Amm Task Aug 19.pdf

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-23-00-040-001-A - Deactivation of the Lavatory/Galley Extraction Fan

** ON A/C ALL TASK 21-23-00-040-001-A Deactivation of the Lavatory/Galley Extraction Fan

FIN : 1HU Task Summary MMEL or CDL Ref MMEL 21-23-01A

Access NO

Test NO

1.

Reason for the Job MMEL 21-23-01A Lavatory and Galley Extraction Fan (FAA only)

2

Job Set-up Information A.

E/T 00.3

Nb Men 1

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

3.

Mhr 00.3

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Specific Tools NO

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up Subtask 21-23-00-861-053-A A.

4.

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

Procedure Subtask 21-23-00-865-052-A A.

Open, safety and tag this(these) circuit breaker(s): PANEL 122VU 122VU

DESIGNATION FIN AIR COND/LAV/GALLEY VENT CTL/EX- 5HU TRACT FAN/CTL AIR COND/LAV/GALLEY VENT CTL/EX- 6HU TRACT FAN/SPLY

LOCATION U21 U19

Subtask 21-23-00-040-050-B Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-23-00-040-001-A - Deactivation of the Lavatory/Galley Extraction Fan

B.

Deactivation of the Lavatory/Galley Extraction Fan (1) Make sure that: · on the lower ECAM display unit COND page the cabin duct temperatures are shown.

Subtask 21-23-00-862-055-A C.

Placard (1) Put a placard in the cockpit to tell persons that the lavatory/galley extraction fan is deactivated. (2) Make an entry in the logbook.

Subtask 21-23-00-869-050-A D.

Cockpit Effects (1) The message LAV DET may be erroneously displayed on the SD INOP SYS status page.

5.

Close-up Subtask 21-23-00-862-053-A A.

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

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-006-A - Blower Fan Inoperative Check that the Air Conditioned Inlet Valve is Open

** ON A/C ALL TASK 21-26-00-040-006-A Blower Fan Inoperative - Check that the Air Conditioned Inlet Valve is Open Task Summary MMEL or CDL Ref MMEL 21-26-01B 1.

Reason for the Job MMEL 21-26-01B Avionics Blower Fan

2

Job Set-up Information A.

Access YES

Specific Tools NO

Mhr 00.5

E/T 00.5

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Test YES

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 824

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 52-41-00-010-002-A). Open the Avionics Compartment Doors for Access (Ref. 52-41-00-410-002-A). Close the Avionics Compartment Doors after Access Conditioned-air inlet valve SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-006-A - Blower Fan Inoperative Check that the Air Conditioned Inlet Valve is Open

A

824

C

Z127

A

C

FR24A FR20

B 21HQ

B MANUAL OVERRIDE (SHOWN IN OPEN POSITION) C = CLOSED O = OPEN C

O

CONNECTOR N_MM_212600_4_AEN0_01_00

Figure 21-26-00-991-00900-00-B / SHEET 1/1 - Conditioned-air inlet valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-006-A - Blower Fan Inoperative Check that the Air Conditioned Inlet Valve is Open

3.

Job Set-up Subtask 21-26-00-861-074-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

Subtask 21-26-00-010-064-A B.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 824. (2) Open the access door 824 (Ref. AMM TASK 52-41-00-010-002) .

4.

Procedure Subtask 21-26-00-040-055-A A.

Conditioned Air Inlet Valve (Ref. Fig. Conditioned-air inlet valve SHEET 1) (1) On the VENTILATION part of the overhead control and indicating panel 22VU: · release the BLOWER pushbutton switch (the OVRD legend comes on). (2) In the avionics compartment: · make sure that the conditioned-air inlet valve 21HQ is open (the position indicator of the valve is at 0).

5.

Close-up Subtask 21-26-00-410-065-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access door 824 (Ref. AMM TASK 52-41-00-410-002) . (3) Remove the access platform(s).

Subtask 21-26-00-941-092-A B.

Aircraft Maintenance Configuration (1) Put a WARNING NOTICE(S) in the cockpit to tell the crew that the Blower Fan is deactivated. (2) Make an entry in the logbook.

Subtask 21-26-00-862-082-A C.

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

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-010-A - Blower Fault Warning - Check of the Blower Fan and AVNCS SYS FAULT Warning

** ON A/C ALL TASK 21-26-00-040-010-A Blower Fault Warning - Check of the Blower Fan and AVNCS SYS FAULT Warning Task Summary MMEL or CDL Ref MMEL 21-09-01A

Access YES

1.

Reason for the Job MMEL 21-09-01A VENT BLOWER FAULT Alert

2

Job Set-up Information A.

Specific Tools NO

Mhr 00.5

E/T 00.5

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Test YES

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 824

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 21-26-00-710-001-A). (Ref. 21-26-00-710-001-A-01). (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A). (Ref. 52-41-00-010-002-A). (Ref. 52-41-00-410-002-A). 3.

DESIGNATION Operational Check of the Avionics Equipment Ventilation-System via MCDU Operational Check of the Avionics Equipment Ventilation (without the CFDS) Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power Open the Avionics Compartment Doors for Access Close the Avionics Compartment Doors after Access

Job Set-up Subtask 21-26-00-861-076-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Subtask 21-26-00-010-072-A B.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 824.

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-010-A - Blower Fault Warning - Check of the Blower Fan and AVNCS SYS FAULT Warning

(2) Open the access door 824 (Ref. AMM TASK 52-41-00-010-002) . 4.

Procedure Subtask 21-26-00-869-102-A A.

In the avionics compartment, make sure that the blower fan 20HQ operates correctly: (1) Do this test: ACTION On the circuit breaker panel 122VU: · Open the circuit breaker 3HQ · Close the circuit breaker 3HQ

RESULT On the upper ECAM display unit: · After approximately 10 seconds, the AVNCS SYS FAULT warning comes into view. · The AVNCS SYS FAULT warning goes out of view. The self-test of the blower fan starts and continues for approximately 60 seconds. You can hear the blower fan operate.

Subtask 21-26-00-710-062-A B. 5.

Do an operational test of the avionics equipment ventilation (Ref. AMM TASK 21-26-00-710-001) .

Close-up Subtask 21-26-00-410-073-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access door 824 (Ref. AMM TASK 52-41-00-410-002) . (3) Remove the access platform(s).

Subtask 21-26-00-941-096-A B.

Aircraft Maintenance Configuration (1) Put a WARNING NOTICE(S) in the cockpit to tell the crew that the BLOWER FAULT warning is not serviceable. (2) Make an entry in the logbook.

Subtask 21-26-00-862-076-A C.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-011-A - Extract Fault Warning - Check of the Extract Fan and AVNCS SYS FAULT Warning

** ON A/C ALL TASK 21-26-00-040-011-A Extract Fault Warning - Check of the Extract Fan and AVNCS SYS FAULT Warning Task Summary MMEL or CDL Ref MMEL 21-09-02A

Access YES

1.

Reason for the Job MMEL 21-09-02A VENT EXTRACT FAULT Alert

2

Job Set-up Information A.

Specific Tools NO

Mhr 00.5

E/T 00.5

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Test YES

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 824

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 21-26-00-710-001-A). (Ref. 21-26-00-710-001-A-01). (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A). (Ref. 52-41-00-010-002-A). (Ref. 52-41-00-410-002-A). 3.

DESIGNATION Operational Check of the Avionics Equipment Ventilation-System via MCDU Operational Check of the Avionics Equipment Ventilation (without the CFDS) Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power Open the Avionics Compartment Doors for Access Close the Avionics Compartment Doors after Access

Job Set-up Subtask 21-26-00-861-077-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Subtask 21-26-00-010-073-A B.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 824.

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-011-A - Extract Fault Warning - Check of the Extract Fan and AVNCS SYS FAULT Warning

(2) Open the access door 824 (Ref. AMM TASK 52-41-00-010-002) . 4.

Procedure Subtask 21-26-00-869-104-A A.

In the avionics compartment, make sure that the extract fan 18HQ operates correctly: (1) Do this test: ACTION On the circuit breaker panel 122VU: · Open the circuit breaker 3HQ · Close the circuit breaker 3HQ

RESULT On the upper ECAM display unit: · After approximately 10 seconds, the AVNCS SYS FAULT warning comes into view. · The AVNCS SYS FAULT warning goes out of view. The self-test of the extract fan starts and continues for approximately 60 seconds. You can hear the extract fan operate.

Subtask 21-26-00-710-063-A B. 5.

Do an operational test of the avionics equipment ventilation (Ref. AMM TASK 21-26-00-710-001) .

Close-up Subtask 21-26-00-410-074-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access door 824 (Ref. AMM TASK 52-41-00-410-002) . (3) Remove the access platform(s).

Subtask 21-26-00-941-098-A B.

Aircraft Maintenance Configuration (1) Put a WARNING NOTICE(S) in the cockpit to tell the crew that the EXTRACT FAULT warning is not serviceable. (2) Make an entry in the logbook.

Subtask 21-26-00-862-077-A C.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-004-A - Verification Test of the Safety Valves (Position Indication on ECAM CAB PRESS Page)

** ON A/C ALL TASK 21-31-00-040-004-A Verification Test of the Safety Valves (Position Indication on ECAM CAB PRESS Page)

FIN : 6HL , 7HL Task Summary MMEL or CDL Ref MMEL 21-07-02-02A

Access NO

Test NO

Specific Tools NO

1.

Reason for the Job MMEL 21-07-02-02A Pressure Safety Valves Position Indication on the CAB PRESS

2

Job Set-up Information A.

Mhr 00.3

E/T 00.3

Nb Men 1

Referenced Information REFERENCE DESIGNATION Safety Valves (6HL,7HL) - Visual Inspection SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-004-A - Verification Test of the Safety Valves (Position Indication on ECAM CAB PRESS Page)

Z260

A

1

B

FR70

PAX DOOR 2

A

FR65

TYPICAL

5

D C REAR PRESSURE BULKHEAD

A

3

B FR70

4

TYPICAL 2

6HL 7HL

C D

2 4

A

C D TYPICAL

FWD

A A TYPICAL

N_MM_213100_4_AAMB_01_00

Figure 21-31-00-991-00500-00-A / SHEET 1/1 - Safety Valves (6HL,7HL) - Visual Inspection ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-004-A - Verification Test of the Safety Valves (Position Indication on ECAM CAB PRESS Page)

3.

Job Set-up Subtask 21-31-00-010-060-A A.

Get Access (1) Remove the food trolleys (1) from the Aft galley. (2) Remove the access panel (5).

4.

Procedure (Ref. Fig. Safety Valves (6HL,7HL) - Visual Inspection SHEET 1) Subtask 21-31-00-280-052-A A.

Visual Inspection of the Safety Valves (6HL,7HL). (1) Do a visual inspection of the two safety valves (2). NOTE: The safety valves (2) must be in the closed position. The ring gate (3) must seat properly on the rubber seal (4).

5.

Close-up Subtask 21-31-00-410-058-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the access panel (5) and the food trolleys (1) in the Aft galley.

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-005-A - Verification Test of the Safety Valves (OPEN Caution on ECAM)

** ON A/C ALL TASK 21-31-00-040-005-A Verification Test of the Safety Valves (OPEN Caution on ECAM)

FIN : 6HL , 7HL Task Summary MMEL or CDL Ref MMEL 21-09-03A

Access NO

1.

Reason for the Job MMEL 21-09-03A CAB PR SAFETY VALVE OPEN Alert

2

Job Set-up Information A.

Test NO

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Referenced Information REFERENCE DESIGNATION Safety Valves (6HL,7HL) - Visual Inspection SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-005-A - Verification Test of the Safety Valves (OPEN Caution on ECAM)

Z260

A

1

B

FR70

PAX DOOR 2

A

FR65

TYPICAL

5

D C REAR PRESSURE BULKHEAD

A

3

B FR70

4

TYPICAL 2

6HL 7HL

C D

2 4

A

C D TYPICAL

FWD

A A TYPICAL

N_MM_213100_4_AAMB_01_00

Figure 21-31-00-991-00500-00-A / SHEET 1/1 - Safety Valves (6HL,7HL) - Visual Inspection ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-005-A - Verification Test of the Safety Valves (OPEN Caution on ECAM)

3.

Job Set-up Subtask 21-31-00-010-061-A A.

Get Access (1) Remove the food trolleys (1) from the Aft galley. (2) Remove the access panel (5).

4.

Procedure (Ref. Fig. Safety Valves (6HL,7HL) - Visual Inspection SHEET 1) Subtask 21-31-00-280-053-A A.

Visual Inspection of the Safety Valves (6HL,7HL). (1) Do a visual inspection of the two safety valves (2). NOTE: The safety valves (2) must be in the closed position. The ring gate (3) must seat properly on the rubber seal (4).

5.

Close-up Subtask 21-31-00-410-059-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the access panel (5) and the food trolleys (1) in the Aft galley.

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-55-00-040-001-A - Operational Test of the Emergency Ram-Air Inlet System

** ON A/C ALL TASK 21-55-00-040-001-A Operational Test of the Emergency Ram-Air Inlet System Task Summary MMEL or CDL Ref MMEL 21-07-01-06A

Access NO

Test NO

Specific Tools NO

1.

Reason for the Job MMEL 21-07-01-06A Emergency Ram Air Inlet Indication on the BLEED SD page (FAA only)

2

Job Set-up Information A.

E/T 00.4

Nb Men 1

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 34-10-00-860-002-A). (Ref. 34-10-00-860-005-A).

3.

Mhr 00.4

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure ADIRS Start Procedure ADIRS Stop Procedure

Job Set-up Subtask 21-55-00-861-052-A A.

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

Subtask 21-55-00-865-052-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 122VU

DESIGNATION AIR COND/RAM/AIR/INLET AIR COND/CAB/PRESS/CTL1 AIR COND/CAB PRESS/CTL/2

FIN 1HZ 1HL 2HL

LOCATION D10 D09 Y22

Subtask 21-55-00-860-051-A C.

Aircraft Maintenance Configuration (1) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) . (2) Make sure that the PRESS page shows on the ECAM lower display unit. (3) On the AIR COND panel 30VU:

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-55-00-040-001-A - Operational Test of the Emergency Ram-Air Inlet System

· make sure that the PACK 1 and the PACK 2 pushbutton switches are in the off position (the OFF legends are on). (4) Do the start procedure of the ADIRS (Ref. AMM TASK 34-10-00-860-002) . 4.

Procedure Subtask 21-55-00-040-050-A WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE OUTFLOW VALVES ARE CLEAR. MOVEMENT OF THE OUTFLOW VALVES CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

WARNING:

MAKE SURE THAT THERE ARE NO PERSONS OR EQUIPMENT NEAR THE RAM AIR INLET FLAPS. THE MOVEMENT OF THE RAM AIR INLET FLAPS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

A.

Operational Test ACTION RESULT 1.On the AIR COND panel 30VU: On the AIR COND panel 30VU: · lift the black guard and push the RAM AIR push- · in the RAM AIR pushbutton-switch the ON legend button-switch to the on position. comes on. On the ECAM upper display unit: · the green RAM AIR ON message comes on. On the ECAM lower display unit: · the outflow valve symbol shows approx. 50 DEG. open when the differential pressure in the fuselage is less than 1 psi. 2.On the AIR COND panel 30VU: On the AIR COND panel 30VU: · lift the black guard and push the RAM AIR push- · on the RAM AIR pushbutton-switch the ON legend button-switch to the off position. goes off. On the ECAM lower display unit: · the outflow valve symbol moves to the fully open position. On the ECAM upper display unit: · the green RAM AIR ON message goes off.

5.

Close-up Subtask 21-55-00-860-052-A A.

Put the aircraft back to its initial configuration. (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) Do the ADIRS stop procedure (Ref. AMM TASK 34-10-00-860-005) .

Subtask 21-55-00-941-050-A B.

Remove the WARNING NOTICE(S).

Subtask 21-55-00-862-052-A C.

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

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-013-A - Deactivation of the ConditionedAir Inlet Valve when the Blower Fan is Inoperative

** ON A/C ALL TASK 21-26-00-040-013-A Deactivation of the Conditioned-Air Inlet Valve when the Blower Fan is Inoperative Task Summary MMEL or CDL Ref MMEL 21-26-01C 1.

Reason for the Job MMEL 21-26-01C Avionics Blower Fan

2

Job Set-up Information A.

Access YES

Specific Tools NO

Mhr 00.6

E/T 00.6

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

Test YES

QTY AR AR AR AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 824

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 21-26-00-710-001-A).

DESIGNATION Operational Check of the Avionics Equipment Ventilation-System via MCDU (Ref. 21-26-00-710-001-A-01). Operational Check of the Avionics Equipment Ventilation (without the CFDS) (Ref. 24-41-00-861-002-A). Energize the Aircraft Electrical Circuits from the External Power (Ref. 24-41-00-861-002-A-01). Energize the Aircraft Electrical Circuits from the APU (Ref. 24-41-00-861-002-A-02). Energize the Aircraft Electrical Circuits from Engine 1(2) (Ref. 24-41-00-862-002-A). De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 31-60-00-860-001-A). EIS Start Procedure (Ref. 31-60-00-860-002-A). EIS Stop Procedure (Ref. 52-41-00-010-002-A). Open the Avionics Compartment Doors for Access (Ref. 52-41-00-410-002-A). Close the Avionics Compartment Doors after Access Conditioned-air inlet valve SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-013-A - Deactivation of the ConditionedAir Inlet Valve when the Blower Fan is Inoperative

A

824

C

Z127

A

C

FR24A FR20

B 21HQ

B MANUAL OVERRIDE (SHOWN IN OPEN POSITION) C = CLOSED O = OPEN C

O

CONNECTOR N_MM_212600_4_AEN0_01_00

Figure 21-26-00-991-00900-00-B / SHEET 1/1 - Conditioned-air inlet valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-013-A - Deactivation of the ConditionedAir Inlet Valve when the Blower Fan is Inoperative

3.

Job Set-up Subtask 21-26-00-861-087-A A.

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) .

Subtask 21-26-00-865-101-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/AVNCS VENT/CTL

FIN 5HQ

LOCATION D05

Subtask 21-26-00-010-091-A C.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at access door 824. (2) Open access door 824 (Ref. AMM TASK 52-41-00-010-002) .

4.

Procedure (Ref. Fig. Conditioned-air inlet valve SHEET 1) Subtask 21-26-00-040-068-A A.

Deactivation of the Conditioned-Air Inlet Valve (21HQ) when the Blower Fan is Inoperative (1) On the VENTILATION section of overhead panel 22VU: · Release the BLOWER pushbutton switch (the OVRD legend remains off). (2) On the conditioned-air inlet-valve 21HQ: (a) Disconnect connector 21HQ-A from valve 21HQ. (b) Put a CAP - BLANKING on the disconnected electrical connectors. (c) Keep the electrical cable and its connector near the valve. (d) Fully open valve 21HQ with the manual mechanism. (3) On the bottom part of the upper ECAM display unit: (a) The VENT AVNCS SYS FAULT warning comes into view: · Ignore this warning. (b) On the ECAM control panel: · Push the CLR key.

Subtask 21-26-00-865-123-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/AVNCS VENT/CTL

FIN 5HQ

LOCATION D05

Subtask 21-26-00-710-091-A C.

Operational Test

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-013-A - Deactivation of the ConditionedAir Inlet Valve when the Blower Fan is Inoperative

CAUTION:

AFTER THE DEACTIVATION OF THE APPLICABLE VALVE, MAKE SURE THAT YOU DO THE OPERATIONAL TEST OF THE AVIONICS-EQUIPMENT VENTILATION-SYSTEM BEFORE EACH FLIGHT.

(1) On the VENTILATION section of overhead panel 22VU: · Make sure that the OVRD legend of the BLOWER pushbutton switch comes on. · Push the BLOWER pushbutton switch (the OVRD legend goes off). (2) Do an operational test of the avionics equipment ventilation from the MCDU (Ref. AMM TASK 21-2600-710-001) . NOTE: Make sure that all the fault messages shown are related to: - The fault of the blower fan and - The deactivation of the conditioned-air inlet valve (21HQ). If other messages are shown, refer to the related MMEL valve item. (3) On the VENTILATION section of overhead panel 22VU: · Release the BLOWER pushbutton switch (the OVRD legend comes on). 5.

Close-up Subtask 21-26-00-410-088-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close access door 824 (Ref. AMM TASK 52-41-00-410-002) . (3) Remove the access platform(s).

Subtask 21-26-00-942-087-A B.

Safety Precautions (1) Put a WARNING NOTICE(S) in position in the cockpit to tell the crew that the blower fan and the conditioned-air inlet valve are deactivated. (2) Make an entry in the logbook.

Subtask 21-26-00-862-090-A C.

Aircraft Maintenance Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-007-A - Extract Fan Inoperative - Check of Conditioned-Air Inlet Valve Open

** ON A/C ALL TASK 21-26-00-040-007-A Extract Fan Inoperative - Check of Conditioned-Air Inlet Valve Open Task Summary MMEL or CDL Ref MMEL 21-26-02B 1.

Reason for the Job MMEL 21-26-02B Avionics Extract Fan

2

Job Set-up Information A.

Access YES

Specific Tools NO

Mhr 00.5

E/T 00.5

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Test YES

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 824

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 31-60-00-860-001-A). EIS Start Procedure (Ref. 31-60-00-860-002-A). EIS Stop Procedure (Ref. 52-41-00-010-002-A). Open the Avionics Compartment Doors for Access (Ref. 52-41-00-410-002-A). Close the Avionics Compartment Doors after Access Conditioned-air inlet valve SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-007-A - Extract Fan Inoperative - Check of Conditioned-Air Inlet Valve Open

A

824

C

Z127

A

C

FR24A FR20

B 21HQ

B MANUAL OVERRIDE (SHOWN IN OPEN POSITION) C = CLOSED O = OPEN C

O

CONNECTOR N_MM_212600_4_AEN0_01_00

Figure 21-26-00-991-00900-00-B / SHEET 1/1 - Conditioned-air inlet valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-007-A - Extract Fan Inoperative - Check of Conditioned-Air Inlet Valve Open

3.

Job Set-up Subtask 21-26-00-861-075-A A.

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) .

Subtask 21-26-00-010-065-A B.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 824. (2) Open the access door 824 (Ref. AMM TASK 52-41-00-010-002) .

4.

Procedure Subtask 21-26-00-040-056-A A.

Conditioned Air Inlet Valve (Ref. Fig. Conditioned-air inlet valve SHEET 1) (1) Make sure that the operation of avionics equipment ventilation with electrical ground power, has the time limits that follow: · outside air temperature 38 deg.C or less, no time limit · outside air temperature 45 deg.C, maximum of 3 hours · outside air temperature 55 deg.C, maximum of thirty five minutes. (2) On the VENTILATION section of the overhead control and indicating panel 22VU: · Release the EXTRACT pushbutton switch (the OVRD legend comes on). (3) On the bottom part of the upper ECAM display unit: · the VENT EXTRACT FAULT warning comes into view. Disregard this warning. On the ECAM control panel: · push the CLR key. (4) If the VENT BLOWER FAULT warning comes into view: · push the CAB FANS pushbutton switch on the VENTILATION section of the panel 22VU (the OFF legend goes off), · make sure that the VENT BLOWER FAULT warning goes out of view. (5) In the avionics compartment: · Make sure that the conditioned-air inlet valve 21HQ is open (the position indicator of the valve is at 0).

5.

Close-up Subtask 21-26-00-410-066-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access door 824 (Ref. AMM TASK 52-41-00-410-002) . (3) Remove the access platform(s).

Subtask 21-26-00-942-079-A B.

Safety Precautions (1) Put a WARNING NOTICE(S) in the cockpit to tell the crew that the Extract Fan is deactivated.

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-007-A - Extract Fan Inoperative - Check of Conditioned-Air Inlet Valve Open

(2) Make an entry in the logbook. Subtask 21-26-00-862-081-A C.

Aircraft Maintenance Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-001-A - Deactivation of the Skin Exchanger Inlet Bypass Valve

** ON A/C ALL TASK 21-26-00-040-001-A Deactivation of the Skin Exchanger Inlet Bypass Valve Task Summary MMEL or CDL Ref MMEL 21-26-03A

Access YES

Test YES

1.

Reason for the Job MMEL 21-26-03A Avionics Skin Exchanger Inlet Bypass Valve

2

Job Set-up Information A.

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific

B.

Specific Tools NO

QTY AR AR AR AR AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER TAPE - ADHESIVE WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 128EG, 824

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 21-26-00-710-001-A). (Ref. 21-26-00-710-001-A-01). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 52-41-00-010-002-A). (Ref. 52-41-00-410-002-A). (Ref. 53-12-13-000-001-A). (Ref. 53-12-13-400-001-A).

DESIGNATION Operational Check of the Avionics Equipment Ventilation-System via MCDU Operational Check of the Avionics Equipment Ventilation (without the CFDS) Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure Open the Avionics Compartment Doors for Access Close the Avionics Compartment Doors after Access Removal of the avionics compartment floor panels Installation of the avionics compartment floor panels

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-001-A - Deactivation of the Skin Exchanger Inlet Bypass Valve

REFERENCE DESIGNATION Skin Exchanger Inlet Bypass Valve SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-001-A - Deactivation of the Skin Exchanger Inlet Bypass Valve

824 80VU

Z120

FR12

A FR24

A

1

MANUAL OVERRIDE

16HQ

CONNECTOR

NOTE: 1

SHOWN IN CLOSED POSITION

C = CLOSED O = OPEN N_MM_212600_4_AJM0_01_00

Figure 21-26-00-991-01200-00-B / SHEET 1/1 - Skin Exchanger Inlet Bypass Valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-001-A - Deactivation of the Skin Exchanger Inlet Bypass Valve

3.

Job Set-up Subtask 21-26-00-861-057-A A.

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) .

Subtask 21-26-00-865-060-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/AVNCS VENT/CTL

FIN 6HQ

LOCATION D06

Subtask 21-26-00-010-053-B C.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 824. (2) Open access door 824 (Ref. AMM TASK 52-41-00-010-002) . (3) Remove access panel 128EG (Ref. AMM TASK 53-12-13-000-001) .

4.

Procedure Subtask 21-26-00-040-051-A A.

Closure Procedure of the Skin Exchanger Inlet-Bypass-Valve (Ref. Fig. Skin Exchanger Inlet Bypass Valve SHEET 1) (1) Disconnect connector 16HQ-A from valve 16HQ. (2) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (3) Keep the electrical cable with its connector near the valve and attach with a TAPE - ADHESIVE. (4) Turn the manual mechanism of the valve (16HQ) to the closed position. (5) On the bottom part of the upper ECAM display unit: (a) The VENT AVNCS SYS FAULT warning comes into view: · Disregard this warning. (b) On the ECAM control panel: · Push the CLR key.

Subtask 21-26-00-865-121-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/AVNCS VENT/CTL

FIN 6HQ

LOCATION D06

Subtask 21-26-00-710-090-A C.

Operational Test CAUTION:

AFTER THE DEACTIVATION OF THE APPLICABLE VALVE, MAKE SURE THAT YOU DO THE OPERATIONAL TEST OF THE AVIONICS-EQUIPMENT VENTILATION-SYSTEM BEFORE EACH FLIGHT.

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-001-A - Deactivation of the Skin Exchanger Inlet Bypass Valve

(1) Do an operational test of the avionics equipment ventilation from the MCDU (Ref. AMM TASK 21-2600-710-001) . NOTE: Make sure that all the fault messages shown are related to the fault of the skin exchanger inlet-bypass-valve. If other messages are shown, refer to the related MMEL valve item. 5.

Close-up Subtask 21-26-00-410-053-B A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install access panel 128EG (Ref. AMM TASK 53-12-13-400-001) . (3) Close access door 824 (Ref. AMM TASK 52-41-00-410-002) . (4) Remove the access platform(s).

Subtask 21-26-00-942-074-A B.

Safety Precautions (Ref. AMM TASK 24-41-00-862-002) . (1) Put a WARNING NOTICE(S) in the cockpit to tell the crew that this valve is deactivated. (2) Make an entry in the logbook.

Subtask 21-26-00-862-057-A C.

Aircraft Maintenance Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-002-A - Deactivation of the Skin Air Outlet Valve in the Closed Position with the Internal Flap in the Open Position

** ON A/C ALL TASK 21-26-00-040-002-A Deactivation of the Skin Air Outlet Valve in the Closed Position with the Internal Flap in the Open Position Task Summary MMEL or CDL Ref MMEL 21-26-04A

Access YES

1.

Reason for the Job MMEL 21-26-04A Avionics Skin Air Outlet Valve

2

Job Set-up Information A.

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

Test YES

QTY AR AR AR AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS 822

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 21-26-00-710-001-A). (Ref. 21-26-00-710-001-A-01). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

DESIGNATION Operational Check of the Avionics Equipment Ventilation-System via MCDU Operational Check of the Avionics Equipment Ventilation (without the CFDS) Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure

(Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). Skin-Air Outlet Valve Skin Exchanger Isolation Valve SHEET 1 ECAM Display after Deactivation of the Skin Air Outlet Valve SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-002-A - Deactivation of the Skin Air Outlet Valve in the Closed Position with the Internal Flap in the Open Position

A Z120 822

B FR24A

FR18

22HQ FR16

A HANDLE STOWED AND LATCHED INTERNAL FLAP IN FO POSITION 01

INTERNAL FLAP 01 IN FO POSITION MAIN FLAP 01 IN FC POSITION

MAIN FLAP IN FC POSITION

01

HANDLE STOWED AND LATCHED

C C

TYPE A

NOTE: 01 FC : FULLY CLOSED FO : FULLY OPEN

TYPE B

B N_MM_212600_4_ABP0_01_02

Figure 21-26-00-991-00800-00-B / SHEET 1/2 - Skin-Air Outlet Valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-002-A - Deactivation of the Skin Air Outlet Valve in the Closed Position with the Internal Flap in the Open Position

HANDLE

HANDLE LATCH

INTERNAL FLAP

DEACTIVATION SWITCH

MAIN FLAP

TYPE A

MAIN FLAP

HANDLE LATCH

HANDLE INTERNAL FLAP DEACTIVATION SWITCH

TYPE B

C N_MM_212600_4_ABP0_02_00

Figure 21-26-00-991-00800-00-B / SHEET 2/2 - Skin-Air Outlet Valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-002-A - Deactivation of the Skin Air Outlet Valve in the Closed Position with the Internal Flap in the Open Position

24HQ

A A

C FR16

822 FR12

C VALVE

B B

(SHOWN IN OPEN POSITION) C = CLOSED O = OPEN

MANUAL OVERRIDE

C

O

CONNECTOR N_MM_212600_4_ADN0_01_00

Figure 21-26-00-991-01000-00-B / SHEET 1/1 - Skin Exchanger Isolation Valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-002-A - Deactivation of the Skin Air Outlet Valve in the Closed Position with the Internal Flap in the Open Position

A B

A SYSTEM DISPLAY UNIT

CAB PRESS P PSI 8 0 0.0

GND COOL

V/S FT/MN

CAB ALT FT

2 0

10

0

0 300

2 SYS 1

SAFETY

VENT INLET OUTLET PACK 1

PACK 2

B PRESS PUSHBUTTON SWITCH

ECAM

TO CONFIG

CANC

UPPER DISPLAY

OFF

ENG

BLEED

PRESS

HYD

ELEC

FUEL

APU

COND

DOOR

F/CTL

WHEEL

ALL

STS

RCL

BRT

LOWER DISPLAY

CLR OFF

CIR

BRT

N_MM_212600_4_AHM0_01_00

Figure 21-26-00-991-01800-00-A / SHEET 1/1 - ECAM Display after Deactivation of the Skin Air Outlet Valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-002-A - Deactivation of the Skin Air Outlet Valve in the Closed Position with the Internal Flap in the Open Position

3.

Job Set-up Subtask 21-26-00-861-059-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . NOTE: The energization of the aircraft electrical circuits starts a full self-test of the ventilation system. The test continues for approximately two minutes. (2) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) .

Subtask 21-26-00-865-076-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/AVNCS VENT/CTL

FIN 6HQ

LOCATION D06

Subtask 21-26-00-869-117-A C.

If the ground horn is in operation: · On the external-power panel 108VU: Push the RESET pushbutton switch to stop the mechanical call horn.

Subtask 21-26-00-010-075-A D.

Get Access (1) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position on the right side of the aircraft, below the skin-air outlet valve 22HQ. (2) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access door 822. (3) Open the access door 822.

4.

Procedure (Ref. Fig. Skin-Air Outlet Valve) (Ref. Fig. Skin Exchanger Isolation Valve SHEET 1) (Ref. Fig. ECAM Display after Deactivation of the Skin Air Outlet Valve SHEET 1) Subtask 21-26-00-040-052-B CAUTION:

A.

DO NOT USE FORCE TO TURN THE HANDLE. THERE ARE SHEAR PINS IN THE HANDLE. IF YOU APPLY FORCE TO THE HANDLE WHEN THE FLAP IS IN THE FULLY OPEN OR CLOSED POSITION, THE SHEAR PINS WILL BREAK.

Partial Opening Procedure of the Skin-Air Outlet Valve NOTE: If the aircraft de-icing is necessary, you must be careful not to apply de-icing fluid on the skin airoutlet-valve area. During aircraft de-icing, you can keep the internal flap of the skin air-outlet-valve closed to prevent avionics equipment contamination. Open the flap after de-icing. NOTE: There are two types of skin-air outlet valve 22HQ. To know which type of valve is installed and the correct deactivation procedure to use, refer to the detail C on figure (Ref. Fig. Skin-Air Outlet Valve) - If you deactivate the 22HQ (type B), refer to the paragraph A.(1). - If you deactivate the 22HQ (type A), refer to the paragraph A.(2). (1) If the skin-air outlet valve 22HQ (type B) is installed:

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-002-A - Deactivation of the Skin Air Outlet Valve in the Closed Position with the Internal Flap in the Open Position

(a) When the valve is fully closed (main and internal flaps closed): (Ref. Fig. Skin-Air Outlet Valve) WARNING: OPEN ONLY THE INTERNAL FLAP. THE MAIN FLAP MUST STAY FULLY CLOSED. IF THE MAIN FLAP IS NOT FULLY CLOSED, THE AIRCRAFT WILL NOT PRESSURIZE. 1

Push the PUSH handle latch to release the handle.

2

Before you turn the handle, push it in the direction of the valve to disengage the clutch mechanism.

3

Turn it to give access to the deactivation switch.

4

Set the deactivation switch to OFF.

5

Pull the handle to engage the clutch mechanism. NOTE: Continuous rotation clockwise is required until desired position is obtained.

6

Turn the handle clockwise to open the internal flap.

7

When the internal flap stops to move and the main flap starts to move: · Turn the handle counterclockwise 1/4 turn or 1/2 turn.

8

Stow and latch the handle. NOTE: When the internal flap is open, if you continue to turn the handle clockwise, the main flap opens.

9

After 40 seconds, on the lower ECAM DU, do a check of the CAB PRESS page: · Make sure that the position indication shows the skin-air outlet valve in amber or green and open to 45 degrees (not fully open). NOTE: If the position indication of the skin-air outlet valve goes out of view and an amber XX comes into view, the valve is not in the correct position (open to 45 degrees). (Ref. Fig. ECAM Display after Deactivation of the Skin Air Outlet Valve SHEET 1)

(b) When the valve is fully open (main and internal flaps open): (Ref. Fig. Skin-Air Outlet Valve) WARNING: OPEN ONLY THE INTERNAL FLAP. THE MAIN FLAP MUST STAY FULLY CLOSED. IF THE MAIN FLAP IS NOT FULLY CLOSED, THE AIRCRAFT WILL NOT PRESSURIZE. 1

Push the PUSH handle latch to release the handle.

2

Pull the handle to engage the clutch mechanism.

3

Set the deactivation switch to OFF.

4

Turn the handle counterclockwise until the main flap closes. NOTE: Continuous rotation counterclockwise is required until desired position is obtained.

5

When the main flap stops to move and the internal flap starts to move: · Turn the handle clockwise a quarter of a turn or half a turn.

6

Stow and latch the handle.

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-002-A - Deactivation of the Skin Air Outlet Valve in the Closed Position with the Internal Flap in the Open Position

7

After 40 seconds, on the lower ECAM DU, do a check of the CAB PRESS page: · Make sure that the position indication shows the skin-air outlet valve in amber or green and open to 45 degrees (not fully open). NOTE: If the position indication of the skin-air outlet valve goes out of view and an amber XX comes into view, the valve is not in the correct position (open to 45 degrees). (Ref. Fig. ECAM Display after Deactivation of the Skin Air Outlet Valve SHEET 1) NOTE: When the main flap is closed, if you continue to turn the handle counterclockwise, the internal flap closes.

(2) If the skin-air outlet valve 22HQ (type A) is installed: WARNING: OPEN ONLY THE INTERNAL FLAP. THE MAIN FLAP MUST STAY FULLY CLOSED. IF THE MAIN FLAP IS NOT FULLY CLOSED, THE AIRCRAFT WILL NOT PRESSURIZE. (a) Push the PUSH handle latch to release the handle. (b) Pull the handle to engage the mechanism. (c) Fold out the handle. (d) Set the deactivation switch to OFF. (e) Turn the handle clockwise to open the internal flap. NOTE: Continuous rotation clockwise is required until desired position is obtained. (f)

Fold, stow and latch the handle. NOTE: The internal flap opens when the main flap closes. (Ref. Fig. Skin-Air Outlet Valve)

(g) After 40 seconds, on the lower ECAM DU, do a check of the CAB PRESS page: · Make sure that the position indication shows the skin-air outlet valve in amber or green and open to 45 degrees (not fully open). NOTE: If the position indication of the skin-air outlet valve goes out of view and an amber XX comes into view, the valve is not in the correct position (open to 45 degrees). (Ref. Fig. ECAM Display after Deactivation of the Skin Air Outlet Valve SHEET 1) (3) On the skin exchanger isolation-valve 24HQ: (Ref. Fig. Skin Exchanger Isolation Valve SHEET 1) (a) Disconnect the electrical connector 24HQ-A from the valve 24HQ. (b) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (c) Attach the electrical cable with its connector near the valve. (d) Open manually the valve 24HQ (manual control handle in position 0). (4) In the bottom part of the upper ECAM DU: · The VENT AVNCS SYS FAULT warning comes into view. Ignore this warning. On the ECAM control panel: · Push the CLR key. Subtask 21-26-00-865-093-A Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-002-A - Deactivation of the Skin Air Outlet Valve in the Closed Position with the Internal Flap in the Open Position

B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/AVNCS VENT/CTL

FIN 6HQ

LOCATION D06

Subtask 21-26-00-710-087-A C.

Operational Test of the Avionics Equipment Ventilation from the MCDU CAUTION:

AFTER THE DEACTIVATION OF THE APPLICABLE VALVE, MAKE SURE THAT YOU DO THE OPERATIONAL TEST OF THE AVIONICS-EQUIPMENT VENTILATION-SYSTEM BEFORE EACH FLIGHT.

(1) Do an operational test of the avionics equipment ventilation from the MCDU (Ref. AMM TASK 21-2600-710-001) . (a) If the valve is not in the correct position (open to 45 degrees): · After forty seconds, on the lower ECAM DU, on the CAB PRESS page: . The position indication of the skin-air outlet valve goes out of view and an amber XX comes into view. (Ref. Fig. ECAM Display after Deactivation of the Skin Air Outlet Valve SHEET 1) (b) If there is an extract-fan fault indication: · On the VENTILATION section of the overhead panel 22VU: . The FAULT legend of the EXTRACT pushbutton switch comes on amber, and · On the CAB PRESS page: . The EXTRACT indication is amber. (c) Release the EXTRACT pushbutton switch (the OVRD legend comes on). (d) Push the EXTRACT pushbutton switch (AUTO position). (2) Make sure that the extract fan indication is correct. (3) Make sure that all the fault messages shown are related to: · The fault of the skin air outlet-valve, and · The deactivation of the skin exchanger isolation-valve. (a) If other messages are shown, refer to the related MMEL item. (4) No other procedure is necessary, if: On the lower ECAM DU, on the CAB PRESS page: · The skin air-inlet-valve symbol is shown amber (because the outside air temperature is near the AEVC (Avionics Equipment Ventilation Computer) temperature limit), and · The operational test of the AEVC gives no maintenance message related to the skin air-inlet valve. 5.

Close-up Subtask 21-26-00-410-075-A A.

Close Access (1) Close the access door 822. (2) Remove the access platform(s).

Subtask 21-26-00-942-076-A B.

Safety Precautions (1) Make an entry in the logbook.

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-002-A - Deactivation of the Skin Air Outlet Valve in the Closed Position with the Internal Flap in the Open Position

Subtask 21-26-00-862-059-A C.

Aircraft Maintenance Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-004-A - Deactivation of the Skin Air Inlet Valve

** ON A/C ALL TASK 21-26-00-040-004-A Deactivation of the Skin Air Inlet Valve

FIN : 15HQ Task Summary MMEL or CDL Ref MMEL 21-26-05A

Access YES

1.

Reason for the Job MMEL 21-26-05A Avionics Skin Air Inlet Valve

2

Job Set-up Information A.

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

Test YES

QTY AR AR AR AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE ACCESS PLATFORM 3M (10 FT) SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 127 824

ZONE DESCRIPTION REAR AVIONIC COMPARTMENT

C. Referenced Information REFERENCE (Ref. 21-26-00-710-001-A). (Ref. 21-26-00-710-001-A-01). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 52-41-00-010-002-A).

DESIGNATION Operational Check of the Avionics Equipment Ventilation-System via MCDU Operational Check of the Avionics Equipment Ventilation (without the CFDS) Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure Open the Avionics Compartment Doors for Access

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-004-A - Deactivation of the Skin Air Inlet Valve

REFERENCE DESIGNATION (Ref. 52-41-00-410-002-A). Close the Avionics Compartment Doors after Access Skin Air-Inlet Valve SHEET 1 Conditioned-air inlet valve SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-004-A - Deactivation of the Skin Air Inlet Valve

824

80VU

A A

FR24A FR20

15HQ

B

C

B

DEACTIVATION SWITCH HANDLE

C HANDLE LATCH

N_MM_212600_4_AAP0_01_00

Figure 21-26-00-991-00500-00-B / SHEET 1/1 - Skin Air-Inlet Valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-004-A - Deactivation of the Skin Air Inlet Valve

A

824

C

Z127

A

C

FR24A FR20

B 21HQ

B MANUAL OVERRIDE (SHOWN IN OPEN POSITION) C = CLOSED O = OPEN C

O

CONNECTOR N_MM_212600_4_AEN0_01_00

Figure 21-26-00-991-00900-00-B / SHEET 1/1 - Conditioned-air inlet valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-004-A - Deactivation of the Skin Air Inlet Valve

3.

Job Set-up Subtask 21-26-00-861-063-A A.

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) .

Subtask 21-26-00-865-098-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU 49VU

DESIGNATION AIR COND/AVNCS VENT/CTL AIR COND/AVNCS VENT/CTL

FIN 6HQ 5HQ

LOCATION D06 D05

Subtask 21-26-00-010-077-A C.

Get Access (1) Put an ACCESS PLATFORM 3M (10 FT) in position on the left side of the aircraft below the valve 15HQ. (2) Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 824. (3) Open access door 824 (Ref. AMM TASK 52-41-00-010-002) .

4.

Procedure (Ref. Fig. Skin Air-Inlet Valve SHEET 1) Subtask 21-26-00-040-054-B A.

Closing Procedure of the Skin Air-Inlet Valve CAUTION:

DO NOT USE FORCE TO TURN THE HANDLE. THERE ARE SHEAR PINS IN THE HANDLE. IF YOU APPLY FORCE TO THE HANDLE WHEN THE FLAP IS IN THE FULLY OPEN OR CLOSED POSITION, THE SHEAR PINS WILL BREAK.

(1) On skin air-inlet valve 15HQ: (a) Push the PUSH latch to release the handle. (b) Before you turn the handle, push it in the direction of the valve to disengage the clutch mechanism. (c) Turn the handle to get access to the deactivation switch. (d) Set the deactivation switch to OFF. (e) Pull the handle to engage the clutch mechanism. (f)

Turn the handle counterclockwise to fully close the flap.

(g) Stow and latch the handle. Subtask 21-26-00-865-117-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU 49VU

DESIGNATION AIR COND/AVNCS VENT/CTL AIR COND/AVNCS VENT/CTL

FIN 6HQ 5HQ

LOCATION D06 D05

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-004-A - Deactivation of the Skin Air Inlet Valve

Subtask 21-26-00-710-088-A C.

Operational Test CAUTION:

AFTER THE DEACTIVATION OF THE APPLICABLE VALVE, MAKE SURE THAT YOU DO THE OPERATIONAL TEST OF THE AVIONICS-EQUIPMENT VENTILATION-SYSTEM BEFORE EACH FLIGHT.

(1) Do an operational test of the avionics equipment ventilation from the Multipurpose Control and Display Unit (MCDU) (Ref. AMM TASK 21-26-00-710-001) . NOTE: Make sure that all the fault messages shown are related to the fault of the skin air-inlet valve (15HQ). If other messages are shown, refer to the related MMEL valve item. (2) On the VENTILATION section of overhead panel 22VU: · Release the EXTRACT pushbutton switch (the OVRD legend comes on). (3) In the avionics compartment: · Make sure that the conditioned-air inlet valve (21HQ) is open (the position indicator of the valve is at 0). (Ref. Fig. Conditioned-air inlet valve SHEET 1) (4) On the bottom part of the upper ECAM display-unit: (a) The VENT AVNCS-SYS FAULT warning comes into view: · Ignore this warning. (b) On the ECAM control panel: · Push the CLR key. 5.

Close-up Subtask 21-26-00-410-076-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close access door 824 (Ref. AMM TASK 52-41-00-410-002) . (3) Remove the access platform(s).

Subtask 21-26-00-941-063-A B.

Aircraft Maintenance Configuration (1) Put a WARNING NOTICE(S) in the cockpit to tell the crew that the valve is disconnected. (2) Make an entry in the logbook.

Subtask 21-26-00-862-063-A C.

Aircraft Maintenance Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-015-A - Extract Fan Inoperative - Do the Deactivation of the Conditioned-Air Inlet Valve

** ON A/C ALL TASK 21-26-00-040-015-A Extract Fan Inoperative - Do the Deactivation of the Conditioned-Air Inlet Valve Task Summary MMEL or CDL Ref MMEL 21-26-02C 1.

Reason for the Job MMEL 21-26-02C Avionics Extract Fan

2

Job Set-up Information A.

Access YES

Specific Tools NO

Mhr 00.6

E/T 00.6

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

Test YES

QTY 1 AR AR AR

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 824

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 21-26-00-710-001-A).

DESIGNATION Operational Check of the Avionics Equipment Ventilation-System via MCDU (Ref. 21-26-00-710-001-A-01). Operational Check of the Avionics Equipment Ventilation (without the CFDS) (Ref. 24-41-00-861-002-A). Energize the Aircraft Electrical Circuits from the External Power (Ref. 24-41-00-861-002-A-01). Energize the Aircraft Electrical Circuits from the APU (Ref. 24-41-00-861-002-A-02). Energize the Aircraft Electrical Circuits from Engine 1(2) (Ref. 24-41-00-862-002-A). De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 31-60-00-860-001-A). EIS Start Procedure (Ref. 31-60-00-860-002-A). EIS Stop Procedure (Ref. 52-41-00-010-002-A). Open the Avionics Compartment Doors for Access (Ref. 52-41-00-410-002-A). Close the Avionics Compartment Doors after Access Conditioned-air inlet valve SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-015-A - Extract Fan Inoperative - Do the Deactivation of the Conditioned-Air Inlet Valve

A

824

C

Z127

A

C

FR24A FR20

B 21HQ

B MANUAL OVERRIDE (SHOWN IN OPEN POSITION) C = CLOSED O = OPEN C

O

CONNECTOR N_MM_212600_4_AEN0_01_00

Figure 21-26-00-991-00900-00-B / SHEET 1/1 - Conditioned-air inlet valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-015-A - Extract Fan Inoperative - Do the Deactivation of the Conditioned-Air Inlet Valve

3.

Job Set-up Subtask 21-26-00-861-091-A A.

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) .

Subtask 21-26-00-865-105-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/AVNCS VENT/CTL

FIN 5HQ

LOCATION D05

Subtask 21-26-00-010-095-A C.

Get Access (1) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the access door 824. (2) Open the access door 824 (Ref. AMM TASK 52-41-00-010-002) .

4.

Procedure (Ref. Fig. Conditioned-air inlet valve SHEET 1) Subtask 21-26-00-040-071-A A.

Opening Procedure of the Conditioned-Air Inlet Valve (1) On the VENTILATION section of the overhead control and indicating panel 22VU: · Release the EXTRACT pushbutton switch (the OVRD legend comes on). (2) On the conditioned-air inlet valve 21HQ: (a) Disconnect the connector 21HQ-A from the conditioned-air inlet valve 21HQ. (b) Put CAP - BLANKING on the disconnected electrical connectors. (c) Keep the electrical cable and its connector near the valve. (d) Fully open the conditioned-air inlet valve 21HQ with the manual mechanism. (3) On the bottom part of the upper ECAM display unit: · The VENT AVNCS SYS FAULT warning comes into view. Ignore this warning. On the ECAM control panel: · Push the CLR key.

Subtask 21-26-00-865-109-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/AVNCS VENT/CTL

FIN 5HQ

LOCATION D05

Subtask 21-26-00-710-084-A C.

Do the Operational Test:

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-015-A - Extract Fan Inoperative - Do the Deactivation of the Conditioned-Air Inlet Valve

CAUTION:

AFTER THE DEACTIVATION OF THE APPLICABLE VALVE, MAKE SURE THAT YOU DO THE OPERATIONAL TEST OF THE AVIONICS-EQUIPMENT VENTILATION-SYSTEM BEFORE EACH FLIGHT.

(1) Do an operational test of the avionics equipment ventilation from the Multipurpose Control and Display Unit (MCDU) (Ref. AMM TASK 21-26-00-710-001) . NOTE: Make sure that all the fault messages shown are related to: - The fault of the extract fan, and - The deactivation of the conditioned-air inlet valve (21HQ). If other messages are shown, refer to the related MMEL valve item. 5.

Close-up Subtask 21-26-00-410-092-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access door 824 (Ref. AMM TASK 52-41-00-410-002) . (3) Remove the access platform(s).

Subtask 21-26-00-942-089-A B.

Safety Precautions (1) Put WARNING NOTICE(S) in position in the cockpit to tell the crew that the extract fan and the conditioned-air inlet valve are deactivated. (2) Make an entry in the logbook.

Subtask 21-26-00-862-094-A C.

Aircraft Maintenance Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-003-A - Deactivation of the Conditioned-Air Inlet Valve

** ON A/C ALL TASK 21-26-00-040-003-A Deactivation of the Conditioned-Air Inlet Valve Task Summary MMEL or CDL Ref MMEL 21-26-08A

Access YES

Test YES

1.

Reason for the Job MMEL 21-26-08A Avionics Air Conditioning Inlet Valve

2

Job Set-up Information A.

Mhr 00.2

E/T 00.2

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

Specific Tools NO

QTY AR AR AR AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 824

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 21-26-00-710-001-A).

DESIGNATION Operational Check of the Avionics Equipment Ventilation-System via MCDU (Ref. 21-26-00-710-001-A-01). Operational Check of the Avionics Equipment Ventilation (without the CFDS) (Ref. 24-41-00-861-002-A). Energize the Aircraft Electrical Circuits from the External Power (Ref. 24-41-00-861-002-A-01). Energize the Aircraft Electrical Circuits from the APU (Ref. 24-41-00-861-002-A-02). Energize the Aircraft Electrical Circuits from Engine 1(2) (Ref. 24-41-00-862-002-A). De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 31-60-00-860-001-A). EIS Start Procedure (Ref. 31-60-00-860-002-A). EIS Stop Procedure (Ref. 52-41-00-010-002-A). Open the Avionics Compartment Doors for Access (Ref. 52-41-00-410-002-A). Close the Avionics Compartment Doors after Access Conditioned-air inlet valve SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-003-A - Deactivation of the Conditioned-Air Inlet Valve

A

824

C

Z127

A

C

FR24A FR20

B 21HQ

B MANUAL OVERRIDE (SHOWN IN OPEN POSITION) C = CLOSED O = OPEN C

O

CONNECTOR N_MM_212600_4_AEN0_01_00

Figure 21-26-00-991-00900-00-B / SHEET 1/1 - Conditioned-air inlet valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-003-A - Deactivation of the Conditioned-Air Inlet Valve

3.

Job Set-up Subtask 21-26-00-861-061-A A.

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) .

Subtask 21-26-00-865-064-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/AVNCS VENT/CTL

FIN 5HQ

LOCATION D05

Subtask 21-26-00-010-057-A C.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 824. (2) Open access door 824 (Ref. AMM TASK 52-41-00-010-002) .

4.

Procedure Subtask 21-26-00-040-053-A A.

Opening Procedure of the Conditioned-Air Inlet Valve (Ref. Fig. Conditioned-air inlet valve SHEET 1) (1) On the conditioned-air inlet-valve 21HQ: (a) Disconnect connector 21HQ-A from valve 21HQ. (b) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (c) Keep the electrical cable and its connector near the valve. (d) Fully open valve 21HQ with the manual mechanism. (2) On the bottom part of the upper ECAM display unit: (a) The VENT AVNCS SYS FAULT warning comes into view: · Disregard this warning. (b) On the ECAM control panel: · push the CLR key.

Subtask 21-26-00-865-120-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/AVNCS VENT/CTL

FIN 5HQ

LOCATION D05

Subtask 21-26-00-710-089-A C.

Operational Test CAUTION:

AFTER THE DEACTIVATION OF THE APPLICABLE VALVE, MAKE SURE THAT YOU DO THE OPERATIONAL TEST OF THE AVIONICS-EQUIPMENT VENTILATION-SYSTEM BEFORE EACH FLIGHT.

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-003-A - Deactivation of the Conditioned-Air Inlet Valve

(1) Do an operational test of the avionics equipment ventilation from the MCDU (Ref. AMM TASK 21-2600-710-001) . NOTE: Make sure that all the fault messages shown are related to the fault of the conditioned-air inlet valve (21HQ). If other messages are shown, refer to the related MMEL valve item. 5.

Close-up Subtask 21-26-00-410-058-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close access door 824 (Ref. AMM TASK 52-41-00-410-002) . (3) Remove the access platform(s).

Subtask 21-26-00-942-077-A B.

Safety Precautions (1) Put a WARNING NOTICE(S) in the cockpit to tell the crew that this valve is deactivated. (2) Make an entry in the logbook.

Subtask 21-26-00-862-061-A C.

Aircraft Maintenance Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-014-A - Skin Air-Inlet Valve Inoperative Do the Deactivation of the Conditioned-Air Inlet Valve

** ON A/C ALL TASK 21-26-00-040-014-A Skin Air-Inlet Valve Inoperative - Do the Deactivation of the Conditioned-Air Inlet Valve Task Summary MMEL or CDL Ref MMEL 21-26-05B

Access YES

1.

Reason for the Job MMEL 21-26-05B Avionics Skin Air Inlet Valve

2

Job Set-up Information A.

Specific Tools NO

Mhr 00.6

E/T 00.6

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

Test NO

QTY AR AR AR

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS 824

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 21-26-00-710-001-A). (Ref. 21-26-00-710-001-A-01). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

DESIGNATION Operational Check of the Avionics Equipment Ventilation-System via MCDU Operational Check of the Avionics Equipment Ventilation (without the CFDS) Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure Open the Avionics Compartment Doors for Access Close the Avionics Compartment Doors after Access

(Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 52-41-00-010-002-A). (Ref. 52-41-00-410-002-A). Skin Air-Inlet Valve SHEET 1 Conditioned-air inlet valve SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-014-A - Skin Air-Inlet Valve Inoperative Do the Deactivation of the Conditioned-Air Inlet Valve

824

80VU

A A

FR24A FR20

15HQ

B

C

B

DEACTIVATION SWITCH HANDLE

C HANDLE LATCH

N_MM_212600_4_AAP0_01_00

Figure 21-26-00-991-00500-00-B / SHEET 1/1 - Skin Air-Inlet Valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-014-A - Skin Air-Inlet Valve Inoperative Do the Deactivation of the Conditioned-Air Inlet Valve

A

824

C

Z127

A

C

FR24A FR20

B 21HQ

B MANUAL OVERRIDE (SHOWN IN OPEN POSITION) C = CLOSED O = OPEN C

O

CONNECTOR N_MM_212600_4_AEN0_01_00

Figure 21-26-00-991-00900-00-B / SHEET 1/1 - Conditioned-air inlet valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-014-A - Skin Air-Inlet Valve Inoperative Do the Deactivation of the Conditioned-Air Inlet Valve

3.

Job Set-up Subtask 21-26-00-861-090-A A.

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) .

Subtask 21-26-00-865-104-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU 49VU

DESIGNATION AIR COND/AVNCS VENT/CTL AIR COND/AVNCS VENT/CTL

FIN 6HQ 5HQ

LOCATION D06 D05

Subtask 21-26-00-869-118-A C.

If the ground horn is in operation: · On the external-power panel 108VU: Push the RESET pushbutton switch to stop the mechanical call horn.

Subtask 21-26-00-010-094-A D.

Get Access (1) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position on the left side of the aircraft below the skin air-inlet valve 15HQ. (2) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the access door 824. (3) Open the access door 824 (Ref. AMM TASK 52-41-00-010-002) .

4.

Procedure Subtask 21-26-00-040-070-B A.

Closing Procedure of the Skin Air-Inlet Valve CAUTION:

DO NOT USE FORCE TO TURN THE HANDLE. THERE ARE SHEAR PINS IN THE HANDLE. IF YOU APPLY FORCE TO THE HANDLE WHEN THE FLAP IS IN THE FULLY OPEN OR CLOSED POSITION, THE SHEAR PINS WILL BREAK.

(1) On the skin air-inlet valve 15HQ: (Ref. Fig. Skin Air-Inlet Valve SHEET 1) (a) Push the PUSH latch to release the handle. (b) Before you turn the handle, push it in the direction of the valve to disengage the clutch mechanism. (c) Turn the handle to give access to the deactivation switch. (d) Set the deactivation switch to OFF. (e) Pull the handle to engage the clutch mechanism. (f)

Turn the handle counterclockwise to fully close the flap.

(g) Stow and latch the handle. (2) On the conditioned-air inlet valve 21HQ: (Ref. Fig. Conditioned-air inlet valve SHEET 1)

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-014-A - Skin Air-Inlet Valve Inoperative Do the Deactivation of the Conditioned-Air Inlet Valve

(a) Disconnect the connector 21HQ-A from the conditioned-air inlet valve 21HQ. (b) Put CAP - BLANKING on the disconnected electrical connectors. (c) Keep the electrical cable and its connector near the valve. (d) Fully open the conditioned-air inlet valve 21HQ with the manual mechanism. Subtask 21-26-00-865-108-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU 49VU

DESIGNATION AIR COND/AVNCS VENT/CTL AIR COND/AVNCS VENT/CTL

FIN 6HQ 5HQ

LOCATION D06 D05

Subtask 21-26-00-710-083-B C.

Operational Test CAUTION:

AFTER THE DEACTIVATION OF THE APPLICABLE VALVE, MAKE SURE THAT YOU DO THE OPERATIONAL TEST OF THE AVIONICS-EQUIPMENT VENTILATION-SYSTEM BEFORE EACH FLIGHT.

(1) Do an operational test of the avionics equipment ventilation from the Multipurpose Control and Display Unit (MCDU) (Ref. AMM TASK 21-26-00-710-001) . NOTE: Make sure that all the fault messages shown are related to: - The fault of the skin air-inlet valve, and - The deactivation of the conditioned-air inlet valve (21HQ). BLOWER FAULT legend can come on but you can ignore it. If other messages are shown, refer to the related MMEL valve item. (2) On the VENTILATION section of the overhead control and indicating panel 22VU: · Release the EXTRACT pushbutton switch (the OVRD legend comes on). NOTE: BLOWER FAULT legend goes out of view. (3) On the bottom part of the upper ECAM display unit: · The VENT AVNCS SYS FAULT warning comes into view. Ignore this warning. On the ECAM control panel: · Push the CLR key. 5.

Close-up Subtask 21-26-00-410-091-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access door 824 (Ref. AMM TASK 52-41-00-410-002) . (3) Remove the access platform(s).

Subtask 21-26-00-942-088-A B.

Safety Precautions (1) Make an entry in the logbook.

Subtask 21-26-00-862-093-A Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-014-A - Skin Air-Inlet Valve Inoperative Do the Deactivation of the Conditioned-Air Inlet Valve

C.

Aircraft Maintenance Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-005-A - Avionics Equipment Ventilation Computer Inoperative (AEVC) - Check of the Ventilation System

** ON A/C ALL TASK 21-26-00-040-005-A Avionics Equipment Ventilation Computer Inoperative (AEVC) - Check of the Ventilation System Task Summary MMEL or CDL Ref MMEL 21-26-10A

Access YES

Test YES

1.

Reason for the Job MMEL 21-26-10A Avionics Equipment Ventilation Computer (AEVC)

2

Job Set-up Information A.

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Specific Tools NO

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 824

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 52-41-00-010-002-A). (Ref. 52-41-00-410-002-A). Skin Air-Inlet Valve SHEET 1

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure Open the Avionics Compartment Doors for Access Close the Avionics Compartment Doors after Access

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-005-A - Avionics Equipment Ventilation Computer Inoperative (AEVC) - Check of the Ventilation System

824

80VU

A A

FR24A FR20

15HQ

B

C

B

DEACTIVATION SWITCH HANDLE

C HANDLE LATCH

N_MM_212600_4_AAP0_01_00

Figure 21-26-00-991-00500-00-B / SHEET 1/1 - Skin Air-Inlet Valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-005-A - Avionics Equipment Ventilation Computer Inoperative (AEVC) - Check of the Ventilation System

3.

Job Set-up Subtask 21-26-00-861-073-A A.

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) .

Subtask 21-26-00-010-061-A B.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 824. (2) Open the access door 824 (Ref. AMM TASK 52-41-00-010-002) .

4.

Procedure Subtask 21-26-00-040-050-B A.

AEVC Check of Ventilation System and Skin Air-Inlet Valve-Closure (Ref. Fig. Skin Air-Inlet Valve SHEET 1) (1) Do this test: ACTION RESULT 1.On the VENTILATION section of the overhead On the VENTILATION section of the overhead panel 22VU: panel 22VU: · Release the BLOWER and EXTRACT pushbut- · The OVRD legends of the BLOWER and EXton switches. TRACT pushbutton switches come on. If the ground horn is activated: On the rear circuit The ground horn is deactivated. breaker panel 121VU: · Open the circuit breaker 2WC. NOTE: The circuit breaker 2WC must be closed again after the first engine start. If the horn is operated after landing when the engines are stopped, it can be deactivated again. Then, you must switch off the ADIRS before you go away from the aircraft. On the lower ECAM display unit, on the CAB PRESS page: · The outlet valve is partially open. NOTE: If the ventilation system is defective or when the BLOWER and EXTRACT pushbutton switches are released (OVRD legends on): - There are no more colored backgrounds on the EFIS displays. In the aft avionics compartment: · The conditionned air inlet valve 21HQ is open. · You can hear the extract fan operate. On the CAB PRESS page:

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-005-A - Avionics Equipment Ventilation Computer Inoperative (AEVC) - Check of the Ventilation System ACTION

RESULT · The VENT indication is amber.

(2) On the skin air-inlet valve 15HQ: (a) Push the PUSH latch to release the handle. (b) Push the handle to engage the switch. (c) Set the deactivation switch to OFF. (d) Stow and latch the handle. (e) Make sure that the skin air-inlet valve is fully closed. (3) On the lower ECAM display unit, on the CAB PRESS page: · Make sure that there is no XX on the INLET indication. (4) On the bottom part of the upper ECAM display unit: · The VENT AVNCS SYS FAULT warning comes into view. Disregard this warning. On the ECAM control panel: · Push the CLR key. 5.

Close-up Subtask 21-26-00-410-062-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access door 824 (Ref. AMM TASK 52-41-00-410-002) . (3) Remove the access platform(s).

Subtask 21-26-00-942-078-A B.

Safety Precautions (1) Put a WARNING NOTICE(S) in the cockpit to tell the crew that the AEVC is deactivated. (2) Make an entry in the logbook.

Subtask 21-26-00-862-079-A C.

Aircraft Maintenance Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-008-A - Skin-Exchanger Isolation Valve Inoperative - Check of the Open Position of the Valve

** ON A/C ALL TASK 21-26-00-040-008-A Skin-Exchanger Isolation Valve Inoperative - Check of the Open Position of the Valve Task Summary MMEL or CDL Ref MMEL 21-26-06A

Access YES

Test YES

1.

Reason for the Job MMEL 21-26-06A Avionics Skin Exchanger Isolation Valve

2

Job Set-up Information A.

Mhr 00.2

E/T 00.2

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Specific Tools NO

QTY DESIGNATION 1 ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE 1 WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 822

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 21-26-00-710-001-A).

DESIGNATION Operational Check of the Avionics Equipment Ventilation-System via MCDU (Ref. 21-26-00-710-001-A-01). Operational Check of the Avionics Equipment Ventilation (without the CFDS) (Ref. 24-41-00-861-002-A). Energize the Aircraft Electrical Circuits from the External Power (Ref. 24-41-00-861-002-A-01). Energize the Aircraft Electrical Circuits from the APU (Ref. 24-41-00-861-002-A-02). Energize the Aircraft Electrical Circuits from Engine 1(2) (Ref. 24-41-00-862-002-A). De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Skin Exchanger Isolation Valve SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-008-A - Skin-Exchanger Isolation Valve Inoperative - Check of the Open Position of the Valve

24HQ

A A

C FR16

822 FR12

C VALVE

B B

(SHOWN IN OPEN POSITION) C = CLOSED O = OPEN

MANUAL OVERRIDE

C

O

CONNECTOR N_MM_212600_4_ADN0_01_00

Figure 21-26-00-991-01000-00-B / SHEET 1/1 - Skin Exchanger Isolation Valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-008-A - Skin-Exchanger Isolation Valve Inoperative - Check of the Open Position of the Valve

3.

Job Set-up Subtask 21-26-00-861-065-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

Subtask 21-26-00-010-069-A B.

Get Access (1) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the access door 822. (2) Open the access door 822.

4.

Procedure (Ref. Fig. Skin Exchanger Isolation Valve SHEET 1) Subtask 21-26-00-040-060-A A.

Check of the Open Position of the Valve (1) In the avionics compartment: · Make sure that the skin-exchanger isolation valve 24HQ is open (the position indicator of the valve is at 0). CAUTION:

AFTER THE DEACTIVATION OF THE APPLICABLE VALVE, MAKE SURE THAT YOU DO THE OPERATIONAL TEST OF THE AVIONICS-EQUIPMENT VENTILATION-SYSTEM BEFORE EACH FLIGHT.

(2) Do an operational test of the avionics equipment ventilation from the MCDU (Ref. AMM TASK 21-2600-710-001) . NOTE: Make sure that all the fault messages shown are related to the fault of the skin-exchanger isolation valve. If other messages are shown, refer to the related MMEL valve item. 5.

Close-up Subtask 21-26-00-410-070-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access door 822. (3) Remove the access platform(s).

Subtask 21-26-00-942-075-A B.

Safety Precautions (1) Put a WARNING NOTICE(S) in position in the cockpit to tell the crew that the skin-exchanger isolation valve is deactivated. (2) Make an entry in the logbook.

Subtask 21-26-00-862-065-A C.

Aircraft Maintenance Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-008-A - Skin-Exchanger Isolation Valve Inoperative - Check of the Open Position of the Valve

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-016-A - Deactivation of the Skin-Exchanger Isolation Valve

** ON A/C ALL TASK 21-26-00-040-016-A Deactivation of the Skin-Exchanger Isolation Valve Task Summary MMEL or CDL Ref MMEL 21-26-06B

Access YES

Test YES

1.

Reason for the Job MMEL 21-26-06B Avionics Skin Exchanger Isolation Valve

2

Job Set-up Information A.

Mhr 00.6

E/T 00.6

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

Specific Tools NO

QTY 1 AR AR 1

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 822

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 21-26-00-710-001-A).

DESIGNATION Operational Check of the Avionics Equipment Ventilation-System via MCDU (Ref. 21-26-00-710-001-A-01). Operational Check of the Avionics Equipment Ventilation (without the CFDS) (Ref. 24-41-00-861-002-A). Energize the Aircraft Electrical Circuits from the External Power (Ref. 24-41-00-861-002-A-01). Energize the Aircraft Electrical Circuits from the APU (Ref. 24-41-00-861-002-A-02). Energize the Aircraft Electrical Circuits from Engine 1(2) (Ref. 24-41-00-862-002-A). De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 31-60-00-860-001-A). EIS Start Procedure (Ref. 31-60-00-860-002-A). EIS Stop Procedure (Ref. 52-41-00-010-002-A). Open the Avionics Compartment Doors for Access (Ref. 52-41-00-410-002-A). Close the Avionics Compartment Doors after Access Skin Exchanger Isolation Valve SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-016-A - Deactivation of the Skin-Exchanger Isolation Valve

24HQ

A A

C FR16

822 FR12

C VALVE

B B

(SHOWN IN OPEN POSITION) C = CLOSED O = OPEN

MANUAL OVERRIDE

C

O

CONNECTOR N_MM_212600_4_ADN0_01_00

Figure 21-26-00-991-01000-00-B / SHEET 1/1 - Skin Exchanger Isolation Valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-016-A - Deactivation of the Skin-Exchanger Isolation Valve

3.

Job Set-up Subtask 21-26-00-861-092-A A.

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) .

Subtask 21-26-00-865-106-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/AVNCS VENT/CTL

FIN 6HQ

LOCATION D06

Subtask 21-26-00-010-096-A C.

Get Access (1) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the access door 822. (2) Open the access door 822 (Ref. AMM TASK 52-41-00-010-002) .

4.

Procedure (Ref. Fig. Skin Exchanger Isolation Valve SHEET 1) Subtask 21-26-00-040-072-A A.

Opening Procedure of the Skin-Exchanger Isolation Valve (1) Disconnect the connector 24HQ-A from the skin-exchanger isolation valve 24HQ. (2) Put CAP - BLANKING on the disconnected electrical connectors. (3) Keep the electrical cable and its connector near the valve. (4) Fully open the skin-exchanger isolation valve 24HQ with the manual mechanism. (5) On the bottom part of the upper ECAM display unit: · The VENT AVNCS SYS FAULT warning comes into view. Ignore this warning. On the ECAM control panel: · Push the CLR key.

Subtask 21-26-00-865-110-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/AVNCS VENT/CTL

FIN 6HQ

LOCATION D06

Subtask 21-26-00-710-085-A C.

Do the Operational Test: CAUTION:

AFTER THE DEACTIVATION OF THE APPLICABLE VALVE, MAKE SURE THAT YOU DO THE OPERATIONAL TEST OF THE AVIONICS-EQUIPMENT VENTILATION-SYSTEM BEFORE EACH FLIGHT.

(1) Do an operational test of the avionics equipment ventilation from the Multipurpose Control and Display Unit (MCDU) (Ref. AMM TASK 21-26-00-710-001) .

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-016-A - Deactivation of the Skin-Exchanger Isolation Valve

NOTE: Make sure that all the fault messages shown are related to the fault of the skin-exchanger isolation valve. If other messages are shown, refer to the related MMEL valve item. 5.

Close-up Subtask 21-26-00-410-093-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access door 822 (Ref. AMM TASK 52-41-00-410-002) . (3) Remove the access platform(s).

Subtask 21-26-00-942-090-A B.

Safety Precautions (1) Put a WARNING NOTICE(S) in position in the cockpit to tell the crew that the skin-exchanger isolation valve is deactivated. (2) Make an entry in the logbook.

Subtask 21-26-00-862-095-A C.

Aircraft Maintenance Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-009-A - Deactivation of the Avionics Ventilation Filter

** ON A/C ALL TASK 21-26-00-040-009-A Deactivation of the Avionics Ventilation Filter Task Summary MMEL or CDL Ref MMEL 21-26-09B

Access YES

1.

Reason for the Job MMEL 21-26-09B Avionics Ventilation Filter

2

Job Set-up Information A.

Specific Tools NO

Mhr 00.5

E/T 00.5

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Test YES

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS 824

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 52-41-00-010-002-A). Open the Avionics Compartment Doors for Access (Ref. 52-41-00-410-002-A). Close the Avionics Compartment Doors after Access Conditioned-air inlet valve SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-009-A - Deactivation of the Avionics Ventilation Filter

A

824

C

Z127

A

C

FR24A FR20

B 21HQ

B MANUAL OVERRIDE (SHOWN IN OPEN POSITION) C = CLOSED O = OPEN C

O

CONNECTOR N_MM_212600_4_AEN0_01_00

Figure 21-26-00-991-00900-00-B / SHEET 1/1 - Conditioned-air inlet valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-009-A - Deactivation of the Avionics Ventilation Filter

3.

Job Set-up Subtask 21-26-00-861-080-A A.

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

Subtask 21-26-00-010-071-A B.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 824. (2) Open the access door 824 (Ref. AMM TASK 52-41-00-010-002) .

4.

Procedure (Ref. Fig. Conditioned-air inlet valve SHEET 1) Subtask 21-26-00-040-059-A A.

Deactivation of the Avionics Ventilation Filter (1) On the VENTILATION section of the overhead panel 22VU: · release the EXTRACT pushbutton switch (the OVRD legend comes on). (2) In the avionics compartment: · before each flight, make sure that the conditioned-air inlet valve 21HQ is open (the position indicator of the valve is at 0).

5.

Close-up Subtask 21-26-00-410-072-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access door 824 (Ref. AMM TASK 52-41-00-410-002) . (3) Remove the access platform(s).

Subtask 21-26-00-869-101-A B.

Aircraft Maintenance Configuration (1) Make an entry in the logbook.

Subtask 21-26-00-862-080-A C.

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

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-017-A - Avionics Ventilation Filter Inoperative - Do the Deactivation of the Conditioned-Air Inlet Valve

** ON A/C ALL TASK 21-26-00-040-017-A Avionics Ventilation Filter Inoperative - Do the Deactivation of the Conditioned-Air Inlet Valve Task Summary MMEL or CDL Ref MMEL 21-26-09C

Access YES

1.

Reason for the Job MMEL 21-26-09C Avionics Ventilation Filter

2

Job Set-up Information A.

Specific Tools NO

Mhr 00.6

E/T 00.6

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

Test YES

QTY 1 AR AR AR

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 824

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 21-26-00-710-001-A).

DESIGNATION Operational Check of the Avionics Equipment Ventilation-System via MCDU (Ref. 21-26-00-710-001-A-01). Operational Check of the Avionics Equipment Ventilation (without the CFDS) (Ref. 24-41-00-861-002-A). Energize the Aircraft Electrical Circuits from the External Power (Ref. 24-41-00-861-002-A-01). Energize the Aircraft Electrical Circuits from the APU (Ref. 24-41-00-861-002-A-02). Energize the Aircraft Electrical Circuits from Engine 1(2) (Ref. 24-41-00-862-002-A). De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 31-60-00-860-001-A). EIS Start Procedure (Ref. 31-60-00-860-002-A). EIS Stop Procedure (Ref. 52-41-00-010-002-A). Open the Avionics Compartment Doors for Access (Ref. 52-41-00-410-002-A). Close the Avionics Compartment Doors after Access Conditioned-air inlet valve SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-017-A - Avionics Ventilation Filter Inoperative - Do the Deactivation of the Conditioned-Air Inlet Valve

A

824

C

Z127

A

C

FR24A FR20

B 21HQ

B MANUAL OVERRIDE (SHOWN IN OPEN POSITION) C = CLOSED O = OPEN C

O

CONNECTOR N_MM_212600_4_AEN0_01_00

Figure 21-26-00-991-00900-00-B / SHEET 1/1 - Conditioned-air inlet valve ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-017-A - Avionics Ventilation Filter Inoperative - Do the Deactivation of the Conditioned-Air Inlet Valve

3.

Job Set-up Subtask 21-26-00-861-093-A A.

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) .

Subtask 21-26-00-865-107-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/AVNCS VENT/CTL

FIN 5HQ

LOCATION D05

Subtask 21-26-00-010-097-A C.

Get Access (1) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the access door 824. (2) Open the access door 824 (Ref. AMM TASK 52-41-00-010-002) .

4.

Procedure (Ref. Fig. Conditioned-air inlet valve SHEET 1) Subtask 21-26-00-040-073-A A.

Opening Procedure of the Conditioned-Air Inlet Valve (1) On the VENTILATION section of the overhead control and indicating panel 22VU: · Release the EXTRACT pushbutton switch (the OVRD legend comes on). (2) On the conditioned-air inlet valve 21HQ: (a) Disconnect the connector 21HQ-A from the conditioned-air inlet valve 21HQ. (b) Put CAP - BLANKING on the disconnected electrical connectors. (c) Keep the electrical cable and its connector near the valve. (d) Fully open the conditioned-air inlet valve 21HQ with the manual mechanism. (3) On the bottom part of the upper ECAM display unit: · The VENT AVNCS SYS FAULT warning comes into view. Ignore this warning. On the ECAM control panel: · Push the CLR key.

Subtask 21-26-00-865-111-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/AVNCS VENT/CTL

FIN 5HQ

LOCATION D05

Subtask 21-26-00-710-086-A C.

Do the Operational Test:

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-017-A - Avionics Ventilation Filter Inoperative - Do the Deactivation of the Conditioned-Air Inlet Valve

CAUTION:

AFTER THE DEACTIVATION OF THE APPLICABLE VALVE, MAKE SURE THAT YOU DO THE OPERATIONAL TEST OF THE AVIONICS-EQUIPMENT VENTILATION-SYSTEM BEFORE EACH FLIGHT.

(1) Do an operational test of the avionics equipment ventilation from the Multipurpose Control and Display Unit (MCDU) (Ref. AMM TASK 21-26-00-710-001) . NOTE: Make sure that all the fault messages shown are related to: - The fault of the ventilation filter, and - The deactivation of the conditioned-air inlet valve (21HQ). If other messages are shown, refer to the related MMEL valve item. 5.

Close-up Subtask 21-26-00-410-094-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access door 824 (Ref. AMM TASK 52-41-00-410-002) . (3) Remove the access platform(s).

Subtask 21-26-00-942-091-A B.

Safety Precautions (1) Put a WARNING NOTICE(S) in position in the cockpit to tell the crew that the avionics ventilation filter and the conditioned-air inlet valve are deactivated. (2) Make an entry in the logbook.

Subtask 21-26-00-862-096-A C.

Aircraft Maintenance Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-28-00-040-002-A - Deactivation of the AftCargo-Compartment Ventilation Isolation-Valves

** ON A/C 201-201, 203-203, 206-208, 210-211, 222-222, 227-228, 231-232, 234-237, 240-250 TASK 21-28-00-040-002-A Deactivation of the Aft-Cargo-Compartment Ventilation Isolation-Valves

FIN : 33HN , 34HN Task Summary MMEL or CDL Ref MMEL 21-28-04B

Access YES

1.

Reason for the Job MMEL 21-28-04B AFT Cargo Isolation Valve

2

Job Set-up Information A.

Specific Tools NO

Mhr 00.5

E/T 00.5

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

Test YES

QTY 1 AR AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS 150 160

ZONE DESCRIPTION AFT CARGO COMPARTMENT FWD PRESS BULKHEAD TO AFT BULKHEAD OF AFT CARGO COMPARTMENT BULK CARGO COMPARTMENT AFT BULKHEAD OF AFT CARGO COMPARTMENT TO AFT BULKHEAD OF BULK CARGO COMPARTMENT AFT CAB U/FLOOR COMPT AFT BHD OF BULK

170 826 FOR 33HN (ISOL VALVE AFT CARGO OUTLET) 162DW FOR 34HN (ISOL VALVE AFT CARGO INLET) 151EW C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-28-00-040-002-A - Deactivation of the AftCargo-Compartment Ventilation Isolation-Valves REFERENCE (Ref. 24-41-00-862-002-A-02).

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 52-30-00-860-001-A). Open the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump (Ref. 52-30-00-860-002-A). Close the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump Cargo-Compartment Ventilation Isolation-Valves SHEET 1 FOR 33HN (ISOL VALVE AFT CARGO OUTLET) (Ref. 25-55-12-000-001-A). Removal of the Aft Cargo-Compartment Partition at FR65 (Ref. 25-55-12-400-001-A). Installation of the Aft Cargo-Compartment Partition at FR65 FOR 34HN (ISOL VALVE AFT CARGO INLET) (Ref. 25-55-11-000-003-A). Removal of the Sidewall Panels in the Aft Cargo-Compartment - FR47/ FR59 (Ref. 25-55-11-400-003-A). Installation of the Sidewall Panels in the Aft Cargo-Compartment FR47/FR59

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-28-00-040-002-A - Deactivation of the AftCargo-Compartment Ventilation Isolation-Valves

162DW 33HN EXAMPLE LOCATION

A AR826

FR66

A B 1

EXAMPLE 2

A 34HN FR52 151EW

3

B EXAMPLE OPEN

CLOSED

N_MM_212800_4_ACM0_01_00

Figure 21-28-00-991-00200-00-A / SHEET 1/1 - Cargo-Compartment Ventilation Isolation-Valves ** ON A/C 201-201, 203-203, 206-208, 210-211, 222-222, 227-228, 231-232, 234-237, 240-250 Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-28-00-040-002-A - Deactivation of the AftCargo-Compartment Ventilation Isolation-Valves

3.

Job Set-up Subtask 21-28-00-861-058-A A.

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

Subtask 21-28-00-865-085-A B.

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

DESIGNATION

** ON A/C 201-201, 207-207, 222-222 49VU AIR COND/AFT CARGO/VENT/CTL & MONG

FIN

31HN

LOCATION

C07

** ON A/C 203-203, 206-206, 208-208, 210-211, 227-228, 231-232, 234-237, 240-250 49VU AIR COND/AFT CARGO/VENT & HTG/ 31HN C07 CTL & MONG ** ON A/C 201-201, 203-203, 206-208, 210-211, 222-222, 227-228, 231-232, 234-237, 240-250 122VU AIR COND/AFT CARGO VENT/FAN 30HN S22 Subtask 21-28-00-010-055-A C.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) below the aft cargo-compartment door (door 826). (2) Open the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-001) . (3) FOR 33HN (ISOL VALVE AFT CARGO OUTLET) Remove access panel 162DW (Ref. AMM TASK 25-55-12-000-001) . (4) FOR 34HN (ISOL VALVE AFT CARGO INLET) Remove access panel 151EW (Ref. AMM TASK 25-55-11-000-003) .

4.

Procedure Subtask 21-28-00-040-053-A A.

Deactivation of the Aft-Cargo-Compartment Ventilation Isolation-Valves (Ref. Fig. Cargo-Compartment Ventilation Isolation-Valves SHEET 1) (1) On the isolation valves (2), move the manual override levers (1) to the closed position. (2) Disconnect the electrical connectors (3) (33HN-A and 34 HN-A) and safety them to the aircraft structure. (3) Put the CAP-BLANKING on each disconnected electrical connector and receptacle.

5.

Close-up Subtask 21-28-00-410-056-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) FOR 33HN (ISOL VALVE AFT CARGO OUTLET) Install access panel 162DW (Ref. AMM TASK 25-55-12-400-001) . (3) FOR 34HN (ISOL VALVE AFT CARGO INLET) Install access panel 151EW (Ref. AMM TASK 25-55-11-400-003) . (4) Make an entry in the aircraft log book to record the deactivation. (5) Close the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-002) .

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-28-00-040-002-A - Deactivation of the AftCargo-Compartment Ventilation Isolation-Valves

(6) Remove the access platform(s). Subtask 21-28-00-862-056-A B.

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

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-001-A - Verification Test (Safety Valves and Outflow Valve)

** ON A/C ALL TASK 21-31-00-040-001-A Verification Test (Safety Valves and Outflow Valve)

FIN : 6HL , 7HL , 10HL Task Summary MMEL or CDL Ref MMEL 21-31-03A

Access NO

Test NO

Specific Tools NO

Mhr 01.0

E/T 01.0

Nb Men 2

NOTE: For the test procedure two persons are required. One person must operate the safety valve, the other person must monitor the ECAM upper and lower display units and the panels 130VU and 131VU in the cockpit. 1.

Reason for the Job MMEL 21-31-03A Pressure Safety Valve

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 31-32-00-860-002-A). Procedure to Get Access to the SYSTEM REPORT/TEST/AIR COND Page (Ref. 31-60-00-860-001-A). EIS Start Procedure (Ref. 31-60-00-860-002-A). EIS Stop Procedure (Ref. 34-10-00-860-002-A). ADIRS Start Procedure (Ref. 34-10-00-860-005-A). ADIRS Stop Procedure Safety Valves - Verification Test SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-001-A - Verification Test (Safety Valves and Outflow Valve)

Z260

A

1

B

FR70

PAX DOOR 2

A

FR65 3

TYPICAL

D C REAR PRESSURE BULKHEAD

A

B FR70

POINT 'A'

TYPICAL 2

6HL 7HL

C D

2 POINT 'A'

A

C D TYPICAL

FWD

A A TYPICAL N_MM_213100_4_AAM0_01_01

Figure 21-31-00-991-00800-00-A / SHEET 1/1 - Safety Valves - Verification Test ** ON A/C ALL Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-001-A - Verification Test (Safety Valves and Outflow Valve)

3.

Job Set-up Subtask 21-31-00-861-059-A A.

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

Subtask 21-31-00-865-059-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 122VU 122VU

DESIGNATION AIR COND/CAB/PRESS/CTL1 AIR COND/CAB PRESS/CTL/MAN AIR COND/CAB PRESS/CTL/2

FIN 1HL 3HL 2HL

LOCATION D09 Y23 Y22

Subtask 21-31-00-865-074-A C.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-208, 212-218, 221-230, 236-236, 238-239, 241-242, 301-450, 500-600 122VU RPCU 4HL X23 ** ON A/C ALL Subtask 21-31-00-010-056-A D.

Get Access (1) Remove the food trolleys (1) and the trolley partition if installed. (2) Remove the panel (3).

** ON A/C 016-021, 201-201, 203-207, 209-211, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 Subtask 21-31-00-860-051-A E.

Aircraft Maintenance Configuration (1) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) . (2) On the ECAM control panel push the PRESS pushbutton switch, the CAB PRESS page comes into view on the lower ECAM display unit. (3) On one MCDU get the SYSTEM REPORT/TEST AIR COND menu page (Ref. AMM TASK 31-32-00860-002) . (4) On the AIR COND panel 30VU, make sure that: · the PACK 1 and the PACK 2 pushbutton switches are in the OFF position (the OFF legends are on). · the RAM AIR pushbutton switch is in the OFF position (the ON legend is off). (5) On the CABIN PRESS panel 25VU, make sure that: · the MODE SEL pushbutton switch is in the AUTO configuration (with the FAULT and MAN legends off). · the LDG ELEV selector is in the AUTO position. · the DITCHING pushbutton switch is in the AUTO configuration (with the ON legend off). (6) Do the ADIRS start procedure (Ref. AMM TASK 34-10-00-860-002) . (7) On the ADIRS CDU panel 20VU:

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-001-A - Verification Test (Safety Valves and Outflow Valve)

· make sure that the 3 OFF/NAV/ATT switches are in the NAV position and that the ADR 1, ADR 2 and ADR 3 pushbutton switches are in the on position (with the FAULT and OFF legends off). ** ON A/C 022-022, 024-100, 112-150, 208-208, 212-214, 223-225, 236-236, 238-238, 241-241, 301-349, 351450, 500-600 Subtask 21-31-00-860-051-B E.

Aircraft Maintenance Configuration (1) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) . (2) On the ECAM control panel push the PRESS pushbutton switch, the CAB PRESS page comes into view on the lower ECAM display unit. (3) On one MCDU get the SYSTEM REPORT/TEST AIR COND menu page (Ref. AMM TASK 31-32-00860-002) . (4) On the AIR COND panel 30VU, make sure that: · the PACK 1 and the PACK 2 pushbutton switches are in the OFF position (the OFF legends are on). · the RAM AIR pushbutton switch is in the OFF position (the ON legend is off). (5) On the CABIN PRESS panel 25VU, make sure that: · the MODE SEL pushbutton switch is in the AUTO configuration (with the FAULT and MAN legends off). · the LDG ELEV selector is in the AUTO position. · the DITCHING pushbutton switch is in the AUTO configuration (with the ON legend off). (6) Do the ADIRS start procedure (Ref. AMM TASK 34-10-00-860-002) . (7) On the ADIRS MSU panel 41VU: · make sure that the 3 OFF/NAV/ATT switches are in the NAV position and that the ADR 1, ADR 2 and ADR 3 pushbutton switches are in the on position (with the FAULT and OFF legends off).

** ON A/C ALL 4.

Procedure Subtask 21-31-00-710-064-A A.

Verification Test Part 1. (Ref. Fig. Safety Valves - Verification Test SHEET 1) (1) Operational Test of the Safety Valve Position Indicator NOTE: The test procedure is the same for the safety valves 6HL and 7HL.

ACTION RESULT 1.On one of the safety valves (2): On the ECAM lower display unit: · apply hand pressure at points A and push the · the green SAFETY indication changes to amber valve diaphragm until the spring is compressed and the valve symbol opens and changes to amand hold it for 1 minute. ber. On the panels 130VU and 131VU: · the amber light in the two MASTER CAUTION pushbutton switches come on. · the single audio warning is heard. On the ECAM upper display unit: · the warning message CAB PR SAFETY VALVE OPEN comes on. Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-001-A - Verification Test (Safety Valves and Outflow Valve)

ACTION · release the diaphragm.

RESULT On the ECAM lower display unit: · the open valve symbol closes and changes to green and the amber SAFETY indication changes to green. On the panels 130VU and 131VU: · the amber light in the two MASTER CAUTION pushbutton switches go off. On the ECAM upper display unit: · the warning message CAB PR SAFETY VALVE OPEN goes off.

NOTE: Do this test again for the other safety valve. NOTE: Make sure that one safety valve is operative. The inoperative safety valve must be in the closed position. (The ring gate must seat properly on the rubber seal.) Subtask 21-31-00-710-062-B B.

Verification Test Part 2. WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE OUTFLOW VALVES ARE CLEAR. MOVEMENT OF THE OUTFLOW VALVES CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE OUTFLOW VALVES ARE CLEAR. MOVEMENT OF THE OUTFLOW VALVES CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. (1) Operational Test of the Pressure Control and Monitoring ACTION 1.On the MCDU SYSTEM REPORT/TEST AIR COND menu page: · push the line key adjacent to the CPC 1 indication. 2.On the MCDU CAB PRESS CONT 1 menu page: · push the line key adjacent to the TEST/CALIBRATION indication.

3.On the CABIN PRESS panel 25VU: · set the LDG ELEV selector to 14000 FT.

4.On the MCDU CAB PRESS CONT 1 TEST/ CALIBRATION menu page:

RESULT On the MCDU: · the CAB PRESS CONT 1 page comes on.

On the MCDU: · the CAB PRESS CONT 1 TEST/CALIBRATION page comes on, · the message ECS PACKS ------------ OFF GROUND AIR SUPPLY ---- OFF LFES ----- SET TO 14000 FT ADIRS 1,2,3 ----------- ON MODE SEL ------------ AUTO comes on. On the ECAM upper display unit: · the green MAN LDG ELEV memo message comes on. On the ECAM lower display unit: · the green AUTO xxx FT indication changes to the green MAN 14000 FT indication. On the MCDU: · the message

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-001-A - Verification Test (Safety Valves and Outflow Valve)

ACTION · push the line key adjacent to CONTINUE.

RESULT IN PROGRESS (20...90S) comes on, then the message TEST OK RESET LFES - > AUTO comes on.

NOTE: Do the test again for CPC 2. NOTE: Make sure that the automatic cabin-pressure control-system and the three motors on the outflow valve are operative. Subtask 21-31-00-710-063-A C.

Verification Test Part 3. WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE OUTFLOW VALVES ARE CLEAR. MOVEMENT OF THE OUTFLOW VALVES CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE OUTFLOW VALVES ARE CLEAR. MOVEMENT OF THE OUTFLOW VALVES CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. (1) Operational Test of the Manual Pressure Control and Monitoring ACTION RESULT 1.On the CABIN PRESS panel 25VU: On the ECAM upper display unit: · move the LDG ELEV selector clockwise away · the green MAN LDG ELEV memo message from the AUTO position. comes on. On the ECAM lower display unit: · the green AUTO xxx FT indication changes to the green MAN xxx FT indication. NOTE: The actual manual altitude indication depends on the LDG ELEV selector position. 2.On the CABIN PRESS panel 25VU: · push and release the MODE SEL pushbutton switch.

On the CABIN PRESS panel 25VU: · the white MAN pushbutton switch light comes on. On the ECAM lower display unit: · the white LDG ELEV indication and the green MAN xxx FT indication goes off. · the green SYS 1 (or SYS 2) indication changes to the green MAN indication. · push and hold the MAN V/S CTL toggle switch · the outflow valve symbol closes. to DN. · push and hold the MAN V/S CTL toggle switch · the outflow valve symbol opens. to UP. · release the MAN V/S CTL toggle switch. · the outflow valve symbol stays open. 3.On the CABIN PRESS panel 25VU: On the CABIN PRESS panel 25VU: · push the MODE SEL pushbutton switch. · the white MAN pushbutton switch light goes off. On the ECAM lower display unit: · the white LDG ELEV indication and the green MAN xxx FT indication comes on. Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-001-A - Verification Test (Safety Valves and Outflow Valve)

ACTION

RESULT · the green MAN indication changes to the green SYS 1 (or SYS 2) indication. 4.On the CABIN PRESS panel 25VU: On the ECAM upper display unit: · move the LDG ELEV selector counterclockwise · the green MAN LDG ELEV memo message to the AUTO position. goes off. On the ECAM lower display unit: · the green MAN xxx FT indication changes to the green AUTO xxx FT indication.. 5.

Close-up Subtask 21-31-00-865-075-A A.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-208, 212-218, 221-230, 236-236, 238-239, 241-242, 301-450, 500-600 122VU RPCU 4HL X23 ** ON A/C 016-021, 201-201, 203-207, 209-211, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 Subtask 21-31-00-860-052-A B.

Aircraft Maintenance Configuration (1) On the CABIN PRESS panel 25VU, set the LDG ELEV selector to AUTO. (2) Do the ADIRS stop procedure (Ref. AMM TASK 34-10-00-860-005) . (3) On the ADIRS CDU panel 20VU, make sure that the 3 OFF/NAV/ATT switches are in the OFF position and that the ADR1, ADR2 and ADR3 pushbutton switches are pushed (OFF lights on). (4) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (5) On the MCDU, push the line select key adjacent to the RETURN indication until the CFDS menu page comes into view. (6) Make an entry in the aircraft technical log book to tell the flight crew that one safety valve is inoperative.

** ON A/C 022-022, 024-100, 112-150, 208-208, 212-214, 223-225, 236-236, 238-238, 241-241, 301-349, 351450, 500-600 Subtask 21-31-00-860-052-B B.

Aircraft Maintenance Configuration (1) On the CABIN PRESS panel 25VU, set the LDG ELEV selector to AUTO. (2) Do the ADIRS stop procedure (Ref. AMM TASK 34-10-00-860-005) . (3) On the ADIRS MSU panel 41VU, make sure that the 3 OFF/NAV/ATT switches are in the OFF position and that the ADR1, ADR2 and ADR3 pushbutton switches are pushed (OFF lights on). (4) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (5) On the MCDU, push the line select key adjacent to the RETURN indication until the CFDS menu page comes into view.

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-001-A - Verification Test (Safety Valves and Outflow Valve)

(6) Make an entry in the aircraft technical log book to tell the flight crew that one safety valve is inoperative. ** ON A/C ALL Subtask 21-31-00-410-054-A C.

Close Access (1) Install the access panel (3) and install the food trolleys (1).

Subtask 21-31-00-862-058-A D.

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

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-002-A - Verification Test of the Automatic Cabin-Pressure Control-Systems

** ON A/C ALL TASK 21-31-00-040-002-A Verification Test of the Automatic Cabin-Pressure Control-Systems Task Summary MMEL or CDL Ref MMEL 21-31-02A

Access NO

Test NO

Specific Tools NO

Mhr 00.5

E/T 00.5

1.

Reason for the Job MMEL 21-31-02A Manual Cabin Pressure Control System (MAN V/S CTL selector, Outflow Valve MAN Channel)

2

Job Set-up Information A.

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-32-00-860-002-A). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 34-10-00-860-002-A). (Ref. 34-10-00-860-005-A).

3.

Nb Men 1

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Procedure to Get Access to the SYSTEM REPORT/TEST/AIR COND Page EIS Start Procedure EIS Stop Procedure ADIRS Start Procedure ADIRS Stop Procedure

Job Set-up Subtask 21-31-00-865-062-A A.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 122VU 122VU

DESIGNATION AIR COND/CAB/PRESS/CTL1 AIR COND/CAB PRESS/CTL/MAN AIR COND/CAB PRESS/CTL/2

FIN 1HL 3HL 2HL

LOCATION D09 Y23 Y22

Subtask 21-31-00-860-063-A B.

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) .

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-002-A - Verification Test of the Automatic Cabin-Pressure Control-Systems

(3) On the ECAM control panel push the PRESS pushbutton switch, the CAB PRESS page comes into view on the lower ECAM display unit. (4) On one MCDU get the SYSTEM REPORT/TEST AIR COND menu page (Ref. AMM TASK 31-32-00860-002) . (5) On the AIR COND panel 30VU, make sure that: · the PACK 1 and the PACK 2 pushbutton switches are in the off position (the OFF legends are on), · the RAM AIR pushbutton switch is in the off position (the ON legend is off). (6) On the CABIN PRESS panel 25VU, make sure that: · the MODE SEL pushbutton switch is in the AUTO configuration (with the FAULT and MAN legends off), · the LDG ELEV selector is in the AUTO position, · the DITCHING pushbutton switch is in the AUTO configuration (with the ON legend off). (7) Do the ADIRS start procedure (Ref. AMM TASK 34-10-00-860-002) . 4.

Procedure Subtask 21-31-00-710-065-B WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE OUTFLOW VALVES ARE CLEAR. MOVEMENT OF THE OUTFLOW VALVES CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE OUTFLOW VALVES ARE CLEAR. MOVEMENT OF THE OUTFLOW VALVES CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

A.

Operational Test of the Pressure Control and Monitoring ACTION RESULT 1.On the MCDU SYSTEM REPORT/TEST AIR On the MCDU: COND menu page: · push the line key adjacent to the CPC 1 indica- · the CAB PRESS CONT 1 page comes on. tion. 2.On the MCDU CAB PRESS CONT 1 menu page: On the MCDU: · push the line key adjacent to the TEST/CALIBRATION indication. · the CAB PRESS CONT 1 TEST/CALIBRATION page comes on and shows: ECS PACKS ------------ OFF GROUND AIR SUPPLY ---- OFF LFES ----- SET TO 14000 FT ADIRS 1,2,3 ----------- ON MODE SEL ------------ AUTO comes on. 3.On the CABIN PRESS panel 25VU: On the ECAM upper display unit: · set the LDG ELEV selector to 14000 FT. · the green MAN LDG ELEV memo message comes on. On the ECAM lower display unit: · the green AUTO xxx FT indication changes to the green MAN 14000 FT indication. 4.On the MCDU CAB PRESS CONT 1 TEST/CAL- On the MCDU, the CAB PRESS CONT 1 TEST/CALIBRATION menu page: IBRATION menu page shows: · push the line key adjacent to CONTINUE. IN PROGRESS (20...90S) comes on, then the message TEST OK

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-002-A - Verification Test of the Automatic Cabin-Pressure Control-Systems ACTION

RESULT RESET LFES - > AUTO comes on. NOTE: Do the test again for CPC 2.

(1) Make sure that both automatic pressure control systems are operative. (2) Put a tag in the cockpit to tell the flight crew that the manual pressure control system is inoperative. (3) Make an entry in the aircraft technical logbook. 5.

Close-up Subtask 21-31-00-860-064-A A.

Aircraft Maintenance Configuration (1) On the CABIN PRESS panel 25VU, set the LDG ELEV selector to AUTO. (2) Do the ADIRS stop procedure (Ref. AMM TASK 34-10-00-860-005) . (3) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (4) On the MCDU, push the line select key adjacent to the RETURN indication until the CFDS menu page comes into view. (5) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-006-A - Deactivation of the CPC2

** ON A/C ALL TASK 21-31-00-040-006-A Deactivation of the CPC2 Task Summary MMEL or CDL Ref MMEL 21-31-01B

Access NO

Test NO

Specific Tools NO

Mhr 00.5

E/T 00.5

1.

Reason for the Job MMEL 21-31-01B Automatic Cabin Pressure Conrol System (CPC, Outflow Valve Auto Channel) (FAA only)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 34-10-00-860-002-A).

3.

Nb Men 1

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure ADIRS Start Procedure

Job Set-up Subtask 21-31-00-861-067-A A.

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

Subtask 21-31-00-865-070-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 122VU

DESIGNATION AIR COND/CAB PRESS/CTL/2

FIN 2HL

LOCATION Y22

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-208, 212-218, 221-230, 236-236, 238-239, 241-242, 301-450, 500-600 122VU RPCU 4HL X23

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-006-A - Deactivation of the CPC2

** ON A/C ALL Subtask 21-31-00-860-071-A C.

Aircraft Maintenance Configuration (1) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) . (2) On the ECAM control panel do the steps necessary to get the CAB PRESS page to show on the lower ECAM display unit. (3) On the AIR COND panel 30VU make sure that: · the PACK 1 and the PACK 2 pushbutton switches are in the off position (the OFF legends are on) and, · the RAM AIR pushbutton switch is in the off position (the ON legend is off). (4) Do the ADIRS start procedure (Ref. AMM TASK 34-10-00-860-002) .

4.

Procedure Subtask 21-31-00-710-067-A WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE OUTFLOW VALVES ARE CLEAR. MOVEMENT OF THE OUTFLOW VALVES CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE OUTFLOW VALVES ARE CLEAR. MOVEMENT OF THE OUTFLOW VALVES CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

A.

Verification Test of the Pressure Control and Monitoring Indications ACTION 1.On the overhead panel 25VU push the MODE SEL pushbutton switch to MAN.

2.On the overhead panel 25VU put the MAN V/S CTL switch to the DN position. 3.On the overhead panel 25VU put the MAN V/S CTL switch to the UP position. 4.On the overhead panel 25VU push the MODE SEL pushbutton switch to AUTO.

RESULT On the lower ECAM display make sure that: · the differential pressure, the cabin vertical speed, the cabin altitude indications and the outflow valve position show. On the lower ECAM display make sure that: · the outflow valve position indicator moves in a downwards direction. On the lower ECAM display make sure that: · the outflow valve position indicator moves in an upwards direction. On the lower ECAM display make sure that the outflow valve position indicator moves to the open position.

5.On the ECAM status page make sure that no FCU messages are shown. 5.

Close-up Subtask 21-31-00-865-078-A A.

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

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-006-A - Deactivation of the CPC2

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-208, 212-218, 221-230, 236-236, 238-239, 241-242, 301-450, 500-600 122VU RPCU 4HL X23 ** ON A/C ALL Subtask 21-31-00-862-063-A B.

Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (1) Put a temporary placard in the cockpit that tells persons that the automatic cabin pressure control system 2 is not in operation. (2) Make an entry in the aircraft technical log book to tell the crew that the cabin pressure control system 2 is not in operation. (3) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-007-A - Deactivation of the CPC1

** ON A/C ALL TASK 21-31-00-040-007-A Deactivation of the CPC1 Task Summary MMEL or CDL Ref MMEL 21-31-01A

Access NO

Test NO

Specific Tools NO

Mhr 00.5

E/T 00.5

1.

Reason for the Job MMEL 21-31-01A Automatic Cabin Pressure Conrol System (CPC, Outflow Valve Auto Channel) (FAA only)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 34-10-00-860-002-A).

3.

Nb Men 1

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure ADIRS Start Procedure

Job Set-up Subtask 21-31-00-861-069-A A.

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

Subtask 21-31-00-865-076-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/CAB/PRESS/CTL1

FIN 1HL

LOCATION D09

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-208, 212-218, 221-230, 236-236, 238-239, 241-242, 301-450, 500-600 122VU RPCU 4HL X23

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-007-A - Deactivation of the CPC1

** ON A/C ALL Subtask 21-31-00-860-073-A C.

Aircraft Maintenance Configuration (1) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) . (2) On the ECAM control panel do the steps necessary to get the CAB PRESS page to show on the lower ECAM display unit. (3) On the AIR COND panel 30VU make sure that: · the PACK 1 and the PACK 2 pushbutton switches are in the off position (the OFF legends are on) and, · the RAM AIR pushbutton switch is in the off position (the ON legend is off). (4) Do the ADIRS start procedure (Ref. AMM TASK 34-10-00-860-002) .

4.

Procedure Subtask 21-31-00-710-069-A WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE OUTFLOW VALVES ARE CLEAR. MOVEMENT OF THE OUTFLOW VALVES CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE OUTFLOW VALVES ARE CLEAR. MOVEMENT OF THE OUTFLOW VALVES CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

A.

Verification Test of the Pressure Control and Monitoring Indications ACTION 1.On the overhead panel 25VU push the MODE SEL pushbutton switch to MAN.

2.On the overhead panel 25VU put the MAN V/S CTL switch to the DN position. 3.On the overhead panel 25VU put the MAN V/S CTL switch to the UP position. 4.On the overhead panel 25VU push the MODE SEL pushbutton switch to AUTO.

RESULT On the lower ECAM display make sure that: · the differential pressure, the cabin vertical speed, the cabin altitude indications and the outflow valve position show. On the lower ECAM display make sure that: · the outflow valve position indicator moves in a downwards direction. On the lower ECAM display make sure that: · the outflow valve position indicator moves in an upwards direction. On the lower ECAM display make sure that the outflow valve position indicator moves to the open position.

5.On the ECAM status page make sure that no FCU messages are shown. 5.

Close-up Subtask 21-31-00-865-079-A A.

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

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-31-00-040-007-A - Deactivation of the CPC1

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-208, 212-218, 221-230, 236-236, 238-239, 241-242, 301-450, 500-600 122VU RPCU 4HL X23 ** ON A/C ALL Subtask 21-31-00-862-065-A B.

Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (1) Put a temporary placard in the cockpit that tells persons that the automatic cabin pressure control system 1 is not in operation. (2) Make an entry in the aircraft technical log book to tell the crew that the cabin pressure control system 1 is not in operation. (3) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-43-00-040-002-A - Deactivation of the AFT Cargo Compartment-Heating Trim-Air Valve

** ON A/C 203-203, 206-206, 208-208, 210-211, 227-228, 231-232, 234-237, 240-250 TASK 21-43-00-040-002-A Deactivation of the AFT Cargo Compartment-Heating Trim-Air Valve WARNING:

MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

FIN : 12HC Task Summary MMEL or CDL Ref MMEL 21-43-02B

Access YES

1.

Reason for the Job MMEL 21-43-02B AFT Cargo Compartment Heating

2

Job Set-up Information A.

Specific Tools NO

Mhr 00.7

E/T 00.7

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

Test NO

QTY 1 AR AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS 197 197BB

ZONE DESCRIPTION REAR FAIRING

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 53-35-13-000-002-A). (Ref. 53-35-13-400-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Removal of the Quick-Release Access Panels from the Belly Fairing Structure Installation of the Quick-Release Access Panels on the Belly Fairing Structure

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-43-00-040-002-A - Deactivation of the AFT Cargo Compartment-Heating Trim-Air Valve REFERENCE DESIGNATION AFT Cargo Compartment-Heating Trim-Air Valve SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-43-00-040-002-A - Deactivation of the AFT Cargo Compartment-Heating Trim-Air Valve

Z197 FR46

A 12HC

A

4

3 2 1

DIRECTION OF AIR FLOW

N_MM_214300_4_ACM0_01_00

Figure 21-43-00-991-00200-00-A / SHEET 1/1 - AFT Cargo Compartment-Heating Trim-Air Valve ** ON A/C 203-203, 206-206, 208-208, 210-211, 227-228, 231-232, 234-237, 240-250 Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-43-00-040-002-A - Deactivation of the AFT Cargo Compartment-Heating Trim-Air Valve

3.

Job Set-up Subtask 21-43-00-861-054-A A.

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

Subtask 21-43-00-865-055-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/AFT CARGO/VENT & HTG/ CTL & MONG

FIN 31HN

LOCATION C07

Subtask 21-43-00-941-053-A C.

Safety Precautions (1) On the panel 30VU: (a) Make sure that: · the APU BLEED pushbutton switch is in the off position (the ON legend is off) and, · the ENG 1 BLEED and the ENG 2 BLEED pushbutton switches are in the off position (the OFF legends are on). (b) Put a warning notice in position to tell persons not to operate these switches. (2) On the HP ground connector put a warning notice in position to tell persons not to supply the ground air.

Subtask 21-43-00-010-052-A D.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) in position at the access panel 197BB. (2) Remove the access panel 197BB (Ref. AMM TASK 53-35-13-000-002) .

4.

Procedure (Ref. Fig. AFT Cargo Compartment-Heating Trim-Air Valve SHEET 1) Subtask 21-43-00-040-051-C A.

Deactivation of the AFT Cargo Compartment-Heating Trim Air Valve WARNING: DO NOT TOUCH THE COMPONENT UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS. (1) Turn the manual override lever (2) to close the trim air valve. (2) Disconnect the electrical connector (1) and temporarily attach it to the aircraft structure. (3) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (4) Insert the quick-release pin (4) in the hole (3) in the manual override lever (2) to safety the trim air valve in the closed position. NOTE: When not in use the quick-release pin is stored in the hole in the body of the trim air valve. (5) Put a warning notice in the cockpit to tell the flight crew that the trim air valve is deactivated. (6) Record the deactivation of the trim air valve in the aircraft technical log book.

5.

Close-up Subtask 21-43-00-865-089-A

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-43-00-040-002-A - Deactivation of the AFT Cargo Compartment-Heating Trim-Air Valve

A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/AFT CARGO/VENT & HTG/ CTL & MONG

FIN 31HN

LOCATION C07

Subtask 21-43-00-410-052-A B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the access panel 197BB (Ref. AMM TASK 53-35-13-400-002) . (3) Remove the access platform(s). (4) Remove the WARNING NOTICE(S). NOTE: Do NOT remove the warning notice in the cockpit which tells the flight crew that the trim air valve is deactivated.

Subtask 21-43-00-862-052-A C.

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

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-43-00-040-003-A - Deactivation of the AFT Cargo Compartment-Heating Pressure-Regulating Valve

** ON A/C 203-203, 206-206, 208-208, 210-211, 227-228, 231-232, 234-237, 240-250 TASK 21-43-00-040-003-A Deactivation of the AFT Cargo Compartment-Heating Pressure-Regulating Valve WARNING:

MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

FIN : 11HC Task Summary MMEL or CDL Ref MMEL 21-43-02B

Access YES

1.

Reason for the Job MMEL 21-43-02B AFT Cargo Compartment Heating

2

Job Set-up Information A.

Specific Tools NO

Mhr 00.7

E/T 00.7

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

Test NO

QTY 1 AR AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS 197 197BB

ZONE DESCRIPTION REAR FAIRING

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 53-35-13-000-002-A). (Ref. 53-35-13-400-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Removal of the Quick-Release Access Panels from the Belly Fairing Structure Installation of the Quick-Release Access Panels on the Belly Fairing Structure

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-43-00-040-003-A - Deactivation of the AFT Cargo Compartment-Heating Pressure-Regulating Valve REFERENCE

DESIGNATION

** ON A/C 203-203, 206-206, 210-211, 234-235 AFT Cargo Compartment-Heating Pressure-Regulating Valve SHEET 1 ** ON A/C 208-208, 227-228, 231-232, 236-237, 240-250 AFT Cargo Compartment-Heating Pressure-Regulating Valve SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-43-00-040-003-A - Deactivation of the AFT Cargo Compartment-Heating Pressure-Regulating Valve

A

Z197 2

FR46 11HC

B

1

B

A

N_MM_214300_4_AAM0_01_00

Figure 21-43-00-991-00100-00-A / SHEET 1/1 - AFT Cargo Compartment-Heating Pressure-Regulating Valve ** ON A/C 203-203, 206-206, 210-211, 234-235 Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-43-00-040-003-A - Deactivation of the AFT Cargo Compartment-Heating Pressure-Regulating Valve

A

Z197 FR46 11HC 2

B B A 1

N_MM_214300_4_AAN0_01_00

Figure 21-43-00-991-00100-00-C / SHEET 1/1 - AFT Cargo Compartment-Heating Pressure-Regulating Valve ** ON A/C 208-208, 227-228, 231-232, 236-237, 240-250 | EMB SB 21-1191 for A/C 227-228, 231-232, 237-237, 240-240, 242-244 Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-43-00-040-003-A - Deactivation of the AFT Cargo Compartment-Heating Pressure-Regulating Valve

3.

Job Set-up Subtask 21-43-00-861-060-A A.

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

Subtask 21-43-00-865-061-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/AFT CARGO/VENT & HTG/ CTL & MONG

FIN 31HN

LOCATION C07

Subtask 21-43-00-941-059-A C.

Safety Precautions (1) On the panel 30VU: (a) Make sure that: · the APU BLEED pushbutton switch is in the off position (the ON legend is off) and, · the ENG 1 BLEED and the ENG 2 BLEED pushbutton switches are in the off position (the OFF legends are on). (b) Put a warning notice in position to tell persons not to operate these switches. (2) On the HP ground connector put a warning notice in position to tell persons not to supply the ground air.

Subtask 21-43-00-010-056-A D.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) in position at the access panel 197BB. (2) Remove the access panel 197BB (Ref. AMM TASK 53-35-13-000-002) .

4.

Procedure

** ON A/C 203-203, 206-206, 210-211, 234-235 (Ref. Fig. AFT Cargo Compartment-Heating Pressure-Regulating Valve SHEET 1) ** ON A/C 208-208, 227-228, 231-232, 236-237, 240-250 EMB SB 21-1191 for A/C 227-228, 231-232, 237-237, 240-240, 242-244 (Ref. Fig. AFT Cargo Compartment-Heating Pressure-Regulating Valve SHEET 1) ** ON A/C 203-203, 206-206, 208-208, 210-211, 227-228, 231-232, 234-237, 240-250 Subtask 21-43-00-040-052-A A.

Deactivation of the AFT Cargo Compartment-Heating Pressure Regulating Valve WARNING: DO NOT TOUCH THE COMPONENT UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS. (1) Turn the manual overide handwheel (2) to close the pressure regulating valve. (2) Engage the locking device on the manual overide handwheel (2) to safety the pressure regulating valve in the closed position. (3) Disconnect the electrical connector (1) and temporarily attach it to the aircraft structure. (4) Put the CAP-BLANKING on each disconnected electrical connector and receptacle.

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-43-00-040-003-A - Deactivation of the AFT Cargo Compartment-Heating Pressure-Regulating Valve

5.

Close-up Subtask 21-43-00-865-090-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/AFT CARGO/VENT & HTG/ CTL & MONG

FIN 31HN

LOCATION C07

Subtask 21-43-00-410-055-A B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the access panel 197BB (Ref. AMM TASK 53-35-13-400-002) . (3) Remove the access platform(s). (4) Remove the WARNING NOTICE(S). (5) Put a warning notice in the cockpit to tell the flight crew that the pressure regulating valve is deactivated. (6) Record the deactivation of the pressure regulating valve in the aircraft technical log book.

Subtask 21-43-00-862-057-A C.

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

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-001-A - Deactivation of the Pack Flow-Control Valve

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 TASK 21-51-00-040-001-A Deactivation of the Pack Flow-Control Valve WARNING:

MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

FIN : 8HB , 11HB Task Summary MMEL or CDL Ref MMEL 21-51-01A

Access YES

Test YES

Specific Tools NO

Mhr 00.5

E/T 00.5

Nb Men 1

NOTE: The procedure is the same for the pack flow-control valve 8HB and 11HB. 1.

Reason for the Job MMEL 21-51-01A Pack Flow Control Valve

2

Job Set-up Information A.

Consumable Materials REFERENCE (Material No. 14QFB1)

B.

DESIGNATION Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -

Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTION FOR 11HB (P1 FLOW CTL VALVE) 191KB FOR 8HB (P2 FLOW CTL VALVE) 192KB

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-001-A - Deactivation of the Pack Flow-Control Valve

REFERENCE (Ref. 53-35-13-000-002-A).

DESIGNATION Removal of the Quick-Release Access Panels from the Belly Fairing Structure (Ref. 53-35-13-400-002-A). Installation of the Quick-Release Access Panels on the Belly Fairing Structure Pack Flow Control Valve - Component Location SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-001-A - Deactivation of the Pack Flow-Control Valve

11HB

FR36

8HB FR41

A

A

191KB

192KB

B A

A OPEN

SHUT

2

B

4

3

1

2

B

B

N_MM_215100_4_AAQ0_01_00

Figure 21-51-00-991-00100-00-E / SHEET 1/1 - Pack Flow Control Valve - Component Location ** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-001-A - Deactivation of the Pack Flow-Control Valve

3.

Job Set-up Subtask 21-51-00-861-050-A A.

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

Subtask 21-51-00-010-051-A B.

Get Access (1) Remove the access panel (Ref. AMM TASK 53-35-13-000-002) : (a) FOR 8HB (P2 FLOW CTL VALVE) · 192KB, (b) FOR 11HB (P1 FLOW CTL VALVE) · 191KB.

Subtask 21-51-00-941-051-A C.

Safety Precautions (1) On the panel 30VU: (a) Make sure that: · the APU BLEED pushbutton switch is in the off position (the ON legend is off) and, · the ENG 1 BLEED and the ENG 2 BLEED pushbutton switches are in the off position (the OFF legends are on). (b) Put a warning notice in position to tell persons not to operate these switches. (2) On the HP ground connector put a warning notice in position to tell persons not to supply the ground air.

4.

Procedure Subtask 21-51-00-040-050-B A.

Deactivation of the Pack Flow-Control Valve (Ref. Fig. Pack Flow Control Valve - Component Location SHEET 1) WARNING: DO NOT TOUCH THE COMPONENT UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS. (1) FOR 11HB (P1 FLOW CTL VALVE) (a) Push the PACK 1 pushbutton switch to the off position (the OFF legend comes on). (2) FOR 8HB (P2 FLOW CTL VALVE) (a) Push the PACK 2 pushbutton switch to the off position (the OFF legend comes on). (3) Remove and discard the lockwire from the special screw (1). (4) Remove the special screw (1) from the position (A). (5) Disconnect the quick release connector (3). NOTE: This will open the pack flow-control valve and close the butterfly valve. (6) Make sure that the valve indicator (2) is in the closed position. 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.

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-001-A - Deactivation of the Pack Flow-Control Valve

(7) Install the special screw (1) in the position (B) and safety with dia. Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - (Material No. 14QFB1). (8) Connect the quick release connector (3) to the connection (4). 5.

Close-up Subtask 21-51-00-410-050-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the access panel (Ref. AMM TASK 53-35-13-400-002) : (a) FOR 8HB (P2 FLOW CTL VALVE) · 192KB, (b) FOR 11HB (P1 FLOW CTL VALVE) · 191KB. (3) Remove the WARNING NOTICE(S). (4) Record the deactivation of the pack flow-control valve in the aircraft technical log book.

Subtask 21-51-00-862-050-A B.

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

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-002-A - Deactivation of the Air Conditioning Pack

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 301450, 500-600 TASK 21-51-00-040-002-A Deactivation of the Air Conditioning Pack WARNING:

MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

FIN : 10HM , 11HM Task Summary MMEL or CDL Ref MMEL 21-52-01D MMEL 21-52-01E MMEL 21-52-01F

Access YES YES YES

Test NO NO NO

Specific Tools NO NO NO

Mhr 01.0 01.0 01.0

E/T 01.0 01.0 01.0

Nb Men 2 2 2

NOTE: The procedure is the same for the two air conditioning packs 10HM (11HM). 1.

Reason for the Job MMEL 21-52-01D Air Conditioning Pack MMEL 21-52-01E Air Conditioning Pack MMEL 21-52-01F Air Conditioning Pack

2

Job Set-up Information A.

Consumable Materials REFERENCE (Material No. 14QFB1)

B.

DESIGNATION Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -

Work Zones and Access Panels ZONE/ACCESS 191KB, 192KB

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-002-A - Deactivation of the Air Conditioning Pack

REFERENCE (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 53-35-13-000-002-A). Removal of the Quick-Release Access Panels from the Belly Fairing Structure (Ref. 53-35-13-400-002-A). Installation of the Quick-Release Access Panels on the Belly Fairing Structure Pack FlowControl Unit - Component Location SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-002-A - Deactivation of the Air Conditioning Pack

FR36

A FR41

191BB (192FB)

191KB (192KB)

A LH SHOWN RH SIMILAR

2

B

1 A

N_MM_215100_4_BAM0_01_00

Figure 21-51-00-991-00600-00-A / SHEET 1/1 - Pack FlowControl Unit - Component Location ** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212218, 221-230, 235-236, 238-239, 241-242, 301-450, 500-600 Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-002-A - Deactivation of the Air Conditioning Pack

3.

Job Set-up Subtask 21-51-00-861-058-A A.

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

Subtask 21-51-00-010-058-A B.

Get Access (1) Remove the access panel (Ref. AMM TASK 53-35-13-000-002) : (a) For PACK 1 · 191KB. (b) For PACK 2 · 192KB.

Subtask 21-51-00-941-057-A C.

Safety Precautions (1) On the panel 30VU: (a) Make sure that: · The APU BLEED pushbutton switch is in the OFF position (the ON legend is off). · The ENG 1 BLEED and the ENG 2 BLEED pushbutton switches are in the OFF position (the OFF legends are on). (b) Put a warning notice in position to tell persons not to operate these switches. (2) On the HP ground connector put a warning notice in position to tell persons not to supply the ground air.

Subtask 21-51-00-860-061-A D.

ECAM Warning Check before Deactivation (1) On the Upper ECAM E/WD make sure that the display unit does not show these warnings associated with the operative pack: · AIR PACK 1 REGUL FAULT or AIR PACK 2 REGUL FAULT · AIR COND CTL 1-A FAULT or AIR COND CTL 2-A FAULT · AIR COND CTL 1-B FAULT or AIR COND CTL 2-B FAULT.

4.

Procedure (Ref. Fig. Pack FlowControl Unit - Component Location SHEET 1) Subtask 21-51-00-040-052-A A.

Deactivation of the Air Conditioning Pack WARNING: DO NOT TOUCH THE COMPONENT UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS. 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. (1) For PACK 1 (a) Push the PACK 1 pushbutton switch to the OFF position (the OFF legend comes on). (2) For PACK 2 (a) Push the PACK 2 pushbutton switch to the OFF position (the OFF legend comes on).

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-002-A - Deactivation of the Air Conditioning Pack

(3) On the related flow control unit 23HB (24HB): (a) Remove and discard the lockwire from the blanking cap (1). (b) Remove the blanking cap (1) from the position A. NOTE: This will cause the air to flow out of the pack flow-control unit and close the butterfly valve. (c) Make sure that the forked valve-position indicator lever (2) is in the CLOSED position. (d) Install the blanking cap (1) between the forks of the valve-position indicator lever (2) and on the threaded boss (position B). 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. (e) Safety the blanking cap (1) with Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - (Material No. 14QFB1). 5.

Close-up Subtask 21-51-00-410-058-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the access panel (Ref. AMM TASK 53-35-13-400-002) : (a) For PACK 1 · 191KB. (b) For PACK 2 · 192KB. (3) Remove the WARNING NOTICE(S). (4) Put a temporary placard in the cockpit that tells persons that one air conditioning pack is not in operation. (5) Record the deactivation of the air conditioning pack in the aircraft technical log book.

Subtask 21-51-00-862-057-A B.

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

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-002-A - Deactivation of the Air Conditioning Pack

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 301450, 500-600 TASK 21-51-00-040-002-A Deactivation of the Air Conditioning Pack WARNING:

MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

FIN : 10HM , 11HM Task Summary MMEL or CDL Ref MMEL 21-52-01D MMEL 21-52-01E MMEL 21-52-01F

Access YES YES YES

Test NO NO NO

Specific Tools NO NO NO

Mhr 01.0 01.0 01.0

E/T 01.0 01.0 01.0

Nb Men 2 2 2

NOTE: The procedure is the same for the two air conditioning packs 10HM (11HM). 1.

Reason for the Job MMEL 21-52-01D Air Conditioning Pack MMEL 21-52-01E Air Conditioning Pack MMEL 21-52-01F Air Conditioning Pack

2

Job Set-up Information A.

Consumable Materials REFERENCE (Material No. 14QFB1)

B.

DESIGNATION Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -

Work Zones and Access Panels ZONE/ACCESS 191KB, 192KB

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-002-A - Deactivation of the Air Conditioning Pack

REFERENCE (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 53-35-13-000-002-A). Removal of the Quick-Release Access Panels from the Belly Fairing Structure (Ref. 53-35-13-400-002-A). Installation of the Quick-Release Access Panels on the Belly Fairing Structure Pack FlowControl Unit - Component Location SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-002-A - Deactivation of the Air Conditioning Pack

FR36

A FR41

191BB (192FB)

191KB (192KB)

A LH SHOWN RH SIMILAR

2

B

1 A

N_MM_215100_4_BAM0_01_00

Figure 21-51-00-991-00600-00-A / SHEET 1/1 - Pack FlowControl Unit - Component Location ** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212218, 221-230, 235-236, 238-239, 241-242, 301-450, 500-600 Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-002-A - Deactivation of the Air Conditioning Pack

3.

Job Set-up Subtask 21-51-00-861-058-A A.

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

Subtask 21-51-00-010-058-A B.

Get Access (1) Remove the access panel (Ref. AMM TASK 53-35-13-000-002) : (a) For PACK 1 · 191KB. (b) For PACK 2 · 192KB.

Subtask 21-51-00-941-057-A C.

Safety Precautions (1) On the panel 30VU: (a) Make sure that: · The APU BLEED pushbutton switch is in the OFF position (the ON legend is off). · The ENG 1 BLEED and the ENG 2 BLEED pushbutton switches are in the OFF position (the OFF legends are on). (b) Put a warning notice in position to tell persons not to operate these switches. (2) On the HP ground connector put a warning notice in position to tell persons not to supply the ground air.

Subtask 21-51-00-860-061-A D.

ECAM Warning Check before Deactivation (1) On the Upper ECAM E/WD make sure that the display unit does not show these warnings associated with the operative pack: · AIR PACK 1 REGUL FAULT or AIR PACK 2 REGUL FAULT · AIR COND CTL 1-A FAULT or AIR COND CTL 2-A FAULT · AIR COND CTL 1-B FAULT or AIR COND CTL 2-B FAULT.

4.

Procedure (Ref. Fig. Pack FlowControl Unit - Component Location SHEET 1) Subtask 21-51-00-040-052-A A.

Deactivation of the Air Conditioning Pack WARNING: DO NOT TOUCH THE COMPONENT UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS. 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. (1) For PACK 1 (a) Push the PACK 1 pushbutton switch to the OFF position (the OFF legend comes on). (2) For PACK 2 (a) Push the PACK 2 pushbutton switch to the OFF position (the OFF legend comes on).

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-002-A - Deactivation of the Air Conditioning Pack

(3) On the related flow control unit 23HB (24HB): (a) Remove and discard the lockwire from the blanking cap (1). (b) Remove the blanking cap (1) from the position A. NOTE: This will cause the air to flow out of the pack flow-control unit and close the butterfly valve. (c) Make sure that the forked valve-position indicator lever (2) is in the CLOSED position. (d) Install the blanking cap (1) between the forks of the valve-position indicator lever (2) and on the threaded boss (position B). 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. (e) Safety the blanking cap (1) with Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - (Material No. 14QFB1). 5.

Close-up Subtask 21-51-00-410-058-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the access panel (Ref. AMM TASK 53-35-13-400-002) : (a) For PACK 1 · 191KB. (b) For PACK 2 · 192KB. (3) Remove the WARNING NOTICE(S). (4) Put a temporary placard in the cockpit that tells persons that one air conditioning pack is not in operation. (5) Record the deactivation of the air conditioning pack in the aircraft technical log book.

Subtask 21-51-00-862-057-A B.

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

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-002-A - Deactivation of the Air Conditioning Pack

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 301450, 500-600 TASK 21-51-00-040-002-A Deactivation of the Air Conditioning Pack WARNING:

MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

FIN : 10HM , 11HM Task Summary MMEL or CDL Ref MMEL 21-52-01D MMEL 21-52-01E MMEL 21-52-01F

Access YES YES YES

Test NO NO NO

Specific Tools NO NO NO

Mhr 01.0 01.0 01.0

E/T 01.0 01.0 01.0

Nb Men 2 2 2

NOTE: The procedure is the same for the two air conditioning packs 10HM (11HM). 1.

Reason for the Job MMEL 21-52-01D Air Conditioning Pack MMEL 21-52-01E Air Conditioning Pack MMEL 21-52-01F Air Conditioning Pack

2

Job Set-up Information A.

Consumable Materials REFERENCE (Material No. 14QFB1)

B.

DESIGNATION Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -

Work Zones and Access Panels ZONE/ACCESS 191KB, 192KB

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-002-A - Deactivation of the Air Conditioning Pack

REFERENCE (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 53-35-13-000-002-A). Removal of the Quick-Release Access Panels from the Belly Fairing Structure (Ref. 53-35-13-400-002-A). Installation of the Quick-Release Access Panels on the Belly Fairing Structure Pack FlowControl Unit - Component Location SHEET 1

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-002-A - Deactivation of the Air Conditioning Pack

FR36

A FR41

191BB (192FB)

191KB (192KB)

A LH SHOWN RH SIMILAR

2

B

1 A

N_MM_215100_4_BAM0_01_00

Figure 21-51-00-991-00600-00-A / SHEET 1/1 - Pack FlowControl Unit - Component Location ** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212218, 221-230, 235-236, 238-239, 241-242, 301-450, 500-600 Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-002-A - Deactivation of the Air Conditioning Pack

3.

Job Set-up Subtask 21-51-00-861-058-A A.

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

Subtask 21-51-00-010-058-A B.

Get Access (1) Remove the access panel (Ref. AMM TASK 53-35-13-000-002) : (a) For PACK 1 · 191KB. (b) For PACK 2 · 192KB.

Subtask 21-51-00-941-057-A C.

Safety Precautions (1) On the panel 30VU: (a) Make sure that: · The APU BLEED pushbutton switch is in the OFF position (the ON legend is off). · The ENG 1 BLEED and the ENG 2 BLEED pushbutton switches are in the OFF position (the OFF legends are on). (b) Put a warning notice in position to tell persons not to operate these switches. (2) On the HP ground connector put a warning notice in position to tell persons not to supply the ground air.

Subtask 21-51-00-860-061-A D.

ECAM Warning Check before Deactivation (1) On the Upper ECAM E/WD make sure that the display unit does not show these warnings associated with the operative pack: · AIR PACK 1 REGUL FAULT or AIR PACK 2 REGUL FAULT · AIR COND CTL 1-A FAULT or AIR COND CTL 2-A FAULT · AIR COND CTL 1-B FAULT or AIR COND CTL 2-B FAULT.

4.

Procedure (Ref. Fig. Pack FlowControl Unit - Component Location SHEET 1) Subtask 21-51-00-040-052-A A.

Deactivation of the Air Conditioning Pack WARNING: DO NOT TOUCH THE COMPONENT UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS. 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. (1) For PACK 1 (a) Push the PACK 1 pushbutton switch to the OFF position (the OFF legend comes on). (2) For PACK 2 (a) Push the PACK 2 pushbutton switch to the OFF position (the OFF legend comes on).

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-51-00-040-002-A - Deactivation of the Air Conditioning Pack

(3) On the related flow control unit 23HB (24HB): (a) Remove and discard the lockwire from the blanking cap (1). (b) Remove the blanking cap (1) from the position A. NOTE: This will cause the air to flow out of the pack flow-control unit and close the butterfly valve. (c) Make sure that the forked valve-position indicator lever (2) is in the CLOSED position. (d) Install the blanking cap (1) between the forks of the valve-position indicator lever (2) and on the threaded boss (position B). 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. (e) Safety the blanking cap (1) with Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - (Material No. 14QFB1). 5.

Close-up Subtask 21-51-00-410-058-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the access panel (Ref. AMM TASK 53-35-13-400-002) : (a) For PACK 1 · 191KB. (b) For PACK 2 · 192KB. (3) Remove the WARNING NOTICE(S). (4) Put a temporary placard in the cockpit that tells persons that one air conditioning pack is not in operation. (5) Record the deactivation of the air conditioning pack in the aircraft technical log book.

Subtask 21-51-00-862-057-A B.

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

End of document

Print Date: August 23, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-55-00-040-002-A - Deactivation of the Emergency Ram-Air Inlet in closed Position

** ON A/C ALL TASK 21-55-00-040-002-A Deactivation of the Emergency Ram-Air Inlet in closed Position

FIN : 7HZ 1.

Reason for the Job MMEL 21-55-01A Emergency Ram Air Inlet

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

QTY 1 2 AR

DESIGNATION ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE CAP - BLANKING, PLASTIC SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS 191BB

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 12-33-21-618-001-A-01). (Ref. 12-33-21-618-001-A-02). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Pre-conditioning through the HP Ground Connection Pre-conditioning with the APU Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 53-35-13-000-002-A). Removal of the Quick-Release Access Panels from the Belly Fairing Structure (Ref. 53-35-13-400-002-A). Installation of the Quick-Release Access Panels on the Belly Fairing Structure Emergency Ram Air-Inlet Actuator - Component Location SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-55-00-040-002-A - Deactivation of the Emergency Ram-Air Inlet in closed Position

FR34 FR36

A

191BB

A 7HZ

B B 3

FR34

7HZ ACTUATOR FR33

2

1

N_MM_215500_4_AAM0_01_00

Figure 21-55-00-991-00100-00-A / SHEET 1/1 - Emergency Ram Air-Inlet Actuator - Component Location ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-55-00-040-002-A - Deactivation of the Emergency Ram-Air Inlet in closed Position

3.

Job Set-up Subtask 21-55-00-861-053-A A.

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

Subtask 21-55-00-865-053-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU

DESIGNATION AIR COND/RAM/AIR/INLET

FIN 1HZ

LOCATION D10

Subtask 21-55-00-010-050-A C.

Get Access (1) Remove the access panel (Ref. AMM TASK 53-35-13-000-002) : · 191BB. (2) Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position below the access to the emergency ram-air inlet actuator (7HZ).

4.

Procedure (Ref. Fig. Emergency Ram Air-Inlet Actuator - Component Location SHEET 1) Subtask 21-55-00-040-051-A A.

Deactivation of the Emergency Ram-Air Inlet Actuator (1) Make sure the emergency ram-air inlet is closed. (2) Disconnect the electrical connector (1) of the emergency ram-air inlet actuator (2). (3) Put CAP - BLANKING, PLASTIC on the disconnected connectors. (4) Temporarily attach the electrical connector (1) to the aircraft structure.

Subtask 21-55-00-710-053-A B.

Test (1) Do the pre-conditioning with the APU (Ref. AMM TASK 12-33-21-618-001) or through the HP ground connection (Ref. AMM TASK 12-33-21-618-001) . (2) On the AIR BLEED page of the lower ECAM DU, make sure that the pack discharge-temperature indications for the two packs are normal (i.e. green indication). (3) On the upper ECAM DU, make sure there is no fault shown for the two packs. (4) Stop the pre-conditioning with the APU (Ref. AMM TASK 12-33-21-618-001) or through the HP ground connection (Ref. AMM TASK 12-33-21-618-001) .

5.

Close-up Subtask 21-55-00-410-050-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the access panel (Ref. AMM TASK 53-35-13-400-002) : · 191BB. (3) Remove the access platform(s). (4) Make an entry in the aircraft log book to record the deactivation.

Subtask 21-55-00-862-053-A B.

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

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-55-00-040-002-A - Deactivation of the Emergency Ram-Air Inlet in closed Position

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-61-00-040-002-A - Deactivation of the Air Inlet Flap in the Open Position

** ON A/C ALL TASK 21-61-00-040-002-A Deactivation of the Air Inlet Flap in the Open Position WARNING:

MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

FIN : 8HH , 28HH Task Summary MMEL or CDL Ref MMEL 21-52-02A

Access YES

Test YES

Specific Tools NO

Mhr 01.0

E/T 01.0

Nb Men 1

NOTE: The procedure is the same for the Left and the Right air inlet flaps. 1.

Reason for the Job MMEL 21-52-02A Air Conditioning Pack Ram Air Inlet Flap

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION AR CAP - BLANKING AR SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTION FOR 28HH (P2 RAM AIR IN ACTUATOR) 192KB FOR 8HH (P1 RAM AIR IN ACTUATOR) 191KB

C. Referenced Information REFERENCE (Ref. 21-61-51-000-001-A). (Ref. 21-61-51-820-001-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01).

DESIGNATION Removal of the Air-Inlet Flap Actuator Adjustment of the Air Inlet Flap Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-61-00-040-002-A - Deactivation of the Air Inlet Flap in the Open Position

REFERENCE (Ref. 24-41-00-862-002-A-02).

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 53-35-13-000-002-A). Removal of the Quick-Release Access Panels from the Belly Fairing Structure (Ref. 53-35-13-400-002-A). Installation of the Quick-Release Access Panels on the Belly Fairing Structure Air Inlet Gap Measurement SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-61-00-040-002-A - Deactivation of the Air Inlet Flap in the Open Position

FR41

A A

AIR INLET GAP

N_MM_216100_4_AEM0_01_00

Figure 21-61-00-991-00400-00-A / SHEET 1/1 - Air Inlet Gap Measurement ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-61-00-040-002-A - Deactivation of the Air Inlet Flap in the Open Position

3.

Job Set-up Subtask 21-61-00-861-053-A A.

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

Subtask 21-61-00-865-053-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 8HH (P1 RAM AIR IN ACTUATOR)

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 301-450, 500-600 49VU AIR COND/TEMP CTL/SYS 1 CHAN B/ 52HH D08 28VDC 122VU AIR COND/TEMP CTL SYS 1/CHAN A/ 49HH X22 115VAC 122VU AIR COND/TEMP CTL SYS 1/CHAN A/ 51HH X21 28VDC 122VU AIR COND/TEMP CTL SYS 1/CHAN B/ 50HH Y18 115VAC ** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 122VU AIR COND/PACK TEMP/CTL SYS1/1/ 1HH X22 115VAC 122VU AIR COND/PACK TEMP/CTL SYS1/1/ 3HH X21 28VDC 122VU AIR COND/PACK TEMP CTL SYS2/1/ 4HH Y19 28VDC 122VU AIR COND/PACK TEMP CTL SYS2/1/ 2HH Y18 115VAC ** ON A/C ALL FOR FIN 28HH (P2 RAM AIR IN ACTUATOR) ** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 301-450, 500-600 122VU AIR COND/TEMP CTL SYS 2/CHAN A/ 53HH W22 115VAC 122VU AIR COND/TEMP CTL SYS 2/CHAN A/ 55HH W21 28VDC 122VU AIR COND/TEMP CTL SYS 2/CHAN B/ 56HH Y21 28VDC 122VU AIR COND/TEMP CTL SYS 2/CHAN B/ 54HH Y20 115VAC ** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 122VU AIR COND/PACK TEMP/CTL SYS1/2/ 21HH W22 115VAC 122VU AIR COND/PACK TEMP/CTL SYS1/2/ 23HH W21 28VDC 122VU AIR COND/PACK TEMP CTL SYS2/2/ 24HH Y21 28VDC Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-61-00-040-002-A - Deactivation of the Air Inlet Flap in the Open Position

PANEL 122VU

DESIGNATION AIR COND/PACK TEMP CTL SYS2/2/ 115VAC

FIN 22HH

LOCATION Y20

** ON A/C ALL Subtask 21-61-00-220-050-B C.

Inspection of the Air Inlet Flap before Deactivation (1) Measure the air inlet gap. (Ref. Fig. Air Inlet Gap Measurement SHEET 1) NOTE: Do not apply pressure to the air inlet flap when you do the measurement. (a) If the air inlet gap is 40 mm (1.5748 in.) or over then the air inlet is considered open. (b) Make sure that the Air Inlet Flap is correctly adjusted (Ref. AMM TASK 21-61-51-820-001) .

Subtask 21-61-00-010-057-C D.

Get Access (1) Remove the access panel (Ref. AMM TASK 53-35-13-000-002) . (a) FOR 8HH (P1 RAM AIR IN ACTUATOR) · 191KB. (b) FOR 28HH (P2 RAM AIR IN ACTUATOR) · 192KB.

4.

Procedure Subtask 21-61-00-040-050-A A.

Deactivation of the Air Inlet Flap (1) Disconnect the electrical connector from the air inlet flap actuator 8HH (28HH) (Ref. AMM TASK 2161-51-000-001) . (2) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (3) Temporarily attach the loose electrical connector to the aircraft structure. (4) Put a warning notice in position in the cockpit to tell the flight crew that one air inlet flap is inoperative.

5.

