Installation of the Sense Line between the Bleed-Air Precooler Exchanger (Upstream) 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

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.

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

CAUTION: BE VERY CAREFUL WHEN YOU DO WORK ON OR NEAR THE AIR-CONDITIONING DUCTS. THE DUCTS ARE MADE OF THIN MATERIAL AND YOU CAN EASILY BREAK THEM.

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	1	ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE
No specific	AR	FOIL - ALUMINUM
No specific	AR	PLUG - BLANKING
No specific	AR	WARNING NOTICE(S)
No specific	AR	WATER - SOAPY SOLUTION
No specific	1	WRENCH - STANDARD
No specific	Torque wrench: range to between 0.85 and 0.73 m.daN (75.22 and 64.60 lbf.in )
No specific	Torque wrench: range to between 1.7 and 1.5 m.daN (12.54 and 11.06 lbf.ft )
98D27803000000	1	LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION
98L12003001000	AR	HARNESS,SAFETY

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.14QEB1)	Wire-Locking Dia: 0.6 mm CRES Nickel Alloy -

C. 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, 414BR
FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
423CT, 424BR

D. Referenced Information

REFERENCE	DESIGNATION
TASK 12-00-00-481-002-A	Installation of the Wingrip
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 36-12-00-860-805-A	Pressurization of the Bleed System with the APU
TASK 36-12-00-860-806-A	Pressurization of the Bleed System through the HP Ground Connector
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
Sense Line between the Bleed-Air Precooler Exchanger (Upstream) and the Bleed Differential Pressure-Transducer

3. Job Set-up
Subtask 36-11-49-861-130-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 36-11-49-941-149-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 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 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.
(6) On FLAPS panel 114VU:

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).
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) Put on and attach a 98L12003001000 HARNESS,SAFETY before you start work in the work area (Ref. AMM TASK 12-00-00-481-002).

Subtask 36-11-49-865-232-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: 4020KM1 (POWER PLANTDEMOUNTABLE, ENGINE 1)
49VU	AIR BLEED/ENG 1/CTL	2HA1	D11
122VU	AIR BLEED/ENG 1/MONG	3HA1	Z23
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENGINE 2)
49VU	AIR BLEED/ENG 2/MONG	3HA2	D12
122VU	AIR BLEED/ENG 2/CTL	2HA2	Z22

Subtask 36-11-49-010-281-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 [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
413CT 414BR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
423CT 424BR

4. Procedure
Subtask 36-11-49-420-156-A

A. Installation of the Sense Line between the Bleed Differential Pressure-Transducer (Upstream) and 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).

(3) Do an inspection of the component interfaces and the adjacent area.
(4) Clean the component interfaces and the adjacent area.
(5) Remove the PLUG-BLANKING from each disconnected line end.
(6) Remove the PLUG - BLANKING from the port of the bleed differential pressure-transducer (11) and the bleed-air precooler exchanger (3).
(7) Carefully engage the sense line (1) in the hole of the support (9).
(8) Install the gimbal grommets (10) and (8) to the sense line (1). Do not tighten the gimbal grommets (10) and (8) at this time.
(9) Put the sense line (1) in the correct position between the port of the bleed differential pressure-transducer (11) and the bleed-air precooler exchanger (3).
(10) Connect the union nut (2) of the sense line (1) to the port of the bleed-air precooler exchanger (3). Do not torque the union nut (2) at this time.
(11) Connect the union nut (12) of the sense line (1) to the port of the bleed differential pressure-transducer (11). Do not torque the union nut (12) at this time.
(12) Install the clamps (7) with the sense line (1) to the supports (4).
(13) Install the washers (5) and bolts (6).
(a) Tighten the bolts (6).
(14) Torque the union nut (2):

WARNING: TIGHTEN THE UNION(S) TO THE CORRECT TORQUE VALUE. IF YOU DO NOT TIGHTEN THEM SUFFICIENTLY, HOT AIR LEAKAGE CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.

(a) TORQUE the union nut (2) of the sense line (1) to between 1.7 and 1.5 m.daN (12.54 and 11.06 lbf.ft )

.
(b) Identify the torqued union nut (2) of the sense line (1) with a red line (Ref. AMM TASK 20-23-22-910-001).
(15) Torque the union nut (12):

WARNING: TIGHTEN THE UNION(S) TO THE CORRECT TORQUE VALUE. IF YOU DO NOT TIGHTEN THEM SUFFICIENTLY, HOT AIR LEAKAGE CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.

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

(a) Use a second WRENCH - STANDARD to hold the bleed differential pressure-transducer (11) and TORQUE the union nut (12) of the sense line (1) to between 0.85 and 0.73 m.daN (75.22 and 64.60 lbf.in )

.
(b) Identify the torqued union nut (12) of the sense line (1) with a red line (Ref. AMM TASK 20-23-22-910-001).
(16) Tighten the gimbal grommets (10) and (8).

Subtask 36-11-49-865-233-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: 4020KM1 (POWER PLANTDEMOUNTABLE, ENGINE 1)
49VU	AIR BLEED/ENG 1/CTL	2HA1	D11
122VU	AIR BLEED/ENG 1/MONG	3HA1	Z23
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENGINE 2)
49VU	AIR BLEED/ENG 2/MONG	3HA2	D12
122VU	AIR BLEED/ENG 2/CTL	2HA2	Z22

Subtask 36-11-49-480-093-A

C. Prepare for the Leak Test on the Connections of the Sense Line
(1) There are two procedures to do a leak check at the connections of the bleed air ducts (duct joint, flexible connections).
(a) Soap solution procedure

Leaks are permitted if the WATER - SOAPY SOLUTION stays on the joint line with a continuous series of bubbles.
Leaks are not permitted if the air pressure (from the air source) blows the soap solution off the joint line and prevents a continuous series of bubbles.

(b) Aluminum foil procedure

NOTE: This procedure is recommended when you do a leak check with hot air.

1 Wind the FOIL - ALUMINUM on the joint on time.
2 Twist tight the seam of the foil wrap.

WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.

3 Make the foil wrap as tight as possible on the tube but do not rip the wrap.
4 Attach the foil wrap at the two sides of the pneumatic joint with 14QEB1Wire-Locking Dia: 0.6 mm CRES Nickel Alloy -.

Subtask 36-11-49-790-064-A

D. Leak Test
(1) Pressurize the bleed system through the HP ground connector (Ref. AMM TASK 36-12-00-860-806) or with the APU (Ref. AMM TASK 36-12-00-860-805).
(a) Make sure that there are no leaks at the sense line (1) connections.

NOTE: There is a leak when the foil installed on the pneumatic connection breaks or when it is too hot.

(2) Remove the materials that you used to do the leak test on the sense line (1) connections.

5. Close-up
Subtask 36-11-49-410-214-A

A. Close Access
(1) Put the aircraft back to its initial configuration.
(2) Make sure that the work area is clean and clear of tools and other items.
(3) Install these access panels (Ref. AMM TASK 54-52-11-400-807):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
413CT 414BR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
423CT 424BR
(4) Remove all the fixtures, tools, test and support equipment used during this procedure.
(5) Remove the access platform(s).
(6) Remove the WARNING NOTICE(S).

Subtask 36-11-49-862-121-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 01:11:52 UTC