
8.On the 98L36103002000 TEST SET - ENGINE BLEED: Open the shutoff valve. Slowly pressurize the system from 4 psig (0.28 bar rel.) with the regulator valve of the 98L36103002000 TEST SET - ENGINE BLEED.	On the 98L36103002000 TEST SET - ENGINE BLEED: The digital pressure gage shows the saturation pressure value +4 +0.05 -0. psig (+0.2758 +0.0034 -0.0034 bar rel.).
9.On the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY: Close the shutoff valve.	On the digital pressure gauge: Make sure that the indication shown does not decrease to 0 psig (0.00 bar rel.) in less than 20 seconds. If the pressure decreases to 0 psig (0.00 bar rel.) in less than 20 seconds, replace the damaged DPS sense line.
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 psig (0.00 bar rel.).

Subtask 36-11-00-080-109-A

C. Disconnection of the Test Set
(1) Slowly open the purge valve to depressurize the 98L36103002000 TEST SET - ENGINE BLEED to 0 psig (0.00 bar rel.).

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.

(2) Disconnect the 98D36109004000 ADAPTORS KIT-BLEED from the DPS sense line (1).
(3) Disconnect the 98D36109004000 ADAPTORS KIT-BLEED from the 98L36103002000 TEST SET - ENGINE BLEED.
(4) Disconnect the 98L36103002000 TEST SET - ENGINE BLEED from the AIR SOURCE 3 BAR (43.5 PSI) - REGULATED, FILTERED, DRY.

5. Close-up
Subtask 36-11-00-420-068-A

A. Connection of the DPS Sense Lines

DPS Sense Lines with the Bleed Test Set P/N 98L36103002000 and the Adaptor Kit P/N 98D36109004000

(1) Remove the blanking plug from the sense line ports (8) and (5) of the DPS.
(2) Remove the blanking plug from the DPS sense-line ends (6) and (7).
(3) Connect the DPS sense-line end (7) to the port (8) of the DPS (Ref. AMM TASK 36-11-18-400-802).
(4) Connect the DPS sense-line end (6) to the port (5) of the DPS (Ref. AMM TASK 36-11-18-400-802).
(5) Remove the blanking plug from the sense line ports (2) and (3) of the bleed-air precooler exchanger.
(6) Connect the DPS sense line (4) to the port (3) of the bleed-air precooler exchanger (downstream) (Ref. AMM TASK 36-11-49-400-834).
(7) Connect the DPS sense line (1) to the port (2) of the bleed-air precooler exchanger (upstream) (Ref. AMM TASK 36-11-49-400-833).

Subtask 36-11-00-410-213-A

B. 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) and (Ref. AMM TASK 54-53-11-400-806):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
413CT, 414BR, 413ET and 472AR.
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
423CT, 424BR, 423ET and 424CR.
(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 36-11-00-440-139-A

C. Reactivation of the Thrust Reverser System
(1) Make the thrust reverser serviceable after maintenance (Ref. AMM TASK 78-30-00-440-809).

Subtask 36-11-00-862-159-A

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

[Rev.10 from 2021] 2026.04.01 01:07:49 UTC