Close-up Subtask 21-61-00-865-063-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 8HH (P1 RAM AIR IN ACTUATOR)

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 301-450, 500-600 49VU AIR COND/TEMP CTL/SYS 1 CHAN B/ 52HH D08 28VDC 122VU AIR COND/TEMP CTL SYS 1/CHAN A/ 49HH X22 115VAC 122VU AIR COND/TEMP CTL SYS 1/CHAN A/ 51HH X21 28VDC 122VU AIR COND/TEMP CTL SYS 1/CHAN B/ 50HH Y18 115VAC Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-61-00-040-002-A - Deactivation of the Air Inlet Flap in the Open Position

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 122VU AIR COND/PACK TEMP/CTL SYS1/1/ 1HH X22 115VAC 122VU AIR COND/PACK TEMP/CTL SYS1/1/ 3HH X21 28VDC 122VU AIR COND/PACK TEMP CTL SYS2/1/ 4HH Y19 28VDC 122VU AIR COND/PACK TEMP CTL SYS2/1/ 2HH Y18 115VAC ** ON A/C ALL FOR FIN 28HH (P2 RAM AIR IN ACTUATOR) ** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 301-450, 500-600 122VU AIR COND/TEMP CTL SYS 2/CHAN A/ 53HH W22 115VAC 122VU AIR COND/TEMP CTL SYS 2/CHAN A/ 55HH W21 28VDC 122VU AIR COND/TEMP CTL SYS 2/CHAN B/ 56HH Y21 28VDC 122VU AIR COND/TEMP CTL SYS 2/CHAN B/ 54HH Y20 115VAC ** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 122VU AIR COND/PACK TEMP/CTL SYS1/2/ 21HH W22 115VAC 122VU AIR COND/PACK TEMP/CTL SYS1/2/ 23HH W21 28VDC 122VU AIR COND/PACK TEMP CTL SYS2/2/ 24HH Y21 28VDC 122VU AIR COND/PACK TEMP CTL SYS2/2/ 22HH Y20 115VAC ** ON A/C ALL Subtask 21-61-00-869-053-A B.

Cockpit Effects (1) On the upper ECAM DU the message AIR PACK 1 (PACK 2) REGUL FAULT will be displayed.

Subtask 21-61-00-410-056-C C.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access panel/s (Ref. AMM TASK 53-35-13-400-002) . (a) FOR 8HH (P1 RAM AIR IN ACTUATOR) · 191KB. (b) FOR 28HH (P2 RAM AIR IN ACTUATOR) · 192KB. (3) Make an entry in the log book to record the deactivation.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-61-00-040-002-A - Deactivation of the Air Inlet Flap in the Open Position

Subtask 21-61-00-862-052-A D.

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

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-63-00-040-001-A - Deactivation of the Trim Air Valve

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 TASK 21-63-00-040-001-A Deactivation of the Trim Air Valve WARNING:

MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

WARNING:

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

FIN : 11HK , 12HK , 13HK Task Summary MMEL or CDL Ref MMEL 21-63-02D

Access YES

1.

Reason for the Job MMEL 21-63-02D Cockpit and Cabin Trim Air Valve

2

Job Set-up Information A.

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

Test YES

QTY 1 AR AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER

Consumable Materials REFERENCE No specific

DESIGNATION lockwire-corrosion resistant steel 0.8 mm (0.0314 in.)

C. Work Zones and Access Panels ZONE/ACCESS 825

ZONE DESCRIPTION

D. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-63-00-040-001-A - Deactivation of the Trim Air Valve

REFERENCE (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 25-54-12-000-001-A). Removal of the Forward Cargo-Compartment Partition FR34 or FR35.5 (Ref. 25-54-12-400-001-A). Installation of the Forward Cargo-Compartment Partition FR34 or FR35.5 (Ref. 52-30-00-860-001-A). Open the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump (Ref. 52-30-00-860-002-A). Close the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump (Ref. 06-41-53-00). FUSELAGE - DESCRIPTION AND OPERATION Trim Air Valve - Component Location SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-63-00-040-001-A - Deactivation of the Trim Air Valve

FR40

A

A 1

B EXAMPLE

3 1 2

FLOW

B

NOTE: 1

O = OPEN, C = CLOSED

N_MM_216300_4_AAN0_01_02

Figure 21-63-00-991-00200-00-B / SHEET 1/1 - Trim Air Valve - Component Location ** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-63-00-040-001-A - Deactivation of the Trim Air Valve

3.

Job Set-up (Ref. Fig. Trim Air Valve - Component Location SHEET 1) Subtask 21-63-00-861-050-A A.

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

Subtask 21-63-00-010-050-A B.

Get Access WARNING: DO NOT OPEN OR GO NEAR PRESSURE-SEALED DOORS WHEN THE AIRCRAFT IS PRESSURIZED. A PRESSURE-SEALED DOOR THAT OPENS WHEN THE AIRCRAFT IS PRESSURIZED: - WILL CAUSE EXPLOSIVE DECOMPRESSION. - CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAUSE DAMAGE TO THE AIRCRAFT OR EQUIPMENT. (1) Open the FWD cargo-compartment door 825 (Ref. AMM TASK 52-30-00-860-001) . (2) Put the ACCESS PLATFORM 2M (6 FT) in position at the FWD cargo-compartment door 825. (3) Remove the access panels at partition FR34 (Ref. AMM D/O 06-41-53-00) , (Ref. AMM TASK 2554-12-000-001) .

Subtask 21-63-00-865-078-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL 122VU 122VU 122VU 122VU

4.

DESIGNATION AIR COND/ZONE TEMP CTL/28VDC/ SYS2 AIR COND/ZONE TEMP CTL/28VDC/ SYS1 AIR COND/ZONE TEMP CTL/115VAC/ SYS2 AIR COND/ZONE TEMP CTL/115VAC/ SYS1

FIN 4HK

LOCATION V20

3HK

V19

2HK

V18

1HK

V17

Procedure (Ref. Fig. Trim Air Valve - Component Location SHEET 1) Subtask 21-63-00-040-050-A A.

Deactivation of the Trim Air Valve (1) Move the manual override lever (3) to the CLOSED (or C) position and safety with lockwire-corrosion resistant steel 0.8 mm (0.0314 in.) dia. (2) Disconnect the electrical connector (2) from the trim-air valve (1). (3) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (4) Temporarily attach the disconnected electrical connector (2) to the aircraft structure.

5.

Close-up Subtask 21-63-00-410-050-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the access panels at partition FR34 (Ref. AMM D/O 06-41-53-00) , (Ref. AMM TASK 25-5412-400-001) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-63-00-040-001-A - Deactivation of the Trim Air Valve

(3) Remove the access platform(s). (4) Close the FWD cargo-compartment door 825 (Ref. AMM TASK 52-30-00-860-002) . (5) Make an entry in the log book to record the deactivation. Subtask 21-63-00-865-080-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 122VU 122VU 122VU 122VU

DESIGNATION AIR COND/ZONE TEMP CTL/28VDC/ SYS2 AIR COND/ZONE TEMP CTL/28VDC/ SYS1 AIR COND/ZONE TEMP CTL/115VAC/ SYS2 AIR COND/ZONE TEMP CTL/115VAC/ SYS1

FIN 4HK

V20

LOCATION

3HK

V19

2HK

V18

1HK

V17

Subtask 21-63-00-862-050-A C.

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

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-63-00-040-002-A - Deactivation of the Hot-Air Pressure-Regulating Valve

** ON A/C ALL TASK 21-63-00-040-002-A Deactivation of the Hot-Air Pressure-Regulating Valve WARNING:

MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

WARNING:

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

FIN : 14HK Task Summary MMEL or CDL Ref MMEL 21-63-03C

Access YES

Test YES

1.

Reason for the Job MMEL 21-63-03C Hot Air Pressure Regulating Valve

2

Job Set-up Information A.

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

Specific Tools NO

QTY 1 AR AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER

Consumable Materials REFERENCE No specific

DESIGNATION lockwire-corrosion resistant steel 0.8 mm (0.0314 in.)

C. Work Zones and Access Panels ZONE/ACCESS 825

ZONE DESCRIPTION

D. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-63-00-040-002-A - Deactivation of the Hot-Air Pressure-Regulating Valve

REFERENCE (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 25-54-12-000-001-A). (Ref. 25-54-12-400-001-A). (Ref. 52-30-00-860-001-A). (Ref. 52-30-00-860-002-A). (Ref. 06-41-53-00).

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Removal of the Forward Cargo-Compartment Partition FR34 or FR35.5 Installation of the Forward Cargo-Compartment Partition FR34 or FR35.5 Open the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump Close the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump FUSELAGE - DESCRIPTION AND OPERATION

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 Hot-Air Pressure-Regulating Valve SHEET 1 ** ON A/C 016-022, 024-094, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 350-350 Hot-Air Pressure-Regulating Valve SHEET 1 ** ON A/C 095-100, 301-349, 351-450, 500-600 Hot-Air Pressure-Regulating Valve (P/N 700853A010001) SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-63-00-040-002-A - Deactivation of the Hot-Air Pressure-Regulating Valve

FR40

A

A

1

2

B EXAMPLE

OPEN

B

3 CLOSED

N_MM_216300_4_ACM0_01_01

Figure 21-63-00-991-00300-00-A / SHEET 1/1 - Hot-Air Pressure-Regulating Valve ** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-63-00-040-002-A - Deactivation of the Hot-Air Pressure-Regulating Valve

FR40

A

A

1

2

B EXAMPLE

OPEN

B

3 CLOSED

N_MM_216300_4_ACP0_01_01

Figure 21-63-00-991-00300-00-C / SHEET 1/1 - Hot-Air Pressure-Regulating Valve ** ON A/C 016-022, 024-094, 112-150, 206-206, 208209, 212-218, 221-230, 235-236, 238-239, 241-242, 350-350 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-63-00-040-002-A - Deactivation of the Hot-Air Pressure-Regulating Valve

FR40

FR36

FR32

A

FWD CARGO COMPARTMENT

3

FWD

B TYPICAL

2 14HK

1

B

A TYPICAL N_MM_216300_4_ACX0_01_00

Figure 21-63-00-991-00300-00-E / SHEET 1/1 - Hot-Air Pressure-Regulating Valve (P/N 700853A010001) ** ON A/C 095-100, 301-349, 351-450, 500-600 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-63-00-040-002-A - Deactivation of the Hot-Air Pressure-Regulating Valve

3.

Job Set-up

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 (Ref. Fig. Hot-Air Pressure-Regulating Valve SHEET 1) ** ON A/C 016-022, 024-094, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 350-350 (Ref. Fig. Hot-Air Pressure-Regulating Valve SHEET 1) ** ON A/C 095-100, 301-349, 351-450, 500-600 (Ref. Fig. Hot-Air Pressure-Regulating Valve (P/N 700853A010001) SHEET 1) ** ON A/C ALL Subtask 21-63-00-861-052-A A.

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

Subtask 21-63-00-010-051-A B.

Get Access WARNING: DO NOT OPEN OR GO NEAR PRESSURE-SEALED DOORS WHEN THE AIRCRAFT IS PRESSURIZED. A PRESSURE-SEALED DOOR THAT OPENS WHEN THE AIRCRAFT IS PRESSURIZED: - WILL CAUSE EXPLOSIVE DECOMPRESSION. - CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAUSE DAMAGE TO THE AIRCRAFT OR EQUIPMENT. (1) Open the FWD cargo-compartment door 825 (Ref. AMM TASK 52-30-00-860-001) . (2) Put the ACCESS PLATFORM 2M (6 FT) at the FWD cargo-compartment door 825. (3) Remove the access panel at partition FR34 (Ref. AMM D/O 06-41-53-00) , (Ref. AMM TASK 25-5412-000-001) .

Subtask 21-63-00-865-054-A C.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 301-450, 500-600 49VU AIR COND/TEMP CTL/SYS 1 CHAN B/ 52HH D08 28VDC 122VU AIR COND/TEMP CTL SYS 2/CHAN A/ 53HH W22 115VAC 122VU AIR COND/TEMP CTL SYS 2/CHAN A/ 55HH W21 28VDC 122VU AIR COND/TEMP CTL SYS 1/CHAN A/ 49HH X22 115VAC 122VU AIR COND/TEMP CTL SYS 1/CHAN A/ 51HH X21 28VDC 122VU AIR COND/TEMP CTL SYS 2/CHAN B/ 56HH Y21 28VDC 122VU AIR COND/TEMP CTL SYS 2/CHAN B/ 54HH Y20 115VAC

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-63-00-040-002-A - Deactivation of the Hot-Air Pressure-Regulating Valve

PANEL 122VU

DESIGNATION AIR COND/TEMP CTL SYS 1/CHAN B/ 115VAC

FIN 50HH

LOCATION Y18

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 122VU AIR COND/ZONE TEMP CTL/28VDC/ 4HK V20 SYS2 122VU AIR COND/ZONE TEMP CTL/28VDC/ 3HK V19 SYS1 122VU AIR COND/ZONE TEMP CTL/115VAC/ 2HK V18 SYS2 122VU AIR COND/ZONE TEMP CTL/115VAC/ 1HK V17 SYS1 ** ON A/C ALL 4.

Procedure

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 Subtask 21-63-00-040-053-A A.

Deactivation of the Pressure Regulating Valve (1) Turn the manual override lever (3) to the closed position and safety with lockwire-corrosion resistant steel 0.8 mm (0.0314 in.) dia. (2) Disconnect the electrical connector 14HK-C (1) from the pressure regulating valve (2). (3) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (4) Temporarily attach the disconnected electrical connector 14HK-C (1) to the aircraft structure.

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 301450, 500-600 Subtask 21-63-00-040-053-B A.

Deactivation of the Pressure Regulating Valve (new ECS) (1) Turn the manual override lever (3) to the closed position and safety with lockwire-corrosion resistant steel 0.8 mm (0.0314 in.) dia. (2) Disconnect the electrical connector 14HK-A (1) from the pressure regulating valve (2). (3) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (4) Temporarily attach the disconnected electrical connector 14HK-A (1) to the aircraft structure.

** ON A/C ALL 5.

Close-up Subtask 21-63-00-410-051-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the access panel at partition FR34 (Ref. AMM D/O 06-41-53-00) , (Ref. AMM TASK 25-54-12400-001) . (3) Remove the access platform(s). (4) Close the FWD cargo-compartment door 825 (Ref. AMM TASK 52-30-00-860-002) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-63-00-040-002-A - Deactivation of the Hot-Air Pressure-Regulating Valve

(5) Put a temporary placard in the cockpit that tells persons that the pressure-regulating valve is not in operation. (6) Make an entry in the log book to record the deactivation. Subtask 21-63-00-865-065-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 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 301-450, 500-600 49VU AIR COND/TEMP CTL/SYS 1 CHAN B/ 52HH D08 28VDC 122VU AIR COND/TEMP CTL SYS 2/CHAN A/ 53HH W22 115VAC 122VU AIR COND/TEMP CTL SYS 2/CHAN A/ 55HH W21 28VDC 122VU AIR COND/TEMP CTL SYS 1/CHAN A/ 49HH X22 115VAC 122VU AIR COND/TEMP CTL SYS 1/CHAN A/ 51HH X21 28VDC 122VU AIR COND/TEMP CTL SYS 2/CHAN B/ 56HH Y21 28VDC 122VU AIR COND/TEMP CTL SYS 2/CHAN B/ 54HH Y20 115VAC 122VU AIR COND/TEMP CTL SYS 1/CHAN B/ 50HH Y18 115VAC ** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 122VU AIR COND/ZONE TEMP CTL/28VDC/ 4HK V20 SYS2 122VU AIR COND/ZONE TEMP CTL/28VDC/ 3HK V19 SYS1 122VU AIR COND/ZONE TEMP CTL/115VAC/ 2HK V18 SYS2 122VU AIR COND/ZONE TEMP CTL/115VAC/ 1HK V17 SYS1 ** ON A/C ALL Subtask 21-63-00-862-051-A C.

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

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-63-00-040-004-A - Zone Controller - Deactivation of the Hot-Air Pressure-Regulating Valve

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 TASK 21-63-00-040-004-A Zone Controller - Deactivation of the Hot-Air Pressure-Regulating Valve WARNING:

MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.

FIN : 8HK Task Summary MMEL or CDL Ref MMEL 21-63-01C 1.

Reason for the Job MMEL 21-63-01C Zone Controller Channel

2

Job Set-up Information A.

Access YES

Specific Tools NO

Mhr 00.5

E/T 00.5

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

Test NO

QTY 1 AR AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS 825

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 25-54-12-000-001-A). (Ref. 25-54-12-400-001-A). (Ref. 52-30-00-860-001-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Removal of the Forward Cargo-Compartment Partition FR34 or FR35.5 Installation of the Forward Cargo-Compartment Partition FR34 or FR35.5 Open the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-63-00-040-004-A - Zone Controller - Deactivation of the Hot-Air Pressure-Regulating Valve REFERENCE (Ref. 52-30-00-860-002-A).

DESIGNATION Close the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump (Ref. 06-41-53-00). FUSELAGE - DESCRIPTION AND OPERATION Hot-Air Pressure-Regulating Valve SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-63-00-040-004-A - Zone Controller - Deactivation of the Hot-Air Pressure-Regulating Valve

FR40

A

A 1

2

B EXAMPLE

OPEN

B

3 CLOSED

N_MM_216300_4_AEM0_01_02

Figure 21-63-00-991-00400-00-A / SHEET 1/1 - Hot-Air Pressure-Regulating Valve ** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-63-00-040-004-A - Zone Controller - Deactivation of the Hot-Air Pressure-Regulating Valve

3.

Job Set-up (Ref. Fig. Hot-Air Pressure-Regulating Valve SHEET 1) Subtask 21-63-00-861-060-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

Subtask 21-63-00-010-054-A B.

Get Access WARNING: DO NOT OPEN OR GO NEAR PRESSURE-SEALED DOORS WHEN THE AIRCRAFT IS PRESSURIZED. A PRESSURE-SEALED DOOR THAT OPENS WHEN THE AIRCRAFT IS PRESSURIZED: - WILL CAUSE EXPLOSIVE DECOMPRESSION. - CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAUSE DAMAGE TO THE AIRCRAFT OR EQUIPMENT. (1) Open the FWD cargo-compartment door 825 (Ref. AMM TASK 52-30-00-860-001) . (2) Put the ACCESS PLATFORM 2M (6 FT) in position at the FWD cargo-compartment door 825 (3) Remove the access panel at partition FR34 (Ref. AMM D/O 06-41-53-00) , (Ref. AMM TASK 25-5412-000-001) .

Subtask 21-63-00-865-067-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL 122VU 122VU 122VU 122VU

4.

DESIGNATION AIR COND/ZONE TEMP CTL/28VDC/ SYS2 AIR COND/ZONE TEMP CTL/28VDC/ SYS1 AIR COND/ZONE TEMP CTL/115VAC/ SYS2 AIR COND/ZONE TEMP CTL/115VAC/ SYS1

FIN 4HK

V20

LOCATION

3HK

V19

2HK

V18

1HK

V17

Procedure Subtask 21-63-00-040-052-A A.

Deactivation of the Hot-Air Pressure-Regulating Valve (1) Turn the manual override lever (3) of the pressure regulating valve (2) in the closed position. (2) Disconnect the electrical connector 14HK-C (1) from the pressure regulating valve (2). (3) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (4) Temporarily attach the disconnected electrical connector 14HK-C (1) to the aircraft structure.

5.

Close-up Subtask 21-63-00-410-054-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the access panel at partition FR34 (Ref. AMM D/O 06-41-53-00) , (Ref. AMM TASK 25-54-12400-001) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-63-00-040-004-A - Zone Controller - Deactivation of the Hot-Air Pressure-Regulating Valve

(3) Remove the access platform. (4) Close the FWD cargo-compartment door 825 (Ref. AMM TASK 52-30-00-860-002) . (5) Make an entry in the log book to record the deactivation. Subtask 21-63-00-865-082-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 122VU 122VU 122VU 122VU

DESIGNATION AIR COND/ZONE TEMP CTL/28VDC/ SYS2 AIR COND/ZONE TEMP CTL/28VDC/ SYS1 AIR COND/ZONE TEMP CTL/115VAC/ SYS2 AIR COND/ZONE TEMP CTL/115VAC/ SYS1

FIN 4HK

V20

LOCATION

3HK

V19

2HK

V18

1HK

V17

Subtask 21-63-00-862-057-A C.

Aircraft Maintenance Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 22-30-00-040-004-A - Check of the Throttle Control Units

** ON A/C ALL TASK 22-30-00-040-004-A Check of the Throttle Control Units

FIN : 8KS1 , 8KS2 1.

Reason for the Job MMEL 22-30-01A Autothrust (A/THR) (FAA only)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION 1 WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 210

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). 3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure

Job Set-up Subtask 22-30-00-860-059-A A.

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) On the center pedestal, make sure that all the throttle control levers are set to IDLE (0 degree TLA). (4) On the maintenance panel 50VU: · release the ENG FADEC GND PWR 1 and 2 pushbutton switches (The ON legend of these pushbutton switches comes on).

Subtask 22-30-00-865-062-A Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 22-30-00-040-004-A - Check of the Throttle Control Units

B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 49VU 121VU 121VU

DESIGNATION ENGINE/2/FADEC A/AND EIU 2 ENGINE/1/FADEC A/AND EIU 1 ENGINE/1 AND 2/IGN/SYS A ENGINE/IGN/ENG2/SYS B ENGINE/IGN/ENG1/SYS B

FIN 2KS2 2KS1 1JH 3JH2 3JH1

LOCATION A05 A04 A03 P42 P41

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU ENGINE/ENG2/FADEC B/AND EIU 2 4KS2 Q40 121VU ENGINE/ENG1/FADEC B/AND EIU 1 4KS1 R41 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 121VU ENGINE/IGN/ENG2/SYS A BAT 2JH2 121VU ENGINE/IGN/ENG1/SYS A BAT 2JH1

P40 P39

** ON A/C 401-450 121VU ENGINE/ENG2/FADEC B/AND EIU 2 121VU ENGINE/ENG1/FADEC B/AND EIU 1

R41 R40

4KS2 4KS1

** ON A/C ALL 4.

Procedure

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241, 301-349, 351-450, 500-600 Subtask 22-30-00-710-059-A A.

Operational Test of the Throttle Control Units ACTION 1.Open circuit breakers 2KS1, 2KS2. 2.On the center pedestal: · move the ENG1 and 2 throttle control levers.

RESULT On the upper ECAM display unit: · the small circles on N1 indications follow the position of the throttle control levers.

· move the throttle control levers to IDLE position. 3.Close circuit breakers 2KS1, 2KS2. 4.Open circuit breakers 4KS1, 4KS2. 5.On the center pedestal: On the upper ECAM display unit: · move the ENG1 and 2 throttle control levers. · the small circles on N1 indications follow the position of the throttle control levers. · move the throttle control levers to IDLE position. 6.Close circuit breakers 4KS1, 4KS2.

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 Subtask 22-30-00-710-059-B WARNING:

MAKE SURE THAT YOU OPEN THE CIRCUIT BREAKERS AS FOLLOWS: - 1JH, 2JH1 AND 3JH1 BEFORE 2KS1 - 1JH, 2JH2 AND 3JH2 BEFORE 2KS2.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 22-30-00-040-004-A - Check of the Throttle Control Units

IF YOU DO NOT OBEY THIS SEQUENCE, THERE IS A RISK OF ELECTROCUTION. THIS IS BECAUSE YOU WILL START CONTINUOUS IGNITION IF YOU OPEN CIRCUIT BREAKER 2KS1 OR 2KS2 FIRST. A.

Operational Test of the Throttle Control Units ACTION 1.On the panel 121VU: · open circuit breakers 2JH1, 3JH1, 2JH2 and 3JH2. 2.On the panel 49VU: · open circuit breakers 1JH, 2KS1 and 2KS2. 3.On the center pedestal: · move the ENG1 and 2 throttle control levers.

RESULT

On the upper ECAM display unit: · the thrust limit mode indication and the EPR value limit follow the position of the throttle control levers.

· move the throttle control levers to IDLE position. 4.Close circuit breakers 2KS1, 2KS2. 5.Open circuit breakers 4KS1, 4KS2. 6.On the center pedestal: On the upper ECAM display unit: · move the ENG1 and 2 throttle control levers. · the small circles on EPR indications follow the position of the throttle control levers. · move the throttle control levers to IDLE position. 7.Close circuit breakers 4KS1, 4KS2 and then close circuit breakers 1JH, 2JH1, 3JH1, 2JH2 and 3JH2.

** ON A/C ALL 5.

Close-up Subtask 22-30-00-860-060-A A.

Put the aircraft back to its initial configuration. (1) On the maintenance panel 50VU: · push the ENG FADEC GND PWR 1 and 2 pushbutton switches (The ON legend of these pushbutton switches goes off). (2) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (3) Put a WARNING NOTICE(S) in the cockpit to tell the crew that the autothrust function does not operate. (4) Make an entry in the logbook. (5) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-22-00-040-001-A - Deactivation of the Channel 1 of the Rudder Trim Actuator

** ON A/C ALL TASK 27-22-00-040-001-A Deactivation of the Channel 1 of the Rudder Trim Actuator

FIN : 10CC 1.

Reason for the Job MMEL 22-60-01A FAC 1

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE AR SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS 120 824

ZONE DESCRIPTION AVIONICS COMPARTMENT

C. Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A). (Ref. 27-22-00-710-002-A). 3.

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power Operational Test of the Rudder Trim Actuation

Job Set-up Subtask 27-22-00-860-059-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Subtask 27-22-00-010-052-A B.

Get access to the avionics compartment. (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position below the access door 824. (2) Open the access door 824.

Subtask 27-22-00-865-055-A C.

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

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-22-00-040-001-A - Deactivation of the Channel 1 of the Rudder Trim Actuator

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU AUTO FLT/FAC1/28VDC 5CC1 B04 ** ON A/C 401-450 49VU AUTO FLT/FAC1/28VDC

5CC1

H10

** ON A/C ALL 4.

Procedure Subtask 27-22-00-040-050-A A.

Deactivation of the Channel 1 of the Rudder Trim Actuator (1) On the panel 187VU, remove the relay 7CC1. (2) Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5CC1.

Subtask 27-22-00-710-053-A B. 5.

Do the operational test of the rudder trim actuation (Ref. AMM TASK 27-22-00-710-002) .

Close-up Subtask 27-22-00-941-053-A A.

Safety Precautions (1) Make an entry in the logbook.

Subtask 27-22-00-410-053-A B.

Close Access (1) Close the access door 824. (2) Remove the access platform(s).

Subtask 27-22-00-862-054-A C.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001)

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-23-00-040-001-A - Deactivation of the Channel 1 of the Rudder Travel Limitation Unit

** ON A/C ALL TASK 27-23-00-040-001-A Deactivation of the Channel 1 of the Rudder Travel Limitation Unit

FIN : 4CC 1.

Reason for the Job MMEL 22-60-01A FAC 1

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE AR SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS 120 824

ZONE DESCRIPTION AVIONICS COMPARTMENT

C. Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A). (Ref. 27-23-00-710-002-A). 3.

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power Operational Test of the Rudder-Travel Limitation Unit

Job Set-up Subtask 27-23-00-860-055-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Subtask 27-23-00-010-052-A B.

Get access to the avionics compartment. (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position below the access door 824. (2) Open the access door 824.

Subtask 27-23-00-865-052-A C.

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

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-23-00-040-001-A - Deactivation of the Channel 1 of the Rudder Travel Limitation Unit

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU AUTO FLT/FAC1/28VDC 5CC1 B04 ** ON A/C 401-450 49VU AUTO FLT/FAC1/28VDC

5CC1

H10

** ON A/C ALL 4.

Procedure Subtask 27-23-00-040-050-A A.

Deactivation of the Channel 1 of the Rudder Travel Limitation Unit (1) On the panel 187VU, remove the relay 13CC1. (2) Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5CC1.

Subtask 27-23-00-710-055-A B. 5.

Do the operational test of the rudder travel limitation unit (Ref. AMM TASK 27-23-00-710-002) .

Close-up Subtask 27-23-00-941-050-A A.

Safety Precautions (1) Make an entry in the logbook.

Subtask 27-23-00-410-052-A B.

Close Access (1) Close the access door 824. (2) Remove the access platform(s).

Subtask 27-23-00-862-052-A C.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001)

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-26-00-040-001-A - Deactivation of the Yaw Damper Servo-Actuator

** ON A/C ALL TASK 27-26-00-040-001-A Deactivation of the Yaw Damper Servo-Actuator 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.

FIN : 3CC1 , 3CC2 Task Summary MMEL or CDL Ref MMEL 22-60-04A

Access YES

1.

Reason for the Job MMEL 22-60-04A Yaw Damper System (FAA only)

2

Job Set-up Information A.

Test YES

Mhr 00.7

E/T 00.7

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific No specific No specific No specific No specific No specific

QTY 1 AR 1 1 1 1 1 AR AR AR

No specific

B.

Specific Tools YES

DESIGNATION ACCESS PLATFORM 10M (33 FT) - ADJUSTABLE CAP - BLANKING CAP - BLANKING (MS21914-4 TYPE) CAP - BLANKING (MS21914-5 TYPE) CONTAINER 5 L (1.32 USGAL) PLUG - BLANKING (MS21913-4 TYPE) PLUG - BLANKING (MS21913-5 TYPE) SAFETY CLIP - CIRCUIT BREAKER TIE WRAP WARNING NOTICE(S) Torque wrench: range to between 1.5 and 1.7 m.daN (11.06 and 12.54 lbf.ft) Torque wrench: range to between 2.0 and 2.3 m.daN (14.75 and 16.96 lbf.ft)

Work Zones and Access Panels ZONE/ACCESS 325 325BL, 325BR

ZONE DESCRIPTION VERTICAL STABILIZER TRAILING EDGE

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-26-00-040-001-A - Deactivation of the Yaw Damper Servo-Actuator

C. Referenced Information REFERENCE (Ref. 22-63-00-710-001-A). (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A).

DESIGNATION Operational Test of the Yaw Damper Function Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power (Ref. 29-10-00-864-001-A). Depressurize the Green Hydraulic System (Ref. 29-10-00-864-002-A). Depressurize the Yellow Hydraulic System (Ref. 29-10-00-864-003-A). Depressurize the Blue Hydraulic System (Ref. 29-14-00-614-001-A). Depressurization of the Hydraulic Reservoirs (Ref. 29-14-00-614-002-A). Pressurization of the Hydraulic Reservoirs through the Ground Connector (Ref. 29-14-00-614-002-A-01). Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU) Yaw Damper Servo-Actuator 3CC1 (3CC2) SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-26-00-040-001-A - Deactivation of the Yaw Damper Servo-Actuator

A

Z325

325BL (325BR)

B

A

B 3CC2 3CC1

B

1

2 3 5 4

N_MM_272600_4_AAM0_01_01

Figure 27-26-00-991-00200-00-A / SHEET 1/1 - Yaw Damper Servo-Actuator 3CC1 (3CC2) ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-26-00-040-001-A - Deactivation of the Yaw Damper Servo-Actuator

3.

Job Set-up Subtask 27-26-00-860-050-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) . (2) Make sure that the hydraulic systems are depressurized (Ref. AMM TASK 29-10-00-864-001) (Ref. AMM TASK 29-10-00-864-002) (Ref. AMM TASK 2910-00-864-003) . (3) Put the WARNING NOTICE(S) in the cockpit to tell persons not to operate the flight controls.

Subtask 27-26-00-865-054-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 3CC1 (SERVO ACTR-YAW DAMPER, 1)

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU AUTO FLT/FAC1/28VDC 5CC1 B04 49VU AUTO FLT/FAC1/26VAC 14CC1 B03 ** ON A/C 401-450 49VU AUTO FLT/FAC1/28VDC 49VU AUTO FLT/FAC1/26VAC

5CC1 14CC1

H10 H09

** ON A/C ALL FOR FIN 3CC2 (SERVO ACTR-YAW DAMPER, 2) 121VU AUTO FLT/FAC2/28VDC 121VU AUTO FLT/FAC2/26VAC

5CC2 14CC2

M19 M18

Subtask 27-26-00-010-054-A C.

Get Access (1) Put an ACCESS PLATFORM 10M (33 FT) - ADJUSTABLE in position at zone 325. (2) Open the access door 325BL ( 325BR).

4.

Procedure Subtask 27-26-00-040-050-A A.

Deactivation of the Yaw Damper Servo-Actuator 3CC1 (3CC2). (Ref. Fig. Yaw Damper Servo-Actuator 3CC1 (3CC2) SHEET 1) (1) Disconnect the electrical connectors (2) and (5) from the yaw damper servo-actuator (1). (2) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (3) Attach the electrical connectors (2) and (5) with a TIE WRAP. (4) Make sure that there is no hydraulic leakage from the yaw damper servo-actuator (1). If there are leaks: (a) Depressurize the Green (Yellow) hydraulic reservoir (Ref. AMM TASK 29-14-00-614-001) . (b) Put a CONTAINER 5 L (1.32 USGAL) below the hydraulic connections of the yaw damper servoactuator (1). (c) Disconnect the hydraulic pipes (3) and (4) from the yaw damper servo-actuator (1).

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-26-00-040-001-A - Deactivation of the Yaw Damper Servo-Actuator

(d) Drain the remaining hydraulic fluid into the container. (e) Remove the container. CAUTION: USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT HYDRAULIC LINES ON UNIONS. IF YOU DO NOT USE THE SECOND WRENCH, THERE IS A RISK THAT YOU WILL LOOSEN OR TIGHTEN THE UNION TOO MUCH. (f)

For hydraulic pipe (3) (pressure port): 1

Put a CAP - BLANKING (MS21914-4 TYPE) on the unions of the yaw damper servoactuator. a

2

Torque it to between 1.5 and 1.7 m.daN (11.06 and 12.54 lbf.ft).

Put a PLUG - BLANKING (MS21913-4 TYPE) on the disconnected line ends. a

Torque it to between 1.5 and 1.7 m.daN (11.06 and 12.54 lbf.ft).

(g) For hydraulic pipe (4) (return port): 1

Put a CAP - BLANKING (MS21914-5 TYPE) on the unions of the yaw damper servoactuator. a

2

Torque it to between 2.0 and 2.3 m.daN (14.75 and 16.96 lbf.ft).

Put a PLUG - BLANKING (MS21913-5 TYPE) on the disconnected line ends. a

Torque it to between 2.0 and 2.3 m.daN (14.75 and 16.96 lbf.ft).

(h) Attach the hydraulic pipes (3) and (4) to the adjacent area with TIE WRAP. (i)

Pressurize the Green (Yellow) hydraulic reservoir (Ref. AMM TASK 29-14-00-614-002) .

Subtask 27-26-00-865-055-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 3CC1 (SERVO ACTR-YAW DAMPER, 1)

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU AUTO FLT/FAC1/28VDC 5CC1 B04 49VU AUTO FLT/FAC1/26VAC 14CC1 B03 ** ON A/C 401-450 49VU AUTO FLT/FAC1/28VDC 49VU AUTO FLT/FAC1/26VAC

5CC1 14CC1

H10 H09

** ON A/C ALL FOR FIN 3CC2 (SERVO ACTR-YAW DAMPER, 2) 121VU AUTO FLT/FAC2/28VDC 121VU AUTO FLT/FAC2/26VAC

5CC2 14CC2

M19 M18

Subtask 27-26-00-710-053-A C.

Tests (1) Do the operational test of the yaw damper function (Ref. AMM TASK 22-63-00-710-001) . NOTE: The yaw damper servo-actuator 3CC1 (3CC2) you deactivated does not operate.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-26-00-040-001-A - Deactivation of the Yaw Damper Servo-Actuator

5.

Close-up Subtask 27-26-00-941-053-A A.

Safety Precautions (1) Remove the WARNING NOTICE(S). (2) Put a WARNING NOTICE(S) in the cockpit to tell the crew that the yaw damper servo-actuator 3CC1 (3CC2) is deactivated. (3) Make an entry in the logbook.

Subtask 27-26-00-410-053-A B.

Close Access (1) Close the access doors 325BL ( 325BR). (2) Remove the access platform(s).

Subtask 27-26-00-860-051-A C.

Put the aircraft back to its initial configuration. (1) Make sure that the work area is clean and clear of tools and other items. (2) De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

** ON A/C ALL TASK 23-51-00-040-001-A Deactivation of the Radio Push-to-Talk (PTT) Switch WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

CAUTION:

MAKE SURE THAT THE ITEMS IN THE "FIXTURES, TOOLS, TEST AND SUPPORT EQUIPMENT" PARAGRAPH ARE APPLICABLE TO YOUR AIRCRAFT (THIS LIST IS NOT CUSTOMIZED). REFER TO THE APPLICABLE SUBTASKS.

CAUTION:

MAKE SURE THAT THE SIDE-STICK UNIT STAYS IN VERTICAL POSITION DURING THE MAINTENANCE PROCEDURE. THIS IS TO PREVENT DAMPER FLUID LEAKAGE WHICH CAN CAUSE DAMAGE TO THE UNIT.

FIN : ** ON A/C 016-022, 024-078, 112-150, 201-201, 203-250, 350-350 11RN , 12RN ** ON A/C ALL Task Summary MMEL or CDL Ref MMEL 23-51-06B MMEL 23-51-06A

Access NO NO

Test YES YES

Specific Tools YES YES

Mhr 00.7 00.7

E/T 00.7 00.7

Nb Men 1 1

NOTE: This task is applicable for all side-stick assemblies. To know if the side-stick assembly installed on the aircraft is a new-generation side-stick unit, refer to the procedure (Ref. AMM TASK 27-92-41-860-801). 1.

Reason for the Job MMEL 23-51-06B Sidestick PTT sw MMEL 23-51-06A Sidestick PTT sw NOTE: The maintenance procedure is only necessary when the selector of the side-stick radio is failed in the closed position (Push-To-Talk switches on).

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

QTY AR AR AR

DESIGNATION CAP - WIRE END SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

REFERENCE No specific No specific (DMC519) B.

QTY DESIGNATION Torque wrench: range to between 0.0315 and 0.0385 m.daN (2.79 and 3.41 lbf.in) Torque wrench: range to between 0.15 and 0.18 m.daN (13.27 and 15.93 lbf.in) 1 ELECTRICIAN SERVICE TOOL KIT

Work Zones and Access Panels ZONE/ACCESS 211 212

ZONE DESCRIPTION COCKPIT COCKPIT

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 27-96-00-710-003-A). (Ref. 27-96-00-710-020-A). (Ref. 29-10-00-864-003-A). (Ref. 29-23-00-864-001-A). (Ref. 29-24-00-864-001-A). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 34-10-00-860-004-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Operational Test of the Side Stick Priority Operational Test of the Side Stick Assembly (Activation for the BITE Test) Depressurize the Blue Hydraulic System Depressurize the Green and Yellow Hydraulic Systems after Operation of the PTU Depressurize the Yellow Hydraulic System EIS Start Procedure EIS Stop Procedure IR Alignment Procedure

** ON A/C 027-100, 112-150, 208-208, 212-214, 219-220, 223-226, 231-233, 236-238, 240-250, 301-349, 351-450, 500-600 (Ref. 34-10-00-860-004-A-01). Automatic IR Alignment Procedure ** ON A/C ALL (Ref. 34-10-00-860-004-A-02).

IR Alignment Procedure to do a Check of the Links between each FMGC and the three Air Data/Inertial Reference Units (ADIRUs)

Ref. ESPM 20-42-13 Ref. ESPM 20-43-13 Side Stick Assembly New-Generation Side-Sick Assembly

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

A

A

A LH SHOWN, RH SYMMETRICAL

C

D

A

11RN SECTION

A-A

(12RN)

B

7

6 4 3

A

N_MM_235100_4_AAC0_01_01

Figure 23-51-00-991-00100-00-A / SHEET 1/2 - Side Stick Assembly ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

B

1

LH SHOWN, RH SYMMETRICAL 2 3 11 10

4

8 9

5

7 6

D

2

LH SHOWN, RH SYMMETRICAL 12 5

12

B=40mm

C

1

LH SHOWN, RH SYMMETRICAL

5

A=40mm

NOTE: 1

CUT THE WIRES OF THE DEFECTIVE SWITCH

2

CONNECT WIRES OF THE NEW SWITCH WITH SPLICES N_MM_235100_4_AAC0_02_00

Figure 23-51-00-991-00100-00-A / SHEET 2/2 - Side Stick Assembly ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

A

A

A LH SHOWN, RH SYMMETRICAL

A

B

B

LH SHOWN RH SYMMETRICAL

11RN (12RN)

1

2 3

A

N_MM_235100_4_AAA0_01_00

Figure 23-51-00-991-00500-00-A / SHEET 1/2 - New-Generation Side-Sick Assembly ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

SECTION

A-A 4

4

N_MM_235100_4_AAA0_02_00

Figure 23-51-00-991-00500-00-A / SHEET 2/2 - New-Generation Side-Sick Assembly ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

3.

Job Set-up Subtask 23-51-00-861-055-A A.

Aircraft Maintenance Configuration NOTE: Paragraph 4.A. is only applicable to the side-stick assembly. For the new-generation side-stick assembly, refer to paragraph 4.B. (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

Subtask 23-51-00-865-055-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 11RN (SW-RAD PTT, CAPT) 49VU COM/ACP CAPT/SELCAL/INT 1 AUDIO/AVNCS FOR FIN 12RN (SW-RAD PTT, F/O)

FIN 4RN

LOCATION G06

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-236, 238-250, 301-450, 500-600 49VU COM/AUDIO/ACP/F/O 5RN G07 ** ON A/C 207-207, 210-210, 237-237 49VU COM/ACP F/O/BITE/ INT 2 AUDIO/3&5 OCCPNT

5RN

G07

** ON A/C ALL 4.

Procedure Subtask 23-51-00-010-050-A A.

Disengagement of the Radio PTT Switch (11RN, 12RN) (Ref. Fig. Side Stick Assembly) (1) Remove the screws (1). (2) Remove the cover plate (2). (3) Remove the blanking plug (11), the nut (10), the washer (9) and the trigger (8). (4) Remove the nut (7), the washer (6), the switch (4) with the washer (3).

Subtask 23-51-00-010-056-A B.

Disengagement of the radio Push-to-Talk (PTT) switch (11RN, 12RN) of the new-generation side-stick unit (100CE1, 100CE2) (Ref. Fig. New-Generation Side-Sick Assembly) (1) Remove the screws (1). (2) Remove the cover plate or the tactile indicator (2) according to the Side-Stick Unit (SSU) option. (3) Remove the seal (3).

Subtask 23-51-00-040-050-A C.

Deactivation of the Radio PTT Switch (11RN, 12RN)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

NOTE: Go directly to the paragraph E. for the deactivation of the radio Push-to-Talk (PTT) switch of the new-generation side-stick unit. (1) Do a visual check of the PTT switch wires to see if there are splices already installed: (a) If there are splices installed: · Use the extraction/insertion tool P/N M81969/14.01 from the ELECTRICIAN SERVICE TOOL KIT (DMC519) to disconnect the PTT switch wires from the splices Ref. ESPM 20-43-13. (b) If there is no splice installed: 1

Cut the wires of the PTT switch as follows: a

Before you cut the wires, make sure that the two identification-labels stay on the wires, on the control-handle side.

b

On the two wires, measure 40mm distance "A" from the studs of the PTT switch and make mark on each wire.

c

Cut the two wires at these marks.

d

Install CAP - WIRE END at the end of each wire Ref. ESPM 20-42-13.

Subtask 23-51-00-410-051-A D.

Engagement of the Radio PTT Switch (11RN,12RN) (1) Install the lock plate (3) in the switch (4). (2) Install the switch (4) in the handle. (3) Make sure that the stop of the lock plate (3) is in its housing. (4) Install the washer (6), the nut (7) and tighten it. (5) Install the trigger (8), the washer (9) and the nut (10). CAUTION:

OBEY THE TORQUE VALUES SPECIFIED BELOW.

(6) TORQUE the nut (10) to between 0.0315 and 0.0385 m.daN (2.79 and 3.41 lbf.in). (7) Install the blanking plug (11). (8) Install the cover plate (2). (9) Install the screws (1) and tighten. Subtask 23-51-00-040-053-A E.

Deactivation of the radio Push-to-Talk (PTT) switch (11RN, 12RN) of the new-generation side-stick unit (100CE1, 100CE2) (Ref. Fig. New-Generation Side-Sick Assembly) (1) Pull the two PTT switch wires (green and brown) (4) through the access hole. (2) Cut the power supply wires. (3) Install end caps at the end of each wire Ref. ESPM 20-42-13 connected to the handle connector.

Subtask 23-51-00-410-056-A F.

Engagement of the radio Push-to-Talk (PTT) switch (11RN, 12RN) of the (Ref. Fig. New-Generation Side-Sick Assembly) new-generation side-stick unit (100CE1, 100CE2) (1) Install the seal (3) and the cover plate or tactile indicator (2). (2) Install the screws (1) and tighten them to between 0.15 and 0.18 m.daN (13.27 and 15.93 lbf.in).

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

Subtask 23-51-00-865-056-A G. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 11RN (SW-RAD PTT, CAPT) 49VU COM/ACP CAPT/SELCAL/INT 1 AUDIO/AVNCS FOR FIN 12RN (SW-RAD PTT, F/O)

FIN 4RN

LOCATION G06

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-236, 238-250, 301-450, 500-600 49VU COM/AUDIO/ACP/F/O 5RN G07 ** ON A/C 207-207, 210-210, 237-237 49VU COM/ACP F/O/BITE/ INT 2 AUDIO/3&5 OCCPNT

5RN

G07

** ON A/C ALL Subtask 23-51-00-860-058-A H.

Aircraft Maintenance Configuration (1) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) . (2) Do the IR alignment procedure (Ref. AMM TASK 34-10-00-860-004) . (3) On the overhead panel 23VU: · make sure that the FLT CTL/ELAC 1 and FLT CTL/SEC 1 pushbutton switches are pushed (On these pushbutton switches, the OFF and FAULT legends are off). (4) On the overhead panel 24VU: · make sure that the FLT CTL/ELAC 2, FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches are pushed (On these pushbutton switches, the OFF and FAULT legends are off). (5) On the upper ECAM display unit, make sure that the warnings that follow do not show: · HF1 (2) EMITTING · VHF1 (2) (3) EMITTING · ELAC 1 FAULT · ELAC 2 FAULT · SINGLE PTT STUCK NOTE: If one of these warnings shows, do the trouble shooting procedure related to the maintenance message.

Subtask 23-51-00-710-058-A J.

Operational Tests: (1) Do the Operational test of the Side Stick Priority (Ref. AMM TASK 27-96-00-710-003) . (2) Do the Operational test of the Side Stick Assembly (Ref. AMM TASK 27-96-00-710-020) .

5.

Close-up Subtask 23-51-00-860-059-A A.

Put the aircraft back to its initial configuration. (1) Depressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-864-001) (Ref. AMM TASK 29-24-00-864-001) (Ref. AMM TASK 2910-00-864-003) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

(2) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (3) Put a WARNING NOTICE(S) on the cover panel of the side stick assembly to tell the crew that the radio PTT switch is deactivated. (4) Make an entry in the logbook. (5) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

** ON A/C ALL TASK 23-51-00-040-001-A Deactivation of the Radio Push-to-Talk (PTT) Switch WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

CAUTION:

MAKE SURE THAT THE ITEMS IN THE "FIXTURES, TOOLS, TEST AND SUPPORT EQUIPMENT" PARAGRAPH ARE APPLICABLE TO YOUR AIRCRAFT (THIS LIST IS NOT CUSTOMIZED). REFER TO THE APPLICABLE SUBTASKS.

CAUTION:

MAKE SURE THAT THE SIDE-STICK UNIT STAYS IN VERTICAL POSITION DURING THE MAINTENANCE PROCEDURE. THIS IS TO PREVENT DAMPER FLUID LEAKAGE WHICH CAN CAUSE DAMAGE TO THE UNIT.

FIN : ** ON A/C 016-022, 024-078, 112-150, 201-201, 203-250, 350-350 11RN , 12RN ** ON A/C ALL Task Summary MMEL or CDL Ref MMEL 23-51-06B MMEL 23-51-06A

Access NO NO

Test YES YES

Specific Tools YES YES

Mhr 00.7 00.7

E/T 00.7 00.7

Nb Men 1 1

NOTE: This task is applicable for all side-stick assemblies. To know if the side-stick assembly installed on the aircraft is a new-generation side-stick unit, refer to the procedure (Ref. AMM TASK 27-92-41-860-801). 1.

Reason for the Job MMEL 23-51-06B Sidestick PTT sw MMEL 23-51-06A Sidestick PTT sw NOTE: The maintenance procedure is only necessary when the selector of the side-stick radio is failed in the closed position (Push-To-Talk switches on).

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

QTY AR AR AR

DESIGNATION CAP - WIRE END SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

REFERENCE No specific No specific (DMC519) B.

QTY DESIGNATION Torque wrench: range to between 0.0315 and 0.0385 m.daN (2.79 and 3.41 lbf.in) Torque wrench: range to between 0.15 and 0.18 m.daN (13.27 and 15.93 lbf.in) 1 ELECTRICIAN SERVICE TOOL KIT

Work Zones and Access Panels ZONE/ACCESS 211 212

ZONE DESCRIPTION COCKPIT COCKPIT

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 27-96-00-710-003-A). (Ref. 27-96-00-710-020-A). (Ref. 29-10-00-864-003-A). (Ref. 29-23-00-864-001-A). (Ref. 29-24-00-864-001-A). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 34-10-00-860-004-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Operational Test of the Side Stick Priority Operational Test of the Side Stick Assembly (Activation for the BITE Test) Depressurize the Blue Hydraulic System Depressurize the Green and Yellow Hydraulic Systems after Operation of the PTU Depressurize the Yellow Hydraulic System EIS Start Procedure EIS Stop Procedure IR Alignment Procedure

** ON A/C 027-100, 112-150, 208-208, 212-214, 219-220, 223-226, 231-233, 236-238, 240-250, 301-349, 351-450, 500-600 (Ref. 34-10-00-860-004-A-01). Automatic IR Alignment Procedure ** ON A/C ALL (Ref. 34-10-00-860-004-A-02).

IR Alignment Procedure to do a Check of the Links between each FMGC and the three Air Data/Inertial Reference Units (ADIRUs)

Ref. ESPM 20-42-13 Ref. ESPM 20-43-13 Side Stick Assembly New-Generation Side-Sick Assembly

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

A

A

A LH SHOWN, RH SYMMETRICAL

C

D

A

11RN SECTION

A-A

(12RN)

B

7

6 4 3

A

N_MM_235100_4_AAC0_01_01

Figure 23-51-00-991-00100-00-A / SHEET 1/2 - Side Stick Assembly ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

B

1

LH SHOWN, RH SYMMETRICAL 2 3 11 10

4

8 9

5

7 6

D

2

LH SHOWN, RH SYMMETRICAL 12 5

12

B=40mm

C

1

LH SHOWN, RH SYMMETRICAL

5

A=40mm

NOTE: 1

CUT THE WIRES OF THE DEFECTIVE SWITCH

2

CONNECT WIRES OF THE NEW SWITCH WITH SPLICES N_MM_235100_4_AAC0_02_00

Figure 23-51-00-991-00100-00-A / SHEET 2/2 - Side Stick Assembly ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

A

A

A LH SHOWN, RH SYMMETRICAL

A

B

B

LH SHOWN RH SYMMETRICAL

11RN (12RN)

1

2 3

A

N_MM_235100_4_AAA0_01_00

Figure 23-51-00-991-00500-00-A / SHEET 1/2 - New-Generation Side-Sick Assembly ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

SECTION

A-A 4

4

N_MM_235100_4_AAA0_02_00

Figure 23-51-00-991-00500-00-A / SHEET 2/2 - New-Generation Side-Sick Assembly ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

3.

Job Set-up Subtask 23-51-00-861-055-A A.

Aircraft Maintenance Configuration NOTE: Paragraph 4.A. is only applicable to the side-stick assembly. For the new-generation side-stick assembly, refer to paragraph 4.B. (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

Subtask 23-51-00-865-055-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 11RN (SW-RAD PTT, CAPT) 49VU COM/ACP CAPT/SELCAL/INT 1 AUDIO/AVNCS FOR FIN 12RN (SW-RAD PTT, F/O)

FIN 4RN

LOCATION G06

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-236, 238-250, 301-450, 500-600 49VU COM/AUDIO/ACP/F/O 5RN G07 ** ON A/C 207-207, 210-210, 237-237 49VU COM/ACP F/O/BITE/ INT 2 AUDIO/3&5 OCCPNT

5RN

G07

** ON A/C ALL 4.

Procedure Subtask 23-51-00-010-050-A A.

Disengagement of the Radio PTT Switch (11RN, 12RN) (Ref. Fig. Side Stick Assembly) (1) Remove the screws (1). (2) Remove the cover plate (2). (3) Remove the blanking plug (11), the nut (10), the washer (9) and the trigger (8). (4) Remove the nut (7), the washer (6), the switch (4) with the washer (3).

Subtask 23-51-00-010-056-A B.

Disengagement of the radio Push-to-Talk (PTT) switch (11RN, 12RN) of the new-generation side-stick unit (100CE1, 100CE2) (Ref. Fig. New-Generation Side-Sick Assembly) (1) Remove the screws (1). (2) Remove the cover plate or the tactile indicator (2) according to the Side-Stick Unit (SSU) option. (3) Remove the seal (3).

Subtask 23-51-00-040-050-A C.

Deactivation of the Radio PTT Switch (11RN, 12RN)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

NOTE: Go directly to the paragraph E. for the deactivation of the radio Push-to-Talk (PTT) switch of the new-generation side-stick unit. (1) Do a visual check of the PTT switch wires to see if there are splices already installed: (a) If there are splices installed: · Use the extraction/insertion tool P/N M81969/14.01 from the ELECTRICIAN SERVICE TOOL KIT (DMC519) to disconnect the PTT switch wires from the splices Ref. ESPM 20-43-13. (b) If there is no splice installed: 1

Cut the wires of the PTT switch as follows: a

Before you cut the wires, make sure that the two identification-labels stay on the wires, on the control-handle side.

b

On the two wires, measure 40mm distance "A" from the studs of the PTT switch and make mark on each wire.

c

Cut the two wires at these marks.

d

Install CAP - WIRE END at the end of each wire Ref. ESPM 20-42-13.

Subtask 23-51-00-410-051-A D.

Engagement of the Radio PTT Switch (11RN,12RN) (1) Install the lock plate (3) in the switch (4). (2) Install the switch (4) in the handle. (3) Make sure that the stop of the lock plate (3) is in its housing. (4) Install the washer (6), the nut (7) and tighten it. (5) Install the trigger (8), the washer (9) and the nut (10). CAUTION:

OBEY THE TORQUE VALUES SPECIFIED BELOW.

(6) TORQUE the nut (10) to between 0.0315 and 0.0385 m.daN (2.79 and 3.41 lbf.in). (7) Install the blanking plug (11). (8) Install the cover plate (2). (9) Install the screws (1) and tighten. Subtask 23-51-00-040-053-A E.

Deactivation of the radio Push-to-Talk (PTT) switch (11RN, 12RN) of the new-generation side-stick unit (100CE1, 100CE2) (Ref. Fig. New-Generation Side-Sick Assembly) (1) Pull the two PTT switch wires (green and brown) (4) through the access hole. (2) Cut the power supply wires. (3) Install end caps at the end of each wire Ref. ESPM 20-42-13 connected to the handle connector.

Subtask 23-51-00-410-056-A F.

Engagement of the radio Push-to-Talk (PTT) switch (11RN, 12RN) of the (Ref. Fig. New-Generation Side-Sick Assembly) new-generation side-stick unit (100CE1, 100CE2) (1) Install the seal (3) and the cover plate or tactile indicator (2). (2) Install the screws (1) and tighten them to between 0.15 and 0.18 m.daN (13.27 and 15.93 lbf.in).

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

Subtask 23-51-00-865-056-A G. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 11RN (SW-RAD PTT, CAPT) 49VU COM/ACP CAPT/SELCAL/INT 1 AUDIO/AVNCS FOR FIN 12RN (SW-RAD PTT, F/O)

FIN 4RN

LOCATION G06

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-236, 238-250, 301-450, 500-600 49VU COM/AUDIO/ACP/F/O 5RN G07 ** ON A/C 207-207, 210-210, 237-237 49VU COM/ACP F/O/BITE/ INT 2 AUDIO/3&5 OCCPNT

5RN

G07

** ON A/C ALL Subtask 23-51-00-860-058-A H.

Aircraft Maintenance Configuration (1) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) . (2) Do the IR alignment procedure (Ref. AMM TASK 34-10-00-860-004) . (3) On the overhead panel 23VU: · make sure that the FLT CTL/ELAC 1 and FLT CTL/SEC 1 pushbutton switches are pushed (On these pushbutton switches, the OFF and FAULT legends are off). (4) On the overhead panel 24VU: · make sure that the FLT CTL/ELAC 2, FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches are pushed (On these pushbutton switches, the OFF and FAULT legends are off). (5) On the upper ECAM display unit, make sure that the warnings that follow do not show: · HF1 (2) EMITTING · VHF1 (2) (3) EMITTING · ELAC 1 FAULT · ELAC 2 FAULT · SINGLE PTT STUCK NOTE: If one of these warnings shows, do the trouble shooting procedure related to the maintenance message.

Subtask 23-51-00-710-058-A J.

Operational Tests: (1) Do the Operational test of the Side Stick Priority (Ref. AMM TASK 27-96-00-710-003) . (2) Do the Operational test of the Side Stick Assembly (Ref. AMM TASK 27-96-00-710-020) .

5.

Close-up Subtask 23-51-00-860-059-A A.

Put the aircraft back to its initial configuration. (1) Depressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-864-001) (Ref. AMM TASK 29-24-00-864-001) (Ref. AMM TASK 2910-00-864-003) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-51-00-040-001-A - Deactivation of the Radio Push-to-Talk (PTT) Switch

(2) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (3) Put a WARNING NOTICE(S) on the cover panel of the side stick assembly to tell the crew that the radio PTT switch is deactivated. (4) Make an entry in the logbook. (5) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-73-00-040-002-A - Deactivation of the Forward Attendant Panel

** ON A/C 201-201, 203-205, 207-207, 210-211, 217-217, 219-220, 231-234, 237-237, 240-240, 243-250 TASK 23-73-00-040-002-A Deactivation of the Forward Attendant Panel

FIN : 120RH 1.

Reason for the Job MMEL 23-74-01A Forward Attendant Panel (FAP) Display Unit (FAA only)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Referenced Information REFERENCE (Ref. 11-00-00-400-021-A). (Ref. 23-73-00-740-005-A).

DESIGNATION Installation of the Pressurized Area Placards BITE-Test of the Cabin Intercommunication Data System (CIDS) through the CFDS Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) EIS Start Procedure

(Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 31-60-00-860-001-A). 3.

Job Set-up Subtask 23-73-00-860-187-A A.

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)

4.

Procedure Subtask 23-73-00-865-216-A A.

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

DESIGNATION

FIN

LOCATION

** ON A/C 201-201, 207-207, 210-210 EMB SB 23-1544 for A/C 210-210 121VU COM /CIDS/FLT ATTND/PNL

170RH

Q14

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-73-00-040-002-A - Deactivation of the Forward Attendant Panel

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 203-205, 211-211, 219-220, 231-234, 237-237, 240-240, 243-250 121VU COM NAV/CIDS/FWD ATTND/PNL 170RH Q14 ** ON A/C 217-217 121VU COM/FAP1/NORM

170RH

Q14

** ON A/C 201-201, 203-205, 207-207, 210-211, 217-217, 219-220, 231-234, 237-237, 240-240, 243-250 Subtask 23-73-00-040-051-A B.

Procedure (1) In the cockpit, on the MCDU: · Do the BITE-test of the CIDS through the CFDS. (Ref. AMM TASK 23-73-00-740-005) · Make sure that only FAP-related failure messages show. (2) In the cockpit: · Lift the handset from the cradle. · Push and hold the PTT pushbutton switch and make an announcement. (3) In the cabin: · Make sure that you hear the announcement. (4) Install a placard "INOP" on the deactivated system to tell persons not to use it (Ref. AMM TASK 1100-00-400-021) . (5) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-73-00-040-003-A - Deactivation of the Flight Attendant Panel

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-216, 218-218, 221-230, 235-236, 238-239, 241242, 301-450, 500-600 TASK 23-73-00-040-003-A Deactivation of the Flight Attendant Panel

FIN : 120RH Task Summary MMEL or CDL Ref MMEL 23-74-01B

Access NO

Test NO

1.

Reason for the Job MMEL 23-74-01B Flight Attendant Panel (FAP) Display Unit (FAA only)

2

Job Set-up Information A.

E/T 00.3

Nb Men 1

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Referenced Information REFERENCE (Ref. 11-00-00-400-021-A). (Ref. 23-73-00-740-005-B). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 31-60-00-860-001-A).

3.

Mhr 00.3

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Specific Tools NO

DESIGNATION Installation of the Pressurized Area Placards Interface and Power-Up Test of the Cabin Intercommunication Data System (CIDS) through the CFDS Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) EIS Start Procedure

Job Set-up Subtask 23-73-00-860-192-A A.

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)

4.

Procedure Subtask 23-73-00-865-217-A A.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU

DESIGNATION COM/FAP1/NORM

FIN 170RH

LOCATION Q14

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-73-00-040-003-A - Deactivation of the Flight Attendant Panel

Subtask 23-73-00-040-054-A B.

Procedure (1) In the cockpit, on the MCDU: · Do the Interface and Power-Up test of the CIDS through the CFDS. (Ref. AMM TASK 23-73-00-740-005) · Make sure that only FAP-related failure messages show. (2) In the cockpit: · Lift the handset from the cradle. · Push and hold the PTT pushbutton switch and make an announcement. (3) In the cabin: · Make sure that you hear the announcement. (4) Install a placard "INOP" on the deactivated system to tell persons not to use it (Ref. AMM TASK 1100-00-400-021) . (5) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-73-00-040-004-A - Deactivation of the Flight Attendant Panel - Slide Bottle Pressure Indication, Emergency Exits

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-216, 218-218, 221-230, 235-236, 238-239, 241242, 301-400, 500-600 TASK 23-73-00-040-004-A Deactivation of the Flight Attendant Panel - Slide Bottle Pressure Indication, Emergency Exits

FIN : 120RH Task Summary MMEL or CDL Ref MMEL 23-74-08A

Access NO

Test NO

1.

Reason for the Job MMEL 23-74-08A Slide Bottle Pressure Monitoring on FAP (FAA only)

2

Job Set-up Information A.

E/T 00.6

Nb Men 1

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Referenced Information REFERENCE (Ref. 11-00-00-400-021-A). (Ref. 23-73-00-740-005-B). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 31-60-00-860-001-A).

3.

Mhr 00.6

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Specific Tools NO

DESIGNATION Installation of the Pressurized Area Placards Interface and Power-Up Test of the Cabin Intercommunication Data System (CIDS) through the CFDS Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) EIS Start Procedure

Job Set-up Subtask 23-73-00-860-193-A A.

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)

4.

Procedure Subtask 23-73-00-865-218-A A.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU

DESIGNATION COM/FAP1/NORM

FIN 170RH

LOCATION Q14

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-73-00-040-004-A - Deactivation of the Flight Attendant Panel - Slide Bottle Pressure Indication, Emergency Exits

Subtask 23-73-00-040-055-A B.

Procedure (1) In the aft cargo compartment: · Do the visual check of the slide bottle pressure indication. (Ref. AMM TASK 25-62-00-040-005) (2) In the cockpit, on the MCDU: · Do the Interface and Power-Up test of the CIDS through the CFDS. (Ref. AMM TASK 23-73-00-740-005) · Make sure that only FAP-related failure messages show. (3) In the cockpit: · Lift the handset from the cradle. · Push and hold the PTT pushbutton switch and make an announcement. (4) In the cabin: · Make sure that you hear the announcement. (5) Install a placard "INOP" on the deactivated system to tell persons not to use it (Ref. AMM TASK 1100-00-400-021) . (6) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-73-00-040-005-A - Deactivation of the Programming and Test Panel

** ON A/C 201-201, 203-205, 207-207, 210-211, 217-217, 219-220, 231-234, 237-237, 240-240, 243-250 TASK 23-73-00-040-005-A Deactivation of the Programming and Test Panel

FIN : 110RH Task Summary MMEL or CDL Ref MMEL 23-74-04A

Access NO

1.

Reason for the Job MMEL 23-74-04A PTP Display Unit (FAA only)

2

Job Set-up Information A.

Mhr 00.3

E/T 00.3

Nb Men 1

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Referenced Information REFERENCE (Ref. 11-00-00-400-021-A). (Ref. 23-73-00-740-005-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 31-60-00-860-001-A).

3.

Specific Tools NO

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Test NO

DESIGNATION Installation of the Pressurized Area Placards BITE-Test of the Cabin Intercommunication Data System (CIDS) through the CFDS Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) EIS Start Procedure

Job Set-up Subtask 23-73-00-860-196-A A.

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)

4.

Procedure Subtask 23-73-00-865-219-A A.

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

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-73-00-040-005-A - Deactivation of the Programming and Test Panel

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 201-201, 207-207, 210-210, 217-217 EMB SB 23-1544 for A/C 210-210 121VU COM NAV/CIDS/PROG &/TST PNL

161RH

M07

** ON A/C 203-205, 211-211, 219-220, 231-234, 237-237, 240-240, 243-250 121VU COM NAV/CIDS/PROG AND TST PNL 161RH M06 ** ON A/C 201-201, 203-205, 207-207, 210-211, 217-217, 219-220, 231-234, 237-237, 240-240, 243-250 Subtask 23-73-00-040-057-A B.

Procedure (1) In the cockpit, on the MCDU: · Do the BITE-test of the CIDS through the CFDS. (Ref. AMM TASK 23-73-00-740-005) · Make sure that only PTP-related failure messages show. (2) In the cockpit: · Lift the handset from the cradle. · Push and hold the PTT pushbutton switch and make an announcement. (3) In the cabin: · Make sure that you hear the announcement. (4) Install a placard "INOP" on the deactivated system to tell persons not to use it (Ref. AMM TASK 1100-00-400-021) . (5) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-73-00-040-006-A - Deactivation of the Programming and Test Panel - Slide Bottle Pressure Indication, Emergency Exits

** ON A/C 201-201, 203-205, 207-207, 210-211, 217-217, 219-220, 231-234, 237-237, 240-240, 243-250 TASK 23-73-00-040-006-A Deactivation of the Programming and Test Panel - Slide Bottle Pressure Indication, Emergency Exits

FIN : 110RH Task Summary MMEL or CDL Ref MMEL 23-74-07A

Access NO

Test NO

1.

Reason for the Job MMEL 23-74-07A Slide Bottle Pressure Monitoring on PTP (FAA only)

2

Job Set-up Information A.

E/T 00.6

Nb Men 1

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Referenced Information REFERENCE (Ref. 11-00-00-400-021-A). (Ref. 23-73-00-740-005-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 25-62-00-040-001-A).

(Ref. 31-60-00-860-001-A). 3.

Mhr 00.6

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Specific Tools NO

DESIGNATION Installation of the Pressurized Area Placards BITE-Test of the Cabin Intercommunication Data System (CIDS) through the CFDS Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) Check of the Emergency-Exit Slide-Bottle Pressure because of a Low Pressure Indication on the Programming and Test Panel or Flight Attendant Panel EIS Start Procedure

Job Set-up Subtask 23-73-00-860-197-A A.

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)

4.

Procedure Subtask 23-73-00-865-220-A A.

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

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-73-00-040-006-A - Deactivation of the Programming and Test Panel - Slide Bottle Pressure Indication, Emergency Exits

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 201-201, 207-207, 210-210, 217-217 EMB SB 23-1544 for A/C 210-210 121VU COM NAV/CIDS/PROG &/TST PNL

161RH

M07

** ON A/C 203-205, 211-211, 219-220, 231-234, 237-237, 240-240, 243-250 121VU COM NAV/CIDS/PROG AND TST PNL 161RH M06 ** ON A/C 201-201, 203-205, 207-207, 210-211, 217-217, 219-220, 231-234, 237-237, 240-240, 243-250 Subtask 23-73-00-040-058-A B.

Procedure (1) In the aft cargo compartment: · Do the visual check of the slide bottle pressure indication. (Ref. AMM TASK 25-62-00-040-001) (2) In the cockpit, on the MCDU: · Do the BITE-test of the CIDS through the CFDS. (Ref. AMM TASK 23-73-00-740-005) · Make sure that only PTP-related failure messages show. (3) In the cockpit: · Lift the handset from the cradle. · Push and hold the PTT pushbutton switch and make an announcement. (4) In the cabin: · Make sure that you hear the announcement in all cabin areas. (5) Install a placard "INOP" on the deactivated system to tell persons not to use it (Ref. AMM TASK 1100-00-400-021) . (6) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-73-00-040-007-A - Deactivation of the Programming and Test Panel - Emergency System Test, Cabin Emergency Lighting System

** ON A/C 201-201, 203-205, 207-207, 210-211, 217-217, 219-220, 231-234, 237-237, 240-240, 243-250 TASK 23-73-00-040-007-A Deactivation of the Programming and Test Panel - Emergency System Test, Cabin Emergency Lighting System

FIN : 110RH Task Summary MMEL or CDL Ref MMEL 23-74-01A

Access NO

Test NO

1.

Reason for the Job MMEL 23-74-01A SYS Test Pb on the PTP (FAA only)

2

Job Set-up Information A.

E/T 00.3

Nb Men 1

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Referenced Information REFERENCE (Ref. 11-00-00-400-021-A). (Ref. 23-73-00-740-005-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 33-51-00-040-001-A).

3.

Mhr 00.3

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Specific Tools NO

DESIGNATION Installation of the Pressurized Area Placards BITE-Test of the Cabin Intercommunication Data System (CIDS) through the CFDS Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) EIS Start Procedure Deactivation of the EMER SYSTEM TEST of the Cabin Emergency Lighting System

Job Set-up Subtask 23-73-00-860-198-A A.

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)

4.

Procedure Subtask 23-73-00-865-221-A A.

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

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 23-73-00-040-007-A - Deactivation of the Programming and Test Panel - Emergency System Test, Cabin Emergency Lighting System

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 201-201, 207-207, 210-210, 217-217 EMB SB 23-1544 for A/C 210-210 121VU COM NAV/CIDS/PROG &/TST PNL

161RH

M07

** ON A/C 203-205, 211-211, 219-220, 231-234, 237-237, 240-240, 243-250 121VU COM NAV/CIDS/PROG AND TST PNL 161RH M06 ** ON A/C 201-201, 203-205, 207-207, 210-211, 217-217, 219-220, 231-234, 237-237, 240-240, 243-250 Subtask 23-73-00-040-059-A B.

Procedure (1) In the cockpit: · Do the check of the cabin emergency lighting system. (Ref. AMM TASK 33-51-00-040-001) (2) In the cockpit, on the MCDU: · Do the BITE-test of the CIDS through the CFDS. (Ref. AMM TASK 23-73-00-740-005) · Make sure that only PTP-related failure messages show. (3) In the cockpit: · Lift the handset from the cradle. · Push and hold the PTT pushbutton switch and make an announcement. (4) In the cabin: · Make sure that you hear the announcement. (5) Install a placard "INOP" on the deactivated system to tell persons not to use it (Ref. AMM TASK 1100-00-400-021) . (6) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-50-00-040-001-A - Deactivation of the C/ B TRIPPED Warning on the Upper ECAM DU

** ON A/C ALL TASK 24-50-00-040-001-A Deactivation of the C/B TRIPPED Warning on the Upper ECAM DU 1.

Reason for the Job MMEL 24-09-02A C/B TRIPPED Alert

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS 812, 822

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). 3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure

Job Set-up Subtask 24-50-00-860-054-A A.

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) .

Subtask 24-50-00-010-051-A B.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 822. (2) Open the access door 822. (3) On the battery power center 105VU: · Loosen the two screws and remove the protective cover.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-50-00-040-001-A - Deactivation of the C/ B TRIPPED Warning on the Upper ECAM DU

(4) Open the access door 812. (5) On the AC/DC emergency power center 106VU: · Loosen the five screws and remove the protective cover. 4.

Procedure Subtask 24-50-00-040-052-A A.

Check for C/B TRIPPED (1) If the C/B TRIPPED ECAM warning comes into view, do this check: ACTION 1.If the C/B TRIPPED ON OVHD PANEL warning comes into view on the upper ECAM DU: · On the overhead circuit breaker panel 49VU, · make sure that all the circuit breakers are closed. 2.If the C/B TRIPPED R ELEC BAY warning comes into view on the upper ECAM DU: · On the battery power center 105VU, make sure · that all the circuit breakers are closed. 3.If the C/B TRIPPED L ELEC BAY warning comes into view on the upper ECAM DU: · On the AC/DC emergency power center · 106VU, make sure that all the circuit breakers are closed. 4.If the C/B TRIPPED REAR PNL J-M warning comes into view on the upper ECAM DU: · On the rear circuit breaker panel 121VU · between lines J and M, make sure that all the circuit breakers are closed. 5.If the C/B TRIPPED REAR PNL N-R warning comes into view on the upper ECAM DU: · On the rear circuit breaker panel 121VU · between lines N and R, make sure that all the circuit breakers are closed. 6.If C/B TRIPPED REAR PNL S-V warning comes into view on the upper ECAM DU: · On the rear circuit breaker panel 122VU · between lines S and V, make sure that all the circuit breakers are closed. 7.If the C/B TRIPPED REAR PNL W-Z warning comes into view on the upper ECAM DU: · On the rear circuit breaker panel 122VU · between lines W and Z, make sure that all the circuit breakers are closed.

5.

RESULT

If all the circuit breakers are closed, no maintenance procedure is necessary.

If all the circuit breakers are closed, no maintenance procedure is necessary.

If all the circuit breakers are closed, no maintenance procedure is necessary.

If all the circuit breakers are closed, no maintenance procedure is necessary.

If all the circuit breakers are closed, no maintenance procedure is necessary.

If all the circuit breakers are closed, no maintenance procedure is necessary.

If all the circuit breakers are closed, no maintenance procedure is necessary.

Close-up Subtask 24-50-00-410-051-A A.

Close Access (1) Install the protective cover on the battery power center 105VU.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-50-00-040-001-A - Deactivation of the C/ B TRIPPED Warning on the Upper ECAM DU

(2) Tighten the two screws. (3) Install the protective cover on the AC/DC emergency power center 106VU. (4) Tighten the five screws. (5) Close the access doors 822 and 812. (6) Make sure that the work area is clean and clear of tools and other items. (7) Remove the access platform(s). Subtask 24-50-00-860-055-A B.

Put the aircraft back to its initial 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) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-802-A - Check of the Maintenance Condition of the IDG 1(2)

** ON A/C 301-349, 351-450, 500-600 TASK 24-20-00-040-802-A Check of the Maintenance Condition of the IDG 1(2) WARNING:

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

1.

Reason for the Job MMEL 24-09-03A ELEC IDG 1(2) OIL LO LVL Alert MMEL 24-09-04A ELEC IDG 1(2) FILTER CLOG Alert

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific

B.

QTY 1 AR AR AR AR

DESIGNATION ACCESS PLATFORM 1M(3 FT) AIR SOURCE FILTERED, DRY LIGHT SOURCE - INSPECTION MIRROR - INSPECTION WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. 08BBB1) (Material No. 14SBA1)

DESIGNATION Non Aqueous Cleaner-- Petroleum Based Textile-Lint free Cotton -

C. Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTION FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR, 451AL FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR, 461AL D. Referenced Information REFERENCE DESIGNATION (Ref. 71-13-00-010-802-A). Opening of the Fan Cowl Doors (Ref. 71-13-00-410-802-A). Closing of the Fan Cowl Doors (Ref. 78-30-00-040-805-A). Deactivation of the Thrust Reverser System for Ground Maintenance (Ref. 78-30-00-440-805-A). Reactivation of the Thrust Reverser System after Ground Maintenance (Ref. 78-36-00-010-802-A). Opening of the Thrust Reverser Cowl-Doors (Ref. 78-36-00-410-802-A). Closing of the Thrust Reverser Cowl-Doors IDG Oil Level Sight Glass and DPI SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-802-A - Check of the Maintenance Condition of the IDG 1(2)

INTEGRATED DRIVE GENERATOR (IDG)

DPI BUTTON

A

C D B

IDG OIL LEVEL SIGHTGLASS

A RED

YELLOW 01

01

GREEN RED

B

NORMAL (RESET)

EXTENDED

C

D

FWD

NOTE: 01 DPI BUTTON (SILVER END, RED CYLINDRICAL SIDE)

N_MM_242000_4_PAM0_01_01

Figure 24-20-00-991-00500-00-A / SHEET 1/1 - IDG Oil Level Sight Glass and DPI ** ON A/C 301-349, 351-450, 500-600 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-802-A - Check of the Maintenance Condition of the IDG 1(2)

3.

Job Set-up Subtask 24-20-00-941-052-A A.

Safety Precautions (1) 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. (c) Put WARNING NOTICE(S) in position to tell persons not to operate the ENG/MODE selector switch and the ENG/MASTER 1(2) control switch. (2) 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) Put WARNING NOTICE(S) in position to tell persons not to energize FADEC 1(2). (3) Wait ten minutes after the engine shutdown.

Subtask 24-20-00-010-053-A B.

Get Access (1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR

Subtask 24-20-00-040-053-A C.

Deactivation of the Thrust Reverser System for Ground Maintenance 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) Do the deactivation of the thrust reverser system for ground maintenance (Ref. AMM TASK 78-3000-040-805) .

Subtask 24-20-00-010-054-A D.

Get Access (1) Open the left thrust-reverser cowl-door (Ref. AMM TASK 78-36-00-010-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 451AL (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 461AL (2) Put an ACCESS PLATFORM 1M(3 FT) in position.

4.

Procedure (Ref. Fig. IDG Oil Level Sight Glass and DPI SHEET 1) Subtask 24-20-00-160-050-A A.

Cleaning of the IDG Oil Sight-Glass for Correct Conditions WARNING: DO NOT GET THE FLUID ON YOUR SKIN OR IN YOUR EYES. IF YOU DO: - FLUSH IT AWAY WITH CLEAN WATER

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-802-A - Check of the Maintenance Condition of the IDG 1(2)

- GET MEDICAL AID. (1) Make sure that the IDG oil sight-glass is clean. (a) If the IDG oil sight-glass is not clean: · Clean the sight glass with Non Aqueous Cleaner-- Petroleum Based - (Material No. 08BBB1), and · Remove the remaining solvent with a clean Textile-Lint free Cotton - (Material No. 14SBA1) or blow air on the sight glass with a AIR SOURCE FILTERED, DRY to dry it. (b) If the IDG oil sight-glass is clean: Go to Para. B. of the Procedure. Subtask 24-20-00-210-055-A B.

Check of the IDG Maintenance Conditions CAUTION:

DO NOT DO THIS TASK IF THE IDG IS DISCONNECTED. BEFORE YOU DO A CHECK OF THE IDG OIL LEVEL, MAKE SURE THAT THE IDG IS CONNECTED. A DISCONNECTED IDG CAN CAUSE AN INCORRECT OIL QUANTITY INDICATION AND THUS INCORRECT SERVICING. IF THE LEVEL IS TOO HIGH OR TOO LOW, DAMAGE CAN OCCUR TO THE IDG WHEN IT OPERATES.

CAUTION:

DO NOT OPERATE THE IDG WITHOUT SUFFICIENT OIL. THIS WILL CAUSE DAMAGE TO THE IDG.

(1) Make sure that the IDG oil level at the sight glass is not in the lower red band. (2) Make sure that the red button of the IDG DPI oil filter is not extended. · Use an LIGHT SOURCE - INSPECTION and an MIRROR - INSPECTION, if necessary. 5.

Close-up Subtask 24-20-00-410-053-A A.

Put the aircraft back to its initial configuration. (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the left thrust-reverser cowl-door (Ref. AMM TASK 78-36-00-410-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 451AL (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 461AL

Subtask 24-20-00-440-054-A B.

Reactivation of the Thrust Reverser System after Ground Maintenance (1) Do the reactivation of the thrust reverser system after ground maintenance (Ref. AMM TASK 78-3000-440-805) .

Subtask 24-20-00-410-054-A C.

Close Access (1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-802-A - Check of the Maintenance Condition of the IDG 1(2)

(2) Remove the WARNING NOTICE(S).

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-803-A - Disconnection of the Defective IDG and Draining of the IDG Oil

** ON A/C 301-349, 351-450, 500-600 TASK 24-20-00-040-803-A Disconnection of the Defective IDG and Draining of the IDG Oil 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:

WEAR GOGGLES, INSULATED GLOVES AND OTHER PROTECTIVE CLOTHES. HOT OIL CAN BURN YOUR EYES AND SKIN. IF OIL TOUCHES YOUR EYES OR SKIN, GET MEDICAL AID.

WARNING:

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

WARNING:

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

CAUTION:

DO NOT LET ENGINE OIL FALL ON THE ENGINE. UNWANTED OIL MUST BE REMOVED IMMEDIATELY. THE OIL CAN CAUSE DAMAGE TO THE SURFACE PROTECTION AND TO SOME PARTS.

CAUTION:

DO NOT USE SOLVENTS THAT CONTAIN CHLORINE TO CLEAN THE EQUIPMENT (PUMP, HOSES, TANK AND FUNNEL) USED TO FILL THE IDG WITH OIL. CHLORINE CONTAMINATION OF THE OIL CAN CAUSE FAST DETERIORATION OF THE OIL AND WILL DECREASE THE LIFE OF THE IDG.

CAUTION:

DO NOT OPERATE THE IDG: - IF IT CONTAINS TOO MUCH OIL - IF IT DOES NOT CONTAIN ENOUGH OIL IF YOU DO, YOU CAN CAUSE DAMAGE TO THE IDG.

1.

Reason for the Job MMEL 24-09-03D ELEC IDG 1(2) OIL LO LVL Alert

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific

B.

QTY 2 AR AR AR AR AR

DESIGNATION ACCESS PLATFORM 1M(3 FT) AIR SOURCE FILTERED, DRY COVER - PROTECTION LIGHT SOURCE - INSPECTION MIRROR - INSPECTION WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. 08BBB1)

DESIGNATION Non Aqueous Cleaner-- Petroleum Based -

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-803-A - Disconnection of the Defective IDG and Draining of the IDG Oil

REFERENCE (Material No. 14SBA1)

DESIGNATION Textile-Lint free Cotton -

C. Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTION FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR, 451AL FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR, 461AL D. Referenced Information REFERENCE (Ref. 12-13-24-680-802-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Draining of the Oil from the IDG Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 31-60-00-860-001-A). EIS Start Procedure (Ref. 31-60-00-860-002-A). EIS Stop Procedure (Ref. 71-00-00-860-814-A). Shutdown of the Engine (Ref. 71-00-00-860-823-A). Start the Engine (Normal Automatic Start) (Ref. 71-13-00-010-802-A). Opening of the Fan Cowl Doors (Ref. 71-13-00-410-802-A). Closing of the Fan Cowl Doors (Ref. 78-30-00-040-805-A). Deactivation of the Thrust Reverser System for Ground Maintenance (Ref. 78-30-00-440-805-A). Reactivation of the Thrust Reverser System after Ground Maintenance (Ref. 78-36-00-010-802-A). Opening of the Thrust Reverser Cowl-Doors (Ref. 78-36-00-410-802-A). Closing of the Thrust Reverser Cowl-Doors Ref. TSM 24-21-00-810-815 The Differential Pressure Indicator (DPI) of the IDG1 Oil Filter is Extended - Alternate Procedure Ref. TSM 24-21-00-810-816 The Differential Pressure Indicator (DPI) of the IDG2 Oil Filter is Extended - Alternate Procedure IDG Oil Level Sight Glass and DPI SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-803-A - Disconnection of the Defective IDG and Draining of the IDG Oil

INTEGRATED DRIVE GENERATOR (IDG)

DPI BUTTON

A

C D B

IDG OIL LEVEL SIGHTGLASS

A RED

YELLOW 01

01

GREEN RED

B

NORMAL (RESET)

EXTENDED

C

D

FWD

NOTE: 01 DPI BUTTON (SILVER END, RED CYLINDRICAL SIDE)

N_MM_242000_4_PAM0_01_01

Figure 24-20-00-991-00500-00-A / SHEET 1/1 - IDG Oil Level Sight Glass and DPI ** ON A/C 301-349, 351-450, 500-600 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-803-A - Disconnection of the Defective IDG and Draining of the IDG Oil

3.

Job Set-up Subtask 24-20-00-941-051-A A.

Safety Precautions (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) On the ECAM control panel, push the ELEC key to get the ELEC page. (4) 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) Put WARNING NOTICE(S) in position to tell persons not to operate the ENG/MODE selector switch and the ENG/MASTER 1(2) control switch. (5) 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) Put WARNING NOTICE(S) in position to tell persons not to energize FADEC 1(2).

Subtask 24-20-00-010-051-A B.

Get Access (1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR

Subtask 24-20-00-040-052-A C.

Deactivation of the Thrust Reverser System for Ground Maintenance 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) Do the deactivation of the thrust reverser system for ground maintenance (Ref. AMM TASK 78-3000-040-805) .

Subtask 24-20-00-010-052-A D.

Get Access (1) Open the left thrust-reverser cowl-door (Ref. AMM TASK 78-36-00-010-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 451AL (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 461AL (2) Put an ACCESS PLATFORM 1M(3 FT) in position.

4.

Procedure (Ref. Fig. IDG Oil Level Sight Glass and DPI SHEET 1)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-803-A - Disconnection of the Defective IDG and Draining of the IDG Oil

Subtask 24-20-00-160-051-A A.

Cleaning of the IDG Oil Sight-Glass for Correct Conditions WARNING: DO NOT GET THE FLUID ON YOUR SKIN OR IN YOUR EYES. IF YOU DO: - FLUSH IT AWAY WITH CLEAN WATER - GET MEDICAL AID. (1) Make sure that the IDG oil sight-glass is clean. (a) If the IDG oil sight-glass is not clean: · Clean the sight glass with Non Aqueous Cleaner-- Petroleum Based - (Material No. 08BBB1), and · Remove the remaining solvent with a clean Textile-Lint free Cotton - (Material No. 14SBA1) or blow air on the sight glass with a AIR SOURCE FILTERED, DRY to dry it. (b) If the IDG oil sight-glass is clean, continue the maintenance procedure.

Subtask 24-20-00-210-056-A B.

Check of the IDG Maintenance Conditions (1) Make sure that the red button of the DPI of the oil filter is not extended. Use an LIGHT SOURCE - INSPECTION and an MIRROR - INSPECTION, if necessary. (a) If the red button of the DPI of the oil filter is extended: · Do the troubleshooting procedure for the DPI of the oil-filter that is extended Ref. TSM 24-2100-810-815 or Ref. TSM 24-21-00-810-816 . (2) Make sure that the IDG oil level is not lower red band. · If the IDG oil level is lower red band, continue the maintenance procedure.

Subtask 24-20-00-210-057-A C.

Visual Inspection of IDG for Oil Leaks NOTE: Do not a visual inspection for oil leaks at the drain mast. (1) Do a visual inspection of these components: NOTE: There can be different signs of possible leaks: · Droplets of oil · Wet areas around connections, oil stripes on tubes · Stains or discoloration which can occur when oil or grease goes on very hot surfaces. (a) IDG fittings, plug or valves for leaks: · Pressure fill port · Overflow drain port · Oil-in and oil-out ports (cooling system interface with the IDG) · Case drain. (b) External oil system (oil lines) for leaks: · Tubing. (c) IDG fuel/oil heat-exchanger for leaks: · Oil-in and oil-out fittings of the thermal management system module · Body of the heat exchanger. (d) IDG oil/oil heat-exchanger for leaks: · Oil-in and oil-out fittings of the thermal management system module · Body of the heat exchanger.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-803-A - Disconnection of the Defective IDG and Draining of the IDG Oil

(2) If you find signs of oil leaks: (a) Make an entry in the log book to record the position of the oil leaks. (b) Continue the maintenance procedure. Subtask 24-20-00-410-055-A D.

Close Access (1) Remove the ACCESS PLATFORM 1M(3 FT). (2) Close the left thrust-reverser cowl-door (Ref. AMM TASK 78-36-00-410-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 451AL (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 461AL

Subtask 24-20-00-440-055-A E.

Reactivation of the Thrust Reverser System after Ground Maintenance (1) Do the reactivation of the thrust reverser system after ground maintenance (Ref. AMM TASK 78-3000-440-805) .

Subtask 24-20-00-410-056-A F.

Close Access (1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR (2) Remove the WARNING NOTICE(S).

Subtask 24-20-00-860-059-A G. 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) On the ECAM control panel, push the ELEC key to get the ELEC page. Subtask 24-20-00-865-054-A H.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL FOR FIN 4000XU1 122VU 122VU FOR FIN 4000XU2 122VU 122VU

DESIGNATION (IDG-ENG 1) ELEC/GCU/1 ELEC/IDG1/DISC (IDG-ENG 2) ELEC/GCU/2 ELEC/IDG2/DISC

FIN

LOCATION

2XU1 1XT

T26 T24

2XU2 2XT

T27 T25

Subtask 24-20-00-020-050-A J.

Disconnection of the IDG

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-803-A - Disconnection of the Defective IDG and Draining of the IDG Oil

(1) Start the engine 1(2) (Ref. AMM TASK 71-00-00-860-823) . (2) Make sure that at least the IDG 1(2) and the external power or the APU generator energize the electrical circuits. NOTE: This test is for the system 1. For the other system(s), use the indications between the parentheses.

ACTION RESULT 1.With the engine 1(2) at idle speed, on ELEC On ELEC control panel 35VU: control panel 35VU: · The FAULT legend of the related GEN pushbut· Lift the guard and push the IDG1(2) pushbutton ton switch comes on. switch. On the lower ECAM DU, on the ELEC page: · The load voltage of the related generator are zero. · The frequency parameters of the related generator are amber crosses. · The amber DISC indication comes into view below the IDG indication. · The external power energizes the aircraft electrical circuits. 2.On ELEC control panel 35VU: On ELEC control panel 35VU: · Release the GEN 1(2) pushbutton switch. · The FAULT legend of the related GEN pushbutton switch goes off, · The OFF legend of the related GEN pushbutton switch comes on. 3.On ELEC control panel 35VU: · Lower the safety guard of the IDG1(2) pushbutton switch. (3) Make an entry in the log book to tell persons that you disconnect the IDG(1)2. (4) Stop the engine 1(2) (Ref. AMM TASK 71-00-00-860-814) . Subtask 24-20-00-941-053-A K.

Safety Precautions (1) 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. (2) 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).

Subtask 24-20-00-010-055-A L.

Get Access

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-803-A - Disconnection of the Defective IDG and Draining of the IDG Oil

(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR Subtask 24-20-00-040-054-A M. Deactivation of the Thrust Reverser System for Ground Maintenance 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) Do the deactivation of the thrust reverser system for ground maintenance (Ref. AMM TASK 78-3000-040-805) . Subtask 24-20-00-010-056-A N.

Get Access (1) Open the left thrust-reverser cowl-door (Ref. AMM TASK 78-36-00-010-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 451AL (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 461AL (2) Put an ACCESS PLATFORM 1M(3 FT) in position. (3) Installation of the engine protection covers CAUTION: INSTALL PROTECTION COVERS ON ALL THE OPENINGS IMMEDIATELY TO PREVENT DAMAGE TO THE ENGINE. (a) Install all the necessary COVER - PROTECTION to prevent damage to the engine.

Subtask 24-20-00-680-050-A P.

Draining of the Oil from the IDG1(2) (1) Drain the oil from the IDG (Ref. AMM TASK 12-13-24-680-802) .

Subtask 24-20-00-710-057-A CAUTION:

REPLACE THE IDG1(2) BEFORE NEXT ENGINE START IF: - THE IDG1(2) WAS MECHANICALLY DISCONNECTED, AND - THE FAULT MESSAGE "IDG1(E1-4000XU) OIL DELTA TEMP/GCU1 (1XU1)" OR "IDG2(E2-4000XU) OIL DELTA TEMP/GCU2 (1XU2)" IS THEN SHOWN ON THE PFR OR LAST LEG REPORT. THIS FAULT MESSAGE SHOWS THAT THE IDG IS STILL MECHANICALLY CONNECTED. THIS CAN CAUSE HEAVY DAMAGE TO THE IDG AT THE NEXT ENGINE START.

CAUTION:

AFTER YOU DISCONNECT IDG1(2) AND DRAIN THE OIL: - DO NOT DO THE SERVICING AND CONNECT THE DISCONNECTED IDG1(2), - REPLACE IDG1(2). IF YOU DO NOT OBEY THESE INSTRUCTIONS, YOU WILL INCREASE THE DAMAGE TO IDG1(2) AT THE NEXT ENGINE START.

Q. CAUTION to Prevent Damage to IDG1(2)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-803-A - Disconnection of the Defective IDG and Draining of the IDG Oil

5.

Close-up Subtask 24-20-00-410-051-A A.

Put the aircraft back to its initial configuration. (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the left thrust-reverser cowl-door (Ref. AMM TASK 78-36-00-410-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 451AL (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 461AL

Subtask 24-20-00-440-053-A B.

Reactivation of the Thrust Reverser System after Ground Maintenance (1) Do the reactivation of the thrust reverser system after ground maintenance (Ref. AMM TASK 78-3000-440-805) .

Subtask 24-20-00-410-052-A C.

Close Access (1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR (2) Remove the WARNING NOTICE(S).

Subtask 24-20-00-862-059-A D.

Put the aircraft back to its initial configuration. (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-001-A - Check of the AC Main Generation Maintenance Condition

** ON A/C ALL TASK 24-20-00-040-001-A Check of the AC Main Generation Maintenance Condition CAUTION:

MAKE SURE THAT THE IDG DOES NOT OPERATE FOR MORE THAN 50 HOURS IN THE DISCONNECTED MODE. - IF THE IDG OPERATES FOR 50 HOURS IN THE DISCONNECTED MODE, IT WILL BE NECESSARY TO : - REPLACE THE IDG. - SEND THE REMOVED IDG FOR A SHOP INSPECTION. THERE IS A RISK OF DAMAGE TO THE BALL BEARING ASSEMBLY ON THE IMPUT SHAFT.

NOTE: The procedure is the same for IDG1 (IDG2). 1.

Reason for the Job MMEL 24-22-01A AC Main Generation (IDG, GCU, Line Contactor)

2

Job Set-up Information A.

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

(Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure

** ON A/C 201-201, 233-233 (Ref. 49-00-00-860-003-A). (Ref. 49-00-00-860-003-A-01). (Ref. 49-00-00-860-004-A). (Ref. 49-00-00-860-004-A-01).

APU Start by External Power APU Start by Batteries APU Shutdown by External Power APU Shutdown by Batteries

(Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 (Ref. 49-00-00-860-005-A). APU Start by External Power (Ref. 49-00-00-860-005-A-01). APU Start by Batteries (Ref. 49-00-00-860-006-A). APU Shutdown by External Power (Ref. 49-00-00-860-006-A-01). APU Shutdown by Batteries

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-001-A - Check of the AC Main Generation Maintenance Condition

REFERENCE

DESIGNATION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 (Ref. 49-00-00-860-008-A). APU Start by External Power (Ref. 49-00-00-860-008-A-01). APU Start by Batteries (Ref. 49-00-00-860-009-A). APU Shutdown by External Power (131-9(A)) (Ref. 49-00-00-860-009-A-01). APU Shutdown by Batteries (131-9(A)) ** ON A/C 201-201, 233-233 (Ref. 49-90-00-600-001-A).

Check Oil Level and Replenish (GTCP 36-300)

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 (Ref. 49-90-00-600-004-A). Check Oil Level and Replenish (APS 3200) ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 (Ref. 49-90-00-600-007-A). Check Oil Level and Replenish (131-9(A)) ** ON A/C ALL Oil Consumption of the APU GTCP 36-300 SHEET 1 Oil Consumption of the APU APS 3200 SHEET 1 Oil Consumption of the APU 131-9(A) SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 9

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

0

2

6

1.5

0.5

8

2.0

4

10

2.5

1.0

12

3.0

18

4.5

14

20

5.0

3.5

22

5.5

16

24

6.0

4.0

26

6.5

10

30

GRAPH A

40

50

60

70

80

90

OIL QUANTITY IN THE APU OIL RESERVOIR IS SUFFICIENT FOR MINIMUM 10 HOURS APU OPERATION WITHOUT PREFLIGHT SERVICE IF NO "LOW OIL LEVEL" INDICATION IS SHOWN.

APU OPERATING TIME (HOURS)

20

GRAPH B

OIL QUANTITY IN THE APU OIL RESERVOIR IS SUFFICIENT FOR 10 HOURS APU OPERATION IF SERVICED BEFORE FLIGHT TO THE "FULL" MARK ON THE OIL SIGHT GLASS.

OIL QUANTITY IN THE APU OIL RESERVOIR IS NOT SUFFICIENT FOR 10 HOURS APU OPERATION

(US. GALLONS) (QUARTS)

100

1.9

3.8

5.7

7.6

9.5

11.4

13.3

15.1

17.0

18.9

20.8

22.7

24.6

(LITRES)

THE ADDED OIL (CUMULATIVE) (VERTICAL SCALE) IS THE TOTAL QUANTITY OF OIL WHICH WAS ADDED TO THE APU OIL RESERVOIR IN ORDER TO COMPENSATE FOR THE APU OIL CONSUMPTION DURING AN APU OPERATING TIME PERIOD (HORIZONTAL SCALE).

NOTE:

OIL CONSUMPTION IS THE TERM USED FOR THE INTERNAL LOSS OF OIL FROM BEARING SEALS AND AIR/OIL SEPARATOR DURING APU OPERATION. EXTERNAL LEAKS ARE NOT PERMITTED. YOU MUST CORRECT EXTERNAL LEAKS AND CLEAN THE APU, APU COMPARTMENT AND APU AIR INTAKE IMMEDIATELY IF CONTAMINATED. IF THE OIL CONSUMPTION IS HIGHER THAN THE "GRAPH A" LIMIT, OR THERE IS A SUDDEN INCREASE IN OIL CONSUMPTION, YOU MUST DO THE OIL CONSUMPTION MONITORING VERY CAREFULLY TO PREVENT BAD APU DAMAGE.

CAUTION:

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-001-A - Check of the AC Main Generation Maintenance Condition

ADDED OIL (CUMULATIVE)

N_MM_242000_4_AAM0_01_00

Figure 24-20-00-991-00200-00-A / SHEET 1/1 - Oil Consumption of the APU GTCP 36-300 ** ON A/C ALL

Page 3 of 9

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

0

2

6

1.5

0.5

8

2.0

4

10

2.5

1.0

12

3.0

18

4.5

14

20

5.0

3.5

22

5.5

16

24

6.0

4.0

26

6.5

10

30

40

50

60

70

80

90

OIL QUANTITY IN THE APU OIL RESERVOIR IS SUFFICIENT FOR MINIMUM 10 HOURS APU OPERATION WITHOUT PREFLIGHT SERVICE IF NO "LOW OIL LEVEL" INDICATION IS SHOWN.

GRAPH A

APU OPERATING TIME (HOURS)

20

GRAPH B

OIL QUANTITY IN THE APU OIL RESERVOIR IS SUFFICIENT FOR 10 HOURS APU OPERATIO IF SERVICED BEFORE FLIGHT TO THE "FULL" MARK ON THE OIL SIGHT GLASS.

OIL QUANTITY IN THE APU OIL RESERVOIR IS NOT SUFFICIENT FOR 10 HOURS APU OPERATION

(US. GALLONS) (QUARTS)

100

1.9

3.8

5.7

7.6

9.5

11.4

13.3

15.1

17.0

18.9

20.8

22.7

24.6

(LITRES)

THE ADDED OIL (CUMULATIVE) (VERTICAL SCALE) IS THE TOTAL QUANTITY OF OIL WHICH WAS ADDED TO THE APU OIL RESERVOIR IN ORDER TO COMPENSATE FOR THE APU OIL CONSUMPTION DURING AN APU OPERATING TIME PERIOD (HORIZONTAL SCALE).

NOTE:

OIL CONSUMPTION IS THE TERM USED FOR THE INTERNAL LOSS OF OIL FROM BEARING SEALS AND AIR/OIL SEPARATOR DURING APU OPERATION. EXTERNAL LEAKS ARE NOT PERMITTED. YOU MUST CORRECT EXTERNAL LEAKS AND CLEAN THE APU, APU COMPARTMENT AND APU AIR INTAKE IMMEDIATELY IF CONTAMINATED. IF THE OIL CONSUMPTION IS HIGHER THAN THE "GRAPH A" LIMIT, OR THERE IS A SUDDEN INCREASE IN OIL CONSUMPTION, YOU MUST DO THE OIL CONSUMPTION MONITORING VERY CAREFULLY TO PREVENT BAD APU DAMAGE.

CAUTION:

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-001-A - Check of the AC Main Generation Maintenance Condition

ADDED OIL (CUMULATIVE)

N_MM_242000_4_ABM0_01_00

Figure 24-20-00-991-00300-00-A / SHEET 1/1 - Oil Consumption of the APU APS 3200 ** ON A/C ALL

Page 4 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-001-A - Check of the AC Main Generation Maintenance Condition

CUMULATIVE OIL ADDED QUARTS (GALLONS)

QUARTS (US GALLONS)

LITERS

20 (4.16)

18.9

18 (3.74)

17.0

16 (3.32)

15.1

UNSATISFACTORY CONSUMPTION

14 (2.9) 12 (2.51)

13.2 UNUSUAL OIL CONSUMPTION USE APU ONLY WHEN OIL IS FILLED BEFORE EACH FLIGHT

0.196qt/hr (185cc/hr)

10 (2.07)

11.4 9.4

8 (1.67)

7.6

6 (1.25)

5.7

0.099qt/hr (93cc/hr)

4 (0.84)

3.8

SATISFACTORY CONSUMPTION

2 (0.42)

1.9

0.0

0.0 10

20

30

40

50

60

70

80

90

100

APU OPERATING TIME (HOURS)

NOTE: MAXIMUM OIL CONSUMPTION FOR NEW OR NEWLY OVERHAULED APU IS 0.007qt(6.5cc)AN HOUR

N_MM_242000_4_ACM0_01_00

Figure 24-20-00-991-00400-00-A / SHEET 1/1 - Oil Consumption of the APU 131-9(A) ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-001-A - Check of the AC Main Generation Maintenance Condition

3.

Job Set-up Subtask 24-20-00-860-050-A A.

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) .

4.

Procedure Subtask 24-20-00-210-054-B A.

CAUTION to Prevent Damage to IDG CAUTION:

REPLACE THE IDG1(2) BEFORE NEXT ENGINE START IF: - THE IDG1(2) WAS MECHANICALLY DISCONNECTED, AND - THE FAULT MESSAGE "IDG1(E1-4000XU) OIL DELTA TEMP/GCU1 (1XU1)" OR "IDG2(E2-4000XU) OIL DELTA TEMP/GCU2 (1XU2)" IS THEN SHOWN ON THE PFR OR LAST LEG REPORT. THIS FAULT MESSAGE SHOWS THAT THE IDG IS STILL MECHANICALLY CONNECTED. THIS CAN CAUSE HEAVY DAMAGE TO THE IDG AT THE NEXT ENGINE START.

(1) On the lower ECAM DU, on the ELEC page, make sure that the IDG 1(2) DISC message is shown. NOTE: This is only applicable if one generator is inoperative and the cause of the dispatch under MMEL 24-22-01A was one of these warning messages: - ELEC IDG 1(2) OIL LO PR - ELEC IDG 1(2) OIL OVHT. ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 Subtask 24-20-00-040-051-C B.

Fuel recirculation Check (1) On the ECAM control panel, push the STS key. (2) On the lower ECAM display unit, make sure that the "ENG 1(2) FADEC" message does not come into view on the STATUS page. (a) If the message comes into view for the engine with the IDG in operation: · Make sure that none of the messages that follow come into view: . ACOC OIL TEMP TC/HC/EEC . IDG OIL TEMP TC/HC/EEC . ACOC AIR MOD VLV/HC/EEC . FUEL DIV RET VLV/HC/EEC . HMS FUEL OVTMP . HMS ENG OIL OVTMP . HMS IDG OIL OVTMP . HMS IDG OVTMP W/RECIRC . FUEL DIV RET VLV/EEC (3) On the maintenance panel 50VU: · Release the ENG/FADEC GND PWR/1(2) pushbutton switch(es) (the ON legend(s) come(s) on).

Subtask 24-20-00-710-050-A C.

Do this test:

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-001-A - Check of the AC Main Generation Maintenance Condition

ACTION RESULT 1.On one MCDU, get the SYSTEM REPORT/TEST ENG menu page. 2.On the MCDU, on the ENG menu page: On the MCDU: · push the line key adjacent to the FADEC 1A(2A) · the FADEC 1A(2A) page comes into view. indication. 3.On the FADEC 1A(2A) page: On the MCDU: · push the line key adjacent to the LAST LEG RE- · make sure that there is no message related to the PORT indication. control system of the fuel return valve. 4.On the MCDU: · push the line key adjacent to the RETURN indication until the ENG menu page comes into view. 5.On the MCDU, on the ENG menu page: On the MCDU: · push the line key adjacent to the FADEC 1B(2B) · the FADEC 1B(2B) page comes into view. indication. 6.On the FADEC 1B(2B) page: On the MCDU: · push the line key adjacent to the LAST LEG RE- · make sure that there is no message related to the PORT indication. control system of the fuel return valve. 7.On the MCDU: · push the MCDU MENU mode key.

** ON A/C ALL Subtask 24-20-00-210-053-A D.

Check of the APU Oil Consumption (1) If you do a regular monitoring of the APU oil consumption, make sure that the APU oil quantity is sufficient for the flight: · For the GTCP 36-300 (Ref. Fig. Oil Consumption of the APU GTCP 36-300 SHEET 1) or · For the APS 3200 (Ref. Fig. Oil Consumption of the APU APS 3200 SHEET 1) or · For the 131-9(A) (Ref. Fig. Oil Consumption of the APU 131-9(A) SHEET 1) (2) If you do not do a regular monitoring of the APU oil consumption, do the steps that follow to make sure that the APU oil quantity is sufficient for the flight: (a) Make sure that APU LOW OIL LEVEL indication is not shown: 1

On the ECAM control panel, push the APU key (on the lower ECAM DU, the APU page comes into view).

2

Make sure that the APU LOW OIL LEVEL indication is not shown.

(b) Make sure that there are no oil leaks: 1

Start and operate the APU: · For the GTCP 36-300 (Ref. AMM TASK 49-00-00-860-003) , or · For the APS 3200 (Ref. AMM TASK 49-00-00-860-005) , or · For the 131-9(A) (Ref. AMM TASK 49-00-00-860-008) .

2

During APU operation: · Do a check for oil smell in the passenger compartment. · Do a check for white smoke from the APU exhaust.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-001-A - Check of the AC Main Generation Maintenance Condition

NOTE: An oil smell in the passenger compartment shows that there is an internal and/or external oil leakage. NOTE: Smoke from APU exhaust shows that there is an internal oil leakage. 3

Stop the APU: · For the GTCP 36-300 (Ref. AMM TASK 49-00-00-860-004) , or · For the APS 3200 (Ref. AMM TASK 49-00-00-860-006) , or · For the 131-9(A) (Ref. AMM TASK 49-00-00-860-009) .

(c) Make sure that the APU oil is at maximum level: · For the GTCP 36-300 (Ref. AMM TASK 49-90-00-600-001) , or · For the APS 3200 (Ref. AMM TASK 49-90-00-600-004) , or · For the 131-9(A) (Ref. AMM TASK 49-90-00-600-007) . NOTE: During the oil level check, make sure that there is no external oil leakage in the APU compartment. ** ON A/C 301-349, 351-450, 500-600 Subtask 24-20-00-710-056-B E.

Check of the IDG Heat-Exchanger Bypass-Valves (1) Make sure that the messages that follow are not shown on the last PFR leg: · IDG 1(2) COOLER BYPASS VALVE · IDG 1(2) (E1(2)-4000XU)/IDG 1(2) COOLER BYPASS VALVE.

** ON A/C ALL 5.

Close-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 Subtask 24-20-00-860-051-A A.

Put the aircraft back to its initial configuration. (1) On the panel 50VU: · push the ENG/FADEC GND PWR/1(2) pushbutton switch(es) (the ON legend(s) go(es) off). (2) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (3) Make an entry in the logbook to show that the IDG is connected or disconnected. (4) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241, 301-349, 351-450, 500-600 Subtask 24-20-00-860-051-B A.

Put the aircraft back to its initial configuration. (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) Make an entry in the logbook to show that the IDG is connected or disconnected. (3) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-001-A - Check of the AC Main Generation Maintenance Condition

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-802-A - Check of the Maintenance Condition of the IDG 1(2)

** ON A/C 301-349, 351-450, 500-600 TASK 24-20-00-040-802-A Check of the Maintenance Condition of the IDG 1(2) WARNING:

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

1.

Reason for the Job MMEL 24-09-03A ELEC IDG 1(2) OIL LO LVL Alert MMEL 24-09-04A ELEC IDG 1(2) FILTER CLOG Alert

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific

B.

QTY 1 AR AR AR AR

DESIGNATION ACCESS PLATFORM 1M(3 FT) AIR SOURCE FILTERED, DRY LIGHT SOURCE - INSPECTION MIRROR - INSPECTION WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. 08BBB1) (Material No. 14SBA1)

DESIGNATION Non Aqueous Cleaner-- Petroleum Based Textile-Lint free Cotton -

C. Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTION FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR, 451AL FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR, 461AL D. Referenced Information REFERENCE DESIGNATION (Ref. 71-13-00-010-802-A). Opening of the Fan Cowl Doors (Ref. 71-13-00-410-802-A). Closing of the Fan Cowl Doors (Ref. 78-30-00-040-805-A). Deactivation of the Thrust Reverser System for Ground Maintenance (Ref. 78-30-00-440-805-A). Reactivation of the Thrust Reverser System after Ground Maintenance (Ref. 78-36-00-010-802-A). Opening of the Thrust Reverser Cowl-Doors (Ref. 78-36-00-410-802-A). Closing of the Thrust Reverser Cowl-Doors IDG Oil Level Sight Glass and DPI SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-802-A - Check of the Maintenance Condition of the IDG 1(2)

INTEGRATED DRIVE GENERATOR (IDG)

DPI BUTTON

A

C D B

IDG OIL LEVEL SIGHTGLASS

A RED

YELLOW 01

01

GREEN RED

B

NORMAL (RESET)

EXTENDED

C

D

FWD

NOTE: 01 DPI BUTTON (SILVER END, RED CYLINDRICAL SIDE)

N_MM_242000_4_PAM0_01_01

Figure 24-20-00-991-00500-00-A / SHEET 1/1 - IDG Oil Level Sight Glass and DPI ** ON A/C 301-349, 351-450, 500-600 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-802-A - Check of the Maintenance Condition of the IDG 1(2)

3.

Job Set-up Subtask 24-20-00-941-052-A A.

Safety Precautions (1) 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. (c) Put WARNING NOTICE(S) in position to tell persons not to operate the ENG/MODE selector switch and the ENG/MASTER 1(2) control switch. (2) 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) Put WARNING NOTICE(S) in position to tell persons not to energize FADEC 1(2). (3) Wait ten minutes after the engine shutdown.

Subtask 24-20-00-010-053-A B.

Get Access (1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR

Subtask 24-20-00-040-053-A C.

Deactivation of the Thrust Reverser System for Ground Maintenance 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) Do the deactivation of the thrust reverser system for ground maintenance (Ref. AMM TASK 78-3000-040-805) .

Subtask 24-20-00-010-054-A D.

Get Access (1) Open the left thrust-reverser cowl-door (Ref. AMM TASK 78-36-00-010-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 451AL (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 461AL (2) Put an ACCESS PLATFORM 1M(3 FT) in position.

4.

Procedure (Ref. Fig. IDG Oil Level Sight Glass and DPI SHEET 1) Subtask 24-20-00-160-050-A A.

Cleaning of the IDG Oil Sight-Glass for Correct Conditions WARNING: DO NOT GET THE FLUID ON YOUR SKIN OR IN YOUR EYES. IF YOU DO: - FLUSH IT AWAY WITH CLEAN WATER

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-802-A - Check of the Maintenance Condition of the IDG 1(2)

- GET MEDICAL AID. (1) Make sure that the IDG oil sight-glass is clean. (a) If the IDG oil sight-glass is not clean: · Clean the sight glass with Non Aqueous Cleaner-- Petroleum Based - (Material No. 08BBB1), and · Remove the remaining solvent with a clean Textile-Lint free Cotton - (Material No. 14SBA1) or blow air on the sight glass with a AIR SOURCE FILTERED, DRY to dry it. (b) If the IDG oil sight-glass is clean: Go to Para. B. of the Procedure. Subtask 24-20-00-210-055-A B.

Check of the IDG Maintenance Conditions CAUTION:

DO NOT DO THIS TASK IF THE IDG IS DISCONNECTED. BEFORE YOU DO A CHECK OF THE IDG OIL LEVEL, MAKE SURE THAT THE IDG IS CONNECTED. A DISCONNECTED IDG CAN CAUSE AN INCORRECT OIL QUANTITY INDICATION AND THUS INCORRECT SERVICING. IF THE LEVEL IS TOO HIGH OR TOO LOW, DAMAGE CAN OCCUR TO THE IDG WHEN IT OPERATES.

CAUTION:

DO NOT OPERATE THE IDG WITHOUT SUFFICIENT OIL. THIS WILL CAUSE DAMAGE TO THE IDG.

(1) Make sure that the IDG oil level at the sight glass is not in the lower red band. (2) Make sure that the red button of the IDG DPI oil filter is not extended. · Use an LIGHT SOURCE - INSPECTION and an MIRROR - INSPECTION, if necessary. 5.

Close-up Subtask 24-20-00-410-053-A A.

Put the aircraft back to its initial configuration. (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the left thrust-reverser cowl-door (Ref. AMM TASK 78-36-00-410-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 451AL (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 461AL

Subtask 24-20-00-440-054-A B.

Reactivation of the Thrust Reverser System after Ground Maintenance (1) Do the reactivation of the thrust reverser system after ground maintenance (Ref. AMM TASK 78-3000-440-805) .

Subtask 24-20-00-410-054-A C.

Close Access (1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-802-A - Check of the Maintenance Condition of the IDG 1(2)

(2) Remove the WARNING NOTICE(S).

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit

** ON A/C ALL TASK 24-23-00-040-001-A Deactivation of the APU Generator by Installation of the Substitution Kit WARNING:

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

WARNING:

USE THE CORRECT PERSONAL PROTECTION. OIL CAN HAVE ADDITIVE CALLED TRICRESYL PHOSPHATE IN IT. THIS CHEMICAL IS AN ASPHYXIANT, IT IS POISONOUS AND CAN BE ABSORBED THROUGH THE SKIN. USE CARE WHEN ENGINE OIL IS DRAINED. HOT OIL CAN POSSIBLY CAUSE BAD BURNS.

1.

Reason for the Job MMEL 24-23-01H AC Auxiliary Generation (APU Generator, GCU or GAPCU Auxiliary Power Control function, Line Contactor) MMEL 24-23-01C AC Auxiliary Generation (APU Generator, GCU or GAPCU Auxiliary Power Control function, Line Contactor) NOTE: For the part number reference of the substitution kit with the APU generator removed, refer to IPC 4911-04-05 and/or 49-11-84-40.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific

QTY 1 AR 1 AR

No specific

B.

DESIGNATION ACCESS PLATFORM 4M (13 FT) COVER - PLASTIC PLACARD WARNING NOTICE(S) Torque wrench: range to between 0.22 and 0.24 m.daN (19.47 and 21.24 lbf.in) Torque wrench: range to between 3.9 and 4.4 m.daN (28.76 and 32.45 lbf.ft)

Consumable Materials REFERENCE (Material No. 03ABA1) (Material No. 03ABB1) (Material No. 14QFB1) (Material No. 14SBA1)

DESIGNATION Synthetic base Lubricating Oil-Turbine Engine - Synthetic base Lubricating Oil-Turbine Engine Low Temp. Wire-Locking Dia: 0.8 mm CRES Nickel Alloy Textile-Lint free Cotton -

C. Work Zones and Access Panels ZONE/ACCESS 315AL, 316AR

ZONE DESCRIPTION

D. Expendable Parts

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit

FIG.ITEM

DESIGNATION

IPC-CSN

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 9 seal

49-11-04-05-150

** ON A/C 301-349, 351-450, 500-600 9 seal

49-11-84-40-150

** ON A/C ALL E.

Referenced Information REFERENCE (Ref. 24-23-51-000-001-A). (Ref. 24-23-51-000-001-A-01). (Ref. 24-42-00-861-001-A). (Ref. 29-00-00-864-001-A). (Ref. 29-14-00-614-002-A). (Ref. 29-14-00-614-002-A-01).

** ON A/C 201-201, 233-233 (Ref. 49-00-00-860-003-A). (Ref. 49-00-00-860-003-A-01). (Ref. 49-00-00-860-004-A). (Ref. 49-00-00-860-004-A-01).

DESIGNATION Removal of the APU Generator Removal of the APU Generator with the Minilift Hoist Energize the Ground Service Network from the External Power Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action Pressurization of the Hydraulic Reservoirs through the Ground Connector Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU)

APU Start by External Power APU Start by Batteries APU Shutdown by External Power APU Shutdown by Batteries

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 (Ref. 49-00-00-860-005-A). APU Start by External Power (Ref. 49-00-00-860-005-A-01). APU Start by Batteries (Ref. 49-00-00-860-006-A). APU Shutdown by External Power (Ref. 49-00-00-860-006-A-01). APU Shutdown by Batteries ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 (Ref. 49-00-00-860-008-A). APU Start by External Power (Ref. 49-00-00-860-008-A-01). APU Start by Batteries (Ref. 49-00-00-860-009-A). APU Shutdown by External Power (131-9(A)) (Ref. 49-00-00-860-009-A-01). APU Shutdown by Batteries (131-9(A)) ** ON A/C 201-201, 233-233 (Ref. 49-90-00-600-001-A).

Check Oil Level and Replenish (GTCP 36-300)

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 (Ref. 49-90-00-600-004-A). Check Oil Level and Replenish (APS 3200) Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit REFERENCE

DESIGNATION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 (Ref. 49-90-00-600-007-A). Check Oil Level and Replenish (131-9(A)) ** ON A/C ALL (Ref. 52-41-00-010-001-A). Open the APU Doors for Access (Ref. 52-41-00-410-001-A). Close the APU Doors after Access Components for Flight without an APU Generator Installed SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit

FR80

FR84

A

8XS

2

316AR

4

3 12 315AL

13

14 15

11

1

16 17 5 10

7

6 4095KM

A

9 8

N_MM_242300_4_AAM0_01_01

Figure 24-23-00-991-00100-00-A / SHEET 1/1 Components for Flight without an APU Generator Installed ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit

3.

Job Set-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 24-23-00-860-050-A A.

Obey the MMEL requirements related to Weight Impact and Effect on Balance for Flights without APU Generator (1) Weight Impact: -21.95 kg (-48.3915 lb). (2) Effect on Balance: -871.35 m.daN (-77110.62 lbf.in).

** ON A/C 401-450 Subtask 24-23-00-860-050-B A.

Obey the MMEL requirements related to Weight Impact and Effect on Balance for Flights without APU Generator (1) Weight Impact: -21.95 kg (-48.3915 lb). (2) Effect on Balance: -1023.57 m.daN (-90581.42 lbf.in).

** ON A/C ALL Subtask 24-23-00-860-051-A B.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) . (2) On the APU section of the overhead panel 25VU, make sure that the APU MASTER SW pushbutton switch is released (the ON legend is off). (3) Put a WARNING NOTICE(S) in position in the cockpit to tell persons not to start the APU. (4) Make sure that the ground fire-extinguishing equipment is available. (5) Make sure that the hydraulic systems are depressurized (Ref. AMM TASK 29-00-00-864-001) .

Subtask 24-23-00-865-050-A C.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged: PANEL 121VU 121VU

DESIGNATION APU/APU/CTL APU/ECB/SPLY

FIN 2KD 1KD

LOCATION L42 L41

Subtask 24-23-00-010-050-A D.

Get Access (1) Put the ACCESS PLATFORM 4M (13 FT) in position below the APU compartment. (2) Open the APU access doors 315AL and 316AR (Ref. AMM TASK 52-41-00-010-001) . (3) Set the control switch 11LJ to the ON position. (4) Remove the APU generator (Ref. AMM TASK 24-23-51-000-001) .

4.

Procedure (Ref. Fig. Components for Flight without an APU Generator Installed SHEET 1)

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 24-23-00-420-050-A Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit

A.

Installation of the Substitution Kit for Flight without an APU Generator Installed NOTE: For the Part Number reference of the substitution kit with an APU generator removed, please refer to IPC 49-11-04-05. (1) Do an inspection of the component interfaces and the adjacent area. (a) Remove the COVER - PLASTIC from the generator pad on the accessory drive gearbox. (b) Clean the component interfaces and the adjacent area. (c) Remove and keep the nuts (1) from the studs. Make sure that the nuts (1) are serviceable. (d) Make sure that the face of the generator pad (10) and the studs are in the correct condition. (2) Do a visual inspection of the cable support assembly (5). (a) Make sure that the cable support assembly (5) is in the correct condition. 1

Make sure that the components of the terminal block are in the correct condition.

2

Do an inspection of the component interfaces and the adjacent area.

(3) Do a visual inspection of the seal plate (4095KM) (7). (a) Clean the seal plate (7) with Synthetic base Lubricating Oil-Turbine Engine - (Material No. 03ABA1) or Synthetic base Lubricating Oil-Turbine Engine Low Temp. - (Material No. 03ABB1) and a lint-free cotton cloth Textile-Lint free Cotton - (Material No. 14SBA1). (b) Make sure that the faces of the seal plate (7) are in the correct condition. (4) Do a visual inspection of the assembly cover (11). (a) Make sure that the assembly cover (11) is clean and in the correct condition. (b) Make sure that the oil transfer channel and its inlet and outlet openings are clean and not clogged. (c) Make sure that the drain plug (6) is installed correctly, fully tightened and safetied with WireLocking Dia: 0.8 mm CRES Nickel Alloy - (Material No. 14QFB1). (5) Install the seal plate (4095KM) (7) on the assembly cover (11). (a) Lubricate the new IPC -CSN (49-11-04-05-150) seal (9) and the screws (8) with Synthetic base Lubricating Oil-Turbine Engine - - (Material No. 03ABA1) or Synthetic base Lubricating OilTurbine Engine Low Temp. - (Material No. 03ABB1). (b) Put the seal plate (7) in position on the assembly cover(11). NOTE: Make sure that the dowel pin on the assembly cover (11) engages correctly into the pilot hole on the seal plate (7). (c) Install the screws (8). (d) Install the seal (9) on the assembly cover (11). (6) Install the assembly cover (11). (a) Put the assembly cover (11) in position on the generator pad (10). NOTE: Make sure that the dowel pin on the assembly cover (11) engages correctly into the pilot hole on the seal plate (7). (b) Put the cable support assembly (5) in position.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit

(c) Install the nuts (1). (d) TORQUE the nuts (1) to between 3.9 and 4.4 m.daN (28.76 and 32.45 lbf.ft). (7) Install the generator supply cables (3) on the terminal block on the cable support assembly (5). (a) Remove the nuts (2). (b) Remove the tie-wraps that temporarily hold the generator supply cables (3). (c) Remove the COVER - PLASTIC from the ring terminals of the generator supply cables (3). (d) Attach the generator supply cables (3) to the applicable studs on the terminal block with the nuts (2). NOTE: Refer to the marks on the terminal block and the generator supply cables (3). (e) Attach the generator supply cables (3) with the clamp (14). (f)

Install the spacer (15), clamp (14), washer (13), screw (12), washer (16) and nut (17).

(g) TORQUE the nut (17) to between 0.22 and 0.24 m.daN (19.47 and 21.24 lbf.in). (8) Connect the generator control cable to the connector on the cable support assembly (5). (a) Remove the tie-wrap that temporarily holds the electrical connector (4). (b) Remove the CAP-BLANKING from each electrical connector and receptacle. (c) Make sure that all the electrical connections are clean and in the correct condition. (d) Connect the electrical connector (4) to the cable support assembly (5). ** ON A/C 301-349, 351-450, 500-600 Subtask 24-23-00-420-050-B A.

Installation of the Substitution Kit for the Flight without the APU Generator Installed NOTE: For the part number reference of the substitution kit with the APU generator removed, refer to IPC 49-11-84-40. (1) Do an inspection of the component interfaces and the adjacent area. (a) Remove the COVER - PLASTIC from the generator pad (10) on the accessory drive gearbox. (b) Clean the component interfaces and the adjacent area. (c) Remove and keep the nuts (1) from the studs. Make sure that the nuts (1) are serviceable. (d) Make sure that the face of the generator pad (10) and the studs are in the correct condition. (2) Do a visual inspection of the cable support assembly (5): (a) Make sure that the cable support assembly (5) is in the correct condition: 1

Make sure that the components of the terminal block are in the correct condition.

2

Do an inspection of the component interfaces and the adjacent area.

(3) Do a visual inspection of the seal plate (4095KM) (7): (a) Clean the seal plate (7) with Synthetic base Lubricating Oil-Turbine Engine - (Material No. 03ABA1) or Synthetic base Lubricating Oil-Turbine Engine Low Temp. - (Material No. 03ABB1) and a lint-free cotton cloth Textile-Lint free Cotton - (Material No. 14SBA1). (b) Make sure that the faces of the seal plate (7) are in the correct condition. (4) Do a visual inspection of the assembly cover (11): Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit

(a) Make sure that the assembly cover (11) is clean and in the correct condition. (b) Make sure that the oil transfer channel and its inlet and outlet openings are clean and not clogged. (c) Make sure that the drain plug (6) is installed correctly, fully tightened and safetied with WireLocking Dia: 0.8 mm CRES Nickel Alloy - (Material No. 14QFB1). (5) Install the seal plate (4095KM) (7) on the assembly cover (11): (a) Lubricate the new IPC -CSN (49-11-84-40-150) seal (9) and the screws (8) with Synthetic base Lubricating Oil-Turbine Engine - - (Material No. 03ABA1) or Synthetic base Lubricating OilTurbine Engine Low Temp. - (Material No. 03ABB1). (b) Put the seal plate (7) in position on the assembly cover (11). (c) Make sure that the dowel pin on the assembly cover (11) engages correctly into the pilot hole on the seal plate (7). (d) Install the screws (8). (e) Tighten the screws (8). (f)

Install the seal (9) on the assembly cover (11).

(6) Install the assembly cover (11): (a) Put the assembly cover (11) in position on the generator pad (10). (b) Make sure that the dowel pin on the assembly cover (11) engages correctly into the pilot hole on the seal plate (7). (c) Put the cable support assembly (5) in position. (d) Install the nuts (1). (e) TORQUE the nuts (1) to between 3.9 and 4.4 m.daN (28.76 and 32.45 lbf.ft). (7) Install the generator supply cables (3) on the terminal block on the cable support assembly (5): (a) Remove the nuts (2). (b) Remove the tie wraps that temporarily hold the generator supply cables (3). (c) Remove the COVER - PLASTIC from the ring terminals of the generator supply cables (3). (d) Attach the generator supply cables (3) to the applicable studs on the terminal block with the nuts (2). NOTE: Refer to the marks on the terminal block and the generator supply cables (3). (e) Attach the generator supply cables (3) with the clamp (14). (f)

Install the spacer (15), clamp (14), washer (13), screw (12), washer (16) and nut (17).

(g) TORQUE the nut (17) to between 0.22 and 0.24 m.daN (19.47 and 21.24 lbf.in). (8) Connect the generator control cable to the connector on the cable support assembly (5): (a) Remove the tie wrap that temporarily holds the electrical connector (4). (b) Remove the CAP-BLANKING from each electrical connector and receptacle. (c) Make sure that all the electrical connections are clean and in the correct condition. (d) Connect the electrical connector (4) to the cable support assembly (5). ** ON A/C ALL Subtask 24-23-00-865-051-A

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit

B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/APU/CTL APU/ECB/SPLY

FIN 2KD 1KD

LOCATION L42 L41

Subtask 24-23-00-790-050-A C.

Leak test WARNING: DO NOT TOUCH THE APU UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS WHEN YOU DO THE MAINTENANCE TASK(S). (1) Make sure that the work area is clean and clear of tools and other items. (2) Start the APU: · GTCP 36-300 (Ref. AMM TASK 49-00-00-860-003) or · APS 3200 (Ref. AMM TASK 49-00-00-860-005) or · 131-9(A) (Ref. AMM TASK 49-00-00-860-008) . (3) Do a check for oil leaks. (a) Examine the joint between the assembly cover (11) and the generator pad (10) on the accessory drive gearbox for oil leaks. (b) Examine the drain plug (6) on the assembly cover (11) for oil leaks. NOTE: Leaks are not permitted. (4) Stop the APU: · GTCP 36-300 (Ref. AMM TASK 49-00-00-860-004) or · APS 3200 (Ref. AMM TASK 49-00-00-860-006) or · 131-9(A) (Ref. AMM TASK 49-00-00-860-009) . (5) Do a check of the oil quantity on the APU oil sight-glass. Add oil if the oil level is on or below the ADD mark on the oil sight glass: · GTCP 36-300 (Ref. AMM TASK 49-90-00-600-001) or · APS 3200 (Ref. AMM TASK 49-90-00-600-004) or · 131-9(A) (Ref. AMM TASK 49-90-00-600-007) .

5.

Close-up Subtask 24-23-00-410-050-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Set the control switch 11JL to the OFF position. (3) Close the APU access doors 315AL and 316AR (Ref. AMM TASK 52-41-00-410-001) . (4) Remove the access platform(s).

Subtask 24-23-00-860-052-A B.

Put the aircraft back to its initial configuration.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit

(1) Put a PLACARD in the cockpit to tell persons that the APU generator is deactivated. (2) De-energize the ground service network (Ref. AMM TASK 29-14-00-614-002) . (3) Remove the WARNING NOTICE(S). (4) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-002-A - Deactivation of the APU Generator by Removal of the Quill Shaft

** ON A/C ALL TASK 24-23-00-040-002-A Deactivation of the APU Generator by Removal of the Quill Shaft WARNING:

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

WARNING:

USE THE CORRECT PERSONAL PROTECTION. OIL CAN HAVE ADDITIVE CALLED TRICRESYL PHOSPHATE IN IT. THIS CHEMICAL IS AN ASPHYXIANT, IT IS POISONOUS AND CAN BE ABSORBED THROUGH THE SKIN. USE CARE WHEN ENGINE OIL IS DRAINED. HOT OIL CAN POSSIBLY CAUSE BAD BURNS.

1.

Reason for the Job MMEL 24-23-01I AC Auxiliary Generation (APU Generator, GCU or GAPCU Auxiliary Power Control function, Line Contactor) MMEL 24-23-01C AC Auxiliary Generation (APU Generator, GCU or GAPCU Auxiliary Power Control function, Line Contactor)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

QTY 1 1 AR AR

DESIGNATION ACCESS PLATFORM 4M (13 FT) PLACARD SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 315AL, 316AR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-23-51-000-001-A). (Ref. 24-23-51-000-001-A-01). (Ref. 24-23-51-400-001-A). (Ref. 24-23-51-400-001-A-01). (Ref. 24-42-00-861-001-A). (Ref. 29-00-00-864-001-A).

DESIGNATION Removal of the APU Generator Removal of the APU Generator with the Minilift Hoist Installation of the APU Generator Installation of the APU Generator with the Minilift Hoist Energize the Ground Service Network from the External Power Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action (Ref. 29-14-00-614-002-A). Pressurization of the Hydraulic Reservoirs through the Ground Connector (Ref. 29-14-00-614-002-A-01). Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU) (Ref. 52-41-00-010-001-A). Open the APU Doors for Access (Ref. 52-41-00-410-001-A). Close the APU Doors after Access APU Generator without Quill Shaft SHEET 1 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-002-A - Deactivation of the APU Generator by Removal of the Quill Shaft

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-002-A - Deactivation of the APU Generator by Removal of the Quill Shaft

FR80

FR84

8XS

A 316AR

315AL

A

4 3 1

2

N_MM_242300_4_AAN0_01_00

Figure 24-23-00-991-00200-00-A / SHEET 1/1 - APU Generator without Quill Shaft ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-002-A - Deactivation of the APU Generator by Removal of the Quill Shaft

3.

Job Set-up Subtask 24-23-00-860-055-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) . (2) On the APU section of the overhead panel 25VU, make sure that the APU MASTER SW pushbutton is released (the ON legend is off). (3) Put a WARNING NOTICE(S) in position in the cockpit to tell persons not to start the APU. (4) Make sure that the ground fire extinguishing equipment is available. (5) Make sure that the hydraulic systems are depressurized (Ref. AMM TASK 29-00-00-864-001) .

Subtask 24-23-00-865-054-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/APU/CTL APU/ECB/SPLY

FIN 2KD 1KD

LOCATION L42 L41

Subtask 24-23-00-010-053-A C.

Get Access (1) Put the ACCESS PLATFORM 4M (13 FT) in position below the APU compartment. (2) Open the APU access doors 315AL and 316AR (Ref. AMM TASK 52-41-00-010-001) . (3) Set the control switch 11LJ to the ON position.

4.

Procedure (Ref. Fig. APU Generator without Quill Shaft SHEET 1) Subtask 24-23-00-020-051-A A.

Remove the APU Generator (Ref. AMM TASK 24-23-51-000-001) .

Subtask 24-23-00-020-052-A B.

Remove the Quill Shaft (1) Carefully remove the bolt (1) from the groove in the drive end of the finished rotor assembly. (2) Remove the quill shaft assembly (3) from the drive end of the finished rotor assembly. (3) Remove the seals (2) and (4) from the quill shaft assembly (3). (4) Discard the seals.

Subtask 24-23-00-420-051-A C. 5.

Install the APU generator (Ref. AMM TASK 24-23-51-400-001) without the quill shaft.

Close-up Subtask 24-23-00-865-055-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/APU/CTL APU/ECB/SPLY

FIN 2KD 1KD

LOCATION L42 L41

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-002-A - Deactivation of the APU Generator by Removal of the Quill Shaft

Subtask 24-23-00-410-052-A B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Set the control switch 11JL to the OFF position. (3) Close the APU access doors 315AL and 316AR (Ref. AMM TASK 52-41-00-410-001) . (4) Remove the access platform(s).

Subtask 24-23-00-860-056-A C.

Put the aircraft back to its initial configuration. (1) Put a PLACARD in the cockpit to tell persons that the APU generator is deactivated. (2) De-energize the ground service network (Ref. AMM TASK 29-14-00-614-002) . (3) Remove the WARNING NOTICE(S). (4) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-002-A - RAT Extension Control - Check of the RAT Manual Extension

** ON A/C ALL TASK 24-20-00-040-002-A RAT Extension Control - Check of the RAT Manual Extension 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:

MAKE SURE THAT THE CONTROLS AGREE WITH THE POSITION OF THE ITEMS THEY OPERATE BEFORE YOU PRESSURIZE A HYDRAULIC SYSTEM. UNWANTED MOVEMENT OF HYDRAULICALLY OPERATED ITEMS CAN CAUSE SERIOUS INJURY AND/OR DAMAGE.

1.

Reason for the Job MMEL 24-24-02A RAT Extension Automatic Control

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

QTY 1 AR AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE SAFETY BARRIER(S) WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 812

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 29-10-00-863-003-A). (Ref. 29-10-00-863-003-A-01). (Ref. 29-10-00-864-003-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Pressurize the Blue Hydraulic System with a Hydraulic Ground PowerCart Pressurize the Blue Hydraulic System with the Blue Electric Pump Depressurize the Blue Hydraulic System

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-002-A - RAT Extension Control - Check of the RAT Manual Extension

REFERENCE (Ref. 29-22-00-869-005-A). (Ref. 29-22-00-869-006-A). RAT control SHEET 1

DESIGNATION Extension of the Ram Air Turbine (RAT) on the Ground Retraction of the Ram Air Turbine (RAT) on the Ground

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-002-A - RAT Extension Control - Check of the RAT Manual Extension

Z195

21VU

B

A A

21VU EMER GEN TEST

EMER ELEC PWR RAT & EMER GEN

MAN ON

A U T O

FAULT

C 24XE

B INDICATION LIGHTS

C INTERLOCK ACTUATOR PRESSURE WARNING

RAT STOWED

RESET O N

LOCKING MECHANISM

STOW

LAMP TEST

28V DC

O F F

J2

N_MM_242000_4_AAC0_01_00

Figure 24-20-00-991-00100-00-C / SHEET 1/1 - RAT control ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-002-A - RAT Extension Control - Check of the RAT Manual Extension

3.

Job Set-up Subtask 24-20-00-860-053-A A.

Aircraft Maintenance Configuration (1) Make sure that the WARNING NOTICE(S) are in position. (2) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations. (3) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (4) Pressurize the Blue hydraulic system (Ref. AMM TASK 29-10-00-863-003) .

Subtask 24-20-00-010-050-A B.

Get access to the avionics compartment. (1) Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access door 812 of the avionics compartment. (2) Open the access door 812.

Subtask 24-20-00-865-050-A C.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 106VU

WARNING:

4.

DESIGNATION CSM/G /EV/MAN/SPLY

FIN 6XE

LOCATION B04

MAKE SURE THAT THE RAT TRAVEL RANGE IS CLEAR BEFORE YOU EXTEND/RETRACT THE RAT.

Procedure (Ref. Fig. RAT control SHEET 1) Subtask 24-20-00-710-053-B A.

Extension of the RAT (1) Do the extension of the Ram Air Turbine (RAT) on the ground (Ref. AMM TASK 29-22-00-869-005) .

Subtask 24-20-00-710-054-B B.

Retraction of the RAT (1) Do the retraction of the Ram Air Turbine (RAT) on the ground (Ref. AMM TASK 29-22-00-869-006) .

5.

Close-up Subtask 24-20-00-860-052-A A.

Put the aircraft back to its initial configuration. (1) Depressurize the Blue hydraulic system (Ref. AMM TASK 29-10-00-864-003) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (3) Remove the WARNING NOTICE(S). (4) Remove the safety barriers.

Subtask 24-20-00-410-050-A

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-20-00-040-002-A - RAT Extension Control - Check of the RAT Manual Extension

B.

Close Access (1) Close the access door 812. (2) Remove the access platform(s).

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit

** ON A/C ALL TASK 24-23-00-040-001-A Deactivation of the APU Generator by Installation of the Substitution Kit WARNING:

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

WARNING:

USE THE CORRECT PERSONAL PROTECTION. OIL CAN HAVE ADDITIVE CALLED TRICRESYL PHOSPHATE IN IT. THIS CHEMICAL IS AN ASPHYXIANT, IT IS POISONOUS AND CAN BE ABSORBED THROUGH THE SKIN. USE CARE WHEN ENGINE OIL IS DRAINED. HOT OIL CAN POSSIBLY CAUSE BAD BURNS.

1.

Reason for the Job MMEL 24-23-01H AC Auxiliary Generation (APU Generator, GCU or GAPCU Auxiliary Power Control function, Line Contactor) MMEL 24-23-01C AC Auxiliary Generation (APU Generator, GCU or GAPCU Auxiliary Power Control function, Line Contactor) NOTE: For the part number reference of the substitution kit with the APU generator removed, refer to IPC 4911-04-05 and/or 49-11-84-40.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific

QTY 1 AR 1 AR

No specific

B.

DESIGNATION ACCESS PLATFORM 4M (13 FT) COVER - PLASTIC PLACARD WARNING NOTICE(S) Torque wrench: range to between 0.22 and 0.24 m.daN (19.47 and 21.24 lbf.in) Torque wrench: range to between 3.9 and 4.4 m.daN (28.76 and 32.45 lbf.ft)

Consumable Materials REFERENCE (Material No. 03ABA1) (Material No. 03ABB1) (Material No. 14QFB1) (Material No. 14SBA1)

DESIGNATION Synthetic base Lubricating Oil-Turbine Engine - Synthetic base Lubricating Oil-Turbine Engine Low Temp. Wire-Locking Dia: 0.8 mm CRES Nickel Alloy Textile-Lint free Cotton -

C. Work Zones and Access Panels ZONE/ACCESS 315AL, 316AR

ZONE DESCRIPTION

D. Expendable Parts

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit

FIG.ITEM

DESIGNATION

IPC-CSN

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 9 seal

49-11-04-05-150

** ON A/C 301-349, 351-450, 500-600 9 seal

49-11-84-40-150

** ON A/C ALL E.

Referenced Information REFERENCE (Ref. 24-23-51-000-001-A). (Ref. 24-23-51-000-001-A-01). (Ref. 24-42-00-861-001-A). (Ref. 29-00-00-864-001-A). (Ref. 29-14-00-614-002-A). (Ref. 29-14-00-614-002-A-01).

** ON A/C 201-201, 233-233 (Ref. 49-00-00-860-003-A). (Ref. 49-00-00-860-003-A-01). (Ref. 49-00-00-860-004-A). (Ref. 49-00-00-860-004-A-01).

DESIGNATION Removal of the APU Generator Removal of the APU Generator with the Minilift Hoist Energize the Ground Service Network from the External Power Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action Pressurization of the Hydraulic Reservoirs through the Ground Connector Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU)

APU Start by External Power APU Start by Batteries APU Shutdown by External Power APU Shutdown by Batteries

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 (Ref. 49-00-00-860-005-A). APU Start by External Power (Ref. 49-00-00-860-005-A-01). APU Start by Batteries (Ref. 49-00-00-860-006-A). APU Shutdown by External Power (Ref. 49-00-00-860-006-A-01). APU Shutdown by Batteries ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 (Ref. 49-00-00-860-008-A). APU Start by External Power (Ref. 49-00-00-860-008-A-01). APU Start by Batteries (Ref. 49-00-00-860-009-A). APU Shutdown by External Power (131-9(A)) (Ref. 49-00-00-860-009-A-01). APU Shutdown by Batteries (131-9(A)) ** ON A/C 201-201, 233-233 (Ref. 49-90-00-600-001-A).

Check Oil Level and Replenish (GTCP 36-300)

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 (Ref. 49-90-00-600-004-A). Check Oil Level and Replenish (APS 3200) Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit REFERENCE

DESIGNATION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 (Ref. 49-90-00-600-007-A). Check Oil Level and Replenish (131-9(A)) ** ON A/C ALL (Ref. 52-41-00-010-001-A). Open the APU Doors for Access (Ref. 52-41-00-410-001-A). Close the APU Doors after Access Components for Flight without an APU Generator Installed SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit

FR80

FR84

A

8XS

2

316AR

4

3 12 315AL

13

14 15

11

1

16 17 5 10

7

6 4095KM

A

9 8

N_MM_242300_4_AAM0_01_01

Figure 24-23-00-991-00100-00-A / SHEET 1/1 Components for Flight without an APU Generator Installed ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit

3.

