Decontamination of the Bleed-Air Ducting System disconnected at the Pressure Regulating Valve (PRV) (4000HA1) with ENGINE 2 Bleed Pressure

TASK 36-11-00-615-806-A-01
Decontamination of the Bleed-Air Ducting System disconnected at the Pressure Regulating Valve (PRV) (4000HA1) with ENGINE 2 Bleed Pressure

WARNING: MAKE SURE THAT WHEN THE ENGINES OPERATE ON THE GROUND:

NO PERSONS GO WHERE THE AIRCRAFT CAN CAUSE THEM INJURY OR CAN KILL THEM
NO OBJECTS STAY WHERE THE ENGINES CAN BLOW THEM AWAY OR WHERE THEY CAN BE PULLED INTO THE ENGINES BY SUCTION.

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: BE CAREFUL WHEN THE DUCTS ARE DISCONNECTED THE TEMPERATURE OF THE EXHAUST GASES FROM THE OPEN ENDS OF THE DISCONNECTED DUCTS CAN BE AS HIGH AS 270 DEG.C (518 DEG.F). THE HOT GASES CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

ZONE: 410

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	BLANKET - HEAT ISOLATION
No specific	AR	CAP - BLANKING
No specific	AR	COVER - PROTECTION
No specific	AR	PLUG - BLANKING
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	AR	WARNING NOTICE(S)
98F10103500000	1	CHOCK-MLG,ENGINE RUN-UP

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
410	ENG 1 PYLON BOX AND FORWARD FAIRING
192KB

C. Referenced Information

REFERENCE	DESIGNATION
TASK 05-24-50-210-801-A	General Visual Inspection of Core Compartment (EWIS)
TASK 21-51-00-710-002-A	Operational Test of the Flow Control and Indicating System
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 26-12-17-000-803-A	Removal of the Aft Fire/Overheat Detector
TASK 26-12-17-400-803-A	Installation of the Aft Fire/Overheat Detector
TASK 26-12-61-000-802-A	Removal of the Loop-A Fire Electrical Harness and the Loop-A Fire Detector Cables
TASK 26-12-61-400-802-A	Installation of the Loop-A Fire Electrical Harness and the Loop-A Fire Detector Cables
TASK 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
TASK 36-11-00-710-802-A	Operational Test of the Bleed Air System
TASK 36-11-49-000-822-A	Removal of the Environmental Control System (ECS) Ducts
TASK 36-11-49-000-823-A	Removal of the Environmental Control System (ECS) Sense Lines
TASK 36-11-49-400-822-A	Installation of the Environmental Control System (ECS) Ducts
TASK 36-11-49-400-823-A	Installation of the Environmental Control System (ECS) Sense Lines
TASK 36-11-49-400-824-A	Installation of the Environmental Control System (ECS) Interface Duct
TASK 36-11-52-000-802-A	Removal of the Bleed Pressure-Regulator Valve
TASK 36-11-52-400-802-A	Installation of the Bleed Pressure-Regulator Valve
TASK 36-11-53-000-802-A	Removal of the Overpressure Valve
TASK 36-11-53-400-802-A	Installation of the Overpressure Valve
TASK 36-22-00-790-802-A	Leak Check on all the Bleed Air Ducts and the Packs Components
TASK 53-35-13-000-002-A	Removal of the Quick-Release Access Panels from the Belly Fairing Structure
TASK 53-35-13-400-002-A	Installation of the Quick-Release Access Panels on the Belly Fairing Structure
TASK 71-00-00-860-814-A	Shutdown of the Engine
TASK 71-00-00-860-823-A	Start the Engine (Normal Automatic Start)
TASK 71-00-00-910-804-A	General Warnings and Cautions and Related Safety Data
TASK 75-24-49-000-803-A	Removal of the Component Cooling Lines
TASK 75-24-49-400-803-A	Installation of the Component Cooling Lines
TASK 78-32-00-210-821-A	General Visual Inspection (GVI) of the Thrust Reverser Thermal Insulation Blankets
Flow Control Valve - Electrical Connectors
BLEED Page
Bleed-Air Ducting System - Location and Detail
Pressure Regulating Valve

3. Job Set-up
Subtask 36-11-00-941-197-A ** ON A/C NOT FOR ALL

A. Safety Precautions
(1) Put the aircraft in the engine run up condition.
(2) Obey the safety precautions during engine ground operations (Ref. AMM TASK 71-00-00-910-804).

