Decontamination of the Bleed-Air Ducting System Disconnected at APU Load-Compressor Valve with Engine 2 Bleed Pressure

TASK 36-12-00-615-801-A-01
Decontamination of the Bleed-Air Ducting System Disconnected at APU Load-Compressor Valve 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: 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.

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: DO NOT TOUCH THE APU UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS WHEN YOU DO THE MAINTENANCE TASK(S).

ZONE: 197
ZONE: 211

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	CAP - BLANKING
No specific	1	GROUND AIR-SUPPLY UNIT(HIGH PRESSURE)
No specific	AR	PLUG - BLANKING
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	AR	WARNING NOTICE(S)
98D36109005001	1	DUMMY CHECK VLV - APU
98D36109006000	1	BLEED EXHAUST - APU
98F10103500000	AR	CHOCK-MLG,ENGINE RUN-UP

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
197	REAR FAIRING
211	COCKPIT
192KB, 197KB

C. Referenced Information

REFERENCE	DESIGNATION
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 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
TASK 36-12-41-000-001-A	Removal of a Bleed-Air Duct
TASK 36-12-41-400-001-A	Installation of a Bleed-Air Duct
TASK 36-12-51-000-001-A	Removal of the APU Bleed Check-Valve
TASK 36-12-51-400-001-A	Installation of the APU Bleed Check-Valve
TASK 36-22-00-790-803-A	Leak Check on all the Bleed Air Ducts and the Pack Components
TASK 52-41-00-010-001-A	Open the APU Doors for Access
TASK 52-41-00-410-001-A	Close the APU Doors after Access
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 71-00-00-860-827-A	Start the Engine (Normal Automatic Start)
TASK 71-00-00-860-829-A	Engine Shutdown
TASK 71-00-00-869-803-A	Safety Precautions During Engine Ground Operations
Tool Installation
Flow Control Valve - Electrical Connector
APU bleed exhaust - Installation
Dummy Check Valve - Installation
Bleed-Air Ducting System - Location and Detail
BLEED Page

3. Job Set-up
Subtask 36-12-00-941-061-A

A. Safety Precautions
(1) Obey the safety precautions during engine ground operations (Ref. AMM TASK 71-00-00-869-803).
(2)

Tool Installation

Subtask 36-12-00-865-133-A

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C 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
122VU	AIR BLEED/X FEED VALVE/NORM	1HV	Z20

Subtask 36-12-00-865-130-A

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
121VU	APU/APU/CTL	2KD	L42
121VU	APU/ECB/SPLY	1KD	L41
121VU	APU/FIRE/EXTIG/SQUIB/B	2WF	L39
121VU	APU/FIRE/EXTIG/SQUIB/A	1WF	L38
121VU	APU/FIRE/LP VALVE/NORM	4WF	M42
121VU	APU/FIRE/LP VALVE/STBY	3WF	M41
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 36-12-00-860-111-A

D. Aircraft Maintenance Configuration
(1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(2) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only)
(Ref. AMM TASK 31-60-00-860-001).
(3) In the cockpit, on AIR COND panel 30VU:
(a) Make sure that the ENG 1 and ENG 2 BLEED pushbutton switches are released (the OFF legends are 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 position.
(e) Set the X BLEED selector switch to the SHUT position.
(f) Put the WARNING NOTICE(S) in position to tell persons not to pressurize the pneumatic system on the bleed pushbutton switches.
(4) In the cockpit, on OVERHEAD CTL & IND panel 25VU:
(a) Put the WARNING NOTICE(S) in position to tell persons not to start the APU.

Subtask 36-12-00-480-054-B

E. Preparation for Cleaning of the Bleed-Air Ducting System
(1) As the bleed source is engine 2, secure 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 Connector

(c) Put the CAP-BLANKING on each disconnected electrical connector and receptacle.
(2) Install the 98D36109006000 BLEED EXHAUST - APU as follows:
(a) Open the APU doors for access (Ref. AMM TASK 52-41-00-010-001).
(b) Disconnect the bleed-air ducting system from the APU load-compressor valve (Ref. AMM TASK 36-12-41-000-001).
(c)

APU bleed exhaust - Installation

NOTE: You can change the bleed duct orientation to install the tool easily.