Job Set-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 24-23-00-860-050-A A.

Obey the MMEL requirements related to Weight Impact and Effect on Balance for Flights without APU Generator (1) Weight Impact: -21.95 kg (-48.3915 lb). (2) Effect on Balance: -871.35 m.daN (-77110.62 lbf.in).

** ON A/C 401-450 Subtask 24-23-00-860-050-B A.

Obey the MMEL requirements related to Weight Impact and Effect on Balance for Flights without APU Generator (1) Weight Impact: -21.95 kg (-48.3915 lb). (2) Effect on Balance: -1023.57 m.daN (-90581.42 lbf.in).

** ON A/C ALL Subtask 24-23-00-860-051-A B.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) . (2) On the APU section of the overhead panel 25VU, make sure that the APU MASTER SW pushbutton switch is released (the ON legend is off). (3) Put a WARNING NOTICE(S) in position in the cockpit to tell persons not to start the APU. (4) Make sure that the ground fire-extinguishing equipment is available. (5) Make sure that the hydraulic systems are depressurized (Ref. AMM TASK 29-00-00-864-001) .

Subtask 24-23-00-865-050-A C.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged: PANEL 121VU 121VU

DESIGNATION APU/APU/CTL APU/ECB/SPLY

FIN 2KD 1KD

LOCATION L42 L41

Subtask 24-23-00-010-050-A D.

Get Access (1) Put the ACCESS PLATFORM 4M (13 FT) in position below the APU compartment. (2) Open the APU access doors 315AL and 316AR (Ref. AMM TASK 52-41-00-010-001) . (3) Set the control switch 11LJ to the ON position. (4) Remove the APU generator (Ref. AMM TASK 24-23-51-000-001) .

4.

Procedure (Ref. Fig. Components for Flight without an APU Generator Installed SHEET 1)

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 24-23-00-420-050-A Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit

A.

Installation of the Substitution Kit for Flight without an APU Generator Installed NOTE: For the Part Number reference of the substitution kit with an APU generator removed, please refer to IPC 49-11-04-05. (1) Do an inspection of the component interfaces and the adjacent area. (a) Remove the COVER - PLASTIC from the generator pad on the accessory drive gearbox. (b) Clean the component interfaces and the adjacent area. (c) Remove and keep the nuts (1) from the studs. Make sure that the nuts (1) are serviceable. (d) Make sure that the face of the generator pad (10) and the studs are in the correct condition. (2) Do a visual inspection of the cable support assembly (5). (a) Make sure that the cable support assembly (5) is in the correct condition. 1

Make sure that the components of the terminal block are in the correct condition.

2

Do an inspection of the component interfaces and the adjacent area.

(3) Do a visual inspection of the seal plate (4095KM) (7). (a) Clean the seal plate (7) with Synthetic base Lubricating Oil-Turbine Engine - (Material No. 03ABA1) or Synthetic base Lubricating Oil-Turbine Engine Low Temp. - (Material No. 03ABB1) and a lint-free cotton cloth Textile-Lint free Cotton - (Material No. 14SBA1). (b) Make sure that the faces of the seal plate (7) are in the correct condition. (4) Do a visual inspection of the assembly cover (11). (a) Make sure that the assembly cover (11) is clean and in the correct condition. (b) Make sure that the oil transfer channel and its inlet and outlet openings are clean and not clogged. (c) Make sure that the drain plug (6) is installed correctly, fully tightened and safetied with WireLocking Dia: 0.8 mm CRES Nickel Alloy - (Material No. 14QFB1). (5) Install the seal plate (4095KM) (7) on the assembly cover (11). (a) Lubricate the new IPC -CSN (49-11-04-05-150) seal (9) and the screws (8) with Synthetic base Lubricating Oil-Turbine Engine - - (Material No. 03ABA1) or Synthetic base Lubricating OilTurbine Engine Low Temp. - (Material No. 03ABB1). (b) Put the seal plate (7) in position on the assembly cover(11). NOTE: Make sure that the dowel pin on the assembly cover (11) engages correctly into the pilot hole on the seal plate (7). (c) Install the screws (8). (d) Install the seal (9) on the assembly cover (11). (6) Install the assembly cover (11). (a) Put the assembly cover (11) in position on the generator pad (10). NOTE: Make sure that the dowel pin on the assembly cover (11) engages correctly into the pilot hole on the seal plate (7). (b) Put the cable support assembly (5) in position.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit

(c) Install the nuts (1). (d) TORQUE the nuts (1) to between 3.9 and 4.4 m.daN (28.76 and 32.45 lbf.ft). (7) Install the generator supply cables (3) on the terminal block on the cable support assembly (5). (a) Remove the nuts (2). (b) Remove the tie-wraps that temporarily hold the generator supply cables (3). (c) Remove the COVER - PLASTIC from the ring terminals of the generator supply cables (3). (d) Attach the generator supply cables (3) to the applicable studs on the terminal block with the nuts (2). NOTE: Refer to the marks on the terminal block and the generator supply cables (3). (e) Attach the generator supply cables (3) with the clamp (14). (f)

Install the spacer (15), clamp (14), washer (13), screw (12), washer (16) and nut (17).

(g) TORQUE the nut (17) to between 0.22 and 0.24 m.daN (19.47 and 21.24 lbf.in). (8) Connect the generator control cable to the connector on the cable support assembly (5). (a) Remove the tie-wrap that temporarily holds the electrical connector (4). (b) Remove the CAP-BLANKING from each electrical connector and receptacle. (c) Make sure that all the electrical connections are clean and in the correct condition. (d) Connect the electrical connector (4) to the cable support assembly (5). ** ON A/C 301-349, 351-450, 500-600 Subtask 24-23-00-420-050-B A.

Installation of the Substitution Kit for the Flight without the APU Generator Installed NOTE: For the part number reference of the substitution kit with the APU generator removed, refer to IPC 49-11-84-40. (1) Do an inspection of the component interfaces and the adjacent area. (a) Remove the COVER - PLASTIC from the generator pad (10) on the accessory drive gearbox. (b) Clean the component interfaces and the adjacent area. (c) Remove and keep the nuts (1) from the studs. Make sure that the nuts (1) are serviceable. (d) Make sure that the face of the generator pad (10) and the studs are in the correct condition. (2) Do a visual inspection of the cable support assembly (5): (a) Make sure that the cable support assembly (5) is in the correct condition: 1

Make sure that the components of the terminal block are in the correct condition.

2

Do an inspection of the component interfaces and the adjacent area.

(3) Do a visual inspection of the seal plate (4095KM) (7): (a) Clean the seal plate (7) with Synthetic base Lubricating Oil-Turbine Engine - (Material No. 03ABA1) or Synthetic base Lubricating Oil-Turbine Engine Low Temp. - (Material No. 03ABB1) and a lint-free cotton cloth Textile-Lint free Cotton - (Material No. 14SBA1). (b) Make sure that the faces of the seal plate (7) are in the correct condition. (4) Do a visual inspection of the assembly cover (11): Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit

(a) Make sure that the assembly cover (11) is clean and in the correct condition. (b) Make sure that the oil transfer channel and its inlet and outlet openings are clean and not clogged. (c) Make sure that the drain plug (6) is installed correctly, fully tightened and safetied with WireLocking Dia: 0.8 mm CRES Nickel Alloy - (Material No. 14QFB1). (5) Install the seal plate (4095KM) (7) on the assembly cover (11): (a) Lubricate the new IPC -CSN (49-11-84-40-150) seal (9) and the screws (8) with Synthetic base Lubricating Oil-Turbine Engine - - (Material No. 03ABA1) or Synthetic base Lubricating OilTurbine Engine Low Temp. - (Material No. 03ABB1). (b) Put the seal plate (7) in position on the assembly cover (11). (c) Make sure that the dowel pin on the assembly cover (11) engages correctly into the pilot hole on the seal plate (7). (d) Install the screws (8). (e) Tighten the screws (8). (f)

Install the seal (9) on the assembly cover (11).

(6) Install the assembly cover (11): (a) Put the assembly cover (11) in position on the generator pad (10). (b) Make sure that the dowel pin on the assembly cover (11) engages correctly into the pilot hole on the seal plate (7). (c) Put the cable support assembly (5) in position. (d) Install the nuts (1). (e) TORQUE the nuts (1) to between 3.9 and 4.4 m.daN (28.76 and 32.45 lbf.ft). (7) Install the generator supply cables (3) on the terminal block on the cable support assembly (5): (a) Remove the nuts (2). (b) Remove the tie wraps that temporarily hold the generator supply cables (3). (c) Remove the COVER - PLASTIC from the ring terminals of the generator supply cables (3). (d) Attach the generator supply cables (3) to the applicable studs on the terminal block with the nuts (2). NOTE: Refer to the marks on the terminal block and the generator supply cables (3). (e) Attach the generator supply cables (3) with the clamp (14). (f)

Install the spacer (15), clamp (14), washer (13), screw (12), washer (16) and nut (17).

(g) TORQUE the nut (17) to between 0.22 and 0.24 m.daN (19.47 and 21.24 lbf.in). (8) Connect the generator control cable to the connector on the cable support assembly (5): (a) Remove the tie wrap that temporarily holds the electrical connector (4). (b) Remove the CAP-BLANKING from each electrical connector and receptacle. (c) Make sure that all the electrical connections are clean and in the correct condition. (d) Connect the electrical connector (4) to the cable support assembly (5). ** ON A/C ALL Subtask 24-23-00-865-051-A

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit

B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/APU/CTL APU/ECB/SPLY

FIN 2KD 1KD

LOCATION L42 L41

Subtask 24-23-00-790-050-A C.

Leak test WARNING: DO NOT TOUCH THE APU UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS WHEN YOU DO THE MAINTENANCE TASK(S). (1) Make sure that the work area is clean and clear of tools and other items. (2) Start the APU: · GTCP 36-300 (Ref. AMM TASK 49-00-00-860-003) or · APS 3200 (Ref. AMM TASK 49-00-00-860-005) or · 131-9(A) (Ref. AMM TASK 49-00-00-860-008) . (3) Do a check for oil leaks. (a) Examine the joint between the assembly cover (11) and the generator pad (10) on the accessory drive gearbox for oil leaks. (b) Examine the drain plug (6) on the assembly cover (11) for oil leaks. NOTE: Leaks are not permitted. (4) Stop the APU: · GTCP 36-300 (Ref. AMM TASK 49-00-00-860-004) or · APS 3200 (Ref. AMM TASK 49-00-00-860-006) or · 131-9(A) (Ref. AMM TASK 49-00-00-860-009) . (5) Do a check of the oil quantity on the APU oil sight-glass. Add oil if the oil level is on or below the ADD mark on the oil sight glass: · GTCP 36-300 (Ref. AMM TASK 49-90-00-600-001) or · APS 3200 (Ref. AMM TASK 49-90-00-600-004) or · 131-9(A) (Ref. AMM TASK 49-90-00-600-007) .

5.

Close-up Subtask 24-23-00-410-050-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Set the control switch 11JL to the OFF position. (3) Close the APU access doors 315AL and 316AR (Ref. AMM TASK 52-41-00-410-001) . (4) Remove the access platform(s).

Subtask 24-23-00-860-052-A B.

Put the aircraft back to its initial configuration.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-001-A - Deactivation of the APU Generator by Installation of the Substitution Kit

(1) Put a PLACARD in the cockpit to tell persons that the APU generator is deactivated. (2) De-energize the ground service network (Ref. AMM TASK 29-14-00-614-002) . (3) Remove the WARNING NOTICE(S). (4) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-002-A - Deactivation of the APU Generator by Removal of the Quill Shaft

** ON A/C ALL TASK 24-23-00-040-002-A Deactivation of the APU Generator by Removal of the Quill Shaft WARNING:

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

WARNING:

USE THE CORRECT PERSONAL PROTECTION. OIL CAN HAVE ADDITIVE CALLED TRICRESYL PHOSPHATE IN IT. THIS CHEMICAL IS AN ASPHYXIANT, IT IS POISONOUS AND CAN BE ABSORBED THROUGH THE SKIN. USE CARE WHEN ENGINE OIL IS DRAINED. HOT OIL CAN POSSIBLY CAUSE BAD BURNS.

1.

Reason for the Job MMEL 24-23-01I AC Auxiliary Generation (APU Generator, GCU or GAPCU Auxiliary Power Control function, Line Contactor) MMEL 24-23-01C AC Auxiliary Generation (APU Generator, GCU or GAPCU Auxiliary Power Control function, Line Contactor)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

QTY 1 1 AR AR

DESIGNATION ACCESS PLATFORM 4M (13 FT) PLACARD SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 315AL, 316AR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-23-51-000-001-A). (Ref. 24-23-51-000-001-A-01). (Ref. 24-23-51-400-001-A). (Ref. 24-23-51-400-001-A-01). (Ref. 24-42-00-861-001-A). (Ref. 29-00-00-864-001-A).

DESIGNATION Removal of the APU Generator Removal of the APU Generator with the Minilift Hoist Installation of the APU Generator Installation of the APU Generator with the Minilift Hoist Energize the Ground Service Network from the External Power Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action (Ref. 29-14-00-614-002-A). Pressurization of the Hydraulic Reservoirs through the Ground Connector (Ref. 29-14-00-614-002-A-01). Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU) (Ref. 52-41-00-010-001-A). Open the APU Doors for Access (Ref. 52-41-00-410-001-A). Close the APU Doors after Access APU Generator without Quill Shaft SHEET 1 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-002-A - Deactivation of the APU Generator by Removal of the Quill Shaft

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-002-A - Deactivation of the APU Generator by Removal of the Quill Shaft

FR80

FR84

8XS

A 316AR

315AL

A

4 3 1

2

N_MM_242300_4_AAN0_01_00

Figure 24-23-00-991-00200-00-A / SHEET 1/1 - APU Generator without Quill Shaft ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-002-A - Deactivation of the APU Generator by Removal of the Quill Shaft

3.

Job Set-up Subtask 24-23-00-860-055-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) . (2) On the APU section of the overhead panel 25VU, make sure that the APU MASTER SW pushbutton is released (the ON legend is off). (3) Put a WARNING NOTICE(S) in position in the cockpit to tell persons not to start the APU. (4) Make sure that the ground fire extinguishing equipment is available. (5) Make sure that the hydraulic systems are depressurized (Ref. AMM TASK 29-00-00-864-001) .

Subtask 24-23-00-865-054-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/APU/CTL APU/ECB/SPLY

FIN 2KD 1KD

LOCATION L42 L41

Subtask 24-23-00-010-053-A C.

Get Access (1) Put the ACCESS PLATFORM 4M (13 FT) in position below the APU compartment. (2) Open the APU access doors 315AL and 316AR (Ref. AMM TASK 52-41-00-010-001) . (3) Set the control switch 11LJ to the ON position.

4.

Procedure (Ref. Fig. APU Generator without Quill Shaft SHEET 1) Subtask 24-23-00-020-051-A A.

Remove the APU Generator (Ref. AMM TASK 24-23-51-000-001) .

Subtask 24-23-00-020-052-A B.

Remove the Quill Shaft (1) Carefully remove the bolt (1) from the groove in the drive end of the finished rotor assembly. (2) Remove the quill shaft assembly (3) from the drive end of the finished rotor assembly. (3) Remove the seals (2) and (4) from the quill shaft assembly (3). (4) Discard the seals.

Subtask 24-23-00-420-051-A C. 5.

Install the APU generator (Ref. AMM TASK 24-23-51-400-001) without the quill shaft.

Close-up Subtask 24-23-00-865-055-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/APU/CTL APU/ECB/SPLY

FIN 2KD 1KD

LOCATION L42 L41

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-23-00-040-002-A - Deactivation of the APU Generator by Removal of the Quill Shaft

Subtask 24-23-00-410-052-A B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Set the control switch 11JL to the OFF position. (3) Close the APU access doors 315AL and 316AR (Ref. AMM TASK 52-41-00-410-001) . (4) Remove the access platform(s).

Subtask 24-23-00-860-056-A C.

Put the aircraft back to its initial configuration. (1) Put a PLACARD in the cockpit to tell persons that the APU generator is deactivated. (2) De-energize the ground service network (Ref. AMM TASK 29-14-00-614-002) . (3) Remove the WARNING NOTICE(S). (4) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-51-00-040-001-A - Deactivation of the Galley Supply System

** ON A/C ALL TASK 24-51-00-040-001-A Deactivation of the Galley Supply System 1.

Reason for the Job MMEL 24-26-02B Galley Manual Load Shed System (GALLEY pb-sw)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION 1 PLACARD

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A).

3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure

Job Set-up Subtask 24-51-00-861-051-B A.

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

Subtask 24-51-00-865-052-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 122VU 122VU 122VU 2000VU 2000VU 2000VU 2000VU 2000VU 2000VU 2000VU 2000VU

DESIGNATION ELEC/GALY & CAB/CTL ELEC/GALY & CAB/FAULT/LT CTL ELEC/GALY & CAB/GND/FLT/LOGIC CAB LIGHT PWR-CEILING-AFT CAB LIGHT PWR-CEILING-AFT CAB LIGHT PWR-CEILING-FWD CAB LIGHT PWR-CEILING-FWD CAB LIGHT PWR-WINDOW-AFT CAB LIGHT PWR-WINDOW-AFT CAB LIGHT PWR-WINDOW-FWD CAB LIGHT PWR-WINDOW-FWD

FIN 1XA 8XA 7XA 307LG 304LG 306LG 305LG 302LG 301LG 303LG 300LG

LOCATION S26 S25 S24 H08 H07 H06 H05 H04 H03 H02 H01

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-51-00-040-001-A - Deactivation of the Galley Supply System

Subtask 24-51-00-860-058-B C.

In the forward and aft galleys, make sure that all the circuit breakers are closed.

** ON A/C 201-201, 203-205, 207-207, 210-211, 217-217, 219-220, 231-234, 237-237, 240-240, 243-250 Subtask 24-51-00-860-052-G D.

Aircraft Maintenance Configuration (1) On the overhead ELEC panel 35VU, make sure that the GALY & CAB pushbutton switch is pushed (OFF legend is off). (2) On this panel, make sure that the ELEC/COMMERCIAL pushbutton switch is released (OFF legend is on). (3) On the FWD Attendant Panel (FAP), make sure that the MAIN ON pushbutton switch is set to ON (the green lights of the CABIN WDO and CABIN CLG pushbutton switches are on). (4) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) .

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-216, 218-218, 221-230, 235-236, 238-239, 241242, 301-450, 500-600 Subtask 24-51-00-860-052-I D.

Aircraft Maintenance Configuration (1) On the overhead ELEC panel 35VU, make sure that the GALY & CAB pushbutton switch is pushed (OFF legend is off). (2) On this panel, make sure that the ELEC/COMMERCIAL pushbutton switch is released (OFF legend is on). (3) On the Flight Attendant Panel (FAP), select the CABIN LIGHTING page: · Push the hard key LIGHT MAIN ON/OFF to get the lights on, and · On the CABIN LIGHTING page make sure that AISLE and WDO buttons are green. (4) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) .

** ON A/C ALL 4.

Procedure Subtask 24-51-00-040-050-B A.

Deactivation of the Galley Supply System (1) Test of the Commercial Electrical Load-Shedding ACTION 1.On the ECAM control panel: · Get the ELEC system page. 2.On the ELEC panel 35VU: · Push the ELEC/COMMERCIAL pushbutton switch.

RESULT On the lower display unit of the ECAM system: · The ELEC page comes into view with the white GALLEY SHED indication. On the panel 35VU: · The OFF legend of the ELEC/COMMERCIAL pushbutton switch goes off. On the lower display unit of the ECAM system: · The GALLEY SHED indication goes out of view. In the forward and aft galleys: · Make sure that the galleys operate. In the passenger cabin:

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-51-00-040-001-A - Deactivation of the Galley Supply System

ACTION

RESULT · The CEILING and WINDOW lights come on. 3.On the ELEC panel 35VU: On the panel 35VU: · Release the ELEC/COMMERCIAL pushbutton · The OFF legend of the ELEC/COMMERCIAL switch. pushbutton switch comes on. On the lower display unit of the ECAM system: · The white GALLEY SHED indication comes into view. In the forward and aft galleys: · Make sure that no equipment operate. In the passenger cabin: · The CEILING and WINDOW lights go off. 5.

Close-up Subtask 24-51-00-860-053-B A.

Put the aircraft back to its initial configuration. (1) On the overhead ELEC panel 35VU: · Push the ELEC/COMMERCIAL pushbutton switch (OFF legend is off), and · Push the GALY & CAB pushbutton switch (OFF legend is off). (2) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (3) Make an entry in the logbook. (4) Put a PLACARD in the cockpit to tell persons that the galley supply system is deactivated. (5) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-56-00-040-001-A - Deactivation of the Galley Supply System

** ON A/C ALL TASK 24-56-00-040-001-A Deactivation of the Galley Supply System Task Summary MMEL or CDL Ref MMEL 24-26-01B

Access NO

Test NO

1.

Reason for the Job MMEL 24-26-01B Galley Automatic Load Shed System

2

Job Set-up Information A.

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Specific Tools NO

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Consumable Materials REFERENCE No specific

DESIGNATION PLACARD

C. Referenced Information REFERENCE (Ref. 11-00-00-400-021-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

3.

DESIGNATION Installation of the Pressurized Area Placards Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up Subtask 24-56-00-860-052-B A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Make sure that the pushbutton switch GALLEY 2XA on the overhead panel 35VU is in the OFF position (white indication light shows OFF). (3) Make sure that the pushbutton switch ELEC/COMMERCIAL 22XN on the overhead panel 35VU is in the on position (white indication OFF is off).

Subtask 24-56-00-865-050-A

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-56-00-040-001-A - Deactivation of the Galley Supply System

B.

Open, safety and tag this(these) circuit breaker(s): PANEL 122VU 122VU

DESIGNATION ELEC/GALLEY/CNTOR ELEC/GALY & CAB/CTL

FIN 7MC 1XA

LOCATION S28 S26

** ON A/C 016-022, 024-044, 112-150, 201-201, 203-217, 219-250, 301-450, 500-600 123VU FWD GALLEY/FEEDER F 16MC AC10 ** ON A/C 016-022, 024-044, 112-150, 201-201, 203-217, 219-250, 350-350 123VU AFT GALLEY/FEEDER E 14MC AF09 ** ON A/C 016-022, 024-100, 112-150, 203-211, 213-230, 232-236, 238-250, 301-325, 331-332, 350-350 PRE SB 25-1BKH for A/C 232-232, 244-244 123VU FWD GALLEY/FEEDER C 1MC AE10 ** ON A/C 045-100, 112-150, 201-201, 203-220, 222-230, 232-236, 238-250, 350-350 PRE SB 25-1BKH for A/C 232-232, 244-244 123VU AFT GALLEY/FEEDER A 3MC AF04 ** ON A/C 112-150, 203-206, 209-211, 215-217, 219-220, 226-250, 301-325, 331-332, 350-350 123VU AFT GALLEY/FEEDER B 12MC AD09 ** ON A/C 201-201, 203-205, 207-217, 219-220, 222-237, 239-250, 350-350 123VU FWD GALLEY/FEEDER D 2MC AD04 ** ON A/C 301-325, 331-332 123VU AFT GALLEY/FEEDER E

14MC

** ON A/C 326-330, 333-349, 351-400, 500-600 123VU FWD GALLEY/FEEDER C

1MC

** ON A/C 326-330, 333-349, 351-450, 500-600 123VU AFT GALLEY/FEEDER A

3MC

** ON A/C ALL 4.

Procedure Subtask 24-56-00-040-050-A A.

Deactivation of the Galley Supply (1) Make sure that the galley electrical panel(s) and galley equipment(s) does (do) not operate. (2) Install a PLACARD "INOP" on the galley electrical panel(s) and galley equipment(s) to tell persons not to use it (Ref. AMM TASK 11-00-00-400-021) . (3) Make an entry in the logbook.

5.

Close-up Subtask 24-56-00-862-050-A A.

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

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-56-00-040-002-A - Deactivation of the Galley Supply System

** ON A/C ALL TASK 24-56-00-040-002-A Deactivation of the Galley Supply System Task Summary MMEL or CDL Ref MMEL 24-26-02A

Access NO

Test NO

1.

Reason for the Job MMEL 24-26-02A Galley Manual Load Shed System (GALLEY)

2

Job Set-up Information A.

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Specific Tools NO

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Consumable Materials REFERENCE No specific

DESIGNATION PLACARD

C. Referenced Information REFERENCE (Ref. 11-00-00-400-021-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

3.

DESIGNATION Installation of the Pressurized Area Placards Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up Subtask 24-56-00-860-055-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Make sure that the pushbutton switch GALLEY 2XA on the overhead panel 35VU is in the OFF position (white indication light shows OFF). (3) Make sure that the pushbutton switch ELEC/COMMERCIAL 22XN on the overhead panel 35VU is in the ON position (white indication OFF is off).

Subtask 24-56-00-865-057-A

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-56-00-040-002-A - Deactivation of the Galley Supply System

B.

Open, safety and tag this(these) circuit breaker(s): PANEL 122VU 122VU

DESIGNATION ELEC/GALLEY/CNTOR ELEC/GALY & CAB/CTL

FIN 7MC 1XA

LOCATION S28 S26

** ON A/C 016-022, 024-044, 112-150, 201-201, 203-217, 219-250, 301-450, 500-600 123VU FWD GALLEY/FEEDER F 16MC AC10 ** ON A/C 016-022, 024-044, 112-150, 201-201, 203-217, 219-250, 350-350 123VU AFT GALLEY/FEEDER E 14MC AF09 ** ON A/C 016-022, 024-100, 112-150, 203-211, 213-230, 232-236, 238-250, 301-325, 331-332, 350-350 PRE SB 25-1BKH for A/C 232-232, 244-244 123VU FWD GALLEY/FEEDER C 1MC AE10 ** ON A/C 045-100, 112-150, 201-201, 203-220, 222-230, 232-236, 238-250, 350-350 PRE SB 25-1BKH for A/C 232-232, 244-244 123VU AFT GALLEY/FEEDER A 3MC AF04 ** ON A/C 112-150, 203-206, 209-211, 215-217, 219-220, 226-250, 301-325, 331-332, 350-350 123VU AFT GALLEY/FEEDER B 12MC AD09 ** ON A/C 201-201, 203-205, 207-217, 219-220, 222-237, 239-250, 350-350 123VU FWD GALLEY/FEEDER D 2MC AD04 ** ON A/C 301-325, 331-332 123VU AFT GALLEY/FEEDER E

14MC

** ON A/C 326-330, 333-349, 351-400, 500-600 123VU FWD GALLEY/FEEDER C

1MC

** ON A/C 326-330, 333-349, 351-450, 500-600 123VU AFT GALLEY/FEEDER A

3MC

** ON A/C ALL 4.

Procedure Subtask 24-56-00-040-052-A A.

Deactivation of the Galley Supply (1) Make sure that the galley electrical panel(s) and galley equipment(s) does (do) not operate. (2) Install a PLACARD "INOP" on the galley electrical panel(s) and galley equipment(s) to tell persons not to use it (Ref. AMM TASK 11-00-00-400-021) . (3) Make an entry in the logbook.

5.

Close-up Subtask 24-56-00-862-054-A A.

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

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-012-A - ADIRU/AVNCS VENT Caution Light Inoperative

** ON A/C ALL TASK 21-26-00-040-012-A ADIRU/AVNCS VENT Caution Light Inoperative 1.

Reason for the Job MMEL 24-30-09A External Power Panel ADIRU/AVNCS Vent Caution Light (FAA only)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up Subtask 21-26-00-865-100-A A.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 49VU 49VU 122VU 123VU

DESIGNATION ENGINE/2/FADEC A/AND EIU 2 ENGINE/1/FADEC A/AND EIU 1 AIR COND/AVNCS VENT/CTL AIR COND/AVNCS VENT/CTL AIR COND/AVNCS/VENT/MONG AVNCS VENT/BLOWER/FAN

FIN 2KS2 2KS1 6HQ 5HQ 3HQ 1HQ

LOCATION A05 A04 D06 D05 Y17 AD10

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 123VU AVNCS VENT/EXTC/FAN 2HQ AE02 ** ON A/C 401-450 123VU AVNCS VENT/EXTC/FAN

2HQ

AC04

** ON A/C ALL Subtask 21-26-00-861-086-A B.

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

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 21-26-00-040-012-A - ADIRU/AVNCS VENT Caution Light Inoperative

NOTE: The energization of the aircraft electrical circuits starts a full test of the ventilation system. The test continues for 2 minutes approximately. Subtask 21-26-00-860-066-A C.

Aircraft Maintenance Configuration (1) On the VENTILATION section of the panel 22VU: · make sure that the BLOWER and the EXTRACT pushbutton switches are in the AUTO configuration (pushed, with the FAULT and OVRD legends off).

4.

Procedure Subtask 21-26-00-710-069-A A.

Operational Test of the Mechanic Call Horn ACTION 1.On the circuit breaker panels 49VU and 122VU: · open the circuit breakers 3HQ, 5HQ and 6HQ.

RESULT On the CAPT and F/O glareshield panels 131VU and 130VU: · the MASTER CAUT lights come on and you can hear the single chime. After 30 seconds approximately: · you can hear the mechanic call horn in the nose landing gear well. NOTE: The mechanic call horn operates only if engine 1 and engine 2 are stopped. NOTE: On the panel 108VU, push the RESET pushbutton switch to stop the mechanic call horn.

2.On the circuit breaker panels 49VU and 122VU: · Close the circuit breakers 3HQ, 5HQ and 6HQ. 5.

Close-up Subtask 21-26-00-942-085-A A.

Safety Precautions (1) Put WARNING NOTICE(S) in position in the cockpit to tell the crew that the ADIRU/AVNCS VENT caution light is inoperative. (2) Make an entry in the logbook.

Subtask 21-26-00-862-088-A B.

Aircraft Maintenance Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-30-00-040-001-A - Do a Charging Cycle of the Battery Connected with the Battery Charge Limiter (BCL) or Replacement of the Battery

** ON A/C ALL TASK 24-30-00-040-001-A Do a Charging Cycle of the Battery Connected with the Battery Charge Limiter (BCL) or Replacement of the Battery 1.

Reason for the Job MMEL 24-38-02A Battery Charger Limiter (BCL) This procedure is to make sure that the related battery of the serviceable BCL is fully charged before you interchange the two BCL and charge the other battery with the serviceable BCL.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS 822

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-38-34-000-001-A). (Ref. 24-38-34-400-001-A). (Ref. 24-38-51-000-001-A). (Ref. 24-38-51-400-001-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). 3.

DESIGNATION Removal of the Battery Charge Limiter (BCL) Installation of the Battery Charge Limiter (BCL) Removal of the Battery Installation of the Battery Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure

Job Set-up Subtask 24-30-00-010-053-A A.

Get access to the avionics compartment. (1) Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the avionics compartment door 822. (2) Open the access door 822. (3) Open the access panel of the BATTERY power center 105VU.

Subtask 24-30-00-865-051-A

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-30-00-040-001-A - Do a Charging Cycle of the Battery Connected with the Battery Charge Limiter (BCL) or Replacement of the Battery

B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 105VU 105VU 105VU 105VU 105VU 105VU 125VU

DESIGNATION ELEC/HOT BUS/702PP SPLY ELEC/HOT BUS/701PP SPLY ELEC/BAT REF/BCL2 ELEC/BAT REF/BCL1 ELEC/BAT BUS/REF/BCL1 ELEC/BAT BUS/REF/BCL2 BAT BUS/301PP/SPLY

FIN 5PB2 5PB1 9PB2 9PB1 8PB1 8PB2 11PB

LOCATION D02 D01 F02 F01 G01 J02 CC01

Subtask 24-30-00-860-052-A C.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) In the cockpit, on ELEC control panel 35VU: · Make sure that the BAT 1 and BAT 2 pushbutton switches are released (OFF legends on). (3) In the cockpit, on the APU section of the overhead control and indicating panel 25VU: · Make sure that the APU MASTER SW pushbutton switch is released. (OFF legend on). (4) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) .

4.

Procedure Subtask 24-30-00-040-050-B A.

Charging Cycle of Batteries 1 and 2 with the serviceable BCL 1(2). (1) If the BAT1(2) voltmeter of ELEC panel 35VU related to unserviceable BCL 1(2) shows a voltage of: · Less than 21VDC, do the alternative procedure given in Para. 4.B.(1) or Para. 4.C. · More than or equal to 21VDC, continue the maintenance procedure that follows: (a) On the ECAM control panel: · Push the ELEC key to get the ELEC system page. (b) On the control panel 35VU: · Push the related BAT 1(2) pushbutton switch (OFF and FAULT legends off) related to serviceable BCL to start the charging cycle of the battery 1(2), (c) On the APU section of the overhead control and indicating panel 25VU: · Push the APU MASTER SW pushbutton switch (ON legend on). · Wait two seconds. · Release the APU MASTER SW pushbutton switch (OFF legend on). (d) On the lower ECAM DU: · The green line between the BAT 1(2) indication and the DC BAT busbar indication comes into view. The arrow points to the BAT 1(2) indication. · The related parameter indications (voltage and current) come into view green. (e) On the ELEC system page, make sure that the ground power-unit voltage stays above 114VAC during the charging. (f)

Wait until the battery contactor opens. 1

The green line between the BAT 1(2) indication and the DC BAT busbar indication: · Goes out of view if the battery is correctly charged · Stays in view if a battery charging is necessary.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-30-00-040-001-A - Do a Charging Cycle of the Battery Connected with the Battery Charge Limiter (BCL) or Replacement of the Battery

NOTE: The time for the battery to charge can be of thirty minutes. (g) On the lower ECAM DU, on the ELEC page, make sure that the battery voltage is more than 26VDC and the battery discharge current is equal to or less than 1A. (h) Release the BAT 1 and 2 pushbutton switches (the OFF legend comes on). (i)

Interchange BCL 1 and BCL 2 (Ref. AMM TASK 24-38-34-000-001) and (Ref. AMM TASK 2438-34-400-001) .

(j)

Start a charging cycle of the battery which was connected to the unserviceable BCL 1(2) during the previous flight. 1

On ELEC control panel 35VU, push the related BAT 1(2) pushbutton switch (OFF and FAULT legends off) to start the charging cycle of the battery 1(2) with the serviceable BCL 1(2). a

If the battery contactor 1(2) is not closed (BCL 1(2) FAULT ECAM alert message comes into view on the upper ECAM DU): · Release the BAT1(2) pushbutton switch (the OFF legend comes on) of the battery that was connected to unserviceable BCL 1(2) during the last flight. · Interchange BCL 1 and BCL 2, (Ref. AMM TASK 24-38-34-000-001) and (Ref. AMM TASK 24-38-34-400-001) . · Do the alternative procedure in Para. 4.B.

b

If the battery contactor 1(2) is closed (no BCL 1(2) FAULT ECAM alert message comes into view on the upper ECAM DU): · Do Steps A. (1) (c) thru A. (1) (g).

Subtask 24-30-00-040-051-A B.

Alternative Procedure to Charge the Battery in the Workshop (1) Remove battery 1(2) related to unserviceable BCL 1(2) (Ref. AMM TASK 24-38-51-000-001) . (2) Send battery 1(2) to the overhaul workshop to charge it. (3) Install battery 1(2) (Ref. AMM TASK 24-38-51-400-001) . (4) Release the BAT 1(2) pushbutton switch (OFF legend on) related to the unserviceable BCL 1(2).

Subtask 24-30-00-040-053-A C.

Alternative Procedure to Replace the Battery (1) If the procedures in step A. and B. are not applicable: (a) Replace the battery related to the unserviceable BCL 1(2) with a fully-charged serviceable battery (Ref. AMM TASK 24-38-51-000-001) and (Ref. AMM TASK 24-38-51-400-001) . (b) Release the BAT 1(2) pushbutton switch (OFF legend on) related to the unserviceable BCL 1(2).

5.

Close-up Subtask 24-30-00-410-051-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access panel of the battery power-center 105VU. (3) Close access door 822. (4) Remove the access platform(s).

Subtask 24-30-00-860-053-A

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-30-00-040-001-A - Do a Charging Cycle of the Battery Connected with the Battery Charge Limiter (BCL) or Replacement of the Battery

B.

Put the aircraft back to its initial configuration. (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) Put a warning notice in position in the cockpit to tell the crew that one BCL does not operate. (3) Make an entry in the logbook. (4) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-30-00-040-002-A - Deactivation of the Transformer Rectifier TR2

** ON A/C ALL TASK 24-30-00-040-002-A Deactivation of the Transformer Rectifier TR2 1.

Reason for the Job MMEL 24-32-01B DC Main Generation (TR 1, TR 2)

2

Job Set-up Information A.

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A).

3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure

Job Set-up Subtask 24-30-00-860-054-A A.

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) On the ELEC panel 35VU, make sure that: · The AC ESS FEED pushbutton switch is pushed (the ALTN legend is off).

Subtask 24-30-00-865-052-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 106VU 106VU 123VU 123VU

4.

DESIGNATION AC ESS BUS/STBY/CNTOR/CTL AC ESS/BUS NORM/CNTOR/CTL AC ESS/BUS ON/BUS 1 AC ESS/BUS ON/BUS 2

FIN 5XC 4XC 1XC 2XC

LOCATION B08 B03 AC12 AC01

Procedure Subtask 24-30-00-040-052-A A.

Deactivation of the TR2 if AC ESS FEED Control Is Serviceable (1) Operational test of the AC essential-generation switching system.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-30-00-040-002-A - Deactivation of the Transformer Rectifier TR2

ACTION 1.On the ECAM control panel: · Push the ELEC key.

RESULT On the lower ECAM DU, on the ELEC page: · A green bar comes into view between the AC1 and AC ESS busbars. This shows that the AC1 busbar energizes the AC ESS busbar. 2.On the panel 123VU: On the F/O glareshield panel 130VU: · Open the circuit breaker 1XC. · The MASTER CAUT light comes on. You can hear the single chime. The upper ECAM DU becomes black. The indications shown on the upper ECAM DU: ELEC AC ESS BUS FAULT then AC ESS FEED ... ALTN move to the lower ECAM DU. On the ELEC panel 35VU: · The FAULT legend of the AC ESS FEED pushbutton switch comes on. 3.On the ELEC panel 35VU: On the ELEC panel 35VU: · Release the AC ESS FEED pushbutton switch. · The FAULT legend of the AC ESS FEED pushbutton switch goes off. · The ALTN legend of the AC ESS FEED pushbutton switch comes on. 4.On the ECAM control panel: On the lower ECAM DU, on the ELEC page: · Push the ELEC key. · A green bar comes into view between the AC2 and AC ESS busbars. This shows that the AC2 busbar energizes the AC ESS busbar, · The green bar between the AC1 and AC ESS busbars goes out of view. 5.On the panel 123VU: · Close the circuit breaker 1XC. 6.On the ELEC panel 35VU: On the ELEC panel 35VU: · Push the AC ESS FEED pushbutton switch. · The ALTN legend of the AC ESS FEED pushbutton switch goes off. On the ELEC page: · The green bar between the AC2 and AC ESS busbars goes out of view. · The green bar between the AC1 and AC ESS busbars comes into view. 5.

Close-up Subtask 24-30-00-860-055-A A.

Put the aircraft back to its initial configuration. (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) Make an entry in the logbook. (3) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-41-00-040-001-A - Visual Inspection of the External Power Receptacle

** ON A/C ALL TASK 24-41-00-040-001-A Visual Inspection of the External Power Receptacle WARNING:

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

1.

Reason for the Job MMEL 24-41-02A External Power Receptacle

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION AR GUN - HOT AIR AR WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. 08BBB1) (Material No. 14SBA1)

DESIGNATION Non Aqueous Cleaner-- Petroleum Based Textile-Lint free Cotton -

C. Referenced Information REFERENCE DESIGNATION (Ref. 52-42-12-000-001-A). Removal of the External-Power Receptacle Door (121AL) (Ref. 52-42-12-400-001-A). Installation of the External-Power Receptacle Door (121AL) Ref. SRM 512800 Ref. SRM 531113 External Power Receptacle SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-41-00-040-001-A - Visual Inspection of the External Power Receptacle

FR7

FR8 Z120

A

121AL

A

DOOR

STOP ANGLE

SPRING ROD ASSY

LATCH ASSY

N_MM_244100_4_AAN0_01_00

Figure 24-41-00-991-00200-00-A / SHEET 1/1 - External Power Receptacle ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-41-00-040-001-A - Visual Inspection of the External Power Receptacle

3.

Job Set-up Subtask 24-41-00-860-062-A A.

Safety Precautions (1) Make sure that the ground power source is not connected to the aircraft external-power receptacle.

Subtask 24-41-00-010-053-A B.

Get Access (1) Put an access platform in position at the external-power receptacle door (121AL). (2) Open the external-power receptacle door (121AL).

4.

Procedure (Ref. Fig. External Power Receptacle SHEET 1) Subtask 24-41-00-210-051-A A.

Visual Inspection of the Electrical-Power Receptacle Assembly and the External-Power Receptacle Door (1) Examine the electrical-power receptacle assembly. (a) Examine the electrical-power receptacle assembly for overheat damage Ref. SRM 512800. 1

If there is overheat damage: · Clean the electrical-power receptacle assembly with a Textile-Lint free Cotton - (Material No. 14SBA1) and Non Aqueous Cleaner-- Petroleum Based - (Material No. 08BBB1). · Make sure that there are no holes on the receptacle and the adjacent structure.

(b) Examine the electrical-power receptacle assembly for cracks: 1

Make sure that there are no cracks on the external power receptacle and on the adjacent structure.

(c) Examine the aircraft structure around the electrical power receptacle. 1

If the aircraft structure is damaged: · Repair it Ref. SRM 531113.

(2) Examine the external-power receptacle door (121AL). (a) Open and close the external-power receptacle door (121AL). (b) Make sure that the external-power receptacle door (121AL) operates correctly. 1

If the external-power receptacle door (121AL) does not operate correctly: · Replace the external-power receptacle door (121AL) (Ref. AMM TASK 52-42-12-000001) and (Ref. AMM TASK 52-42-12-400-001) .

(3) If the electrical-power receptacle assembly is damaged and the external-power receptacle door (121AL) was not removed: · Put a WARNING NOTICE(S) in position to tell persons not to connect power connector to the electrical power receptacle. · Put a shrink sleeve ABS0916B07 in position below the pins A and B of the electrical power receptacle. Shrink it with a GUN - HOT AIR. 5.

Close-up Subtask 24-41-00-410-053-A A.

Close Access (1) Close the external-power receptacle door (121AL).

Subtask 24-41-00-942-051-A Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 24-41-00-040-001-A - Visual Inspection of the External Power Receptacle

B.

Put the aircraft back to its initial configuration. (1) Remove the access platform(s). (2) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-11-00-040-001-A - Deactivation of the Defective Recline System of the CAPT (F/O) Seat

** ON A/C ALL TASK 25-11-00-040-001-A Deactivation of the Defective Recline System of the CAPT (F/O) Seat

FIN : ** ON A/C ALL EMB SB 25-1559 for A/C 237-237 3MS , 4MS ** ON A/C ALL 1.

Reason for the Job MMEL 25-11-03A Pilot Seat Recline Adjustment

2

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS 211 212

B.

ZONE DESCRIPTION COCKPIT COCKPIT

Referenced Information REFERENCE DESIGNATION (Ref. 25-11-61-000-001-A). Removal of the Captain (First Officer) Seat Cushion (Ref. 25-11-61-400-001-A). Installation of the Captain (First Officer) Seat Cushion (Ref. 25-11-64-000-001-A). Removal of the Captain (First Officer) Seat-Headrest Assy (Ref. 25-11-64-400-001-A). Installation of the Captain (First Officer) Seat-Headrest Assy Defective Recline System of the CAPT (F/O) Seat SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-11-00-040-001-A - Deactivation of the Defective Recline System of the CAPT (F/O) Seat

FR9

A

2

A

A

811 FR1

3 1

C

B B 4 6

B C

5

N_MM_251100_4_AAM0_01_00

Figure 25-11-00-991-00200-00-A / SHEET 1/1 - Defective Recline System of the CAPT (F/O) Seat ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-11-00-040-001-A - Deactivation of the Defective Recline System of the CAPT (F/O) Seat

3.

Job Set-up Subtask 25-11-00-860-056-A A.

Aircraft Maintenance Configuration (1) Remove the Captain (First Officer) seat cushion (Ref. AMM TASK 25-11-61-000-001) .

4.

Procedure (Ref. Fig. Defective Recline System of the CAPT (F/O) Seat SHEET 1) Subtask 25-11-00-040-050-A A.

Deactivation of the Defective Recline System of the CAPT (F/O) Seat (1) If installed, remove the headrest (Ref. AMM TASK 25-11-64-000-001) . NOTE: Only do the step (1) in Para. 4.A. (2) Remove the fourteen screws (2). (3) Remove the upper back shroud (1) from the CAPT (F/O) seat backrest (3). (4) Loosen the screw (4) on the left and right lock levers (6). (5) Remove the cable (5) from the left and right lock levers (6). (6) Push on the left and right lock levers (6) at the same time and push the CAPT (F/O) seat backrest (3) to the vertical position. (7) Release the left and right lock levers (6). (8) Make sure that the seat backrest (3) is correctly locked in the vertical position. (9) Tighten the screw (4) on the left and right lock levers (6). (10) Put the upper back shroud (1) in position on the CAPT (F/O) seat backrest (3). (11) Install and tighten the fourteen screws (2). (12) If removed, install the headrest (Ref. AMM TASK 25-11-64-400-001) . NOTE: Only do the step (11) in Para. 4.A.

5.

Close-up Subtask 25-11-00-860-057-A A.

Aircraft Maintenance Configuration (1) Install the Captain (First Officer) seat cushion (Ref. AMM TASK 25-11-61-400-001) . (2) Make sure that the work area is clean and clear of tools and other items. (3) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-11-00-040-802-A - Deactivation of the Inoperative Adjustment System of the CAPT (F/O) Seat (Electrical Control)

** ON A/C ALL TASK 25-11-00-040-802-A Deactivation of the Inoperative Adjustment System of the CAPT (F/O) Seat (Electrical Control)

FIN : ** ON A/C ALL EMB SB 25-1559 for A/C 237-237 3MS , 4MS ** ON A/C ALL 1.

Reason for the Job MMEL 25-11-01-01 Pilot Seat Electrical Adjustment (FAA only)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Work Zones and Access Panels ZONE/ACCESS 211 212

3.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

ZONE DESCRIPTION COCKPIT COCKPIT

Job Set-up Subtask 25-11-00-860-073-A A.

4.

Not Applicable

Procedure Subtask 25-11-00-040-054-A A.

Deactivate the Inoperative Adjustment System of the CAPT (F/O) Seat (Electrical Control).

Subtask 25-11-00-865-058-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 3MS (SEAT-CAPTAIN) 122VU COCKPIT SEATS/SEAT CTL/CAPT FOR FIN 4MS (SEAT-F/O) 122VU COCKPIT SEATS/SEAT CTL/F/O

5.

FIN

LOCATION

1MS1

U11

1MS2

U14

Close-up Subtask 25-11-00-860-074-A

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-11-00-040-802-A - Deactivation of the Inoperative Adjustment System of the CAPT (F/O) Seat (Electrical Control)

A.

Aircraft Maintenance Configuration (1) Make sure that the work area is clean and clear of tools and other items. (2) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-008-A - Visual Test to Make Sure that the Escape Slide is in the "ARMED" Position

** ON A/C ALL TASK 52-70-00-040-008-A Visual Test to Make Sure that the Escape Slide is in the "ARMED" Position WARNING:

PUT SAFETY BARRIERS IN POSITION TO KEEP THE TRAVEL RANGE OF THE ESCAPE-SLIDE CLEAR. IF YOU DO NOT, INJURY TO PERSONNEL AND/OR DAMAGE TO EQUIPMENT CAN OCCUR.

1.

Reason for the Job MMEL 25-07-03A Cabin Overwing Exit Slide Permanently Indicated Armed on the DOOR/OXY SD page

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS 831, 841

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 52-10-00-010-001-A). (Ref. 52-10-00-410-001-A). 3.

DESIGNATION Opening of the Passenger/Crew Door Closing of the Passenger/Crew Door

Job Set-up Subtask 52-70-00-010-061-A A.

Get Access (1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at applicable forward passenger/crew door 831 or 841. (2) Open the applicable passenger/crew door (Ref. AMM TASK 52-10-00-010-001) .

4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 52-70-00-210-066-A A.

Visual Test to Make Sure that the Escape Slide is in the "ARMED" Position (1) On the Emergency Exit door, make sure that the escape-slide release mechanism is not in the MAINTENANCE mode. (a) Pull down the cover flap of the hatch and remove it. (b) Make sure that the latch pin is not in the "SLIDE DISARMED" position (retracted latch pin). (c) Put the cover flap on the hatch and push it against the hatch.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-008-A - Visual Test to Make Sure that the Escape Slide is in the "ARMED" Position

** ON A/C 401-450 Subtask 52-70-00-210-066-C A.

Visual Test to Make Sure that the Escape Slide is in the "ARMED" Position NOTE: On each side of the cabin, in the cabin lining, one "SLIDE ARMED" indicator light is installed between the OWEs. (1) Open the handle cover to get access to the slide arming mechanism. (2) Set the slide arming mechanism to "SLIDE ARMED". (3) Make sure that the "SLIDE ARMED" light comes into view on the door. (4) Close the handle cover. (5) Make sure that the "SLIDE ARMED" light goes out of view. (6) Open the handle cover. (7) Set the slide arming mechanism to "SLIDE DISARMED" again. (8) Close the handle cover.

** ON A/C ALL 5.

Close-up Subtask 52-70-00-410-061-A A.

Close Access (1) Remove all the ground support equipment, maintenance equipment, standard and special tools and all other items from the inspection area. (2) Obey the special precautions after work on the door (Ref. AMM TASK 52-10-00-410-001) . (3) Close applicable passenger/crew door 831 or 841. (4) Remove the access platform(s). (5) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-009-A - Visual Test to Make Sure that the Escape Slide is in the "ARMED" Position

** ON A/C ALL TASK 52-70-00-040-009-A Visual Test to Make Sure that the Escape Slide is in the "ARMED" Position WARNING:

PUT SAFETY BARRIERS IN POSITION TO KEEP THE TRAVEL RANGE OF THE ESCAPE-SLIDE CLEAR. IF YOU DO NOT, INJURY TO PERSONNEL AND/OR DAMAGE TO EQUIPMENT CAN OCCUR.

1.

Reason for the Job MMEL 25-07-04A Cabin Overwing Exit Slide Permanently Indicated Not Armed on the DOOR/OXY SD page

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS 831, 841

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 52-10-00-010-001-A). (Ref. 52-10-00-410-001-A). 3.

DESIGNATION Opening of the Passenger/Crew Door Closing of the Passenger/Crew Door

Job Set-up Subtask 52-70-00-010-063-A A.

Get Access (1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at applicable forward passenger/crew door 831 or 841. (2) Open the applicable passenger/crew door (Ref. AMM TASK 52-10-00-010-001) .

4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 52-70-00-210-068-A A.

Visual Test to Make Sure that the Escape Slide is in the "ARMED" Position (1) On the Emergency Exit door, make sure that the escape-slide release mechanism is not in the MAINTENANCE mode. (a) Pull down the cover flap of the hatch and remove it. (b) Make sure that the latch pin is not in the "SLIDE DISARMED" position (retracted latch pin). (c) Put the cover flap on the hatch and push it against the hatch.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-009-A - Visual Test to Make Sure that the Escape Slide is in the "ARMED" Position

** ON A/C 401-450 Subtask 52-70-00-210-068-C A.

Visual Test to Make Sure that the Escape Slide is in the "ARMED" Position NOTE: On each side of the cabin, in the cabin lining, one "SLIDE ARMED" indicator light is installed between the OWEs. (1) Open the handle cover to get access to the slide arming mechanism. (2) Set the slide arming mechanism to "SLIDE ARMED". (3) Make sure that the "SLIDE ARMED" light comes into view on the door. (4) Close the handle cover. (5) Make sure that the "SLIDE ARMED" light goes out of view. (6) Open the handle cover. (7) Set the slide arming mechanism to "SLIDE DISARMED" again. (8) Close the handle cover.

** ON A/C ALL 5.

Close-up Subtask 52-70-00-410-063-A A.

Close Access (1) Remove all the ground support equipment, maintenance equipment, standard and special tools and all other items from the inspection area. (2) Obey the special precautions after work on the door (Ref. AMM TASK 52-10-00-410-001) . (3) Close applicable passenger/crew door 831 or 841. (4) Remove the access platform(s). (5) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-11-00-040-003-A - Deactivation of the Third Occupant Seat

** ON A/C ALL TASK 25-11-00-040-003-A Deactivation of the Third Occupant Seat

FIN : 14MM 1.

Reason for the Job MMEL 25-12-01B Third Occupant Seat

2

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS 212

B.

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 25-11-41-000-001-A).

3.

ZONE DESCRIPTION COCKPIT

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Removal of the Third Occupant Seat

Job Set-up Subtask 25-11-00-860-064-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

4.

Procedure Subtask 25-11-00-040-052-A A.

Deactivation of the Third Occupant Seat (1) If the Third Occupant seat is inoperative: · Remove it (Ref. AMM TASK 25-11-41-000-001) .

5.

Close-up Subtask 25-11-00-860-065-A A.

Aircraft Maintenance Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (2) Make an entry in the logbook.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-11-00-040-003-A - Deactivation of the Third Occupant Seat

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-11-00-040-004-A - Deactivation of the Fourth Occupant Seat

** ON A/C 016-022, 024-100, 201-201, 203-222, 226-226, 229-237, 239-250, 350-350 TASK 25-11-00-040-004-A Deactivation of the Fourth Occupant Seat

FIN : 13MM 1.

Reason for the Job MMEL 25-12-05B Fourth Occupant Seat

2

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS 211

B.

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 25-11-42-000-001-A).

3.

ZONE DESCRIPTION COCKPIT

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Removal of the Fourth Occupant Seat

Job Set-up Subtask 25-11-00-860-068-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

4.

Procedure Subtask 25-11-00-040-053-A A.

Deactivation of the Fourth Occupant Seat (1) If the Fourth Occupant seat is inoperative: · Remove it (Ref. AMM TASK 25-11-42-000-001) .

5.

Close-up Subtask 25-11-00-860-069-A A.

Aircraft Maintenance Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (2) Make an entry in the logbook.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-11-00-040-004-A - Deactivation of the Fourth Occupant Seat

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-13-00-040-001-A - Deactivation of the Captain and/or First Officer Sliding-Tables

** ON A/C ALL TASK 25-13-00-040-001-A Deactivation of the Captain and/or First Officer Sliding-Tables

FIN : ** ON A/C ALL EMB SB 25-1559 for A/C 237-237 3MS , 4MS ** ON A/C ALL 1.

Reason for the Job MMEL 25-13-01B Pilot Sliding Table

2

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS 211 212

B.

Referenced Information REFERENCE (Ref. 25-13-14-000-002-A).

3.

ZONE DESCRIPTION COCKPIT COCKPIT

DESIGNATION Removal of the Sliding Table

Job Set-up Subtask 25-13-00-860-051-A A.

4.

Not Applicable

Procedure Subtask 25-13-00-020-050-A A.

Deactivation of the Captain and/or First Officer Sliding-Tables (1) Remove the defective Captain and/or First Officer sliding-tables (Ref. AMM TASK 25-13-14-000002) .

5.

Close-up Subtask 25-13-00-860-052-A A.

Removal of Equipment (1) Make sure that the work area is clean and clear of tools and other items. (2) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-13-00-040-002-A - Deactivation of the Captain and/or First Officer Retractable Foot-Rests

** ON A/C ALL TASK 25-13-00-040-002-A Deactivation of the Captain and/or First Officer Retractable Foot-Rests

FIN : ** ON A/C ALL EMB SB 25-1559 for A/C 237-237 3MS , 4MS ** ON A/C ALL 1.

Reason for the Job MMEL 25-13-02B Pilot Retractable Footrest

2

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS 211 212

B.

Referenced Information REFERENCE (Ref. 25-13-14-000-005-A).

3.

ZONE DESCRIPTION COCKPIT COCKPIT

DESIGNATION Removal of the Captain and First Officer Retractable Foot-Rests

Job Set-up Subtask 25-13-00-860-055-A A.

4.

Not Applicable

Procedure Subtask 25-13-00-020-051-A A.

Deactivation of the Captain and/or First-Officer Retractable Foot-Rests (1) Remove the defective Captain and/or First-Officer retractable foot-rests (Ref. AMM TASK 25-13-14000-005) .

5.

Close-up Subtask 25-13-00-860-056-A A.

Removal of Equipment (1) Make sure that the work area is clean and clear of tools and other items. (2) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-21-00-040-801-A - Deactivation of the Passenger-Seat Recline Function (Locking of the Passenger Seat Backrest in the Taxi, Takeoff and Landing (TTOL) position)

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-229, 231-250, 301-450, 500-600 TASK 25-21-00-040-801-A Deactivation of the Passenger-Seat Recline Function (Locking of the Passenger Seat Backrest in the Taxi, Takeoff and Landing (TTOL) position) Task Summary MMEL or CDL Ref MMEL 25-20-02A

Access NO

1.

Reason for the Job MMEL 25-20-02A Passenger Seat Backrest

2

Job Set-up Information A.

Mhr 00.3

E/T 00.3

Nb Men 1

ZONE DESCRIPTION FWD PASSENGER COMPARTMENT MID PASSENGER COMPARTMENT AFT PASSENGER COMPARTMENT AFT CABIN UTILITY AREA

Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A).

3.

Specific Tools NO

Work Zones and Access Panels ZONE/ACCESS 230 240 250 260

B.

Test YES

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power

Job Set-up Subtask 25-21-00-860-058-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

4.

Procedure Subtask 25-21-00-040-050-A A.

Deactivation of a Passenger-Seat Recline Function (1) Safety the backrest of the related seat in the TTOL position.

Subtask 25-21-00-560-050-A B.

Aircraft Maintenance Configuration (1) Make an entry in the logbook. (2) Remove all the fixtures, tools, test and support equipment used during this procedure. (3) Make sure that the work area is clean and clear of tools and other items.

5.

Close-up

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-21-00-040-801-A - Deactivation of the Passenger-Seat Recline Function (Locking of the Passenger Seat Backrest in the Taxi, Takeoff and Landing (TTOL) position)

Subtask 25-21-00-860-059-A A.

Aircraft Maintenance Configuration (1) De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-21-00-040-802-A - Safetying of the Passenger Seat Backrest in the Taxi, Takeoff and Landing (TTOL) position

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-229, 231-250, 301-450, 500-600 TASK 25-21-00-040-802-A Safetying of the Passenger Seat Backrest in the Taxi, Takeoff and Landing (TTOL) position Task Summary MMEL or CDL Ref MMEL 25-20-02B

Access NO

1.

Reason for the Job MMEL 25-20-02B Passenger Seat Backrest

2

Job Set-up Information A.

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Test YES

QTY DESIGNATION AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 230 240 250 260

ZONE DESCRIPTION FWD PASSENGER COMPARTMENT MID PASSENGER COMPARTMENT AFT PASSENGER COMPARTMENT AFT CABIN UTILITY AREA

C. Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A).

3.

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power

Job Set-up Subtask 25-21-00-860-062-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

4.

Procedure Subtask 25-21-00-040-051-A A.

Deactivation of a Passenger Seat (1) Safety the backrest of the related seat in the TTOL position. (2) Put a WARNING NOTICE(S) in position to tell persons not to use the seat.

Subtask 25-21-00-560-051-A

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-21-00-040-802-A - Safetying of the Passenger Seat Backrest in the Taxi, Takeoff and Landing (TTOL) position

B.

Aircraft Maintenance Configuration (1) Make an entry in the logbook. (2) Remove all the fixtures, tools, test and support equipment used during this procedure. (3) Make sure that the work area is clean and clear of tools and other items.

5.

Close-up Subtask 25-21-00-860-063-A A.

Aircraft Maintenance Configuration (1) De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-21-00-040-803-A - Safetying of the backrest mounted Passenger Meal Table

** ON A/C ALL TASK 25-21-00-040-803-A Safetying of the backrest mounted Passenger Meal Table 1.

Reason for the Job MMEL 25-20-07A Passenger Seat Meal Table

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 200

ZONE DESCRIPTION UPPER HALF FUSELAGE

C. Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A).

3.

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power

Job Set-up Subtask 25-21-00-860-066-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

4.

Procedure Subtask 25-21-00-040-052-A A.

Deactivation of a backrest mounted Passenger Meal Table (1) Safety the backrest mounted meal table of the related seat in the TTOL position. (2) Put a WARNING NOTICE(S) in position to tell persons not to use the seat.

Subtask 25-21-00-560-052-A B.

Aircraft Maintenance Configuration (1) Make an entry in the logbook. (2) Remove all the fixtures, tools, test and support equipment used during this procedure. (3) Make sure that the work area is clean and clear of tools and other items.

5.

Close-up Subtask 25-21-00-860-067-A

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-21-00-040-803-A - Safetying of the backrest mounted Passenger Meal Table

A.

Aircraft Maintenance Configuration (1) De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-22-00-040-001-A - Deactivation of a Defective Cabin Attendant Seat

** ON A/C ALL TASK 25-22-00-040-001-A Deactivation of a Defective Cabin Attendant Seat Task Summary MMEL or CDL Ref MMEL 25-20-09A MMEL 25-20-09B MMEL 25-20-09C 1.

Reason for the Job MMEL 25-20-09A Cabin Attendant Seat MMEL 25-20-09B Cabin Attendant Seat MMEL 25-20-09C Cabin Attendant Seat

2

Job Set-up Information A.

Access NO NO NO

Specific Tools NO NO NO

Mhr 00.2 00.2 00.2

E/T 00.2 00.2 00.2

Nb Men 1 1 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Test NO NO NO

QTY DESIGNATION 1 WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 25-22-41-000-001-A).

DESIGNATION Energize the Ground Service Network from the External Power Removal of the Wall-Mounted Cabin-Attendant Seats

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 205-218, 221-250, 301-450, 500-600 (Ref. 25-22-42-000-001-A). Removal of the Free-Standing Cabin-Attendant Seat(s) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-325, 331-332, 350-350 (Ref. 25-22-43-000-001-A). Removal of the Cabin Attendant Swivel-Seat ** ON A/C ALL 3.

Job Set-up Subtask 25-22-00-861-052-A A.

4.

Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Procedure Subtask 25-22-00-040-050-A A.

Deactivation of a defective Cabin Attendant Seat (1) Safety the affected seat in its stowed position.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-22-00-040-001-A - Deactivation of a Defective Cabin Attendant Seat

(2) Put a WARNING NOTICE(S) in position to tell persons not to use the seat. (3) If you cannot safety the seat, remove it (Ref. AMM TASK 25-22-41-000-001) or (Ref. AMM TASK 25-22-42-000-001) or (Ref. AMM TASK 25-22-43-000-001) . 5.

Close-up Subtask 25-22-00-410-050-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-22-00-040-001-A - Deactivation of a Defective Cabin Attendant Seat

** ON A/C ALL TASK 25-22-00-040-001-A Deactivation of a Defective Cabin Attendant Seat Task Summary MMEL or CDL Ref MMEL 25-20-09A MMEL 25-20-09B MMEL 25-20-09C 1.

Reason for the Job MMEL 25-20-09A Cabin Attendant Seat MMEL 25-20-09B Cabin Attendant Seat MMEL 25-20-09C Cabin Attendant Seat

2

Job Set-up Information A.

Access NO NO NO

Specific Tools NO NO NO

Mhr 00.2 00.2 00.2

E/T 00.2 00.2 00.2

Nb Men 1 1 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Test NO NO NO

QTY DESIGNATION 1 WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 25-22-41-000-001-A).

DESIGNATION Energize the Ground Service Network from the External Power Removal of the Wall-Mounted Cabin-Attendant Seats

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 205-218, 221-250, 301-450, 500-600 (Ref. 25-22-42-000-001-A). Removal of the Free-Standing Cabin-Attendant Seat(s) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-325, 331-332, 350-350 (Ref. 25-22-43-000-001-A). Removal of the Cabin Attendant Swivel-Seat ** ON A/C ALL 3.

Job Set-up Subtask 25-22-00-861-052-A A.

4.

Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Procedure Subtask 25-22-00-040-050-A A.

Deactivation of a defective Cabin Attendant Seat (1) Safety the affected seat in its stowed position.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-22-00-040-001-A - Deactivation of a Defective Cabin Attendant Seat

(2) Put a WARNING NOTICE(S) in position to tell persons not to use the seat. (3) If you cannot safety the seat, remove it (Ref. AMM TASK 25-22-41-000-001) or (Ref. AMM TASK 25-22-42-000-001) or (Ref. AMM TASK 25-22-43-000-001) . 5.

Close-up Subtask 25-22-00-410-050-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-22-00-040-001-A - Deactivation of a Defective Cabin Attendant Seat

** ON A/C ALL TASK 25-22-00-040-001-A Deactivation of a Defective Cabin Attendant Seat Task Summary MMEL or CDL Ref MMEL 25-20-09A MMEL 25-20-09B MMEL 25-20-09C 1.

Reason for the Job MMEL 25-20-09A Cabin Attendant Seat MMEL 25-20-09B Cabin Attendant Seat MMEL 25-20-09C Cabin Attendant Seat

2

Job Set-up Information A.

Access NO NO NO

Specific Tools NO NO NO

Mhr 00.2 00.2 00.2

E/T 00.2 00.2 00.2

Nb Men 1 1 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Test NO NO NO

QTY DESIGNATION 1 WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 25-22-41-000-001-A).

DESIGNATION Energize the Ground Service Network from the External Power Removal of the Wall-Mounted Cabin-Attendant Seats

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 205-218, 221-250, 301-450, 500-600 (Ref. 25-22-42-000-001-A). Removal of the Free-Standing Cabin-Attendant Seat(s) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-325, 331-332, 350-350 (Ref. 25-22-43-000-001-A). Removal of the Cabin Attendant Swivel-Seat ** ON A/C ALL 3.

Job Set-up Subtask 25-22-00-861-052-A A.

4.

Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Procedure Subtask 25-22-00-040-050-A A.

Deactivation of a defective Cabin Attendant Seat (1) Safety the affected seat in its stowed position.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-22-00-040-001-A - Deactivation of a Defective Cabin Attendant Seat

(2) Put a WARNING NOTICE(S) in position to tell persons not to use the seat. (3) If you cannot safety the seat, remove it (Ref. AMM TASK 25-22-41-000-001) or (Ref. AMM TASK 25-22-42-000-001) or (Ref. AMM TASK 25-22-43-000-001) . 5.

Close-up Subtask 25-22-00-410-050-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-20-00-040-001-A - Deactivation of Overhead Stowage Bin(s)/Cabin and Galley Storage Compartment

** ON A/C ALL TASK 25-20-00-040-001-A Deactivation of Overhead Stowage Bin(s)/Cabin and Galley Storage Compartment Task Summary MMEL or CDL Ref MMEL 25-28-41A

Access NO

Test NO

Specific Tools NO

Mhr 00.2

1.

Reason for the Job MMEL 25-28-41A Overhead Storage Bin(s)/Cabin and Galley Storage Compartment/Closets (FAA only)

2

Job Set-up Information A.

DESIGNATION Adhesive Film Tape-- Aluminium Foil -

Referenced Information REFERENCE (Ref. 11-00-00-400-021-A). (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A).

3.

Nb Men 1

Consumable Materials REFERENCE (Material No. 05RAB9)

B.

E/T 00.2

DESIGNATION Installation of the Pressurized Area Placards Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power

Job Set-up Subtask 25-20-00-861-050-A A.

4.

Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Procedure Subtask 25-20-00-040-050-A A.

Deactivation of the Compartment(s) (1) Attach the compartment door(s) with Adhesive Film Tape-- Aluminium Foil - (Material No. 05RAB9) to the compartment bin(s) to make sure that the compartment(s) stays(stay) closed. NOTE: To safety a compartment door only TAPE 3M 425 is recommended. (2) Install placards "UNSERVICEABLE" or "DO NOT USE" on the compartment(s) (Ref. AMM TASK 1100-00-400-021) . NOTE: The compartment(s) must not be used for storage. Only items that are permanently installed can be stowed. NOTE: The compartment(s) must not be used for the storage of emergency equipment.

5.

Close-up

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-20-00-040-001-A - Deactivation of Overhead Stowage Bin(s)/Cabin and Galley Storage Compartment

Subtask 25-20-00-410-051-A A.

Aircraft Maintenance Configuration (1) Make sure that the work area is clean and clear of tools and other items. (2) Make an entry in the logbook.

Subtask 25-20-00-862-050-A B.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-27-00-040-801-A - Deactivation of the Heated Floor Panels

** ON A/C 401-450 TASK 25-27-00-040-801-A Deactivation of the Heated Floor Panels

FIN : 15DS , 16DS 1.

Reason for the Job MMEL 25-27-42A Heating Function of Heated Floor Panels (Passenger/Crew Doors, Emergency Exits, and Galley Areas) (FAA only) (FAA Reference: MMEL 252701) NOTE: This deactivation task is not related to an AFM-CML/MMEL item for all aircraft under EASA or CAAC regulation.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS 100 200

ZONE DESCRIPTION LOWER HALF FUSELAGE INCLUDING RADOME UPPER HALF FUSELAGE

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up Subtask 25-27-00-861-053-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-41-00-861-002) .

4.

Procedure Subtask 25-27-00-865-060-A A.

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

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-27-00-040-801-A - Deactivation of the Heated Floor Panels

PANEL 2001VU 2001VU

DESIGNATION DOOR AREA HTG PNL-DOOR3-HTR DR AREA HTG PNLS-DOOR 3-CTL

FIN 11DS 13DS

LOCATION F05 F03

Subtask 25-27-00-040-051-B B.

Deactivation of the Heated Floor Panels at the Emergency Exit Doors (1) Remove the related fuse from the applicable control unit: · HFP 15DS (LH) / Control Unit 14DS - Heater 1 · HFP 16DS (RH) / Control Unit 14DS - Heater 2 (2) Install a blanking cap on the related fuse socket. (3) Install a grey INOP label adjacent to the related LED light/fuse on the control unit. (4) Make an entry in the logbook that the related heated floor panel is deactivated.

Subtask 25-27-00-865-062-A C.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 2001VU 2001VU

5.

DESIGNATION DOOR AREA HTG PNL-DOOR3-HTR DR AREA HTG PNLS-DOOR 3-CTL

FIN 11DS 13DS

LOCATION F05 F03

Close-up Subtask 25-27-00-862-053-A A.

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

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-35-00-040-001-A - Deactivation of the Galley-Waste-Compartment Flapper-Door

** ON A/C ALL TASK 25-35-00-040-001-A Deactivation of the Galley-Waste-Compartment Flapper-Door Task Summary MMEL or CDL Ref MMEL 25-35-01A

Access NO

Test NO

Specific Tools NO

1.

Reason for the Job MMEL 25-35-01A Galley Waste Compartment Flapper Door (If Installed)

2

Job Set-up Information A.

E/T 00.2

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Mhr 00.2

QTY DESIGNATION 1 WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. 05RAB9)

DESIGNATION Adhesive Film Tape-- Aluminium Foil -

C. Referenced Information REFERENCE DESIGNATION Galley-Waste-Compartment Flapper-Door SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-35-00-040-001-A - Deactivation of the Galley-Waste-Compartment Flapper-Door

EXAMPLE

A EXAMPLE

WASTE CHUTE

FLAPPER DOOR

C WASTE COMPARTMENT

CONTAINER

A

C EXAMPLE

4

1 ACCESS DOOR 5

1

B 6

1

B EXAMPLE

1

9

1 2 8 3

NOTE: 1

7

IF INSTALLED

N_MM_253500_4_AAA0_01_01

Figure 25-35-00-991-00100-00-A / SHEET 1/1 - Galley-Waste-Compartment Flapper-Door ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-35-00-040-001-A - Deactivation of the Galley-Waste-Compartment Flapper-Door

3.

Job Set-up Subtask 25-35-00-861-077-A A.

4.

There is no special job set-up for this task.

Procedure Subtask 25-35-00-040-050-A A.

Deactivation of the Defective or Missing Waste-Compartment Flapper-Door (Ref. Fig. Galley-Waste-Compartment Flapper-Door SHEET 1) (1) Seal the opening of the waste chute with self adhesive tape Adhesive Film Tape-- Aluminium Foil - (Material No. 05RAB9). (2) Put a WARNING NOTICE(S) in position to tell persons not to use the waste compartment. (3) Open the access door of the waste compartment: (a) Make sure that the waste container is empty.

5.

Close-up Subtask 25-35-00-410-067-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access door of the waste compartment. (3) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-35-00-040-802-A - Deactivation of the GalleyWaste-Compartment Access Door (If Installed)

** ON A/C ALL TASK 25-35-00-040-802-A Deactivation of the Galley-Waste-Compartment Access Door (If Installed) 1.

Reason for the Job MMEL 25-35-02A Galley Waste Compartment Access Door (If Installed)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. 05RAB9)

DESIGNATION Adhesive Film Tape-- Aluminium Foil -

C. Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A). (Ref. 25-35-00-040-001-A). 3.

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power Deactivation of the Galley-Waste-Compartment Flapper-Door

Job Set-up Subtask 25-35-00-860-092-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Subtask 25-35-00-010-096-A B.

Get Access (1) In the galley with the defective access door: · Get access to the galley-waste-compartment.

4.

Procedure Subtask 25-35-00-040-051-A A.

Deactivation (1) Make sure that the waste container is empty. (2) Deactivate the galley-waste-compartment flapper door (Ref. AMM TASK 25-35-00-040-001) . (3) Close the access door and attach it to the galley with Adhesive Film Tape-- Aluminium Foil - (Material No. 05RAB9) to make sure that it cannot open. (4) Put the WARNING NOTICE(S) in position to tell persons not to use the galley-waste-compartment. (5) Make an entry in the logbook.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-35-00-040-802-A - Deactivation of the GalleyWaste-Compartment Access Door (If Installed)

5.

Close-up Subtask 25-35-00-862-083-A A.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-40-00-040-001-A - Deactivation of the Toilet Waste-Compartment Flapper-Door

** ON A/C ALL TASK 25-40-00-040-001-A Deactivation of the Toilet Waste-Compartment Flapper-Door Task Summary MMEL or CDL Ref MMEL 25-40-01A

Access NO

Test NO

1.

Reason for the Job MMEL 25-40-01A Toilet Waste Compartment Flapper Door

2

Job Set-up Information A.

Mhr 00.2

E/T 00.2

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Specific Tools NO

QTY DESIGNATION 1 WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. 05RAB9)

DESIGNATION Adhesive Film Tape-- Aluminium Foil -

C. Work Zones and Access Panels ZONE/ACCESS 200

ZONE DESCRIPTION UPPER HALF FUSELAGE

D. Referenced Information REFERENCE Flapper Door SHEET 1

DESIGNATION

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-40-00-040-001-A - Deactivation of the Toilet Waste-Compartment Flapper-Door

LAVATORY EXAMPLE

A WASTE CHUTE

B

EXAMPLE

A

C

WASTE COMPARTMENT

EXAMPLE

WASTE CONTAINER

B EXAMPLE

C

FLAPPER DOOR ACCESS DOOR

N_MM_254000_4_AAM0_01_00

Figure 25-40-00-991-01500-00-A / SHEET 1/1 - Flapper Door ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-40-00-040-001-A - Deactivation of the Toilet Waste-Compartment Flapper-Door

3.

Job Set-up Subtask 25-40-00-861-056-A A.

4.

There is no special job set-up for this task.

Procedure Subtask 25-40-00-040-050-A A.

Deactivation of the Defective or Missing Waste-Compartment Flapper-Door (Ref. Fig. Flapper Door SHEET 1) (1) Seal the opening of the waste chute with self adhesive tape Adhesive Film Tape-- Aluminium Foil - (Material No. 05RAB9). (2) Put a WARNING NOTICE(S) in position to tell persons not to use the waste compartment. (3) Open the access door of the waste compartment: (a) Make sure that the waste container is empty.

5.

Close-up Subtask 25-40-00-410-062-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access door of the waste compartment. (3) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-40-00-040-802-A - Deactivation of the Toilet Waste-Compartment Access-Door

** ON A/C ALL TASK 25-40-00-040-802-A Deactivation of the Toilet Waste-Compartment Access-Door 1.

Reason for the Job MMEL 25-40-04A Toilet Waste Compartment Access Door

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION 1 WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. 05RAB9)

DESIGNATION Adhesive Film Tape-- Aluminium Foil -

C. Referenced Information REFERENCE Access Door SHEET 1

DESIGNATION

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-40-00-040-802-A - Deactivation of the Toilet Waste-Compartment Access-Door

WASTE CHUTE

A

B TYPICAL

C

WASTE COMPARTMENT WASTE CONTAINER

A TYPICAL

ACCESS DOOR

B

FLAPPER DOOR

TYPICAL

C TYPICAL N_MM_254000_4_AANA_01_00

Figure 25-40-00-991-03300-00-A / SHEET 1/1 - Access Door ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-40-00-040-802-A - Deactivation of the Toilet Waste-Compartment Access-Door

3.

Job Set-up Subtask 25-40-00-861-073-A A.

4.

There is no special job set-up for this task.

Procedure Subtask 25-40-00-040-051-A A.

Deactivation of the Toilet Waste-Compartment Access-Door (Ref. Fig. Access Door SHEET 1) (1) Open the access door of the waste compartment. (a) Make sure that the waste container is empty. (2) Seal the opening of the waste chute with Adhesive Film Tape-- Aluminium Foil - (Material No. 05RAB9). (3) Put the WARNING NOTICE(S) in position to tell persons not to use the waste compartment. (4) Seal the access door with Adhesive Film Tape-- Aluminium Foil - (Material No. 05RAB9).

5.

Close-up Subtask 25-40-00-410-071-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access door of the waste compartment. (3) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-54-00-040-801-A - Deactivation of the Protection Panel(s) for the Decompression Panel(s) at the Forward Partition

** ON A/C ALL TASK 25-54-00-040-801-A Deactivation of the Protection Panel(s) for the Decompression Panel(s) at the Forward Partition Task Summary MMEL or CDL Ref MMEL 25-50-05A

Access NO

Test NO

Specific Tools NO

Mhr 00.5

E/T 00.5

Nb Men 1

1.

Reason for the Job MMEL 25-50-05A Protection Panels of Decompression Panels at the FWD Partition Wall of FWD Cargo Compartment (If Installed)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

QTY 1 AR 1

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 130

ZONE DESCRIPTION FWD CAR COMPT AFT BULKHEAD OF AVNCS COMP TO FWD PRESSURE BULKHEAD OF WING CENTER BOX

C. Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A).

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power (Ref. 25-50-00-200-024-A). Cargo Compartment Linings with Honeycomb Core - General Repair/Protection Information (Ref. 25-54-11-000-001-A). Removal of the Forward Cargo-Compartment Partition FR24A (Ref. 52-30-00-860-001-A). Open the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump (Ref. 52-30-00-860-002-A). Close the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump Clear Area if the Protection Panel is damaged SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-54-00-040-801-A - Deactivation of the Protection Panel(s) for the Decompression Panel(s) at the Forward Partition

EXAMPLE

FR34

FR31

FR28

FR24A

Z130

FR34

EXAMPLE FR31

FR28

FR24A

Z130

NOTE: CLEAR AREA THESE ILLUSTRATIONS ARE ONLY EXAMPLES. OTHER DEVIDER NET CONFIGURATIONS CAN OCCUR. N_MM_255400_4_AAAA_01_00

Figure 25-54-00-991-00100-00-A / SHEET 1/1 - Clear Area if the Protection Panel is damaged ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-54-00-040-801-A - Deactivation of the Protection Panel(s) for the Decompression Panel(s) at the Forward Partition

3.

Job Set-up Subtask 25-54-00-860-050-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) . (2) Open the forward cargo-compartment door (Ref. AMM TASK 52-30-00-860-001) . (3) Put a ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the opening of the forward cargo-compartment door. (4) Set the light switch to on. (5) Put a WARNING NOTICE(S) in position on the control panel of the forward cargo-compartment loading-system to tell persons not to use it.

Subtask 25-54-00-865-050-A B.

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

DESIGNATION

FIN

LOCATION

** ON A/C 206-206, 209-209, 227-228 EMB SB 25-1569 for A/C 209-209 2000VU SEMI AUTO CLS-FWD 2000VU SEMI AUTO CLS-FWD

3MY 2MY

E08 E06

** ON A/C ALL 4.

Procedure Subtask 25-54-00-040-050-A A.

Deactivation of the Protection Panels (Ref. Fig. Clear Area if the Protection Panel is damaged SHEET 1) (1) Identify the protection panel(s) damage limits (Ref. AMM TASK 25-50-00-200-024) . (2) If the damage prevents correct operation of the decompression panel(s): (a) Remove the related protection panel(s) (Ref. AMM TASK 25-54-11-000-001) . (b) Remove all cargo load between the forward partition at frame 24A and the nearest divider net.

5.

Close-up Subtask 25-54-00-865-051-A A.

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

DESIGNATION

FIN

LOCATION

** ON A/C 206-206, 209-209, 227-228 EMB SB 25-1569 for A/C 209-209 2000VU SEMI AUTO CLS-FWD 2000VU SEMI AUTO CLS-FWD

3MY 2MY

E08 E06

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-54-00-040-801-A - Deactivation of the Protection Panel(s) for the Decompression Panel(s) at the Forward Partition

** ON A/C ALL Subtask 25-54-00-860-051-A B.

Put the aircraft back to its initial configuration. (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the WARNING NOTICE(S). (3) Set the light switch to off. (4) Remove the access platform(s). (5) Close the forward cargo-compartment door (Ref. AMM TASK 52-30-00-860-002) . (6) Make an entry in the logbook. (7) De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-006-A - Pre-Flight Installation of the Enclosure Door, when the Escape-Slide is Removed

** ON A/C ALL TASK 25-62-00-040-006-A Pre-Flight Installation of the Enclosure Door, when the Escape-Slide is Removed Task Summary MMEL or CDL Ref MMEL 25-62-02B

Access NO

1.

Reason for the Job MMEL 25-62-02B Cabin Overwing Exit Slide

2

Job Set-up Information A.

Test NO

Specific Tools YES

Mhr 00.5

E/T 00.5

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

QTY DESIGNATION 1 ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 No specific 1 SCREWDRIVER - PHILLIPS HEAD ** ON A/C ALL No specific B.

1

WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 27-00-00-480-002-A).

DESIGNATION Installation of the Flap/Slat Control-Lever Locking Tool (98D27803000000)

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Installation of the Enclosure Door SHEET 1 ** ON A/C 416-450 Enclosure Door Installation ** ON A/C 401-415 Enclosure Door Installation

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-006-A - Pre-Flight Installation of the Enclosure Door, when the Escape-Slide is Removed

Z826

A 194AT

FR47

EXAMPLE 152KW 151KW

A FR48

B

Z150 3

193AT

SECTION 5

2

C-C EXAMPLE

1

PUSH

B

10

EXAMPLE PHILLIPS SCREWDRIVER

C 9

6

C

6

4

6 7

8

5

N_MM_256200_4_DWE0_01_00

Figure 25-62-00-991-01400-00-A / SHEET 1/1 - Installation of the Enclosure Door ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-006-A - Pre-Flight Installation of the Enclosure Door, when the Escape-Slide is Removed

Z150 AFT CARGO COMPARTMENT DOOR

7684MM

FR59

A A C 152BW

FR47.1

7683MM

151AW 151BW

FR47.2 FR46

C FR47

B 2 1 3 1

A TYPICAL

B TYPICAL N_MM_256200_4_DWN0_01_02

Figure 25-62-00-991-01400-00-D / SHEET 1/2 - Enclosure Door Installation ** ON A/C 416-450 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-006-A - Pre-Flight Installation of the Enclosure Door, when the Escape-Slide is Removed

4

E E E 5

193AT (194AT)

D

C

01

TYPICAL

7

D

8

8

6

TYPICAL 9

CORRECT

E

WRONG

TYPICAL NOTE: 01 LH SHOWN, RH SYMMETRICAL

N_MM_256200_4_DWN0_02_02

Figure 25-62-00-991-01400-00-D / SHEET 2/2 - Enclosure Door Installation ** ON A/C 416-450 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-006-A - Pre-Flight Installation of the Enclosure Door, when the Escape-Slide is Removed

7686MM

C

Z250

C 7685MM

B

A B A E

E

1

FR47.2 Z150

A

FR47

TYPICAL

2

D

B TYPICAL

3

C TYPICAL N_MM_256200_4_AZB1_01_00

Figure 25-62-00-991-01400-00-E / SHEET 1/2 - Enclosure Door Installation ** ON A/C 401-415 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-006-A - Pre-Flight Installation of the Enclosure Door, when the Escape-Slide is Removed

3 4

6 5

D TYPICAL

G G G 7

193AT (194AT)

F

E

01

TYPICAL 10

10

11 9

8

F TYPICAL CORRECT NOTE: 01 LH SHOWN, RH SYMMETRICAL

G

WRONG

TYPICAL N_MM_256200_4_AZB1_02_00

Figure 25-62-00-991-01400-00-E / SHEET 2/2 - Enclosure Door Installation ** ON A/C 401-415 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-006-A - Pre-Flight Installation of the Enclosure Door, when the Escape-Slide is Removed

3.

Job Set-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 25-62-00-860-064-A WARNING:

A.

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.

Aircraft Maintenance Configuration (Ref. Fig. Installation of the Enclosure Door SHEET 1) NOTE: The lockpin (3) and the pressure blanking-plug (7) are kept in a pocket which is attached to the inflation reservoir (1). (1) If the inflation reservoir (1) is charged, install the lockpin (3) in the regulator valve assembly (2). (2) Safety the flaps (Ref. AMM TASK 27-00-00-480-002) . (3) Put the WARNING NOTICE(S) on the slat/flap control lever to tell persons not to operate the flaps during the installation procedure. (4) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position adjacent to the related enclosure (4). (5) Install the blanking plug (7) on the enclosure connection (8).

** ON A/C 416-450 Subtask 25-62-00-860-064-C WARNING:

A.

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.

Aircraft Maintenance Configuration (Ref. Fig. Enclosure Door Installation) NOTE: The lockpin (3) and the pressure blanking-plug (6) are kept in a pocket which is attached to the inflation reservoir (1). (1) If the inflation reservoir (1) is charged, install the lockpin (3) in the regulator valve assembly (2). (2) Safety the flaps (Ref. AMM TASK 27-00-00-480-002) . (3) Put the WARNING NOTICE(S) on the slat/flap control lever to tell persons not to operate the flaps during the installation procedure.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-006-A - Pre-Flight Installation of the Enclosure Door, when the Escape-Slide is Removed

(4) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position adjacent to the related enclosure (4). (5) Install the blanking plug (6) on the enclosure connection (7). ** ON A/C 401-415 Subtask 25-62-00-860-064-D A.

Aircraft Maintenance Configuration (Ref. Fig. Enclosure Door Installation) 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. (1) Open the door of the overhead stowage compartment (1) and push the quick-release fasteners (2). NOTE: The lockpin (4) and the pressure blanking-plug (8) are kept in a pocket which is attached to the inflation reservoir (3). (2) If the inflation reservoir (3) is charged, install the lockpin (4) in the regulator valve assembly (5). (3) Safety the flaps (Ref. AMM TASK 27-00-00-480-002) . (4) Put the WARNING NOTICE(S) on the slat/flap control lever to tell persons not to operate the flaps during the installation procedure. (5) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position adjacent to the related enclosure (6). (6) Install the blanking plug (8) on the enclosure connection (9).

** ON A/C ALL 4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 25-62-00-040-052-A A.

Installation Procedure of the Enclosure Door (Ref. Fig. Installation of the Enclosure Door SHEET 1) NOTE: For the MMEL dispatch configuration the escape slide enclosure must stay installed. (1) Put the lower edge of the enclosure door (5) in the groove in the bottom of the enclosure (4). (2) Close the enclosure door (5) on the three ball-lock assemblies (6). (3) Push the head of the lockpin (10) with a SCREWDRIVER - PHILLIPS HEAD, then: (a) Apply force to the enclosure door (5) adjacent to the lockpin (9). (b) Remove the screwdriver. (c) Continue to push the enclosure door (5) until the lockpin (9) moves quickly back to a flush position with the surface of the enclosure door (5).

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-006-A - Pre-Flight Installation of the Enclosure Door, when the Escape-Slide is Removed

(4) Do this procedure with each lockpin (9). (5) Make an entry in the logbook to record the procedure. ** ON A/C 416-450 Subtask 25-62-00-040-052-C A.

Installation Procedure of the Enclosure Door (Ref. Fig. Enclosure Door Installation) NOTE: For the MMEL dispatch configuration the escape slide enclosure must stay installed. (1) Make sure that the ball-lock pins (8) are engaged correctly and you cannot see the red O-rings (9). (2) Put the lower edge of the enclosure door (5) in the groove in the bottom of the enclosure (4). (3) Push the enclosure door (5) on the three ball-lock assemblies (8) to engage it. (4) Make sure that the enclosure door (5) is installed correctly and it is flush with the surface of the enclosure (4). (5) Make an entry in the logbook to record the procedure.

** ON A/C 401-415 Subtask 25-62-00-040-052-D A.

Installation Procedure of the Enclosure Door (Ref. Fig. Enclosure Door Installation) NOTE: For the MMEL dispatch configuration the escape slide enclosure must stay installed. (1) Make sure that the ball-lock pins (10) are engaged correctly and you cannot see the red O-rings (11). (2) Put the lower edge of the enclosure door (7) in the groove in the bottom of the enclosure (6). (3) Push the enclosure door (7) on the three ball-lock assemblies (10) to engage it. (4) Make sure that the enclosure door (7) is installed correctly and it is flush with the surface of the enclosure (6). (5) Make an entry in the logbook to record the procedure.

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 25-62-00-869-054-A B.

System Consequences (1) The message 'SLIDE PRESSURE LOW' shows on the programming and test panel (PTP).

** ON A/C 401-450 Subtask 25-62-00-869-054-C B.

System Consequences (1) The message 'CHECK SLIDE PRESSURE' shows on the flight attendant panel (FAP).

** ON A/C ALL 5.

Close-up Subtask 25-62-00-860-065-A A.

Aircraft Maintenance Configuration

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-006-A - Pre-Flight Installation of the Enclosure Door, when the Escape-Slide is Removed

(1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION (98D27803000000) from the slat/flap control lever. (3) Remove the WARNING NOTICE(S). (4) Remove the access platform(s).

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-007-A - Pre-Flight Installation of the Enclosure Door, when the Escape-Slide is Removed

** ON A/C 401-450 TASK 25-62-00-040-007-A Pre-Flight Installation of the Enclosure Door, when the Escape-Slide is Removed Task Summary MMEL or CDL Ref MMEL 25-62-01B

Access NO

1.

Reason for the Job MMEL 25-62-01B Cabin Door Slide or Slide Raft

2

Job Set-up Information A.

Specific Tools YES

Mhr 00.5

E/T 00.5

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Test NO

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT)

Referenced Information REFERENCE Enclosure Door Installation

DESIGNATION

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-007-A - Pre-Flight Installation of the Enclosure Door, when the Escape-Slide is Removed

Z250 Z844

C A

C Z834

D

A

D FR51

Z150

B

FR48

B

1

A TYPICAL

2

B TYPICAL 3

4 5

C TYPICAL N_MM_256200_4_DENA_01_01

Figure 25-62-00-991-01300-00-B / SHEET 1/2 - Enclosure Door Installation ** ON A/C 401-450 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-007-A - Pre-Flight Installation of the Enclosure Door, when the Escape-Slide is Removed

6

F E F F

7

D

01

TYPICAL 10 8

10 11

9

CORRECT

E TYPICAL NOTE: 01 RH SHOWN, LH SYMMETRICAL

WRONG

F TYPICAL N_MM_256200_4_DENA_02_01

Figure 25-62-00-991-01300-00-B / SHEET 2/2 - Enclosure Door Installation ** ON A/C 401-450 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-007-A - Pre-Flight Installation of the Enclosure Door, when the Escape-Slide is Removed

3.

Job Set-up Subtask 25-62-00-860-062-B A.

Aircraft Maintenance Configuration (Ref. Fig. Enclosure Door Installation) NOTE: The lockpin (3) and the pressure blanking-plug (9) are kept in a pocket which is attached to the inflation reservoir (5). (1) If the inflation reservoir (5) is charged, install the lockpin (3) in the regulator valve assembly (4). (2) Put an ACCESS PLATFORM 2M (6 FT) in position adjacent to the related emergency-exit door. (3) Install the pressure blanking-plug (9) on the enclosure connection (8).

4.

Procedure Subtask 25-62-00-040-053-B A.

Installation of the Enclosure Door (Ref. Fig. Enclosure Door Installation) (1) Make sure that the ball-lock pins (10) are engaged correctly and you cannot see the red O-rings (11). (2) Put the bottom edge of the enclosure door (7) into the groove in the bottom of the enclosure (6). (3) Push the enclosure door (7) on the three ball-lock assemblies (8) to engage it. (4) Make sure that the enclosure door (7) is installed correctly and it is flush with the surface of the enclosure (6). (5) Make an entry in the logbook.

Subtask 25-62-00-869-055-B B.

Effect on the System (1) The flight attendant panel, if the cabin assignment model is programmed to monitor the inflation reservoirs (1), shows the message "SLIDE PRESSURE LOW".

5.

Close-up Subtask 25-62-00-860-063-B A.

Aircraft Maintenance Configuration (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the access platform(s).

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-001-A - Deactivation of the Passenger/Crew Doors - Load Adjustment

** ON A/C ALL TASK 52-10-00-040-001-A Deactivation of the Passenger/Crew Doors - Load Adjustment Task Summary MMEL or CDL Ref MMEL 25-62-01B

Access YES

Test YES

Specific Tools NO

Mhr

E/T

Nb Men

1.

Reason for the Job MMEL 25-62-01B Cabin Door Slide or Slide Raft There is an alternative method for this procedure. This task gives one of the methods. For the other method, refer to the other task in this page block.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

QTY 1 1 AR

DESIGNATION ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE DYNAMOMETER 20 DAN (45 LBF) - PULL SAFETY CLIP - CIRCUIT BREAKER

Consumable Materials REFERENCE (Material No. 14QFB1)

DESIGNATION Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -

C. Work Zones and Access Panels ZONE/ACCESS 831, 831AZ, 832, 832AZ, 841, 841AZ, 842, 842AZ

ZONE DESCRIPTION

D. Referenced Information REFERENCE (Ref. 25-23-46-000-001-A). (Ref. 25-23-46-000-002-A).

DESIGNATION Removal of the Door Linings at the Forward Passenger/Crew Doors Removal of the Door Linings at the Aft Passenger/Crew Doors

** ON A/C 016-022, 024-044, 054-054, 059-059, 061-072, 075-075, 080-080, 204-205, 207-208, 210-210, 212-214, 219-221, 223-228, 230-230, 234-234, 301-349, 351-353, 356-356, 370-400, 500-600 PRE SB 25-1B07 for A/C 207-207 PRE SB 25-1BRN for A/C 018-018, 037-037, 043-043 (Ref. 25-62-44-000-002-A). Removal of the Left-Hand Escape-Slide Pack-Assembly (Ref. 25-62-44-000-010-A). Removal of the Inflated Left-Hand Escape-Slide

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-001-A - Deactivation of the Passenger/Crew Doors - Load Adjustment

REFERENCE

DESIGNATION

** ON A/C 045-053, 055-058, 060-060, 073-074, 076-079, 081-100, 112-150, 201-201, 203-203, 206-206, 209-209, 211-211, 215-218, 222-222, 229-229, 231-233, 235-250, 350-350, 354-355, 357-369, 401-450 POST SB 25-1B07 for A/C 207-207 (Ref. 25-62-44-000-011-A). Removal of the Inflated Left-Hand Escape-Slide-Raft (Ref. 25-62-44-000-012-A). Removal of the Left-Hand Escape-Slide-Raft Pack-Assembly ** ON A/C 016-022, 024-044, 054-054, 059-059, 061-072, 075-075, 080-080, 204-205, 207-208, 210-210, 212-214, 219-221, 223-228, 230-230, 234-234, 301-349, 351-353, 356-356, 370-400, 500-600 PRE SB 25-1B07 for A/C 207-207 PRE SB 25-1BRN for A/C 018-018, 037-037, 043-043 (Ref. 25-62-44-000-802-A). Removal of the Right-Hand Escape-Slide Pack-Assembly (Ref. 25-62-44-000-803-A). Removal of the Inflated Right-Hand Escape-Slide ** ON A/C 045-053, 055-058, 060-060, 073-074, 076-079, 081-100, 112-150, 201-201, 203-203, 206-206, 209-209, 211-211, 215-218, 222-222, 229-229, 231-233, 235-250, 350-350, 354-355, 357-369, 401-450 POST SB 25-1B07 for A/C 207-207 (Ref. 25-62-44-000-804-A). Removal of the Right-Hand Escape-Slide-Raft Pack-Assembly (Ref. 25-62-44-000-805-A). Removal of the Inflated Right-Hand Escape-Slide-Raft ** ON A/C ALL (Ref. 52-10-00-010-001-A). (Ref. 52-10-00-410-001-A). (Ref. 52-10-00-860-001-A). (Ref. 52-10-00-860-002-A).

Opening of the Passenger/Crew Door Closing of the Passenger/Crew Door Special Precautions before Work on the Passenger/Crew Door Special Precautions after Work on the Passenger/Crew Door

** ON A/C 016-022, 024-044, 054-054, 059-059, 061-072, 075-075, 080-080, 204-205, 207-208, 210-210, 212-214, 219-221, 223-228, 230-230, 234-234, 239-239, 301-353, 356-356, 370-400, 500-600 PRE SB 25-1B07 for A/C 207-207 PRE SB 25-1BRN for A/C 018-018, 037-037, 043-043 Load Adjustment of the Inner Control Handle SHEET 1 ** ON A/C 045-053, 055-058, 060-060, 073-074, 076-079, 081-100, 112-150, 201-201, 203-203, 206-206, 209-209, 211-211, 215-218, 222-222, 229-229, 231-233, 235-238, 240-250, 354-355, 357-369, 401-450 POST SB 25-1B07 for A/C 207-207 POST SB 25-1BRN for A/C 018-018, 037-037, 043-043 Load Adjustment of the Inner Control Handle SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-001-A - Deactivation of the Passenger/Crew Doors - Load Adjustment

Z842

A Z832

Z841

A

A

Z831

B

B

1

2 N_MM_521000_4_AAM0_01_00

Figure 52-10-00-991-03000-00-A / SHEET 1/1 - Load Adjustment of the Inner Control Handle ** ON A/C 016-022, 024-044, 054-054, 059-059, 061-072, 075-075, 080-080, 204-205, 207-208, 210210, 212-214, 219-221, 223-228, 230-230, 234-234, 239-239, 301-353, 356-356, 370-400, 500600 | PRE SB 25-1B07 for A/C 207-207 | PRE SB 25-1BRN for A/C 018-018, 037-037, 043-043 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-001-A - Deactivation of the Passenger/Crew Doors - Load Adjustment

Z842

A

A

Z832

A

Z841

Z831

B B

1

2 N_MM_521000_4_AAN0_01_00

Figure 52-10-00-991-03000-00-B / SHEET 1/1 - Load Adjustment of the Inner Control Handle ** ON A/C 045-053, 055-058, 060-060, 073-074, 076-079, 081-100, 112-150, 201-201, 203-203, 206206, 209-209, 211-211, 215-218, 222-222, 229-229, 231-233, 235-238, 240-250, 354-355, 357-369, 401450 | EMB SB 25-1595 for A/C 218-218 | POST SB 25-1B07 for A/C 207-207 | EMB SB 25-1BDU for A/ C 073-074, 076-079, 081-084, 087-087, 091-091 | POST SB 25-1BRN for A/C 018-018, 037-037, 043-043 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-001-A - Deactivation of the Passenger/Crew Doors - Load Adjustment

3.

Job Set-up Subtask 52-10-00-010-083-A A.

Get Access (1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at zone 831(841) or 832(842). (2) Open applicable passenger/crew doors 831, 841 or 832, 842 (Ref. AMM TASK 52-10-00-010-001) . (3) Obey the special precautions before you start work on the door (Ref. AMM TASK 52-10-00-860001) .

Subtask 52-10-00-865-073-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU 121VU

DESIGNATION EIS/SLIDES/ARM AND WARN/FLT EIS/SLIDES/ARM AND WARN/GND EIS/SDAC1 AND 2/DOOR/DET/PAX

FIN 15WN 13WN 48WV

LOCATION P11 P10 P05

** ON A/C 016-022, 024-044, 054-054, 059-059, 061-072, 075-075, 080-080, 204-205, 207-208, 210-210, 212214, 219-221, 223-228, 230-230, 234-234, 301-349, 351-353, 356-356, 370-400, 500-600 PRE SB 25-1B07 for A/C 207-207 PRE SB 25-1BRN for A/C 018-018, 037-037, 043-043 Subtask 52-10-00-010-084-A C.

Removal of the Escape Slide (1) Remove the door lining panels: (a) For the forward passenger/crew doors: (Ref. AMM TASK 25-23-46-000-001) · For left door 831AZ · For right door 841AZ. (b) For the aft passenger/crew doors: (Ref. AMM TASK 25-23-46-000-002) · For left door 832AZ · For right door 842AZ. (2) Remove the escape slide: (a) For the left door, if installed: · Remove the left escape-slide pack-assembly (Ref. AMM TASK 25-62-44-000-002) . · Remove the inflated left escape-slide (Ref. AMM TASK 25-62-44-000-010) . (b) For the right door, if installed: · Remove the right escape-slide pack-assembly (Ref. AMM TASK 25-62-44-000-802) . · Remove the inflated right escape-slide (Ref. AMM TASK 25-62-44-000-803) .

** ON A/C 045-053, 055-058, 060-060, 073-074, 076-079, 081-100, 112-150, 201-201, 203-203, 206-206, 209209, 211-211, 215-218, 222-222, 229-229, 231-233, 235-250, 350-350, 354-355, 357-369, 401-450 POST SB 25-1B07 for A/C 207-207 POST SB 25-1BRN for A/C 018-018, 037-037, 043-043 EMB SB 25-1587 for A/C 239-239, 350-350 EMB SB 25-1595 for A/C 218-218

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-001-A - Deactivation of the Passenger/Crew Doors - Load Adjustment

EMB SB 25-1BDU for A/C 073-074, 076-079, 081-084, 087-087, 091-091 Subtask 52-10-00-010-084-B C.

Removal of the Escape Slide Raft (1) Remove the door lining panels: (a) For the forward passenger/crew doors: (Ref. AMM TASK 25-23-46-000-001) · For left door 831AZ · For right door 841AZ. (b) For the aft passenger/crew doors: (Ref. AMM TASK 25-23-46-000-002) · For left door 832AZ · For right door 842AZ. (2) Remove the escape slide: (a) For the left door, if installed: · Remove the left escape-slide raft-pack-assembly (Ref. AMM TASK 25-62-44-000-012) . · Remove the inflated left escape-slide-raft (Ref. AMM TASK 25-62-44-000-011) . (b) For the right door, if installed: · Remove the right escape-slide raft-pack-assembly (Ref. AMM TASK 25-62-44-000-804) . · Remove the inflated right escape-slide-raft (Ref. AMM TASK 25-62-44-000-805) .

** ON A/C ALL 4.

Procedure Subtask 52-10-00-820-050-A A.

Load Adjustment of the Inner Control Handle

** ON A/C 016-022, 024-044, 054-054, 059-059, 061-072, 075-075, 080-080, 204-205, 207-208, 210-210, 212-214, 219-221, 223-228, 230-230, 234-234, 239-239, 301-353, 356-356, 370-400, 500-600 PRE SB 25-1B07 for A/C 207-207 PRE SB 25-1BRN for A/C 018-018, 037-037, 043-043 (Ref. Fig. Load Adjustment of the Inner Control Handle SHEET 1) ** ON A/C 045-053, 055-058, 060-060, 073-074, 076-079, 081-100, 112-150, 201-201, 203-203, 206-206, 209-209, 211-211, 215-218, 222-222, 229-229, 231-233, 235-238, 240-250, 354-355, 357-369, 401-450 POST SB 25-1B07 for A/C 207-207 POST SB 25-1BRN for A/C 018-018, 037-037, 043-043 EMB SB 25-1595 for A/C 218-218 EMB SB 25-1BDU for A/C 073-074, 076-079, 081-084, 087-087, 091-091 (Ref. Fig. Load Adjustment of the Inner Control Handle SHEET 1) ** ON A/C ALL (1) Removal of the lockwire: WARNING: USE 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. (a) Remove the lockwire from the screw (2).

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-001-A - Deactivation of the Passenger/Crew Doors - Load Adjustment

(2) Measure the loads on the inner control handle with the DYNAMOMETER 20 DAN (45 LBF) - PULL when the door is in the up and down positions. (3) Make sure that the load necessary to open the door with the inner control handle is less than or equal to 18 daN (40.47 lbf). (4) Turn the screw (2) to adjust the load on the torsion bar (1). (5) Safety the screw (2) with the Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - (Material No. 14QFB1). 5.

Close-up Subtask 52-10-00-865-074-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU 121VU

DESIGNATION EIS/SLIDES/ARM AND WARN/FLT EIS/SLIDES/ARM AND WARN/GND EIS/SDAC1 AND 2/DOOR/DET/PAX

FIN 15WN 13WN 48WV

LOCATION P11 P10 P05

Subtask 52-10-00-410-092-A B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Obey the special precautions after work on the door (Ref. AMM TASK 52-10-00-860-002) . (3) Close applicable doors 831, 841 or 832, 842 (Ref. AMM TASK 52-10-00-410-001) . (4) Remove the access platform(s). (5) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-001-A01 - Deactivation of the Passenger/Crew Doors - Load Adjustment

** ON A/C ALL TASK 52-10-00-040-001-A01 Deactivation of the Passenger/Crew Doors - Load Adjustment 1.

Reason for the Job MMEL 25-62-01B Cabin Door Slide or Slide Raft There is an alternative method for this procedure. This task gives one of the methods. For the other method refer to the other task in this page block.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE AR SAFETY CLIP - CIRCUIT BREAKER

Consumable Materials REFERENCE (Material No. 14QFB1)

DESIGNATION Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -

C. Work Zones and Access Panels ZONE/ACCESS 831, 831AZ, 832, 832AZ, 841, 841AZ, 842, 842AZ

ZONE DESCRIPTION

D. Referenced Information REFERENCE (Ref. 25-23-46-000-001-A). (Ref. 25-23-46-000-002-A).

DESIGNATION Removal of the Door Linings at the Forward Passenger/Crew Doors Removal of the Door Linings at the Aft Passenger/Crew Doors

** ON A/C 016-022, 024-044, 054-054, 059-059, 061-072, 075-075, 080-080, 204-205, 207-208, 210-210, 212-214, 219-221, 223-228, 230-230, 234-234, 301-349, 351-353, 356-356, 370-400, 500-600 PRE SB 25-1B07 for A/C 207-207 PRE SB 25-1BRN for A/C 018-018, 037-037, 043-043 (Ref. 25-62-44-000-002-A). Removal of the Left-Hand Escape-Slide Pack-Assembly (Ref. 25-62-44-000-010-A). Removal of the Inflated Left-Hand Escape-Slide ** ON A/C 045-053, 055-058, 060-060, 073-074, 076-079, 081-100, 112-150, 201-201, 203-203, 206-206, 209-209, 211-211, 215-218, 222-222, 229-229, 231-233, 235-250, 350-350, 354-355, 357-369, 401-450 POST SB 25-1B07 for A/C 207-207 (Ref. 25-62-44-000-011-A). Removal of the Inflated Left-Hand Escape-Slide-Raft (Ref. 25-62-44-000-012-A). Removal of the Left-Hand Escape-Slide-Raft Pack-Assembly

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-001-A01 - Deactivation of the Passenger/Crew Doors - Load Adjustment

REFERENCE

DESIGNATION

** ON A/C 016-022, 024-044, 054-054, 059-059, 061-072, 075-075, 080-080, 204-205, 207-208, 210-210, 212-214, 219-221, 223-228, 230-230, 234-234, 301-349, 351-353, 356-356, 370-400, 500-600 PRE SB 25-1B07 for A/C 207-207 PRE SB 25-1BRN for A/C 018-018, 037-037, 043-043 (Ref. 25-62-44-000-802-A). Removal of the Right-Hand Escape-Slide Pack-Assembly (Ref. 25-62-44-000-803-A). Removal of the Inflated Right-Hand Escape-Slide ** ON A/C 045-053, 055-058, 060-060, 073-074, 076-079, 081-100, 112-150, 201-201, 203-203, 206-206, 209-209, 211-211, 215-218, 222-222, 229-229, 231-233, 235-250, 350-350, 354-355, 357-369, 401-450 POST SB 25-1B07 for A/C 207-207 (Ref. 25-62-44-000-804-A). Removal of the Right-Hand Escape-Slide-Raft Pack-Assembly (Ref. 25-62-44-000-805-A). Removal of the Inflated Right-Hand Escape-Slide-Raft ** ON A/C ALL (Ref. 52-10-00-010-001-A). (Ref. 52-10-00-410-001-A). (Ref. 52-10-00-860-001-A). (Ref. 52-10-00-860-002-A).

Opening of the Passenger/Crew Door Closing of the Passenger/Crew Door Special Precautions before Work on the Passenger/Crew Door Special Precautions after Work on the Passenger/Crew Door

** ON A/C 016-022, 024-044, 054-054, 059-059, 061-072, 075-075, 080-080, 204-205, 207-208, 210-210, 212-214, 219-221, 223-228, 230-230, 234-234, 239-239, 301-353, 356-356, 370-400, 500-600 PRE SB 25-1B07 for A/C 207-207 PRE SB 25-1BRN for A/C 018-018, 037-037, 043-043 Load Adjustment of the Inner Control Handle SHEET 1 ** ON A/C 045-053, 055-058, 060-060, 073-074, 076-079, 081-100, 112-150, 201-201, 203-203, 206-206, 209-209, 211-211, 215-218, 222-222, 229-229, 231-233, 235-238, 240-250, 354-355, 357-369, 401-450 POST SB 25-1B07 for A/C 207-207 POST SB 25-1BRN for A/C 018-018, 037-037, 043-043 Load Adjustment of the Inner Control Handle SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-001-A01 - Deactivation of the Passenger/Crew Doors - Load Adjustment

A Z842

A

A

Z832

Z841

Z831

D

D

INNER CONTROL HANDLE IN THE DOOR FULLY CLOSED AND LOCKED POSITION

B

50 TO 70mm (2 TO 3in.)

B C 1

TIGHTEN

LOOSEN

C

2 N_MM_521000_4_ACM0_01_00

Figure 52-10-00-991-04000-00-A / SHEET 1/1 - Load Adjustment of the Inner Control Handle ** ON A/C 016-022, 024-044, 054-054, 059-059, 061-072, 075-075, 080-080, 204-205, 207-208, 210210, 212-214, 219-221, 223-228, 230-230, 234-234, 239-239, 301-353, 356-356, 370-400, 500600 | PRE SB 25-1B07 for A/C 207-207 | PRE SB 25-1BRN for A/C 018-018, 037-037, 043-043 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-001-A01 - Deactivation of the Passenger/Crew Doors - Load Adjustment

A Z842

A

A

Z832

Z841

Z831

D D

INNER CONTROL HANDLE IN THE DOOR FULLY CLOSED AND LOCKED POSITION

B

50 TO 70mm (2 TO 3in.)

B C 1

TIGHTEN

LOOSEN

C

2 N_MM_521000_4_ACN0_01_00

Figure 52-10-00-991-04000-00-B / SHEET 1/1 - Load Adjustment of the Inner Control Handle ** ON A/C 045-053, 055-058, 060-060, 073-074, 076-079, 081-100, 112-150, 201-201, 203-203, 206206, 209-209, 211-211, 215-218, 222-222, 229-229, 231-233, 235-238, 240-250, 354-355, 357-369, 401450 | EMB SB 25-1595 for A/C 218-218 | POST SB 25-1B07 for A/C 207-207 | EMB SB 25-1BDU for A/ C 073-074, 076-079, 081-084, 087-087, 091-091 | POST SB 25-1BRN for A/C 018-018, 037-037, 043-043 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-001-A01 - Deactivation of the Passenger/Crew Doors - Load Adjustment

3.

Job Set-up Subtask 52-10-00-010-085-A A.

Get Access (1) Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position in the zone 831 (841) or 832 (842). (2) Open the applicable passenger/crew door 831, 841 or 832, 842 (Ref. AMM TASK 52-10-00-010001) . (3) Obey the special precautions before you start work on the door (Ref. AMM TASK 52-10-00-860001) .

Subtask 52-10-00-865-075-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU 121VU

DESIGNATION EIS/SLIDES/ARM AND WARN/FLT EIS/SLIDES/ARM AND WARN/GND EIS/SDAC1 AND 2/DOOR/DET/PAX

FIN 15WN 13WN 48WV

LOCATION P11 P10 P05

** ON A/C 016-022, 024-044, 054-054, 059-059, 061-072, 075-075, 080-080, 204-205, 207-208, 210-210, 212214, 219-221, 223-228, 230-230, 234-234, 301-349, 351-353, 356-356, 370-400, 500-600 PRE SB 25-1B07 for A/C 207-207 PRE SB 25-1BRN for A/C 018-018, 037-037, 043-043 Subtask 52-10-00-010-086-A C.

Removal of the Escape Slide (1) Remove the door lining panels: (a) For the FWD passenger/crew doors: (Ref. AMM TASK 25-23-46-000-001) · for the left door 831AZ · for the right door 841AZ (b) For the Aft passenger/crew doors: (Ref. AMM TASK 25-23-46-000-002) · for the left door 832AZ · for the right door 842AZ (2) Remove the escape slide: (a) For the left door: If installed, remove the left-hand escape slide pack assembly (Ref. AMM TASK 25-62-44-000002) or the inflated left-hand escape slide (Ref. AMM TASK 25-62-44-000-010) . (b) For the right door: If installed, remove the right-hand escape slide pack assembly (Ref. AMM TASK 25-62-44-000802) or the inflated right-hand escape slide (Ref. AMM TASK 25-62-44-000-803) .

** ON A/C 045-053, 055-058, 060-060, 073-074, 076-079, 081-100, 112-150, 201-201, 203-203, 206-206, 209209, 211-211, 215-218, 222-222, 229-229, 231-233, 235-250, 350-350, 354-355, 357-369, 401-450 POST SB 25-1B07 for A/C 207-207 POST SB 25-1BRN for A/C 018-018, 037-037, 043-043 EMB SB 25-1587 for A/C 239-239, 350-350 EMB SB 25-1595 for A/C 218-218 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-001-A01 - Deactivation of the Passenger/Crew Doors - Load Adjustment

EMB SB 25-1BDU for A/C 073-074, 076-079, 081-084, 087-087, 091-091 Subtask 52-10-00-010-086-B C.

Removal of the Escape Slide/Raft (1) Remove the door lining panels: (a) For the FWD passenger/crew doors: (Ref. AMM TASK 25-23-46-000-001) · for the left door 831AZ · for the right door 841AZ (b) For the Aft passenger/crew doors: (Ref. AMM TASK 25-23-46-000-002) · for the left door 832AZ · for the right door 842AZ (2) Remove the escape slide: (a) For the left door: If installed, remove the left-hand escape slide raft pack assembly (Ref. AMM TASK 25-62-44000-012) or the inflated left-hand escape slide raft (Ref. AMM TASK 25-62-44-000-011) . (b) For the right door: If installed, remove the right-hand escape slide raft pack assembly (Ref. AMM TASK 25-62-44000-804) or the inflated right-hand escape slide raft (Ref. AMM TASK 25-62-44-000-805) .

** ON A/C ALL 4.

Procedure

** ON A/C 016-022, 024-044, 054-054, 059-059, 061-072, 075-075, 080-080, 204-205, 207-208, 210-210, 212214, 219-221, 223-228, 230-230, 234-234, 239-239, 301-353, 356-356, 370-400, 500-600 PRE SB 25-1B07 for A/C 207-207 PRE SB 25-1BRN for A/C 018-018, 037-037, 043-043 Subtask 52-10-00-820-052-A A.

Load Adjustment of the Inner Control Handle (Ref. Fig. Load Adjustment of the Inner Control Handle SHEET 1) (1) Remove the lockwire from the screw (2). (2) Adjust the load (less than or equal to 18 daN (40.47 lbf)) on the inner control handle. To do this loosen the screw (2) by 9 turns to apply a load on the torsion bar (1). NOTE: If you replace an escape slide by an escape slide/raft you must adjust the load. To do this, tighten the screw (2) by 11 turns. (3) Safety the screw (2) with Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - (Material No. 14QFB1).

** ON A/C 045-053, 055-058, 060-060, 073-074, 076-079, 081-100, 112-150, 201-201, 203-203, 206-206, 209209, 211-211, 215-218, 222-222, 229-229, 231-233, 235-238, 240-250, 354-355, 357-369, 401-450 POST SB 25-1B07 for A/C 207-207 POST SB 25-1BRN for A/C 018-018, 037-037, 043-043 EMB SB 25-1595 for A/C 218-218 EMB SB 25-1BDU for A/C 073-074, 076-079, 081-084, 087-087, 091-091 Subtask 52-10-00-820-052-B A.

Load Adjustment of the Inner Control Handle

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-001-A01 - Deactivation of the Passenger/Crew Doors - Load Adjustment

(Ref. Fig. Load Adjustment of the Inner Control Handle SHEET 1) (1) Remove the lockwire from the screw (2). (2) Adjust the load (less than or equal to 18 daN (40.47 lbf)) on the inner control handle. To do this loosen the screw (2) by 20 turns to apply a load on the torsion bar (1). NOTE: If you replace an escape slide/raft by an escape slide you must adjust the load. To do this, loosen the screw (2) by 11 turns. (3) Safety the screw (2) with Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - (Material No. 14QFB1) ** ON A/C ALL Subtask 52-10-00-220-080-A B.

Inspection

** ON A/C 016-022, 024-044, 054-054, 059-059, 061-072, 075-075, 080-080, 204-205, 207-208, 210-210, 212-214, 219-221, 223-228, 230-230, 234-234, 239-239, 301-353, 356-356, 370-400, 500-600 PRE SB 25-1B07 for A/C 207-207 PRE SB 25-1BRN for A/C 018-018, 037-037, 043-043 (Ref. Fig. Load Adjustment of the Inner Control Handle SHEET 1) ** ON A/C 045-053, 055-058, 060-060, 073-074, 076-079, 081-100, 112-150, 201-201, 203-203, 206-206, 209-209, 211-211, 215-218, 222-222, 229-229, 231-233, 235-238, 240-250, 354-355, 357-369, 401-450 POST SB 25-1B07 for A/C 207-207 POST SB 25-1BRN for A/C 018-018, 037-037, 043-043 EMB SB 25-1595 for A/C 218-218 EMB SB 25-1BDU for A/C 073-074, 076-079, 081-084, 087-087, 091-091 (Ref. Fig. Load Adjustment of the Inner Control Handle SHEET 1) ** ON A/C ALL (1) Pull the inner control handle by 50 mm (1.9685 in.) to 70 mm (2.7559 in.) from the door. (2) Release the inner control handle. (3) Make sure that the inner control handle moves back to the door fully closed and locked position. (4) If the handle does not come back to its initial position, turn the screw (2) by a few more turns until you get this position. NOTE: It is important to do this final check as the operator does not know the initial adjustment (because of the mechanical wear and differences from one door to another). 5.

Close-up Subtask 52-10-00-865-076-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU 121VU

DESIGNATION EIS/SLIDES/ARM AND WARN/FLT EIS/SLIDES/ARM AND WARN/GND EIS/SDAC1 AND 2/DOOR/DET/PAX

FIN 15WN 13WN 48WV

LOCATION P11 P10 P05

Subtask 52-10-00-410-093-A

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-001-A01 - Deactivation of the Passenger/Crew Doors - Load Adjustment

B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Obey the special precautions after the work on the door (Ref. AMM TASK 52-10-00-860-002) . (3) Close the door 831, 841 or 832, 842 (Ref. AMM TASK 52-10-00-410-001) . (4) Remove the access platform(s). (5) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-001-A - Check of the Emergency-Exit Slide-Bottle Pressure because of a Low Pressure Indication on the Programming and Test Panel or Flight Attendant Panel

** ON A/C ALL TASK 25-62-00-040-001-A Check of the Emergency-Exit Slide-Bottle Pressure because of a Low Pressure Indication on the Programming and Test Panel or Flight Attendant Panel

FIN : 7506MM , 7507MM , ** ON A/C 401-415 7685MM , 7686MM , ** ON A/C 401-450 7693MM , 7694MM ** ON A/C ALL Task Summary MMEL or CDL Ref MMEL 25-62-07A

Access YES

Test YES

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

1.

Reason for the Job MMEL 25-62-07A Cabin Overwing Exit CHECK SLIDE PRESSURE Message on Flight Attendant Panel (FAP) (If Installed)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE

QTY DESIGNATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 No specific 1 ACCESS PLATFORM 2M (6 FT) FOR 7506MM (RESERVOIR ASSY OWS L) No specific 1 MIRROR - INSPECTION, FLEXIBLE ** ON A/C 416-450 FOR 7683MM (RESERVOIR ASSY OWS LH) FOR 7684MM (RESERVOIR ASSY OWS RH) No specific 1 ACCESS PLATFORM 2M (6 FT) ** ON A/C ALL B.

Work Zones and Access Panels ZONE/ACCESS 150

ZONE DESCRIPTION AFT CARGO COMPARTMENT FWD PRESS BULKHEAD TO AFT BULKHEAD OF AFT CARGO COMPARTMENT

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 FOR 7506MM (RESERVOIR ASSY OWS L) 151KW

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-001-A - Check of the Emergency-Exit Slide-Bottle Pressure because of a Low Pressure Indication on the Programming and Test Panel or Flight Attendant Panel ZONE/ACCESS ZONE DESCRIPTION FOR 7507MM (RESERVOIR ASSY OWS R) 152KW ** ON A/C 416-450 FOR 7683MM (RESERVOIR ASSY OWS LH) FOR 7684MM (RESERVOIR ASSY OWS RH) 151AW ** ON A/C ALL C. Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A).

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 (Ref. 52-30-00-860-001-A). Open the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump (Ref. 52-30-00-860-002-A). Close the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump ** ON A/C ALL ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Pressure Gage - Inflation Reservoir ** ON A/C 401-415 Pressure Gage - Inflation Reservoir ** ON A/C 416-450 Pressure Gage - Inflation Reservoir ** ON A/C 416-450 FOR 7683MM (RESERVOIR ASSY OWS LH) FOR 7684MM (RESERVOIR ASSY OWS RH) (Ref. 25-55-11-000-001-A). Removal of the Aft Cargo-Compartment Partition at FR47 (Ref. 25-55-11-400-001-A). Installation of the Aft Cargo-Compartment Partition at FR47 (Ref. 25-80-00-000-001-A). Removal of the Insulation Blankets (Ref. 25-80-00-400-001-A). Installation of the Insulation Blankets (Ref. 52-30-00-860-001-A). Open the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump (Ref. 52-30-00-860-002-A). Close the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump ** ON A/C ALL

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-001-A - Check of the Emergency-Exit Slide-Bottle Pressure because of a Low Pressure Indication on the Programming and Test Panel or Flight Attendant Panel

152KW

FR56

7507MM

A

Z150 151KW

A FR46 7506MM

A

FR47

EXAMPLE

FR48

B

1

N_MM_256200_4_AAM0_01_01

Figure 25-62-00-991-00200-00-A / SHEET 1/2 - Pressure Gage - Inflation Reservoir ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-001-A - Check of the Emergency-Exit Slide-Bottle Pressure because of a Low Pressure Indication on the Programming and Test Panel or Flight Attendant Panel

B EXAMPLE GAGE MODEL A

AREA B

AREA A

NEEDLE

2

GREEN CURSOR

GAGE MODEL B

AREA B

AREA A

RED BAND

GREEN BAND TEMP. COMP.

2

NEEDLE N_MM_256200_4_AAM0_02_01

Figure 25-62-00-991-00200-00-A / SHEET 2/2 - Pressure Gage - Inflation Reservoir ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-001-A - Check of the Emergency-Exit Slide-Bottle Pressure because of a Low Pressure Indication on the Programming and Test Panel or Flight Attendant Panel

C

Z250

7694MM

C 7693MM

C

A

7686MM

C

A

A FR51

A

7685MM FR47

B B

2 1

A B

TYPICAL

TYPICAL

N_MM_256200_4_AZA2_01_00

Figure 25-62-00-991-00200-00-F / SHEET 1/2 - Pressure Gage - Inflation Reservoir ** ON A/C 401-415 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-001-A - Check of the Emergency-Exit Slide-Bottle Pressure because of a Low Pressure Indication on the Programming and Test Panel or Flight Attendant Panel

D

C TYPICAL

GAGE AREA B AREA A RED BAND GREEN BAND TEMP. COMP.

3

NEEDLE

D TYPICAL

N_MM_256200_4_AZA2_02_00

Figure 25-62-00-991-00200-00-F / SHEET 2/2 - Pressure Gage - Inflation Reservoir ** ON A/C 401-415 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-001-A - Check of the Emergency-Exit Slide-Bottle Pressure because of a Low Pressure Indication on the Programming and Test Panel or Flight Attendant Panel

Z250 7693MM PAX COMPARTMENT EMERGENCY EXIT

B

B

AFT CARGO COMPARTMENT DOOR

Z150

FR51 7694MM FR47.5 7684MM

FR59

A

152BW 151AW 151BW

A

FR47.1

FR47.2 7683MM FR46 FR47

C

A TYPICAL N_MM_256200_4_AAN0_01_01

Figure 25-62-00-991-00200-00-D / SHEET 1/2 - Pressure Gage - Inflation Reservoir ** ON A/C 416-450 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-001-A - Check of the Emergency-Exit Slide-Bottle Pressure because of a Low Pressure Indication on the Programming and Test Panel or Flight Attendant Panel

C

B TYPICAL AREA B AREA A RED BAND GREEN BAND TEMP. COMP.

NEEDLE

1

C TYPICAL N_MM_256200_4_AAN0_02_01

Figure 25-62-00-991-00200-00-D / SHEET 2/2 - Pressure Gage - Inflation Reservoir ** ON A/C 416-450 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-001-A - Check of the Emergency-Exit Slide-Bottle Pressure because of a Low Pressure Indication on the Programming and Test Panel or Flight Attendant Panel

3.

Job Set-up Subtask 25-62-00-861-054-A A.

Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 25-62-00-010-064-A B.

Get Access (Ref. Fig. Pressure Gage - Inflation Reservoir) (1) Open the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-001) . (2) Put an ACCESS PLATFORM 2M (6 FT) in position adjacent to the aft cargo compartment door. (3) Set AFT CARGO COMPT light switch 8LU to the ON position. (4) FOR 7506MM (RESERVOIR ASSY OWS L) (a) Remove access panel 151KW. (5) FOR 7507MM (RESERVOIR ASSY OWS R) (a) Remove access panel 152KW.

** ON A/C 416-450 Subtask 25-62-00-010-064-D B.

Get Access (1) FOR 7683MM , (RESERVOIR ASSY OWS LH), 7684MM (RESERVOIR ASSY OWS RH) (a) Open the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-001) . (b) Put an ACCESS PLATFORM 2M (6 FT) in position adjacent to the aft cargo-compartment door. (c) Set AFT CARGO COMPT light switch 8LU to the ON position. (d) Remove mid panel 151AW of the partition (Ref. AMM TASK 25-55-11-000-001) . (e) Remove the insulation blankets (Ref. AMM TASK 25-80-00-000-001) . (2) FOR 7693MM , (RESERVOIR ASSY DOOR 3LH), 7694MM (RESERVOIR ASSY DOOR 3RH) (a) Open the door of the related overhead stowage compartment.

** ON A/C 401-415 Subtask 25-62-00-010-064-F B.

Get Access (Ref. Fig. Pressure Gage - Inflation Reservoir) (1) Open the door of the overhead stowage compartment (1) and push the quick-release fasteners (2).

** ON A/C ALL 4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 25-62-00-210-063-A A.

Visual Inspection (Ref. Fig. Pressure Gage - Inflation Reservoir) (1) Make sure that the pressure gage (2) shows the correct pressure.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-001-A - Check of the Emergency-Exit Slide-Bottle Pressure because of a Low Pressure Indication on the Programming and Test Panel or Flight Attendant Panel

NOTE: There are two different types of pressure gages (2) (MODEL A and MODEL B). MODEL A has a green cursor that is sensitive to temperature. MODEL B has a needle with an internal mechanism that is sensitive to temperature. The two models can give temporary low pressure indications when there are sudden temperature changes from a cold to a warm environment. This usually occurs after a longer flight and when the aircraft door is opened in a warm environment. The cursor/needle moves to changes in temperature faster than the gas pressure can adapt to this change in the inflation reservoir. (a) The indications for MODEL A are as follows: · The needle in AREA A (green cursor width) shows that the pressure level is correct. · The needle in AREA B, which is half the range of AREA A, shows a pressure level that is permitted if sudden temperature changes occurred in the last 60 minutes. (b) The indications for MODEL B are as follows: · The GREEN BAND shows a correct pressure level. · AREA B, which is a range equal to AREA A, shows a pressure level that is permitted if sudden temperature changes occurred in the last 60 minutes. (c) FOR 7506MM (RESERVOIR ASSY OWS L) · Use a MIRROR - INSPECTION, FLEXIBLE to see the pressure gage (2) on the left inflation reservoir (1). (d) If the pressure gage (2) shows an indication in AREA B: 1

Let temperature conditions become stable and then examine the pressure again.

2

If the pressure gage (2) continues to show an indication in AREA B: a

Stop the operation of the applicable door.

b

Refer to the associated MMEL item.

c

Make an entry in the logbook.

** ON A/C 416-450 Subtask 25-62-00-210-063-E A.

Visual Inspection (Ref. Fig. Pressure Gage - Inflation Reservoir) (1) Make sure that the pressure gage (1) shows the correct pressure. NOTE: The pressure gage (1) has a needle with an internal mechanism that is sensitive to temperature. It can give incorrect pressure indications when there are sudden temperature changes from a cold to a warm environment. This usually occurs after a longer flight and when the aircraft door is opened in a warm environment. The needle moves to changes in temperature faster than the gas pressure can adapt to this change in the inflation reservoir. (a) The indications are as follows: · The GREEN BAND shows a correct pressure level. · AREA B, which is a range equal to AREA A, shows a pressure level that is permitted if sudden temperature changes occurred in the last 60 minutes. (b) If the pressure gage (1) shows an indication in AREA B: 1

Let temperature conditions become stable and then examine the pressure again.

2

If the pressure gage (1) continues to show an indication in AREA B: a

Stop the operation of the applicable door.

b

Refer to the associated MMEL item.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-001-A - Check of the Emergency-Exit Slide-Bottle Pressure because of a Low Pressure Indication on the Programming and Test Panel or Flight Attendant Panel

c

Make an entry in the logbook.

** ON A/C 401-415 Subtask 25-62-00-210-063-F A.

Visual Inspection (Ref. Fig. Pressure Gage - Inflation Reservoir) (1) Make sure that the pressure gage (3) shows the correct pressure. NOTE: The pressure gage (3) has a needle with an internal mechanism that is sensitive to temperature. It can give incorrect pressure indications when there are sudden temperature changes from a cold to a warm environment. This usually occurs after a longer flight and when the aircraft door is opened in a warm environment. The needle moves to changes in temperature faster than the gas pressure can adapt to this change in the inflation reservoir. (2) The indications are as follows: · The GREEN BAND shows a correct pressure level. · AREA B, which is a range equal to AREA A, shows a pressure level that is permitted if sudden temperature changes occurred in the last 60 minutes. (3) If the pressure gage (3) shows an indication in AREA B: (a) Let temperature conditions become stable and then examine the pressure again. (b) If the pressure gage (3) continues to show an indication in AREA B: 1

Stop the operation of the applicable door.

2

Refer to the associated MMEL item.

3

Make an entry in the logbook.

** ON A/C ALL 5.

Close-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 25-62-00-410-059-A A.

Close Access (Ref. Fig. Pressure Gage - Inflation Reservoir) (1) Make sure that the work area is clean and clear of tools and other items. (2) FOR 7506MM (RESERVOIR ASSY OWS L) (a) Install access panel 151KW. (3) FOR 7507MM (RESERVOIR ASSY OWS R) (a) Install access panel 152KW. (4) Set AFT CARGO COMPT light switch 8LU to the OFF position. (5) Remove the access platform(s). (6) Close the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-002) . (7) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (8) Make an entry in the logbook.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-001-A - Check of the Emergency-Exit Slide-Bottle Pressure because of a Low Pressure Indication on the Programming and Test Panel or Flight Attendant Panel

** ON A/C 416-450 Subtask 25-62-00-410-059-D A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) FOR 7683MM , (RESERVOIR ASSY OWS LH), 7684MM (RESERVOIR ASSY OWS RH) (a) Install the insulation blankets (Ref. AMM TASK 25-80-00-400-001) . (b) Install mid panel 151AW of the partition (Ref. AMM TASK 25-55-11-400-001) . (c) Set AFT CARGO COMPT light switch 8LU to the OFF position. (d) Remove the access platform(s). (e) Close the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-002) . (3) FOR 7693MM , (RESERVOIR ASSY DOOR 3LH), 7694MM (RESERVOIR ASSY DOOR 3RH) (a) Close the door of the related overhead stowage compartment. (4) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (5) Make an entry in the logbook.

** ON A/C 401-415 Subtask 25-62-00-410-059-F A.

Close Access (Ref. Fig. Pressure Gage - Inflation Reservoir) (1) Lock the quick-release fasteners (2). (2) Make sure that you can see the pressure gage (3) through the inspection window. (3) Close the door of the overhead stowage compartment (1). (4) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (5) Make an entry in the logbook.

** ON A/C ALL Subtask 25-62-00-862-054-A B.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 12 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-008-A - Check of the Passenger-Door SlideBottle Pressure because of a Low Pressure Indication on the Programming and Test Panel or Flight Attendant Panel ** ON A/C ALL TASK 25-62-00-040-008-A Check of the Passenger-Door Slide-Bottle Pressure because of a Low Pressure Indication on the Programming and Test Panel or Flight Attendant Panel Task Summary MMEL or CDL Ref MMEL 25-62-06A

Access NO

Test NO

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

1.

Reason for the Job MMEL 25-62-06A Cabin Door SLIDE PRESS LOW Message on Programming and Test Panel (PTP) STATUS Page (If Installed)

2

Job Set-up Information A.

Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A).

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power Pressure Gage - Inflation Reservoir SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-008-A - Check of the Passenger-Door SlideBottle Pressure because of a Low Pressure Indication on the Programming and Test Panel or Flight Attendant Panel

GAGE MODEL A

AREA B

AREA A

NEEDLE

GREEN CURSOR

GAGE MODEL B

AREA B

AREA A

RED BAND

GREEN BAND TEMP. COMP.

NEEDLE N_MM_256200_4_GAA0_01_02

Figure 25-62-00-991-01600-00-A / SHEET 1/1 - Pressure Gage - Inflation Reservoir ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 25-62-00-040-008-A - Check of the Passenger-Door SlideBottle Pressure because of a Low Pressure Indication on the Programming and Test Panel or Flight Attendant Panel 3.

Job Set-up Subtask 25-62-00-861-061-A A.

4.

Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Procedure Subtask 25-62-00-210-068-A A.

Visual Inspection (Ref. Fig. Pressure Gage - Inflation Reservoir SHEET 1) (1) Make sure that the pressure gage of the inflation reservoir shows the correct pressure. NOTE: There are two different types of pressure gages (MODEL A and MODEL B). MODEL A has a green cursor that is sensitive to temperature. MODEL B has a needle with an internal mechanism that is sensitive to temperature. The two models can give temporary low pressure indications when there are sudden temperature changes from a cold to a warm environment. This usually occurs after a longer flight and when the aircraft door is opened in a warm environment. The cursor/needle moves to changes in temperature faster than the gas pressure can adapt to this change in the inflation reservoir. (a) The indications for MODEL A are as follows: · The needle in AREA A (green cursor width) shows that the pressure level is correct. · The needle in AREA B, which is half the range of AREA A, shows a pressure level that is permitted if sudden temperature changes occurred in the last 60 minutes. (b) The indications for MODEL B are as follows: · The GREEN BAND shows a correct pressure level. · AREA B, which is a range equal to AREA A, shows a pressure level that is permitted if sudden temperature changes occurred in the last 60 minutes. (c) If the pressure gage shows an indication in AREA B:

5.

1

Let the temperature conditions become stable and then examine the pressure again.

2

If the pressure gage continues to show an indication in AREA B: a

Stop the operation of the applicable door.

b

Refer to the associated MMEL item.

c

Make an entry in the logbook.

Close-up Subtask 25-62-00-862-061-A A.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

** ON A/C ALL TASK 26-21-00-040-001-A Engine Bottle Pressure Check

FIN : 6WE1 , 6WE2 , 8WE1 , 8WE2 Task Summary MMEL or CDL Ref MMEL 26-01-01-02A MMEL 26-01-01-02B

Access YES YES

1.

Reason for the Job MMEL 26-01-01-02A ENG AGENT pb DISCH light MMEL 26-01-01-02B ENG AGENT pb DISCH light

2

Job Set-up Information A.

Specific Tools NO NO

Mhr 00.5 00.5

E/T 00.5 00.5

Nb Men 1 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific

B.

Test YES YES

QTY AR AR AR AR AR AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE ALLEN KEY 3/32 IN CAP - BLANKING MULTIMETER - STANDARD SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 415 425

ZONE DESCRIPTION LOWER PYLON LOWER PYLON

** ON A/C 301-349, 351-450, 500-600 FOR 6WE1 (BOTTLE 1-FIRE EXTING, ENG 1) 415BL ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 FOR 6WE1 (BOTTLE 1-FIRE EXTING, ENG 1) FOR 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) 415BL, 415BR ** ON A/C 301-349, 351-450, 500-600 FOR 6WE2 (BOTTLE 1-FIRE EXTING, ENG 2) 425BL

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

ZONE/ACCESS

ZONE DESCRIPTION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 FOR 6WE2 (BOTTLE 1-FIRE EXTING, ENG 2) FOR 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2) 425BL, 425BR ** ON A/C 301-349, 351-450, 500-600 FOR 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) 415CR FOR 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2) 425CR ** ON A/C ALL C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 26-12-00-710-001-A). (Ref. 26-21-41-280-001-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Operational Check of Loop/Squib Weight Check of the Engine Fire-Extinguisher Bottle

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (Ref. 54-51-21-000-001-A). Removal of the Pylon Lateral Access-Doors ** ON A/C 301-349, 351-450, 500-600 (Ref. 54-51-21-000-802-A). Removal of the Pylon Lateral Access-Doors ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (Ref. 54-51-21-400-001-A). Installation of the Pylon Lateral Access-Doors ** ON A/C 301-349, 351-450, 500-600 (Ref. 54-51-21-400-802-A). Installation of the Pylon Lateral Access-Doors ** ON A/C ALL ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Engine Fire Extinguishing - Location SHEET 1 ** ON A/C 301-349, 351-450, 500-600 Engine Fire Extinguishing - Location SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

A

B

8WE1 (8WE2)

Z410 (Z420)

6WE1 (6WE2)

A LH SHOWN RH SYMMETRICAL

1

2

C

1

3

B

C

TYPICAL

N_MM_262100_4_AAM0_01_01

Figure 26-21-00-991-00600-00-A / SHEET 1/1 - Engine Fire Extinguishing - Location ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

A 8WE1 (8WE2) Z410 (Z420) 6WE1 (6WE2)

B

A LH SHOWN RH SYMMETRICAL

1

2 3

B TYPICAL

N_MM_262100_4_PAM0_01_01

Figure 26-21-00-991-00600-00-B / SHEET 1/1 - Engine Fire Extinguishing - Location ** ON A/C 301-349, 351-450, 500-600 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

3.

Job Set-up Subtask 26-21-00-860-076-A A.

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

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 26-21-00-875-050-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION FOR FIN 6WE2 (BOTTLE 1-FIRE EXTING, ENG 2), 6WE1 (BOTTLE 1-FIRE EXTING, ENG 1) 121VU ENGINE/ENG1 AND 2 FIRE EX2WE1 Q44 TIG/BTL1/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EX1WE1 Q43 TIG/BTL1/SQUIB/A FOR FIN 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2), 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) 121VU ENGINE/ENG1 AND 2 FIRE EX2WE2 Q42 TIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EX1WE2 Q41 TIG/BTL2/SQUIB/A

** ON A/C 301-349, 351-450, 500-600 Subtask 26-21-00-875-050-B B.

Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION FOR FIN 6WE2 (BOTTLE 1-FIRE EXTING, ENG 2), 6WE1 (BOTTLE 1-FIRE EXTING, ENG 1) ** ON A/C 301-349, 351-400, 500-600 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B ** ON A/C 401-450 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B

1WE1

Q43

2WE2

Q42

1WE1

Q42

2WE2

Q41

** ON A/C 301-349, 351-450, 500-600 FOR FIN 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2), 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) ** ON A/C 301-349, 351-400, 500-600 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A

2WE1

Q44

1WE2

Q41

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

PANEL

DESIGNATION

** ON A/C 401-450 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A

FIN

LOCATION

2WE1

Q43

1WE2

Q40

** ON A/C ALL Subtask 26-21-00-941-063-A C.

Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Make sure that the ENG/MODE/CRANK/NORM/IGN/START selector switch is in the NORM position. (b) Put a WARNING NOTICE(S) to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead 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) to tell persons not to energize the FADEC 1(2). (4) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position below the pylon.

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 26-21-00-010-065-A D.