Subtask 36-11-00-865-219-A ** ON A/C NOT FOR ALL

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
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

Subtask 36-11-00-865-240-A ** ON A/C NOT FOR ALL

C. Open, safety and tag this(these) circuit breaker(s):

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
122VU	AIR COND/TEMP CTL SYS 2/CHAN A/115VAC	53HH	W22
122VU	AIR COND/TEMP CTL SYS 2/CHAN A/28VDC	55HH	W21
122VU	AIR COND/TEMP CTL SYS 2/CHAN B/28VDC	56HH	Y21
122VU	AIR COND/TEMP CTL SYS 2/CHAN B/115VAC	54HH	Y20

Subtask 36-11-00-860-251-A ** ON A/C NOT FOR ALL

D. Aircraft Maintenance Configuration
(1) Energize the aircraft electrical circuits from the external power (Ref. AMM TASK 24-41-00-861-002).
(2) Do the EIS start procedure (Ref. AMM TASK 31-60-00-860-001).
(3) In the cockpit, on AIR COND panel 30VU:
(a) Make sure that the ENG 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) Make sure that the PACK 1 and 2 pushbutton switches are released (the OFF legends are on).
(d) Make sure that the PACK FLOW selector-switch is set to LO.
(e) Put the WARNING NOTICE(S) in position to tell persons not to pressurize the pneumatic system on the bleed push-button switches.
(4) On the HP ground connector (7300HM):
(a) Put the WARNING NOTICE(S) in position to tell persons not to pressurize the pneumatic system.
(5) Use a 98F10103500000 CHOCK-MLG,ENGINE RUN-UP if the power run above the idle speed is necessary after the engine starts.

Subtask 36-11-00-480-155-A ** ON A/C NOT FOR ALL

E. Preparation for Cleaning of the Bleed-Air Ducting System
(1) As the bleed source is engine 2, secure the PACK 2 as follows:
(a) Remove access panel 192KB (Ref. AMM TASK 53-35-13-000-002).

CAUTION: MAKE SURE THAT THE ELECTRICAL CONNECTORS ARE CLEAN BEFORE YOU DISCONNECT OR CONNECT THEM. CONTAMINATION ON THE ELECTRICAL CONNECTORS CAN CAUSE DAMAGE TO EQUIPMENT.

(b)

Flow Control Valve - Electrical Connectors ** ON A/C NOT FOR ALL

WARNING: MAKE SURE THAT WHEN THE ENGINES OPERATE ON THE GROUND:

NO PERSONS GO WHERE THE AIRCRAFT CAN CAUSE THEM INJURY OR CAN KILL THEM
NO OBJECTS STAY WHERE THE ENGINES CAN BLOW THEM AWAY OR WHERE THEY CAN BE PULLED INTO THE ENGINES BY SUCTION.

(2) Start engine 2 and keep the engine RPM to idle (Ref. AMM TASK 71-00-00-860-823).
(a) In the cockpit, on AIR COND panel 30VU:
1 Make sure that the ENG 2 BLEED pushbutton-switch is released (the OFF legend is on).
2 Make sure that the APU BLEED pushbutton-switch is released (the ON legend is off).
3 Set the X BLEED selector-switch to the CLOSED position:
a Put the WARNING NOTICE(S) in position to tell persons not to operate the X BLEED selector-switch.

(3) Remove the PRV (4000HA1) as follows:
(a) On the ECAM control panel, push the BLEED key:
1 On the SD, the BLEED page comes into view.
2 On the BLEED page, do a check of:

The pressure value in the duct that reads the bleed pressure sensor
The temperature value in the duct that reads the bleed temperature sensor.

(b) When the pressure and temperature values in the duct are almost the same as external pressure and temperature:
1 Remove the overpressure valve (Ref. AMM TASK 36-11-53-000-802):
a Put a COVER - PROTECTION on the open end of the overpressure valve.
2 Remove the ECS starter duct (Ref. AMM TASK 36-11-49-000-822):
a Put a PLUG - BLANKING on the open ends of the ECS starter duct.
3 Make sure that the link assemblies of the ECS interface duct are installed correctly (Ref. AMM TASK 36-11-49-400-824):
a Make sure that the link assemblies are not preloaded and do not move because of the engine vibration.
4 Remove the Active Clearance Control (ACC) hose (Ref. AMM TASK 75-24-49-000-803):
a Put the PLUG - BLANKING on the open ends of the ACC hose.
5 Remove the ECS sense lines connected to the pylon (Ref. AMM TASK 36-11-49-000-823):
a Put the PLUG - BLANKING on the open ends of the ECS sense lines.
6 Remove the aft fire/overheat detector (Ref. AMM TASK 26-12-17-000-803).
7 Remove the loop-A fire harness and electrical rail assembly (Ref. AMM TASK 26-12-61-000-802).
8 Remove the PRV (4000HA1) (Ref. AMM TASK 36-11-52-000-802):
a Put the COVER - PROTECTION on the open end of the PRV (4000HA1).
(4) If installed, remove the PLUG - BLANKING from the open end of the ECS interface duct.
(5) Put a BLANKET - HEAT ISOLATION on the adjacent electrical cables and components.

4. Procedure
Subtask 36-11-00-615-063-A ** ON A/C NOT FOR ALL

A. Cleaning of the Odor Smell in the Bleed-Air Ducting System
(1) In the cockpit, on AIR COND panel 30VU:
(a) Set the PACK 2 pushbutton-switch to the pushed position (the OFF legend is off).
(b) Set the ENG 2 BLEED pushbutton-switch to the pushed position (the OFF legend is off).
(c) Set the X BLEED selector-switch to the OPEN position.
(2) On the ECAM control panel, push the BLEED key:
(a) On the SD, the BLEED page comes into view.
(b) The BLEED page shows that the X BLEED valve is OPEN.
(3) On the ECAM display, make sure that the engine bleed temperature is 200 -10 DEG.C or +10 DEG.C (392 -18 DEG.F or +18 DEG.F).
(a) If necessary, slowly push the ENGINE-2 thrust lever to make the engine bleed temperature to 200 -10 DEG.C or +10 DEG.C (392 -18 DEG.F or +18 DEG.F). Not reach more than 40% of N1.
(4) Wait for a minimum of 15 minutes.
(5) The ECAM control panel can show unusual BLEED and pack fault messages.