(d) Install the PLUG - BLANKING to the open end of the APU load-compressor valve.
(e) Make sure that the bleed air is pointed away from the aircraft.
(3) Install the 98D36109005001 DUMMY CHECK VLV - APU as follows:
(a) Remove access panel 197KB (Ref. AMM TASK 53-35-13-000-002).
(b) Remove the APU bleed check-valve (Ref. AMM TASK 36-12-51-000-001).
(c)

Dummy Check Valve - Installation

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.

(4) Start engine 2 with the GROUND AIR-SUPPLY UNIT(HIGH PRESSURE) and keep the engine RPM to idle (Ref. AMM TASK 71-00-00-860-827):
(a) In the cockpit, on the 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 X BLEED selector switch is in the SHUT position:
a Put the WARNING NOTICE(S) in position to tell persons not to operate the X BLEED selector switch.
(5) On the BLEED page, make sure that Pressure Regulating Valve 2 (PRV 2) (4000HA2) and the APU bleed valve are closed.
(6) Disconnect the GROUND AIR-SUPPLY UNIT(HIGH PRESSURE).

NOTE: Airbus recommends you to use the external fire-extinguishing agents in case of fire in the engine tailpipe during the engine shutdown procedure (as the monitoring function is not available).

(7) Get access to the 98D36109005001 DUMMY CHECK VLV - APU and set it to OPEN position.

4. Procedure
Subtask 36-12-00-615-053-A

A. Cleaning of the Odor Smell in the Bleed-Air Ducting System

(1) In the cockpit, on AIR COND panel 30VU:
(a) Set the ENG 2 BLEED pushbutton switch to the pushed position (the OFF legend is off).
(b) Set the PACK 2 pushbutton switch to the pushed position (the OFF legend is off).
(c) Remove the WARNING NOTICE(S) and 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 engine 2 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 the ENGINE-2 thrust lever to the idle position.
(7) In the cockpit, on AIR COND panel 30VU:
(a) Set the ENG 2 BLEED pushbutton switch to the released position (the OFF legend is on).
(b) Set the PACK 2 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 71-00-00-860-829).

5. Close-up
Subtask 36-12-00-080-054-B

A. Put the aircraft back to its initial configuration.

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

(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the 98D36109005001 DUMMY CHECK VLV - APU as follows:

NOTE: After this procedure, the 98D36109005001 DUMMY CHECK VLV - APU will be hot to touch.

(a) Get access to the APU bleed check-valve position.
(b)

Dummy Check Valve - Installation

(c) Install the APU bleed check-valve (Ref. AMM TASK 36-12-51-400-001).
(3) Install access panel 197KB (Ref. AMM TASK 53-35-13-400-002).
(4) Remove the 98D36109006000 BLEED EXHAUST - APU as follows:

NOTE: After this procedure, the 98D36109006000 BLEED EXHAUST - APU will be hot to touch.

(a)

APU bleed exhaust - Installation

(b) Remove the PLUG - BLANKING from the open end of the APU load-compressor valve.
(c) Connect the bleed-air ducting system to the APU load-compressor valve (Ref. AMM TASK 36-12-41-400-001).
(d) Close the APU doors after access (Ref. AMM TASK 52-41-00-410-001).
(5) Connect the electrical connector 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 Connector

Subtask 36-12-00-865-131-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
121VU	APU/APU/CTL	2KD	L42
121VU	APU/ECB/SPLY	1KD	L41
121VU	APU/FIRE/EXTIG/SQUIB/B	2WF	L39
121VU	APU/FIRE/EXTIG/SQUIB/A	1WF	L38
121VU	APU/FIRE/LP VALVE/NORM	4WF	M42
121VU	APU/FIRE/LP VALVE/STBY	3WF	M41
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 36-12-00-710-069-A

C. Operational Test
(1) Do an operational test of the flow control and indicating system (Ref. AMM TASK 21-51-00-710-002).

Subtask 36-12-00-790-066-A

D. Leak Test
(1) Do a leak test of the bleed-air ducting system (Ref. AMM TASK 36-22-00-790-803):
(a) Make sure that there are no leaks.

Subtask 36-12-00-860-112-A

E. Aircraft Maintenance Configuration
(1) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(2) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).
(3) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
(4) De-energize the aircraft electrical circuits supplied from the external power (Ref. AMM TASK 24-41-00-862-002).
(5) Remove the WARNING NOTICE(S).
(6)

Tool Installation

[Rev.10 from 2021] 2026.04.01 01:14:49 UTC