Get Access (1) Remove these access panels (Ref. AMM TASK 54-51-21-000-001) : (a) FOR 6WE1 , (BOTTLE 1-FIRE EXTING, ENG 1), 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) · 415BL, 415BR. (b) FOR 6WE2 , (BOTTLE 1-FIRE EXTING, ENG 2), 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2) · 425BR, 425BL.

** ON A/C 301-349, 351-450, 500-600 Subtask 26-21-00-010-065-E D.

Get Access (1) Remove these access panels (Ref. AMM TASK 54-51-21-000-802) : (a) FOR 6WE1 (BOTTLE 1-FIRE EXTING, ENG 1) · 415BL (b) FOR 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) · 415CR (c) FOR 6WE2 (BOTTLE 1-FIRE EXTING, ENG 2) · 425BL (d) FOR 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2) · 425CR

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

** ON A/C ALL Subtask 26-21-00-020-056-A E.

Disconnect the Electrical Connectors

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (Ref. Fig. Engine Fire Extinguishing - Location SHEET 1) ** ON A/C 301-349, 351-450, 500-600 (Ref. Fig. Engine Fire Extinguishing - Location SHEET 1) ** ON A/C ALL (1) Disconnect the electrical connector (2) from the pressure switch (3) of the related fire extinguisher bottle (1). (2) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. 4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (Ref. Fig. Engine Fire Extinguishing - Location SHEET 1) ** ON A/C 301-349, 351-450, 500-600 (Ref. Fig. Engine Fire Extinguishing - Location SHEET 1) ** ON A/C ALL Subtask 26-21-00-280-051-B A.

Check of Engine-1 Fire-Extinguisher Bottle 1 (6WE1) (1) Do a check for continuity between pin 2 and pin 3 of engine-1 fire-extinguisher bottle 1 (6WE1) with a MULTIMETER - STANDARD. (a) If there is no continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . (b) If there is continuity, go to step 4.A.(2). (2) Engage the ALLEN KEY 3/32 IN into the test point (Allen key). CAUTION: TO DO THE MANUAL PRESSURE TEST OF THE ENGINE-FIRE EXTINGUISHER BOTTLE, TURN THE ALLEN KEY CLOCKWISE UNTIL YOU FEEL A FORCE (AT APPROXIMATELY 10 DEGREES). DO NOT TURN THE ALLEN KEY MORE THAN NECESSARY TO PREVENT DAMAGE TO THE PRESSURE SWITCH. (a) Turn the Allen key clockwise (by 10 degrees approximately) until you feel a force, and hold it in this position. (3) Do a check for continuity between pin 2 and pin 3 of engine-1 fire-extinguisher bottle 1 (6WE1) with the MULTIMETER - STANDARD. (a) If there is continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . (b) If there is no continuity, go to step 4.A.(4). (4) Release the Allen key. NOTE: If the pressure in the bottle is correct, the Allen key goes back to its initial position.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

(5) Do a check for continuity between pin 2 and pin 3 of engine-1 fire-extinguisher bottle 1 (6WE1) with the MULTIMETER - STANDARD. (a) If there is no continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . Subtask 26-21-00-280-052-B B.

Check of Engine-1 Fire-Extinguisher Bottle 2 (8WE1) (1) Do a check for continuity between pin 2 and pin 3 of engine-1 fire-extinguisher bottle 2 (8WE1) with a MULTIMETER - STANDARD. (a) If there is no continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . (b) If there is continuity, go to step 4.B.(2). (2) Engage the ALLEN KEY 3/32 IN into the test point (Allen key). CAUTION: TO DO THE MANUAL PRESSURE TEST OF THE ENGINE-FIRE EXTINGUISHER BOTTLE, TURN THE ALLEN KEY CLOCKWISE UNTIL YOU FEEL A FORCE (AT APPROXIMATELY 10 DEGREES). DO NOT TURN THE ALLEN KEY MORE THAN NECESSARY TO PREVENT DAMAGE TO THE PRESSURE SWITCH. (a) Turn the Allen key clockwise (by 10 degrees approximately) until you feel a force, and hold it in this position. (3) Do a check for continuity between pin 2 and pin 3 of engine-1 fire-extinguisher bottle 2 (8WE1) with the MULTIMETER - STANDARD. (a) If there is continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . (b) If there is no continuity, go to step 4.B.(4). (4) Release the Allen key. NOTE: If the pressure in the bottle is correct, the Allen key goes back to its initial position. (5) Do a check for continuity between pin 2 and pin 3 of engine-1 fire-extinguisher bottle 2 (8WE1) with the MULTIMETER - STANDARD. (a) If there is no continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) .

Subtask 26-21-00-280-053-B C.

Check of Engine-2 Fire-Extinguisher Bottle 1 (6WE2) (1) Do a check for continuity between pin 2 and pin 3 of engine-2 fire-extinguisher bottle 1 (6WE2) with a MULTIMETER - STANDARD. (a) If there is no continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . (b) If there is continuity, go to step 4.C.(2). (2) Engage the ALLEN KEY 3/32 IN into the test point (Allen key). CAUTION: TO DO THE MANUAL PRESSURE TEST OF THE ENGINE-FIRE EXTINGUISHER BOTTLE, TURN THE ALLEN KEY CLOCKWISE UNTIL YOU FEEL A FORCE (AT APPROXIMATELY 10 DEGREES). DO NOT TURN THE ALLEN KEY MORE THAN NECESSARY TO PREVENT DAMAGE TO THE PRESSURE SWITCH.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

(a) Turn the Allen key clockwise (by 10 degrees approximately) until you feel a force, and hold it in this position. (3) Do a check for continuity between pin 2 and pin 3 of engine-2 fire-extinguisher bottle 1 (6WE2) with the MULTIMETER - STANDARD. (a) If there is continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . (b) If there is no continuity, go to step 4.C.(4). (4) Release the Allen key. NOTE: If the pressure in the bottle is correct, the Allen key goes back to its initial position. (5) Do a check for continuity between pin 2 and pin 3 of engine-2 fire-extinguisher bottle 1 (6WE2) with the MULTIMETER - STANDARD. (a) If there is no continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . Subtask 26-21-00-280-054-B D.

Check of Engine-2 Fire-Extinguisher Bottle 2 (8WE2) (1) Do a check for continuity between pin 2 and pin 3 of engine-2 fire-extinguisher bottle 2 (8WE2) with a MULTIMETER - STANDARD. (a) If there is no continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . (b) If there is continuity, go to step 4.D.(2). (2) Engage the ALLEN KEY 3/32 IN into the test point (Allen key). CAUTION: TO DO THE MANUAL PRESSURE TEST OF THE ENGINE-FIRE EXTINGUISHER BOTTLE, TURN THE ALLEN KEY CLOCKWISE UNTIL YOU FEEL A FORCE (AT APPROXIMATELY 10 DEGREES). DO NOT TURN THE ALLEN KEY MORE THAN NECESSARY TO PREVENT DAMAGE TO THE PRESSURE SWITCH. (a) Turn the Allen key clockwise (by 10 degrees approximately) until you feel a force, and hold it in this position. (3) Do a check for continuity between pin 2 and pin 3 of engine-2 fire-extinguisher bottle 2 (8WE2) with the MULTIMETER - STANDARD. (a) If there is continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . (b) If there is no continuity, go to step 4.D.(4). (4) Release the Allen key. NOTE: If the pressure in the bottle is correct, the Allen key goes back to its initial position. (5) Do a check for continuity between pin 2 and pin 3 of engine-2 fire-extinguisher bottle 2 (8WE2) with the MULTIMETER - STANDARD. (a) If there is no continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) .

Subtask 26-21-00-420-050-A E.

Connect the electrical connector

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (Ref. Fig. Engine Fire Extinguishing - Location SHEET 1) ** ON A/C 301-349, 351-450, 500-600 (Ref. Fig. Engine Fire Extinguishing - Location SHEET 1) ** ON A/C ALL (1) Remove the CAP-BLANKING from each electrical connector and receptacle. (2) Make sure that all the electrical connections are clean and in the correct condition. (3) Connect the electrical connector (2) to the pressure switch (3) of the related fire extinguisher bottle (1). ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 26-21-00-875-051-A F.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION FOR FIN 6WE2 (BOTTLE 1-FIRE EXTING, ENG 2), 6WE1 (BOTTLE 1-FIRE EXTING, ENG 1) 121VU ENGINE/ENG1 AND 2 FIRE EX2WE1 Q44 TIG/BTL1/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EX1WE1 Q43 TIG/BTL1/SQUIB/A FOR FIN 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2), 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) 121VU ENGINE/ENG1 AND 2 FIRE EX2WE2 Q42 TIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EX1WE2 Q41 TIG/BTL2/SQUIB/A

** ON A/C 301-349, 351-450, 500-600 Subtask 26-21-00-875-051-B F.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION FOR FIN 6WE2 (BOTTLE 1-FIRE EXTING, ENG 2), 6WE1 (BOTTLE 1-FIRE EXTING, ENG 1) ** ON A/C 301-349, 351-400, 500-600 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B ** ON A/C 401-450 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B

1WE1

Q43

2WE2

Q42

1WE1

Q42

2WE2

Q41

** ON A/C 301-349, 351-450, 500-600 FOR FIN 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2), 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

PANEL

DESIGNATION

** ON A/C 301-349, 351-400, 500-600 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A ** ON A/C 401-450 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A

FIN

LOCATION

2WE1

Q44

1WE2

Q41

2WE1

Q43

1WE2

Q40

** ON A/C ALL Subtask 26-21-00-710-052-A G. Do this test (1) Do an operational test of the engine fire and overheat detection (loop/squib) (Ref. AMM TASK 26-1200-710-001) . NOTE: On the ENG/APU FIRE panel 1WD, ignore the DISCH legends which come on on the ENG 1 (2) AGENT 1 and AGENT 2 pushbutton switches. (2) Make an entry in the logbook. (3) Put an applicable placard in position in the cockpit (refer to your standard practices and local regulations). 5.

Close-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 26-21-00-942-062-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the access planel(s) (Ref. AMM TASK 54-51-21-400-001) . (a) FOR 6WE1 , (BOTTLE 1-FIRE EXTING, ENG 1), 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) · 415BL, 415BR. (b) FOR 6WE2 , (BOTTLE 1-FIRE EXTING, ENG 2), 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2) · 425BR, 425BL. (3) Remove the access platform(s). (4) Remove the WARNING NOTICE(S).

** ON A/C 301-349, 351-450, 500-600 Subtask 26-21-00-410-080-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 54-51-21-400-802) : (a) FOR 6WE1 (BOTTLE 1-FIRE EXTING, ENG 1) · 415BL

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

(b) FOR 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) · 415CR (c) FOR 6WE2 (BOTTLE 1-FIRE EXTING, ENG 2) · 425BL (d) FOR 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2) · 425CR (3) Remove the access platform(s). (4) Remove the WARNING NOTICE(S). ** ON A/C ALL Subtask 26-21-00-862-066-A C.

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

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 12 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

** ON A/C ALL TASK 26-21-00-040-001-A Engine Bottle Pressure Check

FIN : 6WE1 , 6WE2 , 8WE1 , 8WE2 Task Summary MMEL or CDL Ref MMEL 26-01-01-02A MMEL 26-01-01-02B

Access YES YES

1.

Reason for the Job MMEL 26-01-01-02A ENG AGENT pb DISCH light MMEL 26-01-01-02B ENG AGENT pb DISCH light

2

Job Set-up Information A.

Specific Tools NO NO

Mhr 00.5 00.5

E/T 00.5 00.5

Nb Men 1 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific

B.

Test YES YES

QTY AR AR AR AR AR AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE ALLEN KEY 3/32 IN CAP - BLANKING MULTIMETER - STANDARD SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 415 425

ZONE DESCRIPTION LOWER PYLON LOWER PYLON

** ON A/C 301-349, 351-450, 500-600 FOR 6WE1 (BOTTLE 1-FIRE EXTING, ENG 1) 415BL ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 FOR 6WE1 (BOTTLE 1-FIRE EXTING, ENG 1) FOR 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) 415BL, 415BR ** ON A/C 301-349, 351-450, 500-600 FOR 6WE2 (BOTTLE 1-FIRE EXTING, ENG 2) 425BL

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

ZONE/ACCESS

ZONE DESCRIPTION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 FOR 6WE2 (BOTTLE 1-FIRE EXTING, ENG 2) FOR 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2) 425BL, 425BR ** ON A/C 301-349, 351-450, 500-600 FOR 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) 415CR FOR 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2) 425CR ** ON A/C ALL C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 26-12-00-710-001-A). (Ref. 26-21-41-280-001-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Operational Check of Loop/Squib Weight Check of the Engine Fire-Extinguisher Bottle

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (Ref. 54-51-21-000-001-A). Removal of the Pylon Lateral Access-Doors ** ON A/C 301-349, 351-450, 500-600 (Ref. 54-51-21-000-802-A). Removal of the Pylon Lateral Access-Doors ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (Ref. 54-51-21-400-001-A). Installation of the Pylon Lateral Access-Doors ** ON A/C 301-349, 351-450, 500-600 (Ref. 54-51-21-400-802-A). Installation of the Pylon Lateral Access-Doors ** ON A/C ALL ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Engine Fire Extinguishing - Location SHEET 1 ** ON A/C 301-349, 351-450, 500-600 Engine Fire Extinguishing - Location SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

A

B

8WE1 (8WE2)

Z410 (Z420)

6WE1 (6WE2)

A LH SHOWN RH SYMMETRICAL

1

2

C

1

3

B

C

TYPICAL

N_MM_262100_4_AAM0_01_01

Figure 26-21-00-991-00600-00-A / SHEET 1/1 - Engine Fire Extinguishing - Location ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

A 8WE1 (8WE2) Z410 (Z420) 6WE1 (6WE2)

B

A LH SHOWN RH SYMMETRICAL

1

2 3

B TYPICAL

N_MM_262100_4_PAM0_01_01

Figure 26-21-00-991-00600-00-B / SHEET 1/1 - Engine Fire Extinguishing - Location ** ON A/C 301-349, 351-450, 500-600 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

3.

Job Set-up Subtask 26-21-00-860-076-A A.

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

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 26-21-00-875-050-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION FOR FIN 6WE2 (BOTTLE 1-FIRE EXTING, ENG 2), 6WE1 (BOTTLE 1-FIRE EXTING, ENG 1) 121VU ENGINE/ENG1 AND 2 FIRE EX2WE1 Q44 TIG/BTL1/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EX1WE1 Q43 TIG/BTL1/SQUIB/A FOR FIN 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2), 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) 121VU ENGINE/ENG1 AND 2 FIRE EX2WE2 Q42 TIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EX1WE2 Q41 TIG/BTL2/SQUIB/A

** ON A/C 301-349, 351-450, 500-600 Subtask 26-21-00-875-050-B B.

Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION FOR FIN 6WE2 (BOTTLE 1-FIRE EXTING, ENG 2), 6WE1 (BOTTLE 1-FIRE EXTING, ENG 1) ** ON A/C 301-349, 351-400, 500-600 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B ** ON A/C 401-450 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B

1WE1

Q43

2WE2

Q42

1WE1

Q42

2WE2

Q41

** ON A/C 301-349, 351-450, 500-600 FOR FIN 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2), 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) ** ON A/C 301-349, 351-400, 500-600 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A

2WE1

Q44

1WE2

Q41

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

PANEL

DESIGNATION

** ON A/C 401-450 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A

FIN

LOCATION

2WE1

Q43

1WE2

Q40

** ON A/C ALL Subtask 26-21-00-941-063-A C.

Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Make sure that the ENG/MODE/CRANK/NORM/IGN/START selector switch is in the NORM position. (b) Put a WARNING NOTICE(S) to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead 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) to tell persons not to energize the FADEC 1(2). (4) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position below the pylon.

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 26-21-00-010-065-A D.

Get Access (1) Remove these access panels (Ref. AMM TASK 54-51-21-000-001) : (a) FOR 6WE1 , (BOTTLE 1-FIRE EXTING, ENG 1), 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) · 415BL, 415BR. (b) FOR 6WE2 , (BOTTLE 1-FIRE EXTING, ENG 2), 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2) · 425BR, 425BL.

** ON A/C 301-349, 351-450, 500-600 Subtask 26-21-00-010-065-E D.

Get Access (1) Remove these access panels (Ref. AMM TASK 54-51-21-000-802) : (a) FOR 6WE1 (BOTTLE 1-FIRE EXTING, ENG 1) · 415BL (b) FOR 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) · 415CR (c) FOR 6WE2 (BOTTLE 1-FIRE EXTING, ENG 2) · 425BL (d) FOR 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2) · 425CR

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

** ON A/C ALL Subtask 26-21-00-020-056-A E.

Disconnect the Electrical Connectors

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (Ref. Fig. Engine Fire Extinguishing - Location SHEET 1) ** ON A/C 301-349, 351-450, 500-600 (Ref. Fig. Engine Fire Extinguishing - Location SHEET 1) ** ON A/C ALL (1) Disconnect the electrical connector (2) from the pressure switch (3) of the related fire extinguisher bottle (1). (2) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. 4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (Ref. Fig. Engine Fire Extinguishing - Location SHEET 1) ** ON A/C 301-349, 351-450, 500-600 (Ref. Fig. Engine Fire Extinguishing - Location SHEET 1) ** ON A/C ALL Subtask 26-21-00-280-051-B A.

Check of Engine-1 Fire-Extinguisher Bottle 1 (6WE1) (1) Do a check for continuity between pin 2 and pin 3 of engine-1 fire-extinguisher bottle 1 (6WE1) with a MULTIMETER - STANDARD. (a) If there is no continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . (b) If there is continuity, go to step 4.A.(2). (2) Engage the ALLEN KEY 3/32 IN into the test point (Allen key). CAUTION: TO DO THE MANUAL PRESSURE TEST OF THE ENGINE-FIRE EXTINGUISHER BOTTLE, TURN THE ALLEN KEY CLOCKWISE UNTIL YOU FEEL A FORCE (AT APPROXIMATELY 10 DEGREES). DO NOT TURN THE ALLEN KEY MORE THAN NECESSARY TO PREVENT DAMAGE TO THE PRESSURE SWITCH. (a) Turn the Allen key clockwise (by 10 degrees approximately) until you feel a force, and hold it in this position. (3) Do a check for continuity between pin 2 and pin 3 of engine-1 fire-extinguisher bottle 1 (6WE1) with the MULTIMETER - STANDARD. (a) If there is continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . (b) If there is no continuity, go to step 4.A.(4). (4) Release the Allen key. NOTE: If the pressure in the bottle is correct, the Allen key goes back to its initial position.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

(5) Do a check for continuity between pin 2 and pin 3 of engine-1 fire-extinguisher bottle 1 (6WE1) with the MULTIMETER - STANDARD. (a) If there is no continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . Subtask 26-21-00-280-052-B B.

Check of Engine-1 Fire-Extinguisher Bottle 2 (8WE1) (1) Do a check for continuity between pin 2 and pin 3 of engine-1 fire-extinguisher bottle 2 (8WE1) with a MULTIMETER - STANDARD. (a) If there is no continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . (b) If there is continuity, go to step 4.B.(2). (2) Engage the ALLEN KEY 3/32 IN into the test point (Allen key). CAUTION: TO DO THE MANUAL PRESSURE TEST OF THE ENGINE-FIRE EXTINGUISHER BOTTLE, TURN THE ALLEN KEY CLOCKWISE UNTIL YOU FEEL A FORCE (AT APPROXIMATELY 10 DEGREES). DO NOT TURN THE ALLEN KEY MORE THAN NECESSARY TO PREVENT DAMAGE TO THE PRESSURE SWITCH. (a) Turn the Allen key clockwise (by 10 degrees approximately) until you feel a force, and hold it in this position. (3) Do a check for continuity between pin 2 and pin 3 of engine-1 fire-extinguisher bottle 2 (8WE1) with the MULTIMETER - STANDARD. (a) If there is continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . (b) If there is no continuity, go to step 4.B.(4). (4) Release the Allen key. NOTE: If the pressure in the bottle is correct, the Allen key goes back to its initial position. (5) Do a check for continuity between pin 2 and pin 3 of engine-1 fire-extinguisher bottle 2 (8WE1) with the MULTIMETER - STANDARD. (a) If there is no continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) .

Subtask 26-21-00-280-053-B C.

Check of Engine-2 Fire-Extinguisher Bottle 1 (6WE2) (1) Do a check for continuity between pin 2 and pin 3 of engine-2 fire-extinguisher bottle 1 (6WE2) with a MULTIMETER - STANDARD. (a) If there is no continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . (b) If there is continuity, go to step 4.C.(2). (2) Engage the ALLEN KEY 3/32 IN into the test point (Allen key). CAUTION: TO DO THE MANUAL PRESSURE TEST OF THE ENGINE-FIRE EXTINGUISHER BOTTLE, TURN THE ALLEN KEY CLOCKWISE UNTIL YOU FEEL A FORCE (AT APPROXIMATELY 10 DEGREES). DO NOT TURN THE ALLEN KEY MORE THAN NECESSARY TO PREVENT DAMAGE TO THE PRESSURE SWITCH.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

(a) Turn the Allen key clockwise (by 10 degrees approximately) until you feel a force, and hold it in this position. (3) Do a check for continuity between pin 2 and pin 3 of engine-2 fire-extinguisher bottle 1 (6WE2) with the MULTIMETER - STANDARD. (a) If there is continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . (b) If there is no continuity, go to step 4.C.(4). (4) Release the Allen key. NOTE: If the pressure in the bottle is correct, the Allen key goes back to its initial position. (5) Do a check for continuity between pin 2 and pin 3 of engine-2 fire-extinguisher bottle 1 (6WE2) with the MULTIMETER - STANDARD. (a) If there is no continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . Subtask 26-21-00-280-054-B D.

Check of Engine-2 Fire-Extinguisher Bottle 2 (8WE2) (1) Do a check for continuity between pin 2 and pin 3 of engine-2 fire-extinguisher bottle 2 (8WE2) with a MULTIMETER - STANDARD. (a) If there is no continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . (b) If there is continuity, go to step 4.D.(2). (2) Engage the ALLEN KEY 3/32 IN into the test point (Allen key). CAUTION: TO DO THE MANUAL PRESSURE TEST OF THE ENGINE-FIRE EXTINGUISHER BOTTLE, TURN THE ALLEN KEY CLOCKWISE UNTIL YOU FEEL A FORCE (AT APPROXIMATELY 10 DEGREES). DO NOT TURN THE ALLEN KEY MORE THAN NECESSARY TO PREVENT DAMAGE TO THE PRESSURE SWITCH. (a) Turn the Allen key clockwise (by 10 degrees approximately) until you feel a force, and hold it in this position. (3) Do a check for continuity between pin 2 and pin 3 of engine-2 fire-extinguisher bottle 2 (8WE2) with the MULTIMETER - STANDARD. (a) If there is continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) . (b) If there is no continuity, go to step 4.D.(4). (4) Release the Allen key. NOTE: If the pressure in the bottle is correct, the Allen key goes back to its initial position. (5) Do a check for continuity between pin 2 and pin 3 of engine-2 fire-extinguisher bottle 2 (8WE2) with the MULTIMETER - STANDARD. (a) If there is no continuity, do the weight check of the engine fire-extinguisher bottle (Ref. AMM TASK 26-21-41-280-001) .

Subtask 26-21-00-420-050-A E.

Connect the electrical connector

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (Ref. Fig. Engine Fire Extinguishing - Location SHEET 1) ** ON A/C 301-349, 351-450, 500-600 (Ref. Fig. Engine Fire Extinguishing - Location SHEET 1) ** ON A/C ALL (1) Remove the CAP-BLANKING from each electrical connector and receptacle. (2) Make sure that all the electrical connections are clean and in the correct condition. (3) Connect the electrical connector (2) to the pressure switch (3) of the related fire extinguisher bottle (1). ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 26-21-00-875-051-A F.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION FOR FIN 6WE2 (BOTTLE 1-FIRE EXTING, ENG 2), 6WE1 (BOTTLE 1-FIRE EXTING, ENG 1) 121VU ENGINE/ENG1 AND 2 FIRE EX2WE1 Q44 TIG/BTL1/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EX1WE1 Q43 TIG/BTL1/SQUIB/A FOR FIN 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2), 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) 121VU ENGINE/ENG1 AND 2 FIRE EX2WE2 Q42 TIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EX1WE2 Q41 TIG/BTL2/SQUIB/A

** ON A/C 301-349, 351-450, 500-600 Subtask 26-21-00-875-051-B F.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION FOR FIN 6WE2 (BOTTLE 1-FIRE EXTING, ENG 2), 6WE1 (BOTTLE 1-FIRE EXTING, ENG 1) ** ON A/C 301-349, 351-400, 500-600 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B ** ON A/C 401-450 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B

1WE1

Q43

2WE2

Q42

1WE1

Q42

2WE2

Q41

** ON A/C 301-349, 351-450, 500-600 FOR FIN 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2), 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

PANEL

DESIGNATION

** ON A/C 301-349, 351-400, 500-600 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A ** ON A/C 401-450 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A

FIN

LOCATION

2WE1

Q44

1WE2

Q41

2WE1

Q43

1WE2

Q40

** ON A/C ALL Subtask 26-21-00-710-052-A G. Do this test (1) Do an operational test of the engine fire and overheat detection (loop/squib) (Ref. AMM TASK 26-1200-710-001) . NOTE: On the ENG/APU FIRE panel 1WD, ignore the DISCH legends which come on on the ENG 1 (2) AGENT 1 and AGENT 2 pushbutton switches. (2) Make an entry in the logbook. (3) Put an applicable placard in position in the cockpit (refer to your standard practices and local regulations). 5.

Close-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 26-21-00-942-062-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the access planel(s) (Ref. AMM TASK 54-51-21-400-001) . (a) FOR 6WE1 , (BOTTLE 1-FIRE EXTING, ENG 1), 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) · 415BL, 415BR. (b) FOR 6WE2 , (BOTTLE 1-FIRE EXTING, ENG 2), 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2) · 425BR, 425BL. (3) Remove the access platform(s). (4) Remove the WARNING NOTICE(S).

** ON A/C 301-349, 351-450, 500-600 Subtask 26-21-00-410-080-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 54-51-21-400-802) : (a) FOR 6WE1 (BOTTLE 1-FIRE EXTING, ENG 1) · 415BL

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-001-A - Engine Bottle Pressure Check

(b) FOR 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) · 415CR (c) FOR 6WE2 (BOTTLE 1-FIRE EXTING, ENG 2) · 425BL (d) FOR 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2) · 425CR (3) Remove the access platform(s). (4) Remove the WARNING NOTICE(S). ** ON A/C ALL Subtask 26-21-00-862-066-A C.

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

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 12 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-003-A - Test of the Engine SQUIB Legend of the AGENT Pushbutton switch

** ON A/C ALL TASK 26-21-00-040-003-A Test of the Engine SQUIB Legend of the AGENT Pushbutton switch WARNING:

MAKE SURE THAT THE ENG1(2) FIRE PUSHBUTTON SWITCH IS PUSHED IN BEFORE YOU START THE TEST.

CAUTION:

TO RESET THE ENG 1(2) APU FIRE PUSHBUTTON SWITCH: - PUSH THE PUSHBUTTON SWITCH FULLY IN (LATCHED POSITION). THEN CLOSE THE GUARD. DO NOT TRY TO CLOSE THE GUARD AND PUSH THE PUSHBUTTON SWITCH AT THE SAME TIME.

FIN : 6WE1 , 6WE2 , 8WE1 , 8WE2 Task Summary MMEL or CDL Ref MMEL 26-01-01-03A 1.

Reason for the Job MMEL 26-01-01-03A ENG AGENT SQUIB

2

Job Set-up Information A.

Test YES

Specific Tools YES

Mhr 00.5

E/T 01.5

Nb Men 3

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific (53100141-1) OR (M83723-60-18AN)

B.

Access YES

QTY 1 AR 1 AR 1 1

DESIGNATION ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE SAFETY CLIP - CIRCUIT BREAKER VOLTMETER - DC WARNING NOTICE(S) PLUG, SHUNT OR CUP-SHUNT

Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTION 210 CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD 415 LOWER PYLON 425 LOWER PYLON FOR 6WE1 (BOTTLE 1-FIRE EXTING, ENG 1) FOR 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) 415BL ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 415BR

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-003-A - Test of the Engine SQUIB Legend of the AGENT Pushbutton switch ZONE/ACCESS

ZONE DESCRIPTION

** ON A/C 301-349, 351-450, 500-600 415CR ** ON A/C ALL FOR 6WE2 (BOTTLE 1-FIRE EXTING, ENG 2) FOR 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2) 425BL ** ON A/C 301-349, 351-450, 500-600 425CR ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 425BR ** ON A/C ALL C. Referenced Information REFERENCE (Ref. 20-15-00-910-001-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 26-12-00-710-001-A).

DESIGNATION Handling Precautions for Electrostatic Discharge Sensitive Devices Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Operational Check of Loop/Squib

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (Ref. 26-21-41-000-004-A). Removal of the Cartridge of the Engine Fire-Extinguisher Bottle ** ON A/C 301-349, 351-450, 500-600 (Ref. 26-21-41-000-004-C). Removal of the Cartridge of the Engine Fire-Extinguisher Bottle ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (Ref. 26-21-41-400-004-A). Installation of the Cartridge of the Engine Fire-Extinguisher Bottle ** ON A/C 301-349, 351-450, 500-600 (Ref. 26-21-41-400-004-C). Installation of the Cartridge of the Engine Fire-Extinguisher Bottle ** ON A/C ALL (Ref. 29-10-00-710-001-A).

Operational Check of Hydraulic Fire Shut Off Valves and Associated Indicating System

** ON A/C 301-349, 351-450, 500-600 (Ref. 54-51-21-000-802-A). Removal of the Pylon Lateral Access-Doors (Ref. 54-51-21-400-802-A). Installation of the Pylon Lateral Access-Doors

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-003-A - Test of the Engine SQUIB Legend of the AGENT Pushbutton switch

** ON A/C ALL 3.

Job Set-up Subtask 26-21-00-861-055-A A.

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

Subtask 26-21-00-941-057-A B.

Safety Precautions (1) On the ENG panel 115VU: (a) Make sure that the ENG/MODE/CRANK/NORM/IGN/START selector switch is in the NORM position. (b) Put a WARNING NOTICE(S) in position to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the 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).

Subtask 26-21-00-865-060-A C.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU ENGINE/ENG1 AND 2 FIRE EX1WE1 Q43 TIG/BTL1/SQUIB/A 121VU ENGINE/ENG1 AND 2 FIRE EX1WE2 Q41 TIG/BTL2/SQUIB/A ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 121VU ENGINE/ENG1 AND 2 FIRE EX2WE1 TIG/BTL1/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EX2WE2 TIG/BTL2/SQUIB/B ** ON A/C 301-349, 351-400, 500-600 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B ** ON A/C 401-450 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B

Q44 Q42

2WE1

Q44

2WE2

Q42

2WE1

Q43

1WE1

Q42

2WE2

Q41

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-003-A - Test of the Engine SQUIB Legend of the AGENT Pushbutton switch PANEL 121VU

DESIGNATION ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A

FIN 1WE2

LOCATION Q40

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 26-21-00-010-057-A D.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position below the engine pylon. (2) Remove the access doors: (a) FOR 6WE1 , (BOTTLE 1-FIRE EXTING, ENG 1), 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) 415BR, 415BL (b) FOR 6WE2 , (BOTTLE 1-FIRE EXTING, ENG 2), 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2) 425BR, 425BL.

** ON A/C 301-349, 351-450, 500-600 Subtask 26-21-00-010-057-B D.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position below the engine pylon. (2) Remove the access doors (Ref. AMM TASK 54-51-21-000-802) : (a) FOR 6WE1 , (BOTTLE 1-FIRE EXTING, ENG 1), 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) · 415BL, 415CR (b) FOR 6WE2 , (BOTTLE 1-FIRE EXTING, ENG 2), 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2) · 425BL, 425CR

** ON A/C ALL Subtask 26-21-00-020-051-B E.

Aircraft Maintenance Configuration WARNING: DO NOT TOUCH THE CARTRIDGE BEFORE YOU DO THE PROCEDURE APPLICABLE TO DEVICES THAT ARE SENSITIVE TO ELECTROSTATIC DISCHARGE. ELECTROSTATIC DISCHARGE CAN CAUSE THE FIRE EXTINGUISHER BOTTLE TO RELEASE ITS CONTENTS SUDDENLY AND CAUSE INJURY TO PERSONS. (1) Before you touch the cartridge, do the procedure for devices that are sensitive to electrostatic discharge (Ref. AMM TASK 20-15-00-910-001) . (2) In the engine pylon, on the engine fire extinguisher bottle, disconnect the electrical connectors from the cartridges: · For the engine 1: 5WE1-A (bottle 1) and 7WE1-A (bottle 2) · For the engine 2: 5WE2-A (bottle 1) and 7WE2-A (bottle 2). (3) Put a PLUG, SHUNT (53100141-1) or CUP-SHUNT (M83723-60-18AN) on the cartridges.

Subtask 26-21-00-420-051-A F.

On the disconnected connectors, on the wiring side: · Connect the pin 1 to an aircraft grounding point. · Connect the pin 2 to an aircraft grounding point.

Subtask 26-21-00-865-061-A G. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-003-A - Test of the Engine SQUIB Legend of the AGENT Pushbutton switch

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU ENGINE/ENG1 AND 2 FIRE EX1WE1 Q43 TIG/BTL1/SQUIB/A 121VU ENGINE/ENG1 AND 2 FIRE EX1WE2 Q41 TIG/BTL2/SQUIB/A ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 121VU ENGINE/ENG1 AND 2 FIRE EX2WE1 TIG/BTL1/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EX2WE2 TIG/BTL2/SQUIB/B ** ON A/C 301-349, 351-400, 500-600 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B ** ON A/C 401-450 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A

Q44 Q42

2WE1

Q44

2WE2

Q42

2WE1

Q43

1WE1

Q42

2WE2

Q41

1WE2

Q40

** ON A/C ALL 4.

Procedure Subtask 26-21-00-710-055-A CAUTION:

A.

MAKE SURE YOU WILL NOT CAUSE UNWANTED CHANGES TO OTHER SYSTEMS BEFORE YOU PUSH THE ENG1(2) FIRE PUSHBUTTON SWITCH. WHEN YOU PUSH THE ENG1(2) FIRE PUSHBUTTON SWITCH: - THESE VALVES CLOSE . THE LP FUEL VALVE . THE HYDRAULIC FIRE VALVE . THE BLEED AIR VALVES . THE ANTI-ICE VALVES . THE AIR CONDITIONING PACK VALVES - THE GENERATOR STOPS.

Do this Test ACTION RESULT 1.On ENG/APU FIRE panel 1WD: On ENG/APU FIRE panel 1WD: · Push and hold the TEST pushbutton switch. · The two SQUIB legends for ENG 1(2) come on. · Release the ENG 1(2) TEST pushbutton switch. - The two SQUIB legends go off.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-003-A - Test of the Engine SQUIB Legend of the AGENT Pushbutton switch

(1) If the result of the test in Para. 4.A. is correct, do the steps that follow. If the result of the test in Para. 4.A. is not correct, do step 4.D. Subtask 26-21-00-960-050-A B.

Replace the cartridge (Ref. AMM TASK 26-21-41-000-004) and (Ref. AMM TASK 26-21-41-400-004) .

Subtask 26-21-00-710-067-A C.

Do steps that follow: (1) Disconnect pins 1 and 2 from the aircraft grounding points. (2) Remove the shunt devices from the cartridges. (3) Connect connectors 5WE1-A (5WE2-A) and 7WE1-A (7WE2-A) to their cartridges. (4) Make sure that the connectors are correctly connected. (5) Do an operational test of the engine fire and overheat detection (loop/squib) (Ref. AMM TASK 26-1200-710-001) .

Subtask 26-21-00-710-068-A D.

If the result of the test in Para. 4.A. is not correct (one or the two legends of the related engine are off), the firing test system is defective. (1) Do the test that follows to make sure that the firing system operates correctly. ACTION 1. In the engine pylon: · Connect a VOLTMETER - DC between: - Pin 1 and the grounding point - Pin 2 and the grounding point. 2. On the overhead panel, on ENG/APU FIRE panel 1WD: · Lift the guard of the ENG 1(2) FIRE pushbutton switch. On ENG/APU FIRE panel 1WD: · Push, then release the ENG 1(2) FIRE pushbutton switch. · Push and hold the related AGENT 1(2) pushbutton switch. On ENG/APU FIRE panel 1WD: · Release the AGENT 1(2) pushbutton switch.

RESULT In the engine pylon: · Make sure that the VOLTMETER - DC shows OVDC. On ENG/APU FIRE panel 1WD: · Ignore the SQUIB legends.

In the engine pylon: · Make sure that the VOLTMETER - DC shows 28VDC between: - Pin 1 and the grounding point - Pin 2 and the grounding point. In the engine pylon: · Make sure that the VOLTMETER - DC shows OVDC between: - Pin 1 and the grounding point - Pin 2 and the grounding point.

On ENG/APU FIRE panel 1WD: · Lift the guard of the ENG 1(2) FIRE pushbutton switch. · Push, then release the ENG 1(2) FIRE pushbutton switch. 3. In the related engine pylon: Disconnect the voltmeter(s). (2) If the result of the test in Para. 4.D. is correct, do the steps that follow. If the result of the test in Para. 4.D. is not correct, do step 4.F. Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-003-A - Test of the Engine SQUIB Legend of the AGENT Pushbutton switch

Subtask 26-21-00-420-057-A E.

Do the steps that follow: (1) If the firing system operates correctly but the firing test system is defective, the aircraft can continue in service. (2) Disconnect the voltmeter. (3) Remove the shunt plugs from the cartridges. (4) Connect connectors 5WE1-A (5WE2-A) and 7WE1-A (7WE2-A) to their cartridges. (5) Make sure that the connectors are correctly connected. (6) On ENG/APU FIRE panel 1WD, close the guard of ENG 1(2) FIRE pushbutton switch. (7) Do an operational test of the engine fire and overheat detection (loop/squib) (Ref. AMM TASK 26-1200-710-001) . (8) Do an operational test of the hydraulic fire shut-off-valves (Ref. AMM TASK 29-10-00-710-001) .

Subtask 26-21-00-350-050-A F.

If the result of the test in Para. 4.D. is not correct, repair the firing system. (1) Do the troubleshooting of the firing system TSM 26.

5.

Close-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 26-21-00-410-057-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the access doors: (a) FOR 6WE1 , (BOTTLE 1-FIRE EXTING, ENG 1), 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) 415BR, 415BL (b) FOR 6WE2 , (BOTTLE 1-FIRE EXTING, ENG 2), 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2) 425BR, 425BL. (3) Remove the WARNING NOTICE(S). (4) Remove the access platform(s). (5) Make an entry in the logbook. (6) Put an applicable placard in position in the cockpit (refer to your standard practices and local regulations).

** ON A/C 301-349, 351-450, 500-600 Subtask 26-21-00-410-057-B A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the access doors (Ref. AMM TASK 54-51-21-400-802) : (a) FOR 6WE1 , (BOTTLE 1-FIRE EXTING, ENG 1), 8WE1 (BOTTLE 2-FIRE EXTING, ENG 1) · 415BL, 415CR (b) FOR 6WE2 , (BOTTLE 1-FIRE EXTING, ENG 2), 8WE2 (BOTTLE 2-FIRE EXTING, ENG 2) · 425BL, 425CR (3) Remove the WARNING NOTICE(S).

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-003-A - Test of the Engine SQUIB Legend of the AGENT Pushbutton switch

(4) Remove the access platform(s). (5) Make an entry in the logbook. (6) Put an applicable placard in position in the cockpit (refer to your standard practices and local regulations). ** ON A/C ALL Subtask 26-21-00-862-055-A B.

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

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-17-00-040-801-A - Deactivation of the Lavatory

** ON A/C ALL TASK 26-17-00-040-801-A Deactivation of the Lavatory Task Summary MMEL or CDL Ref MMEL 26-17-01A

Access NO

Test NO

1.

Reason for the Job MMEL 26-17-01A Lavatory Smoke Detection System (FAA only)

2

Job Set-up Information A.

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Specific Tools NO

QTY DESIGNATION 1 LABEL - INOPERATIVE DO NOT ENTER 1 WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 200

ZONE DESCRIPTION UPPER HALF FUSELAGE

C. Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A).

3.

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power

Job Set-up Subtask 26-17-00-861-056-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

4.

Procedure Subtask 26-17-00-040-050-A A.

Safety Precautions (1) Make sure that the lavatory waste receptacle is empty. (2) Close and lock the related lavatory door. (3) Put a placard LABEL - INOPERATIVE DO NOT ENTER on the related lavatory door. (4) Put a WARNING NOTICE(S) in the cockpit to tell the crew that the smoke detector of the related lavatory does not operate.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-17-00-040-801-A - Deactivation of the Lavatory

(5) Make an entry in the logbook. 5.

Close-up Subtask 26-17-00-862-057-A A.

Aircraft Maintenance Configuration (1) De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-002-A - ENG FIRE TEST - Circuit Verification

** ON A/C ALL TASK 26-21-00-040-002-A ENG FIRE TEST - Circuit Verification CAUTION:

TO RESET THE ENG 1(2) APU FIRE PUSHBUTTON SWITCH: - PUSH THE PUSHBUTTON SWITCH FULLY IN (LATCHED POSITION). THEN CLOSE THE GUARD. DO NOT TRY TO CLOSE THE GUARD AND PUSH THE PUSHBUTTON SWITCH AT THE SAME TIME.

FIN : 6WE1 , 6WE2 , 8WE1 , 8WE2 Task Summary MMEL or CDL Ref MMEL 26-01-01-31A 1.

Reason for the Job MMEL 26-01-01-31A ENG FIRE TEST

2

Job Set-up Information A.

Access NO

Mhr 00.8

E/T 01.6

Nb Men 2

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD LOWER PYLON LOWER PYLON

Referenced Information REFERENCE (Ref. 26-12-00-710-002-A). (Ref. 26-21-00-040-003-A).

3.

Specific Tools NO

Work Zones and Access Panels ZONE/ACCESS 210 415 425

B.

Test YES

DESIGNATION Operational Test of the Engine Fire and Overheat Detection with the Centralized Fault Display System (CFDS) Test of the Engine SQUIB Legend of the AGENT Pushbutton switch

Job Set-up Subtask 26-21-00-869-069-A A.

4.

Not Applicable

Procedure Subtask 26-21-00-710-056-A A.

Do an ENG FIRE TEST - Circuit Verification (1) Do the circuit verification of the ENG Agent SQUIB LTS (Ref. AMM TASK 26-21-00-040-003) . (2) Do the operational test from Multipurpose Control and Display Unit (MCDU) (Ref. AMM TASK 26-12-00-710-002) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-21-00-040-002-A - ENG FIRE TEST - Circuit Verification

5.

Close-up Subtask 26-21-00-860-075-A A.

Put the aircraft back to its initial configuration. (1) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-004-A - Bottle Pressure Check

** ON A/C ALL TASK 26-22-00-040-004-A Bottle Pressure Check

FIN : 11WF Task Summary MMEL or CDL Ref MMEL 26-01-01-05A

Access YES

1.

Reason for the Job MMEL 26-01-01-05A APU AGENT pb DISCH light

2

Job Set-up Information A.

Specific Tools NO

Mhr 00.8

E/T 00.8

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific

B.

Test YES

QTY AR AR AR AR AR

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE ALLEN KEY 3/32 IN MULTIMETER - STANDARD SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 312AR, 314AR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A). (Ref. 26-22-00-040-004-A). (Ref. 26-22-00-040-004-A-01). 3.

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power Bottle Pressure Check Bottle Weight Check

Job Set-up Subtask 26-22-00-861-064-A A.

Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Subtask 26-22-00-865-118-A B.

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

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-004-A - Bottle Pressure Check

PANEL 121VU 121VU

DESIGNATION APU/FIRE/EXTIG/SQUIB/B APU/FIRE/EXTIG/SQUIB/A

FIN 2WF 1WF

LOCATION L39 L38

Subtask 26-22-00-010-071-A C.

Get Access 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. (1) Put on and attach a safety harness before you start work in the work area (2) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the access door 312AR. (3) Open access door 312AR. (4) Set the SERVICE LT switch 3LJ to on. (5) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the access door 314AR. (6) Open access door 314AR and safety it in the open position. (7) Disconnect the connector 11WF-A from the pressure switch 11WF of the APU Fire-Extinguishing Bottle.

4.

Procedure Subtask 26-22-00-710-089-A A.

Test ACTION RESULT 1.On the pressure-switch connector (11WF): On the multimeter: · connect the leads of the MULTIMETER - STANDARD between pin B and pin C. · a closed circuit is shown, indicating a pressurized bottle. · put the ALLEN KEY 3/32 IN into the pressure-switch test socket. · slowly turn the Allen Key clockwise or counter· an open circuit is shown. clockwise approx. 10 degrees. · release the Allen Key. · a closed circuit is shown. · remove the Allen Key from the test socket and disconnect the multimeter.

NOTE: If the test is not OK, you must do the weight check of the APU fire extinguisher bottle (Ref. AMM TASK 26-22-00-040-004) . 5.

Close-up Subtask 26-22-00-410-072-A A.

Close Access (1) Make sure that all the electrical connections are clean and in the correct condition. (2) Connect the connector 11WF-A to the pressure switch 11WF. (3) Make sure that the work area is clean and clear of tools and other items.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-004-A - Bottle Pressure Check

(4) Close the access door 314AR. (5) Set the SERVICE LT switch 3LJ to off. (6) Close the access door 312AR. (7) Remove the access platform(s). (8) Put a WARNING NOTICE(S) in the cockpit to tell the flight crew that the APU AGENT DISCH light is deactivated. (9) Make an entry in the A/C technical logbook. Subtask 26-22-00-865-119-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/FIRE/EXTIG/SQUIB/B APU/FIRE/EXTIG/SQUIB/A

FIN 2WF 1WF

LOCATION L39 L38

Subtask 26-22-00-862-064-A C.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-004-A01 - Bottle Weight Check

** ON A/C ALL TASK 26-22-00-040-004-A01 Bottle Weight Check

FIN : 11WF Task Summary MMEL or CDL Ref MMEL 26-01-01-05A

Access NO

1.

Reason for the Job MMEL 26-01-01-05A APU AGENT pb DISCH light

2

Job Set-up Information A.

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Referenced Information REFERENCE (Ref. 26-22-41-000-001-A). (Ref. 26-22-41-400-001-A).

3.

Test YES

DESIGNATION Removal of the Fire Extinguisher Bottle Installation of the Fire Extinguisher Bottle

Job Set-up Subtask 26-22-00-010-061-A A.

4.

Remove the APU fire extinguisher bottle (11WF) (Ref. AMM TASK 26-22-41-000-001) .

Procedure Subtask 26-22-00-280-053-A A.

Weigh the APU fire extinguisher bottle (1) Make sure that the gross weight of the fire-extinguisher bottle is the same as the last weight shown on the identification plate, plus or minus 50 g (1.76 oz). NOTE: You must weigh the fire-extinguisher bottle without the discharge head and the cartridge. Compare the weight shown on the fire-extinguisher bottle with the weight shown on the identification plate. You must reject the fire-extinguisher bottle if the gross weight is not in the limits.

5.

Close-up Subtask 26-22-00-410-062-A A.

Put the System back to its Operational Configuration (1) Install the APU fire extinguisher bottle (11WF) (Ref. AMM TASK 26-22-41-400-001) . (2) Make an entry in the aircraft technical logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-005-A - Circuit Verification

** ON A/C ALL TASK 26-22-00-040-005-A Circuit Verification WARNING:

MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. UNWANTED ELECTRICAL POWER CAN BE DANGEROUS.

WARNING:

THE CARTRIDGE IS AN EXPLOSIVE DEVICE. REMOVE IT BEFORE YOU DISASSEMBLE THE FIRE EXTINGUISHER BOTTLE. TO PREVENT INJURY TO THE PERSONNEL BECAUSE OF THE EXPLOSION OF THE CARTRIDGE IF IT HAS NOT BEEN FIRED: - INSTALL A SHUNT DEVICE. - THIS WILL SHUNT THE PINS TOGETHER ON THE CARTRIDGE BEFORE ITS REMOVAL. DO NOT USE A FOIL SHUNT.

Task Summary MMEL or CDL Ref MMEL 26-01-01-06A

Access YES

1.

Reason for the Job MMEL 26-01-01-06A APU AGENT pb SQUIB light

2

Job Set-up Information A.

Test YES

Specific Tools YES

Mhr 00.3

E/T 00.7

Nb Men 2

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific

QTY 1 AR AR AR AR AR

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE BOOMSET 600 OHMS HEADSET 600 OHMS MULTIMETER - STANDARD SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

** ON A/C 016-022, 024-100, 204-204, 213-214, 219-221, 229-229, 235-235, 239-239, 350-350 (6971-0010) 1 CAP SHUNT-FIRE BOTTLE ** ON A/C ALL B.

Work Zones and Access Panels ZONE/ACCESS 314AR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-005-A - Circuit Verification

REFERENCE (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

3.

DESIGNATION Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up Subtask 26-22-00-941-059-A A.

Put the WARNING NOTICE(S) in position on the overhead panel 25VU to tell persons not to operate the APU.

Subtask 26-22-00-865-071-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/FIRE/EXTIG/SQUIB/B APU/FIRE/EXTIG/SQUIB/A

FIN 2WF 1WF

LOCATION L39 L38

Subtask 26-22-00-860-058-A C.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) On the CAPT jack panel, connect the HEADSET 600 OHMS to the related connector. (3) On the overhead panel 50VU, make sure that the ON legend on the SVCE INT OVRD pushbutton switch is off. (4) In Zone 314, connect the BOOMSET 600 OHMS to the service interphone jack.

** ON A/C 112-150, 201-201, 203-203, 205-212, 215-218, 222-228, 230-234, 236-238, 240-250, 301-349, 351450, 500-600 Subtask 26-22-00-010-059-A D.

Get Access (1) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the access door 314AR. (2) Open the access door 314AR. (3) Disconnect the connector 12WF-A from the cartridge 12WF. (4) Put a PROTECTIVE CAP-FIRE EXTINGUISHER CARTRIDGE (MS25043-10DA) on the cartridge 12WF. (5) On the electrical connector 12WF-A, temporarily ground the pins A and B.

** ON A/C 016-022, 024-100, 204-204, 213-214, 219-221, 229-229, 235-235, 239-239, 350-350 Subtask 26-22-00-010-059-B D.

Get Access (1) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the access door 314AR. (2) Open the access door 314AR.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-005-A - Circuit Verification

(3) Disconnect the connector 12WF-A from the cartridge 12WF. (4) Put a CAP SHUNT-FIRE BOTTLE (6971-0010) or CAP SHUNT-FIRE BOTTLE (CEC-10) on the cartridge 12WF. (5) On the electrical connector 12WF-A, temporarily ground the pins A and B. ** ON A/C ALL Subtask 26-22-00-865-072-A E.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU

4.

DESIGNATION APU/FIRE/EXTIG/SQUIB/B APU/FIRE/EXTIG/SQUIB/A

FIN 2WF 1WF

LOCATION L39 L38

Procedure Subtask 26-22-00-710-067-A WARNING:

A.

MAKE SURE THAT YOU WILL NOT CAUSE UNWANTED CHANGES TO OTHER SYSTEMS BEFORE YOU PUSH THE APU FIRE PUSHBUTTON SWITCH. WHEN YOU PUSH THE APU FIRE PUSHBUTTON SWITCH, THESE VALVES CLOSE : - LP FUEL SHUTOFF VALVE (APU) - FUEL SOLENOID VALVE (APU) - BLEED AIR VALVE (APU)

Operational Test of the Firing Circuit and the Test Circuit NOTE: For this test procedure we recommend that a minimum of two persons are in constant contact with each other through the service interphone system. One person must monitor the cockpit APU FIRE panel 20VU, the other person must be at Zone 313.

ACTION 1.On the electrical connector 12WF-A: · remove the temporary ground connection from the pins A and B. 2.On the electrical connector 12WF-A: · connect a MULTIMETER - STANDARD between pin A and a ground. 3.On the APU FIRE panel 20VU: · lift the guard then push and release the APU FIRE pushbutton switch. · push and hold the APU AGENT pushbutton switch. 4.On the APU FIRE panel 20VU: · release APU AGENT pushbutton switch. 5.On the electrical connector 12WF-A: · connect the MULTIMETER - STANDARD between pin B and a ground. 6.On the APU FIRE panel 20VU: · push and hold the APU AGENT pushbutton switch. 7.On the APU FIRE panel 20VU:

RESULT

On the multimeter · 0 VDC is shown. On the multimeter · 28 VDC is shown. NOTE: Ignore the APU AGENT SQUIB legend and other subsequent effects. On the multimeter · 0 VDC is shown. On the multimeter · 0 VDC is shown. On the multimeter · 28 VDC is shown. On the multimeter

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-005-A - Circuit Verification

ACTION · release APU AGENT pushbutton switch. · 0 VDC is shown. 8.On the APU FIRE panel 20VU: · push and latch the APU FIRE pushbutton switch. · put the guard of the APU pushbutton switch in the correct position.

RESULT

NOTE: If the test is correct, the firing system will operate correctly. The test system is defective. NOTE: If the test is not correct (no voltage), the firing system is defective and do the applicable trouble shooting procedure.

5.

Close-up Subtask 26-22-00-865-073-A A.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/FIRE/EXTIG/SQUIB/B APU/FIRE/EXTIG/SQUIB/A

FIN 2WF 1WF

LOCATION L39 L38

** ON A/C 112-150, 201-201, 203-203, 205-212, 215-218, 222-228, 230-234, 236-238, 240-250, 301-349, 351450, 500-600 Subtask 26-22-00-410-060-A B.

Put the aircraft back to its initial configuration. (1) Remove the PROTECTIVE CAP-FIRE EXTINGUISHER CARTRIDGE (MS250643-10DA) from the cartridge 12WF. (2) Make sure that all the electrical connections are clean and in the correct condition. (3) Connect the connector 12WF-A to the cartridge 12WF. (4) Disconnect the BOOMSET 600 OHMS from the service interphone jack. (5) Disconnect the HEADSET 600 OHMS from the CAPT jack panel. (6) Make sure that the work area is clean and clear of tools and other items. (7) Close the access door 314AR. (8) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (9) Remove the access platform(s). (10) Remove the warning notice from the panel 25VU. (11) Put the WARNING NOTICE(S) in the cockpit to tell the flight crew that the APU AGENT SQUIB light is deactivated. (12) Make an entry in the aircraft technical logbook.

** ON A/C 016-022, 024-100, 204-204, 213-214, 219-221, 229-229, 235-235, 239-239, 350-350 Subtask 26-22-00-410-060-B B.

Put the aircraft back to its initial configuration.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-005-A - Circuit Verification

(1) Remove the CAP SHUNT-FIRE BOTTLE (6971-0010) or CAP SHUNT-FIRE BOTTLE (CEC-10) from the cartridge 12WF. (2) Make sure that all the electrical connections are clean and in the correct condition. (3) Connect the connector 12WF-A to the cartridge 12WF. (4) Disconnect the BOOMSET 600 OHMS from the service interphone jack. (5) Disconnect the HEADSET 600 OHMS from the CAPT jack panel. (6) Make sure that the work area is clean and clear of tools and other items. (7) Close the access door 314AR. (8) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (9) Remove the access platform(s). (10) Remove the warning notice from the panel 25VU. (11) Put the WARNING NOTICE(S) in the cockpit to tell the flight crew that the APU AGENT SQUIB light is deactivated. (12) Make an entry in the aircraft technical logbook. ** ON A/C ALL Subtask 26-22-00-865-074-A C.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/FIRE/EXTIG/SQUIB/B APU/FIRE/EXTIG/SQUIB/A

FIN 2WF 1WF

LOCATION L39 L38

Subtask 26-22-00-860-059-A D.

Put the aircraft back to its initial configuration. (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-012-A - Test Circuit Verification

** ON A/C ALL TASK 26-22-00-040-012-A Test Circuit Verification WARNING:

MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. UNWANTED ELECTRICAL POWER CAN BE DANGEROUS.

WARNING:

CAREFULLY OBEY THE APPROVED PROCEDURE FOR THIS TASK. TO PREVENT THE EXPLOSION OF THE CARTRIDGE, MAKE SURE THAT YOU INSTALL AN ELECTROSTATIC PROTECTIVE CAP ON THE DISCHARGE CARTRIDGE WHEN YOU DO THIS TASK.

Task Summary MMEL or CDL Ref MMEL 26-01-01-32A 1.

Reason for the Job MMEL 26-01-01-32A APU FIRE TEST pb

2

Job Set-up Information A.

Access YES

Test NO

Specific Tools YES

Mhr 01.5

E/T 00.7

Nb Men 2

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific

QTY 1 AR AR AR AR AR

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE BOOMSET 600 OHMS HEADSET 600 OHMS MULTIMETER - STANDARD SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

** ON A/C 016-022, 024-100, 204-204, 213-214, 219-221, 229-229, 235-235, 239-239, 350-350 (6971-0010) 1 CAP SHUNT-FIRE BOTTLE ** ON A/C ALL B.

Work Zones and Access Panels ZONE/ACCESS 314AR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-012-A - Test Circuit Verification

REFERENCE (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

3.

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up Subtask 26-22-00-941-065-A A.

Put the WARNING NOTICE(S) in position on the overhead panel 25VU to tell persons not to operate the APU.

Subtask 26-22-00-865-099-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/FIRE/EXTIG/SQUIB/B APU/FIRE/EXTIG/SQUIB/A

FIN 2WF 1WF

LOCATION L39 L38

Subtask 26-22-00-860-072-A C.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) On the CAPT jack panel, connect the HEADSET 600 OHMS to the related connector. (3) Remove the snapwire from the APU FIRE pushbutton switch on panel 20VU. (4) In Zone 314, connect the BOOMSET 600 OHMS to the service interphone jack. (5) Energize the Annunciator Light Test Dimming system.

** ON A/C 112-150, 201-201, 203-203, 205-212, 215-218, 222-228, 230-234, 236-238, 240-250, 301-349, 351450, 500-600 Subtask 26-22-00-010-067-A D.

Get Access (1) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the access door 314AR. (2) Open the access door 314AR. (3) Disconnect the electrical connector 12WF-A from the cartridge 12WF. (4) Put a PROTECTIVE CAP-FIRE EXTINGUISHER CARTRIDGE (MS25043-10DA) on the cartridge 12WF.

** ON A/C 016-022, 024-100, 204-204, 213-214, 219-221, 229-229, 235-235, 239-239, 350-350 Subtask 26-22-00-010-067-B D.

Get Access (1) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the access door 314AR. (2) Open the access door 314AR. (3) Disconnect the electrical connector 12WF-A from the cartridge 12WF. (4) Put a CAP SHUNT-FIRE BOTTLE (6971-0010) on the cartridge 12WF.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-012-A - Test Circuit Verification

** ON A/C ALL Subtask 26-22-00-865-100-A E.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU

4.

DESIGNATION APU/FIRE/EXTIG/SQUIB/B APU/FIRE/EXTIG/SQUIB/A

FIN 2WF 1WF

LOCATION L39 L38

Procedure Subtask 26-22-00-710-076-A WARNING:

A.

MAKE SURE THAT YOU WILL NOT CAUSE UNWANTED CHANGES TO OTHER SYSTEMS BEFORE YOU PUSH THE APU FIRE PUSHBUTTON SWITCH. WHEN YOU PUSH THE APU FIRE PUSHBUTTON SWITCH, THESE VALVES CLOSE : - LP FUEL SHUTOFF VALVE (APU) - FUEL SOLENOID VALVE (APU) - BLEED AIR VALVE (APU)

Operational Test of the Test Circuit NOTE: For this test procedure we recommend that a minimum of two persons are in constant contact with each other through the service interphone system. One person must monitor the cockpit APU FIRE panel 20VU, the other person must be at Zone 313.

ACTION 1.On the connector 12WF-A: · connect a MULTIMETER - STANDARD between terminal A and ground, and then between terminal B and ground. 2.On the APU FIRE panel 20VU: · push the APU FIRE pushbutton switch.

RESULT On the connector 12WF-A: · make sure that there is no voltage shown between the terminals A and B and ground.

On the connector 12WF-A: · make sure that there is no voltage shown between the terminals A and B and ground. 3.On the APU FIRE panel 20VU: On the APU FIRE panel 20 VU: · press and hold the SQUIB pushbutton switch. · on the AGENT pushbutton switch, the SQUIB light comes on. On the connector 12WF-A: · make sure that there is 28V DC shown between terminal A and B and ground. 4.On the APU FIRE panel 20VU: On the connector 12WF-A: · release the SQUIB pushbutton switch. · make sure that there is no volatge shown. 5.On the APU FIRE panel 20VU: On the APU FIRE panel 20 VU: · push to release the APU FIRE pushbutton switch. · on the AGENT pushbutton switch, the SQUIB light goes off. NOTE: If the test is correct, the APU fire extinguishing system will operate correctly. The test circuit is faulty.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-012-A - Test Circuit Verification

ACTION

RESULT

NOTE: If the test is not correct (no voltage), the test circuit is faulty and do the applicable trouble shooting procedure.

5.

Close-up Subtask 26-22-00-865-101-A A.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/FIRE/EXTIG/SQUIB/B APU/FIRE/EXTIG/SQUIB/A

FIN 2WF 1WF

LOCATION L39 L38

** ON A/C 112-150, 201-201, 203-203, 205-212, 215-218, 222-228, 230-234, 236-238, 240-250, 301-349, 351450, 500-600 Subtask 26-22-00-410-068-A B.

Put the aircraft back to its initial configuration. (1) Remove the PROTECTIVE CAP-FIRE EXTINGUISHER CARTRIDGE (MS25043-10DA) from the cartridge 12WF. (2) Make sure that all the electrical connections are clean and in the correct condition. (3) Connect the electrical connector 12WF-A to the cartridge 12WF. (4) Disconnect the BOOMSET 600 OHMS from the service interphone jack. (5) Disconnect the HEADSET 600 OHMS from the CAPT jack panel. (6) Make sure that the work area is clean and clear of tools and other items. (7) Close the access door 314AR. (8) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (9) Remove the access platform(s). (10) Remove the warning notice from the panel 25VU. (11) Make an entry in the aircraft technical logbook.

** ON A/C 016-022, 024-100, 204-204, 213-214, 219-221, 229-229, 235-235, 239-239, 350-350 Subtask 26-22-00-410-068-B B.

Put the aircraft back to its initial configuration. (1) Remove the CAP SHUNT-FIRE BOTTLE (6971-0010) from the cartridge 12WF. (2) Make sure that all the electrical connections are clean and in the correct condition. (3) Connect the electrical connector 12WF-A to the cartridge 12WF. (4) Disconnect the BOOMSET 600 OHMS from the service interphone jack. (5) Disconnect the HEADSET 600 OHMS from the CAPT jack panel. (6) Make sure that the work area is clean and clear of tools and other items. (7) Close the access door 314AR.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-012-A - Test Circuit Verification

(8) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (9) Remove the access platform(s). (10) Remove the warning notice from the panel 25VU. (11) Make an entry in the aircraft technical logbook. ** ON A/C ALL Subtask 26-22-00-865-102-A C.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/FIRE/EXTIG/SQUIB/B APU/FIRE/EXTIG/SQUIB/A

FIN 2WF 1WF

LOCATION L39 L38

Subtask 26-22-00-860-073-A D.

Put the aircraft back to its initial configuration. (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-23-00-040-001-A - Cargo Compartment DISCH LT - Verification of Fire-Extinguisher Bottle Weight

** ON A/C ALL TASK 26-23-00-040-001-A Cargo Compartment DISCH LT - Verification of Fire-Extinguisher Bottle Weight Task Summary MMEL or CDL Ref MMEL 26-01-02-01A 1.

Reason for the Job MMEL 26-01-02-01A CARGO SMOKE DISCH

2

Job Set-up Information A.

Access NO

Test NO

Specific Tools NO

Mhr 01.5

E/T 01.5

Nb Men 1

Referenced Information REFERENCE

DESIGNATION

** ON A/C 203-206, 210-211, 215-220, 226-228, 230-230, 234-235, 239-239, 350-350 (Ref. 26-23-41-280-001-A). Remove Cargo Compartment Fire-Extinguisher Bottle for in-shop Weight Check ** ON A/C 016-016, 201-201, 207-207, 209-209, 221-222, 229-229, 231-233, 237-237, 240-240, 242-250, 401-450 (Ref. 26-23-41-280-001-B). Remove Cargo Compartment Fire-Extinguisher Bottle for in-shop Weight Check ** ON A/C 017-022, 024-100, 112-150, 208-208, 212-214, 223-225, 236-236, 238-238, 241-241, 301-349, 351-400, 500-600 (Ref. 26-23-42-280-001-A). Remove Cargo Compartment Fire-Extinguisher Bottle for in-shop Weight Check ** ON A/C ALL 3.

Procedure

** ON A/C 203-206, 210-211, 215-220, 226-228, 230-230, 234-235, 239-239, 350-350 Subtask 26-23-00-280-050-A A.

Weight Check of the Fire Extinguisher Bottle (1) Remove the Lower-Deck Cargo-Compartment (LDCC) fire extinguisher bottle for a weight check (Ref. AMM TASK 26-23-41-280-001) .

** ON A/C 016-016, 201-201, 207-207, 209-209, 221-222, 229-229, 231-233, 237-237, 240-240, 242-250, 401-450 Subtask 26-23-00-280-050-B A.

Weight Check of the Fire Extinguisher Bottle (1) Remove the Lower-Deck Cargo-Compartment (LDCC) fire extinguisher bottle for a weight check (Ref. AMM TASK 26-23-41-280-001) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-23-00-040-001-A - Cargo Compartment DISCH LT - Verification of Fire-Extinguisher Bottle Weight

** ON A/C 017-022, 024-100, 112-150, 208-208, 212-214, 223-225, 236-236, 238-238, 241-241, 301-349, 351400, 500-600 Subtask 26-23-00-280-050-C A.

Weight Check of the Fire Extinguisher Bottle (1) Remove the Lower-Deck Cargo-Compartment (LDCC) fire extinguisher bottle for a weight check (Ref. AMM TASK 26-23-42-280-001) .

** ON A/C ALL 4.

Close-up

** ON A/C 203-206, 210-211, 215-220, 226-228, 230-230, 234-235, 239-239, 350-350 Subtask 26-23-00-420-053-A A.

Put the aircraft back to its initial configuration. (1) Make an entry in the logbook.

** ON A/C 016-016, 201-201, 207-207, 209-209, 221-222, 229-229, 231-233, 237-237, 240-240, 242-250, 401-450 Subtask 26-23-00-420-053-B A.

Put the aircraft back to its initial configuration. (1) Make an entry in the logbook.

** ON A/C 017-022, 024-100, 112-150, 208-208, 212-214, 223-225, 236-236, 238-238, 241-241, 301-349, 351400, 500-600 Subtask 26-23-00-420-053-C A.

Put the aircraft back to its initial configuration. (1) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-17-00-040-802-A - Deactivation of the Smoke-Detection Control Unit (SDCU)

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 TASK 26-17-00-040-802-A Deactivation of the Smoke-Detection Control Unit (SDCU) Task Summary MMEL or CDL Ref MMEL 26-17-02A

Access NO

Test NO

1.

Reason for the Job MMEL 26-17-02A Smoke Detection Control Unit (SDCU) (FAA only)

2

Job Set-up Information A.

E/T 00.3

Nb Men 1

QTY DESIGNATION 1 LABEL - INOPERATIVE DO NOT ENTER 1 WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A).

3.

Mhr 00.3

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Specific Tools NO

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power

Job Set-up Subtask 26-17-00-861-057-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

4.

Procedure Subtask 26-17-00-040-051-A A.

Safety Precautions (1) Make sure that the lavatory waste receptacle is empty. (2) Close and lock the related lavatory door. (3) Put a placard LABEL - INOPERATIVE DO NOT ENTER on the related lavatory door. (4) Put a WARNING NOTICE(S) in the cockpit to tell the crew that the smoke detector of the related lavatory does not operate. (5) Make an entry in the logbook.

5.

Close-up Subtask 26-17-00-862-058-A A.

Put the aircraft back to its initial configuration.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-17-00-040-802-A - Deactivation of the Smoke-Detection Control Unit (SDCU)

(1) De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-18-00-040-801-A - Deactivation of the Video Control Center (VCC) with Standalone Smoke-Detection System (if installed)

** ON A/C 206-206, 229-229, 235-235 TASK 26-18-00-040-801-A Deactivation of the Video Control Center (VCC) with Standalone Smoke-Detection System (if installed) Task Summary MMEL or CDL Ref MMEL 26-18-01B

Access NO

Test NO

Specific Tools NO

1.

Reason for the Job MMEL 26-18-01B Video Control Center Standalone Smoke Detection System (If Installed)

2

Job Set-up Information A.

E/T 00.2

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Mhr 00.2

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER 1 WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 210 220

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD FWD CAB UTILITY AREAS

C. Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A).

3.

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power

Job Set-up Subtask 26-18-00-861-055-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

4.

Procedure Subtask 26-18-00-865-060-A A.

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

DESIGNATION

** ON A/C 206-206 2000VU IFE-IFE CTR-AC 2000VU IFE-IFE CTR-DC-IFEC

FIN

22MK 21MK

LOCATION

C04 C03

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-18-00-040-801-A - Deactivation of the Video Control Center (VCC) with Standalone Smoke-Detection System (if installed) PANEL 2000VU 2000VU 2000VU 2000VU

DESIGNATION IFE-IFE CTR-DC-VCC IFE-VCC-SMOKE IFE CABIN RH FWD - TU IFE CABIN TU LH

FIN 20MH 37MH 24MH 22MH

C01 D06 D02 D01

LOCATION

** ON A/C 206-206, 229-229 2000VU IFE-CABIN-ADB2 2000VU IFE-CABIN-ADB1 2000VU IFE-IFE CENTER-AC-VCC

24MK 23MK 21MH

C06 C05 C02

** ON A/C 229-229 2000VU IFE-IFE CTR-AC-IFEC

22MK

C04

** ON A/C 206-206, 229-229, 235-235 Subtask 26-18-00-040-050-A B.

Deactivation of the VCC Standalone Smoke-Detection System (1) Put a WARNING NOTICE(S) in the cockpit to tell persons that the systems related to the VCC are stopped.

5.

Close-up Subtask 26-18-00-860-058-A A.

Aircraft Maintenance Configuration (1) Make an entry in the logbook. (2) De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-007-A - Bottle Pressure Switch Check

** ON A/C ALL TASK 26-22-00-040-007-A Bottle Pressure Switch Check Task Summary MMEL or CDL Ref MMEL 26-22-02A

Access YES

Test YES

Specific Tools NO

1.

Reason for the Job MMEL 26-22-02A APU Fire Extinguisher Overpressure Indication (Red Disc)

2

Job Set-up Information A.

E/T 00.5

Nb Men 2

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific

B.

Mhr 00.3

QTY AR AR AR AR AR

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE ALLEN KEY 3/32 IN BOOMSET 600 OHMS HEADSET 600 OHMS SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS 312AR, 314AR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Check of the Pressure Switch SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-007-A - Bottle Pressure Switch Check

A 11WF

A

FR80 314AR

FR76

B

OVERBOARD PIPE DISTRIBUTION PIPE

B PRESSURE SWITCH WITH GUARD

1

2

DISCHARGE INDICATOR (RED DISC) N_MM_262200_4_AAA0_01_00

Figure 26-22-00-991-00200-00-A / SHEET 1/1 - Check of the Pressure Switch ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-007-A - Bottle Pressure Switch Check

3.

Job Set-up Subtask 26-22-00-860-062-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) In the Cockpit on the CAPT jack panel, connect the HEADSET 600 OHMS to the related connector. (3) On the overhead panel 50VU, make sure that the ON legend on the SVCE INT OVRD p/bsw is OFF.

Subtask 26-22-00-865-081-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/APU/CTL APU/ECB/SPLY

FIN 2KD 1KD

LOCATION L42 L41

Subtask 26-22-00-010-062-A C.

Get Access 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. (1) Put on and attach a safety harness before you start work in the work area (2) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the access door 312AR. (3) Open the access door 312AR. (4) Set the SERVICE LT SW 3LJ to ON. (5) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the access door 314AR. (6) Open access door 314AR and safety it in the open position. (7) In Zone 314, connect the BOOMSET 600 OHMS to the service interphone jack.

4.

Procedure (Ref. Fig. Check of the Pressure Switch SHEET 1) Subtask 26-22-00-710-070-A A.

Do a check at the Pressure Switch of the APU Fire Extinguisher Bottle NOTE: For this test procedure we recommend that a minimum of two persons are in constant contact with each other through the service interphone system. One person must monitor the cockpit APU FIRE panel 20VU, the other person must be at Zone 312.

ACTION RESULT 1.On the APU fire extinguisher bottle: On the APU FIRE panel 20VU: · put the ALLEN KEY 3/32 IN (1) into the pres· the DISCH legend in the AGENT p/bsw comes on. sure-switch hexagon test-socket (2). Slowly turn the Allen key clockwise or counterclockwise approx. 10 degrees.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-007-A - Bottle Pressure Switch Check

ACTION

RESULT On the APU FIRE panel 20VU: NOTE: The pressure effect puts the Allen key back · the DISCH legend in the AGENT p/bsw goes off. to its initial position. 2.On the APU Fire extinguisher bottle: · release the Allen key. 3.On the APU fire extinguisher bottle: · remove the Allen key from the test socket. 5.

Close-up Subtask 26-22-00-410-063-A A.

Close Access (1) Disconnect the BOOMSET 600 OHMS from the service interphone jack. (2) Disconnect the HEADSET 600 OHMS from the CAPT jack panel. (3) Make sure that the work area is clean and clear of tools and other items. (4) Close the maintenance access door 314AR. (5) Set the SERVICE LT SW 3LJ to OFF. (6) Close the access door 312AR. (7) Remove the access platform(s). (8) Make an entry in the aircraft technical logbook.

Subtask 26-22-00-865-082-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/APU/CTL APU/ECB/SPLY

FIN 2KD 1KD

LOCATION L42 L41

Subtask 26-22-00-860-063-A C.

Put the aircraft back to its initial configuration. (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-008-A - Check of the remaining Squib Integrity

** ON A/C ALL TASK 26-22-00-040-008-A Check of the remaining Squib Integrity WARNING:

MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. UNWANTED ELECTRICAL POWER CAN BE DANGEROUS.

WARNING:

DO NOT GO IN THE APU COMPARTMENT. IF THE FIRE EXTINGUISHER ACCIDENTALLY FIRES, IT CAN CAUSE INJURY TO PERSONNEL.

Task Summary MMEL or CDL Ref MMEL 26-22-03A

Access YES

Test NO

1.

Reason for the Job MMEL 26-22-03A Squib of the APU Fire Extinguisher Bottle

2

Job Set-up Information A.

Specific Tools YES

Mhr 01.5

E/T 00.7

Nb Men 2

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific

QTY 1 1 1 1 AR 1

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE BOOMSET 600 OHMS HEADSET 600 OHMS MULTIMETER - STANDARD SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

** ON A/C 016-022, 024-100, 204-204, 213-214, 219-221, 229-229, 235-235, 239-239, 350-350 (6971-0010) 1 CAP SHUNT-FIRE BOTTLE ** ON A/C ALL B.

Work Zones and Access Panels ZONE/ACCESS 314AR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-008-A - Check of the remaining Squib Integrity

REFERENCE (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

3.

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up Subtask 26-22-00-941-061-A A.

Safety Precautions (1) Put a WARNING NOTICE(S) in position on the overhead panel 20VU to tell persons not to operate the APU.

Subtask 26-22-00-865-083-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/FIRE/EXTIG/SQUIB/B APU/FIRE/EXTIG/SQUIB/A

FIN 2WF 1WF

LOCATION L39 L38

Subtask 26-22-00-860-064-A C.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) On the CAPT jack panel, connect the HEADSET 600 OHMS to the related connector. (3) On the overhead panel 50VU, make sure that the ON legend on the SVCE INT OVRD pushbutton switch is off. (4) In Zone 314, connect the BOOMSET 600 OHMS to the service interphone jack.

** ON A/C 112-150, 201-201, 203-203, 205-212, 215-218, 222-228, 230-234, 236-238, 240-250, 301-349, 351450, 500-600 Subtask 26-22-00-010-063-A D.

Get Access (1) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the access door 314AR. (2) Open the access door 314AR. 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) Disconnect the connector 12WF-A from the cartridge 12WF. (4) Put a PROTECTIVE CAP-FIRE EXTINGUISHER CARTRIDGE (MS25043-10DA) on the cartridge 12WF. (5) On the electrical connector 12WF-A, temporarily ground the pins A and B.

** ON A/C 016-022, 024-100, 204-204, 213-214, 219-221, 229-229, 235-235, 239-239, 350-350 Subtask 26-22-00-010-063-B D.

Get Access

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-008-A - Check of the remaining Squib Integrity

(1) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the access door 314AR. (2) Open the access door 314AR. 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) Disconnect the connector 12WF-A from the cartridge 12WF. (4) Put a CAP SHUNT-FIRE BOTTLE (6971-0010) or CAP SHUNT-FIRE BOTTLE (CEC-10) on the cartridge 12WF. (5) On the electrical connector 12WF-A, temporarily ground the pins A and B. ** ON A/C ALL Subtask 26-22-00-865-085-A E.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU

4.

DESIGNATION APU/FIRE/EXTIG/SQUIB/B APU/FIRE/EXTIG/SQUIB/A

FIN 2WF 1WF

LOCATION L39 L38

Procedure

** ON A/C 112-150, 201-201, 203-203, 205-212, 215-218, 222-228, 230-234, 236-238, 240-250, 301-349, 351450, 500-600 Subtask 26-22-00-710-072-A WARNING:

A.

MAKE SURE THAT THE OHMMETER HAS A MAXIMUM CURRENT OF 1 AMP. IF THE CURRENT IS MORE THAN 1 AMP, IT CAN CAUSE AN EXPLOSION OF THE CARTRIDGE.

Operational Test of the Test Circuit NOTE: For this test procedure we recommend that a minimum of two persons are in constant contact with each other through the service interphone system. One person must monitor the cockpit APU FIRE panel 20VU, the other person must be at Zone 313.

ACTION 1.On the APU FIRE panel 20VU: · push and hold the TEST pushbutton switch. · hold the TEST pushbutton switch. 2.If the test is correct, the cartridge is defective. · Do the subsequent test to make sure at least one squib is operative. 3.If the test is not correct, the FIRE System Test or the Extinguish Wiring is defective. · Do the applicable Trouble Shooting procedure. 4.Remove the PROTECTIVE CAP-FIRE EXTINGUISHER CARTRIDGE (MS25043-10DA) from the cartridge 12WF. 5.On the electrical connector 12WF:

RESULT On the APU FIRE panel 20VU: · the white SQUIB legend comes on. · the white SQUIB legend goes off.

On the MULTIMETER - STANDARD: · 1 ohm +/- 0.1 is shown.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-008-A - Check of the remaining Squib Integrity

ACTION · connect a MULTIMETER - STANDARD between pin A and ground.

RESULT

The squib A is operative. 6.On the electrical connector 12WF: On the MULTIMETER - STANDARD: · connect a MULTIMETER - STANDARD between · 1 ohm +/- 0.1 is shown. pin B and ground. The squib B is operative.

** ON A/C 016-022, 024-100, 204-204, 213-214, 219-221, 229-229, 235-235, 239-239, 350-350 Subtask 26-22-00-710-072-B WARNING:

A.

MAKE SURE THAT THE OHMMETER HAS A MAXIMUM CURRENT OF 1 AMP. IF THE CURRENT IS MORE THAN 1 AMP, IT CAN CAUSE AN EXPLOSION OF THE CARTRIDGE.

Operational Test of the Test Circuit NOTE: For this test procedure we recommend that a minimum of two persons are in constant contact with each other through the service interphone system. One person must monitor the cockpit APU FIRE panel 20VU, the other person must be at Zone 313.

ACTION 1.On the APU FIRE panel 20VU: · push and hold the TEST pushbutton switch. · hold the TEST pushbutton switch. 2.If the test is correct, the cartridge is defective. · Do the subsequent test to make sure at least one squib is operative. 3.If the test is not correct, the FIRE System Test or the Extinguish Wiring is defective. · Do the applicable Trouble Shooting procedure. 4.Remove the CAP SHUNT-FIRE BOTTLE (69710010) or CAP SHUNT-FIRE BOTTLE (CEC-10) from the cartridge 12WF. 5.On the electrical connector 12WF: · connect a MULTIMETER - STANDARD between pin A and ground.

RESULT On the APU FIRE panel 20VU: · the white SQUIB legend comes on. · the white SQUIB legend goes off.

On the MULTIMETER - STANDARD: · 1 ohm +/- 0.1 is shown.

The squib A is operative. 6.On the electrical connector 12WF: On the MULTIMETER - STANDARD: · connect a MULTIMETER - STANDARD between · 1 ohm +/- 0.1 is shown. pin B and ground. The squib B is operative.

** ON A/C ALL 5.

Close-up Subtask 26-22-00-860-074-A A.

Put the system back to the serviceable condition. (1) On the electrical connector 12WF-A, remove the temporary ground connection from pin A and pin B.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-008-A - Check of the remaining Squib Integrity

Subtask 26-22-00-865-084-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/FIRE/EXTIG/SQUIB/B APU/FIRE/EXTIG/SQUIB/A

FIN 2WF 1WF

LOCATION L39 L38

** ON A/C 112-150, 201-201, 203-203, 205-212, 215-218, 222-228, 230-234, 236-238, 240-250, 301-349, 351450, 500-600 Subtask 26-22-00-410-064-A C.

Put the aircraft back to its initial configuration. (1) Remove the PROTECTIVE CAP-FIRE EXTINGUISHER CARTRIDGE (MS25043-10DA) from the cartridge 12WF. (2) Make sure that all the electrical connections are clean and in the correct condition. (3) Connect the connector 12WF-A to the cartridge 12WF. (4) Disconnect the BOOMSET 600 OHMS from the service interphone jack. (5) Disconnect the HEADSET 600 OHMS from the CAPT jack panel. (6) Make sure that the work area is clean and clear of tools and other items. (7) Close the access door 314AR. (8) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (9) Remove the access platform(s). (10) Remove the WARNING NOTICE(S) from the panel 25VU. (11) Make an entry in the aircraft technical logbook.

** ON A/C 016-022, 024-100, 204-204, 213-214, 219-221, 229-229, 235-235, 239-239, 350-350 Subtask 26-22-00-410-064-B C.

Put the aircraft back to its initial configuration. (1) Remove the CAP SHUNT-FIRE BOTTLE (6971-0010) or CAP SHUNT-FIRE BOTTLE (CEC-10) from the cartridge 12WF. (2) Make sure that all the electrical connections are clean and in the correct condition. (3) Connect the connector 12WF-A to the cartridge 12WF. (4) Disconnect the BOOMSET 600 OHMS from the service interphone jack. (5) Disconnect the HEADSET 600 OHMS from the CAPT jack panel. (6) Make sure that the work area is clean and clear of tools and other items. (7) Close the access door 314AR. (8) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (9) Remove the access platform(s). (10) Remove the WARNING NOTICE(S) from the panel 25VU. (11) Make an entry in the aircraft technical logbook.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-008-A - Check of the remaining Squib Integrity

** ON A/C ALL Subtask 26-22-00-865-086-A D.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/FIRE/EXTIG/SQUIB/B APU/FIRE/EXTIG/SQUIB/A

FIN 2WF 1WF

LOCATION L39 L38

Subtask 26-22-00-860-065-A E.

Put the aircraft back to its initial configuration. (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-010-A - To make sure that the APU Automatic Fire Extinguishing System is operative when the APU FIRE Light on External Power Panel is inoperative

** ON A/C ALL TASK 26-22-00-040-010-A To make sure that the APU Automatic Fire Extinguishing System is operative when the APU FIRE Light on External Power Panel is inoperative Task Summary MMEL or CDL Ref MMEL 26-22-06A

Access NO

Test NO

1.

Reason for the Job MMEL 26-22-06A APU FIRE on the External Power Panel

2

Job Set-up Information A.

E/T 00.3

Nb Men 1

QTY DESIGNATION 1 WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-02).

3.

Mhr 00.3

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Specific Tools NO

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up Subtask 26-22-00-941-063-A A.

Safety Precautions (1) Put the WARNING NOTICE(S) in position on the overhead panel 25VU to tell persons not to operate the APU.

Subtask 26-22-00-860-068-A B.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) or (Ref. AMM TASK 24-41-00-861-002) .

4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 26-22-00-710-074-A WARNING:

DO NOT PUSH THE TEST PUSHBUTTON SWITCH ON THE APU/AUTO EXTING SECTION OF OVERHEAD PANEL 50VU WHILE THE APU IS IN OPERATION.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-010-A - To make sure that the APU Automatic Fire Extinguishing System is operative when the APU FIRE Light on External Power Panel is inoperative IF YOU DO, DISCHARGE OF THE APU-FIRE EXTINGUISHER BOTTLE CAN OCCUR. A.

Operational Test of the Test Circuit ACTION 1.In the APU/AUTO EXTING section of panel 50VU: · Push the TEST ON pushbutton during the test.

RESULT In the APU/AUTO EXTING section of panel 50VU: · The OK legend in the TEST pushbutton switch comes on. NOTE: If the OK legend in the TEST pushbutton switch comes on, all components operate correctly.

2.In the APU/AUTO EXTING section of panel 50VU: · Push the RESET pushbutton switch.

In the APU/AUTO EXTING section of panel 50VU: · The test circuit sets back.

** ON A/C 301-349, 351-450, 500-600 Subtask 26-22-00-710-074-B WARNING:

A.

DO NOT PUSH THE TEST PUSHBUTTON SWITCH ON THE APU/AUTO EXTING SECTION OF OVERHEAD PANEL 50VU WHILE THE APU IS IN OPERATION. IF YOU DO, DISCHARGE OF THE APU-FIRE EXTINGUISHER BOTTLE CAN OCCUR.

Operational Test of the Test Circuit NOTE: This test causes a spurious WARNING in ECAM (APU FIRE LOOP A FAULT) because of a FDU hardware modification.

ACTION 1.In the APU/AUTO EXTING section of panel 50VU: · Push the TEST ON pushbutton during the test.

RESULT In the APU/AUTO EXTING section of panel 50VU: · The OK legend in the TEST pushbutton switch comes on. After 5 seconds, on the ECAM upper display unit: · The warning, APU FIRE LOOP A FAULT comes on. NOTE: If the OK legend in the TEST pushbutton switch comes on, all components operate correctly.

2.In the APU/AUTO EXTING section of panel 50VU: · Push the RESET pushbutton switch.

In the APU/AUTO EXTING section of panel 50VU: · The test circuit sets back.

** ON A/C ALL 5.

Close-up Subtask 26-22-00-410-066-A A.

Put the aircraft back to its initial configuration.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-010-A - To make sure that the APU Automatic Fire Extinguishing System is operative when the APU FIRE Light on External Power Panel is inoperative

(1) Make an entry in the aircraft technical logbook. Subtask 26-22-00-860-069-A B.

Put the aircraft back to its initial configuration. (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) or (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-011-A - To make sure that the APU Automatic Fire Extinguishing System is operative when the APU SHUT OFF PB on External Power Panel is inoperative

** ON A/C ALL TASK 26-22-00-040-011-A To make sure that the APU Automatic Fire Extinguishing System is operative when the APU SHUT OFF PB on External Power Panel is inoperative Task Summary MMEL or CDL Ref MMEL 26-22-07A

Access NO

Test NO

1.

Reason for the Job MMEL 26-22-07A APU SHUT OFF on the External Power Panel

2

Job Set-up Information A.

E/T 00.3

Nb Men 1

QTY DESIGNATION 1 WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-02).

3.

Mhr 00.3

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Specific Tools NO

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up Subtask 26-22-00-941-064-A A.

Put the WARNING NOTICE(S) in position on the overhead panel 25VU to tell persons not to operate the APU.

Subtask 26-22-00-860-070-A B.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) or (Ref. AMM TASK 24-41-00-861-002) .

4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 26-22-00-710-075-A WARNING:

DO NOT PUSH THE TEST PUSHBUTTON SWITCH ON THE APU/AUTO EXTING SECTION OF OVERHEAD PANEL 50VU WHILE THE APU IS IN OPERATION. IF YOU DO, DISCHARGE OF THE APU-FIRE EXTINGUISHER BOTTLE CAN OCCUR.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-011-A - To make sure that the APU Automatic Fire Extinguishing System is operative when the APU SHUT OFF PB on External Power Panel is inoperative

A.

Operational Test of the Test Circuit ACTION 1.In the APU/AUTO EXTING section of panel 50VU: · Push the TEST ON pushbutton during the test.

RESULT In the APU/AUTO EXTING section of panel 50VU: · The OK legend in the TEST pushbutton switch comes on. NOTE: If the OK legend in the TEST pushbutton switch comes on, all components operate correctly.

2.In the APU/AUTO EXTING section of panel 50VU: · Push the RESET pushbutton switch.

In the APU/AUTO EXTING section of panel 50VU: · The test circuit sets back.

** ON A/C 301-349, 351-450, 500-600 Subtask 26-22-00-710-075-B WARNING:

A.

DO NOT PUSH THE TEST PUSHBUTTON SWITCH ON THE APU/AUTO EXTING SECTION OF OVERHEAD PANEL 50VU WHILE THE APU IS IN OPERATION. IF YOU DO, DISCHARGE OF THE APU-FIRE EXTINGUISHER BOTTLE CAN OCCUR.

Operational Test of the Test Circuit NOTE: This test causes a spurious WARNING in ECAM (APU FIRE LOOP A FAULT) because of a FDU hardware modification.

ACTION 1.In the APU/AUTO EXTING section of panel 50VU: · Push the TEST ON pushbutton during the test.

RESULT In the APU/AUTO EXTING section of panel 50VU: · The OK legend in the TEST pushbutton switch comes on. After 5 seconds, on the ECAM upper display unit: · The warning, APU FIRE LOOP A FAULT comes on. NOTE: If the OK legend in the TEST pushbutton switch comes on, all components operate correctly.

2.In the APU/AUTO EXTING section of panel 50VU: · Push the RESET pushbutton switch.

In the APU/AUTO EXTING section of panel 50VU: · The test circuit sets back.

** ON A/C ALL 5.

Close-up Subtask 26-22-00-410-067-A A.

Put the aircraft back to its initial configuration. (1) Make an entry in the aircraft technical logbook.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 26-22-00-040-011-A - To make sure that the APU Automatic Fire Extinguishing System is operative when the APU SHUT OFF PB on External Power Panel is inoperative

Subtask 26-22-00-860-071-A B.

Put the aircraft back to its initial configuration. (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) or (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-40-00-040-001-A - Check of the synchronization between pitch trim handwheel and stabilizer

** ON A/C ALL TASK 27-40-00-040-001-A Check of the synchronization between pitch trim handwheel and stabilizer WARNING:

MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

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.

Task Summary MMEL or CDL Ref MMEL 27-07-05A

Access NO

Test YES

Specific Tools YES

1.

Reason for the Job MMEL 27-07-05A Pitch Trim Position Indication on the F/CTL SD page (FAA only)

2

Job Set-up Information A.

E/T 00.2

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Mhr 00.2

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS 210 310

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD FUSLG TAIL SECTION AFT OF AFT PRESS BHD

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-40-00-040-001-A - Check of the synchronization between pitch trim handwheel and stabilizer REFERENCE (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 29-23-00-863-001-A). (Ref. 29-23-00-864-001-A). (Ref. 29-24-00-863-001-A). (Ref. 29-24-00-864-001-A). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). 3.

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump Depressurize the Green and Yellow Hydraulic Systems after Operation of the PTU Pressurize the Yellow Hydraulic System with the Electric Pump Depressurize the Yellow Hydraulic System EIS Start Procedure EIS Stop Procedure

Job Set-up Subtask 27-40-00-860-050-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) On the FLT CTL panel 23VU: · make sure that the FLT CTL/ELAC 1 and FLT CTL/SEC 1 pushbutton switches are pushed (On these pushbutton switches, the OFF and FAULT legends are off). (3) On the FLT CTL panel 24VU: · make sure that the FLT CTL/ELAC 2 and FLT CTL/SEC 2 pushbutton switches are pushed (On these pushbutton switches, the OFF and FAULT legends are off). (4) Do the EIS start procedure (Ref. AMM TASK 31-60-00-860-001) . (5) On the center pedestal, on the ECAM control panel, push the F/CTL pushbutton switch. (On the lower ECAM display unit, the F/CTL page comes into view). (6) Pressurize the Green and the Yellow hydraulic systems (Ref. AMM TASK 29-23-00-863-001) (Ref. AMM TASK 29-24-00-863-001) .

Subtask 27-40-00-941-050-A B.

Get Access (1) Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at the zone 310 in front of the THS position marks.

Subtask 27-40-00-865-050-A C.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 121VU

4.

DESIGNATION FLIGHT CONTROLS/ELAC2/NORM/ SPLY

FIN 15CE2

LOCATION R20

Procedure Subtask 27-40-00-710-050-A A.

Check of the synchronization between pitch trim handwheel and stabilizer.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-40-00-040-001-A - Check of the synchronization between pitch trim handwheel and stabilizer ACTION 1.On the center pedestal, slowly move one of the pitch-trim control wheels to the 4 deg. DN stop.

RESULT · The 4 Deg DN indication on each graduated wheel is opposite the triangle on the center pedestal index. · In the zone 310, the position mark of the THS is opposite the 4th upper mark on the tail cone. 2.Slowly move one of the pitch-trim control wheels · The 13.5 UP mark on each graduated wheel is opto the 13.5 deg UP stop. posite the triangle of the center pedestal index. · In the zone 310, the position mark of the THS is opposite the 13.5 th lower mark on the tail cone. 3.Move the pitch-trim control wheel to the 0 posi· In the zone 310, the position mark of the THS is in tion. front of the neutral mark on the tail cone. 5.

Close-up Subtask 27-40-00-942-050-A A.

Put the aircraft back to its initial configuration. (1) Depressurize the Green and Yellow hydraulic systems (Ref. AMM TASK 29-23-00-864-001) and (Ref. AMM TASK 29-24-00-864-001) . (2) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (3) Make an entry in the log-book. (4) Make sure that the work area is clean and clear of tools and other items. (5) Remove the access platform(s). (6) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

** ON A/C ALL TASK 27-14-00-040-001-A Deactivation of the Aileron Servo Control 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:

DO NOT DO THIS DEACTIVATION PROCEDURE IF THERE IS EXTERNAL LEAKAGE ON THE UNSERVICEABLE SERVOCONTROL.

WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

FIN : 33CE1 , 33CE2 , 33CE3 , 33CE4 1.

Reason for the Job MMEL 27-14-01A Left Aileron Blue Servo-Control (Controlled by ELAC 1) MMEL 27-14-02A Left Aileron Green Servo-Control (Controlled by ELAC 2) MMEL 27-14-03A Right Aileron Green Servo-Control (Controlled by ELAC 1) MMEL 27-14-04A Right Aileron Blue Servo-Control (Controlled by ELAC 2)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific

B.

QTY 1 1 AR AR AR AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER TIE WRAP WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 575 675 575KB, 675KB, 822

ZONE DESCRIPTION AFT OUTBD SE OF WING AND TE FIXED STRUCT AFT OUTBD SE OF WING AND TE FIXED STRUCT

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 27-14-00-710-001-A). Operational Test of the Aileron and Hydraulic Actuation (Ref. 27-96-00-740-001-A). BITE Test of the EFCS (Ground Scanning) (Ref. 29-10-00-864-001-A). Depressurize the Green Hydraulic System (Ref. 29-10-00-864-003-A). Depressurize the Blue Hydraulic System Deactivation/Reactivation of the Aileron Servocontrol SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

A

A Z675

ACCESS DOOR 675KB

A Z575

LEFT WING

A ACCESS DOOR 575KB

B

RIGHT WING 33CE2

33CE1

33CE4

33CE3

A

AILERON SERVOCONTROL

ELAC 2 ELAC 1 ELAC 1 ELAC 2

33CE1 (GREEN) 33CE2 (GREEN) 33CE3 (BLUE) 33CE4 (BLUE)

B

ASSOCIATED COMPUTER

1

2 N_MM_271400_4_AEM0_01_00

Figure 27-14-00-991-00200-00-A / SHEET 1/1 - Deactivation/Reactivation of the Aileron Servocontrol ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

3.

Job Set-up Subtask 27-14-00-860-057-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Do a ground scanning (Ref. AMM TASK 27-96-00-740-001) . NOTE: If there is only the maintenance messages on: - PEDALS XDCR UNIT 25CE1 (25CE2) and/or - ELAC 1(2) AIL ORDER DISAGREE. the deactivation of the aileron servocontrol is not necessary. You can dispatch the aircraft without further maintenance action. (3) Make sure that the hydraulic systems are depressurized (Ref. AMM TASK 29-10-00-864-001) (Ref. AMM TASK 29-10-00-864-003) .

Subtask 27-14-00-010-052-A B.

Get Access (1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position: (a) at the zone 575 for the left aileron, (b) at the zone 675 for the right aileron. (2) Open the access door: (a) 575KB for the left aileron, (b) 675KB for the right aileron. (3) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 822. (4) Open the access door 822. (5) On the battery power center 105VU: · loosen the two screws and remove the protective cover.

Subtask 27-14-00-865-057-A C.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU FLIGHT CONTROLS/ELAC1/NORM/ 15CE1 B11 SPLY ** ON A/C 401-450 49VU FLIGHT CONTROLS/ELAC1/NORM/ SPLY ** ON A/C ALL 105VU 105VU 121VU 4.

15CE1

B06

FLIGHT CONTROLS/ELAC2/STBY SPLY 16CE2 FLT CTL/ELAC1/STBY SPLY 16CE1 FLIGHT CONTROLS/ELAC2/NORM/ 15CE2 SPLY

A02 A01 R20

Procedure (Ref. Fig. Deactivation/Reactivation of the Aileron Servocontrol SHEET 1)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

Subtask 27-14-00-040-050-A A.

Deactivation of the Aileron Servo Control (1) Make sure that there are no external leaks from the servo control you deactivate. (2) Make sure that the pressure and return lines are correctly connected to the parts of the servo control. (3) Disconnect the electrical connector (1) from the receptacle (2). (4) Put CAP - BLANKING on the disconnected connector (1) and receptacle (2). (5) Attach the connector (1) to a pipe with a TIE WRAP.

Subtask 27-14-00-865-058-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 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU FLIGHT CONTROLS/ELAC1/NORM/ 15CE1 B11 SPLY ** ON A/C 401-450 49VU FLIGHT CONTROLS/ELAC1/NORM/ SPLY ** ON A/C ALL 105VU 105VU 121VU

15CE1

B06

FLIGHT CONTROLS/ELAC2/STBY SPLY 16CE2 FLT CTL/ELAC1/STBY SPLY 16CE1 FLIGHT CONTROLS/ELAC2/NORM/ 15CE2 SPLY

A02 A01 R20

Subtask 27-14-00-710-053-A C.

Do the operational test of the ailerons (Ref. AMM TASK 27-14-00-710-001) . NOTE: Make sure that: - The servocontrol you deactivated does not operate. - The related servocontrol symbol (box) is amber. - The amber F/CTL AILERON SERVO FAULT message is shown on the EWD.

5.

Close-up Subtask 27-14-00-860-058-A A.

Put the aircraft back to its initial configuration. (1) Put a WARNING NOTICE(S) in the cockpit to tell the crew that the left or right aileron servo control is deactivated. (2) Make an entry in the log-book. (3) Make sure that the work area is clean and clear of tools and other items. (4) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Subtask 27-14-00-410-052-A B.

Close Access (1) Close the access door: (a) 575KB for the left aileron.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

(b) 675KB for the right aileron. (2) Install the protective cover on the battery power center 105VU. (3) Tighten the two screws. (4) Close the access door 822. (5) Remove the access platform(s).

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

** ON A/C ALL TASK 27-14-00-040-001-A Deactivation of the Aileron Servo Control 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:

DO NOT DO THIS DEACTIVATION PROCEDURE IF THERE IS EXTERNAL LEAKAGE ON THE UNSERVICEABLE SERVOCONTROL.

WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

FIN : 33CE1 , 33CE2 , 33CE3 , 33CE4 1.

Reason for the Job MMEL 27-14-01A Left Aileron Blue Servo-Control (Controlled by ELAC 1) MMEL 27-14-02A Left Aileron Green Servo-Control (Controlled by ELAC 2) MMEL 27-14-03A Right Aileron Green Servo-Control (Controlled by ELAC 1) MMEL 27-14-04A Right Aileron Blue Servo-Control (Controlled by ELAC 2)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific

B.

QTY 1 1 AR AR AR AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER TIE WRAP WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 575 675 575KB, 675KB, 822

ZONE DESCRIPTION AFT OUTBD SE OF WING AND TE FIXED STRUCT AFT OUTBD SE OF WING AND TE FIXED STRUCT

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 27-14-00-710-001-A). Operational Test of the Aileron and Hydraulic Actuation (Ref. 27-96-00-740-001-A). BITE Test of the EFCS (Ground Scanning) (Ref. 29-10-00-864-001-A). Depressurize the Green Hydraulic System (Ref. 29-10-00-864-003-A). Depressurize the Blue Hydraulic System Deactivation/Reactivation of the Aileron Servocontrol SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

A

A Z675

ACCESS DOOR 675KB

A Z575

LEFT WING

A ACCESS DOOR 575KB

B

RIGHT WING 33CE2

33CE1

33CE4

33CE3

A

AILERON SERVOCONTROL

ELAC 2 ELAC 1 ELAC 1 ELAC 2

33CE1 (GREEN) 33CE2 (GREEN) 33CE3 (BLUE) 33CE4 (BLUE)

B

ASSOCIATED COMPUTER

1

2 N_MM_271400_4_AEM0_01_00

Figure 27-14-00-991-00200-00-A / SHEET 1/1 - Deactivation/Reactivation of the Aileron Servocontrol ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

3.

Job Set-up Subtask 27-14-00-860-057-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Do a ground scanning (Ref. AMM TASK 27-96-00-740-001) . NOTE: If there is only the maintenance messages on: - PEDALS XDCR UNIT 25CE1 (25CE2) and/or - ELAC 1(2) AIL ORDER DISAGREE. the deactivation of the aileron servocontrol is not necessary. You can dispatch the aircraft without further maintenance action. (3) Make sure that the hydraulic systems are depressurized (Ref. AMM TASK 29-10-00-864-001) (Ref. AMM TASK 29-10-00-864-003) .

Subtask 27-14-00-010-052-A B.

Get Access (1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position: (a) at the zone 575 for the left aileron, (b) at the zone 675 for the right aileron. (2) Open the access door: (a) 575KB for the left aileron, (b) 675KB for the right aileron. (3) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 822. (4) Open the access door 822. (5) On the battery power center 105VU: · loosen the two screws and remove the protective cover.

Subtask 27-14-00-865-057-A C.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU FLIGHT CONTROLS/ELAC1/NORM/ 15CE1 B11 SPLY ** ON A/C 401-450 49VU FLIGHT CONTROLS/ELAC1/NORM/ SPLY ** ON A/C ALL 105VU 105VU 121VU 4.

15CE1

B06

FLIGHT CONTROLS/ELAC2/STBY SPLY 16CE2 FLT CTL/ELAC1/STBY SPLY 16CE1 FLIGHT CONTROLS/ELAC2/NORM/ 15CE2 SPLY

A02 A01 R20

Procedure (Ref. Fig. Deactivation/Reactivation of the Aileron Servocontrol SHEET 1)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

Subtask 27-14-00-040-050-A A.

Deactivation of the Aileron Servo Control (1) Make sure that there are no external leaks from the servo control you deactivate. (2) Make sure that the pressure and return lines are correctly connected to the parts of the servo control. (3) Disconnect the electrical connector (1) from the receptacle (2). (4) Put CAP - BLANKING on the disconnected connector (1) and receptacle (2). (5) Attach the connector (1) to a pipe with a TIE WRAP.

Subtask 27-14-00-865-058-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 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU FLIGHT CONTROLS/ELAC1/NORM/ 15CE1 B11 SPLY ** ON A/C 401-450 49VU FLIGHT CONTROLS/ELAC1/NORM/ SPLY ** ON A/C ALL 105VU 105VU 121VU

15CE1

B06

FLIGHT CONTROLS/ELAC2/STBY SPLY 16CE2 FLT CTL/ELAC1/STBY SPLY 16CE1 FLIGHT CONTROLS/ELAC2/NORM/ 15CE2 SPLY

A02 A01 R20

Subtask 27-14-00-710-053-A C.

Do the operational test of the ailerons (Ref. AMM TASK 27-14-00-710-001) . NOTE: Make sure that: - The servocontrol you deactivated does not operate. - The related servocontrol symbol (box) is amber. - The amber F/CTL AILERON SERVO FAULT message is shown on the EWD.

5.

Close-up Subtask 27-14-00-860-058-A A.

Put the aircraft back to its initial configuration. (1) Put a WARNING NOTICE(S) in the cockpit to tell the crew that the left or right aileron servo control is deactivated. (2) Make an entry in the log-book. (3) Make sure that the work area is clean and clear of tools and other items. (4) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Subtask 27-14-00-410-052-A B.

Close Access (1) Close the access door: (a) 575KB for the left aileron.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

(b) 675KB for the right aileron. (2) Install the protective cover on the battery power center 105VU. (3) Tighten the two screws. (4) Close the access door 822. (5) Remove the access platform(s).

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

** ON A/C ALL TASK 27-14-00-040-001-A Deactivation of the Aileron Servo Control 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:

DO NOT DO THIS DEACTIVATION PROCEDURE IF THERE IS EXTERNAL LEAKAGE ON THE UNSERVICEABLE SERVOCONTROL.

WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

FIN : 33CE1 , 33CE2 , 33CE3 , 33CE4 1.

Reason for the Job MMEL 27-14-01A Left Aileron Blue Servo-Control (Controlled by ELAC 1) MMEL 27-14-02A Left Aileron Green Servo-Control (Controlled by ELAC 2) MMEL 27-14-03A Right Aileron Green Servo-Control (Controlled by ELAC 1) MMEL 27-14-04A Right Aileron Blue Servo-Control (Controlled by ELAC 2)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific

B.

QTY 1 1 AR AR AR AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER TIE WRAP WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 575 675 575KB, 675KB, 822

ZONE DESCRIPTION AFT OUTBD SE OF WING AND TE FIXED STRUCT AFT OUTBD SE OF WING AND TE FIXED STRUCT

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 27-14-00-710-001-A). Operational Test of the Aileron and Hydraulic Actuation (Ref. 27-96-00-740-001-A). BITE Test of the EFCS (Ground Scanning) (Ref. 29-10-00-864-001-A). Depressurize the Green Hydraulic System (Ref. 29-10-00-864-003-A). Depressurize the Blue Hydraulic System Deactivation/Reactivation of the Aileron Servocontrol SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

A

A Z675

ACCESS DOOR 675KB

A Z575

LEFT WING

A ACCESS DOOR 575KB

B

RIGHT WING 33CE2

33CE1

33CE4

33CE3

A

AILERON SERVOCONTROL

ELAC 2 ELAC 1 ELAC 1 ELAC 2

33CE1 (GREEN) 33CE2 (GREEN) 33CE3 (BLUE) 33CE4 (BLUE)

B

ASSOCIATED COMPUTER

1

2 N_MM_271400_4_AEM0_01_00

Figure 27-14-00-991-00200-00-A / SHEET 1/1 - Deactivation/Reactivation of the Aileron Servocontrol ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

3.

Job Set-up Subtask 27-14-00-860-057-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Do a ground scanning (Ref. AMM TASK 27-96-00-740-001) . NOTE: If there is only the maintenance messages on: - PEDALS XDCR UNIT 25CE1 (25CE2) and/or - ELAC 1(2) AIL ORDER DISAGREE. the deactivation of the aileron servocontrol is not necessary. You can dispatch the aircraft without further maintenance action. (3) Make sure that the hydraulic systems are depressurized (Ref. AMM TASK 29-10-00-864-001) (Ref. AMM TASK 29-10-00-864-003) .

Subtask 27-14-00-010-052-A B.

Get Access (1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position: (a) at the zone 575 for the left aileron, (b) at the zone 675 for the right aileron. (2) Open the access door: (a) 575KB for the left aileron, (b) 675KB for the right aileron. (3) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 822. (4) Open the access door 822. (5) On the battery power center 105VU: · loosen the two screws and remove the protective cover.

Subtask 27-14-00-865-057-A C.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU FLIGHT CONTROLS/ELAC1/NORM/ 15CE1 B11 SPLY ** ON A/C 401-450 49VU FLIGHT CONTROLS/ELAC1/NORM/ SPLY ** ON A/C ALL 105VU 105VU 121VU 4.

15CE1

B06

FLIGHT CONTROLS/ELAC2/STBY SPLY 16CE2 FLT CTL/ELAC1/STBY SPLY 16CE1 FLIGHT CONTROLS/ELAC2/NORM/ 15CE2 SPLY

A02 A01 R20

Procedure (Ref. Fig. Deactivation/Reactivation of the Aileron Servocontrol SHEET 1)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

Subtask 27-14-00-040-050-A A.

Deactivation of the Aileron Servo Control (1) Make sure that there are no external leaks from the servo control you deactivate. (2) Make sure that the pressure and return lines are correctly connected to the parts of the servo control. (3) Disconnect the electrical connector (1) from the receptacle (2). (4) Put CAP - BLANKING on the disconnected connector (1) and receptacle (2). (5) Attach the connector (1) to a pipe with a TIE WRAP.

Subtask 27-14-00-865-058-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 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU FLIGHT CONTROLS/ELAC1/NORM/ 15CE1 B11 SPLY ** ON A/C 401-450 49VU FLIGHT CONTROLS/ELAC1/NORM/ SPLY ** ON A/C ALL 105VU 105VU 121VU

15CE1

B06

FLIGHT CONTROLS/ELAC2/STBY SPLY 16CE2 FLT CTL/ELAC1/STBY SPLY 16CE1 FLIGHT CONTROLS/ELAC2/NORM/ 15CE2 SPLY

A02 A01 R20

Subtask 27-14-00-710-053-A C.

Do the operational test of the ailerons (Ref. AMM TASK 27-14-00-710-001) . NOTE: Make sure that: - The servocontrol you deactivated does not operate. - The related servocontrol symbol (box) is amber. - The amber F/CTL AILERON SERVO FAULT message is shown on the EWD.

5.

Close-up Subtask 27-14-00-860-058-A A.

Put the aircraft back to its initial configuration. (1) Put a WARNING NOTICE(S) in the cockpit to tell the crew that the left or right aileron servo control is deactivated. (2) Make an entry in the log-book. (3) Make sure that the work area is clean and clear of tools and other items. (4) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Subtask 27-14-00-410-052-A B.

Close Access (1) Close the access door: (a) 575KB for the left aileron.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

(b) 675KB for the right aileron. (2) Install the protective cover on the battery power center 105VU. (3) Tighten the two screws. (4) Close the access door 822. (5) Remove the access platform(s).

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

** ON A/C ALL TASK 27-14-00-040-001-A Deactivation of the Aileron Servo Control 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:

DO NOT DO THIS DEACTIVATION PROCEDURE IF THERE IS EXTERNAL LEAKAGE ON THE UNSERVICEABLE SERVOCONTROL.

WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

FIN : 33CE1 , 33CE2 , 33CE3 , 33CE4 1.

Reason for the Job MMEL 27-14-01A Left Aileron Blue Servo-Control (Controlled by ELAC 1) MMEL 27-14-02A Left Aileron Green Servo-Control (Controlled by ELAC 2) MMEL 27-14-03A Right Aileron Green Servo-Control (Controlled by ELAC 1) MMEL 27-14-04A Right Aileron Blue Servo-Control (Controlled by ELAC 2)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific

B.

QTY 1 1 AR AR AR AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER TIE WRAP WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 575 675 575KB, 675KB, 822

ZONE DESCRIPTION AFT OUTBD SE OF WING AND TE FIXED STRUCT AFT OUTBD SE OF WING AND TE FIXED STRUCT

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 27-14-00-710-001-A). Operational Test of the Aileron and Hydraulic Actuation (Ref. 27-96-00-740-001-A). BITE Test of the EFCS (Ground Scanning) (Ref. 29-10-00-864-001-A). Depressurize the Green Hydraulic System (Ref. 29-10-00-864-003-A). Depressurize the Blue Hydraulic System Deactivation/Reactivation of the Aileron Servocontrol SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

A

A Z675

ACCESS DOOR 675KB

A Z575

LEFT WING

A ACCESS DOOR 575KB

B

RIGHT WING 33CE2

33CE1

33CE4

33CE3

A

AILERON SERVOCONTROL

ELAC 2 ELAC 1 ELAC 1 ELAC 2

33CE1 (GREEN) 33CE2 (GREEN) 33CE3 (BLUE) 33CE4 (BLUE)

B

ASSOCIATED COMPUTER

1

2 N_MM_271400_4_AEM0_01_00

Figure 27-14-00-991-00200-00-A / SHEET 1/1 - Deactivation/Reactivation of the Aileron Servocontrol ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

3.

Job Set-up Subtask 27-14-00-860-057-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Do a ground scanning (Ref. AMM TASK 27-96-00-740-001) . NOTE: If there is only the maintenance messages on: - PEDALS XDCR UNIT 25CE1 (25CE2) and/or - ELAC 1(2) AIL ORDER DISAGREE. the deactivation of the aileron servocontrol is not necessary. You can dispatch the aircraft without further maintenance action. (3) Make sure that the hydraulic systems are depressurized (Ref. AMM TASK 29-10-00-864-001) (Ref. AMM TASK 29-10-00-864-003) .

Subtask 27-14-00-010-052-A B.

Get Access (1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position: (a) at the zone 575 for the left aileron, (b) at the zone 675 for the right aileron. (2) Open the access door: (a) 575KB for the left aileron, (b) 675KB for the right aileron. (3) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 822. (4) Open the access door 822. (5) On the battery power center 105VU: · loosen the two screws and remove the protective cover.

Subtask 27-14-00-865-057-A C.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU FLIGHT CONTROLS/ELAC1/NORM/ 15CE1 B11 SPLY ** ON A/C 401-450 49VU FLIGHT CONTROLS/ELAC1/NORM/ SPLY ** ON A/C ALL 105VU 105VU 121VU 4.

15CE1

B06

FLIGHT CONTROLS/ELAC2/STBY SPLY 16CE2 FLT CTL/ELAC1/STBY SPLY 16CE1 FLIGHT CONTROLS/ELAC2/NORM/ 15CE2 SPLY

A02 A01 R20

Procedure (Ref. Fig. Deactivation/Reactivation of the Aileron Servocontrol SHEET 1)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

Subtask 27-14-00-040-050-A A.

Deactivation of the Aileron Servo Control (1) Make sure that there are no external leaks from the servo control you deactivate. (2) Make sure that the pressure and return lines are correctly connected to the parts of the servo control. (3) Disconnect the electrical connector (1) from the receptacle (2). (4) Put CAP - BLANKING on the disconnected connector (1) and receptacle (2). (5) Attach the connector (1) to a pipe with a TIE WRAP.

Subtask 27-14-00-865-058-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 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU FLIGHT CONTROLS/ELAC1/NORM/ 15CE1 B11 SPLY ** ON A/C 401-450 49VU FLIGHT CONTROLS/ELAC1/NORM/ SPLY ** ON A/C ALL 105VU 105VU 121VU

15CE1

B06

FLIGHT CONTROLS/ELAC2/STBY SPLY 16CE2 FLT CTL/ELAC1/STBY SPLY 16CE1 FLIGHT CONTROLS/ELAC2/NORM/ 15CE2 SPLY

A02 A01 R20

Subtask 27-14-00-710-053-A C.

Do the operational test of the ailerons (Ref. AMM TASK 27-14-00-710-001) . NOTE: Make sure that: - The servocontrol you deactivated does not operate. - The related servocontrol symbol (box) is amber. - The amber F/CTL AILERON SERVO FAULT message is shown on the EWD.

5.

Close-up Subtask 27-14-00-860-058-A A.

Put the aircraft back to its initial configuration. (1) Put a WARNING NOTICE(S) in the cockpit to tell the crew that the left or right aileron servo control is deactivated. (2) Make an entry in the log-book. (3) Make sure that the work area is clean and clear of tools and other items. (4) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Subtask 27-14-00-410-052-A B.

Close Access (1) Close the access door: (a) 575KB for the left aileron.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-14-00-040-001-A - Deactivation of the Aileron Servo Control

(b) 675KB for the right aileron. (2) Install the protective cover on the battery power center 105VU. (3) Tighten the two screws. (4) Close the access door 822. (5) Remove the access platform(s).

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-34-00-040-001-A - Elevator Servocontrol PositionTransducer - Connection of the Spare Transducer

** ON A/C ALL TASK 27-34-00-040-001-A Elevator Servocontrol Position-Transducer - Connection of the Spare Transducer 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:

MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

CAUTION:

DO NOT USE THIS PROCEDURE IF THE SERVOCONTROL HAS ONE TRANSDUCER (RVDT SIMPLEX). THE AIRCRAFT DISPATCH IS NOT POSSIBLE.

Task Summary MMEL or CDL Ref MMEL 27-34-02A

Access YES

Test YES

1.

Reason for the Job MMEL 27-34-02A Elevator Servo-Control Position Transducer

2

Job Set-up Information A.

Mhr 01.5

E/T 00.5

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Specific Tools YES

QTY DESIGNATION 1 ACCESS PLATFORM 6M (20 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS 334 344 334DB, 344DB

ZONE DESCRIPTION THS TRAILING EDGE THS TRAILING EDGE

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-34-00-040-001-A - Elevator Servocontrol PositionTransducer - Connection of the Spare Transducer REFERENCE (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 27-34-00-710-001-A). Operational Test of the Elevator and Hydraulic Actuation (Ref. 29-10-00-864-003-A). Depressurize the Blue Hydraulic System (Ref. 29-23-00-864-001-A). Depressurize the Green and Yellow Hydraulic Systems after Operation of the PTU (Ref. 29-24-00-864-001-A). Depressurize the Yellow Hydraulic System (Ref. 55-13-11-000-001-A). Remove/Open of the Trimmable Horizontal Stabilizer (THS) Trailing-Edge Access-Panels (Ref. 55-13-11-400-001-A). Install/Close of the Trimmable Horizontal Stabilizer (THS) Trailing-Edge Access-Panels Elevator Servocontrols Position-Transducers SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-34-00-040-001-A - Elevator Servocontrol PositionTransducer - Connection of the Spare Transducer

F W D

A

LOWER SURFACE Z330

344DB

334DB

Z340

A B

B

D C

1

1 3 TRANSDUCER

BLANKING CAP 2

B

3 TRANSDUCERS

CD

1 ELECTRICAL CONNECTORS

NOTE: 1

ALTERNATIVE SOLUTION N_MM_273400_4_BJM0_01_02

Figure 27-34-00-991-00400-00-B / SHEET 1/1 - Elevator Servocontrols Position-Transducers ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-34-00-040-001-A - Elevator Servocontrol PositionTransducer - Connection of the Spare Transducer

3.

Job Set-up Subtask 27-34-00-860-068-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) On the overhead panel 23VU, release the FLT CTL/ELAC 1 and FLT CTL/SEC 1 pushbutton switches (on these pushbutton switches, the OFF legends come on). (3) On the overhead panel 24VU, release the FLT CTL/ELAC 2, FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches (on these pushbutton switches, the OFF legends come on). (4) Depressurize the aircraft hydraulic systems: (a) For the left elevator: · Depressurize the Green and Blue systems (Ref. AMM TASK 29-23-00-864-001) (Ref. AMM TASK 29-10-00-864-003) . (b) For the right elevator: · Depressurize the Yellow and Blue systems (Ref. AMM TASK 29-24-00-864-001) (Ref. AMM TASK 29-10-00-864-003) .

Subtask 27-34-00-010-055-A B.

Get Access (1) Put the ACCESS PLATFORM 6M (20 FT) - ADJUSTABLE in position: (a) In the zone 334 for the left elevator. (b) In the zone 344 for the right elevator. (2) Open the THS trailing edge access panels (Ref. AMM TASK 55-13-11-000-001) : (a) 334DB for the left elevator. (b) 344DB for the right elevator.

4.

Procedure (Ref. Fig. Elevator Servocontrols Position-Transducers SHEET 1) Subtask 27-34-00-210-054-A A.

Visual Inspection of the Servocontrol to Identify the Number of Transducer on the Servocontrol: (1) If the servocontrol has one transducer (RVDT simplex): (a) The procedure is not applicable. (2) If the servocontrol has two or three transducers (RVDT duplex or RVDT triplex), continue the procedure to do the connection of the spare transducer.

Subtask 27-34-00-040-050-B B.

Connection of the Spare Transducer: (1) If the servocontrol has two transducers: (a) Swap the connection of the electrical connectors (1) on the transducers (3). (2) If the servocontrol has three transducers: (a) Remove the electrical connector (1) from the defective transducer (3). (b) Remove the blanking cap (2) from the new transducer and put it on the defective transducer. (c) Connect the electrical connector (1) to the new transducer.

Subtask 27-34-00-710-052-A C.

Test

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-34-00-040-001-A - Elevator Servocontrol PositionTransducer - Connection of the Spare Transducer

(1) On the overhead panel 23VU, push the FLT CTL/ELAC 1 and FLT CTL/SEC 1 pushbutton switches (on these pushbutton switches, the OFF legends go off). (2) On the overhead panel 24VU, push the FLT CTL/ELAC 2, FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches (on these pushbutton switches, the OFF legends go off). (3) Do the operational test of the elevators (Ref. AMM TASK 27-34-00-710-001) . 5.

Close-up Subtask 27-34-00-410-055-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the THS trailing edge access panels (Ref. AMM TASK 55-13-11-400-001) : (a) 334DB for the left elevator. (b) 344DB for the right elevator. (3) Remove the access platform(s).

Subtask 27-34-00-860-069-A B.

Put the aircraft back to its initial configuration. (1) Make an entry in the log-book. (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-51-00-040-001-A - Deactivation of the Slat and Flap Control Computer (SFCC) No. 2 Flap Channel

** ON A/C ALL TASK 27-51-00-040-001-A Deactivation of the Slat and Flap Control Computer (SFCC) No. 2 Flap Channel 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.

FIN : 21CV , 22CV Task Summary MMEL or CDL Ref MMEL 27-51-01A 1.

Access NO

Test NO

Specific Tools NO

Mhr 01.0

E/T 01.0

Nb Men 1

Reason for the Job MMEL 27-51-01A SFCC Flap Channel NOTE: For the deactivation of the SFCC No. 2 slat channel refer to TASK 27-51-00-040-005.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

QTY AR AR AR

DESIGNATION SAFETY BARRIER(S) SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 128

ZONE DESCRIPTION REAR AVIONIC COMPARTMENT

C. Referenced Information REFERENCE (Ref. 20-16-00-912-001-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02).

DESIGNATION Circuit Breakers Safety Practices Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-51-00-040-001-A - Deactivation of the Slat and Flap Control Computer (SFCC) No. 2 Flap Channel REFERENCE (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 27-50-00-869-006-A). (Ref. 27-51-00-710-001-A). (Ref. 27-54-00-710-001-A). (Ref. 27-54-00-710-002-A). (Ref. 31-32-00-860-001-A). Ref. ESPM 20-10-00 3.

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Reset of the Wing Tip Brake (WTB) of the Flap System on the Ground Operational Test of the Wing Tip Brake and the Pressure Off Brake Operational Test of the Flap System Operational Test of the Flap and Slat Systems Procedure to Get Access to the SYSTEM REPORT/TEST Menu Page

Job Set-up Subtask 27-51-00-941-070-A A.

Safety Precautions (1) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations. (2) Put a WARNING NOTICE(S) in position to tell persons not to operate the slats and flaps.

Subtask 27-51-00-861-056-A B.

Energize the Aircraft Electrical Circuits (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

Subtask 27-51-00-865-093-A C.

Table of the circuit breakers used in this procedure: PANEL 121VU

4.

DESIGNATION FLIGHT CONTROLS/WTB/FLP/SYS2

FIN 12CV

LOCATION P20

Procedure Subtask 27-51-00-040-051-B A.

Deactivation of the Slat and Flap Control Computer (SFCC) No 2 Flap Channel (1) When you do this procedure, it can be necessary to open circuit breaker 12CV (Ref. AMM TASK 2016-00-912-001) . (a) This circuit breaker has a red threaded bush. To open this circuit breaker you need a special tool Ref. ESPM 20-10-00. (2) Do this procedure: ACTION 1.On the MCDU: · get access to the Flight Controls (F/CTL) SYSTEM REPORT/TEST page (Ref. AMM TASK 31-32-00-860-001) . · push in the key adjacent to < SFCC 1. · push in the key adjacent to SYSTEM STATUS FLP >.

RESULT On the MCDU: · the F/CTL SYSTEM REPORT TEST PAGE is shown. · the SFCC 1 menu is shown. · < NO FAULTS > is shown except FLP 1 NO SFCC 2 DATA and/or FLP 1 NO SFCC 2 DATA CHECK WIRING AND SFCC 2.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-51-00-040-001-A - Deactivation of the Slat and Flap Control Computer (SFCC) No. 2 Flap Channel ACTION · push the key adjacent to < RETURN until the SYSTEM REPORT/TEST F/CTL page is shown. · push in the key adjacent to < SFCC 2.

RESULT · the SFCC 2 menu is shown.

NOTE: If the MCDU shows < NO RESPONSE > for SFCC 2, go to paragraph D. · push in the key adjacent to SYSTEM STATUS · the SYSTEM STATUS FLP page is shown. FLP >. · if FLP SYS LOCKED is shown, reset the wing tip brakes of the flap system with the SFCC 2 (Ref. AMM TASK 27-50-00-869-006) . · if the reset of the wing tip brakes (of the flap · the 28V power supply from SFCC 2 to the wing system) with the SFCC 2 cannot be completed tip brakes is disconnected. satisfactorily, open the circuit breaker 12CV (Ref. AMM TASK 20-16-00-912-001) . · push in the key adjacent to < RETURN until the F/CTL SYSTEM REPORT TEST page is shown. Subtask 27-51-00-865-050-A B.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU AUTO FLT/FAC1/26VAC 14CC1 B03 ** ON A/C 401-450 49VU AUTO FLT/FAC1/26VAC

14CC1

H09

** ON A/C ALL 121VU

14CC2

M18

AUTO FLT/FAC2/26VAC

Subtask 27-51-00-865-117-A C.

Table of the circuit breakers used in this procedure: PANEL 121VU

DESIGNATION FLIGHT CONTROLS/FLP/CTL AND/ MONG/SYS2

FIN 8CV

LOCATION Q21

Subtask 27-51-00-710-073-A D.

Test NOTE: This paragraph is applicable only if the MCDU shows < NO RESPONSE > for SFCC 2. (1) Do the Operational Test of the Flap System (Ref. AMM TASK 27-54-00-710-001) . (a) If the WTB is set due to failure of the Flap 2 channel, the message "FLAPS LEVER ....RECYCLE" will trigger on ECAM.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-51-00-040-001-A - Deactivation of the Slat and Flap Control Computer (SFCC) No. 2 Flap Channel

(2) If the message to recycle the Flap control lever shows on ECAM, open the circuit breaker 12CV (Ref. AMM TASK 20-16-00-912-001) . NOTE: WTB stays open. Subtask 27-51-00-040-055-A E.

Deactivation of the SFCC No. 2 Flap Channel (Continued) (1) Do the Operational Test of the Flap and Slat Systems (Ref. AMM TASK 27-54-00-710-002) . NOTE: The circuit breaker 12CV stays open (if the c/b 12CV was opened before). (2) Do the WTB/POB test with SFCC No. 1 (flap system) only (Ref. AMM TASK 27-51-00-710-001) . NOTE: The circuit breaker 12CV stays open (if the c/b 12CV was opened before). (3) Make sure that the WTB/POB test was successful and that the MCDU shows: SFCC 1 DATE: XXX XX__ UTC: XXXX PERFORMED NO FAULTS RESULT NOT STORED. NOTE: The aircraft can only dispatched if the WTB/POB test was successful. (4) Put the aircraft back to its initial configuration. (a) On the MCDU, push the key adjacent to < RETURN until the CFDS MENU page is shown. (b) On the MCDU, push the MCDU MENU key and make sure that the MCDU MAIN MENU is shown. (5) Deactivation of the SFCC 2 flap channel: (a) Open and safety circuit breaker 8CV. (b) Attach a WARNING NOTICE(S) to the circuit breaker 8CV (in the cockpit) to tell persons that the flap channel for SFCC 2 is deactivated. (6) If circuit breaker 12CV was opened in the test procedure: · attach a WARNING NOTICE(S) to the circuit breaker 12CV (in the cockpit) to tell persons that the 28V power supply (from SFCC 2 to the WTB) is disconnected (Ref. AMM TASK 20-16-00-912001) .

Subtask 27-51-00-869-064-A F.

Cockpit Effects (1) On the ECAM EWD: · The message 'F/CTL FLAP SYS 2 FAULT' shows. (2) On the STATUS SD page: · The message 'F/CTL MAINTENANCE' can show. · The message 'SFCS MAINTENANCE' can show. NOTE: These status messages will only show in flight phases 1 and 10. (3) On the STATUS SD page: · The message 'ENG 2 APPR IDLE ONLY' shows. · The message 'FLAPS SLOW' shows.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-51-00-040-001-A - Deactivation of the Slat and Flap Control Computer (SFCC) No. 2 Flap Channel

NOTE: These status messages will not show in flight phases 1 and 10. (4) Make an entry in the aircraft technical logbook that the SFCC 2 flap channel is deactivated. 5.

Close-up Subtask 27-51-00-862-057-A A.

De-energize the Aircraft Electrical Circuits (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Subtask 27-51-00-865-104-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 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU AUTO FLT/FAC1/26VAC 14CC1 B03 ** ON A/C 401-450 49VU AUTO FLT/FAC1/26VAC

14CC1

H09

** ON A/C ALL 121VU

14CC2

M18

AUTO FLT/FAC2/26VAC

Subtask 27-51-00-942-069-A C.

Removal of Equipment (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the safety barriers. (3) Remove the WARNING NOTICE(S). (4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-51-00-040-004-A - Flap WTB Solenoid - WTB Test Procedure

** ON A/C ALL TASK 27-51-00-040-004-A Flap WTB Solenoid - WTB Test Procedure 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.

FIN : 21CV Task Summary MMEL or CDL Ref MMEL 27-51-02A

Access NO

1.

Reason for the Job MMEL 27-51-02A Flap Wing Tip Brakes Solenoid

2

Job Set-up Information A.

Specific Tools NO

Mhr 01.0

E/T 01.0

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

Test NO

QTY AR AR AR

DESIGNATION SAFETY BARRIER(S) SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 128

ZONE DESCRIPTION REAR AVIONIC COMPARTMENT

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 27-51-00-710-001-A). 3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) Operational Test of the Wing Tip Brake and the Pressure Off Brake

Job Set-up Subtask 27-51-00-941-065-A

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-51-00-040-004-A - Flap WTB Solenoid - WTB Test Procedure

A.

Safety Precautions (1) Put the SAFETY BARRIER(S) in position. (2) Put a WARNING NOTICE(S) in the cockpit to tell persons not to operate the flap system.

Subtask 27-51-00-860-076-A B.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) In the procedure that follows it is necessary to do the WTB/POB test with SFCC 1 (Ref. AMM TASK 27-51-00-710-001) . Prepare to pressurize the hydraulic systems.

Subtask 27-51-00-865-090-A C.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU AUTO FLT/FAC1/26VAC 14CC1 B03 ** ON A/C 401-450 49VU AUTO FLT/FAC1/26VAC

14CC1

H09

** ON A/C ALL 121VU 121VU

14CC2 8CV

M18 Q21

7CV

R21

121VU 4.

AUTO FLT/FAC2/26VAC FLIGHT CONTROLS/FLP/CTL AND/ MONG/SYS2 FLIGHT CONTROLS/SLT/CTL/SYS2

Procedure Subtask 27-51-00-040-054-A A.

Flap WTB Solenoid - WTB Test Procedure (1) Do the WTB/POB test with SFCC No. 1 (flap system) (Ref. AMM TASK 27-51-00-710-001) . (2) Make sure that the WTB/POB test was successful and that the MCDU shows: SFCC 1 DATE: XXX XX__ UTC: XXXX PERFORMED NO FAULTS RESULT NOT STORED NOTE: The aircraft can only dispatched if the WTB/POB test was successful. (3) Put the aircraft back to its initial configuration: (a) On the MCDU, push the key adjacent to < RETURN until the CFDS MENU page is shown. (b) On the MCDU, push the MCDU MENU key and make sure that the MCDU MAIN MENU is shown.

5.

Close-up Subtask 27-51-00-865-102-A A.

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

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-51-00-040-004-A - Flap WTB Solenoid - WTB Test Procedure

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU AUTO FLT/FAC1/26VAC 14CC1 B03 ** ON A/C 401-450 49VU AUTO FLT/FAC1/26VAC

14CC1

H09

** ON A/C ALL 121VU 121VU

14CC2 8CV

M18 Q21

7CV

R21

121VU

AUTO FLT/FAC2/26VAC FLIGHT CONTROLS/FLP/CTL AND/ MONG/SYS2 FLIGHT CONTROLS/SLT/CTL/SYS2

Subtask 27-51-00-942-060-A B.

Removal of Equipment (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the safety barriers. (3) Remove the WARNING NOTICE(S). (4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-93-00-040-002-A - Deactivation of the Stabilizer Actuator Electrical Motor n°2

** ON A/C ALL TASK 27-93-00-040-002-A Deactivation of the Stabilizer Actuator Electrical Motor n°2 1.

Reason for the Job MMEL 27-40-02A Stabilizer Actuator Electrical Motor (FAA only)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 210 822

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 29-23-00-863-001-A). (Ref. 29-23-00-864-001-A). (Ref. 29-24-00-863-001-A). (Ref. 29-24-00-864-001-A). 3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump Depressurize the Green and Yellow Hydraulic Systems after Operation of the PTU Pressurize the Yellow Hydraulic System with the Electric Pump Depressurize the Yellow Hydraulic System

Job Set-up Subtask 27-93-00-861-055-A A.

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

Subtask 27-93-00-010-052-A B.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 822. (2) Open the access door 822.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-93-00-040-002-A - Deactivation of the Stabilizer Actuator Electrical Motor n°2

(3) On the battery power center 105VU: · loosen the two screws and remove the protective cover. Subtask 27-93-00-865-056-A C.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 49VU

DESIGNATION L/G/LGCIU/SYS1/NORM NAV PROBES/ADIRU 1/AND AOA 1/ 26VAC NAV PROBES/ADIRU1/115VAC

FIN 1GA 5FP1

C09 F07

LOCATION

4FP1

F06

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU FLIGHT CONTROLS/ELAC1/NORM/ 15CE1 B11 SPLY 49VU FLIGHT CONTROLS/FCDC1/SPLY 20CE1 B10 49VU FLIGHT CONTROLS/THS/ACTR/MOT2 19CE2 B09 49VU FLIGHT CONTROLS/SEC1/NORM/SPLY 21CE1 B08 49VU FLIGHT CONTROLS/FLP/CTL AND 6CV B07 MONG/SYS1 49VU FLIGHT CONTROLS/SLT/CTL AND 5CV B06 MONG/SYS1 49VU AUTO FLT/FAC1/28VDC 5CC1 B04 49VU AUTO FLT/FAC1/26VAC 14CC1 B03 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP

F09

** ON A/C 301-349, 351-450, 500-600 49VU NAV PROBES/ADIRU3/PWR/SWTG

8FP

F08

15CE1

B06

20CE1 19CE2 21CE1 6CV

B05 B04 B03 B02

5CV

B01

5CC1 14CC1

H10 H09

FLIGHT CONTROLS/ELAC2/STBY SPLY 16CE2 FLT CTL/ELAC1/STBY SPLY 16CE1 FLT CTL/SEC1/STBY SPLY 22CE ADIRS/ADIRU1/28VDC 6FP1 ELEC/HOT BUS/702PP SPLY 5PB2 ELEC/HOT BUS/701PP SPLY 5PB1 ELEC/HOT BUS/702PP SPLY 12PB2

A02 A01 B01 C02 D02 D01 E02

** ON A/C 401-450 49VU FLIGHT CONTROLS/ELAC1/NORM/ SPLY 49VU FLIGHT CONTROLS/FCDC1/SPLY 49VU FLIGHT CONTROLS/THS/ACTR/MOT2 49VU FLIGHT CONTROLS/SEC1/NORM/SPLY 49VU FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 49VU FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 49VU AUTO FLT/FAC1/28VDC 49VU AUTO FLT/FAC1/26VAC ** ON A/C ALL 105VU 105VU 105VU 105VU 105VU 105VU 105VU

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-93-00-040-002-A - Deactivation of the Stabilizer Actuator Electrical Motor n°2

PANEL 105VU 121VU 121VU 121VU 121VU

DESIGNATION ELEC/HOT BUS/701PP SPLY COM NAV/RAD ALTM/2 COM NAV/RAD ALTM/1 AUTO FLT/FAC2/28VDC AUTO FLT/FAC2/26VAC

FIN 12PB1 1SA2 1SA1 5CC2 14CC2

E01 K12 K11 M19 M18

LOCATION

EMB SB 23-1485 for A/C 210-210 121VU ADIRS/ADIRU/3PWR/SWTG 121VU ADIRS/ADIRU/2/26VAC AND AOA 121VU ADIRS/ADIRU/3/26VAC AND AOA 121VU ADIRS/ADIRU/2/115VAC 121VU ADIRS/ADIRU/3/115VAC 121VU ADIRS/ADIRU/2/28VDC 121VU ADIRS/ADIRU/3/28VDC

9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N09 N08 N07 N06 N05 N04 N03

** ON A/C ALL 121VU 121VU 121VU 121VU 121VU

12CV 11CV 2GA 52GA 8CV

P20 P19 Q35 Q34 Q21

21CE3 21CE2 19CE3 19CE1 7CV 15CE2

Q19 Q18 Q17 Q16 R21 R20

** ON A/C ALL

121VU 121VU 121VU 121VU 121VU 121VU

FLIGHT CONTROLS/WTB/FLP/SYS2 FLIGHT CONTROLS/WTB/SLT/SYS2 HYDRAULIC/LGCIU/SYS2 HYDRAULIC/LGCIU/SYS1/GRND SPLY FLIGHT CONTROLS/FLP/CTL AND/ MONG/SYS2 FLIGHT CONTROLS/SEC3/SPLY FLIGHT CONTROLS/SEC2/SPLY FLIGHT CONTROLS/THS ACTR/MOT3 FLIGHT CONTROLS/THS ACTR/MOT1 FLIGHT CONTROLS/SLT/CTL/SYS2 FLIGHT CONTROLS/ELAC2/NORM/ SPLY

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-325, 331-332, 350-350

4.

EMB SB 23-1485 for A/C 210-210 121VU ADIRS/ADIRU/2PWR/SHED

10FP

N10

** ON A/C 326-330, 333-349, 351-450, 500-600 121VU ADIRS/2PWR/SHED &/AOA2 MON

10FP

N10

** ON A/C ALL 122VU 122VU

10CV 9CV

S07 S06

FLIGHT CONTROLS/WTB/FLP/SYS1 FLIGHT CONTROLS/WTB/SLT/SYS1

Procedure Subtask 27-93-00-040-052-A A.

If the ELAC 1 FAULT warning is in view on the upper ECAM display unit: (1) On the overhead panel 23VU, make sure that: · the FAULT legend of the FLT CTL/ELAC 1 pushbutton switch is on.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-93-00-040-002-A - Deactivation of the Stabilizer Actuator Electrical Motor n°2

(2) On the overhead panel 23VU, release the FLT CTL/ELAC 1 pushbutton switch (on this pushbutton switch, the OFF legend comes on). (3) On the overhead panel 24VU, make sure that: · the FLT CTL/ELAC 2 pushbutton switch is pushed (on this pushbutton switch, the OFF and FAULT legends are off). (4) Do the test paragraph C. only. Subtask 27-93-00-040-053-A B.

If the ELAC 1 PITCH FAULT warning is in view on the upper ECAM display unit: (1) Do the tests paragraphs C. and D.

Subtask 27-93-00-710-054-C C.

For the ELAC 1 FAULT or ELAC 1 PITCH FAULT warning: (1) Do this test: ACTION RESULT 1.On the center pedestal, on one MCDU, push The MCDU shows the MDCU MENU page. the MCDU MENU mode key. 2.Push the line key adjacent to the CFDS indica- The MCDU shows the CFDS MENU page. tion. 3.Push the line key adjacent to the SYSTEM RE- The MCDU shows the SYSTEM REPORT/TEST PORT/TEST indication. page. 4.Push the line key adjacent to the F/CTL indica- The MCDU shows the F/CTL page. tion. 5.Push the line key adjacent to the EFCS1 indica- The MCDU shows the EFCS1 page. tion. 6.Push the line key adjacent to the GROUND The MCDU shows the EFCS1 GROUND SCAN SCAN indication. page. 7.Push the line key adjacent to the START GROUND SCAN indication. 8.After two minutes, push the line key adjacent to the GROUND SCAN STOP indication. 9.Push the line key adjacent to the GROUND RE- Make sure that none of the following CFDS fault PORT indication. messages are present: · CFDS fault messages concerning accelerometers 3 (12CE3) and 4 (12CE4) and sidestick: ELAC2 MON OR WIRING FROM ACCLRM3 12CE3, ELAC2 COM OR WIRING FROM ACCLRM3 12CE3, ACCLRM3 12CE3, SEC2 OR WIRING FROM ACCLRM3 12CE3, ELAC2 MON OR WIRING FROM ACCLRM4 12CE4, ELAC2 COM OR WIRING FROM ACCLRM4 12CE4, ACCLRM4 12CE4, SEC2 OR WIRING FROM ACCLRM4 12CE4, ELAC2 OR INPUT OF CAPT ROLL CTL SSTU 4CE1, ELAC2 OR INPUT OF F/O ROLL CTL SSTU 4CE2,

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-93-00-040-002-A - Deactivation of the Stabilizer Actuator Electrical Motor n°2

ACTION

10.On the MCDU, push the line select key adjacent to the RETURN indication until the CFDS menu page comes into view.