NOTE: The system operates correctly and it is not necessary to do the related troubleshooting procedure at this step.

(6) Slowly pull ENGINE-2 thrust lever to the idle position.
(7) In the cockpit, on AIR COND panel 30VU:
(a) Set the PACK 2 pushbutton-switch to the released position (the OFF legend is on).
(b) Set the ENG 2 BLEED pushbutton-switch to the released position (the OFF legend is on).
(c) Set the X BLEED selector-switch to the AUTO position.
(8) Stop engine 2 (Ref. AMM TASK 71-00-00-860-814).

5. Close-up
Subtask 36-11-00-210-064-A ** ON A/C NOT FOR ALL

A. General Visual Inspection (GVI)
(1) Do a GVI of the core compartment (Ref. AMM TASK 05-24-50-210-801):
(a) Specially, examine the area/components near the exhaust plumes of the ECS interface duct.

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

(b) If you see contamination, use the manufacturer's instructions to clean them.
(2) Do a GVI of the thrust reverser thermal-blanket (Ref. AMM TASK 78-32-00-210-821):
(a) Specially, examine the thermal blankets near the exhaust plumes of the ECS interface ducts.

Subtask 36-11-00-080-132-A ** ON A/C NOT FOR ALL

B. Put the aircraft back to its initial configuration.
(1) Connect the electrical connectors to the FCV as follows:
(a) Remove the CAP-BLANKING from each electrical connector and receptacle.

CAUTION: MAKE SURE THAT THE ELECTRICAL CONNECTORS ARE CLEAN BEFORE YOU DISCONNECT OR CONNECT THEM. CONTAMINATION ON THE ELECTRICAL CONNECTORS CAN CAUSE DAMAGE TO EQUIPMENT.

(b)

Flow Control Valve - Electrical Connectors ** ON A/C NOT FOR ALL

Subtask 36-11-00-420-081-A ** ON A/C NOT FOR ALL

C. Connection of the ECS Interface Duct
(1) Remove the BLANKET - HEAT ISOLATION from the adjacent electrical cables and components.
(2) Install the PRV:
(a) Remove the COVER - PROTECTION from the open end of the PRV (4000HA1).
(b) Install the PRV (4000HA1) (Ref. AMM TASK 36-11-52-400-802).
(3) Install the loop-A fire harness and electrical rail assembly (Ref. AMM TASK 26-12-61-400-802).
(4) Install the aft fire/overheat detector (Ref. AMM TASK 26-12-17-400-803).
(5) Install the ECS sense lines:
(a) Remove the PLUG - BLANKING from the open ends of the ECS sense lines.
(b) Install the ECS sense lines connected to the pylon (Ref. AMM TASK 36-11-49-400-823).
(6) Install the ACC hose:
(a) Remove the PLUG - BLANKING from the open ends of the ACC hose.
(b) Install the ACC hose (Ref. AMM TASK 75-24-49-400-803).
(7) Install the ECS Starter duct:
(a) Remove the PLUG - BLANKING from the open ends of the ECS starter duct.
(b) Install the ECS starter duct (Ref. AMM TASK 36-11-49-400-822).
(8) Install the overpressure valve:
(a) Remove the COVER - PROTECTION from the open end of the overpressure valve.
(b) Install the overpressure valve (Ref. AMM TASK 36-11-53-400-802).
(9) Make sure that the work area is clean and clear of tools and other items.

Subtask 36-11-00-865-241-A ** ON A/C NOT FOR ALL

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
122VU	AIR COND/TEMP CTL SYS 2/CHAN A/115VAC	53HH	W22
122VU	AIR COND/TEMP CTL SYS 2/CHAN A/28VDC	55HH	W21
122VU	AIR COND/TEMP CTL SYS 2/CHAN B/28VDC	56HH	Y21
122VU	AIR COND/TEMP CTL SYS 2/CHAN B/115VAC	54HH	Y20

Subtask 36-11-00-790-081-A ** ON A/C NOT FOR ALL

E. Leak Test
(1) Do a leak test of the bleed-air ducting system (Ref. AMM TASK 36-22-00-790-802).

Subtask 36-11-00-710-076-A ** ON A/C NOT FOR ALL

F. Operational Test
(1) Do an operational test of the bleed-air ducting system (Ref. AMM TASK 36-11-00-710-802).
(2) Do an operational test of the flow control and indicating system (Ref. AMM TASK 21-51-00-710-002).

Subtask 36-11-00-860-252-A ** ON A/C NOT FOR ALL

G. Aircraft Maintenance Configuration
(1) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).
(2) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
(3) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
(4) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 01:06:09 UTC