RESULT ELAC2 OR INPUT OF CAPT PITCH CTL SSTU 4CE3, ELAC2 OR INPUT OF F/O PITCH CTL SSTU 4CE4, SEC1(2)(3) OR INPUT OF CAPT ROLL CTL SSTU 4CE1, SEC1(2)(3) OR INPUT OF F/O ROLL CTL SSTU 4CE2, SEC1(2) OR INPUT OF CAPT PITCH CTL SSTU 4CE3, SEC1(2) OR INPUT OF F/O PITCH CTL SSTU 4CE4, CAPT ROLL CTL SSTU 4CE1, F/O ROLL CTL SSTU 4CE2, CAPT PITCH CTL SSTU 4CE3, F/O PITCH CTL SSTU 4CE4. · CFDS fault messages concerning SEC1 or SEC2 pitch changeover logic or to SEC2 pitch control failure: CHECK PITCH CHANGE OVER OF SEC1, CHECK PITCH CHANGE OVER OF SEC2, SEC2 OR WIRING FROM L G ELEV POS XCDR 34CE1, SEC2 OR WIRING FROM R Y ELEV POS XCDR 34CE2, SEC2 OR WIRING FROM L ELEV POS MON XCDR, SEC2 OR WIRING FROM R ELEV POS MON XCDR, SEC2 COM OR WIRING TO L G ELEV SERVO VLV 34CE1, SEC2 COM OR WIRING TO R Y ELEV SERVO VLV 34CE2, SEC2 MON OR WIRING TO L G ELEV SERVO VLV 34CE1, SEC2 MON OR WIRING TO R Y ELEV SERVO VLV 34CE2, SEC2 OR WIRING FROM L B ELEV MODE XCDR 34CE3, SEC2 OR WIRING FROM R B ELEV MODE XCDR 34CE4, SEC2 MON OR WIRING TO L B ELEV SOL VLV 34CE3, SEC2 MON OR WIRING TO R B ELEV SOL VLV 34CE4. The MCDU shows the MCDU MENU page.

Subtask 27-93-00-710-055-A D.

For the ELAC 1 PITCH FAULT warning:

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-93-00-040-002-A - Deactivation of the Stabilizer Actuator Electrical Motor n°2

(1) Do this test: ACTION RESULT 1.On the overhead panel 23VU: On the overhead panel 23VU: · release the FLT CTL/SEC 1 pushbutton switch. · the OFF legend of the FLT CTL/SEC 1 pushbutton switch comes on. 2.On the overhead panel 24VU: On the overhead panel 24VU: · release the FLT CTL/SEC 2 pushbutton switch · the OFF legend of the FLT CTL/SEC 2 pushbut· release the FLT CTL/ELAC 2 pushbutton ton switch comes on. switch. · the OFF legend of the FLT CTL/ELAC 2 pushbutton switch comes on. 3.Pressurize the Green and Yellow hydraulic systems (Ref. AMM TASK 29-23-00-863-001) (Ref. AMM TASK 29-24-00-863-001) . 4.On the panel 114VU: · make sure that the FLAPS control lever is in the 0 position. 5.On the center pedestal: The THS moves out of the neutral position. · move the THS with the pitch-trim control wheels out of the neutral position. 6.On the overhead panel 24VU: On the overhead panel 24VU: · push the FLT CTL/SEC 2 pushbutton switch. · the OFF legend of the FLT CTL/SEC 2 pushbutton switch goes off. The THS must return to the neutral position (electric motor 3 in operation). 5.

Close-up Subtask 27-93-00-860-059-A A.

Put the aircraft back to its initial configuration. (1) For the ELAC 1 FAULT warning : (a) Put a WARNING NOTICE(S) on the FLT CTL/ELAC 1 pushbutton switch, to tell the crew that the ELAC 1 is deactivated. (b) Open the circuit breakers 15CE1 and 16CE1. (c) Make an entry in the log-book. (2) For the ELAC 1 PITCH FAULT warning : (a) On the overhead panel 23VU, push the FLT CTL/SEC 1 pushbutton switch (on this pushbutton switch, the OFF legend goes off). (b) On the overhead panel 24VU, push the FLT CTL/ELAC 2 pushbutton switch (on this pushbutton switch, the OFF legend goes off). (c) Depressurize the Green and Yellow hydraulic systems (Ref. AMM TASK 29-23-00-864-001) (Ref. AMM TASK 29-24-00-864-001) .

Subtask 27-93-00-862-055-A B.

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

Subtask 27-93-00-410-052-A C.

Close Access (1) Install the protective cover on the battery power center 105VU.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-93-00-040-002-A - Deactivation of the Stabilizer Actuator Electrical Motor n°2

(2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform(s).

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

** ON A/C ALL TASK 27-64-00-040-001-A Deactivation of the Spoiler Servo Control 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:

DO NOT DO THIS DEACTIVATION PROCEDURE IF THERE IS EXTERNAL LEAKAGE ON THE UNSERVICEABLE SERVOCONTROL.

WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

FIN : 31CE1 , 31CE2 , 31CE3 , 31CE4 , 31CE5 , 31CE6 , 31CE7 , 31CE8 , 31CE9 , 31CE10 Task Summary MMEL or CDL Ref MMEL 27-64-01A MMEL 27-64-02A MMEL 27-64-03A MMEL 27-64-04A MMEL 27-64-05A 1.

Reason for the Job MMEL 27-64-01A Spoiler 5 MMEL 27-64-02A Spoiler 1 or 3 MMEL 27-64-03A Spoiler 2 or 4 MMEL 27-64-04A Spoilers 1 and 2 MMEL 27-64-05A Spoilers 3 and 4

2

Job Set-up Information A.

Access YES YES YES YES YES

Test YES YES YES YES YES

Specific Tools YES YES YES YES YES

Mhr 01.0 01.0 01.0 01.0 01.0

E/T 00.8 00.8 00.8 00.8 00.8

Nb Men 2 2 2 2 2

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

QTY AR AR AR

DESIGNATION ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE CAP - BLANKING TIE WRAP

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

REFERENCE No specific No specific (98D27603002000) OR (98D27603002001) (98D27803000000) (98D27903500000) B.

QTY AR AR 1 1 1 2

DESIGNATION TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC WARNING NOTICE(S) KEY-SPOILER MAINTENANCE OR KEY-SPOILER MAINTENANCE LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION PIN-SIDE STICK LOCKING

Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTION 580 LEFT WING FLAPS AND SPOILERS 680 RIGHT WING FLAPS AND SPOILERS FOR 31CE1 (SERVO CTL-SPLR1, L G) 573BB FOR 31CE10 (SERVO CTL-SPLR5, R G) 675GB FOR 31CE2 (SERVO CTL-SPLR1, R G) 673BB FOR 31CE3 (SERVO CTL-SPLR2, L Y) 575BB FOR 31CE4 (SERVO CTL-SPLR2, R Y) 675BB FOR 31CE5 (SERVO CTL-SPLR3, L B) 575DB FOR 31CE6 (SERVO CTL-SPLR3, R B) 675DB FOR 31CE7 (SERVO CTL-SPLR4, L Y) 575EB FOR 31CE8 (SERVO CTL-SPLR4, R Y) 675EB FOR 31CE9 (SERVO CTL-SPLR5, L G) 575GB

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 27-50-00-866-008-A). (Ref. 27-50-00-866-008-A-01). (Ref. 27-50-00-866-009-A). (Ref. 27-50-00-866-009-A-01).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Extension of the Flaps on the Ground Extension of the Flaps/Slats on the Ground Retraction of the Flaps on the Ground Retraction of the Flaps/Slats on the Ground

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

REFERENCE (Ref. 27-64-00-710-001-A). (Ref. 29-10-00-863-003-A).

DESIGNATION Operational Test of the Spoiler Hydraulic Actuation Pressurize the Blue Hydraulic System with a Hydraulic Ground PowerCart (Ref. 29-10-00-863-003-A-01). Pressurize the Blue Hydraulic System with the Blue Electric Pump (Ref. 29-10-00-864-003-A). Depressurize the Blue Hydraulic System (Ref. 29-23-00-863-001-A). Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump (Ref. 29-23-00-864-001-A). Depressurize the Green and Yellow Hydraulic Systems after Operation of the PTU (Ref. 29-24-00-863-001-A). Pressurize the Yellow Hydraulic System with the Electric Pump (Ref. 29-24-00-864-001-A). Depressurize the Yellow Hydraulic System Deactivation and Reactivation of the Servocontrol SHEET 1 FOR 31CE1 (SERVO CTL-SPLR1, L G) (Ref. 57-51-37-000-002-A). Removal of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) (Ref. 57-51-37-400-002-A). Installation of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) FOR 31CE10 (SERVO CTL-SPLR5, R G) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE2 (SERVO CTL-SPLR1, R G) (Ref. 57-51-37-000-002-A). Removal of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) (Ref. 57-51-37-400-002-A). Installation of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) FOR 31CE3 (SERVO CTL-SPLR2, L Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE4 (SERVO CTL-SPLR2, R Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE5 (SERVO CTL-SPLR3, L B) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE6 (SERVO CTL-SPLR3, R B) Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

REFERENCE (Ref. 57-51-37-000-004-A).

DESIGNATION Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE7 (SERVO CTL-SPLR4, L Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE8 (SERVO CTL-SPLR4, R Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE9 (SERVO CTL-SPLR5, L G) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

575GB 573BB

575DB

Z580

A

A A A

A

A

A

575EB

575BB

Z680 673BB

A

675BB 675DB 675EB 675GB

A

A 2 1

B

B

B 3

M O

MAINTENANCE DEVICE POST GOODRICH VSB 31077-27-15

MAINTENANCE DEVICE PRE GOODRICH VSB 31077-27-15 N_MM_276400_4_AAC0_01_02 N_MM_276400_4_AAD0_01_01

Figure 27-64-00-991-00700-00-C / SHEET 1/1 - Deactivation and Reactivation of the Servocontrol ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

3.

Job Set-up (Ref. Fig. Deactivation and Reactivation of the Servocontrol SHEET 1) Subtask 27-64-00-860-057-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Extend the flaps (Ref. AMM TASK 27-50-00-866-008) . (3) On the overhead panel 23VU : · Release the FLT CTL/SEC 1 pushbutton switch (on this pushbutton switch, the OFF legend comes on). (4) On the overhead panel 24VU : · Release the FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches (on these pushbutton switches, the OFF legends come on). (5) On the panel 114VU, put the LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION (98D27803000000) in position on the flap and slat control lever. (6) Put the PIN-SIDE STICK LOCKING (98D27903500000) in position on each side-stick controller. (7) Put the WARNING NOTICE(S) on the CAPT and F/O side sticks to tell persons not to touch the side sticks. (8) Depressurize the hydraulic system related to the spoiler that you must deactivate. (a) For the spoiler 1 or 5, depressurize the Green hydraulic system (Ref. AMM TASK 29-23-00-864001) . (b) For the spoiler 2 or 4, depressurize the Yellow hydraulic system (Ref. AMM TASK 29-24-00-864001) . (c) For the spoiler 3, depressurize the Blue hydraulic system (Ref. AMM TASK 29-10-00-864-003) . (9) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position in : (a) Zone 580 for the left spoilers. (b) Zone 680 for the right spoilers. (10) Open the applicable access panels: (a) FOR 31CE1 (SERVO CTL-SPLR1, L G) · The access panel 573BB (Ref. AMM TASK 57-51-37-000-002) . (b) FOR 31CE2 (SERVO CTL-SPLR1, R G) · The access panel 673BB (Ref. AMM TASK 57-51-37-000-002) . (c) FOR 31CE3 (SERVO CTL-SPLR2, L Y) · The access panel 575BB (Ref. AMM TASK 57-51-37-000-004) . (d) FOR 31CE4 (SERVO CTL-SPLR2, R Y) · The access panel 675BB (Ref. AMM TASK 57-51-37-000-004) . (e) FOR 31CE5 (SERVO CTL-SPLR3, L B) · The access panel 575DB (Ref. AMM TASK 57-51-37-000-004) . (f)

FOR 31CE6 (SERVO CTL-SPLR3, R B) · The access panel 675DB (Ref. AMM TASK 57-51-37-000-004) .

(g) FOR 31CE7 (SERVO CTL-SPLR4, L Y) · The access panel 575EB (Ref. AMM TASK 57-51-37-000-004) . (h) FOR 31CE8 (SERVO CTL-SPLR4, R Y) · The access panel 675EB (Ref. AMM TASK 57-51-37-000-004) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

(i)

FOR 31CE9 (SERVO CTL-SPLR5, L G) · The access panel 575GB (Ref. AMM TASK 57-51-37-000-004) .

(j)

FOR 31CE10 (SERVO CTL-SPLR5, R G) · The access panel 675GB (Ref. AMM TASK 57-51-37-000-004) .

(11) Before you de-activate a servocontrol, make sure that it has no external leaks. 4.

Procedure (Ref. Fig. Deactivation and Reactivation of the Servocontrol SHEET 1) Subtask 27-64-00-040-052-B A.

Deactivation of the Spoiler Servocontrol NOTE: When you deactivate a spoiler servocontrol, it is not necessary to deactivate the symmetrical spoiler on the other wing. (This spoiler is inhibited automatically by the SEC). (1) If there is no plate with the 'O' and 'M' indications on the maintenance device (PRE GOODRICH VSB 31077-27-15): CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE. IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL. (a) Install the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) on the servocontrol and turn it a quarter turn counterclockwise. The servocontrol is in maintenance position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key.

(b) Disconnect the electrical connector (2) from the receptacle (1) of the servocontrol. (c) Put CAP - BLANKING on the electrical connector (2) and receptacle (1). (d) Attach the electrical connector (2) to a hydraulic line with a TIE WRAP. (e) Make sure that the spoiler is in the fully retracted position. CAUTION: MAKE SURE THAT NO SPOILER MAINTENANCE KEY STAYS ENGAGED IN THE MAINTENANCE DEVICE HOUSING. AERODYNAMIC FORCES WILL CAUSE UNWANTED MOVEMENT OF THE SPOILER IF THE MAINTENANCE KEY STAYS IN ITS HOUSING. CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL. (f)

Turn the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) a quarter turn clockwise and remove it. The servocontrol is in operational position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key. NOTE: The defective servocontrol must stay hydraulically connected to the aircraft hydraulic system.

(g) Make sure that the work area is clean and clear of tools and other items. CAUTION: MAKE SURE THAT NO SPOILER MAINTENANCE KEY STAYS ENGAGED IN THE MAINTENANCE DEVICE HOUSING. AERODYNAMIC FORCES WILL CAUSE UNWANTED MOVEMENT OF THE SPOILER IF THE MAINTENANCE KEY STAYS IN ITS HOUSING. (h) Gradually apply a manual force to the spoiler surface trailing-edge and make sure that you cannot extend the spoiler. NOTE: If you can extend the spoiler manually with the servocontrol in the operational position: - It is necessary to replace the spoiler servocontrol. (i)

On the overhead panel 23VU: · Push the FLT CTL/SEC 1 pushbutton switch (on this pushbutton switch, the OFF legend goes off).

(j)

On the overhead panel 24VU: · Push the FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches (on these pushbutton switches, the OFF legends go off).

(k) On the ECAM control panel on the center pedestal, push the F/CTL key. On the ECAM lower display unit, the F/CTL page comes into view. (l)

Pressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-863-001) (Ref. AMM TASK 29-24-00-863-001) (Ref. AMM TASK 29-10-00-863-003) .

(2) If there is a plate with the 'O' and 'M' indications on the maintenance device (POST GOODRICH VSB 31077-27-15): CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE. IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

(a) Install the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) on the servocontrol and turn it a quarter turn counterclockwise to the 'M' position (Maintenance). The servocontrol is in maintenance position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key.

(b) Disconnect the electrical connector (2) from the receptacle (1) of the servocontrol. (c) Put CAP - BLANKING on the electrical connector (2) and receptacle (1). (d) Attach the electrical connector (2) to a hydraulic line with a TIE WRAP. (e) Make sure that the spoiler is in the fully retracted position. CAUTION: MAKE SURE THAT THE STOP OF THE HEXAGONAL-HEAD CONTROL SWITCH IS AGAINST THE LETTER 'O' ON THE HOUSING. IF IT IS AGAINST THE LETTER 'M', AERODYNAMIC FORCES WILL CAUSE UNWANTED MOVEMENT OF THE SPOILER AND POSSIBLE DAMAGE TO EQUIPMENT. CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE. IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL. (f)

Turn the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) a quarter turn clockwise to the 'O' position (Operation) and remove it. The servocontrol is in operational position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key. NOTE: The defective servocontrol must stay hydraulically connected to the aircraft hydraulic system.

(g) Make sure that the work area is clean and clear of tools and other items. CAUTION: MAKE SURE THAT NO SPOILER MAINTENANCE KEY STAYS ENGAGED IN THE MAINTENANCE DEVICE HOUSING. AERODYNAMIC FORCES WILL CAUSE UN-

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

WANTED MOVEMENT OF THE SPOILER IF THE MAINTENANCE KEY STAYS IN ITS HOUSING. (h) Gradually apply a manual force to the spoiler surface trailing-edge and make sure that you cannot extend the spoiler. NOTE: If you can extend the spoiler manually with the servocontrol in the operational position: - It is necessary to replace the spoiler servocontrol. (i)

On the overhead panel 23VU: · Push the FLT CTL/SEC 1 pushbutton switch (on this pushbutton switch, the OFF legend goes off).

(j)

On the overhead panel 24VU: · Push the FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches (on these pushbutton switches, the OFF legends go off).

(k) On the ECAM control panel on the center pedestal, push the F/CTL key. On the ECAM lower display-unit, the F/CTL page comes into view. (l)

Pressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-863-001) (Ref. AMM TASK 29-24-00-863-001) (Ref. AMM TASK 29-10-00-863-003) .

Subtask 27-64-00-710-054-A B.

Test of the Spoiler (1) During the operational test that follows: (a) Do a visual check from the ground: · Make sure that the spoiler with the deactivated servocontrol and its symmetrical on the other wing do not extend when they are operated. · Make sure that the spoilers are in the fully retracted position. (b) In the cockpit, on the System Display: · Make sure that the spoiler with the deactivated servocontrol stays amber with its symmetrical on the other wing. · Make sure that the amber F/CTL SPOILER FAULT message is shown on the EWD. (2) Do the operational test of the spoilers (Ref. AMM TASK 27-64-00-710-001) .

5.

Close-up Subtask 27-64-00-860-056-A A.

Put the aircraft back to its initial configuration. (1) On the panel 114VU, remove the LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION (98D27803000000) from the flap and slat control lever. (2) Retract the flaps (Ref. AMM TASK 27-50-00-866-009) . (3) Depressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-864-001) (Ref. AMM TASK 29-24-00-864-001) (Ref. AMM TASK 29-10-00-864-003) . (4) Remove the PIN-SIDE STICK LOCKING (98D27903500000) and the warning notice from each sidestick controller. (5) Close the applicable access panels: (a) FOR 31CE1 (SERVO CTL-SPLR1, L G) · The access panel 573BB (Ref. AMM TASK 57-51-37-400-002) . (b) FOR 31CE2 (SERVO CTL-SPLR1, R G) · The access panel 673BB (Ref. AMM TASK 57-51-37-400-002) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

(c) FOR 31CE3 (SERVO CTL-SPLR2, L Y) · The access panel 575BB (Ref. AMM TASK 57-51-37-400-004) . (d) FOR 31CE4 (SERVO CTL-SPLR2, R Y) · The access panel 675BB (Ref. AMM TASK 57-51-37-400-004) . (e) FOR 31CE5 (SERVO CTL-SPLR3, L B) · The access panel 575DB (Ref. AMM TASK 57-51-37-400-004) . (f)

FOR 31CE6 (SERVO CTL-SPLR3, R B) · The access panel 675DB (Ref. AMM TASK 57-51-37-400-004) .

(g) FOR 31CE7 (SERVO CTL-SPLR4, L Y) · The access panel 575EB (Ref. AMM TASK 57-51-37-400-004) . (h) FOR 31CE8 (SERVO CTL-SPLR4, R Y) · The access panel 675EB (Ref. AMM TASK 57-51-37-400-004) . (i)

FOR 31CE9 (SERVO CTL-SPLR5, L G) · The access panel 575GB (Ref. AMM TASK 57-51-37-400-004) .

(j)

FOR 31CE10 (SERVO CTL-SPLR5, R G) · The access panel 675GB (Ref. AMM TASK 57-51-37-400-004) .

(6) Remove access platform(s). (7) Make sure that the work area is clean and clear of tools and other items. (8) Make an entry in the log-book and record the defective servocontrol. (9) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

** ON A/C ALL TASK 27-64-00-040-001-A Deactivation of the Spoiler Servo Control 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:

DO NOT DO THIS DEACTIVATION PROCEDURE IF THERE IS EXTERNAL LEAKAGE ON THE UNSERVICEABLE SERVOCONTROL.

WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

FIN : 31CE1 , 31CE2 , 31CE3 , 31CE4 , 31CE5 , 31CE6 , 31CE7 , 31CE8 , 31CE9 , 31CE10 Task Summary MMEL or CDL Ref MMEL 27-64-01A MMEL 27-64-02A MMEL 27-64-03A MMEL 27-64-04A MMEL 27-64-05A 1.

Reason for the Job MMEL 27-64-01A Spoiler 5 MMEL 27-64-02A Spoiler 1 or 3 MMEL 27-64-03A Spoiler 2 or 4 MMEL 27-64-04A Spoilers 1 and 2 MMEL 27-64-05A Spoilers 3 and 4

2

Job Set-up Information A.

Access YES YES YES YES YES

Test YES YES YES YES YES

Specific Tools YES YES YES YES YES

Mhr 01.0 01.0 01.0 01.0 01.0

E/T 00.8 00.8 00.8 00.8 00.8

Nb Men 2 2 2 2 2

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

QTY AR AR AR

DESIGNATION ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE CAP - BLANKING TIE WRAP

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

REFERENCE No specific No specific (98D27603002000) OR (98D27603002001) (98D27803000000) (98D27903500000) B.

QTY AR AR 1 1 1 2

DESIGNATION TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC WARNING NOTICE(S) KEY-SPOILER MAINTENANCE OR KEY-SPOILER MAINTENANCE LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION PIN-SIDE STICK LOCKING

Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTION 580 LEFT WING FLAPS AND SPOILERS 680 RIGHT WING FLAPS AND SPOILERS FOR 31CE1 (SERVO CTL-SPLR1, L G) 573BB FOR 31CE10 (SERVO CTL-SPLR5, R G) 675GB FOR 31CE2 (SERVO CTL-SPLR1, R G) 673BB FOR 31CE3 (SERVO CTL-SPLR2, L Y) 575BB FOR 31CE4 (SERVO CTL-SPLR2, R Y) 675BB FOR 31CE5 (SERVO CTL-SPLR3, L B) 575DB FOR 31CE6 (SERVO CTL-SPLR3, R B) 675DB FOR 31CE7 (SERVO CTL-SPLR4, L Y) 575EB FOR 31CE8 (SERVO CTL-SPLR4, R Y) 675EB FOR 31CE9 (SERVO CTL-SPLR5, L G) 575GB

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 27-50-00-866-008-A). (Ref. 27-50-00-866-008-A-01). (Ref. 27-50-00-866-009-A). (Ref. 27-50-00-866-009-A-01).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Extension of the Flaps on the Ground Extension of the Flaps/Slats on the Ground Retraction of the Flaps on the Ground Retraction of the Flaps/Slats on the Ground

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

REFERENCE (Ref. 27-64-00-710-001-A). (Ref. 29-10-00-863-003-A).

DESIGNATION Operational Test of the Spoiler Hydraulic Actuation Pressurize the Blue Hydraulic System with a Hydraulic Ground PowerCart (Ref. 29-10-00-863-003-A-01). Pressurize the Blue Hydraulic System with the Blue Electric Pump (Ref. 29-10-00-864-003-A). Depressurize the Blue Hydraulic System (Ref. 29-23-00-863-001-A). Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump (Ref. 29-23-00-864-001-A). Depressurize the Green and Yellow Hydraulic Systems after Operation of the PTU (Ref. 29-24-00-863-001-A). Pressurize the Yellow Hydraulic System with the Electric Pump (Ref. 29-24-00-864-001-A). Depressurize the Yellow Hydraulic System Deactivation and Reactivation of the Servocontrol SHEET 1 FOR 31CE1 (SERVO CTL-SPLR1, L G) (Ref. 57-51-37-000-002-A). Removal of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) (Ref. 57-51-37-400-002-A). Installation of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) FOR 31CE10 (SERVO CTL-SPLR5, R G) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE2 (SERVO CTL-SPLR1, R G) (Ref. 57-51-37-000-002-A). Removal of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) (Ref. 57-51-37-400-002-A). Installation of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) FOR 31CE3 (SERVO CTL-SPLR2, L Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE4 (SERVO CTL-SPLR2, R Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE5 (SERVO CTL-SPLR3, L B) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE6 (SERVO CTL-SPLR3, R B) Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

REFERENCE (Ref. 57-51-37-000-004-A).

DESIGNATION Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE7 (SERVO CTL-SPLR4, L Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE8 (SERVO CTL-SPLR4, R Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE9 (SERVO CTL-SPLR5, L G) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

575GB 573BB

575DB

Z580

A

A A A

A

A

A

575EB

575BB

Z680 673BB

A

675BB 675DB 675EB 675GB

A

A 2 1

B

B

B 3

M O

MAINTENANCE DEVICE POST GOODRICH VSB 31077-27-15

MAINTENANCE DEVICE PRE GOODRICH VSB 31077-27-15 N_MM_276400_4_AAC0_01_02 N_MM_276400_4_AAD0_01_01

Figure 27-64-00-991-00700-00-C / SHEET 1/1 - Deactivation and Reactivation of the Servocontrol ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

3.

Job Set-up (Ref. Fig. Deactivation and Reactivation of the Servocontrol SHEET 1) Subtask 27-64-00-860-057-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Extend the flaps (Ref. AMM TASK 27-50-00-866-008) . (3) On the overhead panel 23VU : · Release the FLT CTL/SEC 1 pushbutton switch (on this pushbutton switch, the OFF legend comes on). (4) On the overhead panel 24VU : · Release the FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches (on these pushbutton switches, the OFF legends come on). (5) On the panel 114VU, put the LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION (98D27803000000) in position on the flap and slat control lever. (6) Put the PIN-SIDE STICK LOCKING (98D27903500000) in position on each side-stick controller. (7) Put the WARNING NOTICE(S) on the CAPT and F/O side sticks to tell persons not to touch the side sticks. (8) Depressurize the hydraulic system related to the spoiler that you must deactivate. (a) For the spoiler 1 or 5, depressurize the Green hydraulic system (Ref. AMM TASK 29-23-00-864001) . (b) For the spoiler 2 or 4, depressurize the Yellow hydraulic system (Ref. AMM TASK 29-24-00-864001) . (c) For the spoiler 3, depressurize the Blue hydraulic system (Ref. AMM TASK 29-10-00-864-003) . (9) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position in : (a) Zone 580 for the left spoilers. (b) Zone 680 for the right spoilers. (10) Open the applicable access panels: (a) FOR 31CE1 (SERVO CTL-SPLR1, L G) · The access panel 573BB (Ref. AMM TASK 57-51-37-000-002) . (b) FOR 31CE2 (SERVO CTL-SPLR1, R G) · The access panel 673BB (Ref. AMM TASK 57-51-37-000-002) . (c) FOR 31CE3 (SERVO CTL-SPLR2, L Y) · The access panel 575BB (Ref. AMM TASK 57-51-37-000-004) . (d) FOR 31CE4 (SERVO CTL-SPLR2, R Y) · The access panel 675BB (Ref. AMM TASK 57-51-37-000-004) . (e) FOR 31CE5 (SERVO CTL-SPLR3, L B) · The access panel 575DB (Ref. AMM TASK 57-51-37-000-004) . (f)

FOR 31CE6 (SERVO CTL-SPLR3, R B) · The access panel 675DB (Ref. AMM TASK 57-51-37-000-004) .

(g) FOR 31CE7 (SERVO CTL-SPLR4, L Y) · The access panel 575EB (Ref. AMM TASK 57-51-37-000-004) . (h) FOR 31CE8 (SERVO CTL-SPLR4, R Y) · The access panel 675EB (Ref. AMM TASK 57-51-37-000-004) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

(i)

FOR 31CE9 (SERVO CTL-SPLR5, L G) · The access panel 575GB (Ref. AMM TASK 57-51-37-000-004) .

(j)

FOR 31CE10 (SERVO CTL-SPLR5, R G) · The access panel 675GB (Ref. AMM TASK 57-51-37-000-004) .

(11) Before you de-activate a servocontrol, make sure that it has no external leaks. 4.

Procedure (Ref. Fig. Deactivation and Reactivation of the Servocontrol SHEET 1) Subtask 27-64-00-040-052-B A.

Deactivation of the Spoiler Servocontrol NOTE: When you deactivate a spoiler servocontrol, it is not necessary to deactivate the symmetrical spoiler on the other wing. (This spoiler is inhibited automatically by the SEC). (1) If there is no plate with the 'O' and 'M' indications on the maintenance device (PRE GOODRICH VSB 31077-27-15): CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE. IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL. (a) Install the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) on the servocontrol and turn it a quarter turn counterclockwise. The servocontrol is in maintenance position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key.

(b) Disconnect the electrical connector (2) from the receptacle (1) of the servocontrol. (c) Put CAP - BLANKING on the electrical connector (2) and receptacle (1). (d) Attach the electrical connector (2) to a hydraulic line with a TIE WRAP. (e) Make sure that the spoiler is in the fully retracted position. CAUTION: MAKE SURE THAT NO SPOILER MAINTENANCE KEY STAYS ENGAGED IN THE MAINTENANCE DEVICE HOUSING. AERODYNAMIC FORCES WILL CAUSE UNWANTED MOVEMENT OF THE SPOILER IF THE MAINTENANCE KEY STAYS IN ITS HOUSING. CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL. (f)

Turn the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) a quarter turn clockwise and remove it. The servocontrol is in operational position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key. NOTE: The defective servocontrol must stay hydraulically connected to the aircraft hydraulic system.

(g) Make sure that the work area is clean and clear of tools and other items. CAUTION: MAKE SURE THAT NO SPOILER MAINTENANCE KEY STAYS ENGAGED IN THE MAINTENANCE DEVICE HOUSING. AERODYNAMIC FORCES WILL CAUSE UNWANTED MOVEMENT OF THE SPOILER IF THE MAINTENANCE KEY STAYS IN ITS HOUSING. (h) Gradually apply a manual force to the spoiler surface trailing-edge and make sure that you cannot extend the spoiler. NOTE: If you can extend the spoiler manually with the servocontrol in the operational position: - It is necessary to replace the spoiler servocontrol. (i)

On the overhead panel 23VU: · Push the FLT CTL/SEC 1 pushbutton switch (on this pushbutton switch, the OFF legend goes off).

(j)

On the overhead panel 24VU: · Push the FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches (on these pushbutton switches, the OFF legends go off).

(k) On the ECAM control panel on the center pedestal, push the F/CTL key. On the ECAM lower display unit, the F/CTL page comes into view. (l)

Pressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-863-001) (Ref. AMM TASK 29-24-00-863-001) (Ref. AMM TASK 29-10-00-863-003) .

(2) If there is a plate with the 'O' and 'M' indications on the maintenance device (POST GOODRICH VSB 31077-27-15): CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE. IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

(a) Install the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) on the servocontrol and turn it a quarter turn counterclockwise to the 'M' position (Maintenance). The servocontrol is in maintenance position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key.

(b) Disconnect the electrical connector (2) from the receptacle (1) of the servocontrol. (c) Put CAP - BLANKING on the electrical connector (2) and receptacle (1). (d) Attach the electrical connector (2) to a hydraulic line with a TIE WRAP. (e) Make sure that the spoiler is in the fully retracted position. CAUTION: MAKE SURE THAT THE STOP OF THE HEXAGONAL-HEAD CONTROL SWITCH IS AGAINST THE LETTER 'O' ON THE HOUSING. IF IT IS AGAINST THE LETTER 'M', AERODYNAMIC FORCES WILL CAUSE UNWANTED MOVEMENT OF THE SPOILER AND POSSIBLE DAMAGE TO EQUIPMENT. CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE. IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL. (f)

Turn the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) a quarter turn clockwise to the 'O' position (Operation) and remove it. The servocontrol is in operational position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key. NOTE: The defective servocontrol must stay hydraulically connected to the aircraft hydraulic system.

(g) Make sure that the work area is clean and clear of tools and other items. CAUTION: MAKE SURE THAT NO SPOILER MAINTENANCE KEY STAYS ENGAGED IN THE MAINTENANCE DEVICE HOUSING. AERODYNAMIC FORCES WILL CAUSE UN-

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

WANTED MOVEMENT OF THE SPOILER IF THE MAINTENANCE KEY STAYS IN ITS HOUSING. (h) Gradually apply a manual force to the spoiler surface trailing-edge and make sure that you cannot extend the spoiler. NOTE: If you can extend the spoiler manually with the servocontrol in the operational position: - It is necessary to replace the spoiler servocontrol. (i)

On the overhead panel 23VU: · Push the FLT CTL/SEC 1 pushbutton switch (on this pushbutton switch, the OFF legend goes off).

(j)

On the overhead panel 24VU: · Push the FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches (on these pushbutton switches, the OFF legends go off).

(k) On the ECAM control panel on the center pedestal, push the F/CTL key. On the ECAM lower display-unit, the F/CTL page comes into view. (l)

Pressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-863-001) (Ref. AMM TASK 29-24-00-863-001) (Ref. AMM TASK 29-10-00-863-003) .

Subtask 27-64-00-710-054-A B.

Test of the Spoiler (1) During the operational test that follows: (a) Do a visual check from the ground: · Make sure that the spoiler with the deactivated servocontrol and its symmetrical on the other wing do not extend when they are operated. · Make sure that the spoilers are in the fully retracted position. (b) In the cockpit, on the System Display: · Make sure that the spoiler with the deactivated servocontrol stays amber with its symmetrical on the other wing. · Make sure that the amber F/CTL SPOILER FAULT message is shown on the EWD. (2) Do the operational test of the spoilers (Ref. AMM TASK 27-64-00-710-001) .

5.

Close-up Subtask 27-64-00-860-056-A A.

Put the aircraft back to its initial configuration. (1) On the panel 114VU, remove the LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION (98D27803000000) from the flap and slat control lever. (2) Retract the flaps (Ref. AMM TASK 27-50-00-866-009) . (3) Depressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-864-001) (Ref. AMM TASK 29-24-00-864-001) (Ref. AMM TASK 29-10-00-864-003) . (4) Remove the PIN-SIDE STICK LOCKING (98D27903500000) and the warning notice from each sidestick controller. (5) Close the applicable access panels: (a) FOR 31CE1 (SERVO CTL-SPLR1, L G) · The access panel 573BB (Ref. AMM TASK 57-51-37-400-002) . (b) FOR 31CE2 (SERVO CTL-SPLR1, R G) · The access panel 673BB (Ref. AMM TASK 57-51-37-400-002) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

(c) FOR 31CE3 (SERVO CTL-SPLR2, L Y) · The access panel 575BB (Ref. AMM TASK 57-51-37-400-004) . (d) FOR 31CE4 (SERVO CTL-SPLR2, R Y) · The access panel 675BB (Ref. AMM TASK 57-51-37-400-004) . (e) FOR 31CE5 (SERVO CTL-SPLR3, L B) · The access panel 575DB (Ref. AMM TASK 57-51-37-400-004) . (f)

FOR 31CE6 (SERVO CTL-SPLR3, R B) · The access panel 675DB (Ref. AMM TASK 57-51-37-400-004) .

(g) FOR 31CE7 (SERVO CTL-SPLR4, L Y) · The access panel 575EB (Ref. AMM TASK 57-51-37-400-004) . (h) FOR 31CE8 (SERVO CTL-SPLR4, R Y) · The access panel 675EB (Ref. AMM TASK 57-51-37-400-004) . (i)

FOR 31CE9 (SERVO CTL-SPLR5, L G) · The access panel 575GB (Ref. AMM TASK 57-51-37-400-004) .

(j)

FOR 31CE10 (SERVO CTL-SPLR5, R G) · The access panel 675GB (Ref. AMM TASK 57-51-37-400-004) .

(6) Remove access platform(s). (7) Make sure that the work area is clean and clear of tools and other items. (8) Make an entry in the log-book and record the defective servocontrol. (9) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

** ON A/C ALL TASK 27-64-00-040-001-A Deactivation of the Spoiler Servo Control 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:

DO NOT DO THIS DEACTIVATION PROCEDURE IF THERE IS EXTERNAL LEAKAGE ON THE UNSERVICEABLE SERVOCONTROL.

WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

FIN : 31CE1 , 31CE2 , 31CE3 , 31CE4 , 31CE5 , 31CE6 , 31CE7 , 31CE8 , 31CE9 , 31CE10 Task Summary MMEL or CDL Ref MMEL 27-64-01A MMEL 27-64-02A MMEL 27-64-03A MMEL 27-64-04A MMEL 27-64-05A 1.

Reason for the Job MMEL 27-64-01A Spoiler 5 MMEL 27-64-02A Spoiler 1 or 3 MMEL 27-64-03A Spoiler 2 or 4 MMEL 27-64-04A Spoilers 1 and 2 MMEL 27-64-05A Spoilers 3 and 4

2

Job Set-up Information A.

Access YES YES YES YES YES

Test YES YES YES YES YES

Specific Tools YES YES YES YES YES

Mhr 01.0 01.0 01.0 01.0 01.0

E/T 00.8 00.8 00.8 00.8 00.8

Nb Men 2 2 2 2 2

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

QTY AR AR AR

DESIGNATION ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE CAP - BLANKING TIE WRAP

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

REFERENCE No specific No specific (98D27603002000) OR (98D27603002001) (98D27803000000) (98D27903500000) B.

QTY AR AR 1 1 1 2

DESIGNATION TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC WARNING NOTICE(S) KEY-SPOILER MAINTENANCE OR KEY-SPOILER MAINTENANCE LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION PIN-SIDE STICK LOCKING

Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTION 580 LEFT WING FLAPS AND SPOILERS 680 RIGHT WING FLAPS AND SPOILERS FOR 31CE1 (SERVO CTL-SPLR1, L G) 573BB FOR 31CE10 (SERVO CTL-SPLR5, R G) 675GB FOR 31CE2 (SERVO CTL-SPLR1, R G) 673BB FOR 31CE3 (SERVO CTL-SPLR2, L Y) 575BB FOR 31CE4 (SERVO CTL-SPLR2, R Y) 675BB FOR 31CE5 (SERVO CTL-SPLR3, L B) 575DB FOR 31CE6 (SERVO CTL-SPLR3, R B) 675DB FOR 31CE7 (SERVO CTL-SPLR4, L Y) 575EB FOR 31CE8 (SERVO CTL-SPLR4, R Y) 675EB FOR 31CE9 (SERVO CTL-SPLR5, L G) 575GB

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 27-50-00-866-008-A). (Ref. 27-50-00-866-008-A-01). (Ref. 27-50-00-866-009-A). (Ref. 27-50-00-866-009-A-01).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Extension of the Flaps on the Ground Extension of the Flaps/Slats on the Ground Retraction of the Flaps on the Ground Retraction of the Flaps/Slats on the Ground

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

REFERENCE (Ref. 27-64-00-710-001-A). (Ref. 29-10-00-863-003-A).

DESIGNATION Operational Test of the Spoiler Hydraulic Actuation Pressurize the Blue Hydraulic System with a Hydraulic Ground PowerCart (Ref. 29-10-00-863-003-A-01). Pressurize the Blue Hydraulic System with the Blue Electric Pump (Ref. 29-10-00-864-003-A). Depressurize the Blue Hydraulic System (Ref. 29-23-00-863-001-A). Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump (Ref. 29-23-00-864-001-A). Depressurize the Green and Yellow Hydraulic Systems after Operation of the PTU (Ref. 29-24-00-863-001-A). Pressurize the Yellow Hydraulic System with the Electric Pump (Ref. 29-24-00-864-001-A). Depressurize the Yellow Hydraulic System Deactivation and Reactivation of the Servocontrol SHEET 1 FOR 31CE1 (SERVO CTL-SPLR1, L G) (Ref. 57-51-37-000-002-A). Removal of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) (Ref. 57-51-37-400-002-A). Installation of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) FOR 31CE10 (SERVO CTL-SPLR5, R G) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE2 (SERVO CTL-SPLR1, R G) (Ref. 57-51-37-000-002-A). Removal of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) (Ref. 57-51-37-400-002-A). Installation of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) FOR 31CE3 (SERVO CTL-SPLR2, L Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE4 (SERVO CTL-SPLR2, R Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE5 (SERVO CTL-SPLR3, L B) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE6 (SERVO CTL-SPLR3, R B) Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

REFERENCE (Ref. 57-51-37-000-004-A).

DESIGNATION Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE7 (SERVO CTL-SPLR4, L Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE8 (SERVO CTL-SPLR4, R Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE9 (SERVO CTL-SPLR5, L G) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

575GB 573BB

575DB

Z580

A

A A A

A

A

A

575EB

575BB

Z680 673BB

A

675BB 675DB 675EB 675GB

A

A 2 1

B

B

B 3

M O

MAINTENANCE DEVICE POST GOODRICH VSB 31077-27-15

MAINTENANCE DEVICE PRE GOODRICH VSB 31077-27-15 N_MM_276400_4_AAC0_01_02 N_MM_276400_4_AAD0_01_01

Figure 27-64-00-991-00700-00-C / SHEET 1/1 - Deactivation and Reactivation of the Servocontrol ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

3.

Job Set-up (Ref. Fig. Deactivation and Reactivation of the Servocontrol SHEET 1) Subtask 27-64-00-860-057-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Extend the flaps (Ref. AMM TASK 27-50-00-866-008) . (3) On the overhead panel 23VU : · Release the FLT CTL/SEC 1 pushbutton switch (on this pushbutton switch, the OFF legend comes on). (4) On the overhead panel 24VU : · Release the FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches (on these pushbutton switches, the OFF legends come on). (5) On the panel 114VU, put the LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION (98D27803000000) in position on the flap and slat control lever. (6) Put the PIN-SIDE STICK LOCKING (98D27903500000) in position on each side-stick controller. (7) Put the WARNING NOTICE(S) on the CAPT and F/O side sticks to tell persons not to touch the side sticks. (8) Depressurize the hydraulic system related to the spoiler that you must deactivate. (a) For the spoiler 1 or 5, depressurize the Green hydraulic system (Ref. AMM TASK 29-23-00-864001) . (b) For the spoiler 2 or 4, depressurize the Yellow hydraulic system (Ref. AMM TASK 29-24-00-864001) . (c) For the spoiler 3, depressurize the Blue hydraulic system (Ref. AMM TASK 29-10-00-864-003) . (9) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position in : (a) Zone 580 for the left spoilers. (b) Zone 680 for the right spoilers. (10) Open the applicable access panels: (a) FOR 31CE1 (SERVO CTL-SPLR1, L G) · The access panel 573BB (Ref. AMM TASK 57-51-37-000-002) . (b) FOR 31CE2 (SERVO CTL-SPLR1, R G) · The access panel 673BB (Ref. AMM TASK 57-51-37-000-002) . (c) FOR 31CE3 (SERVO CTL-SPLR2, L Y) · The access panel 575BB (Ref. AMM TASK 57-51-37-000-004) . (d) FOR 31CE4 (SERVO CTL-SPLR2, R Y) · The access panel 675BB (Ref. AMM TASK 57-51-37-000-004) . (e) FOR 31CE5 (SERVO CTL-SPLR3, L B) · The access panel 575DB (Ref. AMM TASK 57-51-37-000-004) . (f)

FOR 31CE6 (SERVO CTL-SPLR3, R B) · The access panel 675DB (Ref. AMM TASK 57-51-37-000-004) .

(g) FOR 31CE7 (SERVO CTL-SPLR4, L Y) · The access panel 575EB (Ref. AMM TASK 57-51-37-000-004) . (h) FOR 31CE8 (SERVO CTL-SPLR4, R Y) · The access panel 675EB (Ref. AMM TASK 57-51-37-000-004) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

(i)

FOR 31CE9 (SERVO CTL-SPLR5, L G) · The access panel 575GB (Ref. AMM TASK 57-51-37-000-004) .

(j)

FOR 31CE10 (SERVO CTL-SPLR5, R G) · The access panel 675GB (Ref. AMM TASK 57-51-37-000-004) .

(11) Before you de-activate a servocontrol, make sure that it has no external leaks. 4.

Procedure (Ref. Fig. Deactivation and Reactivation of the Servocontrol SHEET 1) Subtask 27-64-00-040-052-B A.

Deactivation of the Spoiler Servocontrol NOTE: When you deactivate a spoiler servocontrol, it is not necessary to deactivate the symmetrical spoiler on the other wing. (This spoiler is inhibited automatically by the SEC). (1) If there is no plate with the 'O' and 'M' indications on the maintenance device (PRE GOODRICH VSB 31077-27-15): CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE. IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL. (a) Install the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) on the servocontrol and turn it a quarter turn counterclockwise. The servocontrol is in maintenance position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key.

(b) Disconnect the electrical connector (2) from the receptacle (1) of the servocontrol. (c) Put CAP - BLANKING on the electrical connector (2) and receptacle (1). (d) Attach the electrical connector (2) to a hydraulic line with a TIE WRAP. (e) Make sure that the spoiler is in the fully retracted position. CAUTION: MAKE SURE THAT NO SPOILER MAINTENANCE KEY STAYS ENGAGED IN THE MAINTENANCE DEVICE HOUSING. AERODYNAMIC FORCES WILL CAUSE UNWANTED MOVEMENT OF THE SPOILER IF THE MAINTENANCE KEY STAYS IN ITS HOUSING. CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL. (f)

Turn the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) a quarter turn clockwise and remove it. The servocontrol is in operational position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key. NOTE: The defective servocontrol must stay hydraulically connected to the aircraft hydraulic system.

(g) Make sure that the work area is clean and clear of tools and other items. CAUTION: MAKE SURE THAT NO SPOILER MAINTENANCE KEY STAYS ENGAGED IN THE MAINTENANCE DEVICE HOUSING. AERODYNAMIC FORCES WILL CAUSE UNWANTED MOVEMENT OF THE SPOILER IF THE MAINTENANCE KEY STAYS IN ITS HOUSING. (h) Gradually apply a manual force to the spoiler surface trailing-edge and make sure that you cannot extend the spoiler. NOTE: If you can extend the spoiler manually with the servocontrol in the operational position: - It is necessary to replace the spoiler servocontrol. (i)

On the overhead panel 23VU: · Push the FLT CTL/SEC 1 pushbutton switch (on this pushbutton switch, the OFF legend goes off).

(j)

On the overhead panel 24VU: · Push the FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches (on these pushbutton switches, the OFF legends go off).

(k) On the ECAM control panel on the center pedestal, push the F/CTL key. On the ECAM lower display unit, the F/CTL page comes into view. (l)

Pressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-863-001) (Ref. AMM TASK 29-24-00-863-001) (Ref. AMM TASK 29-10-00-863-003) .

(2) If there is a plate with the 'O' and 'M' indications on the maintenance device (POST GOODRICH VSB 31077-27-15): CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE. IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

(a) Install the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) on the servocontrol and turn it a quarter turn counterclockwise to the 'M' position (Maintenance). The servocontrol is in maintenance position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key.

(b) Disconnect the electrical connector (2) from the receptacle (1) of the servocontrol. (c) Put CAP - BLANKING on the electrical connector (2) and receptacle (1). (d) Attach the electrical connector (2) to a hydraulic line with a TIE WRAP. (e) Make sure that the spoiler is in the fully retracted position. CAUTION: MAKE SURE THAT THE STOP OF THE HEXAGONAL-HEAD CONTROL SWITCH IS AGAINST THE LETTER 'O' ON THE HOUSING. IF IT IS AGAINST THE LETTER 'M', AERODYNAMIC FORCES WILL CAUSE UNWANTED MOVEMENT OF THE SPOILER AND POSSIBLE DAMAGE TO EQUIPMENT. CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE. IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL. (f)

Turn the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) a quarter turn clockwise to the 'O' position (Operation) and remove it. The servocontrol is in operational position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key. NOTE: The defective servocontrol must stay hydraulically connected to the aircraft hydraulic system.

(g) Make sure that the work area is clean and clear of tools and other items. CAUTION: MAKE SURE THAT NO SPOILER MAINTENANCE KEY STAYS ENGAGED IN THE MAINTENANCE DEVICE HOUSING. AERODYNAMIC FORCES WILL CAUSE UN-

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

WANTED MOVEMENT OF THE SPOILER IF THE MAINTENANCE KEY STAYS IN ITS HOUSING. (h) Gradually apply a manual force to the spoiler surface trailing-edge and make sure that you cannot extend the spoiler. NOTE: If you can extend the spoiler manually with the servocontrol in the operational position: - It is necessary to replace the spoiler servocontrol. (i)

On the overhead panel 23VU: · Push the FLT CTL/SEC 1 pushbutton switch (on this pushbutton switch, the OFF legend goes off).

(j)

On the overhead panel 24VU: · Push the FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches (on these pushbutton switches, the OFF legends go off).

(k) On the ECAM control panel on the center pedestal, push the F/CTL key. On the ECAM lower display-unit, the F/CTL page comes into view. (l)

Pressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-863-001) (Ref. AMM TASK 29-24-00-863-001) (Ref. AMM TASK 29-10-00-863-003) .

Subtask 27-64-00-710-054-A B.

Test of the Spoiler (1) During the operational test that follows: (a) Do a visual check from the ground: · Make sure that the spoiler with the deactivated servocontrol and its symmetrical on the other wing do not extend when they are operated. · Make sure that the spoilers are in the fully retracted position. (b) In the cockpit, on the System Display: · Make sure that the spoiler with the deactivated servocontrol stays amber with its symmetrical on the other wing. · Make sure that the amber F/CTL SPOILER FAULT message is shown on the EWD. (2) Do the operational test of the spoilers (Ref. AMM TASK 27-64-00-710-001) .

5.

Close-up Subtask 27-64-00-860-056-A A.

Put the aircraft back to its initial configuration. (1) On the panel 114VU, remove the LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION (98D27803000000) from the flap and slat control lever. (2) Retract the flaps (Ref. AMM TASK 27-50-00-866-009) . (3) Depressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-864-001) (Ref. AMM TASK 29-24-00-864-001) (Ref. AMM TASK 29-10-00-864-003) . (4) Remove the PIN-SIDE STICK LOCKING (98D27903500000) and the warning notice from each sidestick controller. (5) Close the applicable access panels: (a) FOR 31CE1 (SERVO CTL-SPLR1, L G) · The access panel 573BB (Ref. AMM TASK 57-51-37-400-002) . (b) FOR 31CE2 (SERVO CTL-SPLR1, R G) · The access panel 673BB (Ref. AMM TASK 57-51-37-400-002) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

(c) FOR 31CE3 (SERVO CTL-SPLR2, L Y) · The access panel 575BB (Ref. AMM TASK 57-51-37-400-004) . (d) FOR 31CE4 (SERVO CTL-SPLR2, R Y) · The access panel 675BB (Ref. AMM TASK 57-51-37-400-004) . (e) FOR 31CE5 (SERVO CTL-SPLR3, L B) · The access panel 575DB (Ref. AMM TASK 57-51-37-400-004) . (f)

FOR 31CE6 (SERVO CTL-SPLR3, R B) · The access panel 675DB (Ref. AMM TASK 57-51-37-400-004) .

(g) FOR 31CE7 (SERVO CTL-SPLR4, L Y) · The access panel 575EB (Ref. AMM TASK 57-51-37-400-004) . (h) FOR 31CE8 (SERVO CTL-SPLR4, R Y) · The access panel 675EB (Ref. AMM TASK 57-51-37-400-004) . (i)

FOR 31CE9 (SERVO CTL-SPLR5, L G) · The access panel 575GB (Ref. AMM TASK 57-51-37-400-004) .

(j)

FOR 31CE10 (SERVO CTL-SPLR5, R G) · The access panel 675GB (Ref. AMM TASK 57-51-37-400-004) .

(6) Remove access platform(s). (7) Make sure that the work area is clean and clear of tools and other items. (8) Make an entry in the log-book and record the defective servocontrol. (9) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

** ON A/C ALL TASK 27-64-00-040-001-A Deactivation of the Spoiler Servo Control 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:

DO NOT DO THIS DEACTIVATION PROCEDURE IF THERE IS EXTERNAL LEAKAGE ON THE UNSERVICEABLE SERVOCONTROL.

WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

FIN : 31CE1 , 31CE2 , 31CE3 , 31CE4 , 31CE5 , 31CE6 , 31CE7 , 31CE8 , 31CE9 , 31CE10 Task Summary MMEL or CDL Ref MMEL 27-64-01A MMEL 27-64-02A MMEL 27-64-03A MMEL 27-64-04A MMEL 27-64-05A 1.

Reason for the Job MMEL 27-64-01A Spoiler 5 MMEL 27-64-02A Spoiler 1 or 3 MMEL 27-64-03A Spoiler 2 or 4 MMEL 27-64-04A Spoilers 1 and 2 MMEL 27-64-05A Spoilers 3 and 4

2

Job Set-up Information A.

Access YES YES YES YES YES

Test YES YES YES YES YES

Specific Tools YES YES YES YES YES

Mhr 01.0 01.0 01.0 01.0 01.0

E/T 00.8 00.8 00.8 00.8 00.8

Nb Men 2 2 2 2 2

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

QTY AR AR AR

DESIGNATION ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE CAP - BLANKING TIE WRAP

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

REFERENCE No specific No specific (98D27603002000) OR (98D27603002001) (98D27803000000) (98D27903500000) B.

QTY AR AR 1 1 1 2

DESIGNATION TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC WARNING NOTICE(S) KEY-SPOILER MAINTENANCE OR KEY-SPOILER MAINTENANCE LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION PIN-SIDE STICK LOCKING

Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTION 580 LEFT WING FLAPS AND SPOILERS 680 RIGHT WING FLAPS AND SPOILERS FOR 31CE1 (SERVO CTL-SPLR1, L G) 573BB FOR 31CE10 (SERVO CTL-SPLR5, R G) 675GB FOR 31CE2 (SERVO CTL-SPLR1, R G) 673BB FOR 31CE3 (SERVO CTL-SPLR2, L Y) 575BB FOR 31CE4 (SERVO CTL-SPLR2, R Y) 675BB FOR 31CE5 (SERVO CTL-SPLR3, L B) 575DB FOR 31CE6 (SERVO CTL-SPLR3, R B) 675DB FOR 31CE7 (SERVO CTL-SPLR4, L Y) 575EB FOR 31CE8 (SERVO CTL-SPLR4, R Y) 675EB FOR 31CE9 (SERVO CTL-SPLR5, L G) 575GB

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 27-50-00-866-008-A). (Ref. 27-50-00-866-008-A-01). (Ref. 27-50-00-866-009-A). (Ref. 27-50-00-866-009-A-01).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Extension of the Flaps on the Ground Extension of the Flaps/Slats on the Ground Retraction of the Flaps on the Ground Retraction of the Flaps/Slats on the Ground

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

REFERENCE (Ref. 27-64-00-710-001-A). (Ref. 29-10-00-863-003-A).

DESIGNATION Operational Test of the Spoiler Hydraulic Actuation Pressurize the Blue Hydraulic System with a Hydraulic Ground PowerCart (Ref. 29-10-00-863-003-A-01). Pressurize the Blue Hydraulic System with the Blue Electric Pump (Ref. 29-10-00-864-003-A). Depressurize the Blue Hydraulic System (Ref. 29-23-00-863-001-A). Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump (Ref. 29-23-00-864-001-A). Depressurize the Green and Yellow Hydraulic Systems after Operation of the PTU (Ref. 29-24-00-863-001-A). Pressurize the Yellow Hydraulic System with the Electric Pump (Ref. 29-24-00-864-001-A). Depressurize the Yellow Hydraulic System Deactivation and Reactivation of the Servocontrol SHEET 1 FOR 31CE1 (SERVO CTL-SPLR1, L G) (Ref. 57-51-37-000-002-A). Removal of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) (Ref. 57-51-37-400-002-A). Installation of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) FOR 31CE10 (SERVO CTL-SPLR5, R G) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE2 (SERVO CTL-SPLR1, R G) (Ref. 57-51-37-000-002-A). Removal of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) (Ref. 57-51-37-400-002-A). Installation of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) FOR 31CE3 (SERVO CTL-SPLR2, L Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE4 (SERVO CTL-SPLR2, R Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE5 (SERVO CTL-SPLR3, L B) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE6 (SERVO CTL-SPLR3, R B) Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

REFERENCE (Ref. 57-51-37-000-004-A).

DESIGNATION Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE7 (SERVO CTL-SPLR4, L Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE8 (SERVO CTL-SPLR4, R Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE9 (SERVO CTL-SPLR5, L G) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

575GB 573BB

575DB

Z580

A

A A A

A

A

A

575EB

575BB

Z680 673BB

A

675BB 675DB 675EB 675GB

A

A 2 1

B

B

B 3

M O

MAINTENANCE DEVICE POST GOODRICH VSB 31077-27-15

MAINTENANCE DEVICE PRE GOODRICH VSB 31077-27-15 N_MM_276400_4_AAC0_01_02 N_MM_276400_4_AAD0_01_01

Figure 27-64-00-991-00700-00-C / SHEET 1/1 - Deactivation and Reactivation of the Servocontrol ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

3.

Job Set-up (Ref. Fig. Deactivation and Reactivation of the Servocontrol SHEET 1) Subtask 27-64-00-860-057-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Extend the flaps (Ref. AMM TASK 27-50-00-866-008) . (3) On the overhead panel 23VU : · Release the FLT CTL/SEC 1 pushbutton switch (on this pushbutton switch, the OFF legend comes on). (4) On the overhead panel 24VU : · Release the FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches (on these pushbutton switches, the OFF legends come on). (5) On the panel 114VU, put the LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION (98D27803000000) in position on the flap and slat control lever. (6) Put the PIN-SIDE STICK LOCKING (98D27903500000) in position on each side-stick controller. (7) Put the WARNING NOTICE(S) on the CAPT and F/O side sticks to tell persons not to touch the side sticks. (8) Depressurize the hydraulic system related to the spoiler that you must deactivate. (a) For the spoiler 1 or 5, depressurize the Green hydraulic system (Ref. AMM TASK 29-23-00-864001) . (b) For the spoiler 2 or 4, depressurize the Yellow hydraulic system (Ref. AMM TASK 29-24-00-864001) . (c) For the spoiler 3, depressurize the Blue hydraulic system (Ref. AMM TASK 29-10-00-864-003) . (9) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position in : (a) Zone 580 for the left spoilers. (b) Zone 680 for the right spoilers. (10) Open the applicable access panels: (a) FOR 31CE1 (SERVO CTL-SPLR1, L G) · The access panel 573BB (Ref. AMM TASK 57-51-37-000-002) . (b) FOR 31CE2 (SERVO CTL-SPLR1, R G) · The access panel 673BB (Ref. AMM TASK 57-51-37-000-002) . (c) FOR 31CE3 (SERVO CTL-SPLR2, L Y) · The access panel 575BB (Ref. AMM TASK 57-51-37-000-004) . (d) FOR 31CE4 (SERVO CTL-SPLR2, R Y) · The access panel 675BB (Ref. AMM TASK 57-51-37-000-004) . (e) FOR 31CE5 (SERVO CTL-SPLR3, L B) · The access panel 575DB (Ref. AMM TASK 57-51-37-000-004) . (f)

FOR 31CE6 (SERVO CTL-SPLR3, R B) · The access panel 675DB (Ref. AMM TASK 57-51-37-000-004) .

(g) FOR 31CE7 (SERVO CTL-SPLR4, L Y) · The access panel 575EB (Ref. AMM TASK 57-51-37-000-004) . (h) FOR 31CE8 (SERVO CTL-SPLR4, R Y) · The access panel 675EB (Ref. AMM TASK 57-51-37-000-004) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

(i)

FOR 31CE9 (SERVO CTL-SPLR5, L G) · The access panel 575GB (Ref. AMM TASK 57-51-37-000-004) .

(j)

FOR 31CE10 (SERVO CTL-SPLR5, R G) · The access panel 675GB (Ref. AMM TASK 57-51-37-000-004) .

(11) Before you de-activate a servocontrol, make sure that it has no external leaks. 4.

Procedure (Ref. Fig. Deactivation and Reactivation of the Servocontrol SHEET 1) Subtask 27-64-00-040-052-B A.

Deactivation of the Spoiler Servocontrol NOTE: When you deactivate a spoiler servocontrol, it is not necessary to deactivate the symmetrical spoiler on the other wing. (This spoiler is inhibited automatically by the SEC). (1) If there is no plate with the 'O' and 'M' indications on the maintenance device (PRE GOODRICH VSB 31077-27-15): CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE. IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL. (a) Install the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) on the servocontrol and turn it a quarter turn counterclockwise. The servocontrol is in maintenance position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key.

(b) Disconnect the electrical connector (2) from the receptacle (1) of the servocontrol. (c) Put CAP - BLANKING on the electrical connector (2) and receptacle (1). (d) Attach the electrical connector (2) to a hydraulic line with a TIE WRAP. (e) Make sure that the spoiler is in the fully retracted position. CAUTION: MAKE SURE THAT NO SPOILER MAINTENANCE KEY STAYS ENGAGED IN THE MAINTENANCE DEVICE HOUSING. AERODYNAMIC FORCES WILL CAUSE UNWANTED MOVEMENT OF THE SPOILER IF THE MAINTENANCE KEY STAYS IN ITS HOUSING. CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL. (f)

Turn the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) a quarter turn clockwise and remove it. The servocontrol is in operational position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key. NOTE: The defective servocontrol must stay hydraulically connected to the aircraft hydraulic system.

(g) Make sure that the work area is clean and clear of tools and other items. CAUTION: MAKE SURE THAT NO SPOILER MAINTENANCE KEY STAYS ENGAGED IN THE MAINTENANCE DEVICE HOUSING. AERODYNAMIC FORCES WILL CAUSE UNWANTED MOVEMENT OF THE SPOILER IF THE MAINTENANCE KEY STAYS IN ITS HOUSING. (h) Gradually apply a manual force to the spoiler surface trailing-edge and make sure that you cannot extend the spoiler. NOTE: If you can extend the spoiler manually with the servocontrol in the operational position: - It is necessary to replace the spoiler servocontrol. (i)

On the overhead panel 23VU: · Push the FLT CTL/SEC 1 pushbutton switch (on this pushbutton switch, the OFF legend goes off).

(j)

On the overhead panel 24VU: · Push the FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches (on these pushbutton switches, the OFF legends go off).

(k) On the ECAM control panel on the center pedestal, push the F/CTL key. On the ECAM lower display unit, the F/CTL page comes into view. (l)

Pressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-863-001) (Ref. AMM TASK 29-24-00-863-001) (Ref. AMM TASK 29-10-00-863-003) .

(2) If there is a plate with the 'O' and 'M' indications on the maintenance device (POST GOODRICH VSB 31077-27-15): CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE. IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

(a) Install the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) on the servocontrol and turn it a quarter turn counterclockwise to the 'M' position (Maintenance). The servocontrol is in maintenance position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key.

(b) Disconnect the electrical connector (2) from the receptacle (1) of the servocontrol. (c) Put CAP - BLANKING on the electrical connector (2) and receptacle (1). (d) Attach the electrical connector (2) to a hydraulic line with a TIE WRAP. (e) Make sure that the spoiler is in the fully retracted position. CAUTION: MAKE SURE THAT THE STOP OF THE HEXAGONAL-HEAD CONTROL SWITCH IS AGAINST THE LETTER 'O' ON THE HOUSING. IF IT IS AGAINST THE LETTER 'M', AERODYNAMIC FORCES WILL CAUSE UNWANTED MOVEMENT OF THE SPOILER AND POSSIBLE DAMAGE TO EQUIPMENT. CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE. IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL. (f)

Turn the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) a quarter turn clockwise to the 'O' position (Operation) and remove it. The servocontrol is in operational position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key. NOTE: The defective servocontrol must stay hydraulically connected to the aircraft hydraulic system.

(g) Make sure that the work area is clean and clear of tools and other items. CAUTION: MAKE SURE THAT NO SPOILER MAINTENANCE KEY STAYS ENGAGED IN THE MAINTENANCE DEVICE HOUSING. AERODYNAMIC FORCES WILL CAUSE UN-

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

WANTED MOVEMENT OF THE SPOILER IF THE MAINTENANCE KEY STAYS IN ITS HOUSING. (h) Gradually apply a manual force to the spoiler surface trailing-edge and make sure that you cannot extend the spoiler. NOTE: If you can extend the spoiler manually with the servocontrol in the operational position: - It is necessary to replace the spoiler servocontrol. (i)

On the overhead panel 23VU: · Push the FLT CTL/SEC 1 pushbutton switch (on this pushbutton switch, the OFF legend goes off).

(j)

On the overhead panel 24VU: · Push the FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches (on these pushbutton switches, the OFF legends go off).

(k) On the ECAM control panel on the center pedestal, push the F/CTL key. On the ECAM lower display-unit, the F/CTL page comes into view. (l)

Pressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-863-001) (Ref. AMM TASK 29-24-00-863-001) (Ref. AMM TASK 29-10-00-863-003) .

Subtask 27-64-00-710-054-A B.

Test of the Spoiler (1) During the operational test that follows: (a) Do a visual check from the ground: · Make sure that the spoiler with the deactivated servocontrol and its symmetrical on the other wing do not extend when they are operated. · Make sure that the spoilers are in the fully retracted position. (b) In the cockpit, on the System Display: · Make sure that the spoiler with the deactivated servocontrol stays amber with its symmetrical on the other wing. · Make sure that the amber F/CTL SPOILER FAULT message is shown on the EWD. (2) Do the operational test of the spoilers (Ref. AMM TASK 27-64-00-710-001) .

5.

Close-up Subtask 27-64-00-860-056-A A.

Put the aircraft back to its initial configuration. (1) On the panel 114VU, remove the LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION (98D27803000000) from the flap and slat control lever. (2) Retract the flaps (Ref. AMM TASK 27-50-00-866-009) . (3) Depressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-864-001) (Ref. AMM TASK 29-24-00-864-001) (Ref. AMM TASK 29-10-00-864-003) . (4) Remove the PIN-SIDE STICK LOCKING (98D27903500000) and the warning notice from each sidestick controller. (5) Close the applicable access panels: (a) FOR 31CE1 (SERVO CTL-SPLR1, L G) · The access panel 573BB (Ref. AMM TASK 57-51-37-400-002) . (b) FOR 31CE2 (SERVO CTL-SPLR1, R G) · The access panel 673BB (Ref. AMM TASK 57-51-37-400-002) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

(c) FOR 31CE3 (SERVO CTL-SPLR2, L Y) · The access panel 575BB (Ref. AMM TASK 57-51-37-400-004) . (d) FOR 31CE4 (SERVO CTL-SPLR2, R Y) · The access panel 675BB (Ref. AMM TASK 57-51-37-400-004) . (e) FOR 31CE5 (SERVO CTL-SPLR3, L B) · The access panel 575DB (Ref. AMM TASK 57-51-37-400-004) . (f)

FOR 31CE6 (SERVO CTL-SPLR3, R B) · The access panel 675DB (Ref. AMM TASK 57-51-37-400-004) .

(g) FOR 31CE7 (SERVO CTL-SPLR4, L Y) · The access panel 575EB (Ref. AMM TASK 57-51-37-400-004) . (h) FOR 31CE8 (SERVO CTL-SPLR4, R Y) · The access panel 675EB (Ref. AMM TASK 57-51-37-400-004) . (i)

FOR 31CE9 (SERVO CTL-SPLR5, L G) · The access panel 575GB (Ref. AMM TASK 57-51-37-400-004) .

(j)

FOR 31CE10 (SERVO CTL-SPLR5, R G) · The access panel 675GB (Ref. AMM TASK 57-51-37-400-004) .

(6) Remove access platform(s). (7) Make sure that the work area is clean and clear of tools and other items. (8) Make an entry in the log-book and record the defective servocontrol. (9) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

** ON A/C ALL TASK 27-64-00-040-001-A Deactivation of the Spoiler Servo Control 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:

DO NOT DO THIS DEACTIVATION PROCEDURE IF THERE IS EXTERNAL LEAKAGE ON THE UNSERVICEABLE SERVOCONTROL.

WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

FIN : 31CE1 , 31CE2 , 31CE3 , 31CE4 , 31CE5 , 31CE6 , 31CE7 , 31CE8 , 31CE9 , 31CE10 Task Summary MMEL or CDL Ref MMEL 27-64-01A MMEL 27-64-02A MMEL 27-64-03A MMEL 27-64-04A MMEL 27-64-05A 1.

Reason for the Job MMEL 27-64-01A Spoiler 5 MMEL 27-64-02A Spoiler 1 or 3 MMEL 27-64-03A Spoiler 2 or 4 MMEL 27-64-04A Spoilers 1 and 2 MMEL 27-64-05A Spoilers 3 and 4

2

Job Set-up Information A.

Access YES YES YES YES YES

Test YES YES YES YES YES

Specific Tools YES YES YES YES YES

Mhr 01.0 01.0 01.0 01.0 01.0

E/T 00.8 00.8 00.8 00.8 00.8

Nb Men 2 2 2 2 2

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

QTY AR AR AR

DESIGNATION ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE CAP - BLANKING TIE WRAP

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

REFERENCE No specific No specific (98D27603002000) OR (98D27603002001) (98D27803000000) (98D27903500000) B.

QTY AR AR 1 1 1 2

DESIGNATION TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC WARNING NOTICE(S) KEY-SPOILER MAINTENANCE OR KEY-SPOILER MAINTENANCE LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION PIN-SIDE STICK LOCKING

Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTION 580 LEFT WING FLAPS AND SPOILERS 680 RIGHT WING FLAPS AND SPOILERS FOR 31CE1 (SERVO CTL-SPLR1, L G) 573BB FOR 31CE10 (SERVO CTL-SPLR5, R G) 675GB FOR 31CE2 (SERVO CTL-SPLR1, R G) 673BB FOR 31CE3 (SERVO CTL-SPLR2, L Y) 575BB FOR 31CE4 (SERVO CTL-SPLR2, R Y) 675BB FOR 31CE5 (SERVO CTL-SPLR3, L B) 575DB FOR 31CE6 (SERVO CTL-SPLR3, R B) 675DB FOR 31CE7 (SERVO CTL-SPLR4, L Y) 575EB FOR 31CE8 (SERVO CTL-SPLR4, R Y) 675EB FOR 31CE9 (SERVO CTL-SPLR5, L G) 575GB

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 27-50-00-866-008-A). (Ref. 27-50-00-866-008-A-01). (Ref. 27-50-00-866-009-A). (Ref. 27-50-00-866-009-A-01).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Extension of the Flaps on the Ground Extension of the Flaps/Slats on the Ground Retraction of the Flaps on the Ground Retraction of the Flaps/Slats on the Ground

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

REFERENCE (Ref. 27-64-00-710-001-A). (Ref. 29-10-00-863-003-A).

DESIGNATION Operational Test of the Spoiler Hydraulic Actuation Pressurize the Blue Hydraulic System with a Hydraulic Ground PowerCart (Ref. 29-10-00-863-003-A-01). Pressurize the Blue Hydraulic System with the Blue Electric Pump (Ref. 29-10-00-864-003-A). Depressurize the Blue Hydraulic System (Ref. 29-23-00-863-001-A). Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump (Ref. 29-23-00-864-001-A). Depressurize the Green and Yellow Hydraulic Systems after Operation of the PTU (Ref. 29-24-00-863-001-A). Pressurize the Yellow Hydraulic System with the Electric Pump (Ref. 29-24-00-864-001-A). Depressurize the Yellow Hydraulic System Deactivation and Reactivation of the Servocontrol SHEET 1 FOR 31CE1 (SERVO CTL-SPLR1, L G) (Ref. 57-51-37-000-002-A). Removal of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) (Ref. 57-51-37-400-002-A). Installation of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) FOR 31CE10 (SERVO CTL-SPLR5, R G) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE2 (SERVO CTL-SPLR1, R G) (Ref. 57-51-37-000-002-A). Removal of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) (Ref. 57-51-37-400-002-A). Installation of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) FOR 31CE3 (SERVO CTL-SPLR2, L Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE4 (SERVO CTL-SPLR2, R Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE5 (SERVO CTL-SPLR3, L B) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE6 (SERVO CTL-SPLR3, R B) Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

REFERENCE (Ref. 57-51-37-000-004-A).

DESIGNATION Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE7 (SERVO CTL-SPLR4, L Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE8 (SERVO CTL-SPLR4, R Y) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) FOR 31CE9 (SERVO CTL-SPLR5, L G) (Ref. 57-51-37-000-004-A). Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) (Ref. 57-51-37-400-004-A). Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

575GB 573BB

575DB

Z580

A

A A A

A

A

A

575EB

575BB

Z680 673BB

A

675BB 675DB 675EB 675GB

A

A 2 1

B

B

B 3

M O

MAINTENANCE DEVICE POST GOODRICH VSB 31077-27-15

MAINTENANCE DEVICE PRE GOODRICH VSB 31077-27-15 N_MM_276400_4_AAC0_01_02 N_MM_276400_4_AAD0_01_01

Figure 27-64-00-991-00700-00-C / SHEET 1/1 - Deactivation and Reactivation of the Servocontrol ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

3.

Job Set-up (Ref. Fig. Deactivation and Reactivation of the Servocontrol SHEET 1) Subtask 27-64-00-860-057-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Extend the flaps (Ref. AMM TASK 27-50-00-866-008) . (3) On the overhead panel 23VU : · Release the FLT CTL/SEC 1 pushbutton switch (on this pushbutton switch, the OFF legend comes on). (4) On the overhead panel 24VU : · Release the FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches (on these pushbutton switches, the OFF legends come on). (5) On the panel 114VU, put the LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION (98D27803000000) in position on the flap and slat control lever. (6) Put the PIN-SIDE STICK LOCKING (98D27903500000) in position on each side-stick controller. (7) Put the WARNING NOTICE(S) on the CAPT and F/O side sticks to tell persons not to touch the side sticks. (8) Depressurize the hydraulic system related to the spoiler that you must deactivate. (a) For the spoiler 1 or 5, depressurize the Green hydraulic system (Ref. AMM TASK 29-23-00-864001) . (b) For the spoiler 2 or 4, depressurize the Yellow hydraulic system (Ref. AMM TASK 29-24-00-864001) . (c) For the spoiler 3, depressurize the Blue hydraulic system (Ref. AMM TASK 29-10-00-864-003) . (9) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position in : (a) Zone 580 for the left spoilers. (b) Zone 680 for the right spoilers. (10) Open the applicable access panels: (a) FOR 31CE1 (SERVO CTL-SPLR1, L G) · The access panel 573BB (Ref. AMM TASK 57-51-37-000-002) . (b) FOR 31CE2 (SERVO CTL-SPLR1, R G) · The access panel 673BB (Ref. AMM TASK 57-51-37-000-002) . (c) FOR 31CE3 (SERVO CTL-SPLR2, L Y) · The access panel 575BB (Ref. AMM TASK 57-51-37-000-004) . (d) FOR 31CE4 (SERVO CTL-SPLR2, R Y) · The access panel 675BB (Ref. AMM TASK 57-51-37-000-004) . (e) FOR 31CE5 (SERVO CTL-SPLR3, L B) · The access panel 575DB (Ref. AMM TASK 57-51-37-000-004) . (f)

FOR 31CE6 (SERVO CTL-SPLR3, R B) · The access panel 675DB (Ref. AMM TASK 57-51-37-000-004) .

(g) FOR 31CE7 (SERVO CTL-SPLR4, L Y) · The access panel 575EB (Ref. AMM TASK 57-51-37-000-004) . (h) FOR 31CE8 (SERVO CTL-SPLR4, R Y) · The access panel 675EB (Ref. AMM TASK 57-51-37-000-004) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

(i)

FOR 31CE9 (SERVO CTL-SPLR5, L G) · The access panel 575GB (Ref. AMM TASK 57-51-37-000-004) .

(j)

FOR 31CE10 (SERVO CTL-SPLR5, R G) · The access panel 675GB (Ref. AMM TASK 57-51-37-000-004) .

(11) Before you de-activate a servocontrol, make sure that it has no external leaks. 4.

Procedure (Ref. Fig. Deactivation and Reactivation of the Servocontrol SHEET 1) Subtask 27-64-00-040-052-B A.

Deactivation of the Spoiler Servocontrol NOTE: When you deactivate a spoiler servocontrol, it is not necessary to deactivate the symmetrical spoiler on the other wing. (This spoiler is inhibited automatically by the SEC). (1) If there is no plate with the 'O' and 'M' indications on the maintenance device (PRE GOODRICH VSB 31077-27-15): CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE. IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL. (a) Install the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) on the servocontrol and turn it a quarter turn counterclockwise. The servocontrol is in maintenance position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key.

(b) Disconnect the electrical connector (2) from the receptacle (1) of the servocontrol. (c) Put CAP - BLANKING on the electrical connector (2) and receptacle (1). (d) Attach the electrical connector (2) to a hydraulic line with a TIE WRAP. (e) Make sure that the spoiler is in the fully retracted position. CAUTION: MAKE SURE THAT NO SPOILER MAINTENANCE KEY STAYS ENGAGED IN THE MAINTENANCE DEVICE HOUSING. AERODYNAMIC FORCES WILL CAUSE UNWANTED MOVEMENT OF THE SPOILER IF THE MAINTENANCE KEY STAYS IN ITS HOUSING. CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL. (f)

Turn the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) a quarter turn clockwise and remove it. The servocontrol is in operational position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key. NOTE: The defective servocontrol must stay hydraulically connected to the aircraft hydraulic system.

(g) Make sure that the work area is clean and clear of tools and other items. CAUTION: MAKE SURE THAT NO SPOILER MAINTENANCE KEY STAYS ENGAGED IN THE MAINTENANCE DEVICE HOUSING. AERODYNAMIC FORCES WILL CAUSE UNWANTED MOVEMENT OF THE SPOILER IF THE MAINTENANCE KEY STAYS IN ITS HOUSING. (h) Gradually apply a manual force to the spoiler surface trailing-edge and make sure that you cannot extend the spoiler. NOTE: If you can extend the spoiler manually with the servocontrol in the operational position: - It is necessary to replace the spoiler servocontrol. (i)

On the overhead panel 23VU: · Push the FLT CTL/SEC 1 pushbutton switch (on this pushbutton switch, the OFF legend goes off).

(j)

On the overhead panel 24VU: · Push the FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches (on these pushbutton switches, the OFF legends go off).

(k) On the ECAM control panel on the center pedestal, push the F/CTL key. On the ECAM lower display unit, the F/CTL page comes into view. (l)

Pressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-863-001) (Ref. AMM TASK 29-24-00-863-001) (Ref. AMM TASK 29-10-00-863-003) .

(2) If there is a plate with the 'O' and 'M' indications on the maintenance device (POST GOODRICH VSB 31077-27-15): CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE. IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

(a) Install the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) on the servocontrol and turn it a quarter turn counterclockwise to the 'M' position (Maintenance). The servocontrol is in maintenance position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key.

(b) Disconnect the electrical connector (2) from the receptacle (1) of the servocontrol. (c) Put CAP - BLANKING on the electrical connector (2) and receptacle (1). (d) Attach the electrical connector (2) to a hydraulic line with a TIE WRAP. (e) Make sure that the spoiler is in the fully retracted position. CAUTION: MAKE SURE THAT THE STOP OF THE HEXAGONAL-HEAD CONTROL SWITCH IS AGAINST THE LETTER 'O' ON THE HOUSING. IF IT IS AGAINST THE LETTER 'M', AERODYNAMIC FORCES WILL CAUSE UNWANTED MOVEMENT OF THE SPOILER AND POSSIBLE DAMAGE TO EQUIPMENT. CAUTION: DO NOT APPLY A HIGH TORQUE LOAD ON THE KEY SPOILER MAINTENANCE TOOL WHEN YOU SET THE SERVOCONTROL TO OPERATIONAL MODE OR MAINTENANCE MODE. IF YOU APPLY A HIGH TORQUE LOAD, IT CAN CAUSE DAMAGE TO THE TOOL AND/OR TO THE SERVOCONTROL. (f)

Turn the KEY-SPOILER MAINTENANCE (98D27603002000) or KEY-SPOILER MAINTENANCE (98D27603002001) (3) a quarter turn clockwise to the 'O' position (Operation) and remove it. The servocontrol is in operational position. NOTE: The necessary torque to operate the maintenance device is 0.350 m.daN (30.97 lbf.in). If 0.350 m.daN (30.97 lbf.in) is not enough to turn the KEY-SPOILER MAINTENANCE, it is possible that the maintenance device is damaged. To prevent more damage to the maintenance device, remove the spoiler servo control and send it back to the supplier for analysis. 1

If necessary, use a TOMMY BAR DIA 4 MM (0,157 IN) - METALLIC to turn the spoiler maintenance key. NOTE: The defective servocontrol must stay hydraulically connected to the aircraft hydraulic system.

(g) Make sure that the work area is clean and clear of tools and other items. CAUTION: MAKE SURE THAT NO SPOILER MAINTENANCE KEY STAYS ENGAGED IN THE MAINTENANCE DEVICE HOUSING. AERODYNAMIC FORCES WILL CAUSE UN-

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

WANTED MOVEMENT OF THE SPOILER IF THE MAINTENANCE KEY STAYS IN ITS HOUSING. (h) Gradually apply a manual force to the spoiler surface trailing-edge and make sure that you cannot extend the spoiler. NOTE: If you can extend the spoiler manually with the servocontrol in the operational position: - It is necessary to replace the spoiler servocontrol. (i)

On the overhead panel 23VU: · Push the FLT CTL/SEC 1 pushbutton switch (on this pushbutton switch, the OFF legend goes off).

(j)

On the overhead panel 24VU: · Push the FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches (on these pushbutton switches, the OFF legends go off).

(k) On the ECAM control panel on the center pedestal, push the F/CTL key. On the ECAM lower display-unit, the F/CTL page comes into view. (l)

Pressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-863-001) (Ref. AMM TASK 29-24-00-863-001) (Ref. AMM TASK 29-10-00-863-003) .

Subtask 27-64-00-710-054-A B.

Test of the Spoiler (1) During the operational test that follows: (a) Do a visual check from the ground: · Make sure that the spoiler with the deactivated servocontrol and its symmetrical on the other wing do not extend when they are operated. · Make sure that the spoilers are in the fully retracted position. (b) In the cockpit, on the System Display: · Make sure that the spoiler with the deactivated servocontrol stays amber with its symmetrical on the other wing. · Make sure that the amber F/CTL SPOILER FAULT message is shown on the EWD. (2) Do the operational test of the spoilers (Ref. AMM TASK 27-64-00-710-001) .

5.

Close-up Subtask 27-64-00-860-056-A A.

Put the aircraft back to its initial configuration. (1) On the panel 114VU, remove the LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION (98D27803000000) from the flap and slat control lever. (2) Retract the flaps (Ref. AMM TASK 27-50-00-866-009) . (3) Depressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-864-001) (Ref. AMM TASK 29-24-00-864-001) (Ref. AMM TASK 29-10-00-864-003) . (4) Remove the PIN-SIDE STICK LOCKING (98D27903500000) and the warning notice from each sidestick controller. (5) Close the applicable access panels: (a) FOR 31CE1 (SERVO CTL-SPLR1, L G) · The access panel 573BB (Ref. AMM TASK 57-51-37-400-002) . (b) FOR 31CE2 (SERVO CTL-SPLR1, R G) · The access panel 673BB (Ref. AMM TASK 57-51-37-400-002) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-64-00-040-001-A - Deactivation of the Spoiler Servo Control

(c) FOR 31CE3 (SERVO CTL-SPLR2, L Y) · The access panel 575BB (Ref. AMM TASK 57-51-37-400-004) . (d) FOR 31CE4 (SERVO CTL-SPLR2, R Y) · The access panel 675BB (Ref. AMM TASK 57-51-37-400-004) . (e) FOR 31CE5 (SERVO CTL-SPLR3, L B) · The access panel 575DB (Ref. AMM TASK 57-51-37-400-004) . (f)

FOR 31CE6 (SERVO CTL-SPLR3, R B) · The access panel 675DB (Ref. AMM TASK 57-51-37-400-004) .

(g) FOR 31CE7 (SERVO CTL-SPLR4, L Y) · The access panel 575EB (Ref. AMM TASK 57-51-37-400-004) . (h) FOR 31CE8 (SERVO CTL-SPLR4, R Y) · The access panel 675EB (Ref. AMM TASK 57-51-37-400-004) . (i)

FOR 31CE9 (SERVO CTL-SPLR5, L G) · The access panel 575GB (Ref. AMM TASK 57-51-37-400-004) .

(j)

FOR 31CE10 (SERVO CTL-SPLR5, R G) · The access panel 675GB (Ref. AMM TASK 57-51-37-400-004) .

(6) Remove access platform(s). (7) Make sure that the work area is clean and clear of tools and other items. (8) Make an entry in the log-book and record the defective servocontrol. (9) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-51-00-040-005-A - Deactivation of the Slat and Flap Control Computer (SFCC) No. 2 Slat Channel

** ON A/C ALL TASK 27-51-00-040-005-A Deactivation of the Slat and Flap Control Computer (SFCC) No. 2 Slat Channel 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.

FIN : 21CV , 22CV Task Summary MMEL or CDL Ref MMEL 27-81-01A 1.

Access NO

Test NO

Specific Tools NO

Mhr 01.0

E/T 01.0

Nb Men 1

Reason for the Job MMEL 27-81-01A SFCC Slat Channel NOTE: For the deactivation of the SFCC No. 2 flap channel refer to TASK 27-51-00-040-001.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

QTY AR AR AR

DESIGNATION SAFETY BARRIER(S) SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 128

ZONE DESCRIPTION REAR AVIONIC COMPARTMENT

C. Referenced Information REFERENCE (Ref. 20-16-00-912-001-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02).

DESIGNATION Circuit Breakers Safety Practices Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-51-00-040-005-A - Deactivation of the Slat and Flap Control Computer (SFCC) No. 2 Slat Channel REFERENCE (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 27-54-00-710-002-A). (Ref. 27-80-00-869-004-A). (Ref. 27-81-00-710-001-A). (Ref. 27-84-00-710-001-A). (Ref. 31-32-00-860-001-A). Ref. ESPM 20-10-00 3.

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Operational Test of the Flap and Slat Systems Reset of the Wing Tip Brake (WTB) of the Slat System on the Ground Operational Test of the Wing-Tip Brake and the Pressure-Off Brake Operational Test of the Slat System Procedure to Get Access to the SYSTEM REPORT/TEST Menu Page

Job Set-up Subtask 27-51-00-941-075-A A.

Safety Precautions (1) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations. (2) Put a WARNING NOTICE(S) in position to tell persons not to operate the slats and flaps.

Subtask 27-51-00-861-057-A B.

Energize the Aircraft Electrical Circuits (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

Subtask 27-51-00-865-096-A C.

Table of the circuit breakers used in this procedure: PANEL 121VU

4.

DESIGNATION FLIGHT CONTROLS/WTB/SLT/SYS2

FIN 11CV

LOCATION P19

Procedure Subtask 27-51-00-040-050-A A.

Deactivation of the Slat and Flap Control Computer (SFCC) No.2 Slat Channel (1) When you do this procedure, it can be necessary to open circuit breaker 11CV (Ref. AMM TASK 2016-00-912-001) . (a) This circuit breaker has a red threaded bush. To open this circuit breaker you need a special tool Ref. ESPM 20-10-00 (2) Do this procedure: ACTION 1.On the MCDU: · get access to the Flight Controls (F/CTL) SYSTEM REPORT/TEST page (Ref. AMM TASK 31-32-00-860-001) · push in the key adjacent to < SFCC1 · push in the key adjacent to < SYSTEM STATUS SLAT

RESULT On the MCDU: · the F/CTL SYSTEM REPORT TEST PAGE is shown · the SFCC1 menu is shown · < NO FAULTS > is shown except SLT 1 NO SFCC 2 DATA and/or SLT 1 NO SFCC 2 DATA CHECK WIRING AND SFCC 2

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-51-00-040-005-A - Deactivation of the Slat and Flap Control Computer (SFCC) No. 2 Slat Channel ACTION RESULT · push the key adjacent to < RETURN until the SYSTEM REPORT/TEST F/CTL page is shown · push in the key adjacent to <SFCC2 · the SFCC2 menu is shown NOTE: If the MCDU shows < NO RESPONSE > for SFCC 2, go to paragraph D. · push in the key adjacent to < SYSTEM · the SYSTEM STATUS SLAT page is shown STATUS SLAT · if SLT SYS LOCKED is shown, reset the wing tip brakes of the slat system with SFCC 2 (Ref. AMM TASK 27-80-00-869-004) · if the reset of the WTBs (of the slat system) · the 28V power supply from SFCC 2 to the WTBs with SFCC 2 cannot be completed satisfactoris disconnected. ily, open the circuit breaker 11CV (Ref. AMM TASK 20-16-00-912-001) . · push in the key adjacent to < RETURN until the F/CTL SYSTEM REPORT/TEST page is shown. Subtask 27-51-00-865-078-A B.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU AUTO FLT/FAC1/26VAC 14CC1 B03 ** ON A/C 401-450 49VU AUTO FLT/FAC1/26VAC

14CC1

H09

** ON A/C ALL 121VU

14CC2

M18

FIN 7CV

R21

AUTO FLT/FAC2/26VAC

Subtask 27-51-00-865-118-A C.

Table of the circuit breakers used in this procedure: PANEL 121VU

DESIGNATION FLIGHT CONTROLS/SLT/CTL/SYS2

LOCATION

Subtask 27-51-00-710-074-A D.

Test NOTE: This paragraph is applicable only if the MCDU shows < NO RESPONSE > for SFCC 2. (1) Do the Operational Test of the Slat System (Ref. AMM TASK 27-84-00-710-001) . (a) If the WTB is set due to failure of the Slat 2 channel, the message "FLAPS LEVER ....RECYCLE" will trigger on ECAM. (2) If the message to recycle the Flap control lever shows on ECAM, open the circuit breaker 11CV (Ref. AMM TASK 20-16-00-912-001) .

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-51-00-040-005-A - Deactivation of the Slat and Flap Control Computer (SFCC) No. 2 Slat Channel

NOTE: WTB stays open. Subtask 27-51-00-040-053-A E.

Deactivation of the SFCC No. 2 Slat Channel (Continued) (1) Do the Operational Test of the Flap and Slat Systems (Ref. AMM TASK 27-54-00-710-002) . NOTE: The circuit breaker 11CV stays open (if the c/b 11CV was opened before). (2) Do the WTB/POB test with SFCC No. 1 (slat system) only (Ref. AMM TASK 27-81-00-710-001) . NOTE: The circuit breaker 11CV stays open (if the c/b 11CV was opened before). (3) Make sure that the WTB/POB test was successful and that the MCDU shows: SFCC 1 DATE: XXX XX__ UTC: XXXX PERFORMED NO FAULTS RESULT NOT STORED. NOTE: The aircraft can only dispatched if the WTB/POB test was successful. (4) Put the aircraft back to its initial configuration: (a) On the MCDU, push the key adjacent to < RETURN until the CFDS MENU page is shown. (b) On the MCDU, push the MCDU MENU key and make sure that the MCDU MAIN MENU is shown. (5) Deactivation of the SFCC 2 slat channel: (a) Open and safety circuit breaker 7CV. (b) Attach a WARNING NOTICE(S) to the circuit breaker 7CV (in the cockpit) to tell persons that the slat channel for SFCC 2 is deactivated. (c) Make an entry in the aircraft technical logbook that the SFCC No. 2 slat channel is deactivated. (6) If the circuit breaker 11CV, was opened in the test procedure: · attach a WARNING NOTICE(S) to the circuit breaker 11CV (in the cockpit) to tell persons that the 28V power supply (from SFCC 2 to the WTB) is disconnected (Ref. AMM TASK 20-16-00-912001) .

Subtask 27-51-00-869-065-A F.

Cockpit Effects (1) On the ECAM EWD: · The message 'F/CTL SLAT SYS 2 FAULT' shows. (2) On the STATUS SD page: · The message 'F/CTL MAINTENANCE' can show. · The message 'SFCS MAINTENANCE' can show. NOTE: These status messages will only show in flight phases 1 and 10. (3) On the STATUS SD page: · The message 'SLATS SLOW' shows.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-51-00-040-005-A - Deactivation of the Slat and Flap Control Computer (SFCC) No. 2 Slat Channel

NOTE: This status message will not show in flight phases 1 and 10. (4) Make an entry in the aircraft technical logbook that the SFCC 2 Slat Channel is deactivated. 5.

Close-up Subtask 27-51-00-862-058-A A.

De-energize the Aircraft Electrical Circuits (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Subtask 27-51-00-865-105-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 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU AUTO FLT/FAC1/26VAC 14CC1 B03 ** ON A/C 401-450 49VU AUTO FLT/FAC1/26VAC

14CC1

H09

** ON A/C ALL 121VU

14CC2

M18

AUTO FLT/FAC2/26VAC

Subtask 27-51-00-942-070-A C.

Removal of Equipment (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the safety barriers. (3) Remove the WARNING NOTICE(S). (4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-81-00-040-001-A - Slat WTB Solenoids - WTB Test Procedure

** ON A/C ALL TASK 27-81-00-040-001-A Slat WTB Solenoids - WTB Test Procedure 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.

FIN : 21CV Task Summary MMEL or CDL Ref MMEL 27-81-02A

Access NO

1.

Reason for the Job MMEL 27-81-02A Slat Wing Tip Brakes Solenoid

2

Job Set-up Information A.

QTY AR AR AR

Mhr 01.0

E/T 01.0

Nb Men 1

DESIGNATION SAFETY BARRIER(S) SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 27-81-00-710-001-A).

3.

Specific Tools NO

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

Test NO

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) Operational Test of the Wing-Tip Brake and the Pressure-Off Brake

Job Set-up Subtask 27-81-00-941-059-A A.

Safety Precautions (1) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations. (2) Put a WARNING NOTICE(S) in the cockpit to tell persons not to operate the slat system.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-81-00-040-001-A - Slat WTB Solenoids - WTB Test Procedure

Subtask 27-81-00-861-054-A B.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) In the deactivation procedure that follows it is necessary to do the WTB/POB test with SFCC 1 (Ref. AMM TASK 27-81-00-710-001) . Prepare to pressurize the hydraulic systems.

Subtask 27-81-00-865-070-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU

4.

DESIGNATION FLIGHT CONTROLS/FLP/CTL AND/ MONG/SYS2 FLIGHT CONTROLS/SLT/CTL/SYS2

FIN 8CV

LOCATION Q21

7CV

R21

Procedure Subtask 27-81-00-040-050-A A.

Slat WTB Solenoids - WTB Test Procedure (1) Do the WTB/POB test with SFCC No. 1 (slat system) (Ref. AMM TASK 27-81-00-710-001) . (2) Make sure that the WTB/POB test was successful and that the MCDU shows: SFCC 1 DATE: XXX XX__ UTC: XXXX PERFORMED NO FAULTS RESULT NOT STORED NOTE: You can only dispatch the aircraft if the WTB/POB test was successful. (3) Put the aircraft back to its initial configuration. (a) On the MCDU, push the key adjacent to < RETURN until the CFDS Menu page is shown. (b) On the MCDU, push the MCDU MENU key and make sure that the MCDU MAIN Menu is shown.

5.

Close-up Subtask 27-81-00-865-073-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION FLIGHT CONTROLS/FLP/CTL AND/ MONG/SYS2 FLIGHT CONTROLS/SLT/CTL/SYS2

FIN 8CV

Q21

LOCATION

7CV

R21

Subtask 27-81-00-942-056-A B.

Removal of Equipment (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the safety barriers. (3) Remove the WARNING NOTICE(S).

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-81-00-040-001-A - Slat WTB Solenoids - WTB Test Procedure

(4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-92-00-040-003-A - Operational Test of the Thrust Reverser System

** ON A/C ALL TASK 27-92-00-040-003-A Operational Test of the Thrust Reverser System 1.

Reason for the Job MMEL 27-92-02A Ground Spoiler Control System (FAA only)

2

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS 210

B.

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 78-31-00-710-041-A). Operational Test of the Thrust Reverser System with the CFDS (Ref. 78-31-00-710-041-A-02). Operational test of the Thrust Reverser without the CFDS and Engine Running ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 78-31-00-710-042-A). Operational Test of the Thrust Reverser System ** ON A/C 301-349, 351-450, 500-600 (Ref. 78-31-00-710-805-A). Operational Test of Thrust Reverser with MCDU (Ref. 78-31-00-710-805-A-01). Thrust Reverser Cycling Test (Engine Running) ** ON A/C ALL 3.

Job Set-up Subtask 27-92-00-861-052-A A.

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

Subtask 27-92-00-865-052-A B.

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

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-92-00-040-003-A - Operational Test of the Thrust Reverser System

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU FLIGHT CONTROLS/SEC1/NORM/SPLY 21CE1 B08 ** ON A/C 401-450 49VU FLIGHT CONTROLS/SEC1/NORM/SPLY 21CE1

B03

** ON A/C ALL 105VU 121VU 121VU

B01 Q19 Q18

FLT CTL/SEC1/STBY SPLY FLIGHT CONTROLS/SEC3/SPLY FLIGHT CONTROLS/SEC2/SPLY

22CE 21CE3 21CE2

Subtask 27-92-00-860-054-A C.

Aircraft Maintenance Configuration (1) On the FLT CTL panel 23VU: · make sure that the FLT CTL/SEC 1 pushbutton switch is pushed (on this pushbutton switch, the FAULT and OFF legends are off). (2) On the FLT CTL panel 24VU: · make sure that the FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches are pushed (on these pushbutton switches, the FAULT and OFF legends are off).

4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 Subtask 27-92-00-710-052-B A.

Do the operational test of the thrust reverser system (Ref. AMM TASK 78-31-00-710-041)

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Subtask 27-92-00-710-052-E A.

Do the operational test of the thrust reverser system (Ref. AMM TASK 78-31-00-710-042)

** ON A/C 301-349, 351-450, 500-600 Subtask 27-92-00-710-052-G A.

Do the operational test of the thrust reverser system (Ref. AMM TASK 78-31-00-710-805) .

** ON A/C ALL 5.

Close-up Subtask 27-92-00-862-051-A A.

Put the aircraft back to its initial configuration. (1) Make an applicable entry in the logbook. (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-93-00-040-001-A - Deactivation of the Elevator Aileron Computer

** ON A/C ALL TASK 27-93-00-040-001-A Deactivation of the Elevator Aileron Computer

FIN : 2CE1 , 2CE2 1.

Reason for the Job MMEL 27-93-01A ELAC 1

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 210 822

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 29-23-00-863-001-A). (Ref. 29-23-00-864-001-A). (Ref. 29-24-00-863-001-A). (Ref. 29-24-00-864-001-A). 3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump Depressurize the Green and Yellow Hydraulic Systems after Operation of the PTU Pressurize the Yellow Hydraulic System with the Electric Pump Depressurize the Yellow Hydraulic System

Job Set-up Subtask 27-93-00-861-051-A A.

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

Subtask 27-93-00-010-051-A B.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the access door 822.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-93-00-040-001-A - Deactivation of the Elevator Aileron Computer

(2) Open the access door 822. (3) On the battery power center 105VU: · loosen the two screws and remove the protective cover. Subtask 27-93-00-865-051-A C.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 49VU

DESIGNATION L/G/LGCIU/SYS1/NORM NAV PROBES/ADIRU 1/AND AOA 1/ 26VAC NAV PROBES/ADIRU1/115VAC

FIN 1GA 5FP1

C09 F07

LOCATION

4FP1

F06

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU FLIGHT CONTROLS/ELAC1/NORM/ 15CE1 B11 SPLY 49VU FLIGHT CONTROLS/FCDC1/SPLY 20CE1 B10 49VU FLIGHT CONTROLS/THS/ACTR/MOT2 19CE2 B09 49VU FLIGHT CONTROLS/SEC1/NORM/SPLY 21CE1 B08 49VU FLIGHT CONTROLS/FLP/CTL AND 6CV B07 MONG/SYS1 49VU FLIGHT CONTROLS/SLT/CTL AND 5CV B06 MONG/SYS1 49VU AUTO FLT/FAC1/28VDC 5CC1 B04 49VU AUTO FLT/FAC1/26VAC 14CC1 B03 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP

F09

** ON A/C 301-349, 351-450, 500-600 49VU NAV PROBES/ADIRU3/PWR/SWTG

8FP

F08

15CE1

B06

20CE1 19CE2 21CE1 6CV

B05 B04 B03 B02

5CV

B01

5CC1 14CC1

H10 H09

FLIGHT CONTROLS/ELAC2/STBY SPLY 16CE2 FLT CTL/ELAC1/STBY SPLY 16CE1 FLT CTL/SEC1/STBY SPLY 22CE ADIRS/ADIRU1/28VDC 6FP1 ELEC/HOT BUS/702PP SPLY 5PB2

A02 A01 B01 C02 D02

** ON A/C 401-450 49VU FLIGHT CONTROLS/ELAC1/NORM/ SPLY 49VU FLIGHT CONTROLS/FCDC1/SPLY 49VU FLIGHT CONTROLS/THS/ACTR/MOT2 49VU FLIGHT CONTROLS/SEC1/NORM/SPLY 49VU FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 49VU FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 49VU AUTO FLT/FAC1/28VDC 49VU AUTO FLT/FAC1/26VAC ** ON A/C ALL 105VU 105VU 105VU 105VU 105VU

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-93-00-040-001-A - Deactivation of the Elevator Aileron Computer

PANEL 105VU 105VU 105VU 121VU 121VU 121VU 121VU

DESIGNATION ELEC/HOT BUS/701PP SPLY ELEC/HOT BUS/702PP SPLY ELEC/HOT BUS/701PP SPLY COM NAV/RAD ALTM/2 COM NAV/RAD ALTM/1 AUTO FLT/FAC2/28VDC AUTO FLT/FAC2/26VAC

FIN 5PB1 12PB2 12PB1 1SA2 1SA1 5CC2 14CC2

D01 E02 E01 K12 K11 M19 M18

LOCATION

EMB SB 23-1485 for A/C 210-210 121VU ADIRS/ADIRU/3PWR/SWTG 121VU ADIRS/ADIRU/2/26VAC AND AOA 121VU ADIRS/ADIRU/3/26VAC AND AOA 121VU ADIRS/ADIRU/2/115VAC 121VU ADIRS/ADIRU/3/115VAC 121VU ADIRS/ADIRU/2/28VDC 121VU ADIRS/ADIRU/3/28VDC

9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N09 N08 N07 N06 N05 N04 N03

** ON A/C ALL 121VU 121VU 121VU 121VU 121VU

12CV 11CV 2GA 52GA 8CV

P20 P19 Q35 Q34 Q21

21CE3 21CE2 19CE3 19CE1 7CV 15CE2

Q19 Q18 Q17 Q16 R21 R20

** ON A/C ALL

121VU 121VU 121VU 121VU 121VU 121VU

FLIGHT CONTROLS/WTB/FLP/SYS2 FLIGHT CONTROLS/WTB/SLT/SYS2 HYDRAULIC/LGCIU/SYS2 HYDRAULIC/LGCIU/SYS1/GRND SPLY FLIGHT CONTROLS/FLP/CTL AND/ MONG/SYS2 FLIGHT CONTROLS/SEC3/SPLY FLIGHT CONTROLS/SEC2/SPLY FLIGHT CONTROLS/THS ACTR/MOT3 FLIGHT CONTROLS/THS ACTR/MOT1 FLIGHT CONTROLS/SLT/CTL/SYS2 FLIGHT CONTROLS/ELAC2/NORM/ SPLY

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-325, 331-332, 350-350

4.

EMB SB 23-1485 for A/C 210-210 121VU ADIRS/ADIRU/2PWR/SHED

10FP

N10

** ON A/C 326-330, 333-349, 351-450, 500-600 121VU ADIRS/2PWR/SHED &/AOA2 MON

10FP

N10

** ON A/C ALL 122VU 122VU

10CV 9CV

S07 S06

FLIGHT CONTROLS/WTB/FLP/SYS1 FLIGHT CONTROLS/WTB/SLT/SYS1

Procedure Subtask 27-93-00-040-050-A A.

If the ELAC 1 FAULT warning is in view on the upper ECAM display unit:

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-93-00-040-001-A - Deactivation of the Elevator Aileron Computer

(1) On the overhead panel 23VU, make sure that: · the FAULT legend of the FLT CTL/ELAC 1 pushbutton switch is on. (2) On the overhead panel 23VU, release the FLT CTL/ELAC 1 pushbutton switch (on this pushbutton switch, the OFF legend comes on). (3) On the overhead panel 24VU, make sure that: · the FLT CTL/ELAC 2 pushbutton switch is pushed (on this pushbutton switch, the OFF and FAULT legends are off). (4) Do the test paragraph C. only. Subtask 27-93-00-040-051-A B.

If the ELAC 1 PITCH FAULT warning is in view on the upper ECAM display unit: (1) Do the tests paragraphs C. and D.

Subtask 27-93-00-710-051-C C.

For the ELAC 1 FAULT or ELAC 1 PITCH FAULT warning: (1) Do this test before each flight: ACTION RESULT 1.On the center pedestal, on one MCDU, push The MCDU shows the MDCU MENU page. the MCDU MENU mode key. 2.Push the line key adjacent to the CFDS indica- The MCDU shows the CFDS MENU page. tion. 3.Push the line key adjacent to the SYSTEM RE- The MCDU shows the SYSTEM REPORT/TEST PORT/TEST indication. page. 4.Push the line key adjacent to the F/CTL indica- The MCDU shows the F/CTL page. tion. 5.Push the line key adjacent to the EFCS1 indica- The MCDU shows the EFCS1 page. tion. 6.Push the line key adjacent to the GROUND The MCDU shows the EFCS1 GROUND SCAN SCAN indication. page. 7.Push the line key adjacent to the START GROUND SCAN indication. 8.After two minutes, push the line key adjacent to the GROUND SCAN STOP indication. 9.Push the line key adjacent to the GROUND RE- Make sure that none of the following CFDS fault PORT indication. messages are present: · CFDS fault messages concerning accelerometers 3 (12CE3) and 4 (12CE4) and sidestick: ELAC2 MON OR WIRING FROM ACCLRM3 12CE3, ELAC2 COM OR WIRING FROM ACCLRM3 12CE3, ACCLRM3 12CE3, SEC2 OR WIRING FROM ACCLRM3 12CE3, ELAC2 MON OR WIRING FROM ACCLRM4 12CE4, ELAC2 COM OR WIRING FROM ACCLRM4 12CE4, ACCLRM4 12CE4, SEC2 OR WIRING FROM ACCLRM4 12CE4,

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-93-00-040-001-A - Deactivation of the Elevator Aileron Computer

ACTION

10.On the MCDU, push the line select key adjacent to the RETURN indication until the CFDS menu page comes into view.

RESULT ELAC2 OR INPUT OF CAPT ROLL CTL SSTU 4CE1, ELAC2 OR INPUT OF F/O ROLL CTL SSTU 4CE2, ELAC2 OR INPUT OF CAPT PITCH CTL SSTU 4CE3, ELAC2 OR INPUT OF F/O PITCH CTL SSTU 4CE4, SEC1(2)(3) OR INPUT OF CAPT ROLL CTL SSTU 4CE1, SEC1(2)(3) OR INPUT OF F/O ROLL CTL SSTU 4CE2, SEC1(2) OR INPUT OF CAPT PITCH CTL SSTU 4CE3, SEC1(2) OR INPUT OF F/O PITCH CTL SSTU 4CE4, CAPT ROLL CTL SSTU 4CE1, F/O ROLL CTL SSTU 4CE2, CAPT PITCH CTL SSTU 4CE3, F/O PITCH CTL SSTU 4CE4. · CFDS fault messages concerning SEC1 or SEC2 pitch changeover logic or to SEC2 pitch control failure: CHECK PITCH CHANGE OVER OF SEC1, CHECK PITCH CHANGE OVER OF SEC2, SEC2 OR WIRING FROM L G ELEV POS XCDR 34CE1, SEC2 OR WIRING FROM R Y ELEV POS XCDR 34CE2, SEC2 OR WIRING FROM L ELEV POS MON XCDR, SEC2 OR WIRING FROM R ELEV POS MON XCDR, SEC2 COM OR WIRING TO L G ELEV SERVO VLV 34CE1, SEC2 COM OR WIRING TO R Y ELEV SERVO VLV 34CE2, SEC2 MON OR WIRING TO L G ELEV SERVO VLV 34CE1, SEC2 MON OR WIRING TO R Y ELEV SERVO VLV 34CE2, SEC2 OR WIRING FROM L B ELEV MODE XCDR 34CE3, SEC2 OR WIRING FROM R B ELEV MODE XCDR 34CE4, SEC2 MON OR WIRING TO L B ELEV SOL VLV 34CE3, SEC2 MON OR WIRING TO R B ELEV SOL VLV 34CE4. The MCDU shows the MCDU MENU page.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-93-00-040-001-A - Deactivation of the Elevator Aileron Computer

Subtask 27-93-00-710-052-A D.

For the ELAC 1 PITCH FAULT warning: (1) Do this test: ACTION RESULT 1.On the overhead panel 23VU: On the overhead panel 23VU: · release the FLT CTL/SEC 1 pushbutton switch. · the OFF legend of the FLT CTL/SEC 1 pushbutton switch comes on. 2.On the overhead panel 24VU: On the overhead panel 24VU: · release the FLT CTL/SEC 2 pushbutton switch · the OFF legend of the FLT CTL/SEC 2 pushbut· release the FLT CTL/ELAC 2 pushbutton ton switch comes on. switch. · the OFF legend of the FLT CTL/ELAC 2 pushbutton switch comes on. 3.Pressurize the Green and Yellow hydraulic systems (Ref. AMM TASK 29-23-00-863-001) (Ref. AMM TASK 29-24-00-863-001) . 4.On the panel 114VU: · make sure that the FLAPS control lever is in the 0 position. 5.On the center pedestal: The THS moves out of the neutral position. · move the THS with the pitch-trim control wheels out of the neutral position. 6.On the overhead panel 24VU: On the overhead panel 24VU: · push the FLT CTL/SEC 2 pushbutton switch. · the OFF legend of the FLT CTL/SEC 2 pushbutton switch goes off. The THS must return to the neutral position (electric motor 3 in operation).

5.

Close-up Subtask 27-93-00-860-050-A A.

Put the aircraft back to its initial configuration. (1) For the ELAC 1 FAULT warning : (a) Put a WARNING NOTICE(S) on the FLT CTL/ELAC 1 pushbutton switch, to tell the crew that the ELAC 1 is deactivated. (b) Open the circuit breakers 15CE1 and 16CE1. (c) Make an entry in the log-book. (2) For the ELAC 1 PITCH FAULT warning : (a) On the overhead panel 23VU, push the FLT CTL/SEC 1 pushbutton switch (on this pushbutton switch, the OFF legend goes off). (b) On the overhead panel 24VU, push the FLT CTL/ELAC 2 pushbutton switch (on this pushbutton switch, the OFF legend goes off). (c) Depressurize the Green and Yellow hydraulic systems (Ref. AMM TASK 29-23-00-864-001) (Ref. AMM TASK 29-24-00-864-001) .

Subtask 27-93-00-862-051-A B.

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

Subtask 27-93-00-410-051-A Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-93-00-040-001-A - Deactivation of the Elevator Aileron Computer

C.

Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close the access door 822. (4) Remove the access platform(s).

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-94-00-040-002-A - Deactivation of the Spoiler Elevator Computer (SEC)

** ON A/C ALL TASK 27-94-00-040-002-A Deactivation of the Spoiler Elevator Computer (SEC)

FIN : 1CE1 , 1CE2 1.

Reason for the Job MMEL 27-94-01A SEC 1 MMEL 27-94-02A SEC 2

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 210 822

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up Subtask 27-94-00-860-054-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) On the overhead panel, on the FLT CTL panel 23VU: · Make sure that the FLT CTL/ELAC1 pushbutton switch is pushed. (On this pushbutton switch the OFF legend is off). (3) On the overhead panel, on the FLT CTL panel 24VU · Make sure that the FLT CTL/ELAC2 pushbutton switch is pushed. (On this pushbutton switch the OFF legend is off).

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-94-00-040-002-A - Deactivation of the Spoiler Elevator Computer (SEC)

Subtask 27-94-00-010-053-A B.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at access door 822. (2) Open access door 822. (3) At the battery power center 105VU: · Loosen the two screws and remove the protective cover.

Subtask 27-94-00-865-053-A C.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 49VU

DESIGNATION L/G/LGCIU/SYS1/NORM NAV PROBES/ADIRU 1/AND AOA 1/ 26VAC NAV PROBES/ADIRU1/115VAC

FIN 1GA 5FP1

C09 F07

LOCATION

4FP1

F06

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU FLIGHT CONTROLS/ELAC1/NORM/ 15CE1 B11 SPLY 49VU FLIGHT CONTROLS/SEC1/NORM/SPLY 21CE1 B08 49VU FLIGHT CONTROLS/FLP/CTL AND 6CV B07 MONG/SYS1 49VU FLIGHT CONTROLS/SLT/CTL AND 5CV B06 MONG/SYS1 49VU AUTO FLT/FAC1/28VDC 5CC1 B04 49VU AUTO FLT/FAC1/26VAC 14CC1 B03 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP

F09

** ON A/C 301-349, 351-450, 500-600 49VU NAV PROBES/ADIRU3/PWR/SWTG

8FP

F08

15CE1

B06

21CE1 6CV

B03 B02

5CV

B01

5CC1 14CC1

H10 H09

FLIGHT CONTROLS/ELAC2/STBY SPLY 16CE2 FLT CTL/ELAC1/STBY SPLY 16CE1 FLT CTL/SEC1/STBY SPLY 22CE ADIRS/ADIRU1/28VDC 6FP1 ELEC/HOT BUS/702PP SPLY 5PB2 ELEC/HOT BUS/701PP SPLY 5PB1

A02 A01 B01 C02 D02 D01

** ON A/C 401-450 49VU FLIGHT CONTROLS/ELAC1/NORM/ SPLY 49VU FLIGHT CONTROLS/SEC1/NORM/SPLY 49VU FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 49VU FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 49VU AUTO FLT/FAC1/28VDC 49VU AUTO FLT/FAC1/26VAC ** ON A/C ALL 105VU 105VU 105VU 105VU 105VU 105VU

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-94-00-040-002-A - Deactivation of the Spoiler Elevator Computer (SEC)

PANEL 105VU 105VU 121VU 121VU 121VU 121VU

DESIGNATION ELEC/HOT BUS/702PP SPLY ELEC/HOT BUS/701PP SPLY COM NAV/RAD ALTM/2 COM NAV/RAD ALTM/1 AUTO FLT/FAC2/28VDC AUTO FLT/FAC2/26VAC

FIN 12PB2 12PB1 1SA2 1SA1 5CC2 14CC2

E02 E01 K12 K11 M19 M18

LOCATION

EMB SB 23-1485 for A/C 210-210 121VU ADIRS/ADIRU/3PWR/SWTG 121VU ADIRS/ADIRU/2/26VAC AND AOA 121VU ADIRS/ADIRU/3/26VAC AND AOA 121VU ADIRS/ADIRU/2/115VAC 121VU ADIRS/ADIRU/3/115VAC 121VU ADIRS/ADIRU/2/28VDC 121VU ADIRS/ADIRU/3/28VDC

9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N09 N08 N07 N06 N05 N04 N03

** ON A/C ALL 121VU 121VU 121VU 121VU 121VU

12CV 11CV 2GA 52GA 8CV

P20 P19 Q35 Q34 Q21

21CE3 21CE2 7CV 15CE2

Q19 Q18 R21 R20

** ON A/C ALL

121VU 121VU 121VU 121VU

FLIGHT CONTROLS/WTB/FLP/SYS2 FLIGHT CONTROLS/WTB/SLT/SYS2 HYDRAULIC/LGCIU/SYS2 HYDRAULIC/LGCIU/SYS1/GRND SPLY FLIGHT CONTROLS/FLP/CTL AND/ MONG/SYS2 FLIGHT CONTROLS/SEC3/SPLY FLIGHT CONTROLS/SEC2/SPLY FLIGHT CONTROLS/SLT/CTL/SYS2 FLIGHT CONTROLS/ELAC2/NORM/ SPLY

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-325, 331-332, 350-350

4.

EMB SB 23-1485 for A/C 210-210 121VU ADIRS/ADIRU/2PWR/SHED

10FP

N10

** ON A/C 326-330, 333-349, 351-450, 500-600 121VU ADIRS/2PWR/SHED &/AOA2 MON

10FP

N10

** ON A/C ALL 122VU 122VU

10CV 9CV

S07 S06

FLIGHT CONTROLS/WTB/FLP/SYS1 FLIGHT CONTROLS/WTB/SLT/SYS1

Procedure Subtask 27-94-00-040-050-B A.

Deactivation of the Spoiler Elevator Computer (SEC1) or (SEC2) (1) Do this test before each flight:

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-94-00-040-002-A - Deactivation of the Spoiler Elevator Computer (SEC)

ACTION 1.Open circuit breakers 21CE1 and 22CE (SEC1), or 21CE2 (SEC2).

RESULT

NOTE: The spoilers related to the SEC deactivated will not operate. 2.On the center pedestal, on one MCDU, push the MCDU MENU mode key. 3.Push the line key adjacent to the CFDS indication. 4.Push the line key adjacent to the SYSTEM REPORT/TEST indication. 5.Push the line key adjacent to the F/CTL indication. 6.Push the line key adjacent to the EFCS1(2) indication. 7.Push the line key adjacent to the GROUND SCAN indication. 8.Push the line key adjacent to the START GROUND SCAN indication and wait for two minutes. 9.Push the line key adjacent to the GROUND SCAN STOP indication. 10.Push the line key adjacent to the GROUND REPORT indication.

The MCDU shows the MCDU MENU page. The MCDU shows the CFDS MENU page. The MCDU shows the SYSTEM REPORT/TEST page. The MCDU shows the F/CTL page. The MCDU shows the EFCS1(2) page. The MCDU shows the EFCS1(2) GROUND SCAN page.

Make sure that none of the CFDS fault messages that follow are there: · CFDS fault messages related to sidestick: ELAC1(2) OR INPUT OF CAPT ROLL CTL SSTU 4CE1, ELAC1(2) OR INPUT OF F/O ROLL CTL SSTU 4CE2, ELAC1(2) OR INPUT OF CAPT PITCH CTL SSTU 4CE3, ELAC1(2) OR INPUT OF F/O PITCH CTL SSTU 4CE4, SEC1(2)(3) (the non defective SECs) OR INPUT OF CAPT ROLL CTL SSTU 4CE1, SEC1(2)(3) (the non defective SECs) OR INPUT OF F/O ROLL CTL SSTU 4CE2, SEC1(2) (the non defective SECs) OR INPUT OF CAPT PITCH CTL SSTU 4CE3, SEC1(2) (the non defective SECs) OR INPUT OF F/O PITCH CTL SSTU 4CE4, CAPT ROLL CTL SSTU 4CE1, F/O ROLL CTL SSTU 4CE2, CAPT PITCH CTL SSTU 4CE3 and F/O PITCH CTL SSTU 4CE4. · CFDS fault messages related to pitch control from the opposite SEC, if SEC1 not in operation: CHECK PITCH CHANGE OVER OF SEC2, SEC2 OR WIRING FROM L G ELEV POS XCDR 34CE1,

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-94-00-040-002-A - Deactivation of the Spoiler Elevator Computer (SEC)

ACTION

11.On the MCDU, push the line select key adjacent to the RETURN indication until the CFDS menu page comes into view.

RESULT SEC2 OR WIRING FROM R Y ELEV POS XCDR 34CE2, SEC2 OR WIRING FROM L ELEV POS MON XCDR, SEC2 OR WIRING FROM R ELEV POS MON XCDR, SEC2 COM OR WIRING TO L G ELEV SERVO VLV 34CE1, SEC2 COM OR WIRING TO R Y ELEV SERVO VLV 34CE2, SEC2 MON OR WIRING TO L G ELEV SERVO VLV 34CE1, SEC2 MON OR WIRING TO R Y ELEV SERVO VLV 34CE2, SEC2 OR WIRING FROM L B ELEV MODE XCDR 34CE3, SEC2 OR WIRING FROM R B ELEV MODE XCDR 34CE4, SEC2 MON OR WIRING TO L B ELEV SOL VLV 34CE3 and SEC2 MON OR WIRING TO R B ELEV SOL VLV 34CE4. · CFDS fault messages related to pitch control from the opposite SEC, if SEC2 not in operation: CHECK PITCH CHANGE OVER OF SEC1, SEC1 OR WIRING FROM L B ELEV POS XCDR 34CE3, SEC1 OR WIRING FROM R B ELEV POS XCDR 34CE4, SEC1 OR WIRING FROM L ELEV POS MON XCDR, SEC1 OR WIRING FROM R ELEV POS MON XCDR, SEC1 COM OR WIRING TO L B ELEV SERVO VLV 34CE3, SEC1 COM OR WIRING TO R B ELEV SERVO VLV 34CE4, SEC1 MON OR WIRING TO L B ELEV SERVO VLV 34CE3, SEC1 MON OR WIRING TO R B ELEV SERVO VLV 34CE4, SEC1 OR WIRING FROM L G ELEV MODE XCDR 34CE1, SEC1 OR WIRING FROM R Y ELEV MODE XCDR 34CE2, SEC1 MON OR WIRING TO L G ELEV SOL VLV 34CE1 and SEC1 MON OR WIRING TO R Y ELEV SOL VLV 34CE2. The MCDU shows the MCDU MENU page.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-94-00-040-002-A - Deactivation of the Spoiler Elevator Computer (SEC)

5.

Close-up Subtask 27-94-00-410-053-A A.

Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close access door 822. (4) Remove the access platform(s).

Subtask 27-94-00-860-057-A B.

Aircraft Maintenance Configuration (1) On the overhead panel, on the FLT CTL panel 23VU or 24VU, put a WARNING NOTICE(S) on the pushbutton switch related to the SEC that you deactivated. (2) Make an entry in the log book. (3) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-94-00-040-002-A - Deactivation of the Spoiler Elevator Computer (SEC)

** ON A/C ALL TASK 27-94-00-040-002-A Deactivation of the Spoiler Elevator Computer (SEC)

FIN : 1CE1 , 1CE2 1.

Reason for the Job MMEL 27-94-01A SEC 1 MMEL 27-94-02A SEC 2

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION 1 ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 210 822

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up Subtask 27-94-00-860-054-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) On the overhead panel, on the FLT CTL panel 23VU: · Make sure that the FLT CTL/ELAC1 pushbutton switch is pushed. (On this pushbutton switch the OFF legend is off). (3) On the overhead panel, on the FLT CTL panel 24VU · Make sure that the FLT CTL/ELAC2 pushbutton switch is pushed. (On this pushbutton switch the OFF legend is off).

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-94-00-040-002-A - Deactivation of the Spoiler Elevator Computer (SEC)

Subtask 27-94-00-010-053-A B.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at access door 822. (2) Open access door 822. (3) At the battery power center 105VU: · Loosen the two screws and remove the protective cover.

Subtask 27-94-00-865-053-A C.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 49VU

DESIGNATION L/G/LGCIU/SYS1/NORM NAV PROBES/ADIRU 1/AND AOA 1/ 26VAC NAV PROBES/ADIRU1/115VAC

FIN 1GA 5FP1

C09 F07

LOCATION

4FP1

F06

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU FLIGHT CONTROLS/ELAC1/NORM/ 15CE1 B11 SPLY 49VU FLIGHT CONTROLS/SEC1/NORM/SPLY 21CE1 B08 49VU FLIGHT CONTROLS/FLP/CTL AND 6CV B07 MONG/SYS1 49VU FLIGHT CONTROLS/SLT/CTL AND 5CV B06 MONG/SYS1 49VU AUTO FLT/FAC1/28VDC 5CC1 B04 49VU AUTO FLT/FAC1/26VAC 14CC1 B03 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP

F09

** ON A/C 301-349, 351-450, 500-600 49VU NAV PROBES/ADIRU3/PWR/SWTG

8FP

F08

15CE1

B06

21CE1 6CV

B03 B02

5CV

B01

5CC1 14CC1

H10 H09

FLIGHT CONTROLS/ELAC2/STBY SPLY 16CE2 FLT CTL/ELAC1/STBY SPLY 16CE1 FLT CTL/SEC1/STBY SPLY 22CE ADIRS/ADIRU1/28VDC 6FP1 ELEC/HOT BUS/702PP SPLY 5PB2 ELEC/HOT BUS/701PP SPLY 5PB1

A02 A01 B01 C02 D02 D01

** ON A/C 401-450 49VU FLIGHT CONTROLS/ELAC1/NORM/ SPLY 49VU FLIGHT CONTROLS/SEC1/NORM/SPLY 49VU FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 49VU FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 49VU AUTO FLT/FAC1/28VDC 49VU AUTO FLT/FAC1/26VAC ** ON A/C ALL 105VU 105VU 105VU 105VU 105VU 105VU

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-94-00-040-002-A - Deactivation of the Spoiler Elevator Computer (SEC)

PANEL 105VU 105VU 121VU 121VU 121VU 121VU

DESIGNATION ELEC/HOT BUS/702PP SPLY ELEC/HOT BUS/701PP SPLY COM NAV/RAD ALTM/2 COM NAV/RAD ALTM/1 AUTO FLT/FAC2/28VDC AUTO FLT/FAC2/26VAC

FIN 12PB2 12PB1 1SA2 1SA1 5CC2 14CC2

E02 E01 K12 K11 M19 M18

LOCATION

EMB SB 23-1485 for A/C 210-210 121VU ADIRS/ADIRU/3PWR/SWTG 121VU ADIRS/ADIRU/2/26VAC AND AOA 121VU ADIRS/ADIRU/3/26VAC AND AOA 121VU ADIRS/ADIRU/2/115VAC 121VU ADIRS/ADIRU/3/115VAC 121VU ADIRS/ADIRU/2/28VDC 121VU ADIRS/ADIRU/3/28VDC

9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N09 N08 N07 N06 N05 N04 N03

** ON A/C ALL 121VU 121VU 121VU 121VU 121VU

12CV 11CV 2GA 52GA 8CV

P20 P19 Q35 Q34 Q21

21CE3 21CE2 7CV 15CE2

Q19 Q18 R21 R20

** ON A/C ALL

121VU 121VU 121VU 121VU

FLIGHT CONTROLS/WTB/FLP/SYS2 FLIGHT CONTROLS/WTB/SLT/SYS2 HYDRAULIC/LGCIU/SYS2 HYDRAULIC/LGCIU/SYS1/GRND SPLY FLIGHT CONTROLS/FLP/CTL AND/ MONG/SYS2 FLIGHT CONTROLS/SEC3/SPLY FLIGHT CONTROLS/SEC2/SPLY FLIGHT CONTROLS/SLT/CTL/SYS2 FLIGHT CONTROLS/ELAC2/NORM/ SPLY

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-325, 331-332, 350-350

4.

EMB SB 23-1485 for A/C 210-210 121VU ADIRS/ADIRU/2PWR/SHED

10FP

N10

** ON A/C 326-330, 333-349, 351-450, 500-600 121VU ADIRS/2PWR/SHED &/AOA2 MON

10FP

N10

** ON A/C ALL 122VU 122VU

10CV 9CV

S07 S06

FLIGHT CONTROLS/WTB/FLP/SYS1 FLIGHT CONTROLS/WTB/SLT/SYS1

Procedure Subtask 27-94-00-040-050-B A.

Deactivation of the Spoiler Elevator Computer (SEC1) or (SEC2) (1) Do this test before each flight:

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-94-00-040-002-A - Deactivation of the Spoiler Elevator Computer (SEC)

ACTION 1.Open circuit breakers 21CE1 and 22CE (SEC1), or 21CE2 (SEC2).

RESULT

NOTE: The spoilers related to the SEC deactivated will not operate. 2.On the center pedestal, on one MCDU, push the MCDU MENU mode key. 3.Push the line key adjacent to the CFDS indication. 4.Push the line key adjacent to the SYSTEM REPORT/TEST indication. 5.Push the line key adjacent to the F/CTL indication. 6.Push the line key adjacent to the EFCS1(2) indication. 7.Push the line key adjacent to the GROUND SCAN indication. 8.Push the line key adjacent to the START GROUND SCAN indication and wait for two minutes. 9.Push the line key adjacent to the GROUND SCAN STOP indication. 10.Push the line key adjacent to the GROUND REPORT indication.

The MCDU shows the MCDU MENU page. The MCDU shows the CFDS MENU page. The MCDU shows the SYSTEM REPORT/TEST page. The MCDU shows the F/CTL page. The MCDU shows the EFCS1(2) page. The MCDU shows the EFCS1(2) GROUND SCAN page.

Make sure that none of the CFDS fault messages that follow are there: · CFDS fault messages related to sidestick: ELAC1(2) OR INPUT OF CAPT ROLL CTL SSTU 4CE1, ELAC1(2) OR INPUT OF F/O ROLL CTL SSTU 4CE2, ELAC1(2) OR INPUT OF CAPT PITCH CTL SSTU 4CE3, ELAC1(2) OR INPUT OF F/O PITCH CTL SSTU 4CE4, SEC1(2)(3) (the non defective SECs) OR INPUT OF CAPT ROLL CTL SSTU 4CE1, SEC1(2)(3) (the non defective SECs) OR INPUT OF F/O ROLL CTL SSTU 4CE2, SEC1(2) (the non defective SECs) OR INPUT OF CAPT PITCH CTL SSTU 4CE3, SEC1(2) (the non defective SECs) OR INPUT OF F/O PITCH CTL SSTU 4CE4, CAPT ROLL CTL SSTU 4CE1, F/O ROLL CTL SSTU 4CE2, CAPT PITCH CTL SSTU 4CE3 and F/O PITCH CTL SSTU 4CE4. · CFDS fault messages related to pitch control from the opposite SEC, if SEC1 not in operation: CHECK PITCH CHANGE OVER OF SEC2, SEC2 OR WIRING FROM L G ELEV POS XCDR 34CE1,

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-94-00-040-002-A - Deactivation of the Spoiler Elevator Computer (SEC)

ACTION

11.On the MCDU, push the line select key adjacent to the RETURN indication until the CFDS menu page comes into view.

RESULT SEC2 OR WIRING FROM R Y ELEV POS XCDR 34CE2, SEC2 OR WIRING FROM L ELEV POS MON XCDR, SEC2 OR WIRING FROM R ELEV POS MON XCDR, SEC2 COM OR WIRING TO L G ELEV SERVO VLV 34CE1, SEC2 COM OR WIRING TO R Y ELEV SERVO VLV 34CE2, SEC2 MON OR WIRING TO L G ELEV SERVO VLV 34CE1, SEC2 MON OR WIRING TO R Y ELEV SERVO VLV 34CE2, SEC2 OR WIRING FROM L B ELEV MODE XCDR 34CE3, SEC2 OR WIRING FROM R B ELEV MODE XCDR 34CE4, SEC2 MON OR WIRING TO L B ELEV SOL VLV 34CE3 and SEC2 MON OR WIRING TO R B ELEV SOL VLV 34CE4. · CFDS fault messages related to pitch control from the opposite SEC, if SEC2 not in operation: CHECK PITCH CHANGE OVER OF SEC1, SEC1 OR WIRING FROM L B ELEV POS XCDR 34CE3, SEC1 OR WIRING FROM R B ELEV POS XCDR 34CE4, SEC1 OR WIRING FROM L ELEV POS MON XCDR, SEC1 OR WIRING FROM R ELEV POS MON XCDR, SEC1 COM OR WIRING TO L B ELEV SERVO VLV 34CE3, SEC1 COM OR WIRING TO R B ELEV SERVO VLV 34CE4, SEC1 MON OR WIRING TO L B ELEV SERVO VLV 34CE3, SEC1 MON OR WIRING TO R B ELEV SERVO VLV 34CE4, SEC1 OR WIRING FROM L G ELEV MODE XCDR 34CE1, SEC1 OR WIRING FROM R Y ELEV MODE XCDR 34CE2, SEC1 MON OR WIRING TO L G ELEV SOL VLV 34CE1 and SEC1 MON OR WIRING TO R Y ELEV SOL VLV 34CE2. The MCDU shows the MCDU MENU page.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-94-00-040-002-A - Deactivation of the Spoiler Elevator Computer (SEC)

5.

Close-up Subtask 27-94-00-410-053-A A.

Close Access (1) Install the protective cover on the battery power center 105VU. (2) Tighten the two screws. (3) Close access door 822. (4) Remove the access platform(s).

Subtask 27-94-00-860-057-A B.

Aircraft Maintenance Configuration (1) On the overhead panel, on the FLT CTL panel 23VU or 24VU, put a WARNING NOTICE(S) on the pushbutton switch related to the SEC that you deactivated. (2) Make an entry in the log book. (3) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-94-00-040-802-A - Deactivation of the Spoiler Elevator Computer 3 (SEC)

** ON A/C ALL TASK 27-94-00-040-802-A Deactivation of the Spoiler Elevator Computer 3 (SEC)

FIN : 1CE3 1.

Reason for the Job MMEL 27-94-03P SEC 3 (FAA only)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER AR WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up Subtask 27-94-00-861-055-A A.

4.

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

Procedure Subtask 27-94-00-040-051-A A.

Deactivation of the Spoiler Elevator Computer 3 (SEC) ACTION 1.On the overhead panel, on the FLT CTL panel 24VU: · Release the SEC3 pushbutton switch. 2.On the circuit breaker panel 121VU: · Open, safety and tag this(these) circuit breaker(s): 21CE3.

RESULT On the overhead panel, on the FLT CTL panel 24VU: · The OFF legend of the SEC3 pushbutton switch comes on.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 27-94-00-040-802-A - Deactivation of the Spoiler Elevator Computer 3 (SEC)

ACTION

RESULT

NOTE: The spoilers associated to the SEC3 will be inoperative.

5.

Close-up Subtask 27-94-00-860-059-A A.

Aircraft Maintenance Configuration (1) On the overhead panel, on the FLT CTL panel 24VU, put a WARNING NOTICE(S) on the pushbutton switch SEC3. (2) Make an entry in the log book. (3) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-003-A - Check of the Fuel Quantity Indicating System, When an Outer Tank Indication is Unserviceable

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 TASK 28-40-00-040-003-A Check of the Fuel Quantity Indicating System, When an Outer Tank Indication is Unserviceable 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.

Task Summary MMEL or CDL Ref MMEL 28-07-01-03A MMEL 28-07-01-03C

Access NO NO

Test YES YES

Specific Tools NO NO

1.

Reason for the Job MMEL 28-07-01-03A Outer Tank Fuel Quantity Indication on the FUEL SD page MMEL 28-07-01-03C Outer Tank Fuel Quantity Indication on the FUEL SD page

2

Job Set-up Information A.

Nb Men 1 1

QTY DESIGNATION AR SAFETY BARRIER(S) AR WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 12-11-28-650-007-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A).

3.

E/T 00.7 00.7

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Mhr 00.7 00.7

DESIGNATION Use of Magnetic Level Indicators (MLI) Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures

Job Set-up Subtask 28-40-00-941-059-A

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-003-A - Check of the Fuel Quantity Indicating System, When an Outer Tank Indication is Unserviceable

A.

Safety Precautions WARNING: OBEY THE FUEL SAFETY PROCEDURES. (1) You must obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00-910-001) . (2) Put the SAFETY BARRIER(S) in position.

Subtask 28-40-00-860-051-A B.

Aircraft Maintenance Configuration (1) Make sure that the aircraft is refueled for the subsequent flight. (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

4.

Procedure Subtask 28-40-00-040-052-A A.

Make sure that the Fuel Tank Contains the Correct Quantity of Fuel (1) To make sure that the applicable fuel tank contains the correct quantity of fuel, do one of these subsequent steps: · Read the FUEL QTY display on the Multi-Tank Indicator (MTI) 6QT, on the Refuel/Defuel Control Panel 800VU. or, · Read the applicable MLIs (Ref. AMM TASK 12-11-28-650-007) .

Subtask 28-40-00-040-053-A DELETED Subtask 28-40-00-040-054-A DELETED Subtask 28-40-00-941-052-A B.

Aircraft Configuration (1) Put a WARNING NOTICE(S) in position to tell the flight crew that: · the applicable outer tank ECAM fuel quantity indication is unserviceable. (2) Write an applicable entry in the aircraft technical log.

5.

Close-up Subtask 28-40-00-862-052-A A.

De-energize the Electrical Circuits (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Subtask 28-40-00-942-056-A B.

Removal of Equipment (1) Remove the safety barriers. (2) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-802-A - Check of the High Level Fuel-DetectionSystem, When an Outer Tank Indication is Unserviceable

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 TASK 28-40-00-040-802-A Check of the High Level Fuel-Detection-System, When an Outer Tank Indication is Unserviceable 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.

1.

Reason for the Job MMEL 28-07-01-03B Outer Tank Fuel Quantity Indication on the FUEL SD page MMEL 28-07-01-03D Outer Tank Fuel Quantity Indication on the FUEL SD page

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION AR SAFETY BARRIER(S) AR WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 12-11-28-650-003-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A). (Ref. 28-25-00-650-001-A). (Ref. 28-46-00-710-001-A).

3.

DESIGNATION Pressure Refuel with Automatic Control Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures Pressure Defuel Test of the Tank High-Level Sensing-System

Job Set-up Subtask 28-40-00-941-072-A A.

Safety Precautions WARNING: OBEY THE FUEL SAFETY PROCEDURES.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-802-A - Check of the High Level Fuel-DetectionSystem, When an Outer Tank Indication is Unserviceable

(1) You must obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00-910-001) . (2) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations. Subtask 28-40-00-860-077-A B.

Aircraft Maintenance Configuration (1) Make sure that the aircraft is refueled for the subsequent flight. (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

4.

Procedure Subtask 28-40-00-040-086-A A.

Make sure that the Fuel Tank Contains the Correct Quantity of Fuel (1) Do the procedure that follows: (a) Do a test of the high level sensors (Ref. AMM TASK 28-46-00-710-001) . (b) Fully refuel the wing tanks (Ref. AMM TASK 12-11-28-650-003) until: · The high level sensors operate and · On the Refuel/Defuel Control Panel 800VU the high level lights come on. (c) Multiply the total volume of the fuel refueled by its specific gravity. The result is the total mass of the fuel refueled. NOTE: The total quantity of the fuel is equal to the maximum capacity of the wing tanks. The difference between the maximum capacity and the quantity of the fuel uplifted is the quantity of the fuel initially available before the refuel. (d) If necessary, defuel the wing tanks to keep the necessary quantity of fuel for the subsequent flight (Ref. AMM TASK 28-25-00-650-001) .

Subtask 28-40-00-040-088-A DELETED Subtask 28-40-00-040-089-A DELETED Subtask 28-40-00-941-073-A B.

Aircraft Configuration (1) Put a WARNING NOTICE(S) in position to tell the flight crew that: · the applicable outer tank ECAM fuel quantity indication is unserviceable. (2) Write an applicable entry in the aircraft technical log.

5.

Close-up Subtask 28-40-00-860-078-A A.

Aircraft Maintenance Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Subtask 28-40-00-942-070-A B.

Removal of Equipment

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-802-A - Check of the High Level Fuel-DetectionSystem, When an Outer Tank Indication is Unserviceable

(1) Remove the safety barriers. (2) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-003-A - Check of the Fuel Quantity Indicating System, When an Outer Tank Indication is Unserviceable

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 TASK 28-40-00-040-003-A Check of the Fuel Quantity Indicating System, When an Outer Tank Indication is Unserviceable 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.

Task Summary MMEL or CDL Ref MMEL 28-07-01-03A MMEL 28-07-01-03C

Access NO NO

Test YES YES

Specific Tools NO NO

1.

Reason for the Job MMEL 28-07-01-03A Outer Tank Fuel Quantity Indication on the FUEL SD page MMEL 28-07-01-03C Outer Tank Fuel Quantity Indication on the FUEL SD page

2

Job Set-up Information A.

Nb Men 1 1

QTY DESIGNATION AR SAFETY BARRIER(S) AR WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 12-11-28-650-007-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A).

3.

E/T 00.7 00.7

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Mhr 00.7 00.7

DESIGNATION Use of Magnetic Level Indicators (MLI) Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures

Job Set-up Subtask 28-40-00-941-059-A

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-003-A - Check of the Fuel Quantity Indicating System, When an Outer Tank Indication is Unserviceable

A.

Safety Precautions WARNING: OBEY THE FUEL SAFETY PROCEDURES. (1) You must obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00-910-001) . (2) Put the SAFETY BARRIER(S) in position.

Subtask 28-40-00-860-051-A B.

Aircraft Maintenance Configuration (1) Make sure that the aircraft is refueled for the subsequent flight. (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

4.

Procedure Subtask 28-40-00-040-052-A A.

Make sure that the Fuel Tank Contains the Correct Quantity of Fuel (1) To make sure that the applicable fuel tank contains the correct quantity of fuel, do one of these subsequent steps: · Read the FUEL QTY display on the Multi-Tank Indicator (MTI) 6QT, on the Refuel/Defuel Control Panel 800VU. or, · Read the applicable MLIs (Ref. AMM TASK 12-11-28-650-007) .

Subtask 28-40-00-040-053-A DELETED Subtask 28-40-00-040-054-A DELETED Subtask 28-40-00-941-052-A B.

Aircraft Configuration (1) Put a WARNING NOTICE(S) in position to tell the flight crew that: · the applicable outer tank ECAM fuel quantity indication is unserviceable. (2) Write an applicable entry in the aircraft technical log.

5.

Close-up Subtask 28-40-00-862-052-A A.

De-energize the Electrical Circuits (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Subtask 28-40-00-942-056-A B.

Removal of Equipment (1) Remove the safety barriers. (2) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-802-A - Check of the High Level Fuel-DetectionSystem, When an Outer Tank Indication is Unserviceable

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 TASK 28-40-00-040-802-A Check of the High Level Fuel-Detection-System, When an Outer Tank Indication is Unserviceable 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.

1.

Reason for the Job MMEL 28-07-01-03B Outer Tank Fuel Quantity Indication on the FUEL SD page MMEL 28-07-01-03D Outer Tank Fuel Quantity Indication on the FUEL SD page

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION AR SAFETY BARRIER(S) AR WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 12-11-28-650-003-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A). (Ref. 28-25-00-650-001-A). (Ref. 28-46-00-710-001-A).

3.

DESIGNATION Pressure Refuel with Automatic Control Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures Pressure Defuel Test of the Tank High-Level Sensing-System

Job Set-up Subtask 28-40-00-941-072-A A.

Safety Precautions WARNING: OBEY THE FUEL SAFETY PROCEDURES.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-802-A - Check of the High Level Fuel-DetectionSystem, When an Outer Tank Indication is Unserviceable

(1) You must obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00-910-001) . (2) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations. Subtask 28-40-00-860-077-A B.

Aircraft Maintenance Configuration (1) Make sure that the aircraft is refueled for the subsequent flight. (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

4.

Procedure Subtask 28-40-00-040-086-A A.

Make sure that the Fuel Tank Contains the Correct Quantity of Fuel (1) Do the procedure that follows: (a) Do a test of the high level sensors (Ref. AMM TASK 28-46-00-710-001) . (b) Fully refuel the wing tanks (Ref. AMM TASK 12-11-28-650-003) until: · The high level sensors operate and · On the Refuel/Defuel Control Panel 800VU the high level lights come on. (c) Multiply the total volume of the fuel refueled by its specific gravity. The result is the total mass of the fuel refueled. NOTE: The total quantity of the fuel is equal to the maximum capacity of the wing tanks. The difference between the maximum capacity and the quantity of the fuel uplifted is the quantity of the fuel initially available before the refuel. (d) If necessary, defuel the wing tanks to keep the necessary quantity of fuel for the subsequent flight (Ref. AMM TASK 28-25-00-650-001) .

Subtask 28-40-00-040-088-A DELETED Subtask 28-40-00-040-089-A DELETED Subtask 28-40-00-941-073-A B.

Aircraft Configuration (1) Put a WARNING NOTICE(S) in position to tell the flight crew that: · the applicable outer tank ECAM fuel quantity indication is unserviceable. (2) Write an applicable entry in the aircraft technical log.

5.

Close-up Subtask 28-40-00-860-078-A A.

Aircraft Maintenance Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Subtask 28-40-00-942-070-A B.

Removal of Equipment

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-802-A - Check of the High Level Fuel-DetectionSystem, When an Outer Tank Indication is Unserviceable

(1) Remove the safety barriers. (2) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-020-A - Deactivation of the ACT Transfer Valve in the Closed Position

** ON A/C 401-415 TASK 28-28-00-040-020-A Deactivation of the ACT Transfer Valve in the Closed Position WARNING:

OBEY THE FUEL SAFETY PROCEDURES.

Task Summary MMEL or CDL Ref MMEL 28-07-01-05C

Access NO

Test NO

Specific Tools YES

1.

Reason for the Job MMEL 28-07-01-05C Center Tank Fuel Quantity Indication on the FUEL SD page (FAA only)

2

Job Set-up Information A.

E/T 00.8

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific (T720456)

B.

Mhr 00.8

QTY 1 AR AR 1 1 1

DESIGNATION ACCESS PLATFORM 1M(3 FT) CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER TIE WRAP WARNING NOTICE(S) TOOL - VALVE LOCKING

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A). (Ref. 32-12-00-010-001-A). (Ref. 32-12-00-410-001-A). (Ref. 57-17-11-000-001-A). (Ref. 57-17-11-000-001-A-01). (Ref. 57-17-11-400-001-A). (Ref. 57-17-11-400-001-A-01).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures Open the Main Gear Doors for Access Close the Main Gear Doors after Access Removal of the Access Covers 147AZ (148AZ) Removal of the Access Cover 148AZ or/and the ACT-Equipment Support Door Installation of Access Covers 147AZ (148AZ) Installation of Access Cover 148AZ or/and the ACT-Equipment Support-Door

ACT Fuel-Transfer Valve 165QM

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-020-A - Deactivation of the ACT Transfer Valve in the Closed Position

FR42

FR36

A

B Z140

A D 2 6 FR42

C 165QM

5

1

4 3 7 PIN SLOT

B N_MM_282800_4_PLA1_01_00

Figure 28-28-00-991-00300-00-B / SHEET 1/2 - ACT Fuel-Transfer Valve 165QM ** ON A/C 401-415 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-020-A - Deactivation of the ACT Transfer Valve in the Closed Position

CLOSED POSITION OPEN POSITION

C

A

B

A

B

OPEN POSITION

CLOSED POSITION

D

A A

B B

N_MM_282800_4_PLA1_02_00

Figure 28-28-00-991-00300-00-B / SHEET 2/2 - ACT Fuel-Transfer Valve 165QM ** ON A/C 401-415 Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-020-A - Deactivation of the ACT Transfer Valve in the Closed Position

3.

Job Set-up Subtask 28-28-00-860-224-A A.

Aircraft Maintenance Configuration (1) Obey the fuel safety procedures when you work on the fuel system (Ref. AMM TASK 28-00-00-910001) . (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) On the APU section of overhead panel 25VU make sure that the APU/MASTER SW pushbutton switch is released (the ON legend is off). (4) On the FUEL section of HYD/FUEL panel 40VU make sure that all tank pump pushbutton switches are released (the OFF legends are on). (5) Put a WARNING NOTICE(S) in position: · On the APU section of overhead panel 25VU to tell persons not to operate the APU/MASTER SW pushbutton switch · On the FUEL section of panel 40VU to tell persons not to operate the fuel system · On the ENG/APU FIRE panel located on overhead panel 20VU to tell persons not to operate the fire extinguishing system · On the Additional Center Tank (ACT) control section of panel 28VU, to tell persons not to operate the fuel system.

Subtask 28-28-00-010-114-B B.

Get Access (1) Open the left main-gear door for access (Ref. AMM TASK 32-12-00-010-001) . (2) Put an ACCESS PLATFORM 1M(3 FT) in position in the left MLG bay. (3) Remove the ACT equipment-support door (Ref. AMM TASK 57-17-11-000-001) .

4.

Procedure (Ref. Fig. ACT Fuel-Transfer Valve 165QM) Subtask 28-28-00-040-072-B CAUTION:

A.

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

Deactivation of the ACT Fuel-Transfer Valve in the Closed Position NOTE: A refuel of the ACT is not possible while ACT fuel-transfer valve is OFF in valve position CLOSED. (1) Disconnect the electrical connectors (3) and (4) from the receptacles of the ACT fuel-transfer valveactuator (2). (2) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (3) Safety the electrical connectors (3) and (4) to the adjacent electrical harness with a TIE WRAP. (4) Do a visual check of the indicator of the ACT fuel-transfer valve-actuator (2) to identify the position of the valve: · Indicator in horizontal position the transfer valve is OPEN · Indicator in vertical position the transfer valve is CLOSED. (5) Cut and discard the lockwire:

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-020-A - Deactivation of the ACT Transfer Valve in the Closed Position

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. (a) Cut and discard the lockwire from the screw (5). (6) Loosen the screw (5) and remove the V-clamp (6) and the ACT fuel-transfer valve-actuator (2). (7) Remove the O-ring (7) and discard it: (a) Turn the shaft of the ACT fuel-transfer valve (1) to the closed position if necessary. (b) Install the TOOL - VALVE LOCKING (T720456) on the flange of the ACT fuel-transfer valve (1) to lock it in the closed position. 5.

Close-up Subtask 28-28-00-860-225-B A.

Put the aircraft back to the serviceable condition. (1) Install the ACT equipment-support door (Ref. AMM TASK 57-17-11-400-001) . (2) Make sure that the work area is clean and clear of tools and other items. (3) Remove the access platform(s). (4) Close the main gear doors (Ref. AMM TASK 32-12-00-410-001) . (5) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (6) Remove the WARNING NOTICE(S). (7) In the cockpit put a placard in position to tell the crew that the ACT fuel- transfer valve is OFF in valve position CLOSED. (8) On the refuel/defuel control panel 801VU put a placard in position to tell the ground crew: DO NOT REFUEL THE ACT(s). (9) Make an entry in the logbook.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-001-A - APU LP Valve Indication - Valve Closure Procedure

** ON A/C ALL TASK 28-40-00-040-001-A APU LP Valve Indication - Valve Closure Procedure 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.

Task Summary MMEL or CDL Ref MMEL 28-07-04-02A

Access NO

Test YES

1.

Reason for the Job MMEL 28-07-04-02A APU LP Fuel Valve Indication on the FUEL SD page

2

Job Set-up Information A.

E/T 01.0

Nb Men 1

QTY AR AR 1

DESIGNATION SAFETY BARRIER(S) WARNING NOTICE(S) SLEEVE - GROUND LOCK

Referenced Information REFERENCE (Ref. 28-00-00-910-001-A). (Ref. 28-29-00-040-002-A). (Ref. 32-12-00-010-001-A).

3.

Mhr 01.0

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific (460005835)

B.

Specific Tools YES

DESIGNATION Fuel Safety Procedures APU LP VALVE - Deactivation Open the Main Gear Doors for Access

Job Set-up Subtask 28-40-00-941-056-A A.

Safety Precautions WARNING: OBEY THE FUEL SAFETY PROCEDURES. (1) You must obey the fuel safety procedures when you work on the fuel system (Ref. AMM TASK 2800-00-910-001) . (2) Put the SAFETY BARRIER(S) in position.

Subtask 28-40-00-010-054-A

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-001-A - APU LP Valve Indication - Valve Closure Procedure

B.

Get Access (1) Open the MLG doors (Ref. AMM TASK 32-12-00-010-001) . (2) Make sure that the SLEEVE - GROUND LOCK (460005835) is installed on the applicable MLG door actuating-cylinder.

4.

Procedure

** ON A/C 219-220 Subtask 28-40-00-040-050-A A.

Deactivation of the APU LP Valve (1) Do the deactivation procedure of the APU LP valve (Ref. AMM TASK 28-29-00-040-002) . (2) Put a WARNING NOTICE(S) in position in the cockpit to tell the flight crew that the ECAM APU LP valve indication is unserviceable. (3) Make an entry in the aircraft-logbook that the APU fuel LP-valve (14QM) is locked in closed position and the APU must not operate.

** ON A/C 016-022, 024-100, 112-150, 203-203, 211-211, 217-217, 221-221, 227-228, 231-232, 236-238, 240-250 Subtask 28-40-00-040-050-B A.

Deactivation of the APU LP Valve (1) Do the deactivation procedure of the APU LP valve (Ref. AMM TASK 28-29-00-040-002) . (2) Put a WARNING NOTICE(S) in position in the cockpit to tell the flight crew that the ECAM APU LP valve indication is unserviceable. (3) Make an entry in the aircraft-logbook that the APU fuel LP-valve (14QM) is locked in closed position and the APU must not operate.

** ON A/C 201-201, 204-210, 212-216, 218-218, 222-226, 229-230, 233-235, 239-239, 301-450, 500-600 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1069 for A/C 204-204 Subtask 28-40-00-040-050-C A.

Deactivation of the APU LP Valve (1) Do the deactivation procedure of the APU LP valve (Ref. AMM TASK 28-29-00-040-002) . (2) Put a WARNING NOTICE(S) in position in the cockpit to tell the flight crew that the ECAM APU LP valve indication is unserviceable. (3) Make an entry in the aircraft-logbook that the APU fuel LP-valve (14QM) is locked in closed position and the APU must not operate.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-005-A - Check of the Fuel Quantity Indicating System, When an Inner Tank Indication is Unserviceable

** ON A/C ALL TASK 28-40-00-040-005-A Check of the Fuel Quantity Indicating System, When an Inner Tank Indication is Unserviceable 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.

Task Summary MMEL or CDL Ref MMEL 28-07-01-04A

Access NO

Test YES

Specific Tools NO

1.

Reason for the Job MMEL 28-07-01-04A Inner Tank Fuel Quantity Indication on the FUEL SD page

2

Job Set-up Information A.

Nb Men 1

QTY DESIGNATION AR SAFETY BARRIER(S) AR WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 12-11-28-650-007-A). (Ref. 12-32-28-281-001-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A).

3.

E/T 00.3

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Mhr 00.3

DESIGNATION Use of Magnetic Level Indicators (MLI) Drain Water Content Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures

Job Set-up Subtask 28-40-00-941-061-A A.

Safety Precautions

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-005-A - Check of the Fuel Quantity Indicating System, When an Inner Tank Indication is Unserviceable

WARNING: OBEY THE FUEL SAFETY PROCEDURES. (1) You must obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00-910-001) . (2) Put the SAFETY BARRIER(S) in position. Subtask 28-40-00-860-056-A B.

Aircraft Maintenance Configuration (1) Make sure that the aircraft is refueled for the subsequent flight. (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

4.

Procedure

** ON A/C 016-022, 024-024, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 Subtask 28-40-00-040-056-A A.

Make sure that the Fuel Tank Contains the Correct Quantity of Fuel (and not contamination such as unwanted free water). (1) Check for unwanted free water. (Ref. AMM TASK 12-32-28-281-001) (2) To make sure that the applicable fuel tank contains the correct quantity of fuel, do one of these subsequent steps: · Read the FUEL QTY display on the Multi-Tank Indicator (MTI) 6QT, on the Refuel/Defuel Control Panel 800VU, or, · Read the applicable MLIs (Ref. AMM TASK 12-11-28-650-007) .

** ON A/C 025-100, 112-150, 208-208, 213-214, 223-225, 236-236, 238-238, 241-241, 301-349, 351-400, 500-600 Subtask 28-40-00-040-056-C A.

Make sure that the Fuel Tank Contains the Correct Quantity of Fuel (and not contamination such as unwanted free water). (1) Check for unwanted free water. (Ref. AMM TASK 12-32-28-281-001) (2) To make sure that the applicable fuel tank contains the correct quantity of fuel, do one of these subsequent steps: · Read the FUEL QTY display on the Multi-Tank Indicator (MTI) 6QT, on the Refuel/Defuel Control Panel 800VU, or, · Read the applicable MLIs (Ref. AMM TASK 12-11-28-650-007) (if the inner tank contains more than 2500 liters of fuel).

** ON A/C 401-450 Subtask 28-40-00-040-056-F A.

Make sure that the Fuel Tank Contains the Correct Quantity of Fuel (and not contamination such as unwanted free water). (1) Check for unwanted free water. (Ref. AMM TASK 12-32-28-281-001)

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-005-A - Check of the Fuel Quantity Indicating System, When an Inner Tank Indication is Unserviceable

(2) To make sure that the applicable fuel tank contains the correct quantity of fuel, do one of these subsequent steps: · Read the FUEL QTY display on the Multi-Tank Indicator (MTI) 6QT, on the Refuel/Defuel Control Panel 800VU, or, · Read the applicable MLIs (Ref. AMM TASK 12-11-28-650-007) (if the wing tank contains between 2400 and 7000 liters of fuel). ** ON A/C ALL Subtask 28-40-00-040-057-A DELETED Subtask 28-40-00-040-058-A DELETED 5.

Close-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 28-40-00-860-059-A A.

Aircraft Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (2) Put a WARNING NOTICE(S) in position to tell the flight crew that: · the applicable wing tank inner-cell ECAM fuel quantity indication is unserviceable. (3) Write an applicable entry in the aircraft technical log.

** ON A/C 401-450 Subtask 28-40-00-860-059-B A.

Aircraft Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (2) Put a WARNING NOTICE(S) in position to tell the flight crew that: · the applicable wing tank ECAM fuel quantity indication is unserviceable. (3) Write an applicable entry in the aircraft technical log.

** ON A/C ALL Subtask 28-40-00-942-059-A B.

Removal of Equipment (1) Remove the safety barriers. (2) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-006-A - Check of the Fuel Quantity Indicating System, When the Center Tank Indication is Unserviceable

** ON A/C ALL TASK 28-40-00-040-006-A Check of the Fuel Quantity Indicating System, When the Center Tank Indication is Unserviceable 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.

Task Summary MMEL or CDL Ref MMEL 28-07-01-05A

Access NO

Test YES

Specific Tools NO

1.

Reason for the Job MMEL 28-07-01-05A Center Tank Fuel Quantity Indication on the FUEL SD page

2

Job Set-up Information A.

Nb Men 1

QTY DESIGNATION AR SAFETY BARRIER(S) AR WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 12-11-28-650-003-A). (Ref. 12-11-28-650-004-A). (Ref. 12-11-28-650-007-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A).

3.

E/T 00.3

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Mhr 00.3

DESIGNATION Pressure Refuel with Automatic Control Pressure Refuel with Manual Control Use of Magnetic Level Indicators (MLI) Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures

Job Set-up Subtask 28-40-00-941-063-A A.

Safety Precautions

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-006-A - Check of the Fuel Quantity Indicating System, When the Center Tank Indication is Unserviceable

WARNING: OBEY THE FUEL SAFETY PROCEDURES. (1) You must obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00-910-001) . (2) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations. Subtask 28-40-00-860-057-A B.

Aircraft Maintenance Configuration (1) Make sure that the aircraft is refueled for the next flight, (Ref. AMM TASK 12-11-28-650-003) or (Ref. AMM TASK 12-11-28-650-004) . (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

4.

Procedure Subtask 28-40-00-040-059-A A.

Fuel Configuration (1) To make sure that the center tank contains the correct quantity of fuel, do one of these subsequent steps: · read the FUEL QTY CTR display on the Fuel Quantity Indicator 6QT, on the Refuel/Defuel Control Panel 800VU, or, · read the MLI 92QM (Ref. AMM TASK 12-11-28-650-007) .

Subtask 28-40-00-040-060-A DELETED Subtask 28-40-00-040-061-A DELETED 5.

Close-up Subtask 28-40-00-860-060-A A.

Aircraft Maintenance Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (2) Put a WARNING NOTICE(S) in position to tell the flight crew that the center tank ECAM fuel quantity indication is unserviceable. (3) Make a note in the aircraft technical log that the center tank ECAM fuel quantity indication is unserviceable.

Subtask 28-40-00-942-060-A B.

Removal of Equipment (1) Remove the safety barriers. (2) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-009-A - Engine LP Valve Indication - When ECAM Display Inoperative

** ON A/C ALL TASK 28-40-00-040-009-A Engine LP Valve Indication - When ECAM Display Inoperative 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.

1.

Reason for the Job MMEL 28-07-04-01A Engine LP Fuel Valve Indication on the FUEL SD page

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

QTY AR AR AR AR

DESIGNATION ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE SAFETY BARRIER(S) SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 27-80-00-866-004-A). Extending the Slats on the Ground (Ref. 27-80-00-866-005-A). Retracting the Slats on the Ground (Ref. 28-00-00-910-001-A). Fuel Safety Procedures (Ref. 57-41-37-000-003-A). Removal of the Access Panel (Ref. 57-41-37-400-003-A). Installation of the Access Panel LP Valve - Cockpit Component Location SHEET 1 LP Valve - Component Location and Detail SHEET 1

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-009-A - Engine LP Valve Indication - When ECAM Display Inoperative

A

A PANEL 115VU

MASTER 1

ENG

MASTER 2

ON

ON 115VU PUSH

ENG 1

OFF

FIRE

ENG 2

MODE AUTO IGN

CRANK

IGN

OFF

FIRE

FAULT

FAULT

1

2 ENGINE CONTROL PANEL

N_MM_284000_4_AEM0_01_00

Figure 28-40-00-991-00300-00-A / SHEET 1/1 - LP Valve - Cockpit Component Location ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-009-A - Engine LP Valve Indication - When ECAM Display Inoperative

ACCESS PANEL 522AT (622AT)

A

A

FRONT SPAR

LP FUEL VALVE 12QM 13QM

B

ACTUATOR 9QG 10QG VALVE CLOSED

B

VALVE OPEN

SEE / FEEL INDICATOR

N_MM_284000_4_AGM0_01_00

Figure 28-40-00-991-00400-00-A / SHEET 1/1 - LP Valve - Component Location and Detail ** ON A/C ALL Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-009-A - Engine LP Valve Indication - When ECAM Display Inoperative

3.

Job Set-up Subtask 28-40-00-941-066-A A.

Safety Precautions WARNING: OBEY THE FUEL SAFETY PROCEDURES. (1) You must obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00-910-001) . (2) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations. (3) Put a WARNING NOTICE(S) in position to tell persons not to operate the slats. (4) Put a WARNING NOTICE(S) in the cockpit to tell persons not to operate the bleed air.

Subtask 28-40-00-010-058-A B.

Get Access (1) Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position in zone 522(622). (2) Remove the applicable access panel(s) (Ref. AMM TASK 57-41-37-000-003) : · for the LH LP valve 12QM, remove panel 522AT · for the RH LP valve 13QM, remove panel 622AT.

Subtask 28-40-00-860-063-A C.

Aircraft Maintenance Configuration (1) Make sure that there is no bleed air. (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) Fully extend the slats (Ref. AMM TASK 27-80-00-866-004) . (4) Make sure that the LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION (98D27803000000) is on the flap/slat control lever.

Subtask 28-40-00-865-057-A D.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 121VU 121VU

4.

DESIGNATION FUEL/LP VALVE/MOT1/ENG2 FUEL/LP VALVE/MOT1/ENG1 FUEL/LP VALVE/MOT2/ENG2 FUEL/LP VALVE/MOT2/ENG1

FIN 2QG 1QG 4QG 3QG

LOCATION A09 A08 M26 M25

Procedure (Ref. Fig. LP Valve - Cockpit Component Location SHEET 1) (Ref. Fig. LP Valve - Component Location and Detail SHEET 1) Subtask 28-40-00-040-079-A A.

Test of the valve 12QM (1) In the test that follows, on each operation of the LP valve: · make sure that the see/feel indicator operates smoothly, from the valve open (valve closed) position to the valve closed (valve open) position · make sure that the see/feel indicator marks are accurately aligned in the valve open position

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-009-A - Engine LP Valve Indication - When ECAM Display Inoperative

· make sure that the see/feel indicator marks are at 90 degrees to each other in the valve closed position. (2) For the valve 12QM, do this test: ACTION RESULT 1.On the panel 115VU: · make sure that the ENG/MASTER 1 switch is in the OFF position. 2.On the LP valve actuator 9QG: The indicator shows that the LP valve is closed. · look at the position of the mechanical see/feel indicator. 3.On the panel 121VU: The ENG 1 LP valve MOTOR 2 SUPPLY and · Open, safety and tag this(these) circuit CONTROL are isolated. breaker(s): · 3QG. 4.On the panel 115VU: In zone 510, the LP valve moves to the open posi· put the ENG/MASTER 1 switch to the ON posi- tion. tion. 5.On the LP valve actuator 9QG: The indicator shows that the LP valve is open. · look at the position of the mechanical see/feel indicator. 6.On the panel 115VU: In zone 510 the LP valve moves to the closed pos· put the ENG/MASTER 1 switch to the OFF pos- ition. ition. 7.On the LP valve actuator 9QG: The indicator shows that the LP valve is closed. · look at the position of the mechanical see/feel indicator. 8.On the panel 121VU: The ENG 1 LP valve MOTOR 2 SUPPLY and · Remove the safety clip(s) and the tag(s) and CONTROL are energized. close this(these) circuit breaker(s): · 3QG. 9.On the panel 49VU: The ENG 1 LP valve MOTOR 1 SUPPLY and Open, safety and tag this(these) circuit CONTROL are isolated. breaker(s): · 1QG. 10.On panel 115VU: In zone 510 the LP valve moves to the open posi· put the ENG/MASTER 1 switch to the ON posi- tion. tion. 11.On the LP valve actuator 9QG: The indicator shows that the LP valve is open. · look at the position of the mechanical see/feel indicator. 12.On the panel 115VU: In zone 510 the LP valve moves to the closed pos· put the ENG/MASTER 1 switch to the OFF pos- ition. ition. 13.On the LP valve actuator 9QG: The indicator shows that the LP valve is closed. · look at the position of the mechanical see/feel indicator. 14.On the panel 49VU: The ENG 1 LP valve MOTOR 1 SUPPLY and · Remove the safety clip(s) and the tag(s) and CONTROL are energized. close this(these) circuit breaker(s): · 1QG.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-009-A - Engine LP Valve Indication - When ECAM Display Inoperative

Subtask 28-40-00-040-080-A B.

Test of the valve 13QM (1) In the test that follows, on each operation of the LP valve: · make sure that the see/feel indicator operates smoothly, from the valve open (valve closed) position to the valve closed (valve open) position · make sure that the see/feel indicator marks are accurately aligned in the valve open position · make sure that the see/feel indicator marks are at 90 degrees to each other in the valve closed position. (2) For the valve 13QM, do this test: ACTION RESULT 1.On the panel 115VU: · make sure that the ENG/MASTER 2 switch is in the OFF position. 2.On the LP valve actuator 10QG: The indicator shows that the LP valve is closed. · look at the position of the mechanical see/feel indicator. 3.On the panel 121VU: The ENG 2 LP valve MOTOR 2 SUPPLY and · Open, safety and tag this(these) circuit CONTROL are isolated. breaker(s): · 4QG. 4.On the panel 115VU: In zone 610, the LP valve moves to the open posi· put the ENG/MASTER 2 switch to the ON posi- tion. tion. 5.On the LP valve actuator 10QG: The indicator shows that the LP valve is open. · look at the position of the mechanical see/feel indicator. 6.On the panel 115VU: In zone 610 the LP valve moves to the closed pos· put the ENG/MASTER 2 switch to the OFF pos- ition. ition. 7.On the LP valve actuator 10QG: The indicator shows that the LP valve is closed. · look at the position of the mechanical see/feel indicator. 8.On the panel 121VU: The ENG 2 LP valve MOTOR 2 SUPPLY and · Remove the safety clip(s) and the tag(s) and CONTROL are energized. close this(these) circuit breaker(s): · 4QG. 9.On the panel 49VU: The ENG 2 LP valve MOTOR 1 SUPPLY and Open, safety and tag this(these) circuit CONTROL are isolated. breaker(s): · 2QG. 10.On panel 115VU: In zone 610 the LP valve moves to the open posi· put the ENG/MASTER 2 switch to the ON posi- tion. tion. 11.On the LP valve actuator 10QG: The indicator shows that the LP valve is open. · look at the position of the mechanical see/feel indicator. 12.On the panel 115VU: In zone 610 the LP valve moves to the closed pos· put the ENG/MASTER 2 switch to the OFF pos- ition. ition. 13.On the LP valve actuator 10QG: The indicator shows that the LP valve is closed.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-009-A - Engine LP Valve Indication - When ECAM Display Inoperative

ACTION RESULT · look at the position of the mechanical see/feel indicator. 14.On the panel 49VU: The ENG 2 LP valve MOTOR 1 SUPPLY and · Remove the safety clip(s) and the tag(s) and CONTROL are energized. close this(these) circuit breaker(s): · 2QG. 5.

Close-up Subtask 28-40-00-860-064-A A.

Aircraft Maintenance Configuration (1) Remove the LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION (98D27803000000) from the flap/slat control lever. (2) Fully retract the slats (Ref. AMM TASK 27-80-00-866-005) : (3) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (4) Make an entry in the aircraft technical log that the LH/RH or both engine LP valve indication(s) will not be displayed on the ECAM DU.

Subtask 28-40-00-410-056-A B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the applicable access panel(s) (Ref. AMM TASK 57-41-37-400-003) : · for the LH LP valve 12QM, install 522AT · for the RH LP valve 13QM, install 622AT.

Subtask 28-40-00-942-063-A C.

Removal of Equipment (1) Remove the safety barriers. (2) Remove the access platform(s). (3) Remove the WARNING NOTICE(S). (4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-803-A - Check of the High Level Fuel-DetectionSystem, When an Inner Tank Indication is Unserviceable

** ON A/C ALL TASK 28-40-00-040-803-A Check of the High Level Fuel-Detection-System, When an Inner Tank Indication is Unserviceable 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.

1.

Reason for the Job MMEL 28-07-01-04B Inner Tank Fuel Quantity Indication on the FUEL SD page

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION AR SAFETY BARRIER(S) AR WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 12-11-28-650-003-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A). (Ref. 28-25-00-650-001-A).

DESIGNATION Pressure Refuel with Automatic Control Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures Pressure Defuel

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 416-450, 500-600 (Ref. 28-46-00-710-001-A). Test of the Tank High-Level Sensing-System ** ON A/C ALL 3.

Job Set-up Subtask 28-40-00-941-075-A A.

Safety Precautions

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-803-A - Check of the High Level Fuel-DetectionSystem, When an Inner Tank Indication is Unserviceable

WARNING: OBEY THE FUEL SAFETY PROCEDURES. (1) You must obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00-910-001) . (2) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations. Subtask 28-40-00-860-081-A B.

Aircraft Maintenance Configuration (1) Make sure that the aircraft is refueled for the subsequent flight. (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

4.

Procedure Subtask 28-40-00-040-087-A A.

Make sure that the Fuel Tank Contains the Correct Quantity of Fuel (and not contamination such as unwanted free water). (1) Do the procedure that follows: (a) Do a test of the high level sensors (Ref. AMM TASK 28-46-00-710-001) . (b) Fully refuel the wing tanks (Ref. AMM TASK 12-11-28-650-003) until: · The high level sensors operate and · On the Refuel/Defuel Control Panel 800VU the high level lights come on. (c) Multiply the total volume of the fuel refueled by its specific gravity. The result is the total mass of the fuel refueled. NOTE: The total quantity of the fuel is equal to the maximum capacity of the wing tanks. The difference between the maximum capacity and the quantity of the fuel uplifted is the quantity of the fuel initially available before the refuel. (d) If necessary, defuel the wing tanks to keep the necessary quantity of fuel for the subsequent flight (Ref. AMM TASK 28-25-00-650-001) .

Subtask 28-40-00-040-090-A DELETED Subtask 28-40-00-040-091-A DELETED 5.

Close-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 28-40-00-860-080-A A.

Aircraft Maintenance Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (2) Put a WARNING NOTICE(S) in position to tell the flight crew that: · the applicable wing tank inner-cell ECAM fuel quantity indication is unserviceable. (3) Write an applicable entry in the aircraft technical log.

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-803-A - Check of the High Level Fuel-DetectionSystem, When an Inner Tank Indication is Unserviceable

** ON A/C 401-450 Subtask 28-40-00-860-080-B A.

Aircraft Maintenance Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (2) Put a WARNING NOTICE(S) in position to tell the flight crew that: · the applicable wing tank ECAM fuel quantity indication is unserviceable. (3) Write an applicable entry in the aircraft technical log.

** ON A/C ALL Subtask 28-40-00-942-072-A B.

Removal of Equipment (1) Remove the safety barriers. (2) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: August 26, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-002-A - Crossfeed Valve Indication - Valve Operating Procedure

** ON A/C ALL TASK 28-40-00-040-002-A Crossfeed Valve Indication - Valve Operating Procedure 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.

Task Summary MMEL or CDL Ref MMEL 28-07-04-03A MMEL 28-07-04-03B

Access YES YES

Test YES YES

1.

Reason for the Job MMEL 28-07-04-03A Crossfeed Valve Indication on the FUEL SD page MMEL 28-07-04-03B Crossfeed Valve Indication on the FUEL SD page

2

Job Set-up Information A.

Mhr 00.3 00.3

E/T 00.3 00.3

Nb Men 1 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Specific Tools YES YES

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) AR SAFETY BARRIER(S)

Work Zones and Access Panels ZONE/ACCESS 192MB

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-002-A - Crossfeed Valve Indication - Valve Operating Procedure

REFERENCE (Ref. 32-12-00-010-001-A). (Ref. 32-12-00-410-001-A). Fuel Crossfeed Valve SHEET 1

DESIGNATION Open the Main Gear Doors for Access Close the Main Gear Doors after Access

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-002-A - Crossfeed Valve Indication - Valve Operating Procedure

A

Z148

A REAR SPAR

ACTUATOR 5QE

CROSSFEED VALVE 10QM

B B

VALVE OPEN

VALVE CLOSED

N_MM_284000_4_ACM0_01_00

Figure 28-40-00-991-00200-00-A / SHEET 1/1 - Fuel Crossfeed Valve ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-002-A - Crossfeed Valve Indication - Valve Operating Procedure

3.

Job Set-up (Ref. Fig. Fuel Crossfeed Valve SHEET 1) Subtask 28-40-00-941-058-A A.

Safety Precautions WARNING: OBEY THE FUEL SAFETY PROCEDURES. (1) You must obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00-910-001) . (2) Put the SAFETY BARRIER(S) in position.

Subtask 28-40-00-010-055-A B.

Get Access (1) Open the RH MLG door (Ref. AMM TASK 32-12-00-010-001) . (2) Make sure that the SLEEVE - GROUND LOCK (460005835) is installed on the applicable MLG door actuating-cylinder. (3) Open the access door 192MB. NOTE: If operating in battery power, do not keep the door open longer than necessary because the battery can discharge. (4) Put an ACCESS PLATFORM 2M (6 FT) below the actuator 5QE of the fuel crossfeed valve 10QM.

Subtask 28-40-00-861-051-A C.

Energize the Electrical Circuits (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

Subtask 28-40-00-865-052-A D.

Table of the circuit breakers used in this procedure: PANEL 49VU 121VU

4.

DESIGNATION FUEL/X FEED/VALVE/MOT1 FUEL/X FEED/VALVE/MOT2

FIN 2QE 1QE

LOCATION A12 M24

Procedure (Ref. Fig. Fuel Crossfeed Valve SHEET 1) Subtask 28-40-00-040-051-A A.

Crossfeed Valve Indication - Valve Operating Procedure (1) In the test that follows, on each operation of the crossfeed valve: · listen to the actuator and make sure it stops each time the crossfeed valve moves to the end of its travel · make sure that the see/feel indicator operates smoothly, from the valve open (valve closed) position to the valve closed (valve open) position. (2) Do this test: ACTION 1.Open tag and safety C/B 1QE. 2.On the fuel control panel 40VU: · push (in) the X FEED pushbutton switch (P/ BSW).

RESULT On the panel 40VU: · the X FEED P/BSW ON light comes on

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-002-A - Crossfeed Valve Indication - Valve Operating Procedure

ACTION

3.On the fuel control panel 40VU: · release (out) the X FEED P/BSW.

4.Remove the safety clip(s) and the tag(s) and close C/B 1QE. 5.Open, safety and tag C/B 2QE. 6.On the fuel control panel 40VU: · push (in) the X FEED P/BSW.

RESULT · when the valve is fully open, the X FEED P/BSW OPEN light comes on. On the valve actuator, when the valve is fully open: · the see/feel indicator marks are accurately aligned in the valve open position. On the panel 40VU: · the X FEED P/BSW ON light goes off · when the valve is fully closed, the X FEED P/ BSW OPEN light goes off. On the valve actuator, when the valve is fully closed: · the see/feel indicator marks are at 90 degrees to one another in the valve closed position.

On the panel 40VU: · the X FEED P/BSW ON light comes on. NOTE: The X FEED P/BSW OPEN light will not come on when cicuit breaker 2QE is open. On the valve actuator, when the valve is fully open: - the see/feel indicator marks are accurately aligned in the valve open position.

7.On the fuel control panel 40VU: · release (out) the X FEED P/BSW.

On the panel 40VU: · the X FEED P/BSW ON light goes off. On the valve actuator, when the valve is fully closed: · the see/feel indicator marks are at 90 degrees to one another in the valve closed position.

8.Remove the safety clip(s) and the tag(s) and close C/B 2QE. 5.

Close-up Subtask 28-40-00-410-052-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the RH MLG door (Ref. AMM TASK 32-12-00-410-001) . (3) Close the access door 192MB.

Subtask 28-40-00-862-051-A B.

De-energize the Electrical Circuits (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Subtask 28-40-00-942-055-A C.

Removal of Equipment

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-002-A - Crossfeed Valve Indication - Valve Operating Procedure

(1) Make a note in the aircraft technical log to say that the crossfeed valve indication (on the ECAM lower DU) is deactivated. (2) Remove the safety barriers. (3) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-002-A - Crossfeed Valve Indication - Valve Operating Procedure

** ON A/C ALL TASK 28-40-00-040-002-A Crossfeed Valve Indication - Valve Operating Procedure 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.

Task Summary MMEL or CDL Ref MMEL 28-07-04-03A MMEL 28-07-04-03B

Access YES YES

Test YES YES

1.

Reason for the Job MMEL 28-07-04-03A Crossfeed Valve Indication on the FUEL SD page MMEL 28-07-04-03B Crossfeed Valve Indication on the FUEL SD page

2

Job Set-up Information A.

Mhr 00.3 00.3

E/T 00.3 00.3

Nb Men 1 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Specific Tools YES YES

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) AR SAFETY BARRIER(S)

Work Zones and Access Panels ZONE/ACCESS 192MB

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-002-A - Crossfeed Valve Indication - Valve Operating Procedure

REFERENCE (Ref. 32-12-00-010-001-A). (Ref. 32-12-00-410-001-A). Fuel Crossfeed Valve SHEET 1

DESIGNATION Open the Main Gear Doors for Access Close the Main Gear Doors after Access

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-002-A - Crossfeed Valve Indication - Valve Operating Procedure

A

Z148

A REAR SPAR

ACTUATOR 5QE

CROSSFEED VALVE 10QM

B B

VALVE OPEN

VALVE CLOSED

N_MM_284000_4_ACM0_01_00

Figure 28-40-00-991-00200-00-A / SHEET 1/1 - Fuel Crossfeed Valve ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-002-A - Crossfeed Valve Indication - Valve Operating Procedure

3.

Job Set-up (Ref. Fig. Fuel Crossfeed Valve SHEET 1) Subtask 28-40-00-941-058-A A.

Safety Precautions WARNING: OBEY THE FUEL SAFETY PROCEDURES. (1) You must obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00-910-001) . (2) Put the SAFETY BARRIER(S) in position.

Subtask 28-40-00-010-055-A B.

Get Access (1) Open the RH MLG door (Ref. AMM TASK 32-12-00-010-001) . (2) Make sure that the SLEEVE - GROUND LOCK (460005835) is installed on the applicable MLG door actuating-cylinder. (3) Open the access door 192MB. NOTE: If operating in battery power, do not keep the door open longer than necessary because the battery can discharge. (4) Put an ACCESS PLATFORM 2M (6 FT) below the actuator 5QE of the fuel crossfeed valve 10QM.

Subtask 28-40-00-861-051-A C.

Energize the Electrical Circuits (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

Subtask 28-40-00-865-052-A D.

Table of the circuit breakers used in this procedure: PANEL 49VU 121VU

4.

DESIGNATION FUEL/X FEED/VALVE/MOT1 FUEL/X FEED/VALVE/MOT2

FIN 2QE 1QE

LOCATION A12 M24

Procedure (Ref. Fig. Fuel Crossfeed Valve SHEET 1) Subtask 28-40-00-040-051-A A.

Crossfeed Valve Indication - Valve Operating Procedure (1) In the test that follows, on each operation of the crossfeed valve: · listen to the actuator and make sure it stops each time the crossfeed valve moves to the end of its travel · make sure that the see/feel indicator operates smoothly, from the valve open (valve closed) position to the valve closed (valve open) position. (2) Do this test: ACTION 1.Open tag and safety C/B 1QE. 2.On the fuel control panel 40VU: · push (in) the X FEED pushbutton switch (P/ BSW).

RESULT On the panel 40VU: · the X FEED P/BSW ON light comes on

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-002-A - Crossfeed Valve Indication - Valve Operating Procedure

ACTION

3.On the fuel control panel 40VU: · release (out) the X FEED P/BSW.

4.Remove the safety clip(s) and the tag(s) and close C/B 1QE. 5.Open, safety and tag C/B 2QE. 6.On the fuel control panel 40VU: · push (in) the X FEED P/BSW.

RESULT · when the valve is fully open, the X FEED P/BSW OPEN light comes on. On the valve actuator, when the valve is fully open: · the see/feel indicator marks are accurately aligned in the valve open position. On the panel 40VU: · the X FEED P/BSW ON light goes off · when the valve is fully closed, the X FEED P/ BSW OPEN light goes off. On the valve actuator, when the valve is fully closed: · the see/feel indicator marks are at 90 degrees to one another in the valve closed position.

On the panel 40VU: · the X FEED P/BSW ON light comes on. NOTE: The X FEED P/BSW OPEN light will not come on when cicuit breaker 2QE is open. On the valve actuator, when the valve is fully open: - the see/feel indicator marks are accurately aligned in the valve open position.

7.On the fuel control panel 40VU: · release (out) the X FEED P/BSW.

On the panel 40VU: · the X FEED P/BSW ON light goes off. On the valve actuator, when the valve is fully closed: · the see/feel indicator marks are at 90 degrees to one another in the valve closed position.

8.Remove the safety clip(s) and the tag(s) and close C/B 2QE. 5.

Close-up Subtask 28-40-00-410-052-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the RH MLG door (Ref. AMM TASK 32-12-00-410-001) . (3) Close the access door 192MB.

Subtask 28-40-00-862-051-A B.

De-energize the Electrical Circuits (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Subtask 28-40-00-942-055-A C.

Removal of Equipment

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-002-A - Crossfeed Valve Indication - Valve Operating Procedure

(1) Make a note in the aircraft technical log to say that the crossfeed valve indication (on the ECAM lower DU) is deactivated. (2) Remove the safety barriers. (3) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-12-00-040-003-A - To Set the Transfer Valves Open for Flight

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 TASK 28-12-00-040-003-A To Set the Transfer Valves Open for Flight 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.

FIN : 27QM , 29QM , 28QM , 30QM 1.

Reason for the Job MMEL 28-12-01B Overpressure Protector between the Inner and the Outer Tank

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR SAFETY BARRIER(S)

Referenced Information REFERENCE (Ref. 12-11-28-650-003-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A).

3.

DESIGNATION Pressure Refuel with Automatic Control Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures EIS Start Procedure EIS Stop Procedure

Job Set-up Subtask 28-12-00-941-062-A A.

Safety Precautions WARNING: OBEY THE FUEL SAFETY PROCEDURES.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-12-00-040-003-A - To Set the Transfer Valves Open for Flight

(1) You must obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00-910-001) . (2) Put the SAFETY BARRIER(S) in position. ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 206-209, 211-225, 227-233, 235-250, 301-400, 500-600 Subtask 28-12-00-650-058-A B.

Fuel Configuration (1) Refuel the aircraft with the necessary quantity of fuel (Ref. AMM TASK 12-11-28-650-003) . (2) Before you continue with this procedure make sure that: · the quantity of fuel onboard the aircraft is correct · the refuel/defuel panel door is closed.

** ON A/C 205-205, 210-210, 226-226, 234-234 Subtask 28-12-00-650-058-C B.

Fuel Configuration (1) Refuel the aircraft with the necessary quantity of fuel (Ref. AMM TASK 12-11-28-650-003) . (2) Before you continue with this procedure make sure that: · The quantity of fuel onboard the aircraft is correct · The refuel/defuel panel door is closed. · In the cockpit, on overhead panel 51VU, pushbutton switch 23QU is set to the OFF position.

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 28-12-00-860-065-A C.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Do the EIS start procedure (ECAM only) (Ref. AMM TASK 31-60-00-860-001) . (3) On the ECAM control panel, push the FUEL pushbutton switch to show the FUEL page on the ECAM lower display unit.

Subtask 28-12-00-865-058-A D.

Table of the circuit breakers used in this procedure: PANEL DESIGNATION FIN FOR FIN 102QM (PROTECTOR-OVERPRESSURE, L WING TK) 49VU FUEL/XFR VALVE1/WING/R 2QP 121VU FUEL/XFR VALVE2/WING/R 4QP FOR FIN 103QM (PROTECTOR-OVERPRESSURE, R WING TK) 49VU FUEL/XFR VALVE1/WING/L 1QP 121VU FUEL/XFR VALVE2/WING/L 3QP

4.

LOCATION A11 M23 A10 M22

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 206-209, 211-225, 227-233, 235-250, 301-400, 500-600 Subtask 28-12-00-040-054-A A.

To Set the LH Wing Transfer Valves 27QM and 28QM Open for Flight (1) If the LH Overpressure Protector 102QM is damaged do this procedure:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-12-00-040-003-A - To Set the Transfer Valves Open for Flight

NOTE: The circuit breakers must be opened and closed in the sequence given.

ACTION 1.On the panel 49VU: · open the circuit breaker 2QP

· wait ten seconds. 2.On the panel 121VU: · open the circuit breaker 4QP

· wait ten seconds. 3.On the panel 49VU: · close the circuit breaker 2QP.

RESULT · the green left-wing transfer-valve indicator moves from the closed position to the open position · the green right-wing transfer-valve indicator moves from the closed position to the intermediate (amber) position · the left-wing outer-cell fuel content decreases and the left-wing inner-cell fuel content increases.

· the green left-wing transfer-valve indicator, open position stays in view · the amber right-wing transfer-valve indicator, intermediate (amber) position stays in view · the left-wing outer-cell fuel content decreases and the left-wing inner-cell fuel content increases.

· the amber right-wing transfer-valve indicator moves from the intermediate position to the green open position · both wing outer-cell fuel contents decrease and the inner-cell fuel contents increase.

4.On the panel 121VU: · close the circuit breaker 4QP. (2) Monitor the wing fuel quantity indications on the ECAM display unit. Make sure the quantity of fuel in the wing tank inner cell increases as fuel moves from the outer cell. The LH wing transfer valves are now set to the open position and the aircraft is ready for flight. NOTE: The wing transfer valves will close again if the refuel/defuel panel door is opened. Subtask 28-12-00-040-055-A B.

To Set the RH Wing Transfer Valves 29QM and 30QM Open for Flight (1) If the RH Overpressure Protector 103QM is damaged do this procedure: NOTE: The circuit breakers must be opened and closed in the sequence given.

ACTION 1.On the panel 49VU: · open circuit breaker 1QP

RESULT · the green right-wing transfer-valve indicator moves from the closed position to the open position

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-12-00-040-003-A - To Set the Transfer Valves Open for Flight

ACTION

· wait ten seconds. 2.On the panel 121VU: · open the circuit breaker 3QP

· wait ten seconds. 3.On the panel 49VU: · close the circuit breaker 1QP.

RESULT · the green left-wing transfer-valve indicator moves from the closed position to the intermediate (amber) position · the right-wing outer-cell fuel content decreases and the right-wing inner-cell fuel content increases.

· the green right-wing transfer-valve indicator, open position stays in view · the amber left-wing transfer-valve indicator, intermediate (amber) position stays in view · the right-wing outer-cell fuel content decreases and the right-wing inner-cell fuel content increases.

· the amber left-wing transfer valve indicator moves from the intermediate position to the green open position · both wing outer cell fuel contents decrease and the inner cell fuel contents increase.

4.On panel 121VU: · close the circuit breaker 3QP. (2) Monitor the wing fuel quantity indications on the ECAM display unit. Make sure the quantity of fuel in the wing tank inner cell increases as fuel moves from the outer cell. The RH wing transfer valves are now set to the open position and the aircraft is ready for flight. NOTE: The wing transfer valves will close again if the refuel/defuel panel door is opened. ** ON A/C 205-205, 210-210, 226-226, 234-234 Subtask 28-12-00-040-054-C A.

To Set LH Wing Transfer-Valves 27QM and 28QM Open for Flight (1) If LH Overpressure-Protector 102QM is damaged do this procedure: NOTE: The circuit breakers must be open and close in the given sequence.

ACTION 1.On panel 49VU: · Open circuit breaker 2QP

RESULT · The green left-wing transfer-valve indicator moves from the close position to the open position · The green right-wing transfer-valve indicator moves from the close position to the intermediate (amber) position · The left-wing outer-cell fuel content decreases and the left-wing inner-cell fuel content increases.

· Wait for ten seconds.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-12-00-040-003-A - To Set the Transfer Valves Open for Flight

ACTION 2.On panel 121VU: · Open circuit breaker 4QP

· Wait for ten seconds. 3.On panel 49VU: · Close circuit breaker 2QP.

RESULT · The green left-wing transfer-valve indicator, open position stays in view · The amber right-wing transfer-valve indicator, intermediate (amber) position stays in view · The left-wing outer-cell fuel content decreases and the left-wing inner-cell fuel content increases.

· The amber right-wing transfer-valve indicator moves from the intermediate position to the green open position. · Both wing outer-cell fuel contents decrease and the inner-cell fuel contents increase.

4.On panel 121VU: · Close circuit breaker 4QP. (2) Monitor the wing fuel quantity indications on the ECAM display unit. (3) Make sure the quantity of fuel in the wing tank inner-cells increase as fuel moves from the outer cells. (4) The LH wing transfer-valves are now set to the open position. NOTE: The wing transfer valves will close again if: - The refuel/defuel panel door is open or - In the cockpit, on overhead panel 51VU, pushbutton switch 23QU is set to the ON position. Subtask 28-12-00-040-055-C B.

To Set RH Wing Transfer-Valves 29QM and 30QM Open for Flight (1) If RH Overpressure-Protector 103QM is damaged do this procedure: NOTE: The circuit breakers must be open and close in the given sequence.

ACTION 1.On panel 49VU: · Open circuit breaker 1QP.

· Wait for ten seconds. 2.On panel 121VU: · Open circuit breaker 3QP.

RESULT · The green right-wing transfer-valve indicator moves from the close position to the open position · The green left-wing transfer-valve indicator moves from the close position to the intermediate (amber) position · The right-wing outer-cell fuel content decreases and the right-wing inner-cell fuel content increases.

· The green right-wing transfer-valve indicator open position stays in view. · The amber left-wing transfer-valve indicator intermediate (amber) position stays in view.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-12-00-040-003-A - To Set the Transfer Valves Open for Flight

ACTION

· Wait for ten seconds. 3.On panel 49VU: · Close circuit breaker 1QP.

RESULT · The right-wing outer-cell fuel content decreases and the right-wing inner-cell fuel content increases.

· The amber left-wing transfer-valve indicator moves from the intermediate position to the green open position · Both wing outer cell fuel contents decrease and the inner cell fuel contents increase.

4.On panel 121VU: · Close circuit breaker 3QP. (2) Monitor the wing fuel quantity indications on the ECAM display unit. (3) Make sure the quantity of fuel in the wing tank inner-cells increase as fuel moves from the outer cells. (4) The RH wing transfer-valves are now set to the open position. NOTE: The wing transfer valves will close again if: - The refuel/defuel panel door is open or - In the cockpit, on overhead panel 51VU, pushbutton switch 23QU is set to the ON position. ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 5.

Close-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 206-209, 211-225, 227-233, 235-250, 301-400, 500-600 Subtask 28-12-00-860-066-A A.

Aircraft Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (3) Make a note in the aircraft technical log that the applicable transfer valves are set to the open position.

** ON A/C 205-205, 210-210, 226-226, 234-234 Subtask 28-12-00-860-066-C A.

Aircraft Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (3) Make a note in the aircraft technical log that: · The applicable transfer valves are set to the open position · In the cockpit, on overhead panel 51VU, pushbutton switch 23QU is set to the ON position.

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 28-12-00-942-065-A B.

Removal of Equipment (1) Remove the SAFETY BARRIER(S).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-12-00-040-003-A - To Set the Transfer Valves Open for Flight

(2) Make sure that the work area is clean and clear of tools and other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-15-00-040-001-A - To Set the LH Wing Transfer Valve Open for Flight

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 TASK 28-15-00-040-001-A To Set the LH Wing Transfer Valve Open for Flight 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.

FIN : 27QM , 28QM 1.

Reason for the Job MMEL 28-15-01C LH Wing Transfer Valve NOTE: This procedure must only be done if the aircraft is energized and will stay energized until take-off. If possible do this procedure immediately before take-off. This will prevent possible fuel overflow from the outer fuel tanks into the vent system. If you de-energize the aircraft after this procedure and before take-off, you must do this procedure again when the aircraft is energized. This is because the transfer valve will close when the aircraft is energized again.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR SAFETY BARRIER(S)

Referenced Information REFERENCE (Ref. 12-11-28-650-003-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 28-00-00-910-001-A). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A).

3.

DESIGNATION Pressure Refuel with Automatic Control Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) Fuel Safety Procedures EIS Start Procedure EIS Stop Procedure

Job Set-up Subtask 28-15-00-941-056-A A.

Safety Precautions WARNING: OBEY THE FUEL SAFETY PROCEDURES.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-15-00-040-001-A - To Set the LH Wing Transfer Valve Open for Flight

(1) You must obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00-910-001) . (2) Put the SAFETY BARRIER(S) in position. ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 206-209, 211-225, 227-233, 235-250, 301-400, 500-600 Subtask 28-15-00-650-054-A B.

Fuel Configuration (1) Refuel the aircraft with the necessary quantity of fuel (Ref. AMM TASK 12-11-28-650-003) . (2) Before you continue with this procedure make sure that: · the quantity of fuel onboard the aircraft is correct · the refuel/defuel panel door is closed.

** ON A/C 205-205, 210-210, 226-226, 234-234 Subtask 28-15-00-650-054-C B.

Fuel Configuration (1) Refuel the aircraft with the necessary quantity of fuel (Ref. AMM TASK 12-11-28-650-003) . (2) Before you continue with this procedure make sure that: · The quantity of fuel onboard the aircraft is correct · The refuel/defuel panel door is close · In the cockpit, on panel 51VU, pushbutton switch 23QU is set to the OFF position.

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 28-15-00-860-058-A C.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Do the EIS start procedure (ECAM only) (Ref. AMM TASK 31-60-00-860-001) . (3) On the ECAM control panel, push (in) the FUEL pushbutton switch to show the FUEL page on the ECAM lower display unit.

Subtask 28-15-00-865-053-A D.

Table of the circuit breakers used in this procedure: PANEL 49VU 121VU

4.

DESIGNATION FUEL/XFR VALVE1/WING/R FUEL/XFR VALVE2/WING/R

FIN 2QP 4QP

LOCATION A11 M23

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 206-209, 211-225, 227-233, 235-250, 301-400, 500-600 Subtask 28-15-00-040-050-A A.

To Set the Transfer Valve 27QM Open for Flight (1) If the transfer valve 28QM is unserviceable, set the transfer valve 27QM to the open position as follows: ACTION 1.On the panel 121VU: · open the circuit breaker 4QP · wait for ten seconds.

RESULT · the green left-wing transfer-valve indicator moves from the closed position to the open position

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-15-00-040-001-A - To Set the LH Wing Transfer Valve Open for Flight

ACTION

2.On the panel 121VU: · close the circuit breaker 4QP.

RESULT · the green right-wing transfer-valve indicator moves from the closed position to the intermediate (amber) position · the fuel content in the left wing outer-cell decreases and the fuel content in the left wing inner-cell increases. · the amber right-wing transfer-valve indicator moves from the intermediate position to the green open position · the fuel content in the wings outer-cell decreases and the fuel content in the wings inner-cell increases.

(2) Monitor the wing fuel-quantity indication on the ECAM display unit. (3) Make sure the quantities of fuel in the wing tank inner-cells increase as fuel moves from the outer cells. (4) The LH and RH wing transfer-valves are now set to the open position and the aircraft is ready for flight. NOTE: The wing transfer valves will close again if: - the refuel/defuel panel door is opened - the aircraft is energized. ** ON A/C 205-205, 210-210, 226-226, 234-234 Subtask 28-15-00-040-050-C A.

To Set Transfer Valve 27QM Open for Flight (1) If transfer valve 28QM is unserviceable, set transfer valve 27QM to the open position as follows: ACTION 1.On panel 121VU: · Open circuit breaker 4QP · Wait for ten seconds.

·

·

·

2.On panel 121VU: · Close circuit breaker 4QP.

·

·

RESULT The green left-wing transfer-valve indicator moves from the close position to the open position The green right-wing transfer-valve indicator moves from the close position to the intermediate (amber) position The fuel content in the left wing outer-cell decreases and the fuel content in the left wing inner-cell increases. The amber right-wing transfer-valve indicator moves from the intermediate position to the green open position The fuel content in the wings outer-cell decreases and the fuel content in the wings inner cell increases.

(2) Monitor the wing fuel-quantity indication on the ECAM display unit. (3) Make sure the quantities of fuel in the wing tank inner-cells increases as fuel moves from the outer cells. (4) The LH and RH wing transfer-valves are now set to the open position.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-15-00-040-001-A - To Set the LH Wing Transfer Valve Open for Flight

NOTE: The wing transfer valves will close again if: - The refuel/defuel panel door is open - The aircraft is energized - In the cockpit, on panel 51VU, pushbutton switch 23QU is set to the ON position - The cockpit refuel panel is used to energize the refuel bus. ** ON A/C 016-022, 024-079, 112-150, 201-201, 203-204, 206-209, 211-225, 227-233, 235-250, 350-350 PRE SB 28-1216 for A/C 016-022, 024-079, 112-114, 201-201, 203-204, 206-209, 211-225, 227-230, 233-233, 235-236, 238-243, 350-350 EMB SB 31-1373 for A/C 016-022, 024-072, 112-115, 201-201, 207-209, 212-225, 227-233, 235-239, 241-242, 244-244, 350-350 EMB SB 31-1414 for A/C 016-022, 024-072, 112-115, 201-201, 203-204, 206-209, 211-225, 227-233, 235-244, 350-350 Subtask 28-15-00-040-052-A B.

To Set the Transfer Valve 28QM Open for Flight (1) If the transfer valve 27QM is unserviceable, set the transfer valve 28QM to the open position as follows: ACTION 1.On the panel 49VU: · open the circuit breaker 2QP · wait for ten seconds.

2.On panel 49VU: · close the circuit breaker 2QP.

RESULT · the green left-wing transfer-valve indicator moves from the closed position to the open position · the green right-wing transfer-valve indicator moves from the closed position to the intermediate (amber) position · the fuel content in the left wing outer-cell decreases and the fuel content in the left wing inner-cell increases. · the amber right-wing transfer-valve indicator moves from the intermediate position to the green open position · the fuel content in the wings outer-cell decreases and the fuel content in the wings inner-cell increases.

(2) Monitor the wing fuel-quantity indication on the ECAM display unit. (3) Make sure the quantities of fuel in the wing tank inner-cells increase as fuel moves from the outer cells. (4) The LH and RH wing transfer-valves are now set to the open position and the aircraft is ready for flight. NOTE: The wing transfer valves will close again if: - the refuel/defuel panel door is opened - the aircraft is energized. ** ON A/C 205-205, 210-210, 226-226, 234-234 PRE SB 28-1216 for A/C 205-205, 210-210, 226-226, 234-234 EMB SB 31-1373 for A/C 210-210, 226-226, 234-234 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-15-00-040-001-A - To Set the LH Wing Transfer Valve Open for Flight

EMB SB 31-1414 for A/C 205-205, 210-210, 226-226, 234-234 Subtask 28-15-00-040-052-C B.

To Set the Transfer Valve 28QM Open for Flight (1) If the transfer valve 27QM is unserviceable, set the transfer valve 28QM to the open position as follows: ACTION 1.On the panel 49VU: · open the circuit breaker 2QP · wait for ten seconds.

2.On panel 49VU: · close the circuit breaker 2QP.

RESULT · the green left-wing transfer-valve indicator moves from the closed position to the open position · the green right-wing transfer-valve indicator moves from the closed position to the intermediate (amber) position · the fuel content in the left wing outer-cell decreases and the fuel content in the left wing inner-cell increases. · the amber right-wing transfer-valve indicator moves from the intermediate position to the green open position · the fuel content in the wings outer-cell decreases and the fuel content in the wings inner-cell increases.

(2) Monitor the wing fuel-quantity indication on the ECAM display unit. (3) Make sure the quantities of fuel in the wing tank inner-cells increase as fuel moves from the outer cells. (4) The LH and RH wing transfer-valves are now set to the open position and the aircraft is ready for flight. NOTE: The wing transfer valves will close again if: - the refuel/defuel panel door is opened - the aircraft is energized - in the cockpit, on the panel 51VU the P/BSW 23QU is set to the ON position - the cockpit refuel panel is used to energize the refuel bus. ** ON A/C 080-100, 301-349, 351-400, 500-600 POST SB 28-1216 for A/C 016-022, 024-079, 112-114, 201-201, 203-204, 206-209, 211-225, 227-230, 233-233, 235-236, 238-243, 350-350 EMB SB 31-1373 for A/C 016-022, 024-072, 112-114, 201-201, 207-209, 212-225, 227-230, 233-233, 235-236, 238-239, 241-242, 350-350 EMB SB 31-1414 for A/C 016-022, 024-072, 112-114, 201-201, 203-204, 206-209, 211-225, 227-230, 233-233, 235-236, 238-243, 350-350 Subtask 28-15-00-040-052-D B.

To Set the Transfer Valve 28QM Open for Flight (1) If the transfer valve 27QM is unserviceable, set the transfer valve 28QM to the open position as follows:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-15-00-040-001-A - To Set the LH Wing Transfer Valve Open for Flight

ACTION 1.On the panel 49VU: · open the circuit breaker 2QP · wait for ten seconds.

2.On panel 49VU: · close the circuit breaker 2QP.

RESULT · the green left-wing transfer-valve indicator moves from the closed position to the open position · the green right-wing transfer-valve indicator moves from the closed position to the intermediate (amber) position · the fuel content in the left wing outer-cell decreases and the fuel content in the left wing inner-cell increases · the ECAM upper DU will show the caution FUEL R WING TK OVERFLOW. · the amber right-wing transfer-valve indicator moves from the intermediate position to the green open position · the fuel content in the wings outer-cell decreases and the fuel content in the wings inner-cell increases · on the ECAM upper DU, the caution FUEL R WING TK OVERFLOW goes off.

(2) Monitor the wing fuel-quantity indication on the ECAM display unit. (3) Make sure the quantities of fuel in the wing tank inner-cells increase as fuel moves from the outer cells. (4) The LH and RH wing transfer-valves are now set to the open position and the aircraft is ready for flight. NOTE: The wing transfer valves will close again if: - the refuel/defuel panel door is opened - the aircraft is energized. ** ON A/C POST SB 28-1216 for A/C 205-205, 210-210, 226-226, 234-234 EMB SB 31-1373 for A/C 210-210, 226-226, 234-234 EMB SB 31-1414 for A/C 205-205, 210-210, 226-226, 234-234 Subtask 28-15-00-040-052-E B.

To Set Transfer Valve 28QM Open for Flight (1) If transfer valve 27QM is unserviceable, set transfer valve 28QM to the open position as follows: ACTION 1.On panel 49VU: · Open circuit breaker 2QP · Wait for ten seconds.

RESULT · The green left-wing transfer-valve indicator moves from the close position to the open position · The green right-wing transfer-valve indicator moves from the close position to the intermediate (amber) position · The fuel content in the left wing outer-cell decreases and the fuel content in the left wing inner-cell increases

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-15-00-040-001-A - To Set the LH Wing Transfer Valve Open for Flight

ACTION

2.On panel 49VU: · Close circuit breaker 2QP.

RESULT · The ECAM upper DU will show the caution FUEL R WING TK OVERFLOW. · The amber right-wing transfer-valve indicator moves from the intermediate position to the green open position · The fuel content in the wings outer-cell decreases and the fuel content in the wings inner cell increases · On the ECAM upper DU, the caution FUEL R WING TK OVERFLOW goes off.

(2) Monitor the wing fuel-quantity indication on the ECAM display unit. (3) Make sure the quantities of fuel in the wing tank inner-cells increase as fuel moves from the outer cells. (4) The LH and RH wing transfer-valves are set to the open position. NOTE: The wing transfer valves will close again if: - The refuel/defuel panel door is open - The aircraft is energized - In the cockpit, on panel 51VU, pushbutton switch 23QU is set to the ON position - The cockpit refuel panel is used to energize the refuel bus. ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 5.

Close-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 206-209, 211-225, 227-233, 235-250, 301-400, 500-600 Subtask 28-15-00-860-059-A A.

Aircraft Maintenance Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) Make a note in the aircraft technical log that the applicable LH and RH wing transfer-valves are set to the open position.

** ON A/C 205-205, 210-210, 226-226, 234-234 Subtask 28-15-00-860-059-C A.

Aircraft Maintenance Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) Make a note in the aircraft technical log that: · The applicable LH and RH wing transfer-valves are set to the open position · In the cockpit, on panel 51VU, pushbutton switch 23QU must not be set to the ON position.

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 28-15-00-942-054-A B.

Removal of Equipment (1) Remove the SAFETY BARRIER(S). (2) Make sure that the work area is clean and clear of tools and other items.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-15-00-040-001-A - To Set the LH Wing Transfer Valve Open for Flight

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-15-00-040-002-A - To Set the RH Wing Transfer Valve Open for Flight

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 TASK 28-15-00-040-002-A To Set the RH Wing Transfer Valve Open for Flight 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.

FIN : 29QM , 30QM 1.

Reason for the Job MMEL 28-15-02C RH Wing Transfer Valve NOTE: This procedure must only be done if the aircraft is energized and will stay energized until take-off. If possible do this procedure immediately before take-off. This will prevent possible fuel overflow from the outer fuel tanks into the vent system. If you de-energize the aircraft after this procedure and before take-off, you must do this procedure again when the aircraft is energized. This is because the transfer valve will close when the aircraft is energized again.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR SAFETY BARRIER(S)

Referenced Information REFERENCE (Ref. 12-11-28-650-003-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 28-00-00-910-001-A). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A).

3.

DESIGNATION Pressure Refuel with Automatic Control Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) Fuel Safety Procedures EIS Start Procedure EIS Stop Procedure

Job Set-up Subtask 28-15-00-941-057-A A.

Safety Precautions WARNING: OBEY THE FUEL SAFETY PROCEDURES.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-15-00-040-002-A - To Set the RH Wing Transfer Valve Open for Flight

(1) You must obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00-910-001) . (2) Put the SAFETY BARRIER(S) in position. ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 206-209, 211-225, 227-233, 235-250, 301-400, 500-600 Subtask 28-15-00-650-055-A B.

Fuel Configuration (1) Refuel the aircraft with the necessary quantity of fuel (Ref. AMM TASK 12-11-28-650-003) . (2) Before you continue with this procedure make sure that: · the quantity of fuel onboard the aircraft is correct · the refuel/defuel panel door is closed.

** ON A/C 205-205, 210-210, 226-226, 234-234 Subtask 28-15-00-650-055-C B.

Fuel Configuration (1) Refuel the aircraft with the necessary quantity of fuel (Ref. AMM TASK 12-11-28-650-003) . (2) Before you continue with this procedure make sure that: · The quantity of fuel onboard the aircraft is correct · The refuel/defuel panel door is close · In the cockpit, on panel 51VU, pushbutton switch 23QU is set to the OFF position.

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 28-15-00-860-060-A C.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Do the EIS start procedure (ECAM only) (Ref. AMM TASK 31-60-00-860-001) . (3) On the ECAM control panel, push (in) the FUEL pushbutton switch to show the FUEL page on the ECAM lower display unit.

Subtask 28-15-00-865-054-A D.

Table of the circuit breakers used in this procedure: PANEL 49VU 121VU

4.

DESIGNATION FUEL/XFR VALVE1/WING/L FUEL/XFR VALVE2/WING/L

FIN 1QP 3QP

LOCATION A10 M22

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 206-209, 211-225, 227-233, 235-250, 301-400, 500-600 Subtask 28-15-00-040-051-A A.

To Set the Transfer Valve 29QM Open for Flight (1) If the transfer valve 30QM is unserviceable, set the transfer valve 29QM to the open position as follows: ACTION 1.On the panel 121VU: · open the circuit breaker 3QP · wait for ten seconds.

RESULT · the green right-wing transfer-valve indicator moves from the closed position to the open position

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-15-00-040-002-A - To Set the RH Wing Transfer Valve Open for Flight

ACTION

2.On the panel 121VU: · close the circuit breaker 3QP.

RESULT · the green left-wing transfer-valve indicator moves from the closed position to the intermediate (amber) position · the fuel content in the right wing outer-cell decreases and the fuel content in the right wing inner-cell increases. · the amber left-wing transfer-valve indicator moves from the intermediate position to the green open position · the fuel content in the wings outer-cell decreases and the fuel content in the wings inner-cell increases.

(2) Monitor the wing fuel-quantity indication on the ECAM display unit. (3) Make sure the quantities of fuel in the wing tank inner-cells increase as fuel moves from the outer cells. (4) The LH and RH wing transfer-valves are now set to the open position and the aircraft is ready for flight. NOTE: The wing transfer valves will close again if: - the refuel/defuel panel door is opened - the aircraft is energized. ** ON A/C 205-205, 210-210, 226-226, 234-234 Subtask 28-15-00-040-051-C A.

To Set Transfer Valve 29QM Open for Flight (1) If transfer valve 30QM is unserviceable, set transfer valve 29QM to the open position as follows: ACTION 1.On panel 121VU: · Open circuit breaker 3QP · Wait for ten seconds.

·

·

·

2.On panel 121VU: · Close circuit breaker 3QP.

·

·

RESULT The green right-wing transfer-valve indicator moves from the close position to the open position The green left-wing transfer-valve indicator moves from the close position to the intermediate (amber) position The fuel content in the right wing outer-cell decreases and the fuel content in the right wing inner-cell increases. The amber left-wing transfer-valve indicator moves from the intermediate position to the green open position The fuel content in the wings outer-cell decreases and the fuel content in the wings inner cell increases.

(2) Monitor the wing fuel-quantity indication on the ECAM display unit. (3) Make sure the quantities of fuel in the wing tank inner-cells increase as fuel moves from the outer cells. (4) The LH and RH wing transfer-valves are now set to the open position.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-15-00-040-002-A - To Set the RH Wing Transfer Valve Open for Flight

NOTE: The wing transfer valves will close again if: - The refuel/defuel panel door is open - The aircraft is energized - In the cockpit, on panel 51VU, pushbutton switch 23QU is set to the ON position - The cockpit refuel panel is used to energize the refuel bus. ** ON A/C 016-022, 024-079, 112-150, 201-201, 203-204, 206-209, 211-225, 227-233, 235-250, 350-350 PRE SB 28-1216 for A/C 016-022, 024-079, 112-114, 201-201, 203-204, 206-209, 211-225, 227-230, 233-233, 235-236, 238-243, 350-350 EMB SB 31-1373 for A/C 016-022, 024-072, 112-115, 201-201, 207-209, 212-225, 227-233, 235-239, 241-242, 244-244, 350-350 EMB SB 31-1414 for A/C 016-022, 024-072, 112-115, 201-201, 203-204, 206-209, 211-225, 227-233, 235-244, 350-350 Subtask 28-15-00-040-053-A B.

To Set the Transfer Valve 30QM Open for Flight (1) If the transfer valve 29QM is unserviceable, set the transfer valve 30QM to the open position as follows: ACTION 1.On the panel 49VU: · open the circuit breaker 1QP · wait for ten seconds.

2.On panel 49VU: · close the circuit breaker 1QP.

RESULT · the green right-wing transfer-valve indicator moves from the closed position to the open position · the green left-wing transfer-valve indicator moves from the closed position to the intermediate (amber) position · the fuel content in the right wing outer-cell decreases and the fuel content in the right wing inner-cell increases. · the amber left-wing transfer-valve indicator moves from the intermediate position to the green open position · the fuel content in the wings outer-cell decreases and the fuel content in the wings inner-cell increases.

(2) Monitor the wing fuel-quantity indication on the ECAM display unit. (3) Make sure the quantities of fuel in the wing tank inner-cells increase as fuel moves from the outer cells. (4) The LH and RH wing transfer-valves are now set to the open position and the aircraft is ready for flight. NOTE: The wing transfer valves will close again if: - the refuel/defuel panel door is opened - the aircraft is energized again. ** ON A/C 205-205, 210-210, 226-226, 234-234 PRE SB 28-1216 for A/C 205-205, 210-210, 226-226, 234-234 EMB SB 31-1373 for A/C 210-210, 226-226, 234-234 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-15-00-040-002-A - To Set the RH Wing Transfer Valve Open for Flight

EMB SB 31-1414 for A/C 205-205, 210-210, 226-226, 234-234 Subtask 28-15-00-040-053-C B.

To Set the Transfer Valve 30QM Open for Flight (1) If the transfer valve 29QM is unserviceable, set the transfer valve 30QM to the open position as follows: ACTION 1.On the panel 49VU: · open the circuit breaker 1QP · wait for ten seconds.

2.On panel 49VU: · close the circuit breaker 1QP.

RESULT · the green right-wing transfer-valve indicator moves from the closed position to the open position · the green left-wing transfer-valve indicator moves from the closed position to the intermediate (amber) position · the fuel content in the right wing outer-cell decreases and the fuel content in the right wing inner-cell increases. · the amber left-wing transfer-valve indicator moves from the intermediate position to the green open position · the fuel content in the wings outer-cell decreases and the fuel content in the wings inner-cell increases.

(2) Monitor the wing fuel-quantity indication on the ECAM display unit. (3) Make sure the quantities of fuel in the wing tank inner-cells increase as fuel moves from the outer cells. (4) The LH and RH wing transfer-valves are now set to the open position and the aircraft is ready for flight. NOTE: The wing transfer valves will close again if: - the refuel/defuel panel door is opened - the aircraft is energized - in the cockpit, on the panel 51VU the P/BSW 23QU is set to the ON position - the cockpit refuel panel is used to energize the refuel bus. ** ON A/C 080-100, 301-349, 351-400, 500-600 POST SB 28-1216 for A/C 016-022, 024-079, 112-114, 201-201, 203-204, 206-209, 211-225, 227-230, 233-233, 235-236, 238-243, 350-350 EMB SB 31-1373 for A/C 016-022, 024-072, 112-114, 201-201, 207-209, 212-225, 227-230, 233-233, 235-236, 238-239, 241-242, 350-350 EMB SB 31-1414 for A/C 016-022, 024-072, 112-114, 201-201, 203-204, 206-209, 211-225, 227-230, 233-233, 235-236, 238-243, 350-350 Subtask 28-15-00-040-053-D B.

To Set the Transfer Valve 30QM Open for Flight (1) If the transfer valve 29QM is unserviceable, set the transfer valve 30QM to the open position as follows:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-15-00-040-002-A - To Set the RH Wing Transfer Valve Open for Flight

ACTION 1.On the panel 49VU: · open the circuit breaker 1QP · wait for ten seconds.

2.On panel 49VU: · close the circuit breaker 1QP.

RESULT · the green right-wing transfer-valve indicator moves from the closed position to the open position · the green left-wing transfer-valve indicator moves from the closed position to the intermediate (amber) position · the fuel content in the right wing outer-cell decreases and the fuel content in the right wing inner-cell increases · the ECAM upper DU will show the caution FUEL L WING TK OVERFLOW. · the amber left-wing transfer-valve indicator moves from the intermediate position to the green open position · the fuel content in the wings outer-cell decreases and the fuel content in the wings inner-cell increases · on the ECAM upper DU, the caution FUEL L WING TK OVERFLOW goes off.

(2) Monitor the wing fuel-quantity indication on the ECAM display unit. (3) Make sure the quantities of fuel in the wing tank inner-cells increase as fuel moves from the outer cells. (4) The LH and RH wing transfer-valves are now set to the open position and the aircraft is ready for flight. NOTE: The wing transfer valves will close again if: - the refuel/defuel panel door is opened - the aircraft is energized again. ** ON A/C POST SB 28-1216 for A/C 205-205, 210-210, 226-226, 234-234 EMB SB 31-1373 for A/C 210-210, 226-226, 234-234 EMB SB 31-1414 for A/C 205-205, 210-210, 226-226, 234-234 Subtask 28-15-00-040-053-E B.

To Set Transfer Valve 30QM Open for Flight (1) If transfer valve 29QM is unserviceable, set transfer valve 30QM to the open position as follows: ACTION 1.On panel 49VU: · Open circuit breaker 1QP · Wait for ten seconds.

RESULT · The green right-wing transfer-valve indicator moves from the close position to the open position · The green left-wing transfer-valve indicator moves from the close position to the intermediate (amber) position · The fuel content in the right wing outer-cell decreases and the fuel content in the right wing inner-cell increases

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-15-00-040-002-A - To Set the RH Wing Transfer Valve Open for Flight

ACTION

2.On panel 49VU: · Close circuit breaker 1QP.

RESULT · The ECAM upper DU will show the caution FUEL L WING TK OVERFLOW. · The amber left-wing transfer-valve indicator moves from the intermediate position to the green open position · The fuel content in the wings outer-cell decreases and the fuel content in the wings inner cell increases · on the ECAM upper DU, the caution FUEL L WING TK OVERFLOW goes off.

(2) Monitor the wing fuel-quantity indication on the ECAM display unit. (3) Make sure the quantities of fuel in the wing tank inner-cells increase as fuel moves from the outer cells. (4) The LH and RH wing transfer-valves are set to the open position. NOTE: The wing transfer valves will close again if: - The refuel/defuel panel door is open - The aircraft is energized - In the cockpit, on panel 51VU, pushbutton switch 23QU is set to the ON position - The cockpit refuel panel is used to energize the refuel bus. ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 5.

Close-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 206-209, 211-225, 227-233, 235-250, 301-400, 500-600 Subtask 28-15-00-860-061-A A.

Aircraft Maintenance Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) Make a note in the aircraft technical log that the applicable LH and RH wing transfer-valves are set to the open position.

** ON A/C 205-205, 210-210, 226-226, 234-234 Subtask 28-15-00-860-061-C A.

Aircraft Maintenance Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) Make a note in the aircraft technical log that: · The applicable LH and RH wing transfer-valves are set to the open position · In the cockpit, on panel 51VU, pushbutton switch 23QU must not be set to the ON position.

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 28-15-00-942-055-A B.

Removal of Equipment (1) Remove the SAFETY BARRIER(S). (2) Make sure that the work area is clean and clear of tools and other items.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-15-00-040-002-A - To Set the RH Wing Transfer Valve Open for Flight

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-21-00-040-001-A - Check Operation of the Recirculation System When Main Fuel Pump 2 does not Operate

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 TASK 28-21-00-040-001-A Check Operation of the Recirculation System When Main Fuel Pump 2 does not Operate 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.

1.

Reason for the Job MMEL 28-21-01B Wing Tank Pump

2

Job Set-up Information A.

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-32-00-860-012-A).

3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Procedure to Get Access to the SYSTEM REPORT/TEST/ENG Page

Job Set-up Subtask 28-21-00-860-086-A A.

Aircraft Maintenance Configuration WARNING: MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. UNWANTED ELECTRICAL POWER CAN BE DANGEROUS. (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

Subtask 28-21-00-865-063-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 121VU 121VU

DESIGNATION ENGINE/2/FADEC A/AND EIU 2 ENGINE/1/FADEC A/AND EIU 1 ENGINE/ENG2/FADEC B/AND EIU 2 ENGINE/ENG1/FADEC B/AND EIU 1

FIN 2KS2 2KS1 4KS2 4KS1

LOCATION A05 A04 Q40 R41

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-21-00-040-001-A - Check Operation of the Recirculation System When Main Fuel Pump 2 does not Operate

4.

Procedure Subtask 28-21-00-040-050-A A.

Check Operation of the Recirculation System When Main Fuel Pump 2 does not Operate (1) Do this test: ACTION RESULT 1.On the MCDU, get access to the ENG page (Ref. AMM TASK 31-32-00-860-012) . 2.On the panel 50VU, make sure that the ENG/ On the panel 50VU, the ENG/FADEC GND PWR/1 FADEC GND PWR/1 pushbutton switch (P/BSW) P/BSW ON light is on. is released out. 3.On the MCDU: · push in the key adjacent to the FADEC 1A in- · the ENGINE 1 MAIN MENU is shown dication · push in the key adjacent to the FADEC TEST · the FADEC TEST ENGINE 1 CHANNEL A page indication is shown · push in the key adjacent to the PUSH BUTTON · this indication is shown: TO START TEST> indication. PUT THE MODE SELECTOR SWITCH TO PLACE THE MASTER LEVER SWITCH TO NOTE: The tests that follow are usually done without an air pressure supply to the engine starter motor (non-engine motor test). If air pressure is supplied, the engine fan blades will turn during the tests. You must obey the applicable safety precautions. 4.On the panel 115VU: · make sure that the MODE switch (6KS) is in the NORM (center) position · put the MASTER 1 switch to the ON position.

· this indication is shown: ***** WARNING ***** ***** TEST ACTIVE ***** · when the test has stopped this indication is shown: A NON-MONITORING TEST WAS PERFORMED DUE TO INSUFFICIENT STARTER AIR PRESSURE OR DUE TO A STARTER AIR VALVE FAILURE

5.On the MCDU: · push in the key adjacent to the DISPLAY NON- · the test results are shown MONITORING TEST RESULTS indication · make sure that the indication FRV, J7 ECU is not shown

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-21-00-040-001-A - Check Operation of the Recirculation System When Main Fuel Pump 2 does not Operate ACTION · push in the key adjacent to the RETURN indic- · ation. 6.On the panel 115VU, put the MASTER 1 switch to the OFF position. 7.On the MCDU: · push in the key adjacent to the RETURN indication until the SYSTEM REPORT/TEST ENG page is shown · push in the key adjacent to the FADEC 1B in- · dication · push in the key adjacent to the FADEC TEST · indication · push in the key adjacent to the PUSH BUTTON · TO START TEST> indication.

8.On the panel 115VU: · make sure that the MODE switch (6KS) is in the NORM (center) position · put the MASTER 1 switch to the ON position.

RESULT the TEST COMPLETE page is shown.

the ENGINE 1 MAIN MENU is shown the FADEC TEST ENGINE 1 CHANNEL B page is shown this indication is shown: PUT THE MODE SELECTOR SWITCH TO PLACE THE MASTER LEVER SWITCH TO

· this indication is shown: ***** WARNING ***** ***** TEST ACTIVE ***** · when the test has stopped this indication is shown: A NON-MONITORING TEST WAS PERFORMED DUE TO INSUFFICIENT STARTER AIR PRESSURE OR DUE TO A STARTER AIR VALVE FAILURE

9.On the MCDU: · push in the key adjacent to the DISPLAY NON- · the test results are shown MONITORING TEST RESULTS indication · make sure that the indication FRV, J8 ECU is not shown · push in the key adjacent to the RETURN indic- · the TEST COMPLETE page is shown. ation. 10.On the panel 115VU, put the MASTER 1 switch to the OFF position. 11.On the MCDU: · push in the key adjacent to the RETURN indication until the SYSTEM REPORT/TEST ENG page is shown. 12.On the panel 50VU: · push in the ENG/FADEC GND PWR 1 P/BSW · the OFF light of the ENG/FADEC GND PWR 1 P/BSW goes off · make sure that the ENG/FADEC GND PWR 2 · the ON light of the ENG/FADEC GND PWR 2 P/ P/BSW is released out. BSW is on. 13.On the MCDU: Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-21-00-040-001-A - Check Operation of the Recirculation System When Main Fuel Pump 2 does not Operate ACTION · push in the key adjacent to the FADEC 2A in- · dication · push in the key adjacent to the FADEC TEST · indication · push in the key adjacent to the PUSH BUTTON · TO START TEST> indication.

14.On the panel 115VU: · make sure that the MODE switch (6KS) is in the NORM (center) position · put the MASTER 2 switch to the ON position.

RESULT the ENGINE 2 MAIN MENU is shown the FADEC TEST ENGINE 2 CHANNEL A page is shown this indication is shown: PUT THE MODE SELECTOR SWITCH TO PLACE THE MASTER LEVER SWITCH TO

· this indication is shown: ***** WARNING ***** ***** TEST ACTIVE ***** · when the test has stopped this indication is shown: A NON-MONITORING TEST WAS PERFORMED DUE TO INSUFFICIENT STARTER AIR PRESSURE OR DUE TO A STARTER AIR VALVE FAILURE

15.On the MCDU: · push in the key adjacent to the DISPLAY NON- · MONITORING TEST RESULTS indication · make sure that the indication FRV, J7 ECU is not shown · push in the key adjacent to the RETURN indic- · ation. 16.On the panel 115VU, put the MASTER 2 switch to the OFF position. 17.On the MCDU: · push in the key adjacent to the RETURN indication until the SYSTEM REPORT/TEST ENG page is shown · push in the key adjacent to the FADEC 2B in- · dication · push in the key adjacent to the FADEC TEST · indication · push in the key adjacent to the PUSH BUTTON · TO START TEST> indication.

18.On the panel 115VU: · make sure that the MODE switch (6KS) is in the NORM (center) position · put the MASTER 2 switch to the ON position.

the test results are shown

the TEST COMPLETE page is shown.

the ENGINE 2 MAIN MENU is shown the FADEC TEST ENGINE 2 CHANNEL B page is shown this indication is shown: PUT THE MODE SELECTOR SWITCH TO PLACE THE MASTER LEVER SWITCH TO

· this indication is shown:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-21-00-040-001-A - Check Operation of the Recirculation System When Main Fuel Pump 2 does not Operate ACTION

RESULT ***** WARNING ***** ***** TEST ACTIVE ***** · when the test has stopped this indication is shown: A NON-MONITORING TEST WAS PERFORMED DUE TO INSUFFICIENT STARTER AIR PRESSURE OR DUE TO A STARTER AIR VALVE FAILURE

19.On the MCDU: · push in the key adjacent to the DISPLAY NON- · the test results are shown MONITORING TEST RESULTS indication · make sure that the indication FRV, J8 ECU is not shown · push in the key adjacent to the RETURN indic- · the TEST COMPLETE page is shown. ation. 20.On the panel 115VU, put the MASTER 2 switch to the OFF position. 21.On the panel 50VU: · push in the ENG/FADEC GND PWR 2 P/BSW. · the ON light of the ENG/FADEC GND PWR 2 P/ BSW goes off. 22.On the MCDU: · push in the key adjacent to the RETURN indication until the SYSTEM REPORT/TEST page is shown · push in the key adjacent to the FUEL indication · the FUEL page is shown · push in the NEXT PAGE key · the second FUEL page is shown · push in the key adjacent to the FLSS STATUS · the FLSS STATUS page is shown indication · make sure that none of these messages are shown: L SURGE SENSOR 28QJ1 R SURGE SENSOR 28QJ2 L INN TEMP SENSOR 29QJ1 R INN TEMP SENSOR 29QJ2 L OUT TEMP SENSOR 30QJ1 R OUT TEMP SENSOR 30QJ2 L LO LEVEL SENSOR 38QJ1 R LO LEVEL SENSOR 38QJ2 · push in the key adjacent to RETURN until the CFDS MENU page is shown · push in the MCDU MENU key. · the MCDU MENU is shown. 5.

Close-up Subtask 28-21-00-860-087-A A.

Aircraft Maintenance Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (2) Put a PLACARD in the cockpit to tell persons that the main fuel pump 2 is not in operation.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-21-00-040-001-A - Check Operation of the Recirculation System When Main Fuel Pump 2 does not Operate

(3) Put an applicable entry in the aircraft log book. Subtask 28-21-00-942-083-A B.

Removal of Equipment (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the WARNING NOTICE(S). (3) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-24-00-040-002-A - Functional Test of Engine LP Fuel Valve with a Defective Actuator Motor

** ON A/C ALL TASK 28-24-00-040-002-A Functional Test of Engine LP Fuel Valve with a Defective Actuator Motor 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.

FIN : 9QG , 10QG 1.

Reason for the Job MMEL 28-24-01A Engine LP Fuel Valve Electrical Motor

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

QTY 1 1 AR 1

DESIGNATION ACCESS PLATFORM 3M (10 FT) SAFETY BARRIER(S) SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 522AT, 622AT

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 57-41-37-000-003-A). (Ref. 57-41-37-400-003-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure Removal of the Access Panel Installation of the Access Panel

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-24-00-040-002-A - Functional Test of Engine LP Fuel Valve with a Defective Actuator Motor REFERENCE

DESIGNATION

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241, 301-349, 351-450, 500-600 LP Fuel Shut Off Valve - Location and Detail SHEET 1 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 LP Fuel Shut off Valve - Location and Detail SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-24-00-040-002-A - Functional Test of Engine LP Fuel Valve with a Defective Actuator Motor

ACCESS PANEL 522AT (622AT)

A

A

FRONT SPAR

LP FUEL VALVE 12QM 13QM

B

ACTUATOR 9QG 10QG VALVE CLOSED

B

VALVE OPEN

SEE / FEEL INDICATOR

N_MM_282400_4_AAM0_01_00

Figure 28-24-00-991-00900-00-A / SHEET 1/1 - LP Fuel Shut Off Valve - Location and Detail ** ON A/C 207-207, 210-210, 212-214, 217-218, 223226, 234-234, 236-236, 241-241, 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-24-00-040-002-A - Functional Test of Engine LP Fuel Valve with a Defective Actuator Motor

ACCESS PANEL 522AT (622AT) (UNDER SLAT)

A

A

FRONT SPAR

LP FUEL VALVE 12QM 13QM

B

ACTUATOR 9QG 10QG VALVE CLOSED

B

VALVE OPEN

SEE / FEEL INDICATOR

N_MM_282400_4_BAM0_01_00

Figure 28-24-00-991-00900-00-B / SHEET 1/1 - LP Fuel Shut off Valve - Location and Detail ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-24-00-040-002-A - Functional Test of Engine LP Fuel Valve with a Defective Actuator Motor

3.

Job Set-up Subtask 28-24-00-941-061-A A.

Safety Precautions (1) Put the SAFETY BARRIER(S) in position. (2) Put a WARNING NOTICE(S) in the cockpit to tell persons not to operate the flaps or slats. (3) Put a WARNING NOTICE(S) in the cockpit to tell persons not to operate the APU or bleed air. (4) Put a WARNING NOTICE(S) in the cockpit to tell persons not to start the engines.

Subtask 28-24-00-010-057-A B.

Get Access NOTE: It is necessary to listen to the LP valve actuator during the test that follows. If the actuator motor can be heard with the access panel in position, it is not necessary to remove it. ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241, 301-349, 351-450, 500-600 (Ref. Fig. LP Fuel Shut Off Valve - Location and Detail SHEET 1) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. LP Fuel Shut off Valve - Location and Detail SHEET 1) (1) Put an ACCESS PLATFORM 3M (10 FT) in position below the applicable zone 520 or 620. (2) Remove the applicable access panel (Ref. AMM TASK 57-41-37-000-003) : · for the LH LP valve, remove panel 522AT · for the RH LP valve, remove panel 622AT.

Subtask 28-24-00-865-071-A C.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 121VU 121VU

DESIGNATION FUEL/LP VALVE/MOT1/ENG2 FUEL/LP VALVE/MOT1/ENG1 FUEL/LP VALVE/MOT2/ENG2 FUEL/LP VALVE/MOT2/ENG1

FIN 2QG 1QG 4QG 3QG

LOCATION A09 A08 M26 M25

Subtask 28-24-00-865-072-A D.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU ENGINE/ENG1 AND 2 FIRE EX1WE1 Q43 TIG/BTL1/SQUIB/A 121VU ENGINE/ENG1 AND 2 FIRE EX1WE2 Q41 TIG/BTL2/SQUIB/A ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 121VU ENGINE/ENG1 AND 2 FIRE EX2WE1 TIG/BTL1/SQUIB/B

Q44

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-24-00-040-002-A - Functional Test of Engine LP Fuel Valve with a Defective Actuator Motor PANEL 121VU

DESIGNATION ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B

** ON A/C 301-349, 351-400, 500-600 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B ** ON A/C 401-450 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A

FIN 2WE2

Q42

LOCATION

2WE1

Q44

2WE2

Q42

2WE1

Q43

1WE1

Q42

2WE2

Q41

1WE2

Q40

** ON A/C ALL Subtask 28-24-00-860-066-A E.

Aircraft Maintenance Configuration (1) Deactivate the unserviceable motor on the defective LP valve actuator as follows: (a) If the LH actuator 9QG motor 1 is unserviceable: · open, safety and tag the circuit breaker 1QG. (b) If the LH actuator 9QG motor 2 is unserviceable: · open, safety and tag the circuit breaker 3QG. (c) If the RH actuator 10QG motor 1 is unserviceable: · open, safety and tag the circuit breaker 2QG. (d) If the RH actuator 10QG motor 2 is unserviceable: · open, safety and tag the circuit breaker 4QG. (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) Do the EIS start procedure (ECAM only) (Ref. AMM TASK 31-60-00-860-001) .

4.

Procedure Subtask 28-24-00-750-052-A A.

Test of the LH Engine LP Valve Actuator 9QG NOTE: It is necessary to have two persons for this test procedure. One person must be in the cockpit (to operate the LP valve) and one person must be near the LP valve (to listen to the actuator motor). (1) For the LH LP Valve Actuator 9QG, do this test: ACTION 1.On the ECAM CP: · Push (in) the FUEL P/BSW.

RESULT On the ECAM lower DU: · The FUEL system page shows · The LEFT LP valve indication shows the valve closed (amber cross-line).

2.On the panel 40VU: Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-24-00-040-002-A - Functional Test of Engine LP Fuel Valve with a Defective Actuator Motor ACTION · Push (in) the L TK PUMPS 1 P/BSW or L TK PUMPS 2 P/BSW.

RESULT · The applicable P/BSW OFF light goes off.

NOTE: This will pressurize the left engine feedline. On the ECAM lower DU: · The applicable L TK pump symbol changes from an amber cross-line to a green in-line. 3.On the panel 115VU: On the ECAM lower DU: · Put the ENG/MASTER 1 pushbutton switch to · The LEFT LP valve indication changes to show the ON position to open the LP valve. the valve open (green in-line). 4.On the LP valve actuator 9QG also: · Listen to the actuator motor and measure the · The actuator motor must not operate for more time that it operates for as the LP valve opens. than 4 seconds. 5.On the panel 40VU: · Release (out) the L TK PUMPS 1 P/BSW or L · The applicable P/BSW OFF light comes on. TK PUMPS 2 P/BSW and wait for 5 seconds. NOTE: This will release the pressure through the applicable suction valve. On the ECAM lower DU: · The FUEL page shows the applicable L TK pump symbol as an amber cross-line. 6.On the ENG/APU FIRE panel 1WD: On the ECAM lower DU: · Push (in) the ENG FIRE 1 pushbutton switch to · The LEFT LP valve indication changes to show close the LP valve. the valve closed (amber cross-line). 7.On the LP valve actuator 9QG also: · Listen to the actuator motor and measure the · The actuator motor must not operate for more time that it operates for as the LP valve closes. than 4 seconds. 8.On the panel 40VU: · Push (in) the L TK PUMPS 1 P/BSW or L TK · The applicable P/BSW OFF light goes off. PUMPS 2 P/BSW. NOTE: This will pressurize the left engine feedline. On the ECAM lower DU: · The applicable L TK pump symbol changes from an amber cross-line to a green in-line. On the ECAM lower DU: · The LEFT LP valve indication changes to show the valve open (green in-line).

9.On the ENG/APU FIRE panel 1WD: · Release (out) the ENG FIRE 1 pushbutton switch to open the LP valve. 10.On the LP valve actuator 9QG also: · Listen to the actuator motor and measure the · The actuator motor must not operate for more time that it operates for as the LP valve opens. than 4 seconds. 11.On the panel 40VU: · Release (out) the L TK PUMPS 1 P/BSW or L · The applicable P/BSW OFF light comes on. TK PUMPS 2 P/BSW and wait for 5 seconds.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-24-00-040-002-A - Functional Test of Engine LP Fuel Valve with a Defective Actuator Motor ACTION

RESULT

NOTE: This will release the pressure through the applicable suction valve. On the ECAM lower DU: · The FUEL page shows the applicable L TK pump symbol as an amber cross-line. 12.On the panel 115VU: On the ECAM lower DU: · Put the ENG/MASTER 1 pushbutton switch to · The LEFT LP valve indication changes to show the OFF position to close the LP valve. the valve closed (amber cross-line). 13.On the LP valve actuator 9QG also: · Listen to the actuator motor and measure the · The actuator motor must not operate for more time that it operates for as the LP valve closes. than 4 seconds. Subtask 28-24-00-750-053-A B.

Test of the RH Engine LP Valve Actuator 10QG NOTE: It is necessary to have two persons for this test procedure. One person must be in the cockpit (to operate the LP valve) and one person must be near the LP valve (to listen to the actuator motor). (1) For the RH LP Valve Actuator 10QG, do this test: ACTION 1.On the ECAM CP: · Push (in) the FUEL P/BSW.

2.On the panel 40VU: · Push (in) the R TK PUMPS 1 P/BSW or R TK PUMPS 2 P/BSW.

RESULT On the ECAM lower DU: · The FUEL system page shows · The RIGHT LP valve indication shows the valve closed (amber cross-line). · The applicable P/BSW OFF light goes off.

NOTE: This will pressurize the right engine feedline. On the ECAM lower DU: · The applicable R TK pump symbol changes from an amber cross-line to a green in-line. 3.On the panel 115VU: On the ECAM lower DU: · Put the ENG/MASTER 2 pushbutton switch to · The RIGHT LP valve indication changes to show the ON position to open the LP valve. the valve open (green in-line). 4.On the LP valve actuator 10QG also: · Listen to the actuator motor and measure the · The actuator motor must not operate for more time that it operates for as the LP valve opens. than 4 seconds. 5.On the panel 40VU: · Release (out) the R TK PUMPS 1 P/BSW or R · The applicable P/BSW OFF light comes on. TK PUMPS 2 P/BSW and wait for 5 seconds. NOTE: This will release the pressure through the applicable suction valve. On the ECAM lower DU:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-24-00-040-002-A - Functional Test of Engine LP Fuel Valve with a Defective Actuator Motor ACTION

RESULT · The FUEL page shows the applicable R TK pump symbol as an amber cross-line. 6.On the ENG/APU FIRE panel 1WD: On the ECAM lower DU: · Push (in) the ENG FIRE 2 pushbutton switch to · The RIGHT LP valve indication changes to show close the LP valve. the valve closed (amber cross-line). 7.On the LP valve actuator 10QG also: · Listen to the actuator motor and measure the · The actuator motor must not operate for more time that it operates for as the LP valve closes. than 4 seconds. 8.On the panel 40VU: · Push (in) the R TK PUMPS 1 P/BSW or R TK · The applicable P/BSW OFF light goes off. PUMPS 2 P/BSW. NOTE: This will pressurize the right engine feedline. On the ECAM lower DU: · The applicable R TK pump symbol changes from an amber cross-line to a green in-line. On the ECAM lower DU: · The RIGHT LP valve indication changes to show the valve open (green in-line).

9.On the ENG/APU FIRE panel 1WD: · Release (out) the ENG FIRE 2 pushbutton switch to open the LP valve. 10.On the LP valve actuator 10QG also: · Listen to the actuator motor and measure the · The actuator motor must not operate for more time that it operates for as the LP valve opens. than 4 seconds. 11.On the panel 40VU: · Release (out) the R TK PUMPS 1 P/BSW or R · The applicable P/BSW OFF light comes on. TK PUMPS 2 P/BSW and wait for 5 seconds. NOTE: This will release the pressure through the applicable suction valve.

On the ECAM lower DU: · The FUEL page shows the applicable R TK pump symbol as an amber cross-line. 12.On the panel 115VU: On the ECAM lower DU: · Put the ENG/MASTER 2 pushbutton switch to · The RIGHT LP valve indication changes to show the OFF position to close the LP valve. the valve closed (amber cross-line). 13.On the LP valve actuator 10QG also · Listen to the actuator motor and measure the · The actuator motor must not operate for more time that it operates for as the LP valve closes. than 4 seconds. 5.

Close-up Subtask 28-24-00-860-067-A A.

Aircraft Maintenance Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Subtask 28-24-00-865-073-A B.

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

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-24-00-040-002-A - Functional Test of Engine LP Fuel Valve with a Defective Actuator Motor

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU ENGINE/ENG1 AND 2 FIRE EX1WE1 Q43 TIG/BTL1/SQUIB/A 121VU ENGINE/ENG1 AND 2 FIRE EX1WE2 Q41 TIG/BTL2/SQUIB/A ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 121VU ENGINE/ENG1 AND 2 FIRE EX2WE1 TIG/BTL1/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EX2WE2 TIG/BTL2/SQUIB/B ** ON A/C 301-349, 351-400, 500-600 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B ** ON A/C 401-450 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B 121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A

Q44 Q42

2WE1

Q44

2WE2

Q42

2WE1

Q43

1WE1

Q42

2WE2

Q41

1WE2

Q40

** ON A/C ALL Subtask 28-24-00-410-058-A C.

Close Access (1) Install the applicable access panel (if removed) (Ref. AMM TASK 57-41-37-400-003) : · for the LH LP valve, install panel 522AT · for the RH LP valve, install panel 622AT.

Subtask 28-24-00-942-060-A D.

Removal of Equipment (1) Remove the safety barriers. (2) Remove the access platform(s). (3) Remove the WARNING NOTICE(S). (4) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (5) Make a note in the aircraft log that the defective motor of the LP valve is deactivated.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

** ON A/C ALL TASK 28-25-00-040-005-A Refuel Valve - Refuel Procedure Using Manual Plunger Override WARNING:

OBEY THE FUEL SAFETY PROCEDURES.

WARNING:

STOP THE FUEL TANKER 60 M (196.85 FT) FROM THE AIRCRAFT NOSE WHILE THE WEATHER RADAR OPERATES. DO NOT OPERATE THE FUEL TANKER/PUMP UNIT UNTIL YOU STOP THE OPERATION OF THE WEATHER RADAR.

WARNING:

MAKE SURE THE AREA AROUND THE AIRCRAFT IS SAFE BEFORE YOU START THE REFUEL/DEFUEL PROCEDURE. IN THE SAFETY AREA, DO NOT: - SMOKE - MAKE SPARKS OR FIRE - USE ANY EQUIPMENT WHICH IS NOT APPROVED FOR REFUEL/DEFUEL PROCEDURES. AIRCRAFT FUEL IS FLAMMABLE.

WARNING:

DO NOT SPILL FUEL ON THE ENGINES OR THE BRAKES. IF YOU SPILL FUEL ON ENGINES OR BRAKES THAT ARE HOT, IT CAN CAUSE FIRES.

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.

Task Summary MMEL or CDL Ref MMEL 28-25-03A 1.

Reason for the Job MMEL 28-25-03A Refuel Valve

2

Job Set-up Information A.

Access YES

Test YES

Specific Tools YES

Mhr 00.7

E/T 00.7

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

QTY DESIGNATION AR ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 416-450, 500-600 No specific AR ACCESS PLATFORM 4M (13 FT) ** ON A/C ALL No specific

AR PLACARD

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

B.

REFERENCE

QTY DESIGNATION

** ON A/C 401-415 No specific

2

** ON A/C ALL No specific No specific

AR SAFETY BARRIER(S) AR WARNING NOTICE(S)

ROD - NON METALLIC

Work Zones and Access Panels ZONE/ACCESS 140 190 500 600 192MB, 522JB, 622JB, 744

ZONE DESCRIPTION CENTER WING BELLY FAIR, AIR CONDITIONING & HYD COMPT LEFT WING RIGHT WING

** ON A/C 401-415 622HB, 734 ** ON A/C ALL C. Referenced Information REFERENCE (Ref. 12-11-28-650-001-A). (Ref. 12-11-28-650-002-A). (Ref. 12-34-24-869-001-A). (Ref. 28-00-00-910-001-A). (Ref. 28-25-00-869-001-A). (Ref. 32-12-00-010-001-A). (Ref. 32-12-00-410-001-A).

DESIGNATION General Refuel/Defuel Safety Procedures Refuel/Defuel Safety Procedures for use in the Hangar Aircraft Bonding and Grounding (Earthing) for the Refuel/Defuel or Oxygen Servicing Operations Fuel Safety Procedures Fuel Transfer Open the Main Gear Doors for Access Close the Main Gear Doors after Access

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 416-450, 500-600 Refuel Valve SHEET 1 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 205-250, 350-350 Refuel/Defuel Control Panel SHEET 1 ** ON A/C 204-204 Refuel/Defuel Control Panel SHEET 1 ** ON A/C 301-349, 351-400, 416-450, 500-600 Refuel/Defuel Control Panel SHEET 1 ** ON A/C 401-415 Refuel Valve SHEET 1 ** ON A/C 401-415 Refuel/Defuel Panels 800VU and 801VU SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

10QU

STA7792/RIB14

A

522 JB(622 JB)

STA8268/RIB15 REAR SPAR

A

7QU (8QU)

A

MANUALLY OPERATED PLUNGER

REFUEL VALVE

N_MM_282500_4_BAN0_01_00

Figure 28-25-00-991-02200-00-B / SHEET 1/1 - Refuel Valve ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 416-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

A

REFUEL COUPLING REFUEL/DEFUEL CONTROL PANEL

A

FUEL QTY kg x 1000 INDICATOR LEFT

CTR

HI.

RIGHT

LVL.

LEFT

CTR

RIGHT

REFUEL VALVES OPEN OPEN NORM NORM SHUT SHUT MODE

SELECT REFUEL

6QT

OPEN NORM SHUT

TEST BATT POWER HI. LVL ON

REFUEL DEFUEL CONTROL PANEL 800VU

OFF DEFUEL XFR

OPEN LTS

PRESELECTED

REFUEL

NORM ACTUAL

kg x 1000

DEC

INC CKPT

END

PRESELECTOR 5QT

N_MM_282500_4_CAM0_01_00

Figure 28-25-00-991-02400-00-G / SHEET 1/1 - Refuel/Defuel Control Panel ** ON A/C 016-022, 024-100, 112-150, 201-201, 203203, 205-250, 350-350 | EMB SB 31-1211 for A/C 219-220 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

A

REFUEL COUPLING REFUEL/DEFUEL CONTROL PANEL

A

FUEL QTY lbs x 1000 INDICATOR

CTR

LEFT

HI.

RIGHT

LVL. CTR

LEFT

RIGHT

REFUEL VALVES OPEN OPEN NORM NORM SHUT SHUT MODE

SELECT REFUEL

6QT

OPEN NORM SHUT

TEST BATT POWER HI. LVL ON

REFUEL DEFUEL CONTROL PANEL 800VU

OFF DEFUEL XFR PRESELECTED

OPEN LTS

REFUEL

NORM ACTUAL

lbs x 1000

DEC

INC CKPT

END

PRESELECTOR 5QT

N_MM_282500_4_CVM0_01_00

Figure 28-25-00-991-02400-00-H / SHEET 1/1 - Refuel/Defuel Control Panel ** ON A/C 204-204 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

REFUEL COUPLING

A

REFUEL/DEFUEL CONTROL PANEL

A FUEL QTY kg X 1000 LEFT

CTR

HI. LEFT

LVL. CTR

RIGHT

REFUEL VALVES OPEN OPEN NORM NORM SHUT SHUT MODE SELECT REFUEL

INDICATOR 6QT

RIGHT

TEST HI. LVL

OPEN NORM SHUT BATT POWER ON

OFF DEFUEL XFR PRESELECTED

DEC

OPEN LTS REFUEL kg X 1000

REFUEL/DEFUEL CONTROL PANEL 800VU

NORM ACTUAL

CKPT END

INC

PRESELECTOR 5QT

N_MM_282500_4_CAM2_01_00

Figure 28-25-00-991-02400-00-S / SHEET 1/1 - Refuel/Defuel Control Panel ** ON A/C 301-349, 351-400, 416-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

10QU 41QU

STA7792/RIB14

A

522 JB(622 JB)

STA8268/RIB15

A

A

REAR SPAR

7QU (8QU)

A

MANUALLY OPERATED PLUNGER

REFUEL VALVE

N_MM_282500_4_BAP0_01_00

Figure 28-25-00-991-02200-00-C / SHEET 1/1 - Refuel Valve ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

REFUEL COUPLING 40QM

A

622HB 192MB

REFUEL/DEFUEL CONTROL PANEL

INDICATOR 6QT

TOTAL ACT

FUEL QTY

ACT

kg x 1000

LEFT

RIGHT

CTR

LVL

HI LEFT

VALVES

REFUEL SW POS = OPEN

CTR

= NORM

AFT1

UP

REFUEL VALVE

OPEN

OPEN

OPEN

NORM

NORM

NORM

SHUT

SHUT

MODE SELECT

DOWN = SHUT

RIGHT

CTR

BATT POWER

HI LVL

ON

REFUEL

HI LVL

SHUT

TEST

REFUEL/DEFUEL CONTROL PANEL 800VU

OFF

DEFUEL / XFR OPEN

REFUEL

PRESELECTED

LTS

NORM ACTUAL

kg x 1000

801VU REFUEL/DEFUEL CONTROL PANEL

DEC

INC

CKPT

END

5QT PRESELECTOR

A

N_MM_282500_4_EEM1_01_00

Figure 28-25-00-991-03800-00-C / SHEET 1/1 - Refuel/Defuel Panels 800VU and 801VU ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

3.

Job Set-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 416-450, 500-600 (Ref. Fig. Refuel Valve SHEET 1) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 205-250, 350-350 EMB SB 31-1211 for A/C 219-220 (Ref. Fig. Refuel/Defuel Control Panel SHEET 1) ** ON A/C 204-204 (Ref. Fig. Refuel/Defuel Control Panel SHEET 1) ** ON A/C 301-349, 351-400, 416-450, 500-600 (Ref. Fig. Refuel/Defuel Control Panel SHEET 1) ** ON A/C 401-415 (Ref. Fig. Refuel Valve SHEET 1) (Ref. Fig. Refuel/Defuel Panels 800VU and 801VU SHEET 1) ** ON A/C ALL Subtask 28-25-00-941-079-A A.

Safety Precautions (1) Obey the fuel safety procedures (Ref. AMM TASK 28-00-00-910-001) . (2) You must obey the refuel/defuel safety procedures (Ref. AMM TASK 12-11-28-650-001) and (Ref. AMM TASK 12-11-28-650-002) . (3) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations. (4) Put the WARNING NOTICE(S) in position to tell persons not to operate the Main Landing Gear (MLG) doors.

** ON A/C 016-022, 024-100, 112-150, 203-205, 208-208, 210-221, 223-226, 229-235, 237-240, 242-250, 301400, 416-450, 500-600 Subtask 28-25-00-010-077-B B.

Get Access (1) Open the access panel 192MB to get access to the refuel panel 800VU. NOTE: If operating in battery power,do not keep the door open longer than necessary because the battery can discharge. (2) Put the ACCESS PLATFORM 4M (13 FT) adjacent to the refuel coupling 40QM. (3) To get access to the left refuel valve 7QU: (a) Put the ACCESS PLATFORM 4M (13 FT) in position below zone 522. (b) Remove the access panel 522JB. (4) To get access to the right refuel valve 8QU: (a) Put the ACCESS PLATFORM 4M (13 FT) in position below zone 622. (b) Remove the access panel 622JB. (5) To get access to the center tank refuel valve 10QU:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

(a) Open the RH MLG door 744 (Ref. AMM TASK 32-12-00-010-001) . (b) Make sure that the SLEEVE - GROUND LOCK (460005835) is on the applicable MLG door actuator. (c) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below zone 148. ** ON A/C 201-201, 206-207, 209-209, 222-222, 227-228, 236-236, 241-241 EMB SB 28-1030 for A/C 209-209 Subtask 28-25-00-010-077-F B.

Get Access (1) Open the access panel 192MB to get access to the refuel panel 800VU. NOTE: If operating in battery power, do not keep the door open longer than necessary because the battery can discharge. (2) Put the ACCESS PLATFORM 4M (13 FT) adjacent to the refuel coupling 100QM(40QM). (3) To get access to the left refuel valve 7QU: (a) Put the ACCESS PLATFORM 4M (13 FT) in position below zone 522. (b) Remove the access panel 522JB. (4) To get access to the right refuel valve 8QU: (a) Put the ACCESS PLATFORM 4M (13 FT) in position below zone 622. (b) Remove the access panel 622JB. (5) To get access to the center tank refuel valve 10QU: (a) Open the RH MLG door 744 (Ref. AMM TASK 32-12-00-010-001) . (b) Make sure that the SLEEVE - GROUND LOCK (460005835) is on the applicable MLG door actuator. (c) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below zone 148.

** ON A/C 401-415 Subtask 28-25-00-010-077-G B.

Get Access (1) Open access door 192MB to get access to refuel/defuel panels 800VU and 801VU: (a) If operating in battery power, do not keep the door open longer than necessary because the battery can discharge. (2) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE adjacent to refuel/defuel coupling 40QM. (3) Remove access panel 622HB. (4) To get access to left refuel valve 7QU: (a) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below zone 522. (b) Remove access panel 522JB. (5) To get access to right refuel valve 8QU: (a) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below zone 622. (b) Remove access panel 622JB.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

(6) To get access to center tank refuel valve 10QU: (a) Open RH MLG door 744 (Ref. AMM TASK 32-12-00-010-001) . (b) Make sure that the SLEEVE - GROUND LOCK (460005835) is on the applicable MLG door actuator. (c) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below zone 148. (7) To get access to ACT refuel valve 41QU: (a) Open LH MLG door 734 (Ref. AMM TASK 32-12-00-010-001) . (b) Make sure that the SLEEVE - GROUND LOCK (460005835) is on the applicable MLG door actuator. (c) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below zone 147. ** ON A/C 016-022, 024-100, 112-150, 203-205, 208-208, 210-221, 223-226, 229-235, 237-240, 242-250, 301400, 500-600 Subtask 28-25-00-860-060-A C.

Aircraft Maintenance Configuration (1) Make sure that the aircraft and the fuel tanker/pump unit are grounded correctly (Ref. AMM TASK 12-34-24-869-001) and electrically bonded together correctly. NOTE: Bonding is mandatory. For grounding you must obey the local area regulations. (2) Remove the refuel-coupling cap 41QM. (3) Make sure that the coupling of the fuel supply hose is clean before you connect it to the aircraft-refuel coupling 40QM. (4) If the intercell transfer valves are open: (a) Refuel the aircraft until there is a minimum of 1000 kg (2204.6220 lb) of fuel in the wing tank inner-cell. (b) On panels 49VU and 121VU, open the circuit breakers 1QT and 2QT. NOTE: It is not necessary to install safety clips and tags on the circuit breakers. (c) After a minimum of 5 seconds the FQIC will de-energize. (d) On panels 49VU and 121VU, close the circuit breakers 1QT and 2QT. (e) After a minimum of 60 seconds the FQIC will energize and operates the intercell transfer valves. (f)

If the intercell transfer valves stay open: · The inner and outer cells of the wing tanks fill together · The full capacity of the wing tank is less than normal · Make an entry in the aircraft technical log, to correct the fuel configuration before the next flight (the wing tank outer-cells must be filled).

** ON A/C 201-201, 206-207, 209-209, 222-222, 227-228, 236-236, 241-241 EMB SB 28-1030 for A/C 209-209 Subtask 28-25-00-860-060-C C.

Aircraft Maintenance Configuration

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

(1) Make sure that the aircraft and the fuel tanker/pump unit are grounded correctly (Ref. AMM TASK 12-34-24-869-001) and electrically bonded together correctly. NOTE: Bonding is mandatory. For grounding you must obey the local area regulations. (2) Remove the refuel coupling cap 101QM (41QM). (3) Make sure that the coupling of the fuel supply-hose is clean and then connect it to the aircraft refuel coupling 100QM (40QM). (4) If the intercell transfer valves are open: (a) Refuel the aircraft until there is a minimum of 1000 kg (2204.6220 lb) of fuel in the wing-tank inner-cell. (b) On panels 49VU and 121VU, open the circuit breakers 1QT and 2QT. NOTE: It is not necessary to install safety clips and tags on the circuit breakers. (c) After a minimum of 5 seconds, the FQIC will de-energize. (d) On panels 49VU and 121VU, close the circuit breakers 1QT and 2QT. (e) After a minimum of 60 seconds, the FQIC will energize again and cycle the intercell transfer valves. (f)

If the intercell transfer valves stay open: · the inner and outer cells of the wing tanks fill together · the full capacity of the wing tank is less than normal · make an entry in the aircraft technical log, to correct the fuel configuration before the next flight (the wing-tank outer-cells must be filled).

** ON A/C 401-450 Subtask 28-25-00-860-060-D C.

Aircraft Maintenance Configuration WARNING: MAKE SURE THAT YOU BOND THE FUEL TANKER TO THE AIRCRAFT. IF YOU DO NOT, AN ELECTRICAL DISCHARGE CAN OCCUR WHICH CAN CAUSE AN EXPLOSION OR FIRE. (1) Obey the local regulations for grounding (earthing) the aircraft. If you must ground (earth) the aircraft: (a) Ground (earth) the fuel tanker/pump unit and the aircraft correctly (Ref. AMM TASK 12-34-24869-001) . (2) Bond the fuel tanker/pump unit to the aircraft (Ref. AMM TASK 12-34-24-869-001) . (3) Remove refuel/defuel coupling cap 41QM. WARNING: MAKE SURE THAT THE FUEL SUPPLY HOSE IS CORRECTLY CONNECTED TO THE COUPLING BEFORE YOU REFUEL/DEFUEL THE AIRCRAFT. DO NOT CONNECT THE FUEL SUPPLY HOSE IF THERE ARE SIGNS OF DAMAGE TO THE AIRCRAFT COUPLING LUGS OR SLOTS. (4) Make sure that the coupling of the fuel supply-hose is clean and then connect it to aircraft refuel/ defuel coupling 40QM.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 12 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

** ON A/C ALL 4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 416-450, 500-600 (Ref. Fig. Refuel Valve SHEET 1) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 205-250, 350-350 EMB SB 31-1211 for A/C 219-220 (Ref. Fig. Refuel/Defuel Control Panel SHEET 1) ** ON A/C 204-204 (Ref. Fig. Refuel/Defuel Control Panel SHEET 1) ** ON A/C 301-349, 351-400, 416-450, 500-600 (Ref. Fig. Refuel/Defuel Control Panel SHEET 1) ** ON A/C 401-415 (Ref. Fig. Refuel Valve SHEET 1) (Ref. Fig. Refuel/Defuel Panels 800VU and 801VU SHEET 1) ** ON A/C 016-022, 024-094, 112-150, 201-201, 203-250, 350-350 Subtask 28-25-00-650-066-B A.

Pressure Refuel Failed Closed WARNING: BE CAREFUL NOT TO FILL THE TANKS MORE THAN NECESSARY NEAR THE END OF THE REFUEL PROCEDURE. WHEN YOU USE THE MANUAL OVERRIDE (MANUAL PLUNGER), THE HIGH-LEVEL PROTECTION SYSTEM WILL NOT STOP THE REFUELING AUTOMATICALLY. THUS THERE IS A RISK OF OVERFILLING AND FUEL SPILLAGE. CAUTION:

DO NOT REFUEL OR DEFUEL THROUGH THE TWO REFUEL/DEFUEL COUPLINGS AT THE SAME TIME. THIS IS TO PREVENT PRESSURE DIFFERENCE PROBLEMS.

CAUTION:

DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM PRESSURE OF 50 PSI (3.45 BARS). IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE AIRCRAFT OR EQUIPMENT CAN OCCUR.

(1) To prevent a fuel spill, on the panel 40VU, make sure that: · the X FEED P/BSW 4QE is released out (OFF) · the MODE SEL P/BSW 48QA is in the AUTO position · the CTR TK PUMP 1 & 2 P/BSW are released out (OFF). (2) Start the pump on the fuel tanker/pump unit. (3) Push and hold in the manual plunger(s) on the applicable refuel valve(s) 7QU(8QU) or 10QU. (4) Monitor the fuel quantity on the refuel control panel 800VU. (5) When the quantity of fuel in the tank(s) is correct, release the manual plunger(s) on the related refuel valve(s). (6) When all the fuel quantities are correct, stop the pump on the fuel tanker/pump unit. Subtask 28-25-00-650-086-A B.

Pressure Refuel Failed Open

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 13 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

WARNING: BE CAREFUL NOT TO FILL THE TANKS MORE THAN NECESSARY NEAR THE END OF THE REFUEL PROCEDURE. WHEN YOU USE THE MANUAL OVERRIDE (MANUAL PLUNGER), THE HIGH-LEVEL PROTECTION SYSTEM WILL NOT STOP THE REFUELING AUTOMATICALLY. THUS THERE IS A RISK OF OVERFILLING AND FUEL SPILLAGE. CAUTION:

DO NOT REFUEL OR DEFUEL THROUGH THE TWO REFUEL/DEFUEL COUPLINGS AT THE SAME TIME. THIS IS TO PREVENT PRESSURE DIFFERENCE PROBLEMS.

CAUTION:

DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM PRESSURE OF 50 PSI (3.45 BARS). IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE AIRCRAFT OR EQUIPMENT CAN OCCUR.

(1) To prevent a fuel spill, on panel 40VU, make sure that: · the X FEED P/BSW 4QE is released out (OFF) · the MODE SEL P/BSW 48QA is in the AUTO position · the CTR TK PUMP 1 & 2 P/BSW are released out (OFF). (2) Start the pump on the fuel tanker/pump unit. (3) Push and hold in the manual plunger(s) on the applicable refuel valve(s) 7QU(8QU) or 10QU. (4) Monitor the fuel quantity on the refuel control panel 800VU. (5) Stop the pump on the fuel tanker/pump unit 500 kg (1102.3110 lb) below required quantity. (6) If fuel is still required in other tanks. Re-start the fuel tanker/pump unit and fill by increments of 500 kg (1102.3110 lb) and monitor the fuel quantity on the refuel panel 800VU and 801VU. (7) When quantity of fuel in the tank(s) is correct, release the manual plunger(s) on the related refuel valve(s). (8) Stop the pump on the fuel tanker/pump unit. (9) If fuel in the applicable tank is over quantity a manual ground transfer may be required (Ref. AMM TASK 28-25-00-869-001) . ** ON A/C 401-415 Subtask 28-25-00-650-066-D A.

Pressure Refuel Failed Closed WARNING: BE CAREFUL NOT TO FILL THE TANKS MORE THAN NECESSARY NEAR THE END OF THE REFUEL PROCEDURE. WHEN YOU USE THE MANUAL OVERRIDE (MANUAL PLUNGER), THE HIGH-LEVEL PROTECTION SYSTEM WILL NOT STOP THE REFUELING AUTOMATICALLY. THUS THERE IS A RISK OF OVERFILLING AND FUEL SPILLAGE. CAUTION:

DO NOT REFUEL OR DEFUEL THROUGH THE TWO REFUEL/DEFUEL COUPLINGS AT THE SAME TIME. THIS IS TO PREVENT PRESSURE DIFFERENCE PROBLEMS.

CAUTION:

DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM PRESSURE OF 50 PSI (3.45 BARS). IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE AIRCRAFT OR EQUIPMENT CAN OCCUR.

(1) To prevent a fuel spill, on panel 40VU, make sure that: · X FEED P/BSW 4QE is released (the OPEN legend is off) Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 14 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

· MODE SEL P/BSW 4QL is in the AUTO position (the MAN legend is off) · The CTR TK L XFR P/BSW and CTR TK R XFR P/BSW are released (the OFF legend is on). (2) Start the pump on the fuel tanker/pump unit. (3) To refuel the wing tank(s), push and hold the manual plunger(s) on applicable refuel valve(s) 7QU(8QU). (4) To refuel the center tank, push and hold the manual plunger on the refuel valve 10QU. (5) To refuel the ACT(s), get a suitable ROD - NON METALLIC. Put the rod through the ACT-equipment door cover and push and hold the manual plunger on refuel valve 41QU. (6) Monitor the fuel quantity on refuel/defuel control-panels 800VU and 801VU. (7) When the quantity of fuel in the tank(s) is correct, release the manual plunger(s) on the related refuel valve(s). (8) When all the fuel quantities are correct, stop the pump on the fuel tanker/pump unit. Subtask 28-25-00-650-086-C B.

Pressure Refuel Failed Open WARNING: BE CAREFUL NOT TO FILL THE TANKS MORE THAN NECESSARY NEAR THE END OF THE REFUEL PROCEDURE. WHEN YOU USE THE MANUAL OVERRIDE (MANUAL PLUNGER), THE HIGH-LEVEL PROTECTION SYSTEM WILL NOT STOP THE REFUELING AUTOMATICALLY. THUS THERE IS A RISK OF OVERFILLING AND FUEL SPILLAGE. CAUTION:

DO NOT REFUEL OR DEFUEL THROUGH THE TWO REFUEL/DEFUEL COUPLINGS AT THE SAME TIME. THIS IS TO PREVENT PRESSURE DIFFERENCE PROBLEMS.

CAUTION:

DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM PRESSURE OF 50 PSI (3.45 BARS). IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE AIRCRAFT OR EQUIPMENT CAN OCCUR.

(1) To prevent a fuel spill, on panel 40VU, make sure that: · X FEED P/BSW 4QE is released (the OPEN legend is off) · MODE SEL P/BSW 4QL is in the AUTO position (the MAN legend is off) · The CTR TK L XFR P/BSW and CTR TK R XFR P/BSW are released (the OFF legend is on). (2) Start the pump on the fuel tanker/pump unit. (3) To refuel the wing tank(s), push and hold the manual plunger(s) on applicable refuel valve(s) 7QU(8QU). (4) To refuel the center tank, push and hold the manual plunger on refuel valve 10QU. (5) To refuel the ACT(s), get a suitable ROD - NON METALLIC. Put the rod through the ACT-equipment door cover and push and hold the manual plunger on refuel valve 41QU. (6) Monitor the fuel quantity on refuel control panels 800VU and 801VU. (7) Stop the pump on the fuel tanker/pump unit 500 kg (1102.3110 lb) below required quantity. (8) If fuel is still necessary in other tanks: (a) Start the fuel tanker/pump unit and fill in increments of 500 kg (1102.3110 lb) and monitor the quantity on refuel/defuel panels 800VU and 801VU. (9) When quantity of fuel in the tank(s) is correct: (a) Release the manual plunger(s) on the related refuel valve(s).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 15 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

(10) Stop the pump on the fuel tanker/pump unit. (11) If fuel in the applicable tank is over quantity: (a) Do the manual ground transfer (Ref. AMM TASK 28-25-00-869-001) . ** ON A/C 095-100, 301-349, 351-400, 416-450, 500-600 Subtask 28-25-00-650-066-E A.

Pressure Refuel Failed Closed WARNING: BE CAREFUL NOT TO FILL THE TANKS MORE THAN NECESSARY NEAR THE END OF THE REFUEL PROCEDURE. WHEN YOU USE THE MANUAL OVERRIDE (MANUAL PLUNGER), THE HIGH-LEVEL PROTECTION SYSTEM WILL NOT STOP THE REFUELING AUTOMATICALLY. THUS THERE IS A RISK OF OVERFILLING AND FUEL SPILLAGE. CAUTION:

DO NOT REFUEL OR DEFUEL THROUGH THE TWO REFUEL/DEFUEL COUPLINGS AT THE SAME TIME. THIS IS TO PREVENT PRESSURE DIFFERENCE PROBLEMS.

CAUTION:

DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM PRESSURE OF 50 PSI (3.45 BARS). IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE AIRCRAFT OR EQUIPMENT CAN OCCUR.

(1) To prevent a fuel spill, on the panel 40VU, make sure that: · the X FEED P/BSW 4QE is released out (OFF) · the MODE SEL P/BSW 4QL is in the AUTO position · the CTR TK L and R XFR P/BSW are released out (OFF). (2) Start the pump on the fuel tanker/pump unit. (3) Push and hold in the manual plunger(s) on the applicable refuel valve(s) 7QU(8QU) or 10QU. (4) Monitor the fuel quantity on the refuel control panel 800VU. (5) When the quantity of fuel in the tank(s) is correct, release the manual plunger(s) on the related refuel valve(s). (6) When all the fuel quantities are correct, stop the pump on the fuel tanker/pump unit. Subtask 28-25-00-650-086-D B.

Pressure Refuel Failed Open WARNING: BE CAREFUL NOT TO FILL THE TANKS MORE THAN NECESSARY NEAR THE END OF THE REFUEL PROCEDURE. WHEN YOU USE THE MANUAL OVERRIDE (MANUAL PLUNGER), THE HIGH-LEVEL PROTECTION SYSTEM WILL NOT STOP THE REFUELING AUTOMATICALLY. THUS THERE IS A RISK OF OVERFILLING AND FUEL SPILLAGE. CAUTION:

DO NOT REFUEL OR DEFUEL THROUGH THE TWO REFUEL/DEFUEL COUPLINGS AT THE SAME TIME. THIS IS TO PREVENT PRESSURE DIFFERENCE PROBLEMS.

CAUTION:

DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM PRESSURE OF 50 PSI (3.45 BARS). IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE AIRCRAFT OR EQUIPMENT CAN OCCUR.

(1) To prevent a fuel spill, on the panel 40VU, make sure that: Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 16 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

· the X FEED P/BSW 4QE is released out (OFF) · the MODE SEL P/BSW 4QL is in the AUTO position · the CTR TK L and R XFR P/BSW are released out (OFF). (2) Start the pump on the fuel tanker/pump unit. (3) Push and hold in the manual plunger(s) on the applicable refuel valve(s) 7QU(8QU) or 10QU. (4) Monitor the fuel quantity on the refuel control panel 800VU. (5) Stop the pump on the fuel tanker/pump unit 500 kg (1102.3110 lb) below required quantity. (6) If fuel is still required in other tanks. Re-start the fuel tanker/pump unit and fill by increments of 500 kg (1102.3110 lb) and monitor the fuel quantity on the refuel panel 800VU and 801VU. (7) When the quantity of fuel in the tank(s) is correct, release the manual plunger(s) on the related refuel valve(s). (8) Stop the pump on the fuel tanker/pump unit. (9) If fuel in the applicable tank is over quantity a manual ground transfer may be required (Ref. AMM TASK 28-25-00-869-001) . ** ON A/C ALL 5.

Close-up

** ON A/C ALL EMB SB 28-1030 for A/C 209-209 Subtask 28-25-00-860-061-A A.

Aircraft Configuration (1) Disconnect the coupling of the fuel supply hose from the aircraft refuel/defuel coupling 40QM. (2) Put a PLACARD in the cockpit to tell persons that a refuel procedure with a manual plunger override is in progress.

** ON A/C 016-022, 024-100, 112-150, 203-205, 208-208, 210-221, 223-226, 229-235, 237-240, 242-250, 301400, 416-450, 500-600 Subtask 28-25-00-410-067-B B.

Close Access (1) Install the coupling cap 41QM. CAUTION:

MAKE SURE THAT THE HANDLE OF THE REFUEL COUPLING CAP POINTS AFT WHEN THE CAP IS CLOSED AND LOCKED.

(2) Close the access panel 192MB. (3) For the left refuel valve 7QU, close the access panel 522JB. (4) For the right refuel valve 8QU, close the access panel 622JB. (5) For the center tank refuel valve 10QU, close the RH MLG door 744 (Ref. AMM TASK 32-12-00-410001) . ** ON A/C 201-201, 206-207, 209-209, 222-222, 227-228, 236-236, 241-241

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 17 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

EMB SB 28-1030 for A/C 209-209 Subtask 28-25-00-410-067-D B.

Close Access (1) Install the coupling cap 101QM(41QM). CAUTION:

MAKE SURE THAT THE HANDLE OF THE REFUEL COUPLING CAP POINTS AFT WHEN THE CAP IS CLOSED AND LOCKED.

(2) Close the access panel 192MB. (3) For the left refuel valve 7QU, close the access panel 522JB. (4) For the right refuel valve 8QU, close the access panel 622JB. (5) For the center tank refuel valve 10QU, close the RH MLG door 744 (Ref. AMM TASK 32-12-00-410001) . ** ON A/C 401-415 Subtask 28-25-00-410-067-G B.

Close Access CAUTION:

MAKE SURE THAT THE HANDLE OF THE REFUEL COUPLING CAP POINTS AFT WHEN THE CAP IS CLOSED AND LOCKED.

(1) Install refuel/defuel coupling cap 41QM. (2) Install access panel 622HB. (3) Close access door 192MB. (4) For left refuel valve 7QU, close access panel 522JB. (5) For right refuel valve 8QU, close access panel 622JB. (6) For center tank refuel valve 10QU, close RH MLG door 744 (Ref. AMM TASK 32-12-00-410-001) . (7) For ACT refuel valve 41QU, close LH MLG door 734 (Ref. AMM TASK 32-12-00-410-001) . ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 28-25-00-860-062-A C.

Aircraft Maintenance Configuration (1) Disconnect these bonding/ground cables: · Between the aircraft and the fuel tanker/pump unit · If applicable, between the fuel tanker/pump unit and the ground · If applicable, between the aircraft and the ground. (2) Write in the aircraft technical log to do a check of the fuel configuration. NOTE: Fuel correction is automatic after the fuel pumps are set to on (the wing tank outer cells must be filled).

** ON A/C 401-450 Subtask 28-25-00-860-062-B C.

Aircraft Maintenance Configuration (1) Disconnect these bonding/ground cables: · Between the aircraft and the fuel tanker/pump unit

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 18 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-005-A - Refuel Valve - Refuel Procedure Using Manual Plunger Override

· If applicable, between the fuel tanker/pump unit and the ground · If applicable, between the aircraft and the ground. (2) Write in the A/C technical log to do a check of the fuel configuration. ** ON A/C ALL Subtask 28-25-00-942-076-A D.

Removal of Equipment (1) Make sure that the work area is clean and clear of tools and other items. (2) If installed, remove the safety barriers. (3) Remove the access platform(s). (4) Remove the WARNING NOTICE(S). (5) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 19 of 19

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-014-A - Deactivation of the ACT Transfer Valve in the Closed Position

** ON A/C 401-415 TASK 28-28-00-040-014-A Deactivation of the ACT Transfer Valve in the Closed Position WARNING:

OBEY THE FUEL SAFETY PROCEDURES.

Task Summary MMEL or CDL Ref MMEL 28-21-02C

Access NO

1.

Reason for the Job MMEL 28-21-02C Center Tank Pump (FAA only)

2

Job Set-up Information A.

Specific Tools YES

Mhr 00.8

E/T 00.8

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific (T720456)

B.

Test NO

QTY 1 AR AR 1 1 1

DESIGNATION ACCESS PLATFORM 1M(3 FT) CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER TIE WRAP WARNING NOTICE(S) TOOL - VALVE LOCKING

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A). (Ref. 32-12-00-010-001-A). (Ref. 32-12-00-410-001-A). (Ref. 57-17-11-000-001-A). (Ref. 57-17-11-000-001-A-01). (Ref. 57-17-11-400-001-A). (Ref. 57-17-11-400-001-A-01).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures Open the Main Gear Doors for Access Close the Main Gear Doors after Access Removal of the Access Covers 147AZ (148AZ) Removal of the Access Cover 148AZ or/and the ACT-Equipment Support Door Installation of Access Covers 147AZ (148AZ) Installation of Access Cover 148AZ or/and the ACT-Equipment Support-Door

ACT Fuel-Transfer Valve 165QM

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-014-A - Deactivation of the ACT Transfer Valve in the Closed Position

FR42

FR36

A

B Z140

A D 2 6 FR42

C 165QM

5

1

4 3 7 PIN SLOT

B N_MM_282800_4_PLA1_01_00

Figure 28-28-00-991-00300-00-B / SHEET 1/2 - ACT Fuel-Transfer Valve 165QM ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-014-A - Deactivation of the ACT Transfer Valve in the Closed Position

CLOSED POSITION OPEN POSITION

C

A

B

A

B

OPEN POSITION

CLOSED POSITION

D

A A

B B

N_MM_282800_4_PLA1_02_00

Figure 28-28-00-991-00300-00-B / SHEET 2/2 - ACT Fuel-Transfer Valve 165QM ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-014-A - Deactivation of the ACT Transfer Valve in the Closed Position

3.

Job Set-up Subtask 28-28-00-860-200-A A.

Aircraft Maintenance Configuration (1) Obey the fuel safety procedures when you work on the fuel system (Ref. AMM TASK 28-00-00-910001) . (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) On the APU section of the overhead panel 25VU, make sure that the APU/MASTER SW pushbutton switch is released (the ON legend is off). (4) On the FUEL section of the HYD/FUEL panel 40VU, make sure that all tank pump pushbutton switches are released (the OFF legends are on). (5) Put a WARNING NOTICE(S) in position: · On the APU section of the overhead panel 25VU, to tell persons not to operate the APU/MASTER SW pushbutton switch · On the FUEL section of the panel 40VU, to tell persons not to operate the fuel system · On the ENG/APU FIRE panel located on the overhead panel 20VU, to tell persons not to operate the fire extinguishing system · On the Additional Center Tank (ACT) control section of panel 28VU, to tell persons not to operate the fuel system.

Subtask 28-28-00-010-102-B B.

Get Access (1) Open the left main-gear door for access (Ref. AMM TASK 32-12-00-010-001) . (2) Put an ACCESS PLATFORM 1M(3 FT) in position in the left MLG bay. (3) Remove the ACT equipment-support door (Ref. AMM TASK 57-17-11-000-001) .

4.

Procedure (Ref. Fig. ACT Fuel-Transfer Valve 165QM) Subtask 28-28-00-040-066-B CAUTION:

A.

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

Deactivation of the ACT Fuel-Transfer Valve in Valve Closed Position NOTE: A refuel of the ACT is not possible while ACT fuel-transfer valve is OFF in valve position CLOSED. (1) Disconnect the electrical connectors (3) and (4) from the receptacles of the ACT transfer-valve actuator (2). (2) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (3) Safety the electrical connectors (3) and (4) to the adjacent electrical harness with a TIE WRAP. (4) Do a visual inspection on the indicator of the ACT transfer-valve actuator (2) to identify the position of the valve: · Indicator in horizontal position: the transfer valve is OPEN · Indicator in vertical position: the transfer valve is CLOSED. (5) Cut and discard the lockwire:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-014-A - Deactivation of the ACT Transfer Valve in the Closed Position

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. (a) Cut and discard the lockwire from the screw (5). (6) Loosen the screw (5) and remove the V-clamp (6) and the ACT transfer-valve actuator (2). (7) Remove the O-ring (7) and discard it: (a) Turn the shaft of the ACT fuel-transfer valve (1) to the closed position if necessary. (b) Install the TOOL - VALVE LOCKING (T720456) on the flange of the ACT fuel-transfer valve (1) to lock it in the closed position. 5.

Close-up Subtask 28-28-00-860-201-B A.

Put the aircraft back to the serviceable condition. (1) Install the ACT equipment-support door (Ref. AMM TASK 57-17-11-400-001) . (2) Make sure that the work area is clean and clear of tools and other items. (3) Remove the access platform(s). (4) Close the main gear doors (Ref. AMM TASK 32-12-00-410-001) . (5) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (6) Remove the WARNING NOTICE(S). (7) In the cockpit, put a placard in position to tell the crew that the ACT fuel-transfer valve is OFF in valve position CLOSED. (8) On refuel/defuel control panel 801VU, put a placard in position to tell the ground crew: DO NOT REFUEL THE ACT(s). (9) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-004-A - Transfer Valve Indication - Intercell Transfer

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 TASK 28-40-00-040-004-A Transfer Valve Indication - Intercell Transfer 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.

Task Summary MMEL or CDL Ref MMEL 28-07-04-04A

Access YES

Test YES

1.

Reason for the Job MMEL 28-07-04-04A Wing Transfer Valve Indication on the FUEL SD page

2

Job Set-up Information A.

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Specific Tools NO

QTY DESIGNATION AR SAFETY BARRIER(S)

Work Zones and Access Panels ZONE/ACCESS 192MB

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 12-11-28-650-003-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A). (Ref. 28-25-00-650-001-A). (Ref. 28-25-00-869-001-A). (Ref. 31-60-00-860-001-A).

DESIGNATION Pressure Refuel with Automatic Control Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures Pressure Defuel Fuel Transfer EIS Start Procedure

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-004-A - Transfer Valve Indication - Intercell Transfer

REFERENCE (Ref. 31-60-00-860-002-A). 3.

DESIGNATION EIS Stop Procedure

Job Set-up Subtask 28-40-00-941-060-A A.

Safety Precautions WARNING: OBEY THE FUEL SAFETY PROCEDURES. (1) You must obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00-910-001) . (2) Put the SAFETY BARRIER(S) in position.

Subtask 28-40-00-010-056-A B.

Get Access (1) Open the access door 192MB. NOTE: If operating in battery power, do not keep the door open longer than necessary because the battery can discharge.

Subtask 28-40-00-861-053-A C.

Energize the Electrical Circuits (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

Subtask 28-40-00-650-052-A D.

Fuel Configuration (1) Refuel, defuel or transfer fuel as necessary (Ref. AMM TASK 12-11-28-650-003) , (Ref. AMM TASK 28-25-00-650-001) , (Ref. AMM TASK 28-25-00-869-001) to get: · a minimum of 900 kg (1980 lbs) to a maximum of 4000 kg (8820 lbs) in the inner cell of each wing tank · maximum fuel in the outer cell of each wing tank.

Subtask 28-40-00-860-054-A E.

Aircraft Maintenance Configuration (1) Do the EIS start procedure (ECAM only) (Ref. AMM TASK 31-60-00-860-001) . (2) On the panel 11VU, push (in) the FUEL P/BSW. (3) On the panel 800VU: · set the MODE SELECT SWITCH to the REFUEL. NOTE: It is necessary in this test to transfer fuel from the outer cell of each wing tank to its related inner cell.

Subtask 28-40-00-865-056-A F.

Table of the circuit breakers used in this procedure: PANEL 49VU 49VU 121VU 121VU

DESIGNATION FUEL/XFR VALVE1/WING/R FUEL/XFR VALVE1/WING/L FUEL/XFR VALVE2/WING/R FUEL/XFR VALVE2/WING/L

FIN 2QP 1QP 4QP 3QP

LOCATION A11 A10 M23 M22

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-004-A - Transfer Valve Indication - Intercell Transfer

4.

Procedure Subtask 28-40-00-040-055-A A.

Transfer Valve Indication - Intercell Transfer (1) Do this test: ACTION 1.Open, safety clip and tag C/B 3QP

RESULT On the ECAM DU: · make sure that the right-wing outer-cell fuel content decreases and the right- wing inner-cell fuel content increases. 2.Remove the safety clip and the tag and close C/ On the ECAM DU: B 3QP · make sure that the fuel transfer stops. 3.Open, safety clip and tag C/B 4QP On the ECAM DU: · make sure that the left-wing outer-cell fuel content decreases and the left- wing inner-cell fuel content increases. 4.Remove the safety clip and the tag and close C/ On the ECAM DU: B 4QP · make sure that the fuel transfer stops. 5.Open, safety clip and tag C/B 2QP On the ECAM DU: · make sure that the left-wing outer-cell fuel content decreases and the left- wing inner-cell fuel content increases. 6.Remove the safety clip and the tag and close C/ On the ECAM DU: B 2QP · make sure that the fuel transfer stops. 7.Open, safety clip and tag C/B 1QP On the ECAM DU: · make sure that the right-wing outer-cell fuel content decreases and the right- wing inner-cell fuel content increases. 8.Remove the safety clip and the tag and close C/ On the ECAM DU: B 1QP · make sure that the fuel transfer stops. 5.

Close-up Subtask 28-40-00-860-055-A A.

Aircraft Maintenance Configuration (1) On the panel 800VU: · set the MODE SELECT switch to the OFF position. (2) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (3) Make an applicable entry in the aircraft log.

Subtask 28-40-00-410-054-A B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access door 192MB.

Subtask 28-40-00-650-053-A C.

Fuel Configuration (1) Refuel, defuel or transfer fuel as necessary (Ref. AMM TASK 12-11-28-650-003) , (Ref. AMM TASK 28-25-00-650-001) , (Ref. AMM TASK 28-25-00-869-001) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-004-A - Transfer Valve Indication - Intercell Transfer

Subtask 28-40-00-862-053-A D.

De-energize the Electrical Circuits (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Subtask 28-40-00-942-058-A E.

Removal of Equipment (1) Remove the safety barriers. (2) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-440-002-A - Reactivation of the Transfer Defuel Valve

** ON A/C ALL TASK 28-25-00-440-002-A Reactivation of the Transfer Defuel Valve 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.

FIN : 11QM 1.

Reason for the Job MMEL 28-25-04A Transfer Defuel Valve

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

QTY AR AR AR

DESIGNATION ACCESS PLATFORM 3M (10 FT) SAFETY BARRIER(S) WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 192MB

ZONE DESCRIPTION

C. Referenced Information REFERENCE DESIGNATION (Ref. 28-00-00-910-001-A). Fuel Safety Procedures (Ref. 28-25-43-000-001-A). Removal of the Defuel/Transfer Valve (Ref. 28-25-43-400-001-A). Installation of the Defuel/Transfer Valve (Ref. 28-25-53-000-001-A). Removal of the Center-Tank Defuel/Transfer Valve-Actuator (Ref. 28-25-53-400-001-A). Installation of the Center-Tank Defuel/Transfer Valve-Actuator (Ref. 32-12-00-010-001-A). Open the Main Gear Doors for Access (Ref. 32-12-00-410-001-A). Close the Main Gear Doors after Access Transfer Defuel Valve (11QM) - Location and Detail SHEET 1 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 205-250, 350-350 Refuel/Defuel Control Panel SHEET 1 ** ON A/C 204-204 Refuel/Defuel Control Panel SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-440-002-A - Reactivation of the Transfer Defuel Valve

REFERENCE

DESIGNATION

** ON A/C 301-349, 351-400, 416-450, 500-600 Refuel/Defuel Control Panel SHEET 1 ** ON A/C 401-415 Refuel/Defuel Panels 800VU and 801VU SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-440-002-A - Reactivation of the Transfer Defuel Valve

A

B A STA18694/ FR42 Z141-Z142 STA15900/ FR36

TRANSFER DEFUEL VALVE 11QM

C

1

B DRIVE SHAFT

D TO ENGINE FEED LINE

REAR SPAR

2

ACTUATOR 11QU

V-BAND CLAMP 82QM

VALVE 11QM

3

TO REFUEL LINE

VALVE LOCKING TOOL T720456

C D OPEN

SEE/FEEL INDICATOR CLOSED

OPEN

CLOSED

N_MM_282500_4_AEM0_01_00

Figure 28-25-00-991-01600-00-A / SHEET 1/1 - Transfer Defuel Valve (11QM) - Location and Detail ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-440-002-A - Reactivation of the Transfer Defuel Valve

A

REFUEL COUPLING REFUEL/DEFUEL CONTROL PANEL

A

FUEL QTY kg x 1000 INDICATOR LEFT

CTR

HI.

RIGHT

LVL.

LEFT

CTR

RIGHT

REFUEL VALVES OPEN OPEN NORM NORM SHUT SHUT MODE

SELECT REFUEL

6QT

OPEN NORM SHUT

TEST BATT POWER HI. LVL ON

REFUEL DEFUEL CONTROL PANEL 800VU

OFF DEFUEL XFR

OPEN LTS

PRESELECTED

REFUEL

NORM ACTUAL

kg x 1000

DEC

INC CKPT

END

PRESELECTOR 5QT

N_MM_282500_4_CAM0_01_00

Figure 28-25-00-991-02400-00-G / SHEET 1/1 - Refuel/Defuel Control Panel ** ON A/C 016-022, 024-100, 112-150, 201-201, 203203, 205-250, 350-350 | EMB SB 31-1211 for A/C 219-220 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-440-002-A - Reactivation of the Transfer Defuel Valve

A

REFUEL COUPLING REFUEL/DEFUEL CONTROL PANEL

A

FUEL QTY lbs x 1000 INDICATOR

CTR

LEFT

HI.

RIGHT

LVL. CTR

LEFT

RIGHT

REFUEL VALVES OPEN OPEN NORM NORM SHUT SHUT MODE

SELECT REFUEL

6QT

OPEN NORM SHUT

TEST BATT POWER HI. LVL ON

REFUEL DEFUEL CONTROL PANEL 800VU

OFF DEFUEL XFR PRESELECTED

OPEN LTS

REFUEL

NORM ACTUAL

lbs x 1000

DEC

INC CKPT

END

PRESELECTOR 5QT

N_MM_282500_4_CVM0_01_00

Figure 28-25-00-991-02400-00-H / SHEET 1/1 - Refuel/Defuel Control Panel ** ON A/C 204-204 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-440-002-A - Reactivation of the Transfer Defuel Valve

REFUEL COUPLING

A

REFUEL/DEFUEL CONTROL PANEL

A FUEL QTY kg X 1000 LEFT

CTR

HI. LEFT

LVL. CTR

RIGHT

REFUEL VALVES OPEN OPEN NORM NORM SHUT SHUT MODE SELECT REFUEL

INDICATOR 6QT

RIGHT

TEST HI. LVL

OPEN NORM SHUT BATT POWER ON

OFF DEFUEL XFR PRESELECTED

DEC

OPEN LTS REFUEL kg X 1000

REFUEL/DEFUEL CONTROL PANEL 800VU

NORM ACTUAL

CKPT END

INC

PRESELECTOR 5QT

N_MM_282500_4_CAM2_01_00

Figure 28-25-00-991-02400-00-S / SHEET 1/1 - Refuel/Defuel Control Panel ** ON A/C 301-349, 351-400, 416-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-440-002-A - Reactivation of the Transfer Defuel Valve

REFUEL COUPLING 40QM

A

622HB 192MB

REFUEL/DEFUEL CONTROL PANEL

INDICATOR 6QT

TOTAL ACT

FUEL QTY

ACT

kg x 1000

LEFT

RIGHT

CTR

LVL

HI LEFT

VALVES

REFUEL SW POS = OPEN

CTR

= NORM

AFT1

UP

REFUEL VALVE

OPEN

OPEN

OPEN

NORM

NORM

NORM

SHUT

SHUT

MODE SELECT

DOWN = SHUT

RIGHT

CTR

BATT POWER

HI LVL

ON

REFUEL

HI LVL

SHUT

TEST

REFUEL/DEFUEL CONTROL PANEL 800VU

OFF

DEFUEL / XFR OPEN

REFUEL

PRESELECTED

LTS

NORM ACTUAL

kg x 1000

801VU REFUEL/DEFUEL CONTROL PANEL

DEC

INC

CKPT

END

5QT PRESELECTOR

A

N_MM_282500_4_EEM1_01_00

Figure 28-25-00-991-03800-00-C / SHEET 1/1 - Refuel/Defuel Panels 800VU and 801VU ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-440-002-A - Reactivation of the Transfer Defuel Valve

3.

Job Set-up (Ref. Fig. Transfer Defuel Valve (11QM) - Location and Detail SHEET 1)

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 205-250, 350-350 EMB SB 31-1211 for A/C 219-220 (Ref. Fig. Refuel/Defuel Control Panel SHEET 1) ** ON A/C 204-204 (Ref. Fig. Refuel/Defuel Control Panel SHEET 1) ** ON A/C 301-349, 351-400, 416-450, 500-600 (Ref. Fig. Refuel/Defuel Control Panel SHEET 1) ** ON A/C 401-415 (Ref. Fig. Refuel/Defuel Panels 800VU and 801VU SHEET 1) ** ON A/C ALL Subtask 28-25-00-941-077-A A.

Safety Precautions WARNING: OBEY THE FUEL SAFETY PROCEDURES. (1) You must obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00-910-001) . (2) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations. (3) Put a WARNING NOTICE(S) in position to tell persons not to operate the MLG doors.

Subtask 28-25-00-010-064-A B.

Get Access (1) Open the MLG doors (Ref. AMM TASK 32-12-00-010-001) . (2) Make sure that the SLEEVE - GROUND LOCK (460005835) is on the applicable MLG door actuator. (3) Put an ACCESS PLATFORM 3M (10 FT) below the transfer defuel valve (11QM). (4) Open the access panel 192MB. NOTE: If operating in battery power, do not keep the door open longer than necessary because the battery can discharge.

Subtask 28-25-00-860-059-A C.

Aircraft Maintenance Configuration (1) On the panel 800VU, make sure that the MODE SELECT switch is in the OFF and guarded position. Make sure that the warning notice is still attached to the switch. (2) Make sure that the circuit breaker 1QU on panel 121VU, is still open, safetied and tagged. Make sure that the warning notice is still attached to the circuit breaker.

4.

Procedure (Ref. Fig. Transfer Defuel Valve (11QM) - Location and Detail SHEET 1)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-440-002-A - Reactivation of the Transfer Defuel Valve

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 205-250, 350-350 EMB SB 31-1211 for A/C 219-220 (Ref. Fig. Refuel/Defuel Control Panel SHEET 1) ** ON A/C 204-204 (Ref. Fig. Refuel/Defuel Control Panel SHEET 1) ** ON A/C 301-349, 351-400, 416-450, 500-600 (Ref. Fig. Refuel/Defuel Control Panel SHEET 1) ** ON A/C 401-415 (Ref. Fig. Refuel/Defuel Panels 800VU and 801VU SHEET 1) ** ON A/C ALL Subtask 28-25-00-440-051-A A.

Reactivation of the Transfer Defuel Valve (1) Remove the applicable item(s) from the polythene bag(s). (2) Remove the blanking caps from the electrical connectors. (3) If applicable, release the screw (2) and remove V-band clamp (82QM). Remove the TOOL - VALVE LOCKING (T720456) from the transfer defuel valve (11QM). (4) Make sure that you remove the dowel (3) from between the TOOL - VALVE LOCKING (T720456) and the face plate of the drive shaft. Keep the dowel (3) safe with the TOOL - VALVE LOCKING (T720456) . (5) If the transfer defuel valve (11QM) is unserviceable, then replace it, (Ref. AMM TASK 28-25-43-000001) and (Ref. AMM TASK 28-25-43-400-001) . (6) If the actuator (11QU) is unserviceable, then replace it, (Ref. AMM TASK 28-25-53-000-001) and (Ref. AMM TASK 28-25-53-400-001) . NOTE: It is possible that the actuator (11QU) is in a polythene bag. (7) Reconnect the electrical connector (1) to the actuator (11QU). (8) If you do not know the cause of the failure, trouble-shoot the system and do the corrective action (Ref. TSM Chapter 28).

Subtask 28-25-00-865-062-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 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU FUEL/RFL/DFL/XFR/DEFUEL/VALVE 1QU L23 ** ON A/C 401-450 121VU FUEL/RFL/DFL/XFR/DEFUEL/VALVE

1QU

L22

** ON A/C ALL 5.

Close-up Subtask 28-25-00-410-064-A

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-440-002-A - Reactivation of the Transfer Defuel Valve

A.

Close Access (1) Remove the WARNING NOTICE(S) from the circuit breaker 1QU in the cockpit and the MODE SELECT switch on the panel 800VU. (2) Remove the access platform(s). (3) Make sure that the work area is clean and clear of tools and other items. (4) Close the MLG doors (Ref. AMM TASK 32-12-00-410-001) . (5) Close the access panel 192MB.

Subtask 28-25-00-942-068-A B.

Removal of Equipment (1) Remove the safety barriers. (2) Remove the WARNING NOTICE(S). (3) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (4) Write an entry in the aircraft technical log to say that the transfer/defuel valve is reactivated.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

** ON A/C ALL TASK 28-25-00-040-008-A Refuel/Defuel Control Panel - Manual Refuel WARNING:

DO NOT TRANSMIT WITH THE HF SYSTEM DURING REFUEL/DEFUEL OR TRANSFER OPERATIONS. TRANSMISSION WITH THE HF SYSTEM DURING THESE FUEL OPERATIONS CAN CAUSE INJURY AND/OR START A FIRE.

WARNING:

STOP THE FUEL TANKER 60 M (196.85 FT) FROM THE AIRCRAFT NOSE WHILE THE WEATHER RADAR OPERATES. DO NOT OPERATE THE FUEL TANKER/PUMP UNIT UNTIL YOU STOP THE OPERATION OF THE WEATHER RADAR.

WARNING:

MAKE SURE THE AREA AROUND THE AIRCRAFT IS SAFE BEFORE YOU START THE REFUEL/DEFUEL PROCEDURE. IN THE SAFETY AREA, DO NOT: - SMOKE - MAKE SPARKS OR FIRE - USE ANY EQUIPMENT WHICH IS NOT APPROVED FOR REFUEL/DEFUEL PROCEDURES. AIRCRAFT FUEL IS FLAMMABLE.

WARNING:

MAKE SURE THAT THE WHEEL CHOCKS ARE IN POSITION. MOVEMENT OF THE AIRCRAFT CAN BE DANGEROUS.

WARNING:

MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

Task Summary MMEL or CDL Ref MMEL 28-25-05B MMEL 28-25-05A 1.

Access YES YES

Test YES YES

Specific Tools YES YES

Mhr 00.7 00.7

E/T 00.7 00.7

Nb Men 1 1

Reason for the Job MMEL 28-25-05B Exterior Refuel/Defuel Control Panel MMEL 28-25-05A Exterior Refuel/Defuel Control Panel NOTE: If installed, use the cockpit pre-selector to refuel.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

QTY AR AR AR

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE ACCESS PLATFORM 4M (13 FT) SAFETY BARRIER(S)

Work Zones and Access Panels

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

ZONE/ACCESS 522JB, 622JB, 744

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 12-11-28-650-001-A). (Ref. 12-11-28-650-002-A). (Ref. 12-32-28-281-001-A). (Ref. 12-34-24-869-001-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 32-00-00-481-001-A). (Ref. 32-12-00-010-001-A). (Ref. 32-12-00-410-001-A).

DESIGNATION General Refuel/Defuel Safety Procedures Refuel/Defuel Safety Procedures for use in the Hangar Drain Water Content Aircraft Bonding and Grounding (Earthing) for the Refuel/Defuel or Oxygen Servicing Operations Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) EIS Start Procedure Installation of the Safety Devices on the Landing Gears Open the Main Gear Doors for Access Close the Main Gear Doors after Access

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 416-450, 500-600 Refuel Valve SHEET 1 ** ON A/C 401-415 Refuel Valve SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

10QU

STA7792/RIB14

A

522 JB(622 JB)

STA8268/RIB15 REAR SPAR

A

7QU (8QU)

A

MANUALLY OPERATED PLUNGER

REFUEL VALVE

N_MM_282500_4_BAN0_01_00

Figure 28-25-00-991-02200-00-B / SHEET 1/1 - Refuel Valve ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 416-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

10QU 41QU

STA7792/RIB14

A

522 JB(622 JB)

STA8268/RIB15

A

A

REAR SPAR

7QU (8QU)

A

MANUALLY OPERATED PLUNGER

REFUEL VALVE

N_MM_282500_4_BAP0_01_00

Figure 28-25-00-991-02200-00-C / SHEET 1/1 - Refuel Valve ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

3.

Job Set-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 416-450, 500-600 (Ref. Fig. Refuel Valve SHEET 1) ** ON A/C 401-415 (Ref. Fig. Refuel Valve SHEET 1) ** ON A/C 016-022, 024-100, 112-150, 203-205, 208-208, 210-221, 223-226, 229-235, 237-240, 242-250, 301450, 500-600 Subtask 28-25-00-941-087-A A.

Safety Precautions WARNING: OBEY THE FUEL SAFETY PROCEDURES. (1) You must obey the refuel/defuel safety procedures (Ref. AMM TASK 12-11-28-650-001) (Ref. AMM TASK 12-11-28-650-002) . (2) Make sure that the ground safety locks are installed on the landing gear (Ref. AMM TASK 32-00-00481-001) . (3) Make sure that the chocks do not touch the tires. The weight of the fuel can lower the aircraft and cause the chocks to catch. (4) Put the SAFETY BARRIER(S) in position.

** ON A/C 201-201, 206-207, 209-209, 222-222, 227-228, 236-236, 241-241 EMB SB 28-1030 for A/C 209-209 Subtask 28-25-00-941-087-B A.

Safety Precautions WARNING: OBEY THE FUEL SAFETY PROCEDURES. (1) You must obey the refuel/defuel safety precautions (Ref. AMM TASK 12-11-28-650-001) (Ref. AMM TASK 12-11-28-650-002) . (2) Make sure that the ground safety locks are installed on the landing gear (Ref. AMM TASK 32-00-00481-001) . CAUTION:

DO NOT REFUEL OR DEFUEL THROUGH THE TWO REFUEL/DEFUEL COUPLINGS AT THE SAME TIME. THIS IS TO PREVENT PRESSURE DIFFERENCE PROBLEMS.

(3) Make sure that the chocks do not touch the tires. The weight of the fuel can lower the aircraft and cause the chocks to catch. (4) Put the SAFETY BARRIER(S) in position. ** ON A/C ALL Subtask 28-25-00-010-088-B B.

Get Access (1) To get access to the left refuel valve 7QU:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

(a) Put the ACCESS PLATFORM 4M (13 FT) in position below zone 522. (b) Remove the access panel 522JB. (2) To get access to the right refuel valve 8QU: (a) Put the ACCESS PLATFORM 4M (13 FT) in position below zone 622. (b) Remove the access panel 622JB. (3) To get access to the center tank refuel valve 10QU: (a) Open the RH MLG door 744 (Ref. AMM TASK 32-12-00-010-001) . (b) Make sure that the SLEEVE - GROUND LOCK (460005835) is on the applicable MLG door actuator. (c) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below zone 148. 4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 203-205, 208-208, 210-221, 223-226, 229-235, 237-240, 242-250, 301400, 500-600 Subtask 28-25-00-860-075-A A.

Aircraft Maintenance Configuration (1) Make sure that the aircraft and the fuel tanker/pump unit are grounded correctly (Ref. AMM TASK 12-34-24-869-001) and electrically bonded together correctly. NOTE: Bonding is mandatory. For grounding you must obey the local area regulations. (2) Do a fuel sampling for water contamination check on the fuel in the fuel tanker/pump unit (Ref. AMM TASK 12-32-28-281-001) . (3) Remove the refuel coupling cap 41QM. (4) Make sure that the coupling of the fuel supply-hose is clean. (5) Connect the coupling of the fuel supply-hose to the aircraft refuel coupling. (6) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (7) Energize the ECAM system (Ref. AMM TASK 31-60-00-860-001) . (8) On the ECAM control panel, push (in) the FUEL P/BSW. (9) On the ECAM lower DU: · make sure that the FUEL page is shown · make sure that the intercell transfer valves are closed. (10) If the intercell transfer valves are open: (a) Refuel the aircraft until there is a minimum of 1000 kg (2204.6220 lb) of fuel in the wing-tank inner-cell. (b) On panels 49VU and 121VU, open the circuit breakers 1QT and 2QT. NOTE: It is not necessary to install safety clips and tags on the circuit breakers. (c) After a minimum of 5 seconds, the FQIC will de-energize. (d) On panels 49VU and 121VU, close the circuit breakers 1QT and 2QT. (e) After a minimum of 60 seconds, the FQIC will energize again and cycle the intercell transfer valves.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

(f)

If the intercell transfer valves stay open: · the inner and outer cells of the wing tanks fill together · the full capacity of the wing tank is less than normal · make an entry in the aircraft technical log, to correct the fuel configuration before the next flight (the wing-tank outer-cells must be filled).

** ON A/C 201-201, 206-207, 209-209, 222-222, 227-228, 236-236, 241-241 EMB SB 28-1030 for A/C 209-209 Subtask 28-25-00-860-075-B A.

Aircraft Maintenance Configuration (1) Make sure that the aircraft and the fuel tanker/pump unit are grounded correctly (Ref. AMM TASK 12-34-24-869-001) and electrically bonded together correctly. NOTE: Bonding is mandatory. For grounding you must obey the local area regulations. (2) Do a fuel sampling for water contamination check on the fuel in the fuel tanker/pump unit (Ref. AMM TASK 12-32-28-281-001) . CAUTION:

DO NOT REFUEL OR DEFUEL THROUGH THE TWO REFUEL/DEFUEL COUPLINGS AT THE SAME TIME. THIS IS TO PREVENT PRESSURE DIFFERENCE PROBLEMS.

(3) Remove the applicable refuel coupling cap 101QM(41QM). (4) Make sure that the coupling of the fuel supply-hose is clean. (5) Connect the coupling of the fuel supply-hose to the aircraft refuel coupling. (6) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (7) Energize the ECAM system (Ref. AMM TASK 31-60-00-860-001) . (8) On the ECAM control panel, push (in) the FUEL P/BSW. (9) On the ECAM lower DU: · make sure that the FUEL page is shown · make sure that the intercell transfer valves are closed. (10) If the intercell transfer valves are open: (a) Refuel the aircraft until there is a minimum of 1000 kg (2204.6220 lb) of fuel in the wing-tank inner-cell. (b) On panels 49VU and 121VU, open the circuit breakers 1QT and 2QT. NOTE: It is not necessary to install safety clips and tags on the circuit breakers. (c) After a minimum of 5 seconds, the FQIC will de-energize. (d) On panels 49VU and 121VU, close the circuit breakers 1QT and 2QT. (e) After a minimum of 60 seconds, the FQIC will energize again and cycle the intercell transfer valves. (f)

If the intercell transfer valves stay open: · the inner and outer cells of the wing tanks fill together · the full capacity of the wing tank is less than normal

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

· make an entry in the aircraft technical log, to correct the fuel configuration before the next flight (the wing-tank outer-cells must be filled). ** ON A/C 401-450 Subtask 28-25-00-860-075-C A.

Aircraft Maintenance Configuration (1) Make sure that the aircraft and the fuel tanker/pump unit are grounded correctly (Ref. AMM TASK 12-34-24-869-001) and electrically bonded together correctly. NOTE: Bonding is mandatory. For grounding you must obey the local area regulations. (2) Do a fuel sampling for water contamination check on the fuel in the fuel tanker/pump unit (Ref. AMM TASK 12-32-28-281-001) . (3) Remove the refuel coupling cap 41QM. (4) Make sure that the coupling of the fuel supply-hose is clean. (5) Connect the coupling of the fuel supply-hose to the aircraft refuel coupling. (6) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (7) Energize the ECAM system (Ref. AMM TASK 31-60-00-860-001) . (8) On the ECAM control panel, push (in) the FUEL P/BSW. (9) On the ECAM lower DU: · make sure that the FUEL page is shown

** ON A/C ALL Subtask 28-25-00-650-077-B B.

Fueling WARNING: BE CAREFUL NOT TO FILL THE TANKS MORE THAN NECESSARY NEAR THE END OF THE REFUEL PROCEDURE. WHEN YOU USE THE MANUAL OVERRIDE (MANUAL PLUNGER), THE HIGH-LEVEL PROTECTION SYSTEM WILL NOT STOP THE REFUELING AUTOMATICALLY. THUS THERE IS A RISK OF OVERFILLING AND FUEL SPILLAGE. CAUTION:

DO NOT REFUEL OR DEFUEL THROUGH THE TWO REFUEL/DEFUEL COUPLINGS AT THE SAME TIME. THIS IS TO PREVENT PRESSURE DIFFERENCE PROBLEMS.

CAUTION:

DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM PRESSURE OF 50 PSI (3.45 BARS). IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE AIRCRAFT OR EQUIPMENT CAN OCCUR.

(1) To prevent a fuel spill, on the panel 40VU, make sure that: · the X FEED P/BSW 4QE is released out (OFF) · the MODE SEL P/BSW 48QA is in the AUTO position · the CTR TK PUMP 1 & 2 P/BSW are released out (OFF). (2) Start the pump on the fuel tanker/pump unit. (3) Push and hold (in) the manual plunger(s) on the applicable refuel valve(s) 7QU(8QU) or 10QU. (4) Monitor the fuel quantity on the ECAM FUEL page.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

(5) When the quantity of fuel in the tank(s) is correct, release (out) the manual plunger(s) on the related refuel valve(s). (6) Stop the pump on the fuel tanker/pump unit. 5.

Close-up

** ON A/C 016-022, 024-100, 112-150, 203-205, 208-208, 210-221, 223-226, 229-235, 237-240, 242-250, 301450, 500-600 Subtask 28-25-00-860-076-A A.

Aircraft Configuration (1) Disconnect the coupling of the fuel supply-hose from the aircraft refuel/defuel coupling. CAUTION:

MAKE SURE THAT THE HANDLE OF THE REFUEL COUPLING CAP POINTS AFT WHEN THE CAP IS CLOSED AND LOCKED.

(2) Install the refuel coupling cap 41QM. (3) Make sure that the PLACARD that you use stays with the refuel/defuel panel until the manual refill is complete. (4) Make an entry in to the aircraft log. ** ON A/C 201-201, 206-207, 209-209, 222-222, 227-228, 236-236, 241-241 EMB SB 28-1030 for A/C 209-209 Subtask 28-25-00-860-076-B A.

Aircraft Configuration (1) Disconnect the coupling of the fuel supply-hose from the aircraft refuel/defuel coupling. CAUTION:

MAKE SURE THAT THE HANDLE OF THE REFUEL COUPLING CAP POINTS AFT WHEN THE CAP IS CLOSED AND LOCKED.

(2) Install the applicable refuel coupling cap 101QM(41QM). (3) Make sure that the PLACARD that you use stays with the refuel/defuel panel until the manual refill is complete. (4) Make an entry in to the aircraft log. ** ON A/C ALL Subtask 28-25-00-410-084-B B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) For the left refuel valve 7QU, close the access panel 522JB. (3) For the right refuel valve 8QU, close the access panel 622JB. (4) For the center tank refuel valve 10QU, close the RH MLG door 744 (Ref. AMM TASK 32-12-00-410001) .

Subtask 28-25-00-942-083-A C.

Removal of Equipment (1) Disconnect these bonding/ground cables:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

· between the aircraft and the fuel tanker/pump unit · if applicable, between the fuel tanker/pump unit and the ground · if applicable, between the aircraft and the ground. (2) Remove the safety barriers. (3) Remove the access platform(s). (4) Remove the WARNING NOTICE(S). (5) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

** ON A/C ALL TASK 28-25-00-040-008-A Refuel/Defuel Control Panel - Manual Refuel WARNING:

DO NOT TRANSMIT WITH THE HF SYSTEM DURING REFUEL/DEFUEL OR TRANSFER OPERATIONS. TRANSMISSION WITH THE HF SYSTEM DURING THESE FUEL OPERATIONS CAN CAUSE INJURY AND/OR START A FIRE.

WARNING:

STOP THE FUEL TANKER 60 M (196.85 FT) FROM THE AIRCRAFT NOSE WHILE THE WEATHER RADAR OPERATES. DO NOT OPERATE THE FUEL TANKER/PUMP UNIT UNTIL YOU STOP THE OPERATION OF THE WEATHER RADAR.

WARNING:

MAKE SURE THE AREA AROUND THE AIRCRAFT IS SAFE BEFORE YOU START THE REFUEL/DEFUEL PROCEDURE. IN THE SAFETY AREA, DO NOT: - SMOKE - MAKE SPARKS OR FIRE - USE ANY EQUIPMENT WHICH IS NOT APPROVED FOR REFUEL/DEFUEL PROCEDURES. AIRCRAFT FUEL IS FLAMMABLE.

WARNING:

MAKE SURE THAT THE WHEEL CHOCKS ARE IN POSITION. MOVEMENT OF THE AIRCRAFT CAN BE DANGEROUS.

WARNING:

MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

Task Summary MMEL or CDL Ref MMEL 28-25-05B MMEL 28-25-05A 1.

Access YES YES

Test YES YES

Specific Tools YES YES

Mhr 00.7 00.7

E/T 00.7 00.7

Nb Men 1 1

Reason for the Job MMEL 28-25-05B Exterior Refuel/Defuel Control Panel MMEL 28-25-05A Exterior Refuel/Defuel Control Panel NOTE: If installed, use the cockpit pre-selector to refuel.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

QTY AR AR AR

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE ACCESS PLATFORM 4M (13 FT) SAFETY BARRIER(S)

Work Zones and Access Panels

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

ZONE/ACCESS 522JB, 622JB, 744

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 12-11-28-650-001-A). (Ref. 12-11-28-650-002-A). (Ref. 12-32-28-281-001-A). (Ref. 12-34-24-869-001-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 32-00-00-481-001-A). (Ref. 32-12-00-010-001-A). (Ref. 32-12-00-410-001-A).

DESIGNATION General Refuel/Defuel Safety Procedures Refuel/Defuel Safety Procedures for use in the Hangar Drain Water Content Aircraft Bonding and Grounding (Earthing) for the Refuel/Defuel or Oxygen Servicing Operations Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) EIS Start Procedure Installation of the Safety Devices on the Landing Gears Open the Main Gear Doors for Access Close the Main Gear Doors after Access

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 416-450, 500-600 Refuel Valve SHEET 1 ** ON A/C 401-415 Refuel Valve SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

10QU

STA7792/RIB14

A

522 JB(622 JB)

STA8268/RIB15 REAR SPAR

A

7QU (8QU)

A

MANUALLY OPERATED PLUNGER

REFUEL VALVE

N_MM_282500_4_BAN0_01_00

Figure 28-25-00-991-02200-00-B / SHEET 1/1 - Refuel Valve ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 416-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

10QU 41QU

STA7792/RIB14

A

522 JB(622 JB)

STA8268/RIB15

A

A

REAR SPAR

7QU (8QU)

A

MANUALLY OPERATED PLUNGER

REFUEL VALVE

N_MM_282500_4_BAP0_01_00

Figure 28-25-00-991-02200-00-C / SHEET 1/1 - Refuel Valve ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

3.

Job Set-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 416-450, 500-600 (Ref. Fig. Refuel Valve SHEET 1) ** ON A/C 401-415 (Ref. Fig. Refuel Valve SHEET 1) ** ON A/C 016-022, 024-100, 112-150, 203-205, 208-208, 210-221, 223-226, 229-235, 237-240, 242-250, 301450, 500-600 Subtask 28-25-00-941-087-A A.

Safety Precautions WARNING: OBEY THE FUEL SAFETY PROCEDURES. (1) You must obey the refuel/defuel safety procedures (Ref. AMM TASK 12-11-28-650-001) (Ref. AMM TASK 12-11-28-650-002) . (2) Make sure that the ground safety locks are installed on the landing gear (Ref. AMM TASK 32-00-00481-001) . (3) Make sure that the chocks do not touch the tires. The weight of the fuel can lower the aircraft and cause the chocks to catch. (4) Put the SAFETY BARRIER(S) in position.

** ON A/C 201-201, 206-207, 209-209, 222-222, 227-228, 236-236, 241-241 EMB SB 28-1030 for A/C 209-209 Subtask 28-25-00-941-087-B A.

Safety Precautions WARNING: OBEY THE FUEL SAFETY PROCEDURES. (1) You must obey the refuel/defuel safety precautions (Ref. AMM TASK 12-11-28-650-001) (Ref. AMM TASK 12-11-28-650-002) . (2) Make sure that the ground safety locks are installed on the landing gear (Ref. AMM TASK 32-00-00481-001) . CAUTION:

DO NOT REFUEL OR DEFUEL THROUGH THE TWO REFUEL/DEFUEL COUPLINGS AT THE SAME TIME. THIS IS TO PREVENT PRESSURE DIFFERENCE PROBLEMS.

(3) Make sure that the chocks do not touch the tires. The weight of the fuel can lower the aircraft and cause the chocks to catch. (4) Put the SAFETY BARRIER(S) in position. ** ON A/C ALL Subtask 28-25-00-010-088-B B.

Get Access (1) To get access to the left refuel valve 7QU:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

(a) Put the ACCESS PLATFORM 4M (13 FT) in position below zone 522. (b) Remove the access panel 522JB. (2) To get access to the right refuel valve 8QU: (a) Put the ACCESS PLATFORM 4M (13 FT) in position below zone 622. (b) Remove the access panel 622JB. (3) To get access to the center tank refuel valve 10QU: (a) Open the RH MLG door 744 (Ref. AMM TASK 32-12-00-010-001) . (b) Make sure that the SLEEVE - GROUND LOCK (460005835) is on the applicable MLG door actuator. (c) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below zone 148. 4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 203-205, 208-208, 210-221, 223-226, 229-235, 237-240, 242-250, 301400, 500-600 Subtask 28-25-00-860-075-A A.

Aircraft Maintenance Configuration (1) Make sure that the aircraft and the fuel tanker/pump unit are grounded correctly (Ref. AMM TASK 12-34-24-869-001) and electrically bonded together correctly. NOTE: Bonding is mandatory. For grounding you must obey the local area regulations. (2) Do a fuel sampling for water contamination check on the fuel in the fuel tanker/pump unit (Ref. AMM TASK 12-32-28-281-001) . (3) Remove the refuel coupling cap 41QM. (4) Make sure that the coupling of the fuel supply-hose is clean. (5) Connect the coupling of the fuel supply-hose to the aircraft refuel coupling. (6) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (7) Energize the ECAM system (Ref. AMM TASK 31-60-00-860-001) . (8) On the ECAM control panel, push (in) the FUEL P/BSW. (9) On the ECAM lower DU: · make sure that the FUEL page is shown · make sure that the intercell transfer valves are closed. (10) If the intercell transfer valves are open: (a) Refuel the aircraft until there is a minimum of 1000 kg (2204.6220 lb) of fuel in the wing-tank inner-cell. (b) On panels 49VU and 121VU, open the circuit breakers 1QT and 2QT. NOTE: It is not necessary to install safety clips and tags on the circuit breakers. (c) After a minimum of 5 seconds, the FQIC will de-energize. (d) On panels 49VU and 121VU, close the circuit breakers 1QT and 2QT. (e) After a minimum of 60 seconds, the FQIC will energize again and cycle the intercell transfer valves.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

(f)

If the intercell transfer valves stay open: · the inner and outer cells of the wing tanks fill together · the full capacity of the wing tank is less than normal · make an entry in the aircraft technical log, to correct the fuel configuration before the next flight (the wing-tank outer-cells must be filled).

** ON A/C 201-201, 206-207, 209-209, 222-222, 227-228, 236-236, 241-241 EMB SB 28-1030 for A/C 209-209 Subtask 28-25-00-860-075-B A.

Aircraft Maintenance Configuration (1) Make sure that the aircraft and the fuel tanker/pump unit are grounded correctly (Ref. AMM TASK 12-34-24-869-001) and electrically bonded together correctly. NOTE: Bonding is mandatory. For grounding you must obey the local area regulations. (2) Do a fuel sampling for water contamination check on the fuel in the fuel tanker/pump unit (Ref. AMM TASK 12-32-28-281-001) . CAUTION:

DO NOT REFUEL OR DEFUEL THROUGH THE TWO REFUEL/DEFUEL COUPLINGS AT THE SAME TIME. THIS IS TO PREVENT PRESSURE DIFFERENCE PROBLEMS.

(3) Remove the applicable refuel coupling cap 101QM(41QM). (4) Make sure that the coupling of the fuel supply-hose is clean. (5) Connect the coupling of the fuel supply-hose to the aircraft refuel coupling. (6) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (7) Energize the ECAM system (Ref. AMM TASK 31-60-00-860-001) . (8) On the ECAM control panel, push (in) the FUEL P/BSW. (9) On the ECAM lower DU: · make sure that the FUEL page is shown · make sure that the intercell transfer valves are closed. (10) If the intercell transfer valves are open: (a) Refuel the aircraft until there is a minimum of 1000 kg (2204.6220 lb) of fuel in the wing-tank inner-cell. (b) On panels 49VU and 121VU, open the circuit breakers 1QT and 2QT. NOTE: It is not necessary to install safety clips and tags on the circuit breakers. (c) After a minimum of 5 seconds, the FQIC will de-energize. (d) On panels 49VU and 121VU, close the circuit breakers 1QT and 2QT. (e) After a minimum of 60 seconds, the FQIC will energize again and cycle the intercell transfer valves. (f)

If the intercell transfer valves stay open: · the inner and outer cells of the wing tanks fill together · the full capacity of the wing tank is less than normal

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

· make an entry in the aircraft technical log, to correct the fuel configuration before the next flight (the wing-tank outer-cells must be filled). ** ON A/C 401-450 Subtask 28-25-00-860-075-C A.

Aircraft Maintenance Configuration (1) Make sure that the aircraft and the fuel tanker/pump unit are grounded correctly (Ref. AMM TASK 12-34-24-869-001) and electrically bonded together correctly. NOTE: Bonding is mandatory. For grounding you must obey the local area regulations. (2) Do a fuel sampling for water contamination check on the fuel in the fuel tanker/pump unit (Ref. AMM TASK 12-32-28-281-001) . (3) Remove the refuel coupling cap 41QM. (4) Make sure that the coupling of the fuel supply-hose is clean. (5) Connect the coupling of the fuel supply-hose to the aircraft refuel coupling. (6) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (7) Energize the ECAM system (Ref. AMM TASK 31-60-00-860-001) . (8) On the ECAM control panel, push (in) the FUEL P/BSW. (9) On the ECAM lower DU: · make sure that the FUEL page is shown

** ON A/C ALL Subtask 28-25-00-650-077-B B.

Fueling WARNING: BE CAREFUL NOT TO FILL THE TANKS MORE THAN NECESSARY NEAR THE END OF THE REFUEL PROCEDURE. WHEN YOU USE THE MANUAL OVERRIDE (MANUAL PLUNGER), THE HIGH-LEVEL PROTECTION SYSTEM WILL NOT STOP THE REFUELING AUTOMATICALLY. THUS THERE IS A RISK OF OVERFILLING AND FUEL SPILLAGE. CAUTION:

DO NOT REFUEL OR DEFUEL THROUGH THE TWO REFUEL/DEFUEL COUPLINGS AT THE SAME TIME. THIS IS TO PREVENT PRESSURE DIFFERENCE PROBLEMS.

CAUTION:

DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM PRESSURE OF 50 PSI (3.45 BARS). IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE AIRCRAFT OR EQUIPMENT CAN OCCUR.

(1) To prevent a fuel spill, on the panel 40VU, make sure that: · the X FEED P/BSW 4QE is released out (OFF) · the MODE SEL P/BSW 48QA is in the AUTO position · the CTR TK PUMP 1 & 2 P/BSW are released out (OFF). (2) Start the pump on the fuel tanker/pump unit. (3) Push and hold (in) the manual plunger(s) on the applicable refuel valve(s) 7QU(8QU) or 10QU. (4) Monitor the fuel quantity on the ECAM FUEL page.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

(5) When the quantity of fuel in the tank(s) is correct, release (out) the manual plunger(s) on the related refuel valve(s). (6) Stop the pump on the fuel tanker/pump unit. 5.

Close-up

** ON A/C 016-022, 024-100, 112-150, 203-205, 208-208, 210-221, 223-226, 229-235, 237-240, 242-250, 301450, 500-600 Subtask 28-25-00-860-076-A A.

Aircraft Configuration (1) Disconnect the coupling of the fuel supply-hose from the aircraft refuel/defuel coupling. CAUTION:

MAKE SURE THAT THE HANDLE OF THE REFUEL COUPLING CAP POINTS AFT WHEN THE CAP IS CLOSED AND LOCKED.

(2) Install the refuel coupling cap 41QM. (3) Make sure that the PLACARD that you use stays with the refuel/defuel panel until the manual refill is complete. (4) Make an entry in to the aircraft log. ** ON A/C 201-201, 206-207, 209-209, 222-222, 227-228, 236-236, 241-241 EMB SB 28-1030 for A/C 209-209 Subtask 28-25-00-860-076-B A.

Aircraft Configuration (1) Disconnect the coupling of the fuel supply-hose from the aircraft refuel/defuel coupling. CAUTION:

MAKE SURE THAT THE HANDLE OF THE REFUEL COUPLING CAP POINTS AFT WHEN THE CAP IS CLOSED AND LOCKED.

(2) Install the applicable refuel coupling cap 101QM(41QM). (3) Make sure that the PLACARD that you use stays with the refuel/defuel panel until the manual refill is complete. (4) Make an entry in to the aircraft log. ** ON A/C ALL Subtask 28-25-00-410-084-B B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) For the left refuel valve 7QU, close the access panel 522JB. (3) For the right refuel valve 8QU, close the access panel 622JB. (4) For the center tank refuel valve 10QU, close the RH MLG door 744 (Ref. AMM TASK 32-12-00-410001) .

Subtask 28-25-00-942-083-A C.

Removal of Equipment (1) Disconnect these bonding/ground cables:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-25-00-040-008-A - Refuel/Defuel Control Panel - Manual Refuel

· between the aircraft and the fuel tanker/pump unit · if applicable, between the fuel tanker/pump unit and the ground · if applicable, between the aircraft and the ground. (2) Remove the safety barriers. (3) Remove the access platform(s). (4) Remove the WARNING NOTICE(S). (5) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-001-A - Deactivation of the Fuel Transfer Valve

** ON A/C 401-415 TASK 28-28-00-040-001-A Deactivation of the Fuel Transfer Valve WARNING:

OBEY THE FUEL SAFETY PROCEDURES.

FIN : 165QM Task Summary MMEL or CDL Ref MMEL 28-28-02B MMEL 28-28-02A

Access NO NO

1.

Reason for the Job MMEL 28-28-02B ACT Transfer Valve MMEL 28-28-02A ACT Transfer Valve (FAA only)

2

Job Set-up Information A.

Specific Tools YES YES

Mhr 01.3 01.3

E/T 01.3 01.3

Nb Men 1 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific (T720456) (T720521)

B.

Test NO NO

QTY 1 1 AR AR 1 3 1 1

DESIGNATION ACCESS PLATFORM 1M(3 FT) BRIDGE-WIRE CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER TIE WRAP WARNING NOTICE(S) TOOL - VALVE LOCKING TOOL-VALVE LOCKING

Referenced Information REFERENCE (Ref. 12-11-28-650-003-A). (Ref. 12-11-28-650-004-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A). (Ref. 32-12-00-010-001-A).

DESIGNATION Pressure Refuel with Automatic Control Pressure Refuel with Manual Control Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures Open the Main Gear Doors for Access

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-001-A - Deactivation of the Fuel Transfer Valve

REFERENCE (Ref. 32-12-00-410-001-A). (Ref. 57-17-11-000-001-A). (Ref. 57-17-11-000-001-A-01). (Ref. 57-17-11-400-001-A). (Ref. 57-17-11-400-001-A-01).

DESIGNATION Close the Main Gear Doors after Access Removal of the Access Covers 147AZ (148AZ) Removal of the Access Cover 148AZ or/and the ACT-Equipment Support Door Installation of Access Covers 147AZ (148AZ) Installation of Access Cover 148AZ or/and the ACT-Equipment Support-Door

ACT Fuel-Transfer Valve 165QM

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-001-A - Deactivation of the Fuel Transfer Valve

FR42

FR36

A

B Z140

A D 2 6 FR42

C 165QM

5

1

4 3 7 PIN SLOT

B N_MM_282800_4_PLA1_01_00

Figure 28-28-00-991-00300-00-B / SHEET 1/2 - ACT Fuel-Transfer Valve 165QM ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-001-A - Deactivation of the Fuel Transfer Valve

CLOSED POSITION OPEN POSITION

C

A

B

A

B

OPEN POSITION

CLOSED POSITION

D

A A

B B

N_MM_282800_4_PLA1_02_00

Figure 28-28-00-991-00300-00-B / SHEET 2/2 - ACT Fuel-Transfer Valve 165QM ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-001-A - Deactivation of the Fuel Transfer Valve

3.

Job Set-up Subtask 28-28-00-860-071-A A.

Aircraft Maintenance Configuration (1) Obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00910-001) . (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) On the APU section of overhead panel 25VU, make sure that the APU/MASTER SW pushbutton switch (P/BSW) is released (the ON legend is off). (4) On the FUEL section of HYD/FUEL panel 40VU, make sure that all the L TK PUMPS and R TK PUMPS P/BSWs are released (the OFF legends are on). (5) Put the WARNING NOTICE(S) in position: · On the APU section of overhead panel 25VU, to tell persons not to operate the APU/MASTER SW P/BSW. · On the FUEL section of panel 40VU, to tell persons not to operate the fuel system. · On the ENG/APU FIRE panel located on overhead panel 20VU, to tell persons not to operate the fire extinguishing system. · On the Additional Center Tank (ACT) control section of panel 28VU, to tell persons not to operate the fuel system.

Subtask 28-28-00-865-058-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION FUEL/RFL/DFL/SPLY FUEL/RFL/DFL/XFR/DEFUEL/VALVE

FIN 2QU 1QU

LOCATION L23 L22

Subtask 28-28-00-010-051-D C.

Get Access (1) Open the left main-gear door for access (Ref. AMM TASK 32-12-00-010-001) . (2) Put an ACCESS PLATFORM 1M(3 FT) in position in the left Main-Landing-Gear (MLG) bay. (3) Remove the ACT-equipment support door (Ref. AMM TASK 57-17-11-000-001) .

4.

Procedure (Ref. Fig. ACT Fuel-Transfer Valve 165QM) Subtask 28-28-00-040-050-B A.

Deactivation of the ACT fuel-transfer valve (valve is OFF in the open position) NOTE: The subsequent procedure is the same for each installed ACT. Therefore, only one procedure is given. Differences between each ACT are given where applicable. (1) Removal of the ACT fuel-transfer valve-actuator (2): 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. (a) Disconnect the electrical connectors (3) and (4) from the receptacles of the ACT fuel-transfer valve-actuator (2).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-001-A - Deactivation of the Fuel Transfer Valve

(b) Cut and discard the lockwire: 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. 1

Cut and discard the lockwire from the screw (5).

(c) Loosen the screw (5) and remove the V-clamp (6) from the ACT fuel-transfer valve-actuator (2). (d) Remove the ACT fuel-transfer valve-actuator (2) from the shaft of the ACT fuel-transfer valve (1). (e) Remove the O-ring (7) and discard it. NOTE: If it is necessary to refuel the ACT(s) before the deactivation of the valve, you can temporarily put the fuel transfer valve into the closed position to enable the refuel of the ACT(s). NOTE: If it is not necessary to refuel the ACT(s), you can continue with work step paragraph (3). (2) Refuel the ACT(s): (a) On the line end of the electrical connector A (3), install a BRIDGE-WIRE (shunt) between the pins B and E. NOTE: The installed shunt provides a equivalent earth path for the ACT refuel valve and prevents an inhibition of ACT refuel. (b) Do a visual check on the indicator of the ACT fuel-transfer valve-actuator (2) to identify the position of the valve: · Indicator in horizontal position, the transfer valve is OPEN · Indicator in vertical position, the transfer valve is CLOSED. (c) Turn the shaft of the ACT fuel-transfer valve (1) to the closed position. (d) Install the TOOL - VALVE LOCKING (T720456) on the flange of the ACT fuel-transfer valve (1) to lock the valve in the closed position during the refuel of the ACT(s). (e) Remove the safety clips and tags then close these circuit breakers: - 2QU, 1QU. (f)

Do refuel the applicable ACT(s) (Ref. AMM TASK 12-11-28-650-003) or (Ref. AMM TASK 1211-28-650-004) .

(g) After the refuel of the ACT(s), open safety and tag again these circuit breakers: - 2QU, 1QU. (h) On the line end of the electrical connector A (3), remove the BRIDGE-WIRE (shunt) from the connector. (i)

Remove the TOOL - VALVE LOCKING (T720456) from the flange of the ACT fuel-transfer valve (1).

(3) Deactivate the ACT fuel-transfer valve in open position: 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. (a) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-001-A - Deactivation of the Fuel Transfer Valve

(b) Safety the electrical connectors (4) and (3) to the adjacent electrical harness with a TIE WRAP. (c) Do a visual check on the indicator of the ACT fuel-transfer valve-actuator (2) to identify the position of the valve: · Indicator in horizontal position, the transfer valve is OPEN · Indicator in vertical position, the transfer valve is CLOSED. (d) Turn the shaft of the ACT fuel-transfer valve (1) to the open position. (e) Install the TOOL-VALVE LOCKING (T720521) on the flange of the ACT fuel-transfer valve (1) to lock the valve in the open position. 5.

Close-up Subtask 28-28-00-865-059-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION FUEL/RFL/DFL/SPLY FUEL/RFL/DFL/XFR/DEFUEL/VALVE

FIN 2QU 1QU

LOCATION L23 L22

Subtask 28-28-00-860-072-D B.

Aircraft Maintenance Configuration (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the ACT-equipment support door (Ref. AMM TASK 57-17-11-400-001) . (3) Remove the access platform(s). (4) Close the main gear door (Ref. AMM TASK 32-12-00-410-001) . (5) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (6) Remove the WARNING NOTICES: · From APU section of overhead panel 25VU · From FUEL section of panel 40VU · From ENG/APU FIRE panel located on the overhead panel 20VU · From ACT control section of panel 28VU. (7) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-008-A - Deactivation of the ACT Transfer Valve in the Closed Position

** ON A/C 401-415 TASK 28-28-00-040-008-A Deactivation of the ACT Transfer Valve in the Closed Position WARNING:

OBEY THE FUEL SAFETY PROCEDURES.

Task Summary MMEL or CDL Ref MMEL 28-28-09C 1.

Reason for the Job MMEL 28-28-09C ACT 1 Inlet Valve

2

Job Set-up Information A.

Access NO

Specific Tools YES

Mhr 00.8

E/T 00.8

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific (T720456)

B.

Test NO

QTY 1 AR AR 1 1 1

DESIGNATION ACCESS PLATFORM 1M(3 FT) CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER TIE WRAP WARNING NOTICE(S) TOOL - VALVE LOCKING

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A). (Ref. 32-12-00-010-001-A). (Ref. 32-12-00-410-001-A). (Ref. 57-17-11-000-001-A). (Ref. 57-17-11-000-001-A-01). (Ref. 57-17-11-400-001-A). (Ref. 57-17-11-400-001-A-01).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures Open the Main Gear Doors for Access Close the Main Gear Doors after Access Removal of the Access Covers 147AZ (148AZ) Removal of the Access Cover 148AZ or/and the ACT-Equipment Support Door Installation of Access Covers 147AZ (148AZ) Installation of Access Cover 148AZ or/and the ACT-Equipment Support-Door

ACT Fuel-Transfer Valve 165QM

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-008-A - Deactivation of the ACT Transfer Valve in the Closed Position

FR42

FR36

A

B Z140

A D 2 6 FR42

C 165QM

5

1

4 3 7 PIN SLOT

B N_MM_282800_4_PLA1_01_00

Figure 28-28-00-991-00300-00-B / SHEET 1/2 - ACT Fuel-Transfer Valve 165QM ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-008-A - Deactivation of the ACT Transfer Valve in the Closed Position

CLOSED POSITION OPEN POSITION

C

A

B

A

B

OPEN POSITION

CLOSED POSITION

D

A A

B B

N_MM_282800_4_PLA1_02_00

Figure 28-28-00-991-00300-00-B / SHEET 2/2 - ACT Fuel-Transfer Valve 165QM ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-008-A - Deactivation of the ACT Transfer Valve in the Closed Position

3.

Job Set-up Subtask 28-28-00-860-172-A A.

Aircraft Maintenance Configuration (1) Obey the fuel safety procedures when you work on the fuel system (Ref. AMM TASK 28-00-00-910001) . (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) On the APU section of overhead panel 25VU, make sure that the APU/MASTER SW pushbutton switch is released (the ON legend is off). (4) On the FUEL section of HYD/FUEL panel 40VU, make sure that all tank pump pushbutton switches are released (the OFF legends are on). (5) Put a WARNING NOTICE(S) in position: · On the APU section of overhead panel 25VU, to tell persons not to operate the APU/MASTER SW pushbutton switch · On the FUEL section of panel 40VU, to tell persons not to operate the fuel system · On the ENG/APU FIRE panel located on the overhead panel 20VU, to tell persons not to operate the fire extinguishing system · On the Additional Center Tank (ACT) control section of panel 28VU, to tell persons not to operate the fuel system.

Subtask 28-28-00-010-089-C B.

Get Access (1) Open the left main-gear door for access (Ref. AMM TASK 32-12-00-010-001) . (2) Put an ACCESS PLATFORM 1M(3 FT) in position in the left MLG bay. (3) Remove the ACT equipment-support door (Ref. AMM TASK 57-17-11-000-001) .

4.

Procedure (Ref. Fig. ACT Fuel-Transfer Valve 165QM) Subtask 28-28-00-040-061-C CAUTION:

A.

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

Deactivation of the ACT Fuel-Transfer Valve in Valve Closed Position NOTE: A refuel of the ACT is not possible while ACT fuel-transfer valve OFF in valve CLOSED position. (1) Disconnect the electrical connectors (3) and (4) from the receptacles of the ACT fuel-transfer valveactuator (2). (2) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (3) Safety the electrical connectors (3) and (4) to the adjacent electrical harness with a TIE WRAP. (4) Do a visual check of the indicator of the ACT fuel-transfer valve-actuator to identify the position of the valve: · Indicator in horizontal position: the transfer valve is OPEN · Indicator in vertical position: the transfer valve is CLOSED. (5) Cut and discard the lockwire:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-008-A - Deactivation of the ACT Transfer Valve in the Closed Position

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. (a) Cut and discard the lockwire from the screw (5). (6) Loosen the screw (5) and remove the V-clamp (6) and the ACT fuel-transfer valve-actuator (2). (7) Remove the O-ring (7) and discard it: (a) Turn the shaft of the ACT fuel-transfer valve (1) to the closed position if necessary. (b) Install the TOOL - VALVE LOCKING (T720456) on the flange of the ACT fuel-transfer valve (1) to lock it in the closed position. 5.

Close-up Subtask 28-28-00-860-173-C A.

Put the aircraft back to the serviceable condition. (1) Install the ACT equipment-support door (Ref. AMM TASK 57-17-11-400-001) . (2) Make sure that the work area is clean and clear of tools and other items. (3) Remove the access platform(s). (4) Close the main gear doors (Ref. AMM TASK 32-12-00-410-001) . (5) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (6) Remove the WARNING NOTICE(S). (7) In the cockpit put a placard in position to tell the crew that the ACT fuel-transfer valve is OFF in valve CLOSED position. (8) On refuel/defuel control panel 801VU put a placard in position to tell the ground crew: · DO NOT REFUEL THE ACT(s). (9) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-017-A - Deactivation of the ACT Transfer Valve in the Closed Position

** ON A/C 401-415 TASK 28-28-00-040-017-A Deactivation of the ACT Transfer Valve in the Closed Position WARNING:

OBEY THE FUEL SAFETY PROCEDURES.

Task Summary MMEL or CDL Ref MMEL 28-28-04B

Access NO

1.

Reason for the Job MMEL 28-28-04B ACT Air Shutoff Valve (FAA only)

2

Job Set-up Information A.

Specific Tools YES

Mhr 00.8

E/T 00.8

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific (T720456)

B.

Test NO

QTY 1 AR AR 1 1 1

DESIGNATION ACCESS PLATFORM 1M(3 FT) CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER TIE WRAP WARNING NOTICE(S) TOOL - VALVE LOCKING

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A). (Ref. 32-12-00-010-001-A). (Ref. 32-12-00-410-001-A). (Ref. 57-17-11-000-001-A). (Ref. 57-17-11-000-001-A-01). (Ref. 57-17-11-400-001-A). (Ref. 57-17-11-400-001-A-01).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures Open the Main Gear Doors for Access Close the Main Gear Doors after Access Removal of the Access Covers 147AZ (148AZ) Removal of the Access Cover 148AZ or/and the ACT-Equipment Support Door Installation of Access Covers 147AZ (148AZ) Installation of Access Cover 148AZ or/and the ACT-Equipment Support-Door

ACT Fuel-Transfer Valve 165QM

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-017-A - Deactivation of the ACT Transfer Valve in the Closed Position

FR42

FR36

A

B Z140

A D 2 6 FR42

C 165QM

5

1

4 3 7 PIN SLOT

B N_MM_282800_4_PLA1_01_00

Figure 28-28-00-991-00300-00-B / SHEET 1/2 - ACT Fuel-Transfer Valve 165QM ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-017-A - Deactivation of the ACT Transfer Valve in the Closed Position

CLOSED POSITION OPEN POSITION

C

A

B

A

B

OPEN POSITION

CLOSED POSITION

D

A A

B B

N_MM_282800_4_PLA1_02_00

Figure 28-28-00-991-00300-00-B / SHEET 2/2 - ACT Fuel-Transfer Valve 165QM ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-017-A - Deactivation of the ACT Transfer Valve in the Closed Position

3.

Job Set-up Subtask 28-28-00-860-214-A A.

Aircraft Maintenance Configuration (1) Obey the fuel safety procedures when you work on the fuel system (Ref. AMM TASK 28-00-00-910001) . (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) On the APU section of overhead panel 25VU make sure that the APU/MASTER SW pushbutton switch is released (the ON legend is off). (4) On the FUEL section of HYD/FUEL panel 40VU make sure that all tank pump pushbutton switches are released (the OFF legends are on). (5) Put a WARNING NOTICE(S) in position: · On the APU section of overhead panel 25VU to tell persons not to operate the APU/MASTER SW pushbutton switch · On the FUEL section of panel 40VU to tell persons not to operate the fuel system · On the ENG/APU FIRE panel located on overhead panel 20VU to tell persons not to operate the fire extinguishing system · On the Additional Center Tank (ACT) control section of panel 28VU to tell persons not to operate the fuel system.

Subtask 28-28-00-010-109-B B.

Get Access (1) Open the left main-gear door for access (Ref. AMM TASK 32-12-00-010-001) . (2) Put an ACCESS PLATFORM 1M(3 FT) in position in the left MLG bay. (3) Remove the ACT equipment-support door (Ref. AMM TASK 57-17-11-000-001) .

4.

Procedure (Ref. Fig. ACT Fuel-Transfer Valve 165QM) Subtask 28-28-00-040-069-B CAUTION:

A.

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

Deactivation of the ACT Fuel-Transfer Valve in the Closed Position NOTE: A refuel of the ACT is not possible while ACT fuel-transfer valve is OFF in valve position CLOSED. (1) Disconnect the electrical connectors (3) and (4) from the receptacles of the ACT fuel-transfer valveactuator (2). (2) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (3) Safety the electrical connectors (3) and (4) to the adjacent electrical harness with a TIE WRAP. (4) Do a visual inspection of the indicator of the ACT fuel-transfer valve-actuator (2) to identify the position of the valve: · Indicator in horizontal position: the transfer valve is OPEN · Indicator in vertical position: the transfer valve is CLOSED. (5) Cut and discard the lockwire:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-017-A - Deactivation of the ACT Transfer Valve in the Closed Position

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. (a) Cut and discard the lockwire from the screw (5). (6) Loosen the screw (5) and remove the V-clamp (6) and the ACT fuel-transfer valve-actuator (2). (7) Remove the O-ring (7) and discard it: (a) Turn the shaft of the ACT fuel-transfer valve (1) to the closed position, if necessary. (b) Install the TOOL - VALVE LOCKING (T720456) on the flange of the ACT fuel-transfer valve (1) to lock it in the closed position. 5.

Close-up Subtask 28-28-00-860-215-B A.

Put the aircraft back to the serviceable condition. (1) Install the ACT equipment-support door (Ref. AMM TASK 57-17-11-400-001) . (2) Make sure that the work area is clean and clear of tools and other items. (3) Remove the access platform(s). (4) Close the main gear doors (Ref. AMM TASK 32-12-00-410-001) . (5) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (6) Remove the WARNING NOTICE(S). (7) In the cockpit, put a placard in position to tell the crew that the ACT fuel-transfer valve is OFF in valve position CLOSED. (8) On refuel/defuel control panel 801VU, put a placard in position to tell the ground crew: DO NOT REFUEL THE ACT(s). (9) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-005-A - Deactivation of the FWD ACT's Isolation Valve in the Closed Position

** ON A/C 401-415 TASK 28-28-00-040-005-A Deactivation of the FWD ACT's Isolation Valve in the Closed Position WARNING:

OBEY THE FUEL SAFETY PROCEDURES.

FIN : 236QM Task Summary MMEL or CDL Ref MMEL 28-28-16A

Access NO

1.

Reason for the Job MMEL 28-28-16A Forward ACT Isolation Valve

2

Job Set-up Information A.

Specific Tools YES

Mhr 00.8

E/T 00.8

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific

B.

Test NO

QTY 1 AR AR 1 AR

DESIGNATION ACCESS PLATFORM 2M (6 FT) CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER TIE WRAP WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. 14QFC1)

DESIGNATION Wire-Locking Dia: 0.8 mm CRES -

C. Referenced Information REFERENCE DESIGNATION (Ref. 12-11-28-650-004-A). Pressure Refuel with Manual Control (Ref. 24-41-00-861-002-A). Energize the Aircraft Electrical Circuits from the External Power (Ref. 24-41-00-861-002-A-01). Energize the Aircraft Electrical Circuits from the APU (Ref. 24-41-00-861-002-A-02). Energize the Aircraft Electrical Circuits from Engine 1(2) (Ref. 28-00-00-910-001-A). Fuel Safety Procedures (Ref. 32-12-00-010-001-A). Open the Main Gear Doors for Access (Ref. 32-12-00-410-001-A). Close the Main Gear Doors after Access ACT-FWD Isolation-Valve Actuator

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-005-A - Deactivation of the FWD ACT's Isolation Valve in the Closed Position

FR42

FR36

A B Z140

A C 2 6 FR42

5 236QM 1

4 3 7 PIN SLOT

B N_MM_282800_4_PLA3_01_00

Figure 28-28-00-991-01300-00-B / SHEET 1/2 - ACT-FWD Isolation-Valve Actuator ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-005-A - Deactivation of the FWD ACT's Isolation Valve in the Closed Position

A

B

A

B

VALVE OPEN

VALVE CLOSED

C

A A

B B

N_MM_282800_4_PLA3_02_00

Figure 28-28-00-991-01300-00-B / SHEET 2/2 - ACT-FWD Isolation-Valve Actuator ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-005-A - Deactivation of the FWD ACT's Isolation Valve in the Closed Position

3.

Job Set-up Subtask 28-28-00-860-112-A A.

Aircraft Maintenance Configuration WARNING: OBEY THE FUEL SAFETY PROCEDURES. (1) Obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00910-001) . (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) On the APU section of overhead panel 25VU make sure that the APU/MASTER SW pushbutton switch is released (the ON legend is off) (4) On the FUEL section of HYD/FUEL panel 40VU make sure that all tank pump pushbutton switches are released (the OFF legends are on). (5) Put a WARNING NOTICE(S) in position: · On the APU section of overhead panel 25VU to tell persons not to operate the APU/MASTER SW pushbutton switch · On the FUEL section of panel 40VU to tell persons not to operate the fuel system · On the ENG/APU FIRE panel located on the overhead panel 20VU to tell persons not to operate the fire extinguishing system · On the Additional Center Tank (ACT) control section of panel 28VU to tell persons not to operate the fuel system. (6) Put a WARNING NOTICE(S) in position on the MLG doors to tell persons not to operate the doors.

Subtask 28-28-00-010-061-A B.

Get Access (1) Open the left MLG door (Ref. AMM TASK 32-12-00-010-001) . (2) Put an ACCESS PLATFORM 2M (6 FT) in position in the left MLG bay.

4.

Procedure (Ref. Fig. ACT-FWD Isolation-Valve Actuator) Subtask 28-28-00-040-054-C A.

Forward-ACT Isolation Valve is OFF in the Closed Position NOTE: The forward-ACT isolation valve can stay in the closed position if there is no fuel in the ACT FWD. In this case do the subsequent procedure. (1) On refuel/defuel control panel 801VU, put the REFUEL VALVE selector switches of ACT AFT2 and ACT FWD to SHUT position. 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.

(2) Disconnect the electrical connectors (3) and (4) from the receptacle of the isolation valve actuator (2). (3) On the line end of the electrical connector A, install a BRIDGE-WIRE (shunt) on the electrical connector (3) between the pins B and E. (4) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (5) Safety the electrical connectors (3) and (4) to the adjacent electrical harness with a TIE WRAP. Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-005-A - Deactivation of the FWD ACT's Isolation Valve in the Closed Position

(6) Do a visual check of the see/feel indicator of the isolation valve actuator (2) to identify the position of the valve: · See/feel indicator in horizontal position: the isolation valve is OPEN · See/feel indicator in vertical position: the isolation valve is CLOSED. (7) Cut and discard the lockwire: 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. (a) Cut and discard the lockwire from the screw (5). (8) Loosen the screw (5) and disconnect the V-clamp (6) from the V-flange of the forward isolation valve (1). (9) Remove the O-ring (7) and discard it. (10) Remove the isolation valve actuator (2) from the forward isolation valve (1). (11) Manually turn the input pin of the forward isolation valve (1) to the closed position. (12) Install the TOOL - VALVE LOCKING (T720456) on the V-flange of the forward isolation valve (1) to lock it in the closed position. (13) Install the V-clamp (6) on the shaft of the forward isolation valve (1). (14) Tighten the screw (5) to safety the TOOL - VALVE LOCKING (T720456) on the valve. 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. (15) Safety the screw (5) with Wire-Locking Dia: 0.8 mm CRES - (Material No. 14QFC1). 5.

Close-up Subtask 28-28-00-860-113-A A.

Put the aircraft back to the serviceable condition. (1) Make sure that the work area is clean and clear of tools and other items. (2) On refuel/defuel control panel 801VU, put a placard in position to tell the ground crew that the automatic refuel of the aircraft is not possible. NOTE: On the refuel/defuel control panel 801VU, the AFMS FAULT light comes ON after AFMC power-up test. (3) If you must refuel the aircraft, do the pressure refuel with manual control (Ref. AMM TASK 12-11-28650-004) . (4) Close the left MLG door (Ref. AMM TASK 32-12-00-410-001) . (5) Remove the access platform(s). (6) Remove the Warning Notice(s) from the cockpit and from the MLG door. (7) Make an entry in the logbook.

End of document Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-007-A - Deactivation of the Vent Valve in the Closed Position

** ON A/C 401-415 TASK 28-28-00-040-007-A Deactivation of the Vent Valve in the Closed Position WARNING:

OBEY THE FUEL SAFETY PROCEDURES.

FIN : 234QM Task Summary MMEL or CDL Ref MMEL 28-28-06C 1.

Reason for the Job MMEL 28-28-06C ACT Vent Valve

2

Job Set-up Information A.

Access YES

Specific Tools YES

Mhr 01.3

E/T 01.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific (T720456)

B.

Test NO

QTY 1 1 AR AR 1 AR 1

DESIGNATION ACCESS PLATFORM 1M(3 FT) BRIDGE-WIRE CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER TIE WRAP WARNING NOTICE(S) TOOL - VALVE LOCKING

Consumable Materials REFERENCE (Material No. 14QFC1)

DESIGNATION Wire-Locking Dia: 0.8 mm CRES -

C. Work Zones and Access Panels ZONE/ACCESS 195 195BB

ZONE DESCRIPTION HYDRAULIC COMPT AND FAIRINGS

D. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-007-A - Deactivation of the Vent Valve in the Closed Position

REFERENCE (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A). (Ref. 28-28-00-860-802-A). ACT Vent-Valve Actuator

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures ACT Vent Valve - Simulation Fully Open with Vent Valve Deactivated

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-007-A - Deactivation of the Vent Valve in the Closed Position

A Z140

234QM

FR42

FR36

B

SLOT

7

A

6 5 1 2

91QH

3

C 4

B N_MM_282800_4_ABB0_01_00

Figure 28-28-00-991-01200-00-B / SHEET 1/2 - ACT Vent-Valve Actuator ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-007-A - Deactivation of the Vent Valve in the Closed Position

B

A

B

A

CLOSED POSITION

OPEN POSITION

C

A A

B B

N_MM_282800_4_ABB0_02_00

Figure 28-28-00-991-01200-00-B / SHEET 2/2 - ACT Vent-Valve Actuator ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-007-A - Deactivation of the Vent Valve in the Closed Position

3.

Job Set-up Subtask 28-28-00-860-114-A A.

Aircraft Maintenance Configuration (1) Obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00910-001) . (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) On the APU section of overhead panel 25VU, make sure that the APU/MASTER SW pushbutton switch is released (the ON legend is off). (4) On the FUEL section of HYD/FUEL panel 40VU, make sure that all tank pump pushbutton switches are released (the OFF legends are on). (5) Put a WARNING NOTICE(S) in position: · On the APU section of overhead panel 25VU, to tell persons not to operate the APU/MASTER SW pushbutton switch, · On the FUEL section of panel 40VU, to tell persons not to operate the fuel system · On the ENG/APU FIRE panel located on overhead panel 20VU, to tell persons not to operate the fire extinguishing system · On the Additional Center Tank (ACT) control section of panel 28VU, to tell persons not to operate the fuel system. (6) Put a WARNING NOTICE(S) in position to tell persons not to operate the main gear doors.

Subtask 28-28-00-865-087-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION FUEL/ACT VENT VLV/MAN/SPLY FUEL/ACT VENT VLV/AUTO/SPLY

FIN 62QH 61QH

LOCATION L21 L20

Subtask 28-28-00-010-068-A C.

Get Access (1) Put an ACCESS PLATFORM 1M(3 FT) in position at zone 195. (2) On the lower fuselage, open access door 195BB.

4.

Procedure (Ref. Fig. ACT Vent-Valve Actuator) Subtask 28-28-00-040-056-B CAUTION:

A.

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

ACT Vent Valve is OFF in the closed position NOTE: The ACT vent valve can stay in CLOSED position during the flight. (1) Disconnect the electrical connectors (3) and (4) from the receptacles of the actuator (2). (2) On the line end of the electrical connector A, install a BRIDGE-WIRE (shunt) on the electrical connector (3) between the pins B and E. (3) Put the CAP-BLANKING on each disconnected electrical connector and receptacle.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-007-A - Deactivation of the Vent Valve in the Closed Position

(4) Safety the electrical connectors (3) and (4) to the adjacent electrical harness with a TIE WRAP. (5) Do a visual check of the see/feel indicator of the vent valve actuator to identify the position of the valve: · See/feel indicator aligned, the ACT vent valve is OPEN · See/feel indicator across, the ACT vent valve is CLOSED. (6) Cut and discard the lockwire: 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. (a) Cut and discard the lockwire from the screw (5). (7) Loosen the screw (5) and remove the V-clamp (1) and the actuator (2) from the shaft (7) of the ACT vent valve. (8) Remove the O-ring (6) and discard it. (9) If necessary, turn the shaft (7) of the ACT vent valve to CLOSED position. (10) Install the TOOL - VALVE LOCKING (T720456) on the flange of the ACT vent valve to lock the valve in CLOSED position. (11) Install the V-clamp (1) on the shaft (7) of the ACT vent valve. (12) Tighten the screw (5) to safety the TOOL - VALVE LOCKING on the valve. 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. (13) Safety the screw (5) with Wire-Locking Dia: 0.8 mm CRES - (Material No. 14QFC1). 5.

Close-up Subtask 28-28-00-865-088-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION FUEL/ACT VENT VLV/MAN/SPLY FUEL/ACT VENT VLV/AUTO/SPLY

FIN 62QH 61QH

LOCATION L21 L20

Subtask 28-28-00-860-115-A B.

Put the aircraft back to the serviceable condition. (1) Make sure that the work area is clean and clear of tools and other items. (2) If you must refuel the ACT(s) with deactivated vent valve, do the simulation task of ACT vent valve fully open (Ref. AMM TASK 28-28-00-860-802) . NOTE: On refuel/defuel control panel 801VU, the AFMS FAULT light comes ON after AFMC powerup test. (3) On the lower fuselage, close access door 195BB. (4) De-energize the aircraft electrical circuits

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-007-A - Deactivation of the Vent Valve in the Closed Position

(Ref. AMM TASK 24-41-00-862-002) . (5) Remove the access platform(s). (6) Remove the WARNING NOTICE(S). (7) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-006-A - Check of the Integrated Impact Wall for Permissible Damage

** ON A/C 401-415 TASK 28-28-00-040-006-A Check of the Integrated Impact Wall for Permissible Damage WARNING:

OBEY THE FUEL SAFETY PROCEDURES.

Task Summary MMEL or CDL Ref MMEL 28-28-08A

Access NO

1.

Reason for the Job MMEL 28-28-08A ACT Integrated Impact Wall

2

Job Set-up Information A.

Specific Tools NO

Mhr 01.0

E/T 01.0

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

Test NO

QTY 1 AR 2

DESIGNATION ACCESS PLATFORM 2M (6 FT) SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 28-00-00-910-001-A). Fuel Safety Procedures (Ref. 28-11-49-000-002-A). Removal of the ACT Integrated Impact Wall (Ref. 28-11-49-400-002-A). Installation of the ACT Integrated Impact Wall (Ref. 52-30-00-860-001-A). Open the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump (Ref. 52-30-00-860-002-A). Close the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump Location of the Attachment Points SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-006-A - Check of the Integrated Impact Wall for Permissible Damage

FR50 FR47.5

A

FR47.2 FR47.1

ACT AFT2

Z150

HEAT SHIELD

HEAT SHIELD PROTECTION COVER

PROTECTION COVER NOTE: "R" ATTACHMENT POINTS "Y" ATTACHMENT POINTS

A N_MM_282800_4_PLA4_01_00

Figure 28-28-00-991-00900-00-C / SHEET 1/1 - Location of the Attachment Points ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-006-A - Check of the Integrated Impact Wall for Permissible Damage

3.

Job Set-up Subtask 28-28-00-860-092-A A.

Aircraft Maintenance Configuration (1) Obey the fuel safety procedures (Ref. AMM TASK 28-00-00-910-001) . (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) Open the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-001) . (4) Put an ACCESS PLATFORM 2M (6 FT) in position at the opening of the aft cargo-compartment. (5) Put a WARNING NOTICE(S) in position on: · Refuel/defuel control panel 801VU · Fuel control panel 40VU · Additional Center Tank (ACT) control panel 28VU to tell persons not to operate the refuel/defuel system.

Subtask 28-28-00-865-072-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

DESIGNATION FUEL/ACT AIR SOV/MAN/SPLY FUEL/ACT AIR SOV/AUTO/SPLY FUEL/ACT XFR VLV/MOT2 FUEL/ACT XFR VLV/MOT1 FUEL/HI/LVL/SPLY FUEL/RFL/DFL/SPLY FUEL/RFL/DFL/XFR/DEFUEL/VALVE FUEL/ACT VENT VLV/MAN/SPLY FUEL/ACT VENT VLV/AUTO/SPLY FUEL/ACT/FUEL PUMP/SPLY

FIN 64QH 63QH 66QH 65QH 1QJ 2QU 1QU 62QH 61QH 25QH

LOCATION J20 J19 J18 J17 L24 L23 L22 L21 L20 Q29

Subtask 28-28-00-010-063-B C.

Get Access (1) Remove the applicable integrated impact wall (Ref. AMM TASK 28-11-49-000-002) . NOTE: The removal is not necessary if three 'Y' attachments points of the protection cover of the integrated impact wall is damaged, see the procedure below.

4.

Procedure (Ref. Fig. Location of the Attachment Points SHEET 1) Subtask 28-28-00-040-055-B CAUTION:

A.

BE CAREFUL NOT TO CAUSE DAMAGE TO THE HEAT SHIELD. DAMAGE TO THE HEAT SHIELD IS NOT PERMITTED.

Do a check for Permissible Damage of the Integrated Impact Wall NOTE: The integrated impact wall has a protection cover and a heat shield which are assembled together. (1) Damage Limits - Protection Cover (a) At least three of the 'Y' attachment points must not be damaged, then you can

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-006-A - Check of the Integrated Impact Wall for Permissible Damage

· Dispatch the aircraft in the subsequent conditions: · The placards must be visible · You must do a repair procedure as soon as possible. (b) Dispatch is possible with all the 'Y' attachment points damaged in the subsequent conditions: · You must remove the remaining protection cover · You must install the heat shield with new spacers · You must do a repair procedure as soon as possible · The placards must be visible. (2) Damage Limits - Heat Shield (a) Major or minor damage to the front surface of the heat shield: NOTE: The protection cover must be removed before you can inspect the heat shield. · Replace the integrated impact wall (Ref. AMM TASK 28-11-49-000-002) (Ref. AMM TASK 28-11-49-400-002) , or · Dispatch the aircraft without cargo. (b) Major or minor damage to the rear profiled surface of the wall: · Replace the integrated impact wall (Ref. AMM TASK 28-11-49-000-002) (Ref. AMM TASK 28-11-49-400-002) , or · Dispatch the aircraft without cargo. 5.

Close-up Subtask 28-28-00-865-073-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

DESIGNATION FUEL/ACT AIR SOV/MAN/SPLY FUEL/ACT AIR SOV/AUTO/SPLY FUEL/ACT XFR VLV/MOT2 FUEL/ACT XFR VLV/MOT1 FUEL/HI/LVL/SPLY FUEL/RFL/DFL/SPLY FUEL/RFL/DFL/XFR/DEFUEL/VALVE FUEL/ACT VENT VLV/MAN/SPLY FUEL/ACT VENT VLV/AUTO/SPLY FUEL/ACT/FUEL PUMP/SPLY

FIN 64QH 63QH 66QH 65QH 1QJ 2QU 1QU 62QH 61QH 25QH

LOCATION J20 J19 J18 J17 L24 L23 L22 L21 L20 Q29

Subtask 28-28-00-860-093-C B.

Put the aircraft back to the serviceable condition. (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the integrated impact wall (Ref. AMM TASK 28-11-49-400-002) . (3) Remove the access platform(s). (4) Close the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-002) . (5) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (6) Remove the WARNING NOTICE(S). (7) If you have done restrictions to the integrated impact wall: (a) Put a WARNING NOTICE(S) in position in the cockpit to tell these actions to the flight crew.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-006-A - Check of the Integrated Impact Wall for Permissible Damage

(b) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-29-00-040-002-A - APU LP VALVE - Deactivation

** ON A/C ALL TASK 28-29-00-040-002-A APU LP VALVE - Deactivation

FIN : 14QM Task Summary MMEL or CDL Ref MMEL 28-29-01B 1.

Reason for the Job MMEL 28-29-01B APU LP Fuel Valve

2

Job Set-up Information A.

Access NO

Test NO

Mhr 00.7

E/T 00.7

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific No specific No specific No specific

QTY 1 AR 1 1 AR 1 2 2

No specific (B12990) B.

Specific Tools YES

1

DESIGNATION BAG - POLYTHENE CAP - BLANKING FLASHLIGHT MIRROR - INSPECTION SAFETY CLIP - CIRCUIT BREAKER STEPLADDER 2.0 M (6.6 FT) TIE WRAP WARNING NOTICE(S) Torque wrench: range to between 0.117 and 0.143 m.daN (10.35 and 12.65 lbf.in) Torque wrench: range to between 0.6 and 0.7 m.daN (53.10 and 61.95 lbf.in) LOCKING COVER

Referenced Information REFERENCE (Ref. 20-28-00-912-802-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Electrical Bonding - General Maintenance Procedure Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 32-12-00-010-001-A). Open the Main Gear Doors for Access (Ref. 32-12-00-410-001-A). Close the Main Gear Doors after Access APU LP Fuel Valve and Actuator (P/N B27000).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-29-00-040-002-A - APU LP VALVE - Deactivation

REFERENCE DESIGNATION APU LP Fuel Valve and Actuator (P/N A08000).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-29-00-040-002-A - APU LP VALVE - Deactivation

1

FR53

2

FR48

3

FR57

4

FR59 1

FR31

2

FR35.4

3

FR28

4

FR31

A

Z147

3 4

A

C

5 6

2

6

B

3

CENTER SECTION REAR SPAR FR42

4 1 3QF

NOTE: 1

A320

2

A321

3

A319

4

A318

SHUT OFF VALVE

APU FUEL LP VALVE ACTUATOR

D

9

N_MM_282900_4_AAMA_01_00

Figure 28-29-00-991-00100-00-A / SHEET 1/2 - APU LP Fuel Valve and Actuator (P/N B27000). ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-29-00-040-002-A - APU LP VALVE - Deactivation

B

1

VISUAL INDICATOR COLOURED BAR

LABEL READING RED OPEN

LABEL READING GREEN CLOSED

C CABLES SHOWN TIED BACK WITH TIE-WRAPS

D 7

2 TIE WRAP

VALVE OPEN

VALVE CLOSED

N_MM_282900_4_AAMA_02_00

Figure 28-29-00-991-00100-00-A / SHEET 2/2 - APU LP Fuel Valve and Actuator (P/N B27000). ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-29-00-040-002-A - APU LP VALVE - Deactivation

1

FR53

2

FR48

3

FR57

4

FR59 1

FR31

2

FR35.4

3

FR28

4

FR31

A

Z147

A 3

C

2

B

4

3

2

5 LOCKING COVER 4

FR42 CENTER SECTION REAR SPAR 1 ACTUATOR P/N A08000

SHUT-OFF VALVE

NOTE: 1

A320

2

A321

3

A319

4

A318

6 7 5020QM ADAPTER P/N A08900 N_MM_282900_4_ACMA_01_00

Figure 28-29-00-991-00200-00-A / SHEET 1/2 - APU LP Fuel Valve and Actuator (P/N A08000). ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-29-00-040-002-A - APU LP VALVE - Deactivation

B EXAMPLE

POSITION INDICATOR

C CABLES SHOWN TIED BACK WITH TIE-WRAPS

8 TIE WRAP

N_MM_282900_4_ACMA_02_00

Figure 28-29-00-991-00200-00-A / SHEET 2/2 - APU LP Fuel Valve and Actuator (P/N A08000). ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-29-00-040-002-A - APU LP VALVE - Deactivation

3.

Job Set-up Subtask 28-29-00-860-054-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) (2) On the panel 25VU, make sure that the APU MASTER SW pushbutton switch is in the off position (the ON and FAULT legends are off).

Subtask 28-29-00-865-058-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/FUEL/LP VALVE/CTL APU/FUEL/LP VALVE/SPLY

FIN 1QF 2QF

LOCATION M40 M39

Subtask 28-29-00-010-051-A C.

Get Access (1) Open the main landing-gear doors Z734,Z744 (Ref. AMM TASK 32-12-00-010-001) . (2) Put the STEPLADDER 2.0 M (6.6 FT) in position at the main landing-gear bay.

4.

Procedure Subtask 28-29-00-040-050-A A.

Deactivation of the APU Fuel LP-Valve (Actuator P/N B27000) (Ref. Fig. APU LP Fuel Valve and Actuator (P/N B27000).) (1) In the Main Landing Gear (MLG) bay, check the position of the APU fuel LP-valve (14QM) at the visual position indicator of the APU fuel LP-valve-actuator (3QF). NOTE: Use a FLASHLIGHT and a MIRROR - INSPECTION to see the visual position indicator. (2) If the visual position indicator shows a green bar, the APU fuel LP-valve is in the closed position, then you must do this procedure: (a) Disconnect the electrical connectors 3QF-A and 3QF-B (2) from the actuator (1). (b) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (c) Fold the electrical connectors/cables (2) back over the cable clamps and attach them with a TIE WRAP to a stowage position. (3) If the visual position indicator shows a red bar, the APU fuel LP valve is in the open position, then you must do this procedure: (a) Disconnect the electrical connectors 3QF-A and 3QF-B (2) from the actuator (1). (b) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (c) Fold the electrical connectors/cables (2) back over the cable clamps and attach them with a TIE WRAP to a stowage position. (d) Hold the APU fuel LP-valve actuator (1) in position and remove the nuts (3), the washers (4) and the bonding strap (5). (e) Disconnect the drive shaft of the actuator from the drive shaft of the valve and remove the actuator (1). (f)

Turn the drive shaft of the valve (7) to the horizontal position (closed position).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-29-00-040-002-A - APU LP VALVE - Deactivation

(g) Viewed on the actuator mounting face, turn the drive shaft of the actuator in counterclockwise direction until the visual position indicator shows a green bar (closed position). (h) Make sure that you do not damage the drive shaft of the actuator when you turn it. NOTE: Do not apply more torque than 0.12 m.daN (10.62 lbf.in) to turn the drive shaft of the actuator. NOTE: Do not turn the drive shaft of the actuator in clockwise direction. NOTE: Install a new actuator: - if you can not turn the drive shaft of the actuator within the torque limit of 0.12 m.daN (10.62 lbf.in) - if you can turn the drive shaft of the actuator freely without a torque - if the drive shaft of the actuator is damaged and does not engage correctly into the drive shaft of the valve. (i)

Put the actuator (1) in position on the studs (9).

(j)

Engage the drive shaft of the actuator into the drive shaft of the valve (7) (closed position).

(k) Make sure that the washers (4), the nuts (3) and the bonding strap (5) are in a good condition. (l)

Connect the bonding strap (5) to the actuator (1), install the washers (4) and the nuts (3) (Ref. AMM TASK 20-28-00-912-802) .

(m) Torque the nuts (3) to between 0.6 and 0.7 m.daN (53.10 and 61.95 lbf.in). (4) In the cockpit, on the panel 25VU, put a WARNING NOTICE(S) in position to tell people not to operate the APU (APU fuel LP-valve is locked in closed position). (5) Make an entry in the aircraft-logbook, that the APU fuel LP-valve (14QM) is locked in closed position and the APU must not operate. (6) Cockpit effects: The APU LP Valve symbol shows the transit position on the ECAM FUEL page when the valve is deactivated. Subtask 28-29-00-040-051-A B.

Deactivation of the APU Fuel LP-Valve (with Actuator P/N A08000) (Ref. Fig. APU LP Fuel Valve and Actuator (P/N A08000).) (1) In the Main Landing Gear (MLG) bay, check the position of the APU fuel LP-valve (14QM) at the visual position indicator of the APU fuel LP-valve-actuator (3QF). (2) If the visual position indicator is in the SHUT position, then you must do this procedure: (a) Disconnect the electrical connectors 3QF-A and 3QF-B (4) from the actuator (1). (b) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (c) Fold the electrical connectors/cables (4) back over the cable clamps and attach the cables (4) with a TIE WRAP (8) to a stowage position. (3) If the visual position indicator is in the OPEN position, then you must do this procedure: (a) Disconnect the electrical connectors 3QF-A and 3QF-B (4) from the actuator (1). (b) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (c) Fold the electrical connectors/cables (4) back over the cable clamps and attach the cables (4) with a TIE WRAP (8) to a stowage position. (d) If necessary, remove the screw (3) and disconnect the bonding strap (2).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-29-00-040-002-A - APU LP VALVE - Deactivation

(e) Hold the APU fuel LP-valve actuator (1) in position and and loosen the V-Band clamp (6). (f)

Disconnect and remove the actuator (1) from the valve adapter (7).

(g) Turn the drive shaft of the valve to the horizontal position (closed position). (h) Turn the drive shaft of the actuator in counterclockwise direction until the visual position indicator is in the SHUT position. (i)

Make sure that you do not damage the drive shaft of the actuator when you turn it. NOTE: Do not apply more torque than 0.12 m.daN (10.62 lbf.in) to turn the drive shaft of the actuator. NOTE: Do not turn the drive shaft of the actuator in clockwise direction. NOTE: Lock the valve with the applicable LOCKING COVER (Ref. Para. (4)): - if you can not turn the drive shaft of the actuator within the torque limit of 0.12 m.daN (10.62 lbf.in) - if you can turn the drive shaft of the actuator freely without a torque - if the drive shaft of the actuator is damaged and does not engage correctly into the drive shaft of the valve.

(j)

Put the actuator (1) in position on the valve adapter (7).

(k) Engage the drive shaft of the actuator into the drive shaft of the valve (closed position). (l)

Install the V-Band clamp (6) on the actuator (1) and the valve adapter (7).

(m) TORQUE the nuts of the V-Band clamp (6) to between 0.117 and 0.143 m.daN (10.35 and 12.65 lbf.in). (n) If removed, connect the bonding strap (2) to the actuator (1) and install the screw (3) (Ref. AMM TASK 20-28-00-912-802) . (4) Lock the APU fuel LP-valve (14QM) in the closed position with the LOCKING COVER (B12990) : NOTE: This is an alternative procedure to lock the APU fuel LP-valve if the actuator (3QF) is removed. NOTE: You must lock the APU fuel LP-valve in the closed position with the LOCKING COVER: - if you can not turn the drive shaft of the actuator counterclockwise within the torque limit of 0.12 m.daN (10.62 lbf.in) - if you can turn the drive shaft of the actuator freely without a torque - if the drive shaft of the actuator is damaged and does not engage into the drive shaft of the valve. (a) Put the LOCKING COVER (5) in position on the valve adapter (7). (b) Engage the LOCKING COVER (5) into the slot of the valve drive shaft (closed position). (c) Install the V-Band clamp (6) on the LOCKING COVER (5) and the valve adapter (7). (d) TORQUE the nuts of the V-Band clamp (6) to between 0.117 and 0.143 m.daN (10.35 and 12.65 lbf.in). (e) Connect the bonding strap (2) to the LOCKING COVER (5) and install the screw (3) (Ref. AMM TASK 20-28-00-912-802) . (f)

TORQUE the screw (3) to between 0.6 and 0.7 m.daN (53.10 and 61.95 lbf.in).

(g) Put the actuator (1) in a BAG - POLYTHENE and keep it in a safe location.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-29-00-040-002-A - APU LP VALVE - Deactivation

(5) In the cockpit, on the panel 25VU, put a WARNING NOTICE(S) in position to tell people not to operate the APU (APU fuel LP-valve is locked in closed position). (6) Make an entry in the aircraft-logbook that the APU fuel LP-valve (14QM) is locked in closed position and the APU must not operate. (7) Cockpit effects: The APU LP Valve symbol shows the transit position on the ECAM FUEL page when the valve is deactivated. 5.

Close-up Subtask 28-29-00-410-052-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the stepladder. (3) Close the main landing-gear doors (Ref. AMM TASK 32-12-00-410-001) .

Subtask 28-29-00-860-055-A B.

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

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-29-00-440-002-A - APU LP VALVE - Reactivation

** ON A/C ALL TASK 28-29-00-440-002-A APU LP VALVE - Reactivation

FIN : 14QM 1.

Reason for the Job MMEL 28-29-01B APU LP Fuel Valve

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION 1 STEPLADDER 2.0 M (6.6 FT)

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 28-29-51-400-001-A). Installation of the APU Fuel LP Valve Actuator (Ref. 32-12-00-010-001-A). Open the Main Gear Doors for Access (Ref. 32-12-00-410-001-A). Close the Main Gear Doors after Access Ref. TSM 28-29-00-810-801 APU Fuel Supply Failure APU LP Fuel Valve and Actuator (P/N B27000). APU LP Fuel Valve and Actuator (P/N A08000).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-29-00-440-002-A - APU LP VALVE - Reactivation

1

FR53

2

FR48

3

FR57

4

FR59 1

FR31

2

FR35.4

3

FR28

4

FR31

A

Z147

3 4

A

C

5 6

2

6

B

3

CENTER SECTION REAR SPAR FR42

4 1 3QF

NOTE: 1

A320

2

A321

3

A319

4

A318

SHUT OFF VALVE

APU FUEL LP VALVE ACTUATOR

D

9

N_MM_282900_4_AAMA_01_00

Figure 28-29-00-991-00100-00-A / SHEET 1/2 - APU LP Fuel Valve and Actuator (P/N B27000). ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-29-00-440-002-A - APU LP VALVE - Reactivation

B

1

VISUAL INDICATOR COLOURED BAR

LABEL READING RED OPEN

LABEL READING GREEN CLOSED

C CABLES SHOWN TIED BACK WITH TIE-WRAPS

D 7

2 TIE WRAP

VALVE OPEN

VALVE CLOSED

N_MM_282900_4_AAMA_02_00

Figure 28-29-00-991-00100-00-A / SHEET 2/2 - APU LP Fuel Valve and Actuator (P/N B27000). ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-29-00-440-002-A - APU LP VALVE - Reactivation

1

FR53

2

FR48

3

FR57

4

FR59 1

FR31

2

FR35.4

3

FR28

4

FR31

A

Z147

A 3

C

2

B

4

3

2

5 LOCKING COVER 4

FR42 CENTER SECTION REAR SPAR 1 ACTUATOR P/N A08000

SHUT-OFF VALVE

NOTE: 1

A320

2

A321

3

A319

4

A318

6 7 5020QM ADAPTER P/N A08900 N_MM_282900_4_ACMA_01_00

Figure 28-29-00-991-00200-00-A / SHEET 1/2 - APU LP Fuel Valve and Actuator (P/N A08000). ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-29-00-440-002-A - APU LP VALVE - Reactivation

B EXAMPLE

POSITION INDICATOR

C CABLES SHOWN TIED BACK WITH TIE-WRAPS

8 TIE WRAP

N_MM_282900_4_ACMA_02_00

Figure 28-29-00-991-00200-00-A / SHEET 2/2 - APU LP Fuel Valve and Actuator (P/N A08000). ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-29-00-440-002-A - APU LP VALVE - Reactivation

3.

Job Set-up Subtask 28-29-00-860-056-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002)

Subtask 28-29-00-865-060-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged: PANEL 121VU 121VU

DESIGNATION APU/FUEL/LP VALVE/CTL APU/FUEL/LP VALVE/SPLY

FIN 1QF 2QF

LOCATION M40 M39

Subtask 28-29-00-010-052-A C.

Get Access (1) Open the main landing-gear doors Z734, Z744 (Ref. AMM TASK 32-12-00-010-001) . (2) Put the STEPLADDER 2.0 M (6.6 FT) in position at the main landing-gear bay.

4.

Procedure Subtask 28-29-00-440-050-A A.

Reactivation of the APU LP Shutoff Valve (Actuator P/N B27000) (Ref. Fig. APU LP Fuel Valve and Actuator (P/N B27000).) (1) If the LP-valve actuator was removed to deactivate the LP shutoff valve do the following steps: (a) Remove the electrical connectors (2) from the locking device (8). (b) Remove the nuts (3), the washers (4) and the bonding strap (5) from the actuator mount studs (9). (c) Remove the locking device (8). (d) Install the APU-fuel LP-valve actuator (1) (Ref. AMM TASK 28-29-51-400-001) . (2) If the LP shutoff valve was deactivated without a removal of the actuator do following steps: (a) Remove the tie-wraps from the tied back cables/connectors (2). (b) Make sure that all the electrical connections are clean and in the correct condition. (c) Connect the connectors (2) to the actuator.

Subtask 28-29-00-440-051-A B.

Reactivation of the APU LP Shutoff Valve (Actuator P/N A08000) (Ref. Fig. APU LP Fuel Valve and Actuator (P/N A08000).) (1) If the LP-valve actuator was removed to deactivate the LP shutoff valve do the following steps: (a) Remove the tie-wraps (8) from the tied back cables/connectors (4). (b) Make sure that all the electrical connections are clean and in the correct condition. (c) Remove the screw (3) and the bonding strap (2) from the locking cover (5). (d) Remove the V-Band clamp (6) and the locking cover (5). (e) Install the APU-fuel LP-valve actuator (1) (Ref. AMM TASK 28-29-51-400-001) . (2) If the LP shutoff valve was deactivated without a removal of the actuator do following steps: (a) Remove the tie-wraps (8) from the tied back cables/connectors (4).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-29-00-440-002-A - APU LP VALVE - Reactivation

(b) Make sure that all the electrical connections are clean and in the correct condition. (c) Connect the connectors (4) to the actuator. Subtask 28-29-00-865-059-A C.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION APU/FUEL/LP VALVE/CTL APU/FUEL/LP VALVE/SPLY

FIN 1QF 2QF

LOCATION M40 M39

Subtask 28-29-00-810-050-A D.

Trouble Shooting (1) Trouble shoot the APU LP Fuel Shutoff-Valve Ref. TSM 28-29-00-810-801 . (2) Remove the WARNING NOTICE(S). (3) Make an entry in the logbook that the APU LP Fuel Shutoff-Valve is reactivated.

5.

Close-up Subtask 28-29-00-410-053-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the stepladder. (3) Close the main landing-gear doors Z734, Z744 (Ref. AMM TASK 32-12-00-410-001) .

Subtask 28-29-00-860-057-A B.

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

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-015-A - Deactivation of the ACT Transfer Valve in the Closed Position

** ON A/C 401-415 TASK 28-28-00-040-015-A Deactivation of the ACT Transfer Valve in the Closed Position WARNING:

OBEY THE FUEL SAFETY PROCEDURES.

Task Summary MMEL or CDL Ref MMEL 28-46-02A

Access NO

Test NO

1.

Reason for the Job MMEL 28-46-02A High Level Detection System (FAA only)

2

Job Set-up Information A.

Mhr 00.8

E/T 00.8

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific (T720456)

B.

Specific Tools YES

QTY 1 AR AR 1 1 1

DESIGNATION ACCESS PLATFORM 1M(3 FT) CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER TIE WRAP WARNING NOTICE(S) TOOL - VALVE LOCKING

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A). (Ref. 32-12-00-010-001-A). (Ref. 32-12-00-410-001-A). (Ref. 57-17-11-000-001-A). (Ref. 57-17-11-000-001-A-01). (Ref. 57-17-11-400-001-A). (Ref. 57-17-11-400-001-A-01).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures Open the Main Gear Doors for Access Close the Main Gear Doors after Access Removal of the Access Covers 147AZ (148AZ) Removal of the Access Cover 148AZ or/and the ACT-Equipment Support Door Installation of Access Covers 147AZ (148AZ) Installation of Access Cover 148AZ or/and the ACT-Equipment Support-Door

ACT Fuel-Transfer Valve 165QM

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-015-A - Deactivation of the ACT Transfer Valve in the Closed Position

FR42

FR36

A

B Z140

A D 2 6 FR42

C 165QM

5

1

4 3 7 PIN SLOT

B N_MM_282800_4_PLA1_01_00

Figure 28-28-00-991-00300-00-B / SHEET 1/2 - ACT Fuel-Transfer Valve 165QM ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-015-A - Deactivation of the ACT Transfer Valve in the Closed Position

CLOSED POSITION OPEN POSITION

C

A

B

A

B

OPEN POSITION

CLOSED POSITION

D

A A

B B

N_MM_282800_4_PLA1_02_00

Figure 28-28-00-991-00300-00-B / SHEET 2/2 - ACT Fuel-Transfer Valve 165QM ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-015-A - Deactivation of the ACT Transfer Valve in the Closed Position

3.

Job Set-up Subtask 28-28-00-860-204-A A.

Aircraft Maintenance Configuration (1) Obey the fuel safety procedures when you work on the fuel system (Ref. AMM TASK 28-00-00-910001) . (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) On the APU section of overhead panel 25VU make sure that the APU/MASTER SW pushbutton switch is released (the ON legend is off). (4) On the FUEL section of HYD/FUEL panel 40VU make sure that all tank pump pushbutton switches are released (the OFF legends are on). (5) Put a WARNING NOTICE(S) in position: · On the APU section of overhead panel 25VU to tell persons not to operate the APU/MASTER SW pushbutton switch · On the FUEL section of panel 40VU to tell persons not to operate the fuel system · On the ENG/APU FIRE panel located on overhead panel 20VU to tell persons not to operate the fire extinguishing system · On the Additional Center Tank (ACT) control section of panel 28VU to tell persons not to operate the fuel system.

Subtask 28-28-00-010-104-B B.

Get Access (1) Open the left main-gear door for access (Ref. AMM TASK 32-12-00-010-001) . (2) Put an ACCESS PLATFORM 1M(3 FT) in position in the left MLG bay. (3) Remove the ACT equipment-support door (Ref. AMM TASK 57-17-11-000-001) .

4.

Procedure (Ref. Fig. ACT Fuel-Transfer Valve 165QM) Subtask 28-28-00-040-067-B CAUTION:

A.

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

Deactivation of the ACT Fuel-Transfer Valve in the Closed Position NOTE: A refuel of the ACT is not possible while ACT fuel-transfer valve is OFF in the CLOSED position. (1) Disconnect the electrical connectors (3) and (4) from the receptacles of the ACT transfer-valve actuator (2). (2) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (3) Safety the electrical connectors (3) and (4) to the adjacent electrical harness with a TIE WRAP. (4) Do a visual check of the indicator of the ACT transfer-valve actuator (2) to identify the position of the valve: · Indicator in horizontal position: the transfer valve is OPEN · Indicator in vertical position: the transfer valve is CLOSED. (5) Cut and discard lockwire:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-015-A - Deactivation of the ACT Transfer Valve in the Closed Position

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. (a) Cut and discard lockwire from the screw (5). (6) Loosen the screw (5) and remove the V-clamp (6) and the ACT transfer-valve actuator (2). (7) Remove the O-ring (7) and discard it: (a) Turn the shaft of the ACT fuel-transfer valve (1) to the closed position, if necessary. (b) Install the TOOL - VALVE LOCKING (T720456) on the flange of the ACT fuel-transfer valve (1) to lock it in the closed position. 5.

Close-up Subtask 28-28-00-860-205-B A.

Put the aircraft back to the serviceable condition. (1) Install the ACT equipment-support door (Ref. AMM TASK 57-17-11-400-001) . (2) Make sure that the work area is clean and clear of tools and other items. (3) Remove the access platform(s). (4) Close the main gear doors (Ref. AMM TASK 32-12-00-410-001) . (5) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (6) Remove the WARNING NOTICE(S). (7) In the cockpit, put a placard in position to tell the crew that the ACT fuel-transfer valve is OFF in the closed position. (8) On refuel/defuel control panel 801VU, put a placard in position to tell the ground crew: DO NOT REFUEL THE ACT(s). (9) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-018-A - Deactivation of the ACT Transfer Valve in the Closed Position

** ON A/C 401-415 TASK 28-28-00-040-018-A Deactivation of the ACT Transfer Valve in the Closed Position WARNING:

OBEY THE FUEL SAFETY PROCEDURES.

Task Summary MMEL or CDL Ref MMEL 28-46-05A

Access NO

Test NO

1.

Reason for the Job MMEL 28-46-05A Low Level Detection System in the ACT (FAA only)

2

Job Set-up Information A.

Mhr 00.8

E/T 00.8

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific (T720456)

B.

Specific Tools YES

QTY 1 AR AR 1 1 1

DESIGNATION ACCESS PLATFORM 1M(3 FT) CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER TIE WRAP WARNING NOTICE(S) TOOL - VALVE LOCKING

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A). (Ref. 32-12-00-010-001-A). (Ref. 32-12-00-410-001-A). (Ref. 57-17-11-000-001-A). (Ref. 57-17-11-000-001-A-01). (Ref. 57-17-11-400-001-A). (Ref. 57-17-11-400-001-A-01).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures Open the Main Gear Doors for Access Close the Main Gear Doors after Access Removal of the Access Covers 147AZ (148AZ) Removal of the Access Cover 148AZ or/and the ACT-Equipment Support Door Installation of Access Covers 147AZ (148AZ) Installation of Access Cover 148AZ or/and the ACT-Equipment Support-Door

ACT Fuel-Transfer Valve 165QM

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-018-A - Deactivation of the ACT Transfer Valve in the Closed Position

FR42

FR36

A

B Z140

A D 2 6 FR42

C 165QM

5

1

4 3 7 PIN SLOT

B N_MM_282800_4_PLA1_01_00

Figure 28-28-00-991-00300-00-B / SHEET 1/2 - ACT Fuel-Transfer Valve 165QM ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-018-A - Deactivation of the ACT Transfer Valve in the Closed Position

CLOSED POSITION OPEN POSITION

C

A

B

A

B

OPEN POSITION

CLOSED POSITION

D

A A

B B

N_MM_282800_4_PLA1_02_00

Figure 28-28-00-991-00300-00-B / SHEET 2/2 - ACT Fuel-Transfer Valve 165QM ** ON A/C 401-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-018-A - Deactivation of the ACT Transfer Valve in the Closed Position

3.

Job Set-up Subtask 28-28-00-860-216-A A.

Aircraft Maintenance Configuration (1) Obey the fuel safety procedures when you work on the fuel system (Ref. AMM TASK 28-00-00-910001) . (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) On the APU section of overhead panel 25VU, make sure that the APU/MASTER SW pushbutton switch is released (the ON legend is off). (4) On the fuel section of HYD/FUEL panel 40VU, make sure that all tank pump pushbutton switches are released (the OFF legends are on). (5) Put a WARNING NOTICE(S) in position: · On APU section of overhead panel 25VU, to tell persons not to operate the APU/MASTER SW pushbutton switch · On FUEL section of panel 40VU, to tell persons not to operate the fuel system · On ENG/APU FIRE panel located on overhead panel 20VU, to tell persons not to operate the fire extinguishing system · On Additional Center Tank (ACT) control section of panel 28VU, to tell persons not to operate the fuel system.

Subtask 28-28-00-010-110-B B.

Get Access (1) Open the left main-gear door for access (Ref. AMM TASK 32-12-00-010-001) . (2) Put an ACCESS PLATFORM 1M(3 FT) in position in the left MLG bay. (3) Remove the ACT equipment-support door (Ref. AMM TASK 57-17-11-000-001) .

4.

Procedure (Ref. Fig. ACT Fuel-Transfer Valve 165QM) Subtask 28-28-00-040-070-B CAUTION:

A.

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

Deactivation of the ACT Fuel-Transfer Valve in the Closed Position NOTE: A refuel of the ACT is not possible while ACT fuel-transfer valve is OFF in valve CLOSED position. (1) Disconnect the electrical connectors (3) and (4) from the receptacles of the ACT fuel-transfer valveactuator (2). (2) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (3) Safety the electrical connectors (3) and (4) to the adjacent electrical harness with a TIE WRAP. (4) Do a visual check of the indicator of the ACT fuel-transfer valve-actuator (2) to identify the position of the valve: · Indicator in horizontal position: the transfer valve is OPEN · Indicator in vertical position: the transfer valve is CLOSED. (5) Cut and discard the lockwire:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-28-00-040-018-A - Deactivation of the ACT Transfer Valve in the Closed Position

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. (a) Cut and discard the lockwire from the screw (5). (6) Loosen the screw (5) and remove the v-clamp (6) and the ACT fuel-transfer valve-actuator (2). (7) Remove the O-ring (7) and discard it: (a) Turn the shaft of the ACT fuel-transfer valve (1) to the closed position if necessary. (b) Install the TOOL - VALVE LOCKING (T720456) on the flange of the ACT fuel-transfer valve (1) to lock it in the closed position. 5.

Close-up Subtask 28-28-00-860-217-B A.

Put the aircraft back to the serviceable condition. (1) Install the ACT equipment-support door (Ref. AMM TASK 57-17-11-400-001) . (2) Make sure that the work area is clean and clear of tools and other items. (3) Remove the access platform(s). (4) Close the main gear doors (Ref. AMM TASK 32-12-00-410-001) . (5) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (6) Remove the WARNING NOTICE(S). (7) In the cockpit put a placard in position to tell the crew that the ACT fuel-transfer valve is OFF in valve position CLOSED. (8) On the refuel/defuel control panel 801VU put a placard in position to tell the ground crew: DO NOT REFUEL THE ACT(s). (9) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-012-A - Refuel Procedure for use with an Unserviceable Magnetic Level Indicator (MLI)

** ON A/C ALL TASK 28-40-00-040-012-A Refuel Procedure for use with an Unserviceable Magnetic Level Indicator (MLI) 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.

1.

Reason for the Job MMEL 28-43-01B Manual Magnetic Indicators

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR SAFETY BARRIER(S)

Referenced Information REFERENCE (Ref. 12-11-28-650-004-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 28-00-00-910-001-A).

DESIGNATION Pressure Refuel with Manual Control Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Fuel Safety Procedures

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 416-450, 500-600 (Ref. 28-46-00-710-001-A). Test of the Tank High-Level Sensing-System ** ON A/C ALL (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). 3.

EIS Start Procedure EIS Stop Procedure

Job Set-up Subtask 28-40-00-941-071-A A.

Safety Precautions

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-012-A - Refuel Procedure for use with an Unserviceable Magnetic Level Indicator (MLI)

WARNING: OBEY THE FUEL SAFETY PROCEDURES. (1) You must obey the fuel safety procedures when you work on the fuel system (Ref. AMM TASK 2800-00-910-001) . (2) Put the SAFETY BARRIER(S) in position. Subtask 28-40-00-860-075-A B.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Do the EIS start procedure (ECAM only) (Ref. AMM TASK 31-60-00-860-001) . (3) On the ECAM control panel, push (in) the FUEL pushbutton switch to show the FUEL page on the ECAM lower display unit. (4) Make sure that the F.USED indications on the FUEL page are correctly shown.

4.

Procedure Subtask 28-40-00-040-085-A A.

Refuel Procedure for use with an Unserviceable Magnetic Level Indicator (MLI) WARNING: BE CAREFUL NOT TO FILL THE TANKS MORE THAN NECESSARY NEAR THE END OF THE REFUEL PROCEDURE. WHEN YOU USE THE MANUAL OVERRIDE (MANUAL PLUNGER), THE HIGH-LEVEL PROTECTION SYSTEM WILL NOT STOP THE REFUELING AUTOMATICALLY. THUS THERE IS A RISK OF OVERFILLING AND FUEL SPILLAGE. CAUTION:

DO NOT REFUEL OR DEFUEL THROUGH THE TWO REFUEL/DEFUEL COUPLINGS AT THE SAME TIME. THIS IS TO PREVENT PRESSURE DIFFERENCE PROBLEMS.

CAUTION:

DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM PRESSURE OF 50 PSI (3.45 BARS). IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE AIRCRAFT OR EQUIPMENT CAN OCCUR.

(1) Do a test of the high level sensors (Ref. AMM TASK 28-46-00-710-001) . (2) Refuel the aircraft as follows: (a) Fully refuel the wing tanks until (Ref. AMM TASK 12-11-28-650-004) : · the high level sensors operate and · the high level lights on the Refuel/Defuel Control Panel 800VU come on. (b) Multiply the total volume of the fuel by the specific gravity of the fuel. The result is the total mass of the fuel. NOTE: Make sure that this total is equal to the maximum capacity of the applicable wing tank. 5.

Close-up Subtask 28-40-00-860-076-A A.

Aircraft Configuration (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 28-40-00-040-012-A - Refuel Procedure for use with an Unserviceable Magnetic Level Indicator (MLI)

(3) Make a note in the aircraft technical log that the FQI system of the applicable wing is unserviceable. Subtask 28-40-00-942-069-A B.

Removal of Equipment (1) Remove the SAFETY BARRIER(S). (2) Make sure that the work area is clean and clear of tools and other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-30-00-040-001-A - Integrity Check of the RAT after RAT FAULT Warning

** ON A/C ALL TASK 29-30-00-040-001-A Integrity Check of the RAT after RAT FAULT Warning

FIN : 2GE Task Summary MMEL or CDL Ref MMEL 29-09-08A 1.

Access NO

Test YES

Specific Tools NO

Mhr 00.6

E/T 00.6

Nb Men 1

Reason for the Job MMEL 29-09-08A HYD RAT FAULT Alert NOTE: Use this procedure together with the Master Minimum Equipment List (MMEL). If the fault indication is because of a defect in the indication system it is permitted to dispatch the aircraft. It is also permitted to dispatch the aircraft if the defect is in the RAT ground test system (if the system is known to be in the "flight" condition). It is not permitted to dispatch the aircraft if the fault indication is because of a defect which could prevent operation of the RAT. NOTE: If any part of the system is deactivated, after each flight, the deactivated component must be reactivated and this procedure done again. This is to find any faults which were not shown because of the deactivation.

2

Job Set-up Information A.

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 29-10-00-863-003-A). Pressurize the Blue Hydraulic System with a Hydraulic Ground PowerCart (Ref. 29-10-00-863-003-A-01). Pressurize the Blue Hydraulic System with the Blue Electric Pump (Ref. 29-10-00-864-003-A). Depressurize the Blue Hydraulic System (Ref. 29-22-00-869-005-A). Extension of the Ram Air Turbine (RAT) on the Ground (Ref. 29-22-00-869-006-A). Retraction of the Ram Air Turbine (RAT) on the Ground (Ref. 31-60-00-860-001-A). EIS Start Procedure (Ref. 31-60-00-860-002-A). EIS Stop Procedure Ref. TSM 29-22-00-810-801 Fault of the Ram Air Turbine Location of RAT - Components SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-30-00-040-001-A - Integrity Check of the RAT after RAT FAULT Warning

A

B

A 195BB 197EB

1GE-E

C

C EJECTION JACK

B INDICATION LIGHTS

RAM AIR TURBINE INTERLOCK ACTUATOR PRESSURE WARNING

RAT STOWED

RESET O N

RAT CONTROL STOW

LAMP TEST

PANEL 3GE

28V DC

O F F

J2

N_MM_293000_4_AEP0_01_00

Figure 29-30-00-991-00300-00-D / SHEET 1/1 - Location of RAT - Components ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-30-00-040-001-A - Integrity Check of the RAT after RAT FAULT Warning

3.

Job Set-up Subtask 29-30-00-860-050-A A.

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) On the ECAM control panel on the center pedestal, press the HYD pushbutton switch (P/BSW). Make sure that the ECAM lower Display Unit (DU) shows the HYD page. (4) Make sure that the ECAM upper DU shows the RAT FAULT indication.

Subtask 29-30-00-010-056-A B.

Get Access (1) Open the access panels 195BB and 197EB.

4.

Procedure (Ref. Fig. Location of RAT - Components SHEET 1) Subtask 29-30-00-040-050-B A.

Integrity Check of the Ram Air Turbine (RAT) after RAT FAULT Warning (1) Do a visual check of the left belly fairing to make sure that the RAT is not extended. (2) If the RAT is extended: (a) Do the applicable troubleshooting procedures Ref. TSM 29-22-00-810-801 . (b) If the fault has been corrected, go to Para. 5.A. (3) If the RAT is not extended, do the steps that follow: (a) Pressurize the Blue hydraulic system (Ref. AMM TASK 29-10-00-863-003) . (b) Extend the RAT (Ref. AMM TASK 29-22-00-869-005) . If the RAT STOWED indicator light comes on, ignore it. (c) Make sure that the RAT stays in the deployed position. (d) Retract the RAT (Ref. AMM TASK 29-22-00-869-006) . If the RAT STOWED indicator light goes off, ignore it. (e) Make sure that the RAT stays in the stowed position. If the RAT FAULT indicator light comes on, ignore it. This RAT FAULT warning is false. (f)

Depressurize the Blue hydraulic system (Ref. AMM TASK 29-10-00-864-003) .

(g) Make an entry in the logbook. 5.

Close-up Subtask 29-30-00-410-054-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access panels 195BB and 197EB.

Subtask 29-30-00-860-051-A B.

Put the aircraft back to the serviceable condition. (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-30-00-040-001-A - Integrity Check of the RAT after RAT FAULT Warning

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

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-30-00-040-003-A - Deactivation of the Reservoir Low-Level Warning

** ON A/C ALL TASK 29-30-00-040-003-A Deactivation of the Reservoir Low-Level Warning Task Summary MMEL or CDL Ref MMEL 29-09-05A 1.

Access YES

Test NO

Specific Tools NO

Mhr 00.5

E/T 00.5

Nb Men 1

Reason for the Job MMEL 29-09-05A HYD G(B)(Y) RSVR LO LVL Alert (FAA only) NOTE: The ECAM caution message -RSVR LO LVL- can be incorrectly shown because of a defective lowlevel switch. This condition is identified if the related PUMP FAULT LIGHT comes on (for the Blue hydraulic system) or, at the same time, the related PUMP FAULT light and PTU FAULT light come on (for the Green and/or Yellow hydraulic systems). When one or two of these lights are 'ON', do a check of the related low-level switch (Ref. AMM TASK 29-31-00-710-001). Deactivate the switch if you cannot repair or replace it. Push the 'CLEAR' button on the ECAM to clear the -RSVR LO LVL- caution message. The PUMP FAULT lights will come on in if there is a pump failure. The subsequent quantity differences will be shown by the -RSVR LO LVL- caution message on the ECAM when the transmitter is in operation. Although, for this condition, the PUMP FAULT lights will not operate as usual because of the deactivated low-level switch.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION 2 CAP - PROTECTION AR TIE WRAP

Work Zones and Access Panels ZONE/ACCESS 196BB, 197FB

ZONE DESCRIPTION

C. Referenced Information REFERENCE DESIGNATION (Ref. 12-12-29-611-001-A). Fill the Hydraulic Fluid Reservoir with a Hand Pump (Ref. 12-12-29-611-002-A). Fill the Hydraulic Fluid Reservoir with a Hydraulic Service Cart (Ref. 32-12-00-010-001-A). Open the Main Gear Doors for Access (Ref. 32-12-00-410-001-A). Close the Main Gear Doors after Access Location of the Reservoir Low-Level Switches SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-30-00-040-003-A - Deactivation of the Reservoir Low-Level Warning

A

A C

197FB FR43

B

196BB

FR42

Z147

D B

FR41 FR42

FR50

C

FR49

D

D

EXAMPLE

D

LOW LEVEL SWITCH

N_MM_293000_4_AGM0_01_00

Figure 29-30-00-991-00400-00-A / SHEET 1/1 - Location of the Reservoir Low-Level Switches ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-30-00-040-003-A - Deactivation of the Reservoir Low-Level Warning

3.

Job Set-up (Ref. Fig. Location of the Reservoir Low-Level Switches SHEET 1) Subtask 29-30-00-010-054-A A.

Get Access (1) Open these access doors: · For the Green reservoir, open one main gear door (Ref. AMM TASK 32-12-00-010-001) NOTE: You can open one of the two doors, but access is better from the RH side. · For the Blue reservoir, open the access door 197FB · For the Yellow reservoir, open the access door 196BB and the RH main door of the main gear (Ref. AMM TASK 32-12-00-010-001) .

4.

Procedure Subtask 29-30-00-040-052-A A.

Deactivation of the Reservoir Low-Level Switches (1) Disconnect the applicable electrical connector from the low-level switch of the related hydraulic reservoir. (2) Install a CAP - PROTECTION on the disconnected electrical connector and on the receptacle of the reservoir. (3) Use a TIE WRAP and attach the cable to a part of the adjacent structure. (4) Make sure that oil or other liquids cannot go into the connector end.

Subtask 29-30-00-210-052-A B.

Visual Check of the Reservoir Content (1) Do a check of the content of the deactivated reservoir with the quantity indicator on the reservoir before each flight. (2) If necessary, fill the reservoir to the correct level (Ref. AMM TASK 12-12-29-611-001) or (Ref. AMM TASK 12-12-29-611-002) .

Subtask 29-30-00-941-050-A C. 5.

Put a warning notice in the flight compartment to tell the crew that the fluid low-level warning-system does not operate.

Close-up Subtask 29-30-00-410-058-A A.

Close Access (1) Close these access doors: · For the Green reservoir, close the main gear door (Ref. AMM TASK 32-12-00-410-001) · For the Blue reservoir, close the access door 197FB · For the Yellow reservoir, close the access door 196BB and the RH main door of the main gear (Ref. AMM TASK 32-12-00-410-001) . (2) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-30-00-040-802-A - Deactivation of the Pressure Transmitter

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 233-233 TASK 29-30-00-040-802-A Deactivation of the Pressure Transmitter 1.

Reason for the Job MMEL 29-07-08A System Pressure Indication on the HYD SD page

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION AR CAP - PROTECTION AR TIE WRAP

Work Zones and Access Panels ZONE/ACCESS 147 195 196 195BB, 196BB

ZONE DESCRIPTION MAIN GEAR WELL AND HYDRAULIC COMPARTMENT HYDRAULIC COMPT AND FAIRINGS HYDRAULIC COMPT AND FAIRINGS

C. Referenced Information REFERENCE DESIGNATION (Ref. 32-12-00-010-001-A). Open the Main Gear Doors for Access (Ref. 32-12-00-410-001-A). Close the Main Gear Doors after Access Location of the Pressure Transmitter

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-30-00-040-802-A - Deactivation of the Pressure Transmitter

FR44

Z147

C B

Z196

D

A

Z195 195BB 196BB

FR41

A FR42

FR41 FR42

E

B F

C

N_MM_293000_4_AAAA_01_00

Figure 29-30-00-991-00500-00-A / SHEET 1/2 - Location of the Pressure Transmitter ** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 233233 | EMB SB 31-1286 for A/C 201-201, 207-207, 210-210 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-30-00-040-802-A - Deactivation of the Pressure Transmitter

D E

1065GN 3065GN

1

D

E 1

2065GN

F

N_MM_293000_4_AAAA_02_00

Figure 29-30-00-991-00500-00-A / SHEET 2/2 - Location of the Pressure Transmitter ** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 233233 | EMB SB 31-1286 for A/C 201-201, 207-207, 210-210 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-30-00-040-802-A - Deactivation of the Pressure Transmitter

3.

Job Set-up

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 233-233 EMB SB 31-1286 for A/C 201-201, 207-207, 210-210 Subtask 29-30-00-010-058-A A.

Get Access (1) Open the related access doors to get access to the HP manifold. (a) For the Green system, open one main gear door (Ref. AMM TASK 32-12-00-010-001) . (b) For the Blue system, open the access panel 195BB. (c) For the Yellow system, open the access panel 196BB.

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 233-233 4.

Procedure

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 233-233 EMB SB 31-1286 for A/C 201-201, 207-207, 210-210 (Ref. Fig. Location of the Pressure Transmitter) Subtask 29-30-00-040-053-A A.

Deactivation of the Hydraulic Pressure Transmitter (1) Disconnect the applicable electrical connector from the pressure transmitter of the related HP manifold. (2) Install the CAP - PROTECTION on the disconnected connector and on the receptacle. (3) Use the TIE WRAP and attach the cable to a part of the adjacent structure. (4) Make sure that oil or other liquids cannot go into the connector end.

Subtask 29-30-00-941-051-A B.

Put the warning notice in the flight compartment to tell the crew that the hydraulic pressure transmitter does not operate.

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 233-233 5.

Close-up

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 233-233 EMB SB 31-1286 for A/C 201-201, 207-207, 210-210 Subtask 29-30-00-410-060-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the related access doors: (a) For the Green system, close the main gear door (Ref. AMM TASK 32-12-00-410-001) . (b) For the Blue system, close the access panel 195BB. (c) For the Yellow system, close the access panel 196BB.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-30-00-040-802-A - Deactivation of the Pressure Transmitter

(3) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-31-00-040-001-A - Deactivation of the Reservoir Quantity Indication of the Green and Blue Hydraulic Systems on the ECAM

** ON A/C ALL TASK 29-31-00-040-001-A Deactivation of the Reservoir Quantity Indication of the Green and Blue Hydraulic Systems on the ECAM Task Summary MMEL or CDL Ref MMEL 29-07-05A

Access NO

Test YES

1.

Reason for the Job MMEL 29-07-05A Reservoir Quantity Indication on the HYD SD page

2

Job Set-up Information A.

QTY 2 AR AR

E/T 00.8

Nb Men 2

DESIGNATION CAP - PROTECTION SAFETY CLIP - CIRCUIT BREAKER TIE WRAP

Referenced Information REFERENCE (Ref. 12-12-29-611-001-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 29-10-00-680-001-A). (Ref. 29-10-00-680-003-A). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 32-12-00-010-001-A). (Ref. 32-12-00-410-001-A). Ref. TSM 29-11-00-810-803 Ref. TSM 29-12-00-810-803

3.

Mhr 00.7

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

Specific Tools NO

DESIGNATION Fill the Hydraulic Fluid Reservoir with a Hand Pump Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Drainage of the Reservoir of the Green Hydraulic System Drainage of the Reservoir of the Blue Hydraulic System EIS Start Procedure EIS Stop Procedure Open the Main Gear Doors for Access Close the Main Gear Doors after Access Loss of the Correct Quantity in the Green Hydraulic Reservoir Loss of the Correct Quantity in the Blue Hydraulic Reservoir

Job Set-up Subtask 29-31-00-010-050-A A.

Get Access (1) Open the access door for the reservoir it is necessary to deactivate (a) For the Green reservoir:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-31-00-040-001-A - Deactivation of the Reservoir Quantity Indication of the Green and Blue Hydraulic Systems on the ECAM · Open one main-gear main door (Ref. AMM TASK 32-12-00-010-001) NOTE: You can open one of the two doors, but access is good from the RH side. (b) For the Blue reservoir: · Open the access door 197FB. (2) Do the troubleshooting procedure to check if the fault of the quantity indicator is electrical or mechanical: · For the Green reservoir Ref. TSM 29-11-00-810-803 · For the Blue reservoir Ref. TSM 29-12-00-810-803 . Subtask 29-31-00-865-050-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU

4.

DESIGNATION HYDRAULIC/HYD/QTY/IND

FIN 1831GQ P35

LOCATION

Procedure Subtask 29-31-00-040-053-A A.

Deactivation of the Reservoir Quantity Indication of the Green and Blue Hydraulic Systems (1) Disconnect the applicable electrical connector 1000GQ-A or 2000GQ-A from the quantity transmitter of the related reservoir. (2) Install a CAP - PROTECTION in the connector and the receptacle. (3) Use a TIE WRAP and secure the cable to a part of the structure. NOTE: Attach the cable to the structure so that the disconnected end of the connector points down. Oil or other liquids can not then enter the connector.

Subtask 29-31-00-040-050-A B.

Electrical Failure of the Quantity Indicator (1) Examine the mechanical indicator on the applicable reservoir to check the quantity of the hydraulic fluid. Do this before each flight. (2) Do a check of the LO LVL ECAM warning. Do this check only before the first flight of the aircraft under this MMEL item. (a) Make sure that the aircraft configuration is: 1

For deactivation of the Green reservoir indication: · The landing gear extended with the landing gear doors closed (one main door of the main gear can be open) · The thrust reverser for the left engine is off (closed) · The speedbrakes and the spoilers are retracted · Green power accumulator empty of fluid and filled with nitrogen to the correct pressure.

2

For deactivation of the Blue reservoir indication: · The speedbrakes and the spoilers are retracted · Blue power accumulator empty of fluid and filled with nitrogen to the correct pressure.

3

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

4

Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-31-00-040-001-A - Deactivation of the Reservoir Quantity Indication of the Green and Blue Hydraulic Systems on the ECAM

5

Drain the applicable reservoir until the low level warning comes on (Ref. AMM TASK 29-1000-680-001) or (Ref. AMM TASK 29-10-00-680-003) . Keep the air pressure in the reservoir at more than 22 psig (1.5 bar relative) while you drain the reservoir.

6

Put fluid into the reservoir to fill it to its correct fill level (Ref. AMM TASK 12-12-29-611001) .

7

Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) .

8

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

9

Make an entry in the logbook.

Subtask 29-31-00-040-055-A C.

Mechanical Failure of the Quantity Indicator (1) Make sure that the aircraft configuration is: (a) For deactivation of the Green reservoir indication: · The landing gear extended with the landing gear doors closed (one main door of the main gear can be open) · The thrust reverser for the left engine is off (closed) · The speedbrakes and the spoilers are retracted · Green power accumulator empty of fluid and filled with nitrogen to the correct pressure. (b) For deactivation of the Blue reservoir indication: · The speedbrakes and the spoilers are retracted · Blue power accumulator empty of fluid and filled with nitrogen to the correct pressure. (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) . (4) Drain the applicable reservoir until the low level warning comes on (Ref. AMM TASK 29-10-00-680001) or (Ref. AMM TASK 29-10-00-680-003) . Keep the air pressure in the reservoir at more than 22 psig (1.5 bar relative) while you drain the reservoir. (5) Put fluid into the reservoir to fill it to its correct fill level (Ref. AMM TASK 12-12-29-611-001) . The quantity of fluid which is necessary to add is: · For the Green reservoir: 11 l (2.9 USgal) · For the Blue reservoir: 4 l (1.05 USgal). NOTE: These quantities are for fluid temperatures between 10 and 20 deg. C (50 and 68 deg. F). If the temperature is not in these limits, the quantity of fluid necessary changes by: - 0.5 l (0.13 USgal) for each 10 deg. C (18 deg. F) for the Green reservoir - 0.25 l (0.065 USgal) for each 10 deg. C (18 deg. F) for the Blue reservoir. (6) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (7) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (8) Make an entry in the logbook.

5.

Close-up Subtask 29-31-00-865-060-A A.

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

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-31-00-040-001-A - Deactivation of the Reservoir Quantity Indication of the Green and Blue Hydraulic Systems on the ECAM

PANEL 121VU

DESIGNATION HYDRAULIC/HYD/QTY/IND

FIN 1831GQ P35

LOCATION

Subtask 29-31-00-410-050-A B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access door as applicable: · 197FB or · the main door of the main gear (Ref. AMM TASK 32-12-00-410-001) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-31-00-040-002-A - Deactivation of the Reservoir Quantity Indication of the Yellow Hydraulic System on the ECAM

** ON A/C ALL TASK 29-31-00-040-002-A Deactivation of the Reservoir Quantity Indication of the Yellow Hydraulic System on the ECAM Task Summary MMEL or CDL Ref MMEL 29-07-05A

Access YES

Test NO

1.

Reason for the Job MMEL 29-07-05A Reservoir Quantity Indication on the HYD SD page

2

Job Set-up Information A.

Mhr 01.0

E/T 01.0

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

Specific Tools NO

QTY 2 AR AR

DESIGNATION CAP - PROTECTION SAFETY CLIP - CIRCUIT BREAKER TIE WRAP

Work Zones and Access Panels ZONE/ACCESS 196BB

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 12-12-29-611-001-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 29-10-00-680-002-A). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 32-12-00-010-001-A). (Ref. 32-12-00-410-001-A). Ref. TSM 29-13-00-810-801 3.

DESIGNATION Fill the Hydraulic Fluid Reservoir with a Hand Pump Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Drainage of the Reservoir of the Yellow Hydraulic System EIS Start Procedure EIS Stop Procedure Open the Main Gear Doors for Access Close the Main Gear Doors after Access Loss of the Correct Quantity in the Yellow Hydraulic Reservoir

Job Set-up Subtask 29-31-00-010-053-A A.

Get Access

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-31-00-040-002-A - Deactivation of the Reservoir Quantity Indication of the Yellow Hydraulic System on the ECAM

(1) Open the access door 196BB. (2) Open the RH main door of the main gear (Ref. AMM TASK 32-12-00-010-001) . (3) Do the troubleshooting procedure to check if the fault of the quantity indicator is electrical or mechanical Ref. TSM 29-13-00-810-801 . Subtask 29-31-00-865-054-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU

4.

DESIGNATION HYDRAULIC/HYD/QTY/IND

FIN 1831GQ P35

LOCATION

Procedure Subtask 29-31-00-040-054-A A.

Deactivation of the Reservoir Quantity Indication of the Yellow Hydraulic System (1) Release the transmitter cable from the two P-clips nearest to the reservoir end of the cable. (2) Put the P-clips back in position on their brackets after you have released the cable. (3) Disconnect the electrical connector 3000GQ-A from the quantity transmitter of the reservoir. (4) Install a CAP - PROTECTION in the connector and the receptacle. (5) Put the connector through the hole in the top of the rear wall (FR42) of the Yellow hydraulic compartment. (6) Use a TIE WRAP to attach the connector and the cable to the structure in the main gear compartment. NOTE: Attach the cable to the structure so that the disconnected end of the connector points down. Oil or other liquids can not then enter the connector.

Subtask 29-31-00-040-052-A B.

Electrical Failure of the Quantity Indicator (1) Examine the mechanical indicator on the reservoir to check the quantity of the hydraulic fluid. Do this before each flight. (2) Do a check of the LO LVL ECAM warning. Do this check only before the first flight of the aircraft under this MMEL item. (a) Make sure that the aircraft configuration is: · The thrust reverser for the right engine OFF (closed) · The speedbrakes and the spoilers retracted · Yellow power accumulator empty of fluid and filled with nitrogen to the correct pressure · Forward and aft cargo-compartment doors closed. 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

Drain the Yellow reservoir until the low level warning comes on (Ref. AMM TASK 29-10-00680-002) . Keep the air pressure in the reservoir at not less than 22 psig (1.5 bar relative) while you drain the fluid.

4

Put the fluid into the Yellow reservoir to fill it to its correct fill level (Ref. AMM TASK 12-1229-611-001) .

(3) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-31-00-040-002-A - Deactivation of the Reservoir Quantity Indication of the Yellow Hydraulic System on the ECAM

(4) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (5) Make an entry in the logbook. Subtask 29-31-00-040-056-A C.

Mechanical Failure of the Quantity Indicator (1) Make sure that the aircraft configuration is: · The thrust reverser for the right engine is off (closed) · The speedbrakes and the spoilers retracted · Yellow power accumulator empty of fluid and filled with nitrogen to the correct pressure · Forward and aft cargo-compartment doors closed. (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) . (4) Drain the Yellow reservoir until the low level warning comes on (Ref. AMM TASK 29-10-00-680002) . Keep the air pressure in the reservoir at not less than 22 psig (1.5 bar relative) while you drain the fluid. (5) Put the fluid into the Yellow reservoir to fill it to its correct fill level (Ref. AMM TASK 12-12-29-611001) . The quantity of fluid which it is necessary to add is: · With the brake accumulator empty of fluid but filled with nitrogen to the correct pressure: 12 l (3.2 USgal) · With the brake accumulator full of fluid at the system pressure of 206 bar (3000 psi): 9 l (2.4 USgal). NOTE: These quantities are for fluid temperatures between 10 and 20 deg. C (50 and 68 deg. F). If the temperature is not in these limits, the quantity of fluid necessary changes by 0.5 l (0.13 USgal) for each 10 deg. C (18 deg. F). (6) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (7) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (8) Make an entry in the logbook.

5.

Close-up Subtask 29-31-00-865-061-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU

DESIGNATION HYDRAULIC/HYD/QTY/IND

FIN 1831GQ P35

LOCATION

Subtask 29-31-00-410-054-A B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the RH main door of the main gear (Ref. AMM TASK 32-12-00-410-001) . (3) Close the access door 196BB.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-34-00-040-001-A - Deactivation of the Reservoir Air Pressure Switches and Check of the Reservoir Air Pressure of the Green and Yellow Hydraulic System

** ON A/C ALL TASK 29-34-00-040-001-A Deactivation of the Reservoir Air Pressure Switches and Check of the Reservoir Air Pressure of the Green and Yellow Hydraulic System

FIN : 1384GH , 2384GH , 3384GH Task Summary MMEL or CDL Ref MMEL 29-09-04A

Access NO

Test YES

1.

Reason for the Job MMEL 29-09-04A HYD G(B)(Y) RSVR LO AIR PR Alert

2

Job Set-up Information A.

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

Specific Tools NO

QTY 1 2 AR AR

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE CAP - PROTECTION SAFETY CLIP - CIRCUIT BREAKER TIE WRAP

Referenced Information REFERENCE (Ref. 29-14-00-614-002-A).

DESIGNATION Pressurization of the Hydraulic Reservoirs through the Ground Connector (Ref. 29-14-00-614-002-A-01). Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU) (Ref. 32-12-00-010-001-A). Open the Main Gear Doors for Access (Ref. 32-12-00-410-001-A). Close the Main Gear Doors after Access Reservoir Air Pressure Switches of the Green and Yellow Hydraulic System SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-34-00-040-001-A - Deactivation of the Reservoir Air Pressure Switches and Check of the Reservoir Air Pressure of the Green and Yellow Hydraulic System

A A

B

C

1384GH

Z147

FR43

196BB

FR42 1000GQ

C EXAMPLE 1384GH 3384GH

1 FR41

B

FR42

3384GH

C

3000GQ

N_MM_293400_4_AAM0_01_00

Figure 29-34-00-991-00100-00-A / SHEET 1/1 - Reservoir Air Pressure Switches of the Green and Yellow Hydraulic System ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-34-00-040-001-A - Deactivation of the Reservoir Air Pressure Switches and Check of the Reservoir Air Pressure of the Green and Yellow Hydraulic System

3.

Job Set-up Subtask 29-34-00-865-050-A A.

Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 1384GH (AIR PRESSURE SWITCH)

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU HYDRAULIC/G HYD/PUMP ENG1/ 1702GK R34 MONG ** ON A/C 401-450 121VU HYDRAULIC/G HYD/PUMP ENG1/ MONG

1702GK

R33

** ON A/C ALL FOR FIN 3384GH (AIR PRESSURE SWITCH) 121VU HYDRAULIC/Y HYD/PUMP ENG2/MONG 3700GD Q37 Subtask 29-34-00-010-050-A B.

Get Access (1) Open the applicable access door: · One main gear door for 1384GH (Ref. AMM TASK 32-12-00-010-001) . NOTE: Access is better from the Right Hand (RH) side. · 196BB and the RH main gear door for 3384GH (Ref. AMM TASK 32-12-00-010-001) . (2) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position to be satisfactory for the Green reservoir.

4.

Procedure Subtask 29-34-00-040-050-A A.

Deactivation of the Reservoir Air Pressure Switches (Ref. Fig. Reservoir Air Pressure Switches of the Green and Yellow Hydraulic System SHEET 1) (1) Disconnect the applicable electrical connector (1) 1384GH-A or 3384GH-A from the pressure switch. (2) Install a CAP - PROTECTION on the disconnected connector (1) and on the receptacle. (3) For the pressure switch 1384GH: · Use a TIE WRAP and attach the disconnected cable to a part of the structure. NOTE: Attach the cable to the structure so that the disconnected end of the connector points down. This prevents the contamination of the connector with oil or other liquids. (4) For the pressure switch 3384GH: (a) Put the disconnected connector and the end of the cable through the hole in FR42 into the main gear compartment. (b) Use a TIE WRAP and attach the disconnected cable to a part of the structure in the main gear compartment.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-34-00-040-001-A - Deactivation of the Reservoir Air Pressure Switches and Check of the Reservoir Air Pressure of the Green and Yellow Hydraulic System

NOTE: Attach the cable to the structure so that the disconnected end of the connector points down. This prevents the contamination of the connector with oil or other liquids. (5) Make an entry in the logbook. (6) Look on the air pressure gages on the applicable reservoir and make sure that the air pressure is not less than 37 psi. (7) If necessary, pressurize the reservoir (Ref. AMM TASK 29-14-00-614-002) . 5.

Close-up Subtask 29-34-00-410-050-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the access platform. (3) Close the applicable access door(s) · 196BB and the RH main gear door (Ref. AMM TASK 32-12-00-410-001) · The main gear door (Ref. AMM TASK 32-12-00-410-001) .

Subtask 29-34-00-865-070-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 1384GH (AIR PRESSURE SWITCH)

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU HYDRAULIC/G HYD/PUMP ENG1/ 1702GK R34 MONG ** ON A/C 401-450 121VU HYDRAULIC/G HYD/PUMP ENG1/ MONG

1702GK

R33

** ON A/C ALL FOR FIN 3384GH (AIR PRESSURE SWITCH) 121VU HYDRAULIC/Y HYD/PUMP ENG2/MONG 3700GD Q37

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-34-00-040-002-A - Deactivation of the Reservoir Air Pressure Switch and Check of the Reservoir Air Pressure of the Blue Hydraulic System

** ON A/C ALL TASK 29-34-00-040-002-A Deactivation of the Reservoir Air Pressure Switch and Check of the Reservoir Air Pressure of the Blue Hydraulic System

FIN : 2384GH Task Summary MMEL or CDL Ref MMEL 29-09-04A

Access YES

Test NO

1.

Reason for the Job MMEL 29-09-04A HYD G(B)(Y) RSVR LO AIR PR Alert

2

Job Set-up Information A.

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

Specific Tools NO

QTY 1 2 AR AR

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE CAP - PROTECTION SAFETY CLIP - CIRCUIT BREAKER TIE WRAP

Work Zones and Access Panels ZONE/ACCESS 197FB

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 29-14-00-614-002-A).

DESIGNATION Pressurization of the Hydraulic Reservoirs through the Ground Connector (Ref. 29-14-00-614-002-A-01). Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU) Reservoir Air Pressure Switch of the Blue Hydraulic System SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-34-00-040-002-A - Deactivation of the Reservoir Air Pressure Switch and Check of the Reservoir Air Pressure of the Blue Hydraulic System

A FR50

A FR49 197FB

B

2000GQ

B

2384GH

1

N_MM_293400_4_ACM0_01_00

Figure 29-34-00-991-00200-00-A / SHEET 1/1 - Reservoir Air Pressure Switch of the Blue Hydraulic System ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-34-00-040-002-A - Deactivation of the Reservoir Air Pressure Switch and Check of the Reservoir Air Pressure of the Blue Hydraulic System

3.

Job Set-up Subtask 29-34-00-865-064-A A.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU

DESIGNATION HYD/HYD PWR/B WARN/& CTL

FIN 2702GJ

LOCATION C12

Subtask 29-34-00-010-053-A B.

Get Access (1) Open the access door 197FB. (2) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position to be satisfactory for the Blue reservoir.

4.

Procedure Subtask 29-34-00-040-051-A A.

Deactivation of the Reservoir Air Pressure Switch (Ref. Fig. Reservoir Air Pressure Switch of the Blue Hydraulic System SHEET 1) (1) Disconnect the electrical connector (1) 2384GH-A from the pressure switch. (2) Install a CAP - PROTECTION on the disconnected connector (1) and on the receptacle. (3) Use a TIE WRAP and attach the disconnected cable to a part of the structure. NOTE: Attach the cable to the structure so that the disconnected end of the connector points down. This prevents the contamination of the connector with oil or other liquids. (4) Make an entry in the logbook. (5) Look on the air pressure gages of the reservoir and make sure that the air pressure is not less than 37 psi. (6) If necessary, pressurize the reservoir (Ref. AMM TASK 29-14-00-614-002) .

5.

Close-up Subtask 29-34-00-410-053-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the access platform. (3) Close the access door 197FB.

Subtask 29-34-00-865-068-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU

DESIGNATION HYD/HYD PWR/B WARN/& CTL

FIN 2702GJ

LOCATION C12

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-001-A - Deactivation of the Case Drain Filter of the Engine Driven Pump of the Green Hydraulic System

** ON A/C ALL TASK 29-10-00-040-001-A Deactivation of the Case Drain Filter of the Engine Driven Pump of the Green Hydraulic System

FIN : 1084GM Task Summary MMEL or CDL Ref MMEL 29-10-09A

Access NO

1.

Reason for the Job MMEL 29-10-09A Hydraulic Case Drain Filter

2

Job Set-up Information A.

Specific Tools NO

Mhr 00.7

E/T 00.7

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Test YES

QTY DESIGNATION 1 CONTAINER 2 L (0.53 USGAL) 1 WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. 02ABA1) No specific

DESIGNATION Phosphate Ester Hydraulic Fluid-General Power - lockwire, corrosion-resistant steel, dia. 0.8 mm (0.032 in.)

C. Referenced Information REFERENCE (Ref. 12-12-29-611-001-A). (Ref. 12-12-29-611-002-A). (Ref. 29-00-00-864-001-A). (Ref. 29-00-00-910-002-A). (Ref. 29-14-00-614-001-A). (Ref. 29-14-00-614-002-A). (Ref. 29-14-00-614-002-A-01). (Ref. 29-23-00-860-001-A). (Ref. 29-23-00-860-002-A).

DESIGNATION Fill the Hydraulic Fluid Reservoir with a Hand Pump Fill the Hydraulic Fluid Reservoir with a Hydraulic Service Cart Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action Safety Procedures of the Hydraulic System Depressurization of the Hydraulic Reservoirs Pressurization of the Hydraulic Reservoirs through the Ground Connector Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU) Disconnection of the Isolation Coupling of the Power Transfer Unit (PTU) Connection of the Isolation Coupling of the Power Transfer Unit (PTU)

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 71-00-00-710-001-B). Dry Motoring Check

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-001-A - Deactivation of the Case Drain Filter of the Engine Driven Pump of the Green Hydraulic System REFERENCE

DESIGNATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 71-00-00-710-045-A). Test No.1 : Dry Motor Leak Check (Ref. 71-13-00-010-010-A). Opening of the Fan Cowls 437AL(447AL),438AR(448AR) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 71-13-00-010-040-B). Opening of the Fan Cowl Doors ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 71-13-00-410-010-A). Closing of the Fan Cowls 437AL(447AL),438AR(448AR) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 71-13-00-410-040-B). Closing of the Fan Cowl Doors ** ON A/C ALL ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241, 301-349, 351-450, 500-600 Case Drain Filters of the Engine Driven Pumps SHEET 1 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Case Drain Filters of the Engine Driven Pumps SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-001-A - Deactivation of the Case Drain Filter of the Engine Driven Pump of the Green Hydraulic System

A

A

Z400

A Z400

CASE DRAIN FILTER 1084GM/3084GM

1

B 4

B CLOGGING INDICATOR

3 2

N_MM_291000_4_AAM0_01_00

Figure 29-10-00-991-00200-00-A / SHEET 1/1 - Case Drain Filters of the Engine Driven Pumps ** ON A/C 207-207, 210-210, 212-214, 217-218, 223226, 234-234, 236-236, 241-241, 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-001-A - Deactivation of the Case Drain Filter of the Engine Driven Pump of the Green Hydraulic System

A A

Z400

A Z400

B CASE DRAIN FILTER 1084GM/3084GM

B 1

C 4

C CLOGGING INDICATOR

3 2

N_MM_291000_4_AAP0_01_00

Figure 29-10-00-991-00200-00-B / SHEET 1/1 - Case Drain Filters of the Engine Driven Pumps ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-001-A - Deactivation of the Case Drain Filter of the Engine Driven Pump of the Green Hydraulic System

3.

Job Set-up Subtask 29-10-00-860-083-A A.

Aircraft Maintenance Configuration WARNING: OBEY THE HYDRAULIC SAFETY PROCEDURES. (1) Obey the hydraulic safety procedures (Ref. AMM TASK 29-00-00-910-002) . (2) Put the WARNING NOTICE(S) in position to tell persons not to pressurize the Green hydraulic system: · In the cockpit on the hydraulic section 40VU of the overhead panel · On the ground service panel of the Green hydraulic system. (3) Make sure that the Green hydraulic system is depressurized and put it in the maintenance configuration. (Ref. AMM TASK 29-00-00-864-001) . (4) Disconnect the isolation coupling of the Power Transfer Unit (PTU) (Ref. AMM TASK 29-23-00-860001) . (5) Depressurize the reservoir of the Green hydraulic system (Ref. AMM TASK 29-14-00-614-001) .

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241, 301-349, 351-450, 500-600 Subtask 29-10-00-010-057-A B.

Open the left fan cowl door of the left (No. 1) engine (Ref. AMM TASK 71-13-00-010-040) .

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 Subtask 29-10-00-010-057-C B.

Open the left fan cowl door of the left (No. 1) engine (Ref. AMM TASK 71-13-00-010-010) .

** ON A/C ALL Subtask 29-10-00-941-050-A C. 4.

Put a CONTAINER 2 L (0.53 USGAL) in position under the filter to collect the hydraulic fluid.

Procedure

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241, 301-349, 351-450, 500-600 (Ref. Fig. Case Drain Filters of the Engine Driven Pumps SHEET 1) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 (Ref. Fig. Case Drain Filters of the Engine Driven Pumps SHEET 1) ** ON A/C ALL Subtask 29-10-00-040-050-A A.

Deactivation of the Case Drain Filter (1084GM) (1) Remove and discard the lockwire between the filter bowl (3) and the filter head (1). (2) Remove the filter bowl (3) together with the filter element (2). NOTE: You will possibly have to pull the filter element (2) to release it from the filter head (1). (3) Discard the filter element (2).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-001-A - Deactivation of the Case Drain Filter of the Engine Driven Pump of the Green Hydraulic System

(4) Clean the filter bowl (3) and apply Phosphate Ester Hydraulic Fluid-General Power - (Material No. 02ABA1) to its threads. (5) Install the filter bowl (3) in the filter head (1) and tighten it with your hands. (6) Safety the filter bowl (3) to the filter head (1) with lockwire, corrosion-resistant steel, dia. 0.8 mm (0.032 in.) . (7) If the red clogging indicator is out, push it in to set it again. Subtask 29-10-00-860-084-A B.

Preparation for the Test (1) Make sure that the content of the reservoir of the Green hydraulic system is correct. Add fluid as necessary (Ref. AMM TASK 12-12-29-611-001) or (Ref. AMM TASK 12-12-29-611-002) . (2) Pressurize the reservoir of the Green hydraulic system (Ref. AMM TASK 29-14-00-614-002) . (3) Remove the WARNING NOTICE(S). (4) Remove the container.

** ON A/C 301-349, 351-450, 500-600 Subtask 29-10-00-710-051-A C.

Test (1) Dry-motor the left (No. 1) engine (Ref. AMM TASK 71-00-00-710-001) . (2) Make sure that there are no hydraulic leaks from the filter assembly, and that the clogging indicator stays in. (3) If the clogging indicator comes out, push it in to set it again. If it will not stay in, do the troubleshooting of the filter assembly to find the cause. (4) Stop the operation of the left (No. 1) engine (Ref. AMM TASK 71-00-00-710-001) .

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Subtask 29-10-00-710-051-B C.

Test (1) Dry-motor the left (No. 1) engine (Ref. AMM TASK 71-00-00-710-001) . (2) Make sure that there are no hydraulic leaks from the filter assembly, and that the clogging indicator stays in. (3) If the clogging indicator comes out, push it in to set it again. If it will not stay in, do the troubleshooting of the filter assembly to find the cause. (4) Stop the operation of the left (No. 1) engine (Ref. AMM TASK 71-00-00-710-001) .

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 Subtask 29-10-00-710-051-C C.

Test (1) Dry-motor the left (No. 1) engine (Ref. AMM TASK 71-00-00-710-045) . (2) Make sure that there are no hydraulic leaks from the filter assembly, and that the clogging indicator stays in. (3) If the clogging indicator comes out, push it in to set it again. If it will not stay in, do the troubleshooting of the filter assembly to find the cause.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-001-A - Deactivation of the Case Drain Filter of the Engine Driven Pump of the Green Hydraulic System

(4) Stop the operation of the left (No. 1) engine (Ref. AMM TASK 71-00-00-710-045) . ** ON A/C ALL 5.

Close-up

** ON A/C 301-349, 351-450, 500-600 Subtask 29-10-00-410-057-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the left fan cowl door of the left (No. 1) engine (Ref. AMM TASK 71-13-00-410-040) . (3) Connect the isolation coupling of the Power Transfer Unit (PTU) (Ref. AMM TASK 29-23-00-860002) .

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Subtask 29-10-00-410-057-B A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the left fan cowl door of the left (No. 1) engine (Ref. AMM TASK 71-13-00-410-040) . (3) Connect the isolation coupling of the Power Transfer Unit (PTU) (Ref. AMM TASK 29-23-00-860002) .

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 Subtask 29-10-00-410-057-C A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the left fan cowl door of the left (No. 1) engine (Ref. AMM TASK 71-13-00-410-010) . (3) Connect the isolation coupling of the Power Transfer Unit (PTU) (Ref. AMM TASK 29-23-00-860002) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-002-A - Deactivation of the Case Drain Filter of the Engine Driven Pump of the Yellow Hydraulic System

** ON A/C ALL TASK 29-10-00-040-002-A Deactivation of the Case Drain Filter of the Engine Driven Pump of the Yellow Hydraulic System

FIN : 3084GM Task Summary MMEL or CDL Ref MMEL 29-10-09A

Access NO

1.

Reason for the Job MMEL 29-10-09A Hydraulic Case Drain Filter

2

Job Set-up Information A.

Specific Tools NO

Mhr 01.5

E/T 01.5

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Test NO

QTY DESIGNATION 1 CONTAINER 2 L (0.53 USGAL) 1 WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. 02ABA1) No specific

DESIGNATION Phosphate Ester Hydraulic Fluid-General Power - lockwire, corrosion-resistant steel, dia. 0.8 mm (0.032 in.)

C. Referenced Information REFERENCE (Ref. 12-12-29-611-001-A). (Ref. 12-12-29-611-002-A). (Ref. 29-00-00-864-001-A). (Ref. 29-00-00-910-002-A). (Ref. 29-14-00-614-001-A). (Ref. 29-14-00-614-002-A). (Ref. 29-14-00-614-002-A-01). (Ref. 29-23-00-860-001-A). (Ref. 29-23-00-860-002-A).

DESIGNATION Fill the Hydraulic Fluid Reservoir with a Hand Pump Fill the Hydraulic Fluid Reservoir with a Hydraulic Service Cart Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action Safety Procedures of the Hydraulic System Depressurization of the Hydraulic Reservoirs Pressurization of the Hydraulic Reservoirs through the Ground Connector Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU) Disconnection of the Isolation Coupling of the Power Transfer Unit (PTU) Connection of the Isolation Coupling of the Power Transfer Unit (PTU)

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 71-00-00-710-001-B). Dry Motoring Check

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-002-A - Deactivation of the Case Drain Filter of the Engine Driven Pump of the Yellow Hydraulic System REFERENCE

DESIGNATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 71-00-00-710-045-A). Test No.1 : Dry Motor Leak Check (Ref. 71-13-00-010-010-A). Opening of the Fan Cowls 437AL(447AL),438AR(448AR) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 71-13-00-010-040-B). Opening of the Fan Cowl Doors ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 71-13-00-410-010-A). Closing of the Fan Cowls 437AL(447AL),438AR(448AR) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 71-13-00-410-040-B). Closing of the Fan Cowl Doors ** ON A/C ALL ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241, 301-349, 351-450, 500-600 Case Drain Filters of the Engine Driven Pumps SHEET 1 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Case Drain Filters of the Engine Driven Pumps SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-002-A - Deactivation of the Case Drain Filter of the Engine Driven Pump of the Yellow Hydraulic System

A

A

Z400

A Z400

CASE DRAIN FILTER 1084GM/3084GM

1

B 4

B CLOGGING INDICATOR

3 2

N_MM_291000_4_AAM0_01_00

Figure 29-10-00-991-00200-00-A / SHEET 1/1 - Case Drain Filters of the Engine Driven Pumps ** ON A/C 207-207, 210-210, 212-214, 217-218, 223226, 234-234, 236-236, 241-241, 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-002-A - Deactivation of the Case Drain Filter of the Engine Driven Pump of the Yellow Hydraulic System

A A

Z400

A Z400

B CASE DRAIN FILTER 1084GM/3084GM

B 1

C 4

C CLOGGING INDICATOR

3 2

N_MM_291000_4_AAP0_01_00

Figure 29-10-00-991-00200-00-B / SHEET 1/1 - Case Drain Filters of the Engine Driven Pumps ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-002-A - Deactivation of the Case Drain Filter of the Engine Driven Pump of the Yellow Hydraulic System

3.

Job Set-up Subtask 29-10-00-860-087-A A.

Aircraft Maintenance Configuration WARNING: OBEY THE HYDRAULIC SAFETY PROCEDURES. (1) Obey the hydraulic safety procedures (Ref. AMM TASK 29-00-00-910-002) . (2) Put the WARNING NOTICE(S) in position to tell persons not to pressurize the Yellow hydraulic system: · In the cockpit on the hydraulic section 40VU of the overhead panel · On the ground service panel of the Yellow hydraulic system. (3) Make sure that the Yellow hydraulic system is depressurized and put it in the maintenance configuration. (Ref. AMM TASK 29-00-00-864-001) . (4) Disconnect the isolation coupling of the Power Transfer Unit (PTU) (Ref. AMM TASK 29-23-00-860001) . (5) Depressurize the reservoir of the Yellow hydraulic system (Ref. AMM TASK 29-14-00-614-001) .

** ON A/C 301-349, 351-450, 500-600 Subtask 29-10-00-010-059-A B.

Open the left fan cowl door of the right (No. 2) engine (Ref. AMM TASK 71-13-00-010-040) .

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Subtask 29-10-00-010-059-B B.

Open the left fan cowl door of the right (No. 2) engine (Ref. AMM TASK 71-13-00-010-040) .

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 Subtask 29-10-00-010-059-C B.

Open the left fan cowl door of the right (No. 2) engine (Ref. AMM TASK 71-13-00-010-010) .

** ON A/C ALL Subtask 29-10-00-941-052-A C. 4.

Put a CONTAINER 2 L (0.53 USGAL) in position under the filter to collect the hydraulic fluid.

Procedure

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241, 301-349, 351-450, 500-600 (Ref. Fig. Case Drain Filters of the Engine Driven Pumps SHEET 1) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 (Ref. Fig. Case Drain Filters of the Engine Driven Pumps SHEET 1) ** ON A/C ALL Subtask 29-10-00-040-051-A A.

Deactivation of the Case Drain Filter (3084GM) (1) Remove and discard the lockwire between the filter bowl (3) and the filter head (1).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-002-A - Deactivation of the Case Drain Filter of the Engine Driven Pump of the Yellow Hydraulic System

(2) Remove the filter bowl (3) together with the filter element (2). NOTE: You will possibly have to pull the filter element (2) to release it from the filter head (1). (3) Discard the filter element (2). (4) Clean the filter bowl (3) and apply Phosphate Ester Hydraulic Fluid-General Power - (Material No. 02ABA1) to its threads. (5) Install the filter bowl (3) in the filter head (1) and tighten it with your hands. (6) Safety the filter bowl (3) to the filter head (1) with lockwire, corrosion-resistant steel, dia. 0.8 mm (0.032 in.) . (7) If the red clogging indicator is out, push it in to set it again. Subtask 29-10-00-860-088-A B.

Preparation for the Test (1) Make sure that the content of the reservoir of the Yellow hydraulic system is correct. Add fluid as necessary (Ref. AMM TASK 12-12-29-611-001) or (Ref. AMM TASK 12-12-29-611-002) . (2) Pressurize the reservoir of the Yellow hydraulic system (Ref. AMM TASK 29-14-00-614-002) . (3) Remove the WARNING NOTICE(S). (4) Remove the container.

** ON A/C 301-349, 351-450, 500-600 Subtask 29-10-00-710-053-A C.

Test (1) Dry-motor the right (No. 2) engine (Ref. AMM TASK 71-00-00-710-001) . (2) Make sure that there are no hydraulic leaks from the filter assembly, and that the clogging indicator stays in. (3) If the clogging indicator comes out, push it in to set it again. If it will not stay in, do the troubleshooting of the filter assembly to find the cause. (4) Stop the operation of the right (No. 2) engine (Ref. AMM TASK 71-00-00-710-001) .

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Subtask 29-10-00-710-053-B C.

Test (1) Dry-motor the right (No. 2) engine (Ref. AMM TASK 71-00-00-710-001) . (2) Make sure that there are no hydraulic leaks from the filter assembly, and that the clogging indicator stays in. (3) If the clogging indicator comes out, push it in to set it again. If it will not stay in, do the troubleshooting of the filter assembly to find the cause. (4) Stop the operation of the right (No. 2) engine (Ref. AMM TASK 71-00-00-710-001) .

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 Subtask 29-10-00-710-053-C C.

Test (1) Dry-motor the right (No. 2) engine (Ref. AMM TASK 71-00-00-710-045) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-002-A - Deactivation of the Case Drain Filter of the Engine Driven Pump of the Yellow Hydraulic System

(2) Make sure that there are no hydraulic leaks from the filter assembly, and that the clogging indicator stays in. (3) If the clogging indicator comes out, push it in to set it again. If it will not stay in, do the troubleshooting of the filter assembly to find the cause. (4) Stop the operation of the right (No. 2) engine (Ref. AMM TASK 71-00-00-710-045) . ** ON A/C ALL 5.

Close-up

** ON A/C 301-349, 351-450, 500-600 Subtask 29-10-00-410-059-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the left fan cowl door of the right (No. 2) engine (Ref. AMM TASK 71-13-00-410-040) . (3) Connect the isolation coupling of the Power Transfer Unit (PTU) (Ref. AMM TASK 29-23-00-860002) .

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Subtask 29-10-00-410-059-B A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the left fan cowl door of the right (No. 2) engine (Ref. AMM TASK 71-13-00-410-040) . (3) Connect the isolation coupling of the Power Transfer Unit (PTU) (Ref. AMM TASK 29-23-00-860002) .

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 Subtask 29-10-00-410-059-C A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the left fan cowl door of the right (No. 2) engine (Ref. AMM TASK 71-13-00-410-010) . (3) Connect the isolation coupling of the Power Transfer Unit (PTU) (Ref. AMM TASK 29-23-00-860002) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-003-A - Deactivation of the Case Drain Filter of the Electric Pump of the Blue Hydraulic System

** ON A/C ALL TASK 29-10-00-040-003-A Deactivation of the Case Drain Filter of the Electric Pump of the Blue Hydraulic System

FIN : 2084GM Task Summary MMEL or CDL Ref MMEL 29-10-09A

Access YES

1.

Reason for the Job MMEL 29-10-09A Hydraulic Case Drain Filter

2

Job Set-up Information A.

Specific Tools NO

Mhr 01.3

E/T 01.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Test NO

QTY DESIGNATION 1 CONTAINER 2 L (0.53 USGAL) 2 WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. 02ABA1) No specific

DESIGNATION Phosphate Ester Hydraulic Fluid-General Power - lockwire, corrosion-resistant steel, dia. 0.8 mm (0.032 in.)

C. Work Zones and Access Panels ZONE/ACCESS 195BB

ZONE DESCRIPTION

D. Referenced Information REFERENCE (Ref. 12-12-29-611-001-A). (Ref. 12-12-29-611-002-A). (Ref. 29-00-00-864-001-A). (Ref. 29-00-00-910-002-A). (Ref. 29-10-00-863-003-A). (Ref. 29-10-00-863-003-A-01). (Ref. 29-10-00-864-003-A). (Ref. 29-14-00-614-001-A). (Ref. 29-14-00-614-002-A).

DESIGNATION Fill the Hydraulic Fluid Reservoir with a Hand Pump Fill the Hydraulic Fluid Reservoir with a Hydraulic Service Cart Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action Safety Procedures of the Hydraulic System Pressurize the Blue Hydraulic System with a Hydraulic Ground PowerCart Pressurize the Blue Hydraulic System with the Blue Electric Pump Depressurize the Blue Hydraulic System Depressurization of the Hydraulic Reservoirs Pressurization of the Hydraulic Reservoirs through the Ground Connector

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-003-A - Deactivation of the Case Drain Filter of the Electric Pump of the Blue Hydraulic System REFERENCE (Ref. 29-14-00-614-002-A-01).

DESIGNATION Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU) Case Drain Filter of the Electric Pump of the Blue Hydraulic System SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-003-A - Deactivation of the Case Drain Filter of the Electric Pump of the Blue Hydraulic System

FR41 FR42

A

A

Z195

195BB

CLOGGING INDICATOR

B

B

1

3

C

C

4

2

N_MM_291000_4_ACM0_01_00

Figure 29-10-00-991-00300-00-A / SHEET 1/1 - Case Drain Filter of the Electric Pump of the Blue Hydraulic System ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-003-A - Deactivation of the Case Drain Filter of the Electric Pump of the Blue Hydraulic System

3.

Job Set-up Subtask 29-10-00-860-091-A A.

Aircraft Maintenance Configuration WARNING: OBEY THE HYDRAULIC SAFETY PROCEDURES. (1) Obey the hydraulic safety procedures (Ref. AMM TASK 29-00-00-910-002) . (2) Put the WARNING NOTICE(S) in position to tell persons not to pressurize the Blue hydraulic system: · in the cockpit on the hydraulic section 40VU of the overhead panel, · on the ground service panel of the Blue hydraulic system. (3) Make sure that the Blue hydraulic system is depressurized and put it in the maintenance configuration. (Ref. AMM TASK 29-00-00-864-001) . (4) Depressurize the reservoir of the Blue hydraulic system (Ref. AMM TASK 29-14-00-614-001) .

Subtask 29-10-00-010-061-A B.

Open the access door 195BB.

Subtask 29-10-00-941-054-A C. 4.

Put a CONTAINER 2 L (0.53 USGAL) in position under the filter to collect the hydraulic fluid.

Procedure (Ref. Fig. Case Drain Filter of the Electric Pump of the Blue Hydraulic System SHEET 1) Subtask 29-10-00-040-052-A A.

Deactivation of the Case Drain Filter (2084GM) 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. (1) Remove and discard the lockwire between the filter bowl (3) and the filter head (1). (2) Remove the filter bowl (3) together with the filter element (2). NOTE: You may have to pull the filter element (2) to release it from the filter head (1). (3) Discard the filter element (2). (4) Clean the filter bowl (3) and apply Phosphate Ester Hydraulic Fluid-General Power - (Material No. 02ABA1) to its threads. (5) Install the filter bowl (3) in the filter head (1) and tighten it with your hands. 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. (6) Safety the filter bowl (3) to the filter head (1) with lockwire, corrosion-resistant steel, dia. 0.8 mm (0.032 in.) . (7) If the red clogging indicator is out, push it in to set it again.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-003-A - Deactivation of the Case Drain Filter of the Electric Pump of the Blue Hydraulic System

Subtask 29-10-00-860-092-A B.

Preparation for the Test (1) Make sure that the content of the reservoir of the Blue hydraulic system is correct. Add fluid as necessary (Ref. AMM TASK 12-12-29-611-001) or (Ref. AMM TASK 12-12-29-611-002) . (2) Pressurize the reservoir of the Blue hydraulic system (Ref. AMM TASK 29-14-00-614-002) . (3) Remove the WARNING NOTICE(S). (4) Remove the container.

Subtask 29-10-00-790-050-A C.

Test (1) Pressurize (with the electric pump) the Blue hydraulic system (Ref. AMM TASK 29-10-00-863-003) . (2) Make sure there are no leaks from the filter assembly, and that the clogging indicator stays in. (3) If the clogging indicator comes out, push it in to set it again. If it will not stay in, do the troubleshooting of the filter assembly to find the cause. (4) Depressurize the Blue hydraulic system (Ref. AMM TASK 29-10-00-864-003) .

5.

Close-up Subtask 29-10-00-410-061-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access door 195BB.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-004-A - Deactivation of the Green Power Accumulator

** ON A/C ALL TASK 29-10-00-040-004-A Deactivation of the Green Power Accumulator WARNING:

MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

FIN : 1070GM Task Summary MMEL or CDL Ref MMEL 29-10-04A

Access NO

1.

Reason for the Job MMEL 29-10-04A Hydraulic System Accumulator

2

Job Set-up Information A.

Specific Tools NO

Mhr 01.5

E/T 01.5

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific OR No specific No specific No specific No specific No specific

B.

Test NO

QTY 1 AR AR

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE CAP - BLANKING CAP - BLANKING (ABS0946V12 TYPE) OR AR CAP - BLANKING (MS21914-12 TYPE) 1 CONTAINER 5 L (1.32 USGAL) AR SAFETY CLIP - CIRCUIT BREAKER 1 WARNING NOTICE(S) Torque wrench: range to between 8.5 and 9.5 m.daN (62.68 and 70.06 lbf.ft)

Consumable Materials REFERENCE (Material No. 02ABA1)

DESIGNATION Phosphate Ester Hydraulic Fluid-General Power - -

C. Referenced Information REFERENCE (Ref. 12-12-29-611-001-A). (Ref. 29-00-00-864-001-A). (Ref. 29-00-00-870-003-A). (Ref. 29-00-00-910-002-A).

DESIGNATION Fill the Hydraulic Fluid Reservoir with a Hand Pump Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action Bleeding Procedure of the Green Hydraulic System Downstream of the Engine Pump Safety Procedures of the Hydraulic System

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-004-A - Deactivation of the Green Power Accumulator

REFERENCE (Ref. 29-10-00-863-001-A).

DESIGNATION Pressurize the Green Hydraulic System with a Hydraulic Ground Power-Cart (Ref. 29-10-00-864-001-A). Depressurize the Green Hydraulic System (Ref. 29-14-00-614-001-A). Depressurization of the Hydraulic Reservoirs (Ref. 29-14-00-614-002-A). Pressurization of the Hydraulic Reservoirs through the Ground Connector (Ref. 29-14-00-614-002-A-01). Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU) (Ref. 29-23-00-860-001-A). Disconnection of the Isolation Coupling of the Power Transfer Unit (PTU) (Ref. 29-23-00-860-002-A). Connection of the Isolation Coupling of the Power Transfer Unit (PTU) (Ref. 29-23-00-863-001-A). Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump (Ref. 32-12-00-010-001-A). Open the Main Gear Doors for Access (Ref. 32-12-00-410-001-A). Close the Main Gear Doors after Access Green Power Accumulator (1070GM) SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-004-A - Deactivation of the Green Power Accumulator

FR45

A FR44

A FR43

B

1070GM Z147

C 1111GM

13

12

C 9

B

11

1

2

10 3 4 5

8

7

6

N_MM_291000_4_AEU0_01_00

Figure 29-10-00-991-01100-00-B / SHEET 1/1 - Green Power Accumulator (1070GM) ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-004-A - Deactivation of the Green Power Accumulator

3.

Job Set-up Subtask 29-10-00-865-083-A A.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU HYDRAULIC/HYD POWER/Y 3803GX N30 ** ON A/C 401-450 121VU HYDRAULIC/HYD POWER/Y

3803GX

N31

** ON A/C ALL 123VU 123VU

3802GX 3801GX

AB06 AB03

Y HYD/ELEC/PUMP Y HYD/ELEC/ELEC PUMP/NORM

Subtask 29-10-00-860-101-A B.

Aircraft Maintenance Configuration WARNING: OBEY THE HYDRAULIC SAFETY PROCEDURES. (1) Obey the hydraulic safety procedures (Ref. AMM TASK 29-00-00-910-002) . (2) Put the WARNING NOTICE(S) in position to tell persons not to pressurize the Green hydraulic system: · in the cockpit on the hydraulic section 40VU of the overhead panel · on the ground service panel of the Green hydraulic system. (3) Open the left main-gear door (Ref. AMM TASK 32-12-00-010-001) . (4) Make sure that the Green hydraulic system is depressurized and put it in the maintenance configuration. (Ref. AMM TASK 29-00-00-864-001) (5) Depressurize the reservoir of the Green hydraulic system (Ref. AMM TASK 29-14-00-614-001) (6) Disconnect the isolation coupling of the Power Transfer Unit (PTU) (Ref. AMM TASK 29-23-00-860001) . (7) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position. (8) Put a CONTAINER 5 L (1.32 USGAL) below the power accumulator to collect the unwanted hydraulic fluid.

4.

Procedure (Ref. Fig. Green Power Accumulator (1070GM) SHEET 1) Subtask 29-10-00-614-050-B A.

Release the nitrogen pressure from the power accumulator (8) as follows: (1) Remove the end cap (9) from the charging valve. (2) Turn the nut (10) to release the nitrogen pressure. (3) When the nitrogen pressure is fully released turn the nut (10) to close the charging valve. (4) Install the end cap (9) on the charging valve.

Subtask 29-10-00-020-056-B

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-004-A - Deactivation of the Green Power Accumulator

B.

Removal of the Hydraulic Pipe CAUTION:

USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT HYDRAULIC LINES ON UNIONS. IF YOU DO NOT USE THE SECOND WRENCH, THERE IS A RISK THAT YOU WILL LOOSEN OR TIGHTEN THE UNION TOO MUCH.

(1) Disconnect the line end fitting (1) from the union (3) of the HP-manifold (2). (2) Disconnect the line end fitting (6) from the union (7) of the power accumulator (8). (3) Remove the nut (12), the bolt (13) and the pipe (4) with the clamp (5). (4) Install the CAP - BLANKING on the line end fittings (1) and (6) of the removed pipe (4). Subtask 29-10-00-420-053-B C.

Installation of the Blanking Caps CAUTION:

USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT HYDRAULIC LINES ON UNIONS. IF YOU DO NOT USE THE SECOND WRENCH, THERE IS A RISK THAT YOU WILL LOOSEN OR TIGHTEN THE UNION TOO MUCH.

(1) Apply the Phosphate Ester Hydraulic Fluid-General Power - - (Material No. 02ABA1) to the threads of the unions (3) and (7). (2) Install the CAP - BLANKING (ABS0946V12 TYPE) or CAP - BLANKING (MS21914-12 TYPE) on the unions (3) and (7). (3) TORQUE the blanking caps to between 8.5 and 9.5 m.daN (62.68 and 70.06 lbf.ft). Subtask 29-10-00-865-084-A D.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU HYDRAULIC/HYD POWER/Y 3803GX N30 ** ON A/C 401-450 121VU HYDRAULIC/HYD POWER/Y

3803GX

N31

** ON A/C ALL 123VU 123VU

3802GX 3801GX

AB06 AB03

Y HYD/ELEC/PUMP Y HYD/ELEC/ELEC PUMP/NORM

Subtask 29-10-00-790-053-A E.

Leak Test WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. (1) Pressurize the Green reservoir (Ref. AMM TASK 29-14-00-614-002) . (2) Pressurize the Green hydraulic system (Ref. AMM TASK 29-10-00-863-001) or (Ref. AMM TASK 29-23-00-863-001) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-004-A - Deactivation of the Green Power Accumulator

(3) After 5 minutes, examine the connection of the blanking cap to the union (3) of the HP-manifold (2). Make sure that there is no leakage. (4) Depressurize the Green hydraulic system (Ref. AMM TASK 29-10-00-864-001) . (5) Do the bleeding procedure of the Green hydraulic system downstream of the engine pump (Ref. AMM TASK 29-00-00-870-003) . NOTE: When you do the bleeding procedure, nitrogen, which has gone into the hydraulic system from the defective accumulator, is removed. 5.

Close-up Subtask 29-10-00-410-076-A A.

Put the aircraft back to the serviceable condition. (1) Make sure that the fluid level in the reservoir of the Green hydraulic system is correct. Add fluid as necessary (Ref. AMM TASK 12-12-29-611-001) . (2) Connect the PTU isolation coupling (Ref. AMM TASK 29-23-00-860-002) . (3) Remove the CONTAINER 5 L (1.32 USGAL) from below the power accumulator. (4) Make sure that the work area is clean and clear of tools and other items. (5) Remove the access platform(s). (6) Close the left main-gear door (Ref. AMM TASK 32-12-00-410-001) . (7) Remove the WARNING NOTICE(S). (8) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-005-A - Deactivation of the Blue Power Accumulator

** ON A/C ALL TASK 29-10-00-040-005-A Deactivation of the Blue Power Accumulator WARNING:

MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

FIN : 2070GM Task Summary MMEL or CDL Ref MMEL 29-10-04A

Access YES

1.

Reason for the Job MMEL 29-10-04A Hydraulic System Accumulator

2

Job Set-up Information A.

Specific Tools NO

Mhr 01.5

E/T 01.5

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific OR No specific No specific No specific No specific No specific

B.

Test NO

QTY DESIGNATION AR CAP - BLANKING AR CAP - BLANKING (ABS0946V10 TYPE) OR AR CAP - BLANKING (MS21914-10 TYPE) AR CONTAINER 5 L (1.32 USGAL) AR SAFETY CLIP - CIRCUIT BREAKER 1 WARNING NOTICE(S) Torque wrench: range to between 7.5 and 8.3 m.daN (55.31 and 61.21 lbf.ft)

Consumable Materials REFERENCE (Material No. 02ABA1)

DESIGNATION Phosphate Ester Hydraulic Fluid-General Power - -

C. Work Zones and Access Panels ZONE/ACCESS 195BB

ZONE DESCRIPTION

D. Referenced Information REFERENCE (Ref. 12-12-29-611-001-A).

DESIGNATION Fill the Hydraulic Fluid Reservoir with a Hand Pump

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-005-A - Deactivation of the Blue Power Accumulator

REFERENCE (Ref. 29-00-00-864-001-A). (Ref. 29-00-00-870-009-A). (Ref. 29-00-00-910-002-A). (Ref. 29-10-00-863-003-A). (Ref. 29-10-00-863-003-A-01). (Ref. 29-10-00-864-003-A). (Ref. 29-14-00-614-001-A). (Ref. 29-14-00-614-002-A). (Ref. 29-14-00-614-002-A-01).

DESIGNATION Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action Bleeding Procedure of the Blue Hydraulic System Downstream of the Blue E-Pump Safety Procedures of the Hydraulic System Pressurize the Blue Hydraulic System with a Hydraulic Ground PowerCart Pressurize the Blue Hydraulic System with the Blue Electric Pump Depressurize the Blue Hydraulic System Depressurization of the Hydraulic Reservoirs Pressurization of the Hydraulic Reservoirs through the Ground Connector Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU)

** ON A/C 201-201, 203-207, 209-211, 217-220, 222-222, 227-235, 237-237, 239-240, 243-250, 350-350 Blue Power Accumulator (2070GM) SHEET 1 ** ON A/C 016-022, 024-100, 112-150, 208-208, 212-216, 221-221, 223-226, 236-236, 238-238, 241-242, 301-349, 351-450, 500-600 Blue Power Accumulator (2070GM) SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-005-A - Deactivation of the Blue Power Accumulator

FR41

A

FR42

B

A 2146GM

D 2070GM 195BB Z195

2

D

1

B 14 13

3

12

C

C 4

11

9

5 6 7

10

8 N_MM_291000_4_AGM0_01_00

Figure 29-10-00-991-01200-00-A / SHEET 1/1 - Blue Power Accumulator (2070GM) ** ON A/C 201-201, 203-207, 209-211, 217-220, 222-222, 227-235, 237-237, 239-240, 243-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-005-A - Deactivation of the Blue Power Accumulator

FR41

A

FR42

A D

195BB 2070GM

B

Z195

2111GM

D

HP MANIFOLD 14 13

B

1 2 3

12

4

11

C 5

10 6 7

C

8

9

N_MM_291000_4_AGF0_01_00

Figure 29-10-00-991-01200-00-B / SHEET 1/1 - Blue Power Accumulator (2070GM) ** ON A/C 016-022, 024-100, 112-150, 208-208, 212-216, 221221, 223-226, 236-236, 238-238, 241-242, 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-005-A - Deactivation of the Blue Power Accumulator

3.

Job Set-up Subtask 29-10-00-865-087-A A.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU 123VU

DESIGNATION HYD/HYD PWR/B WARN/& CTL B HYD/ELEC PUMP

FIN 2702GJ 2701GJ

LOCATION C12 AB09

** ON A/C 201-201, 203-207, 209-211, 217-220, 222-222, 227-235, 237-237, 239-240, 243-250, 350-350 Subtask 29-10-00-860-103-A B.

Aircraft Maintenance Configuration WARNING: OBEY THE HYDRAULIC SAFETY PROCEDURES. (1) Obey the hydraulic safety procedures (Ref. AMM TASK 29-00-00-910-002) . (2) Put the WARNING NOTICE(S) in position to tell persons not to pressurize the Blue hydraulic system: · in the cockpit on the hydraulic section 40VU of the overhead panel · on the ground service panel of the Blue hydraulic system. (3) Make sure that the Blue hydraulic system is depressurized and put it in the maintenance configuration. (Ref. AMM TASK 29-00-00-864-001) . (4) Depressurize the reservoir of the Blue hydraulic system (Ref. AMM TASK 29-14-00-614-001) . (5) Put a CONTAINER 5 L (1.32 USGAL) below the power accumulator to collect the unwanted hydraulic fluid.

** ON A/C 016-022, 024-100, 112-150, 208-208, 212-216, 221-221, 223-226, 236-236, 238-238, 241-242, 301349, 351-450, 500-600 Subtask 29-10-00-860-103-B B.

Aircraft Maintenance Configuration WARNING: OBEY THE HYDRAULIC SAFETY PROCEDURES. (1) Obey the hydraulic safety procedures (Ref. AMM TASK 29-00-00-910-002) . (2) Put the WARNING NOTICE(S) in position to tell persons not to pressurize the Blue hydraulic system: · in the cockpit on the hydraulic section 40VU of the overhead panel · on the ground service panel of the Blue hydraulic system. (3) Make sure that the Blue hydraulic system is depressurized and put it in the maintenance configuration (Ref. AMM TASK 29-00-00-864-001) . (4) Depressurize the reservoir of the Blue hydraulic system (Ref. AMM TASK 29-14-00-614-001) . (5) Put a CONTAINER 5 L (1.32 USGAL) below the power accumulator to collect the unwanted hydraulic fluid. (6) Put a CONTAINER 5 L (1.32 USGAL) below the HP manifold to collect the unwanted hydraulic fluid.

** ON A/C ALL Subtask 29-10-00-010-078-A C.

Open the access door 195BB.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-005-A - Deactivation of the Blue Power Accumulator

4.

Procedure

** ON A/C 201-201, 203-207, 209-211, 217-220, 222-222, 227-235, 237-237, 239-240, 243-250, 350-350 (Ref. Fig. Blue Power Accumulator (2070GM) SHEET 1) ** ON A/C 016-022, 024-100, 112-150, 208-208, 212-216, 221-221, 223-226, 236-236, 238-238, 241-242, 301349, 351-450, 500-600 (Ref. Fig. Blue Power Accumulator (2070GM) SHEET 1) ** ON A/C ALL Subtask 29-10-00-614-052-A A.

Release the nitrogen pressure from the power accumulator (12) as follows: (1) Remove the end cap (14) from the charging valve. (2) Turn the nut (13) to release the nitrogen pressure. (3) When the nitrogen pressure is fully released turn the nut (13) to close the charging valve. (4) Install the end cap (14) on the charging valve.

** ON A/C 201-201, 203-207, 209-211, 217-220, 222-222, 227-235, 237-237, 239-240, 243-250, 350-350 Subtask 29-10-00-020-058-A B.

Removal of the Hydraulic Pipe CAUTION:

USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT HYDRAULIC LINES ON UNIONS. IF YOU DO NOT USE THE SECOND WRENCH, THERE IS A RISK THAT YOU WILL LOOSEN OR TIGHTEN THE UNION TOO MUCH.

(1) Disconnect the line end fitting (1) from the union (2) of the ground leakage measurement manifold (3). (2) Disconnect the line end fitting (10) from the union (11) of the power accumulator (12). (3) Remove the nut (8), the bolt (4), the spacer (6) and the pipe (9) with the clamp (7). (4) Install the CAP - BLANKING on the line end fittings (1) and (10) of the removed pipe (9). Subtask 29-10-00-420-055-A C.

Installation of the Blanking Caps CAUTION:

USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT HYDRAULIC LINES ON UNIONS. IF YOU DO NOT USE THE SECOND WRENCH, THERE IS A RISK THAT YOU WILL LOOSEN OR TIGHTEN THE UNION TOO MUCH.

(1) Apply the Phosphate Ester Hydraulic Fluid-General Power - - (Material No. 02ABA1) to the threads of the unions (2) and (11). (2) Install the CAP - BLANKING (MS21914-10 TYPE) or CAP - BLANKING (ABS0946V10 TYPE) on the unions (2) and (11). (3) TORQUE the blanking caps to between 7.5 and 8.3 m.daN (55.31 and 61.21 lbf.ft). ** ON A/C 016-022, 024-100, 112-150, 208-208, 212-216, 221-221, 223-226, 236-236, 238-238, 241-242, 301349, 351-450, 500-600 Subtask 29-10-00-020-058-B

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-005-A - Deactivation of the Blue Power Accumulator

B.

Removal of the Hydraulic Pipe CAUTION:

USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT HYDRAULIC LINES ON UNIONS. IF YOU DO NOT USE THE SECOND WRENCH, THERE IS A RISK THAT YOU WILL LOOSEN OR TIGHTEN THE UNION TOO MUCH.

(1) Disconnect the line end fitting (2) from the tee connector (1) of the HP manifold (3). (2) Disconnect the line end fitting (10) from the union (11) of the power accumulator (12). (3) Remove the nut (8), the bolt (4), the spacer (6) and the pipe (9) with the clamp (7). (4) Install the CAP - BLANKING on the line end fittings (2) and (10) of the removed pipe (9). Subtask 29-10-00-420-055-B C.

Installation of the Blanking Caps CAUTION:

USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT HYDRAULIC LINES ON UNIONS. IF YOU DO NOT USE THE SECOND WRENCH, THERE IS A RISK THAT YOU WILL LOOSEN OR TIGHTEN THE UNION TOO MUCH.

(1) Apply the Phosphate Ester Hydraulic Fluid-General Power - - (Material No. 02ABA1) to the threads of the tee connector (1) and the union (11). (2) Install the CAP - BLANKING (MS21914-10 TYPE) or CAP - BLANKING (ABS0946V10 TYPE) on the tee connector (1) and the union (11). (3) TORQUE the blanking caps to between 7.5 and 8.3 m.daN (55.31 and 61.21 lbf.ft). ** ON A/C ALL Subtask 29-10-00-865-088-A D.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU 123VU

DESIGNATION HYD/HYD PWR/B WARN/& CTL B HYD/ELEC PUMP

FIN 2702GJ 2701GJ

LOCATION C12 AB09

** ON A/C 201-201, 203-207, 209-211, 217-220, 222-222, 227-235, 237-237, 239-240, 243-250, 350-350 Subtask 29-10-00-790-055-A E.

Leak Test WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. (1) Pressurize the hydraulic reservoir of the Blue hydraulic system (Ref. AMM TASK 29-14-00-614-002) . (2) Pressurize the Blue hydraulic system (Ref. AMM TASK 29-10-00-863-003) (3) After 5 minutes, examine the connection of the blanking cap to the union (2) of the ground leakage measurement manifold (3). Make sure that there is no leakage. (4) Depressurize the Blue hydraulic system (Ref. AMM TASK 29-10-00-864-003) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-005-A - Deactivation of the Blue Power Accumulator

(5) Do the bleeding procedure of the Blue hydraulic system downstream of the Blue E-pump (Ref. AMM TASK 29-00-00-870-009) . NOTE: When you do the bleeding procedure, you remove the nitrogen which came into the hydraulic system from the defective accumulator. ** ON A/C 016-022, 024-100, 112-150, 208-208, 212-216, 221-221, 223-226, 236-236, 238-238, 241-242, 301349, 351-450, 500-600 Subtask 29-10-00-790-055-B E.

Leak Test WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. (1) Pressurize the hydraulic reservoir of the Blue hydraulic system (Ref. AMM TASK 29-14-00-614-002) . (2) Pressurize the Blue hydraulic system (Ref. AMM TASK 29-10-00-863-003) (3) After 5 minutes, examine the connection of the blanking cap to the tee connector (1) of the HP manifold (3). Make sure that there is no leakage. (4) Depressurize the Blue hydraulic system (Ref. AMM TASK 29-10-00-864-003) . (5) Do the bleeding procedure of the Blue hydraulic system downstream of the Blue E-pump (Ref. AMM TASK 29-00-00-870-009) . NOTE: When you do the bleeding procedure, you remove the nitrogen which came into the hydraulic system from the defective accumulator.

** ON A/C ALL 5.

Close-up

** ON A/C 201-201, 203-207, 209-211, 217-220, 222-222, 227-235, 237-237, 239-240, 243-250, 350-350 Subtask 29-10-00-410-078-A A.

Put the aircraft back to the serviceable condition. (1) Make sure that the fluid level in the reservoir of the Blue hydraulic is correct. Add fluid as necessary (Ref. AMM TASK 12-12-29-611-001) . (2) Remove the CONTAINER 5 L (1.32 USGAL) from below the power accumulator. (3) Make sure that the work area is clean and clear of tools and other items. (4) Close the access door 195BB. (5) Remove the WARNING NOTICE(S). (6) Make an entry in the logbook.

** ON A/C 016-022, 024-100, 112-150, 208-208, 212-216, 221-221, 223-226, 236-236, 238-238, 241-242, 301349, 351-450, 500-600 Subtask 29-10-00-410-078-B A.

Put the aircraft back to the serviceable condition. (1) Make sure that the fluid level in the reservoir of the Blue hydraulic is correct. Add fluid as necessary (Ref. AMM TASK 12-12-29-611-001) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-005-A - Deactivation of the Blue Power Accumulator

(2) Remove the CONTAINER 5 L (1.32 USGAL) from below the power accumulator. (3) Remove the CONTAINER 5 L (1.32 USGAL) from below the HP manifold. (4) Make sure that the work area is clean and clear of tools and other items. (5) Close the access door 195BB. (6) Remove the WARNING NOTICE(S). (7) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-006-A - Deactivation of the Yellow Power Accumulator

** ON A/C ALL TASK 29-10-00-040-006-A Deactivation of the Yellow Power Accumulator WARNING:

MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

FIN : 3070GM Task Summary MMEL or CDL Ref MMEL 29-10-04A

Access YES

1.

Reason for the Job MMEL 29-10-04A Hydraulic System Accumulator

2

Job Set-up Information A.

Specific Tools NO

Mhr 01.5

E/T 01.5

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific OR No specific No specific No specific No specific No specific

B.

Test NO

QTY DESIGNATION AR CAP - BLANKING (ABS0946V12 TYPE) OR AR CAP - BLANKING (MS21914-12 TYPE) 1 CONTAINER 5 L (1.32 USGAL) AR SAFETY CLIP - CIRCUIT BREAKER 1 WARNING NOTICE(S) Torque wrench: range to between 8.5 and 9.5 m.daN (62.68 and 70.06 lbf.ft)

Consumable Materials REFERENCE (Material No. 02ABA1)

DESIGNATION Phosphate Ester Hydraulic Fluid-General Power - -

C. Work Zones and Access Panels ZONE/ACCESS 196BB

ZONE DESCRIPTION

D. Referenced Information REFERENCE (Ref. 12-12-29-611-001-A). (Ref. 29-00-00-864-001-A).

DESIGNATION Fill the Hydraulic Fluid Reservoir with a Hand Pump Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-006-A - Deactivation of the Yellow Power Accumulator

REFERENCE (Ref. 29-00-00-870-007-A).

DESIGNATION Bleeding Procedure of the Yellow Hydraulic System Downstream of the Engine Pump (Ref. 29-00-00-910-002-A). Safety Procedures of the Hydraulic System (Ref. 29-10-00-863-002-A). Pressurize the Yellow Hydraulic System with a Hydraulic Ground Power-Cart (Ref. 29-10-00-864-002-A). Depressurize the Yellow Hydraulic System (Ref. 29-14-00-614-001-A). Depressurization of the Hydraulic Reservoirs (Ref. 29-14-00-614-002-A). Pressurization of the Hydraulic Reservoirs through the Ground Connector (Ref. 29-14-00-614-002-A-01). Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU) (Ref. 29-23-00-860-001-A). Disconnection of the Isolation Coupling of the Power Transfer Unit (PTU) (Ref. 29-23-00-860-002-A). Connection of the Isolation Coupling of the Power Transfer Unit (PTU) Yellow Power Accumulator (3070GM) SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-006-A - Deactivation of the Yellow Power Accumulator

FR42

A FR41 3070GM

B

Z196

A 196BB

C

14

1 3111GM

C

13

B

D 2

12 6

3 11 10

D

4

9 5 8

7

N_MM_291000_4_AJM0_01_00

Figure 29-10-00-991-01300-00-A / SHEET 1/1 - Yellow Power Accumulator (3070GM) ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-006-A - Deactivation of the Yellow Power Accumulator

3.

Job Set-up Subtask 29-10-00-865-091-A A.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU

DESIGNATION HYD/HYD PWR/B WARN/& CTL

FIN 2702GJ

LOCATION C12

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU HYDRAULIC/HYD POWER/Y 3803GX N30 ** ON A/C 401-450 121VU HYDRAULIC/HYD POWER/Y

3803GX

N31

** ON A/C ALL 123VU 123VU 123VU

2701GJ 3802GX 3801GX

AB09 AB06 AB03

B HYD/ELEC PUMP Y HYD/ELEC/PUMP Y HYD/ELEC/ELEC PUMP/NORM

Subtask 29-10-00-860-105-A B.

Aircraft Maintenance Configuration WARNING: OBEY THE HYDRAULIC SAFETY PROCEDURES. (1) Obey the hydraulic safety procedures (Ref. AMM TASK 29-00-00-910-002) . (2) Put the WARNING NOTICE(S) in position to tell persons not to pressurize the Yellow hydraulic system: · in the cockpit on the hydraulic section 40VU of the overhead panel, · on the ground service panel of the Yellow hydraulic system. (3) Make sure that the Yellow hydraulic system is depressurized and put it in the maintenance configuration. (Ref. AMM TASK 29-00-00-864-001) . (4) Depressurize the reservoir of the Yellow hydraulic system (Ref. AMM TASK 29-14-00-614-001) . (5) Disconnect the isolation coupling of the Power Transfer Unit (PTU) (Ref. AMM TASK 29-23-00-860001) . (6) Put a CONTAINER 5 L (1.32 USGAL) below the accumulator to collect the unwanted hydraulic fluid.

Subtask 29-10-00-010-080-A C. 4.

Open the access door 196BB.

Procedure (Ref. Fig. Yellow Power Accumulator (3070GM) SHEET 1) Subtask 29-10-00-614-054-A A.

Release the nitrogen pressure from the power accumulator (3) as follows: (1) Remove the end cap (5) from the charging valve. (2) Turn the nut (4) to release the nitrogen pressure. (3) When the nitrogen pressure is fully released turn the nut (4) to close the charging valve. (4) Install the end cap (5) on the charging valve.

Subtask 29-10-00-020-060-A

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-006-A - Deactivation of the Yellow Power Accumulator

B.

Removal of the Hydraulic Pipe CAUTION:

USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT HYDRAULIC LINES ON UNIONS. IF YOU DO NOT USE THE SECOND WRENCH, THERE IS A RISK THAT YOU WILL LOOSEN OR TIGHTEN THE UNION TOO MUCH.

(1) Disconnect the line end fitting (12) from the union (13) of the HP-manifold (14). (2) Disconnect the line end fitting (1) from the union (2) of the power accumulator (3). (3) Remove the nuts (10), the bolts (7) and the pipe (6) with the clamp-block halves (8) and (9). (4) Install the blanking caps on the line end fittings (1) and (12) of the removed pipe (6). Subtask 29-10-00-420-057-A C.

Installation of the Blanking Caps CAUTION:

USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT HYDRAULIC LINES ON UNIONS. IF YOU DO NOT USE THE SECOND WRENCH, THERE IS A RISK THAT YOU WILL LOOSEN OR TIGHTEN THE UNION TOO MUCH.

(1) Apply the Phosphate Ester Hydraulic Fluid-General Power - - (Material No. 02ABA1) to the threads of the unions (2) and (13). (2) Install the CAP - BLANKING (ABS0946V12 TYPE) or CAP - BLANKING (MS21914-12 TYPE) on the unions (2) and (13). (3) TORQUE the blanking caps to between 8.5 and 9.5 m.daN (62.68 and 70.06 lbf.ft). Subtask 29-10-00-865-092-A D.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU

DESIGNATION HYD/HYD PWR/B WARN/& CTL

FIN 2702GJ

LOCATION C12

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU HYDRAULIC/HYD POWER/Y 3803GX N30 ** ON A/C 401-450 121VU HYDRAULIC/HYD POWER/Y

3803GX

N31

** ON A/C ALL 123VU 123VU 123VU

2701GJ 3802GX 3801GX

AB09 AB06 AB03

B HYD/ELEC PUMP Y HYD/ELEC/PUMP Y HYD/ELEC/ELEC PUMP/NORM

Subtask 29-10-00-790-057-A E.

Leak Test WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. (1) Pressurize the reservoir of the Yellow hydraulic system (Ref. AMM TASK 29-14-00-614-002) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-10-00-040-006-A - Deactivation of the Yellow Power Accumulator

(2) Pressurize the Yellow hydraulic system (Ref. AMM TASK 29-10-00-863-002) . (3) After 5 minutes, examine the connections of the blanking cap to the union (13) of the HP-manifold (14). Make sure that there are no hydraulic fluid or nitrogen leaks. (4) Depressurize the Yellow hydraulic system (Ref. AMM TASK 29-10-00-864-002) . (5) Do the bleeding procedure of the Yellow hydraulic system downstream of the engine pump (Ref. AMM TASK 29-00-00-870-007) . NOTE: When you do the bleeding procedure, nitrogen, which has gone into the hydraulic system from the defective accumulator, is removed. 5.

Close-up Subtask 29-10-00-410-080-A A.

Put the aircraft back to the serviceable condition. (1) Make sure that the fluid level in the reservoir of the Yellow hydraulic system is correct. Add fluid as necessary (Ref. AMM TASK 12-12-29-611-001) . (2) Connect the PTU isolation coupling (Ref. AMM TASK 29-23-00-860-002) . (3) Remove the CONTAINER 5 L (1.32 USGAL) from below the power accumulator. (4) Make sure that the work area is clean and clear of tools and other items. (5) Close the access door 196BB. (6) Remove the WARNING NOTICE(S). (7) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-16-00-040-001-A - Deactivation of the Manual Selector Valve

** ON A/C ALL TASK 29-16-00-040-001-A Deactivation of the Manual Selector Valve

FIN : 1134GQ Task Summary MMEL or CDL Ref MMEL 29-20-42A

Access YES

Test NO

Specific Tools YES

Mhr 00.8

1.

Reason for the Job MMEL 29-20-42A Hydraulic Reservoir Four Way Selector Valve on Ground Service Panel (FAA only)

2

Job Set-up Information A.

QTY DESIGNATION 1 HYD GRND PWR UNIT3000

Work Zones and Access Panels ZONE/ACCESS 197CB, 197EB, 198CB

3.

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE (ALT29000001)

B.

E/T 00.8

ZONE DESCRIPTION

Job Set-up Subtask 29-16-00-010-050-A A.

Get Access (1) Get access to the related hydraulic delivery connector of the hydraulic system it is necessary to fill: (a) For the delivery connector (1008GM) of the Green hydraulic system: · Open the access panel 197CB. (b) For the delivery connector (2008GM) of the Blue hydraulic system: · Open the access panel 197EB. (c) For the delivery connector (3008GM) of the Yellow hydraulic system: · Open the access panel 198CB.

4.

Procedure Subtask 29-16-00-611-050-A A.

Procedure to Fill a Reservoir with a Defective Manual Selector Valve (1134GQ) on the Hydraulic GroundService Panel (1) Connect the HYD GRND PWR UNIT3000 (ALT29000001) to the hydraulic delivery connector of the system it is necessary to fill. Do not connect the suction line of the HYD GRND PWR UNIT3000 (ALT29000001) . (2) Slowly increase the pressure until the reservoir fluid level increases.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-16-00-040-001-A - Deactivation of the Manual Selector Valve

(3) Monitor the fluid level at the reservoir. Stop the pressure supply when the fluid level in the reservoir is correct. (4) Do a check of the manual selector valve (1134GQ) for leaks. If necessary, repair the leaks. 5.

Close-up Subtask 29-16-00-860-052-A A.

Put the aircraft back to the serviceable condition. (1) Make sure that the work area is clean and clear of tools and other items. (2) Disconnect the HYD GRND PWR UNIT3000 (ALT29000001) . (3) Close the related access panel: (a) For the delivery connector (1008GM) of the Green hydraulic system: · Close the access panel 197CB. (b) For the delivery connector (2008GM) of the Blue hydraulic system: · Close the access panel 197EB. (c) For the delivery connector (3008GM) of the Yellow hydraulic system: · Close the access panel 198CB. (4) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (5) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-24-00-040-001-A - Deactivation of the Yellow Electric Pump

** ON A/C ALL TASK 29-24-00-040-001-A Deactivation of the Yellow Electric Pump WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

FIN : ** ON A/C ALL EMB SB 29-1134 for A/C 240-240, 243-243 EMB SB 29-1117 for A/C 240-240, 243-243 3075GX ** ON A/C ALL Task Summary MMEL or CDL Ref MMEL 29-24-01A

Access NO

Test NO

1.

Reason for the Job MMEL 29-24-01A Yellow System Electric Pump (FAA only)

2

Job Set-up Information A.

E/T 00.3

Nb Men 1

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

3.

Mhr 00.3

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Specific Tools NO

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up Subtask 29-24-00-860-058-A

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-24-00-040-001-A - Deactivation of the Yellow Electric Pump

A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Make sure that the YELLOW ELEC PUMP pushbutton switch 3804GX on the overhead panel 40VU is in the OFF position (the ON legend is off).

CAUTION:

4.

IMMEDIATELY OPEN THE CIRCUIT BREAKERS FOR THE YELLOW HYDRAULIC SYSTEM AFTER THE CARGO COMPARTMENT DOOR IS FULLY CLOSED/OPEN. IF THE YELLOW HYDRAULIC PUMP OPERATES ON THE GROUND FOR TOO LONG, DAMAGE TO THE YELLOW HYDRAULIC SYSTEM WILL OCCUR.

Procedure NOTE: It is permitted to close the circuit breakers only for the operation of the cargo doors. Subtask 29-24-00-865-053-A A.

Open, safety and tag this(these) circuit breaker(s): PANEL 122VU 123VU 123VU

DESIGNATION DOORS/CARGO Y HYD/ELEC/PUMP Y HYD/ELEC/ELEC PUMP/NORM

FIN 1MJ 3802GX 3801GX

LOCATION T12 AB06 AB03

Subtask 29-24-00-941-051-A B. 5.

Put a warning notice in the flight compartment to tell the crew that the Yellow electric pump does not operate.

Close-up Subtask 29-24-00-862-053-A A.

Aircraft Maintenance Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (2) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-31-00-040-003-A - Deactivation of the Hydraulic Reservoir Quantity-Indicator

** ON A/C ALL TASK 29-31-00-040-003-A Deactivation of the Hydraulic Reservoir Quantity-Indicator

FIN : ** ON A/C ALL EMB SB 31-1156 for A/C 204-204 1834GQ ** ON A/C ALL Task Summary MMEL or CDL Ref MMEL 29-20-41A

Access YES

Test NO

Specific Tools NO

Mhr 01.0

1.

Reason for the Job MMEL 29-20-41A Hydraulic Reservoir Quantity Indicator (Green Servising Panel) (FAA only)

2

Job Set-up Information A.

ZONE DESCRIPTION

Referenced Information REFERENCE (Ref. 12-12-29-611-001-A). (Ref. 12-12-29-611-002-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 32-12-00-010-001-A). (Ref. 32-12-00-410-001-A).

3.

Nb Men 2

Work Zones and Access Panels ZONE/ACCESS 196BB, 197CB, 197FB

B.

E/T 01.0

DESIGNATION Fill the Hydraulic Fluid Reservoir with a Hand Pump Fill the Hydraulic Fluid Reservoir with a Hydraulic Service Cart Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) Open the Main Gear Doors for Access Close the Main Gear Doors after Access

Job Set-up Subtask 29-31-00-860-053-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Open the access door 197CB.

Subtask 29-31-00-865-062-A B.

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

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 29-31-00-040-003-A - Deactivation of the Hydraulic Reservoir Quantity-Indicator

PANEL 121VU 4.

DESIGNATION HYDRAULIC/HYD/QTY/IND

FIN 1831GQ P35

LOCATION

Procedure Subtask 29-31-00-860-054-A A.

Hydraulic Reservoir Filling-Procedure with a defective Reservoir Quantity- Indicator (referred to as the quantity indicator) (1) On the service panel of the Green hydraulic system: · Turn the reservoir-filling manual selector-valve (1134GQ) to the applicable position for each hydraulic system. (2) If the quantity indicator gives an incorrect indication, and it is necessary to fill one or more of the reservoirs: · Fill the applicable reservoir(s) as follows: (a) Get access to the applicable hydraulic reservoir: 1

For the Green hydraulic reservoir: · Open the RH main door of the main landing gear (Ref. AMM TASK 32-12-00-010-001) .

2

For the Blue hydraulic reservoir: · Open the access door 197FB.

3

For the Yellow hydraulic reservoir: · Open the access door 196BB.

(b) Put a person in position at the reservoir you will fill. This person must monitor the contents indicator of the reservoir during the filling procedure. The person must tell you when the reservoir fluid level is correct. (c) Fill the reservoir (Ref. AMM TASK 12-12-29-611-001) or (Ref. AMM TASK 12-12-29-611-002) . (d) Stop the supply of hydraulic fluid when the person at the reservoir tells you the reservoir is full. 5.

Close-up Subtask 29-31-00-860-055-A A.

Put the aircraft back to the serviceable condition. (1) De-energize the ground service network (2) Make sure that the work area is clean and clear of tools and other items. (3) Close access: (a) Close the access door 197CB. (b) For the Green hydraulic reservoir: · Close the main door of the main landing gear (Ref. AMM TASK 32-12-00-410-001) . (c) For the Blue hydraulic reservoir: · Close the access door 197FB. (d) For the Yellow hydraulic reservoir: · Close the access door 196BB. (4) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (5) Make an entry in the logbook.

End of document Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-001-A - Deactivation of the Wing Anti-Ice Control Valve to the CLOSED position

** ON A/C ALL TASK 30-11-00-040-001-A Deactivation of the Wing Anti-Ice Control Valve to the CLOSED position 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.

FIN : 9DL , 10DL Task Summary MMEL or CDL Ref MMEL 30-11-01B 1.

Access YES

Test YES

Specific Tools YES

Mhr 00.3

E/T 00.3

Nb Men 1

Reason for the Job MMEL 30-11-01B Wing Anti-Ice Control Valve NOTE: The wing anti-ice control valve is an interchangeable part.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific (98D27803500001)

B.

QTY AR AR AR AR AR 1

DESIGNATION ACCESS PLATFORM 3M (10 FT) PLACARD SAFETY BARRIER(S) SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S) LOCKING TOOL ZERO POS

Consumable Materials REFERENCE DESIGNATION (Material No. 14QFB1) Wire-Locking Dia: 0.8 mm CRES Nickel Alloy FOR 9DL (VALVE-WING ANTI ICE CONTROL, L) (Material No. 14QFB1) Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -

C. Work Zones and Access Panels Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-001-A - Deactivation of the Wing Anti-Ice Control Valve to the CLOSED position

ZONE/ACCESS ZONE DESCRIPTION FOR 10DL (VALVE-WING ANTI ICE CONTROL, R) 622WB FOR 9DL (VALVE-WING ANTI ICE CONTROL, L) 522WB D. Referenced Information REFERENCE (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 57-41-37-000-008-A). (Ref. 57-41-37-400-008-A).

DESIGNATION EIS Start Procedure EIS Stop Procedure Removal of the Access Panel Installation of the Access Panel

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Wing Anti-Ice Control Valve (SAS 911-002A) - Component Location SHEET 1 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Wing Anti-Ice Control Valve (38E93-X) - Component Location ** ON A/C 401-450 Wing Anti-Ice Control Valve (SAS 911-002A) - Component Location SHEET 1 ** ON A/C 401-450 Wing Anti-Ice Control Valve (38E93-X) - Component Location

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-001-A - Deactivation of the Wing Anti-Ice Control Valve to the CLOSED position

Z522 (Z622)

A

A RIB 9

B

RIB 10 RIB 11

B

FRONT SPAR

5

4 3

C C

9DL 10DL

C E

S

LO

1 D

BOLT STOWAGE POSITION EN

OP

2

N_MM_301100_4_BAM0_01_00

Figure 30-11-00-991-00400-00-A / SHEET 1/1 - Wing AntiIce Control Valve (SAS 911-002A) - Component Location ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-001-A - Deactivation of the Wing Anti-Ice Control Valve to the CLOSED position

A

FR8

Z522 (Z622)

FR9

B D

A FRONT SPAR DATUM

9DL (10DL)

12 11

C

B 10 F W D

C

N_MM_301100_4_BMM0_01_03

Figure 30-11-00-991-00800-00-A / SHEET 1/3 - Wing Anti-Ice Control Valve (38E93-X) - Component Location ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-001-A - Deactivation of the Wing Anti-Ice Control Valve to the CLOSED position

E F G H

D

14

15

15 14

13

13 F W D

E

01

F W D

F

02

NOTE: 01 02

VALVE SHOWN IN CLOSED POSITION VALVE SHOWN IN OPEN POSITION

N_MM_301100_4_BMM0_02_00

Figure 30-11-00-991-00800-00-A / SHEET 2/3 - Wing Anti-Ice Control Valve (38E93-X) - Component Location ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-001-A - Deactivation of the Wing Anti-Ice Control Valve to the CLOSED position

15

G

03

H

04

15

NOTE: 03 LOCKING PLATE IN LOCKED POSITION (PUSH COMPLETELY FROM LEFT OR RIGHT) 04 LOCKING PLATE IN UNLOCKED POSITION (PUSH TO MIDDLE POSITION) N_MM_301100_4_BMM0_03_00

Figure 30-11-00-991-00800-00-A / SHEET 3/3 - Wing Anti-Ice Control Valve (38E93-X) - Component Location ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-001-A - Deactivation of the Wing Anti-Ice Control Valve to the CLOSED position

A Z522 (Z622)

A B

RIB9 RIB10 RIB11

B

FRONT SPAR

C C

9DL (10DL)

1 BOLT STOWAGE POSITION

2

N_MM_301100_4_BJM0_01_01

Figure 30-11-00-991-00400-00-B / SHEET 1/1 - Wing AntiIce Control Valve (SAS 911-002A) - Component Location ** ON A/C 401-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-001-A - Deactivation of the Wing Anti-Ice Control Valve to the CLOSED position

A

FR8

Z522 (Z622)

FR9

B D

A FRONT SPAR DATUM

9DL (10DL)

12 11

C

B 10 F W D

C

N_MM_301100_4_SAM0_01_03

Figure 30-11-00-991-00800-00-B / SHEET 1/3 - Wing Anti-Ice Control Valve (38E93-X) - Component Location ** ON A/C 401-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-001-A - Deactivation of the Wing Anti-Ice Control Valve to the CLOSED position

E F G H

D

14

15

15 14

13

13 F W D

E

01

F W D

F

02

NOTE: 01 02

VALVE SHOWN IN CLOSED POSITION VALVE SHOWN IN OPEN POSITION

N_MM_301100_4_SAM0_02_00

Figure 30-11-00-991-00800-00-B / SHEET 2/3 - Wing Anti-Ice Control Valve (38E93-X) - Component Location ** ON A/C 401-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-001-A - Deactivation of the Wing Anti-Ice Control Valve to the CLOSED position

15

G

03

H

04

15

NOTE: 03 LOCKING PLATE IN LOCKED POSITION (PUSH COMPLETELY FROM LEFT OR RIGHT) 04 LOCKING PLATE IN UNLOCKED POSITION (PUSH TO MIDDLE POSITION) N_MM_301100_4_SAM0_03_00

Figure 30-11-00-991-00800-00-B / SHEET 3/3 - Wing Anti-Ice Control Valve (38E93-X) - Component Location ** ON A/C 401-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-001-A - Deactivation of the Wing Anti-Ice Control Valve to the CLOSED position

3.

Job Set-up Subtask 30-11-00-941-059-A A.

Safety Precautions (1) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations. (2) Before you do work on the Ice Protection system, put WARNING NOTICE(S) in position to tell persons not to operate the: · pneumatic system · engines · slats · APU. (3) Install a LOCKING TOOL ZERO POS (98D27803500001) on the flap/slat control lever. (4) On panel 191DB put a WARNING NOTICE(S) in position to tell persons not to pressurize the bleed air system.

Subtask 30-11-00-860-056-A B.

Aircraft Maintenance Configuration (1) Do the EIS start procedure (Ref. AMM TASK 31-60-00-860-001) .

Subtask 30-11-00-865-052-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU 49VU

DESIGNATION ANTI ICE/WING/CTL ANTI ICE/WING/MONG

FIN 2DL 1DL

LOCATION C02 C01

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU FLIGHT CONTROLS/SLT/CTL AND 5CV B06 MONG/SYS1 ** ON A/C 401-450 49VU FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 ** ON A/C ALL 121VU 121VU

APU/APU/CTL FLIGHT CONTROLS/SLT/CTL/SYS2

5CV

B01

2KD 7CV

L42 R21

Subtask 30-11-00-010-052-B D.

Get Access (1) Put the ACCESS PLATFORM 3M (10 FT) in position below the applicable access panel 522WB(622WB), zone 522(622). (2) Remove the applicable access panel (Ref. AMM TASK 57-41-37-000-008) : (a) FOR 9DL (VALVE-WING ANTI ICE CONTROL, L) · Remove 522WB from panel 522AB (b) FOR 10DL (VALVE-WING ANTI ICE CONTROL, R) · Remove 622WB from panel 622AB.

4.

Procedure

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-001-A - Deactivation of the Wing Anti-Ice Control Valve to the CLOSED position

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 (Ref. Fig. Wing Anti-Ice Control Valve (SAS 911-002A) - Component Location SHEET 1) (Ref. Fig. Wing AntiIce Control Valve (38E93-X) - Component Location) ** ON A/C 401-450 (Ref. Fig. Wing Anti-Ice Control Valve (SAS 911-002A) - Component Location SHEET 1) (Ref. Fig. Wing AntiIce Control Valve (38E93-X) - Component Location) ** ON A/C ALL Subtask 30-11-00-040-056-A A.

Deactivation of the Wing Anti-Ice Control-Valve to the CLOSED Position (for part number SAS 911-002A) 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. (1) Remove and discard the lockwire from the bolt (1). (2) Manually put the indicator (2) to the CLOSED position. This puts the anti-ice control valve in the closed position. (3) Remove the bolt (1) from its stowage position. (4) Install the bolt (1) through the hole in the indicator (2) and in the anti-ice control valve. (5) Tighten the bolt (1) and safety with Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - (Material No. 14QFB1).

Subtask 30-11-00-040-057-A B.

Deactivation of the Wing Anti-Ice Control-Valve to the CLOSED Position (for part number 38E93-X) 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. (1) FOR 9DL (VALVE-WING ANTI ICE CONTROL, L) (a) Remove and discard the lockwire from the locking screw (10). (2) FOR 9DL (VALVE-WING ANTI ICE CONTROL, L) (a) Make sure that the indicator (12) is in the CLOSED position. (b) If necessary, move the indicator (12) to the CLOSED position with hand. (3) FOR 10DL (VALVE-WING ANTI ICE CONTROL, R) (a) Make sure that the bolt (13) is adjacent to the CLOSED indication on the valve body. (b) If necessary, move the rod (14) so that the bolt (13) is adjacent to the CLOSED indication. (4) FOR 9DL (VALVE-WING ANTI ICE CONTROL, L) (a) Remove the locking screw (10) from its stowage position. (5) FOR 9DL (VALVE-WING ANTI ICE CONTROL, L) (a) Install the locking screw (10) through the locking hole in the indicator (12) and the anti-ice control valve.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 12 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-001-A - Deactivation of the Wing Anti-Ice Control Valve to the CLOSED position

(b) Safety the locking screw (10) with a Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - (Material No. 14QFB1). (6) FOR 10DL (VALVE-WING ANTI ICE CONTROL, R) (a) Push the locking plate (15) to engage and lock the rod (14). NOTE: The locking plate (15) has three positions: - When in its middle position, the locking plate (15) is unlocked. - When pushed fully left or fully right, the locking plate (15) locks the rod (14). (b) Make sure that you hear a click when you put the locking plate (15) in the correct position. 5.

Close-up Subtask 30-11-00-410-052-B A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the applicable access panel (Ref. AMM TASK 57-41-37-400-008) : (a) FOR 9DL (VALVE-WING ANTI ICE CONTROL, L) · Install 522WB (b) FOR 10DL (VALVE-WING ANTI ICE CONTROL, R) · Install 622WB.

Subtask 30-11-00-865-061-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU 49VU

DESIGNATION ANTI ICE/WING/CTL ANTI ICE/WING/MONG

FIN 2DL 1DL

LOCATION C02 C01

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU FLIGHT CONTROLS/SLT/CTL AND 5CV B06 MONG/SYS1 ** ON A/C 401-450 49VU FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 ** ON A/C ALL 121VU 121VU

APU/APU/CTL FLIGHT CONTROLS/SLT/CTL/SYS2

5CV

B01

2KD 7CV

L42 R21

Subtask 30-11-00-860-055-A C.

Aircraft Configuration (1) Make sure that the ECAM upper DU, on Panel 4VU, does not show the warning message: WING A.ICE L(R) VALVE OPEN. If necessary, on Panel 11VU press the EMER CANC pushbutton switch on the ECAM Control Panel to cancel the message. (2) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (3) Put a PLACARD in position to tell aircraft crew that one or two of the wing anti-ice control valves are deactivated. (4) Make an applicable entry in the aircraft technical log.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 13 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-001-A - Deactivation of the Wing Anti-Ice Control Valve to the CLOSED position

Subtask 30-11-00-942-055-A D.

Removal of Equipment (1) Remove the safety barriers. (2) Remove the WARNING NOTICE(S). (3) Remove the access platform(s). (4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 14 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-004-A - Deactivation of the RH Wing Anti-Ice Control Valve to the OPEN position

** ON A/C ALL TASK 30-11-00-040-004-A Deactivation of the RH Wing Anti-Ice Control Valve to the OPEN position 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.

FIN : 10DL Task Summary MMEL or CDL Ref MMEL 30-11-01A 1.

Access YES

Test YES

Specific Tools YES

Mhr 01.0

E/T 01.0

Nb Men 1

Reason for the Job MMEL 30-11-01A Wing Anti-Ice Control Valve NOTE: The wing anti-ice control valve is an interchangeable part.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific (98D27803500001)

B.

QTY AR AR AR AR 1

DESIGNATION ACCESS PLATFORM 3M (10 FT) SAFETY BARRIER(S) SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S) LOCKING TOOL ZERO POS

Consumable Materials REFERENCE (Material No. 14QFB1)

DESIGNATION Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -

C. Work Zones and Access Panels ZONE/ACCESS 622AB, 622WB

ZONE DESCRIPTION

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-004-A - Deactivation of the RH Wing Anti-Ice Control Valve to the OPEN position

D. Referenced Information REFERENCE (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 57-41-37-000-004-A). (Ref. 57-41-37-000-008-A). (Ref. 57-41-37-400-002-A). (Ref. 57-41-37-400-008-A).

DESIGNATION EIS Start Procedure EIS Stop Procedure Removal of the Pressure-Relief Panels Removal of the Access Panel Installation of the Pressure-Relief Panels Installation of the Access Panel

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Wing Anti-Ice Control Valve (SAS 911-002A) - Component Location SHEET 1 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Wing Anti-Ice Control Valve (38E93-X) - Component Location ** ON A/C 401-450 Wing Anti-Ice Control Valve (SAS 911-002A) - Component Location SHEET 1 ** ON A/C 401-450 Wing Anti-Ice Control Valve (38E93-X) - Component Location

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-004-A - Deactivation of the RH Wing Anti-Ice Control Valve to the OPEN position

Z522 (Z622)

A

A RIB 9

B

RIB 10 RIB 11

B

FRONT SPAR

5

4 3

C C

9DL 10DL

C E

S

LO

1 D

BOLT STOWAGE POSITION EN

OP

2

N_MM_301100_4_BAM0_01_00

Figure 30-11-00-991-00400-00-A / SHEET 1/1 - Wing AntiIce Control Valve (SAS 911-002A) - Component Location ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-004-A - Deactivation of the RH Wing Anti-Ice Control Valve to the OPEN position

A

FR8

Z522 (Z622)

FR9

B D

A FRONT SPAR DATUM

9DL (10DL)

12 11

C

B 10 F W D

C

N_MM_301100_4_BMM0_01_03

Figure 30-11-00-991-00800-00-A / SHEET 1/3 - Wing Anti-Ice Control Valve (38E93-X) - Component Location ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-004-A - Deactivation of the RH Wing Anti-Ice Control Valve to the OPEN position

E F G H

D

14

15

15 14

13

13 F W D

E

01

F W D

F

02

NOTE: 01 02

VALVE SHOWN IN CLOSED POSITION VALVE SHOWN IN OPEN POSITION

N_MM_301100_4_BMM0_02_00

Figure 30-11-00-991-00800-00-A / SHEET 2/3 - Wing Anti-Ice Control Valve (38E93-X) - Component Location ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-004-A - Deactivation of the RH Wing Anti-Ice Control Valve to the OPEN position

15

G

03

H

04

15

NOTE: 03 LOCKING PLATE IN LOCKED POSITION (PUSH COMPLETELY FROM LEFT OR RIGHT) 04 LOCKING PLATE IN UNLOCKED POSITION (PUSH TO MIDDLE POSITION) N_MM_301100_4_BMM0_03_00

Figure 30-11-00-991-00800-00-A / SHEET 3/3 - Wing Anti-Ice Control Valve (38E93-X) - Component Location ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-004-A - Deactivation of the RH Wing Anti-Ice Control Valve to the OPEN position

A Z522 (Z622)

A B

RIB9 RIB10 RIB11

B

FRONT SPAR

C C

9DL (10DL)

1 BOLT STOWAGE POSITION

2

N_MM_301100_4_BJM0_01_01

Figure 30-11-00-991-00400-00-B / SHEET 1/1 - Wing AntiIce Control Valve (SAS 911-002A) - Component Location ** ON A/C 401-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-004-A - Deactivation of the RH Wing Anti-Ice Control Valve to the OPEN position

A

FR8

Z522 (Z622)

FR9

B D

A FRONT SPAR DATUM

9DL (10DL)

12 11

C

B 10 F W D

C

N_MM_301100_4_SAM0_01_03

Figure 30-11-00-991-00800-00-B / SHEET 1/3 - Wing Anti-Ice Control Valve (38E93-X) - Component Location ** ON A/C 401-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-004-A - Deactivation of the RH Wing Anti-Ice Control Valve to the OPEN position

E F G H

D

14

15

15 14

13

13 F W D

E

01

F W D

F

02

NOTE: 01 02

VALVE SHOWN IN CLOSED POSITION VALVE SHOWN IN OPEN POSITION

N_MM_301100_4_SAM0_02_00

Figure 30-11-00-991-00800-00-B / SHEET 2/3 - Wing Anti-Ice Control Valve (38E93-X) - Component Location ** ON A/C 401-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-004-A - Deactivation of the RH Wing Anti-Ice Control Valve to the OPEN position

15

G

03

H

04

15

NOTE: 03 LOCKING PLATE IN LOCKED POSITION (PUSH COMPLETELY FROM LEFT OR RIGHT) 04 LOCKING PLATE IN UNLOCKED POSITION (PUSH TO MIDDLE POSITION) N_MM_301100_4_SAM0_03_00

Figure 30-11-00-991-00800-00-B / SHEET 3/3 - Wing Anti-Ice Control Valve (38E93-X) - Component Location ** ON A/C 401-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-004-A - Deactivation of the RH Wing Anti-Ice Control Valve to the OPEN position

3.

Job Set-up Subtask 30-11-00-941-064-A A.

Safety Precautions (1) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations. (2) Before you do work on the Ice Protection system, put WARNING NOTICE(S) in position to tell persons not to operate the: · Pneumatic system · Engines · Slats · APU. (3) Install a LOCKING TOOL ZERO POS (98D27803500001) on the flap/slat control lever. (4) On panel 191DB, put a WARNING NOTICE(S) in position to tell persons not to pressurize the bleed air system.

Subtask 30-11-00-860-057-A B.

Aircraft Maintenance Configuration (1) Do the EIS start procedure (Ref. AMM TASK 31-60-00-860-001) .

Subtask 30-11-00-865-065-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU 49VU

DESIGNATION ANTI ICE/WING/CTL ANTI ICE/WING/MONG

FIN 2DL 1DL

LOCATION C02 C01

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU FLIGHT CONTROLS/SLT/CTL AND 5CV B06 MONG/SYS1 ** ON A/C 401-450 49VU FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 ** ON A/C ALL 121VU 121VU

APU/APU/CTL FLIGHT CONTROLS/SLT/CTL/SYS2

5CV

B01

2KD 7CV

L42 R21

Subtask 30-11-00-010-059-B D.

Get Access (1) Put the ACCESS PLATFORM 3M (10 FT) in position below zone 622. (2) Remove the access panel 622WB (Ref. AMM TASK 57-41-37-000-008) . NOTE: If more access is necessary, remove the access panel 622AB (Ref. AMM TASK 57-41-37000-004) .

4.

Procedure

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-004-A - Deactivation of the RH Wing Anti-Ice Control Valve to the OPEN position

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 (Ref. Fig. Wing Anti-Ice Control Valve (SAS 911-002A) - Component Location SHEET 1) (Ref. Fig. Wing AntiIce Control Valve (38E93-X) - Component Location) ** ON A/C 401-450 (Ref. Fig. Wing Anti-Ice Control Valve (SAS 911-002A) - Component Location SHEET 1) (Ref. Fig. Wing AntiIce Control Valve (38E93-X) - Component Location) ** ON A/C ALL Subtask 30-11-00-040-055-A A.

Deactivation of the Wing Anti-Ice Control-Valve to the OPEN Position - PN SAS 911-002A 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. (1) Remove and discard the lockwire from the bolt (1). (2) If necessary, turn the indicator (2) to the OPEN position and install the bolt (1). (3) Safety the bolt (1) with Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - (Material No. 14QFB1).

Subtask 30-11-00-040-058-A B.

Deactivation of the Wing Anti-Ice Control-Valve to the OPEN Position - PN 38E93-X (1) Do one of the steps that follow: (a) For the deactivation procedure of the wing anti-ice control-valve with the locking plate (15), do step (2). (b) For the deactivation procedure of the wing anti-ice control-valve with the locking screw (10), do step (3). (2) Deactivation of the wing anti-ice control-valve with the locking plate (15): (a) If necessary, move the rod (14) until the bolt (13) is adjacent to the OPEN position. (b) Push the locking plate (15) to engage and lock the rod (14). NOTE: The locking plate (15) has three positions: - When in its middle position, the locking plate (15) is unlocked. - When pushed fully left or fully right, the locking plate (15) locks the rod (14). (c) Make sure that you hear a click when you put the locking plate (15) in the correct position. (3) Deactivation of the wing anti-ice control-valve with the locking screw (10): 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. (a) Remove and discard the lockwire from the locking screw (10). (b) Make sure that the indicator (12) is in the OPEN position. (c) If necessary, slowly move the indicator (12) to the OPEN position with your hand. (d) Remove the locking screw (10) from its stowage position.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 12 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-004-A - Deactivation of the RH Wing Anti-Ice Control Valve to the OPEN position

(e) Install the locking screw (10) on the wing anti-ice control-valve through the locking hole in the indicator (12). (f) 5.

Safety the locking screw (10) with a Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - (Material No. 14QFB1).

Close-up Subtask 30-11-00-410-057-B A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) If removed, install the access panel 622AB (Ref. AMM TASK 57-41-37-400-002) . (3) Install the access panel 622WB (Ref. AMM TASK 57-41-37-400-008) .

Subtask 30-11-00-865-066-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU 49VU

DESIGNATION ANTI ICE/WING/CTL ANTI ICE/WING/MONG

FIN 2DL 1DL

LOCATION C02 C01

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU FLIGHT CONTROLS/SLT/CTL AND 5CV B06 MONG/SYS1 ** ON A/C 401-450 49VU FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 ** ON A/C ALL 121VU 121VU

APU/APU/CTL FLIGHT CONTROLS/SLT/CTL/SYS2

5CV

B01

2KD 7CV

L42 R21

Subtask 30-11-00-860-058-A C.

Aircraft Maintenance Configuration (1) Make sure that the warning message WING A.ICE L(R) VALVE OPEN does not show on panel 4VU on the ECAM upper DU. · If necessary, on panel 11VU, push the EMER CANC pushbutton switch on the ECAM control panel to cancel the message. (2) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (3) Make an applicable entry in the aircraft technical log that the RH anti-ice valve is deactivated. The engine bleed must not be operated during ground operation (unless for engine start). If the crossbleed valve is open, the APU bleed must not be operated during ground operation (unless for engine start). If the engine or APU bleed is operated, heat damage to the slats can occur.

Subtask 30-11-00-942-060-A D.

Removal of Equipment (1) Remove the safety barriers. (2) Remove the WARNING NOTICE(S). (3) Remove the access platform(s).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 13 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-004-A - Deactivation of the RH Wing Anti-Ice Control Valve to the OPEN position

(4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 14 of 14

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-002-A - Wing Anti Ice Fault LT - Valve Deactivation

** ON A/C ALL TASK 30-11-00-040-002-A Wing Anti Ice Fault LT - Valve Deactivation 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:

MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

Task Summary MMEL or CDL Ref MMEL 30-01-01-03B

Access NO

Test YES

1.

Reason for the Job MMEL 30-01-01-03B ANTI ICE WING pb-sw FAULT light

2

Job Set-up Information A.

E/T 01.0

Nb Men 1

QTY DESIGNATION AR SAFETY BARRIER(S) AR WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 30-11-00-040-001-A).

3.

Mhr 01.0

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Specific Tools NO

DESIGNATION Deactivation of the Wing Anti-Ice Control Valve to the CLOSED position

Job Set-up Subtask 30-11-00-941-069-A A.

Safety Precautions (1) Put the SAFETY BARRIER(S) in position. (2) Before you do work on the Ice Protection system, put WARNING NOTICE(S) in position to tell persons not to operate the: · pneumatic system · engines · slats

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-11-00-040-002-A - Wing Anti Ice Fault LT - Valve Deactivation

· APU. (3) On panel 191DB, put a WARNING NOTICE(S) in position to tell persons not to pressurize the bleed air system. 4.

Procedure Subtask 30-11-00-040-053-A A.

Deactivate the Two Anti-Ice Control Valves (1) Deactivate the two anti-ice control valves (Ref. AMM TASK 30-11-00-040-001) . (2) Make an entry in the aircraft technical log to tell the crew that the wing anti-ice LT is deactivated. (3) Put a PLACARD in the cockpit to tell persons that the wing anti-ice LT is Deactivated.

5.

Close-up Subtask 30-11-00-942-067-A A.

Removal of Equipment (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the safety barriers. (3) Remove the WARNING NOTICE(S). (4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-001-A - Deactivation of the Engine Anti-Ice Valve in CLOSED Position

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 TASK 30-21-00-040-001-A Deactivation of the Engine Anti-Ice Valve in CLOSED Position 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.

Task Summary MMEL or CDL Ref MMEL 30-21-01A 1.

Reason for the Job MMEL 30-21-01A Engine Anti-Ice Valve

2

Job Set-up Information A.

Access YES

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Test YES

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER AR WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. CP8004)

DESIGNATION lockwire 0.6 mm (0.0236 in.) dia

C. Work Zones and Access Panels ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 437AL, 438AR FOR 1000EM2 (ENGINE-2) 447AL, 448AR

ZONE DESCRIPTION

D. Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A).

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power (Ref. 71-13-00-010-040-B). Opening of the Fan Cowl Doors (Ref. 71-13-00-410-040-B). Closing of the Fan Cowl Doors Anti-Ice Valve of the Engine Air Intake SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-001-A - Deactivation of the Engine Anti-Ice Valve in CLOSED Position

A MANUEL OVERRIDE REMOVE STOWED ROTATE TO DESIRED POSITION INSTALL PIN IN LOCKED POSITION

4000DN

B

CL OP

LOCK

STOW

B LOCK PIN

OVERPRESSURE INDICATOR

A

PRESSURE REDUCER

ELECTRICAL CONNECTOR

ACTUATOR

PILOT VALVE SOLENOID

SERVO PORT OUTLET PORT BUTTERFLY SHUTOFF VALVE FLOW DIRECTION

INLET PORT N_MM_302100_4_UAM0_01_00

Figure 30-21-00-991-90100-00-A / SHEET 1/1 - Anti-Ice Valve of the Engine Air Intake ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-001-A - Deactivation of the Engine Anti-Ice Valve in CLOSED Position

3.

Job Set-up Subtask 30-21-00-861-056-A A.

Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Subtask 30-21-00-860-050-A B.

Safety Precautions (1) 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) Put a WARNING NOTICE(S) in position to tell persons not to operate the ENG/MODE selector switch and the ENG/MASTER 1(2) control switch. (2) On the ENG section 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) to tell persons not to energize FADEC 1(2). (3) On the ANTI ICE section of the panel 25VU: (a) Release the ANTI ICE/ENG 1(2) pushbutton switch (the ON legend goes off).

Subtask 30-21-00-865-051-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL FOR FIN 1000EM1 122VU FOR FIN 1000EM2 122VU

DESIGNATION (ENGINE-1) ANTI ICE/ENG/1 (ENGINE-2) ANTI ICE/ENG/2

FIN

LOCATION

1DN1

X10

1DN2

W10

Subtask 30-21-00-010-052-A D.

Get Access (1) Open the fan-cowl doors (Ref. AMM TASK 71-13-00-010-040) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR

4.

Procedure (Ref. Fig. Anti-Ice Valve of the Engine Air Intake SHEET 1) Subtask 30-21-00-040-050-A A.

Deactivation of the Anti Ice Valve CAUTION:

DO NOT APPLY A TORQUE OF MORE THAN 70 LBF.IN. WHEN YOU OPEN OR CLOSE THE VALVE MANUALLY. HIGH TORQUE CAN CAUSE DAMAGE TO THE INTERNAL SHAFT IN THE VALVE. IF THE VALVE DOES NOT OPEN OR CLOSE WHEN YOU APPLY THE SPECIFIED TORQUE, YOU MUST DO AN OVERHAUL OF THE VALVE.

(1) On the anti ice valve 4000DN:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-001-A - Deactivation of the Engine Anti-Ice Valve in CLOSED Position

· set the manual override control to CL with a hexagonal wrench and lock it with the locking pin which is on the valve. (2) Installation of lockwire: 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. (a) Safety the locking pin with lockwire 0.6 mm (0.0236 in.) dia (Material No. CP8004). 5.

Close-up Subtask 30-21-00-865-059-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL FOR FIN 1000EM1 122VU FOR FIN 1000EM2 122VU

DESIGNATION (ENGINE-1) ANTI ICE/ENG/1 (ENGINE-2) ANTI ICE/ENG/2

FIN

LOCATION

1DN1

X10

1DN2

W10

Subtask 30-21-00-410-052-A B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-040) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR

Subtask 30-21-00-860-051-A C.

Aircraft Maintenance Configuration (1) Remove the WARNING NOTICE(S). (2) Put a WARNING NOTICE(S) in position in the cockpit to tell persons that the anti ice valve is deactivated in the closed position. (3) Make an entry in the logbook.

Subtask 30-21-00-862-056-A D.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-002-A - Deactivation of the Engine Anti-Ice Valve in the OPEN Position

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 TASK 30-21-00-040-002-A Deactivation of the Engine Anti-Ice Valve in the OPEN Position Task Summary MMEL or CDL Ref MMEL 30-21-01B 1.

Reason for the Job MMEL 30-21-01B Engine Anti-Ice Valve

2

Job Set-up Information A.

Access YES

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Test YES

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER AR WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. CP8004)

DESIGNATION lockwire 0.6 mm (0.0236 in.) dia

C. Work Zones and Access Panels ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 437AL, 438AR FOR 1000EM2 (ENGINE-2) 447AL, 448AR

ZONE DESCRIPTION

D. Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A).

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power (Ref. 71-13-00-010-040-B). Opening of the Fan Cowl Doors (Ref. 71-13-00-410-040-B). Closing of the Fan Cowl Doors Anti-Ice Valve of the Engine Air Intake SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-002-A - Deactivation of the Engine Anti-Ice Valve in the OPEN Position

A MANUEL OVERRIDE REMOVE STOWED ROTATE TO DESIRED POSITION INSTALL PIN IN LOCKED POSITION

4000DN

B

CL OP

LOCK

STOW

B LOCK PIN

OVERPRESSURE INDICATOR

A

PRESSURE REDUCER

ELECTRICAL CONNECTOR

ACTUATOR

PILOT VALVE SOLENOID

SERVO PORT OUTLET PORT BUTTERFLY SHUTOFF VALVE FLOW DIRECTION

INLET PORT N_MM_302100_4_UAM0_01_00

Figure 30-21-00-991-90100-00-A / SHEET 1/1 - Anti-Ice Valve of the Engine Air Intake ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-002-A - Deactivation of the Engine Anti-Ice Valve in the OPEN Position

3.

Job Set-up Subtask 30-21-00-861-060-A A.

Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Subtask 30-21-00-860-053-A B.

Safety Precautions (1) 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) Put a WARNING NOTICE(S) in position to tell persons not to operate the ENG/MODE selector switch and the ENG/MASTER 1(2) control switch. (2) On the ENG section 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) to tell persons not to energize FADEC 1(2). (3) On the ANTI ICE section of the panel 25VU: (a) Release the ANTI ICE/ENG 1(2) pushbutton switch (the ON legend goes off).

Subtask 30-21-00-865-053-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL FOR FIN 1000EM1 122VU FOR FIN 1000EM2 122VU

DESIGNATION (ENGINE-1) ANTI ICE/ENG/1 (ENGINE-2) ANTI ICE/ENG/2

FIN

LOCATION

1DN1

X10

1DN2

W10

Subtask 30-21-00-010-054-A D.

Get Access (1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-040) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR

4.

Procedure (Ref. Fig. Anti-Ice Valve of the Engine Air Intake SHEET 1) Subtask 30-21-00-040-051-A A.

Deactivation of the Anti Ice Valve CAUTION:

DO NOT APPLY A TORQUE OF MORE THAN 70 LBF.IN. WHEN YOU OPEN OR CLOSE THE VALVE MANUALLY. HIGH TORQUE CAN CAUSE DAMAGE TO THE INTERNAL SHAFT IN THE VALVE. IF THE VALVE DOES NOT OPEN OR CLOSE WHEN YOU APPLY THE SPECIFIED TORQUE, YOU MUST DO AN OVERHAUL OF THE VALVE.

(1) On the anti ice valve 4000DN:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-002-A - Deactivation of the Engine Anti-Ice Valve in the OPEN Position

(a) Set the manual override control to OP with a hexagonal wrench and lock it with the locking pin which is on the valve. (2) Installation of lockwire: 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. (a) Safety the locking pin with lockwire 0.6 mm (0.0236 in.) dia (Material No. CP8004). (3) On the overhead panel 25VU: (a) Push the ANTI ICE/ENG 1(2) pushbutton switch. 5.

Close-up Subtask 30-21-00-865-058-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL FOR FIN 1000EM1 122VU FOR FIN 1000EM2 122VU

DESIGNATION (ENGINE-1) ANTI ICE/ENG/1 (ENGINE-2) ANTI ICE/ENG/2

FIN

LOCATION

1DN1

X10

1DN2

W10

Subtask 30-21-00-410-054-A B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-040) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR

Subtask 30-21-00-860-054-A C.

Aircraft Maintenance Configuration (1) Remove the WARNING NOTICE(S). (2) On the ANTI ICE part of the panel 25VU, make sure that the ENG 1(2) pushbutton switch is pushed. (On the pushbutton switch, the ON legend is on). (3) Put a WARNING NOTICE(S) in position in the cockpit. This tells persons that the anti ice valve is deactivated in the open position. (4) Make an entry in the logbook.

Subtask 30-21-00-862-060-A D.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-020-C - Deactivation of the Engine Anti-Ice Valve in the CLOSED Position

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 TASK 30-21-00-040-020-C Deactivation of the Engine Anti-Ice Valve in the CLOSED Position 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.

1.

Reason for the Job MMEL 30-21-01A Engine Anti-Ice Valve

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 437AL, 438AR FOR 1000EM2 (ENGINE-2) 447AL, 448AR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A).

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power (Ref. 71-13-00-010-010-A). Opening of the Fan Cowls 437AL(447AL),438AR(448AR) (Ref. 71-13-00-410-010-A). Closing of the Fan Cowls 437AL(447AL),438AR(448AR) Engine Air Intake Anti Ice Valve SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-020-C - Deactivation of the Engine Anti-Ice Valve in the CLOSED Position

INTAKE ANTI-ICE VALVE

B

A

INTAKE ANTI-ICE VALVE 1 TRANSPORTATION BRACKET 2

A 3 LOCK PIN

CL LOCK

OP

MANUAL OVERIDE REMOVE STOWED PIN-ROTATE TO DESIRED POSITION INSTALL PIN IN LOCKED POSITION

5 NUT

4 VALVE LOCKING-HOLE

B4318

B N_MM_302100_4_XAN0_01_01

Figure 30-21-00-991-15000-13-B / SHEET 1/1 - Engine Air Intake Anti Ice Valve ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-020-C - Deactivation of the Engine Anti-Ice Valve in the CLOSED Position

3.

Job Set-up Subtask 30-21-00-861-064-A A.

Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Subtask 30-21-00-860-084-A B.

Safety Precautions (1) 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) Put a WARNING NOTICE(S) in position to tell persons not to operate the ENG/MODE selector switch and the ENG/MASTER 1(2) control switch. (2) On the ENG section 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) to tell persons not to energize FADEC 1(2). (3) On the ANTI ICE section of the panel 25VU: (a) Release the ANTI ICE/ENG 1(2) pushbutton switch (the ON legend goes off).

Subtask 30-21-00-865-080-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL FOR FIN 1000EM1 122VU FOR FIN 1000EM2 122VU

DESIGNATION (ENGINE-1) ANTI ICE/ENG/1 (ENGINE-2) ANTI ICE/ENG/2

FIN

LOCATION

1DN1

X10

1DN2

W10

Subtask 30-21-00-010-089-A D.

Get Access (1) Open the fan cowls (Ref. AMM TASK 71-13-00-010-010) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR

4.

Procedure (Ref. Fig. Engine Air Intake Anti Ice Valve SHEET 1) Subtask 30-21-00-040-071-A A.

Deactivation of the Engine Air Intake Anti-Ice Valve (1) Lock the anti-ice valve (1) in the closed position. (a) Remove the lock pin (3) from the transportation bracket (2) in the valve (1). (b) Move the valve to the CL position. CAUTION: DO NOT TIGHTEN THE NUT TO MORE THAN 13 LBF.IN (0.15 M.DAN). IF YOU DO, YOU CAN CAUSE DAMAGE TO THE EQUIPMENT.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-020-C - Deactivation of the Engine Anti-Ice Valve in the CLOSED Position

1

Turn the nut (5) to the CL position. Do not exceed 13 lbf.in (0.15 m.daN) to turn the nut.

(c) Hold the valve in the CL (closed) position and install the lock pin (3) into the valve locking hole (4). 5.

Close-up Subtask 30-21-00-865-081-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL FOR FIN 1000EM1 122VU FOR FIN 1000EM2 122VU

DESIGNATION (ENGINE-1) ANTI ICE/ENG/1 (ENGINE-2) ANTI ICE/ENG/2

FIN

LOCATION

1DN1

X10

1DN2

W10

Subtask 30-21-00-410-091-A B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the fan cowls (Ref. AMM TASK 71-13-00-410-010) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR.

Subtask 30-21-00-860-085-A C.

Aircraft Maintenance Configuration (1) Remove the WARNING NOTICE(S). (2) Put a WARNING NOTICE(S) in the cockpit to tell persons which anti-ice valve is locked in the closed position. (3) Make an entry in the logbook.

Subtask 30-21-00-862-064-A D.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-803-A - Deactivation of the NAI Upper Valve with the Thrust Reverser Door Open

** ON A/C 301-349, 351-450, 500-600 TASK 30-21-00-040-803-A Deactivation of the NAI Upper Valve with the Thrust Reverser Door Open WARNING:

WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE) WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ, UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS NECESSARY.

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.

CAUTION:

MAKE SURE THAT THERE IS ALWAYS AN ANTI-ICE VALVE (UPPER OR LOWER) ACTIVATED DURING FLIGHT. IF THE TWO VALVES ARE DEACTIVATED, DAMAGE TO COMPONENTS CAN OCCUR.

FIN : 4010DN 1.

Reason for the Job MMEL 30-21-01B Engine Anti-Ice Valve

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

QTY 1 1 AR AR

DESIGNATION ACCESS PLATFORM 1M(3 FT) DRIVE 1/4 IN - SQUARE SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTION FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR, 452AR FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR, 462AR

C. Referenced Information REFERENCE (Ref. 71-00-00-860-833-A). (Ref. 71-13-00-010-802-A). (Ref. 71-13-00-410-802-A). (Ref. 78-30-00-040-805-A).

DESIGNATION Procedure to Prevent Engine Motoring Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Deactivation of the Thrust Reverser System for Ground Maintenance

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-803-A - Deactivation of the NAI Upper Valve with the Thrust Reverser Door Open REFERENCE DESIGNATION (Ref. 78-30-00-440-805-A). Reactivation of the Thrust Reverser System after Ground Maintenance (Ref. 78-36-00-010-802-A). Opening of the Thrust Reverser Cowl-Doors (Ref. 78-36-00-410-802-A). Closing of the Thrust Reverser Cowl-Doors Upper Anti-ice Valve with the Thrust Reverser Door Open SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-803-A - Deactivation of the NAI Upper Valve with the Thrust Reverser Door Open

ICN-GRAA320NEO-A-302101-G-51563-02333-A-001-01

A

MANUAL OVERRIDE INTERFACE

MANUAL OVERRIDE INTERFACE

SQUARE DRIVE HOLE

SQUARE DRIVE HOLE

UPPER ANTI-ICE VALVE

UPPER ANTI-ICE VALVE

UNLOCKED POSITION

LOCKED POSITION

A N_MM_302100_4_QAA0_01_01

Figure 30-21-00-991-90700-21-A / SHEET 1/1 - Upper Anti-ice Valve with the Thrust Reverser Door Open ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-803-A - Deactivation of the NAI Upper Valve with the Thrust Reverser Door Open

3.

Job Set-up Subtask 30-21-00-941-058-A A.

Safety Precautions (1) Do the procedure to prevent engine motoring (Ref. AMM TASK 71-00-00-860-833) .

Subtask 30-21-00-865-094-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL FOR FIN 4020KM1 122VU FOR FIN 4020KM2 122VU

DESIGNATION FIN (POWER PLANT-DEMOUNTABLE, ENG 1) ANTI ICE/ENG/1 1DN1 (POWER PLANT-DEMOUNTABLE, ENG 2) ANTI ICE/ENG/2 1DN2

LOCATION X10 W10

Subtask 30-21-00-010-091-A C.

Get Access (1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 438AR, 437AL (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 448AR, 447AL

Subtask 30-21-00-040-072-A D.

Deactivation of the Thrust Reverser for Maintenance 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) Do the deactivation of the thrust reverser system for maintenance (Ref. AMM TASK 78-30-00-040805) .

Subtask 30-21-00-010-092-A E.

Get Access (1) Open the right thrust reverser cowl-door (Ref. AMM TASK 78-36-00-010-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 452AR (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 462AR (2) Put an ACCESS PLATFORM 1M(3 FT) in position.

CAUTION:

REMOVE AND INSTALL PROTECTION COVERS AS NECESSARY TO PREVENT DAMAGE TO THE ENGINE AND ADJACENT COMPONENTS.

CAUTION:

WIPE CLEAN ALL PARTS AND TOOLS AS NECESSARY TO REMOVE UNWANTED DEBRIS AND PREVENT DAMAGE TO THE ENGINE.

4.

Procedure (Ref. Fig. Upper Anti-ice Valve with the Thrust Reverser Door Open SHEET 1)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-803-A - Deactivation of the NAI Upper Valve with the Thrust Reverser Door Open

Subtask 30-21-00-040-073-A A.

Deactivation of the NAI Upper Valve with the Thrust Reverser Door Open (1) Lock the NAI upper valve in the open position. CAUTION: WHEN YOU TURN THE MANUAL OVERRIDE INTERFACE, DO NOT APPLY A FORCE OF MORE THAN 115 LBF.IN (1.3 M.DAN). IF YOU DO NOT OBEY THIS INSTRUCTION, YOU CAN CAUSE INTERNAL DAMAGE TO THE NAI VALVE. (a) Put the DRIVE 1/4 IN - SQUARE in the square hole of the manual override interface. (b) Push in the DRIVE 1/4 IN - SQUARE and turn the interface 270 degrees counterclockwise. (c) Release the pressure on the interface. (d) Make sure that the manual override interface locks in position. (e) If you can see, make sure the notch is adjacent to the words "LOCKED OPEN". (f)

5.

Move the interface a small distance if it is not locked in position.

Close-up Subtask 30-21-00-410-095-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the access platform. (3) Close the right thrust reverser cowl-door (Ref. AMM TASK 78-36-00-410-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 452AR (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 462AR

Subtask 30-21-00-440-073-A B.

Do the reactivation of the thrust reverser system after maintenance (Ref. AMM TASK 78-30-00-440-805) .

Subtask 30-21-00-410-094-A C.

Close Access (1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR (2) Remove the WARNING NOTICE(S).

Subtask 30-21-00-865-095-A D.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL FOR FIN 4020KM1 122VU FOR FIN 4020KM2 122VU

DESIGNATION FIN (POWER PLANT-DEMOUNTABLE, ENG 1) ANTI ICE/ENG/1 1DN1 (POWER PLANT-DEMOUNTABLE, ENG 2) ANTI ICE/ENG/2 1DN2

LOCATION X10 W10

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-803-A - Deactivation of the NAI Upper Valve with the Thrust Reverser Door Open

Subtask 30-21-00-942-057-A E.

Put the aircraft back to its initial configuration. (1) Put a WARNING NOTICE(S) in position in the cockpit to tell persons that the NAI upper valve is deactivated in the open position. (2) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-803-A01 - Deactivation of the NAI Upper Valve

** ON A/C 301-349, 351-450, 500-600 TASK 30-21-00-040-803-A01 Deactivation of the NAI Upper Valve WARNING:

WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE) WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ, UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS NECESSARY.

WARNING:

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

CAUTION:

MAKE SURE THAT THERE IS ALWAYS AN ANTI-ICE VALVE (UPPER OR LOWER) ACTIVATED DURING FLIGHT. IF THE TWO VALVES ARE DEACTIVATED, DAMAGE TO COMPONENTS CAN OCCUR.

FIN : 4010DN 1.

Reason for the Job MMEL 30-21-01B Engine Anti-Ice Valve

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

QTY 1 AR 1 AR

DESIGNATION DRIVE 1/4 IN - SQUARE SAFETY CLIP - CIRCUIT BREAKER SCREWDRIVER WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 30-21-00-040-803-A). (Ref. 71-00-00-860-833-A). (Ref. 78-30-00-040-805-A). (Ref. 78-30-00-440-805-A). Upper Anti-Ice Valve

DESIGNATION Deactivation of the NAI Upper Valve with the Thrust Reverser Door Open Procedure to Prevent Engine Motoring Deactivation of the Thrust Reverser System for Ground Maintenance Reactivation of the Thrust Reverser System after Ground Maintenance

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-803-A01 - Deactivation of the NAI Upper Valve

A

UPPER ANTI-ICE VALVE ACCESS PLUG

ICN-GRAA320NEO-A-302101-G-51563-02327-A-002-01

B C D E

A N_MM_302100_4_QAC0_01_02

Figure 30-21-00-991-90200-21-A / SHEET 1/5 - Upper Anti-Ice Valve ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-803-A01 - Deactivation of the NAI Upper Valve

INNER FIXED STRUCTURE

UPPER ANTI-ICE VALVE ACCESS PLUG

UPSTREAM NAIV ACCESS PORT

CLOSE OPEN

TO LOCK OPEN VALVE: REMOVE CAP, PUSH AND ROTATE 270° COUNTERCLOCKWISE, REPLACE CAP

CAP

UPPER ANTI-ICE VALVE ACCESS PLUG

UPSTREAM NAIV ACCESS PORT

PU

TO LOCK OPEN VALVE: REMOVE CAP, PUSH AND ROTATE 270° COUNTERCLOCKWISE, REINSTALL CAP

SH

CLOSE OPEN

ICN-GRAA320NEO-A-302101-G-51563-03887-A-002-01

INNER FIXED STRUCTURE

CAP

B

01

NOTE: 01 UPPER ANTI-ICE VALVE ACCESS PLUG SHOWN IN THE OPEN POSITION N_MM_302100_4_QAC0_02_02

Figure 30-21-00-991-90200-21-A / SHEET 2/5 - Upper Anti-Ice Valve ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-803-A01 - Deactivation of the NAI Upper Valve

INNER FIXED STRUCTURE UPPER ANTI-ICE VALVE ACCESS PLUG

UPSTREAM NAIV ACCESS PORT

OPEN CLOSE

TO LOCK OPEN VALVE: REMOVE CAP, PUSH AND ROTATE 270° COUNTERCLOCKWISE, REPLACE CAP

CAP

UPSTREAM NAIV ACCESS PORT TO LOCK OPEN VALVE: REMOVE CAP, PUSH AND ROTATE 270° COUNTERCLOCKWISE, REINSTALL CAP

UPPER ANTI-ICE VALVE ACCESS PLUG PU

SH

OPEN CLOSE

ICN-GRAA320NEO-A-302101-G-51563-05522-A-001-01

INNER FIXED STRUCTURE

CAP

C

02

NOTE: 02 UPPER ANTI-ICE VALVE ACCESS PLUG SHOWN IN THE CLOSED POSITION N_MM_302100_4_QAC0_03_01

Figure 30-21-00-991-90200-21-A / SHEET 3/5 - Upper Anti-Ice Valve ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-803-A01 - Deactivation of the NAI Upper Valve

INNER FIXED STRUCTURE

MANUAL OVERRIDE INTERFACE

UPSTREAM NAIV ACCESS PORT TO LOCK OPEN VALVE: REMOVE CAP, PUSH AND ROTATE 270° COUNTERCLOCKWISE, REPLACE CAP

SQUARE DRIVE HOLE

ICN-GRAA320NEO-A-302101-G-51563-02332-A-003-01

INNER FIXED STRUCTURE

MANUAL OVERRIDE INTERFACE

UPSTREAM NAIV ACCESS PORT TO LOCK OPEN VALVE: REMOVE CAP, PUSH AND ROTATE 270° COUNTERCLOCKWISE, REINSTALL CAP

D

SQUARE DRIVE HOLE

03

NOTE: 03 ANTI-ICE VALVE ACCESS PLUG NOT SHOWN FOR CLARITY UPPER ANTI-ICE VALVE SHOWN IN THE UNLOCKED POSITION

N_MM_302100_4_QAC0_04_00

Figure 30-21-00-991-90200-21-A / SHEET 4/5 - Upper Anti-Ice Valve ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-803-A01 - Deactivation of the NAI Upper Valve

MANUAL OVERRIDE INTERFACE

INNER FIXED STRUCTURE

UPSTREAM NAIV ACCESS PORT TO LOCK OPEN VALVE: REMOVE CAP, PUSH AND ROTATE 270° COUNTERCLOCKWISE, REPLACE CAP

ICN-GRAA320NEO-A-302101-G-51563-05523-A-001-01

INNER FIXED STRUCTURE

SQUARE DRIVE HOLE

MANUAL OVERRIDE INTERFACE

UPSTREAM NAIV ACCESS PORT TO LOCK OPEN VALVE: REMOVE CAP, PUSH AND ROTATE 270° COUNTERCLOCKWISE, REINSTALL CAP

E

SQUARE DRIVE HOLE

04

NOTE: 04 ANTI-ICE VALVE ACCESS PLUG NOT SHOWN FOR CLARITY UPPER ANTI-ICE VALVE SHOWN IN THE LOCKED POSITION

N_MM_302100_4_QAC0_05_00

Figure 30-21-00-991-90200-21-A / SHEET 5/5 - Upper Anti-Ice Valve ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-803-A01 - Deactivation of the NAI Upper Valve

3.

Job Set-up Subtask 30-21-00-941-065-A A.

Safety Precautions (1) Do the procedure to prevent engine motoring (Ref. AMM TASK 71-00-00-860-833) .

Subtask 30-21-00-865-108-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL FOR FIN 4020KM1 122VU FOR FIN 4020KM2 122VU

DESIGNATION FIN (POWER PLANT-DEMOUNTABLE, ENG 1) ANTI ICE/ENG/1 1DN1 (POWER PLANT-DEMOUNTABLE, ENG 2) ANTI ICE/ENG/2 1DN2

LOCATION X10 W10

Subtask 30-21-00-040-083-A C.

Deactivation of the Thrust Reverser for Maintenance 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) Open the oil tank access-door on the left fan cowl-door and do the deactivation of the thrust reverser system for maintenance (Ref. AMM TASK 78-30-00-040-805) .

4.

Procedure (Ref. Fig. Upper Anti-Ice Valve) Subtask 30-21-00-040-093-A A.

Deactivation of the NAI Upper Valve (1) Remove the NAI upper valve access plug from the thrust reverser Inner Fixed Structure (IFS). NOTE: You can get access to the anti-ice valve manual override interface if you open the right fan cowls door and right thrust reverser door as an alternative (Ref. AMM TASK 30-21-00-040803) . (a) Put the applicable SCREWDRIVER in the access plug. CAUTION: DO NOT USE TOO MUCH FORCE WHEN YOU PUSH AND TURN THE ACCESS PLUG WITH THE SCREWDRIVER. IF YOU DO NOT OBEY THIS PRECAUTION, YOU CAN CAUSE DAMAGE TO THE ACCESS PLUG. (b) Carefully, push the access plug a small distance and turn the access plug approximately 90 degrees counterclockwise to release the access plug from the port sleeve. (c) Make sure that the "OPEN" mark on the access plug aligns with the "CAP" mark on the IFS. See detail B of the figure. (d) Remove the access plug from the port sleeve. NOTE: The access plug is attached to the IFS with a lanyard. (2) Lock the NAI upper valve in the open position.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-803-A01 - Deactivation of the NAI Upper Valve

CAUTION: WHEN YOU TURN THE MANUAL OVERRIDE INTERFACE, DO NOT APPLY A FORCE OF MORE THAN 115 LBF.IN (1.3 M.DAN). IF YOU DO NOT OBEY THIS INSTRUCTION, YOU CAN CAUSE INTERNAL DAMAGE TO THE NAI VALVE. (a) Put the DRIVE 1/4 IN - SQUARE in the square hole of the manual override interface. NOTE: Use an extension tool with the square drive if necessary. (b) Push in the DRIVE 1/4 IN - SQUARE and rotate the interface 270 degrees counterclockwise. (c) Release the pressure on the interface. (d) Make sure that the manual override interface locks in position. (e) Make sure that the indicator on the valve manual override interface aligns with the "LOCKED OPEN" indication on the thrust reverser IFS. (3) Install the NAI upper valve access plug back on the thrust reverser IFS. (a) Put the access plug in position on the port sleeve. (b) Make sure that the tabs on the access plug correctly engage the splines in the port sleeve. CAUTION: DO NOT USE TOO MUCH FORCE WHEN YOU PUSH AND TURN THE ACCESS PLUG WITH THE SCREWDRIVER. IF YOU DO NOT OBEY THIS PRECAUTION, YOU CAN CAUSE DAMAGE TO THE ACCESS PLUG. (c) Carefully, push the access plug a small distance with an applicable SCREWDRIVER and turn the access plug approximately 90 degrees clockwise to attach the access plug. (d) Make sure that the "CLOSE" mark on the access plug aligns with the "CAP" mark on the IFS. See detail C of the figure. (e) Make sure that you fully engage and correctly attach the access plug. 5.

Close-up Subtask 30-21-00-440-090-A A.

Do the reactivation of the thrust reverser system after maintenance and close the oil tank access-door on the left fan cowl-door (Ref. AMM TASK 78-30-00-440-805) .

Subtask 30-21-00-865-116-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL FOR FIN 4020KM1 122VU FOR FIN 4020KM2 122VU

DESIGNATION FIN (POWER PLANT-DEMOUNTABLE, ENG 1) ANTI ICE/ENG/1 1DN1 (POWER PLANT-DEMOUNTABLE, ENG 2) ANTI ICE/ENG/2 1DN2

LOCATION X10 W10

Subtask 30-21-00-942-053-A C.

Put the aircraft back to its initial configuration. (1) Remove the WARNING NOTICE(S). (2) Put a WARNING NOTICE(S) in position in the cockpit to tell persons that the NAI upper valve is deactivated in the open position. (3) Make an entry in the logbook.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-803-A01 - Deactivation of the NAI Upper Valve

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-010-C - Deactivation of the Engine Anti-Ice Valve in the OPEN Position

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 TASK 30-21-00-040-010-C Deactivation of the Engine Anti-Ice Valve in the OPEN Position 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.

1.

Reason for the Job MMEL 30-21-01C Engine Anti-Ice Valve

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 437AL, 438AR FOR 1000EM2 (ENGINE-2) 447AL, 448AR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A).

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power (Ref. 71-13-00-010-010-A). Opening of the Fan Cowls 437AL(447AL),438AR(448AR) (Ref. 71-13-00-410-010-A). Closing of the Fan Cowls 437AL(447AL),438AR(448AR) Engine Air Intake Anti Ice Valve SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-010-C - Deactivation of the Engine Anti-Ice Valve in the OPEN Position

INTAKE ANTI-ICE VALVE

B

A

INTAKE ANTI-ICE VALVE 1 TRANSPORTATION BRACKET 2

A 3 LOCK PIN

CL LOCK

OP

MANUAL OVERIDE REMOVE STOWED PIN-ROTATE TO DESIRED POSITION INSTALL PIN IN LOCKED POSITION

5 NUT

4 VALVE LOCKING-HOLE

B4318

B N_MM_302100_4_XAN0_01_01

Figure 30-21-00-991-15000-13-B / SHEET 1/1 - Engine Air Intake Anti Ice Valve ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-010-C - Deactivation of the Engine Anti-Ice Valve in the OPEN Position

3.

Job Set-up Subtask 30-21-00-861-062-A A.

Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Subtask 30-21-00-860-071-A B.

Safety Precautions (1) 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) Put a WARNING NOTICE(S) in position to tell persons not to operate the ENG/MODE selector switch and the ENG/MASTER 1(2) control switch. (2) On the ENG section 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) to tell persons not to energize FADEC 1(2). (3) On the ANTI ICE section of the panel 25VU: (a) Release the ANTI ICE/ENG 1(2) pushbutton switch (the ON legend goes off).

Subtask 30-21-00-865-082-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL FOR FIN 1000EM1 122VU FOR FIN 1000EM2 122VU

DESIGNATION (ENGINE-1) ANTI ICE/ENG/1 (ENGINE-2) ANTI ICE/ENG/2

FIN

LOCATION

1DN1

X10

1DN2

W10

Subtask 30-21-00-010-070-A D.

Get Access (1) Open the fan cowls (Ref. AMM TASK 71-13-00-010-010) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR

4.

Procedure (Ref. Fig. Engine Air Intake Anti Ice Valve SHEET 1) Subtask 30-21-00-040-058-A A.

Deactivation of the Engine Air Intake Anti-Ice Valve (1) Lock the anti-ice valve (1) in the open position. (a) Remove the lock pin (3) from the transportation bracket (2) in the valve (1). (b) Move the valve to the OP position. CAUTION: DO NOT TIGHTEN THE NUT TO MORE THAN 13 LBF.IN (0.15 M.DAN). IF YOU DO, YOU CAN CAUSE DAMAGE TO THE EQUIPMENT.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-010-C - Deactivation of the Engine Anti-Ice Valve in the OPEN Position

1

Turn the nut (5) to the OP position. Do not exceed 13 lbf.in (0.15 m.daN) to turn the nut.

(c) Hold the valve in the OP (open) position and install the lock pin (3) into the valve locking hole (4). (d) In the cockpit, on the ANTI-ICE section of the panel 25VU: · Push the ENG 1(2) pushbutton switch. 5.

Close-up Subtask 30-21-00-865-083-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL FOR FIN 1000EM1 122VU FOR FIN 1000EM2 122VU

DESIGNATION (ENGINE-1) ANTI ICE/ENG/1 (ENGINE-2) ANTI ICE/ENG/2

FIN

LOCATION

1DN1

X10

1DN2

W10

Subtask 30-21-00-410-072-A B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the fan cowls (Ref. AMM TASK 71-13-00-410-010) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR.

Subtask 30-21-00-860-072-A C.

Aircraft Maintenance Configuration (1) Remove the WARNING NOTICE(S). (2) On the ANTI ICE part of the panel 25VU, make sure that the ENG 1(2) pushbutton switch is pushed. (On the pushbutton switch, the ON legend is on). (3) Put a WARNING NOTICE(S) in position in the cockpit. This tells persons that the anti ice valve is deactivated in the open position. (4) Make an entry in the logbook.

Subtask 30-21-00-862-062-A D.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-804-A - Deactivation of the NAI Lower Valve with the Thrust Reverser Door Open

** ON A/C 301-349, 351-450, 500-600 TASK 30-21-00-040-804-A Deactivation of the NAI Lower Valve with the Thrust Reverser Door Open WARNING:

WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE) WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ, UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS NECESSARY.

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.

CAUTION:

MAKE SURE THAT THERE IS ALWAYS AN ANTI-ICE VALVE (UPPER OR LOWER) ACTIVATED DURING FLIGHT. IF THE TWO VALVES ARE DEACTIVATED, DAMAGE TO COMPONENTS CAN OCCUR.

FIN : 4011DN 1.

Reason for the Job MMEL 30-21-01B Engine Anti-Ice Valve

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

QTY 1 1 AR AR

DESIGNATION ACCESS PLATFORM 1M(3 FT) DRIVE 1/4 IN - SQUARE SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTION FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR, 452AR FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR, 462AR

C. Referenced Information REFERENCE (Ref. 71-00-00-860-833-A). (Ref. 71-13-00-010-802-A). (Ref. 71-13-00-410-802-A). (Ref. 78-30-00-040-805-A).

DESIGNATION Procedure to Prevent Engine Motoring Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Deactivation of the Thrust Reverser System for Ground Maintenance

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-804-A - Deactivation of the NAI Lower Valve with the Thrust Reverser Door Open REFERENCE DESIGNATION (Ref. 78-30-00-440-805-A). Reactivation of the Thrust Reverser System after Ground Maintenance (Ref. 78-36-00-010-802-A). Opening of the Thrust Reverser Cowl-Doors (Ref. 78-36-00-410-802-A). Closing of the Thrust Reverser Cowl-Doors Lower Anti-Ice Valve with the Thrust Reverser Door Open SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-804-A - Deactivation of the NAI Lower Valve with the Thrust Reverser Door Open

ICN-GRAA320NEO-A-302102-G-51563-02309-A-001-01

A

MANUAL OVERRIDE INTERFACE

MANUAL OVERRIDE INTERFACE

SQUARE DRIVE HOLE

SQUARE DRIVE HOLE

LOWER ANTI-ICE VALVE

LOWER ANTI-ICE VALVE

UNLOCKED POSITION

LOCKED POSITION

A

N_MM_302100_4_QAB0_01_01

Figure 30-21-00-991-90800-21-A / SHEET 1/1 - Lower Anti-Ice Valve with the Thrust Reverser Door Open ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-804-A - Deactivation of the NAI Lower Valve with the Thrust Reverser Door Open

3.

Job Set-up Subtask 30-21-00-941-060-A A.

Safety Precautions (1) Do the procedure to prevent engine motoring (Ref. AMM TASK 71-00-00-860-833) .

Subtask 30-21-00-865-098-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL FOR FIN 4020KM1 122VU FOR FIN 4020KM2 122VU

DESIGNATION FIN (POWER PLANT-DEMOUNTABLE, ENG 1) ANTI ICE/ENG/1 1DN1 (POWER PLANT-DEMOUNTABLE, ENG 2) ANTI ICE/ENG/2 1DN2

LOCATION X10 W10

Subtask 30-21-00-010-095-A C.

Get Access (1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR

Subtask 30-21-00-040-075-A D.

Deactivation of the Thrust Reverser System for Ground Maintenance 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) Open the oil tank access-door on the left fan cowl-door and do the deactivation of the thrust reverser system for ground maintenance (Ref. AMM TASK 78-30-00-040-805) .

Subtask 30-21-00-010-096-A E.

Get Access (1) Open the right thrust reverser cowl-door (Ref. AMM TASK 78-36-00-010-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 452AR (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 462AR (2) Put an ACCESS PLATFORM 1M(3 FT) in position.

4.

Procedure (Ref. Fig. Lower Anti-Ice Valve with the Thrust Reverser Door Open SHEET 1) Subtask 30-21-00-040-077-A A.

Deactivation of the NAI Lower Valve with the Thrust Reverser Door Open CAUTION:

INSTALL PROTECTION COVERS ON ALL THE OPENINGS IMMEDIATELY TO PREVENT DAMAGE TO THE ENGINE.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-804-A - Deactivation of the NAI Lower Valve with the Thrust Reverser Door Open

CAUTION:

WIPE CLEAN ALL PARTS AND TOOLS AS NECESSARY TO REMOVE UNWANTED DEBRIS AND PREVENT DAMAGE TO THE ENGINE.

(1) Lock the NAI lower valve in the open position. (a) Put the DRIVE 1/4 IN - SQUARE in the square hole of the manual override interface. CAUTION: WHEN YOU TURN THE MANUAL OVERRIDE INTERFACE, DO NOT APPLY A FORCE OF MORE THAN 115 LBF.IN (1.3 M.DAN). IF YOU DO NOT OBEY THIS INSTRUCTION, YOU CAN CAUSE INTERNAL DAMAGE TO THE NAI VALVE. (b) Push in the DRIVE 1/4 IN - SQUARE and rotate the interface 270 degrees counterclockwise. (c) Release the pressure on the interface. (d) Make sure that the manual override interface locks in position. (e) If you can see, make sure the notch is adjacent to the words "LOCKED OPEN". (f) 5.

Move the interface a small distance if it is not locked in position.

Close-up Subtask 30-21-00-410-098-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the access platform. (3) Close the right thrust reverser cowl-door (Ref. AMM TASK 78-36-00-410-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 452AR (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 462AR

Subtask 30-21-00-440-077-A B.

Do the reactivation of the thrust reverser system after maintenance (Ref. AMM TASK 78-30-00-440-805) .

Subtask 30-21-00-410-099-A C.

Close Access (1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-802) : (a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR (b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR (2) Remove the WARNING NOTICE(S).

Subtask 30-21-00-865-099-A D.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL FOR FIN 4020KM1 122VU FOR FIN 4020KM2 122VU

DESIGNATION FIN (POWER PLANT-DEMOUNTABLE, ENG 1) ANTI ICE/ENG/1 1DN1 (POWER PLANT-DEMOUNTABLE, ENG 2) ANTI ICE/ENG/2 1DN2

LOCATION X10 W10

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-804-A - Deactivation of the NAI Lower Valve with the Thrust Reverser Door Open

Subtask 30-21-00-942-058-A E.

Put the aircraft back to its initial configuration. (1) Remove the WARNING NOTICE(S). (2) Put a WARNING NOTICE(S) in position in the cockpit to tell persons that the NAI lower valve is deactivated in the open position. (3) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-804-A01 - Deactivation of the NAI Lower Valve

** ON A/C 301-349, 351-450, 500-600 TASK 30-21-00-040-804-A01 Deactivation of the NAI Lower Valve WARNING:

WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE) WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ, UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS NECESSARY.

WARNING:

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

CAUTION:

MAKE SURE THAT THERE IS ALWAYS AN ANTI-ICE VALVE (UPPER OR LOWER) ACTIVATED DURING FLIGHT. IF THE TWO VALVES ARE DEACTIVATED, DAMAGE TO COMPONENTS CAN OCCUR.

FIN : 4011DN 1.

Reason for the Job MMEL 30-21-01B Engine Anti-Ice Valve

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

QTY 1 AR 1 AR

DESIGNATION DRIVE 1/4 IN - SQUARE SAFETY CLIP - CIRCUIT BREAKER SCREWDRIVER WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 30-21-00-040-804-A). (Ref. 71-00-00-860-833-A). (Ref. 78-30-00-040-805-A). (Ref. 78-30-00-440-805-A). Lower Anti-Ice Valve

DESIGNATION Deactivation of the NAI Lower Valve with the Thrust Reverser Door Open Procedure to Prevent Engine Motoring Deactivation of the Thrust Reverser System for Ground Maintenance Reactivation of the Thrust Reverser System after Ground Maintenance

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-804-A01 - Deactivation of the NAI Lower Valve

A

LOWER ANTI-ICE VALVE ACCESS PLUG

ICN-GRAA320NEO-A-302102-G-51563-02315-A-003-01

B C D E

A N_MM_302100_4_QAD0_01_02

Figure 30-21-00-991-90300-21-A / SHEET 1/5 - Lower Anti-Ice Valve ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-804-A01 - Deactivation of the NAI Lower Valve

INNER FIXED STRUCTURE

LOWER ANTI-ICE VALVE ACCESS PLUG OPEN

CLOSE

DOWNSTREAM NAIV ACCESS PORT

CAP

TO LOCK OPEN VALVE: REMOVE CAP, PUSH AND ROTATE 270° COUNTERCLOCKWISE, REPLACE CAP

LOWER ANTI-ICE VALVE ACCESS PLUG

SH

PU

DOWNSTREAM NAIV ACCESS PORT

CLOSE OPEN

ICN-GRAA320NEO-A-302102-G-51563-03888-A-002-01

INNER FIXED STRUCTURE

CAP

TO LOCK OPEN VALVE: REMOVE CAP, PUSH AND ROTATE 270° COUNTERCLOCKWISE, REINSTALL CAP

B

01

NOTE: 01 LOWER ANTI-ICE VALVE ACCESS PLUG SHOWN IN THE OPEN POSITION N_MM_302100_4_QAD0_02_03

Figure 30-21-00-991-90300-21-A / SHEET 2/5 - Lower Anti-Ice Valve ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-804-A01 - Deactivation of the NAI Lower Valve

INNER FIXED STRUCTURE

LOWER ANTI-ICE VALVE ACCESS PLUG

OPEN CLOSE

DOWNSTREAM NAIV ACCESS PORT

CAP

TO LOCK OPEN VALVE: REMOVE CAP, PUSH AND ROTATE 270° COUNTERCLOCKWISE, REPLACE CAP

PU

SH

OPEN

DOWNSTREAM NAIV ACCESS PORT

LOWER ANTI-ICE VALVE ACCESS PLUG

CLOSE

ICN-GRAA320NEO-A-302102-G-51563-05526-A-001-01

INNER FIXED STRUCTURE

CAP

TO LOCK OPEN VALVE: REMOVE CAP, PUSH AND ROTATE 270° COUNTERCLOCKWISE, REINSTALL CAP

C

02

NOTE: 02 LOWER ANTI-ICE VALVE ACCESS PLUG SHOWN IN THE CLOSED POSITION N_MM_302100_4_QAD0_03_01

Figure 30-21-00-991-90300-21-A / SHEET 3/5 - Lower Anti-Ice Valve ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-804-A01 - Deactivation of the NAI Lower Valve

INNER FIXED STRUCTURE

MANUAL OVERRIDE INTERFACE

DOWNSTREAM NAIV ACCESS PORT

SQUARE DRIVE HOLE

TO LOCK OPEN VALVE: REMOVE CAP, PUSH AND ROTATE 270° COUNTERCLOCKWISE, REPLACE CAP

MANUAL OVERRIDE INTERFACE ICN-GRAA320NEO-A-302102-G-51563-02316-A-005-01

INNER FIXED STRUCTURE

DOWNSTREAM NAIV ACCESS PORT TO LOCK OPEN VALVE: REMOVE CAP, PUSH AND ROTATE 270° COUNTERCLOCKWISE, REINSTALL CAP

D

SQUARE DRIVE HOLE

03

NOTE: 03 ANTI-ICE VALVE ACCESS PLUG NOT SHOWN FOR CLARITY LOWER ANTI-ICE VALVE SHOWN IN THE UNLOCKED POSITION

N_MM_302100_4_QAD0_04_00

Figure 30-21-00-991-90300-21-A / SHEET 4/5 - Lower Anti-Ice Valve ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-804-A01 - Deactivation of the NAI Lower Valve

MANUAL OVERRIDE INTERFACE INNER FIXED STRUCTURE

DOWNSTREAM NAIV ACCESS PORT

SQUARE DRIVE HOLE

TO LOCK OPEN VALVE: REMOVE CAP, PUSH AND ROTATE 270° COUNTERCLOCKWISE, REPLACE CAP

MANUAL OVERRIDE INTERFACE ICN-GRAA320NEO-A-302102-G-51563-05527-A-001-01

INNER FIXED STRUCTURE

DOWNSTREAM NAIV ACCESS PORT TO LOCK OPEN VALVE: REMOVE CAP, PUSH AND ROTATE 270° COUNTERCLOCKWISE, REINSTALL CAP

E

SQUARE DRIVE HOLE

04

NOTE: 04 ANTI-ICE VALVE ACCESS PLUG NOT SHOWN FOR CLARITY LOWER ANTI-ICE VALVE SHOWN IN THE LOCKED POSITION

N_MM_302100_4_QAD0_05_00

Figure 30-21-00-991-90300-21-A / SHEET 5/5 - Lower Anti-Ice Valve ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-804-A01 - Deactivation of the NAI Lower Valve

3.

Job Set-up Subtask 30-21-00-941-068-A A.

Safety Precautions (1) Do the procedure to prevent engine motoring (Ref. AMM TASK 71-00-00-860-833) .

Subtask 30-21-00-865-114-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL FOR FIN 4020KM1 122VU FOR FIN 4020KM2 122VU

DESIGNATION FIN (POWER PLANT-DEMOUNTABLE, ENG 1) ANTI ICE/ENG/1 1DN1 (POWER PLANT-DEMOUNTABLE, ENG 2) ANTI ICE/ENG/2 1DN2

LOCATION X10 W10

Subtask 30-21-00-040-090-A C.

Deactivation of the Thrust Reverser for Maintenance 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) Open the oil tank access-door on the left fan cowl-door and do the deactivation of the thrust reverser system for maintenance (Ref. AMM TASK 78-30-00-040-805) .

4.

Procedure (Ref. Fig. Lower Anti-Ice Valve) Subtask 30-21-00-040-092-A A.

Deactivation of the NAI Lower Valve (1) Remove the NAI lower valve access plug from the thrust reverser Inner Fixed Structure (IFS). NOTE: You can get access to the anti-ice valve manual override interface if you open the right fan cowl door and right thrust reverser door as an alternative (Ref. AMM TASK 30-21-00-040804) . (a) Put the applicable SCREWDRIVER in the access plug. CAUTION: DO NOT USE TOO MUCH FORCE WHEN YOU PUSH AND TURN THE ACCESS PLUG WITH THE SCREWDRIVER. IF YOU DO NOT OBEY THIS PRECAUTION, YOU CAN CAUSE DAMAGE TO THE ACCESS PLUG. (b) Carefully, push the access plug a small distance and turn the access plug approximately 90 degrees counterclockwise to release the access plug from the port sleeve. (c) Make sure that the "OPEN" mark on the access plug aligns with the "CAP" mark on the IFS. See detail B of the figure. (d) Remove the access plug from the port sleeve. NOTE: The access plug is attached to the IFS with a lanyard. (2) Lock the NAI lower valve in the open position.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-804-A01 - Deactivation of the NAI Lower Valve

CAUTION: WHEN YOU TURN THE MANUAL OVERRIDE INTERFACE, DO NOT APPLY A FORCE OF MORE THAN 115 LBF.IN (1.3 M.DAN). IF YOU DO NOT OBEY THIS INSTRUCTION, YOU CAN CAUSE INTERNAL DAMAGE TO THE NAI VALVE. (a) Put the DRIVE 1/4 IN - SQUARE in the square hole of the manual override interface. NOTE: Use an extension tool with the square drive if necessary. (b) Push in the DRIVE 1/4 IN - SQUARE and turn the interface 270 degrees counterclockwise. (c) Release the pressure on the interface. (d) Make sure that the manual override interface locks in position. (e) Make sure that the indicator on the valve manual override interface aligns with the "LOCKED OPEN" indication on the thrust reverser IFS. (3) Install the NAI lower valve access plug back on the thrust reverser IFS. (a) Put the access plug in position on the port sleeve. (b) Make sure that the tabs on the access plug correctly engage the splines in the port sleeve. CAUTION: DO NOT USE TOO MUCH FORCE WHEN YOU PUSH AND TURN THE ACCESS PLUG WITH THE SCREWDRIVER. IF YOU DO NOT OBEY THIS PRECAUTION, YOU CAN CAUSE DAMAGE TO THE ACCESS PLUG. (c) Carefully, push the access plug a small distance with an applicable SCREWDRIVER and turn the access plug approximately 90 degrees clockwise to attach the access plug. (d) Make sure that the "CLOSE" mark on the access plug aligns with the "CAP" mark on the IFS. See detail C of the figure. (e) Make sure that you fully engage and correctly attach the access plug. 5.

Close-up Subtask 30-21-00-440-089-A A.

Do the reactivation of the thrust reverser system after maintenance and close the oil tank access-door on the left fan cowl-door (Ref. AMM TASK 78-30-00-440-805) .

Subtask 30-21-00-865-115-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL FOR FIN 4020KM1 122VU FOR FIN 4020KM2 122VU

DESIGNATION FIN (POWER PLANT-DEMOUNTABLE, ENG 1) ANTI ICE/ENG/1 1DN1 (POWER PLANT-DEMOUNTABLE, ENG 2) ANTI ICE/ENG/2 1DN2

LOCATION X10 W10

Subtask 30-21-00-942-055-A C.

Put the aircraft back to its initial configuration. (1) Remove the WARNING NOTICE(S). (2) Put a WARNING NOTICE(S) in position in the cockpit to tell persons that the NAI lower valve is deactivated in the open position. (3) Make an entry in the logbook.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-804-A01 - Deactivation of the NAI Lower Valve

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-809-A - Deactivation of the Applicable Antiice Valve after a NAI SYSTEM FAILED CLOSED Fault

** ON A/C 301-349, 351-450, 500-600 TASK 30-21-00-040-809-A Deactivation of the Applicable Anti-ice Valve after a NAI SYSTEM FAILED CLOSED Fault WARNING:

WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE) WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ, UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS NECESSARY.

FIN : 4010DN , 4011DN 1.

Reason for the Job MMEL 30-21-01B Engine Anti-Ice Valve

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A). (Ref. 30-21-00-040-803-A). (Ref. 30-21-00-040-803-A-01). (Ref. 30-21-00-040-804-A). (Ref. 30-21-00-040-804-A-01). (Ref. 30-21-00-440-803-A). (Ref. 30-21-00-440-803-A-01). (Ref. 30-21-00-710-002-A). (Ref. 71-00-00-860-833-A). (Ref. 78-30-00-040-805-A). (Ref. 78-30-00-440-805-A).

3.

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power Deactivation of the NAI Upper Valve with the Thrust Reverser Door Open Deactivation of the NAI Upper Valve Deactivation of the NAI Lower Valve with the Thrust Reverser Door Open Deactivation of the NAI Lower Valve Reactivation of the NAI Upper Valve with the Thrust Reverser Door Open Reactivation of the NAI Upper Valve Operational Check of the Engine-Air-Intake Ice-Protection System (with the Engines in operation) Procedure to Prevent Engine Motoring Deactivation of the Thrust Reverser System for Ground Maintenance Reactivation of the Thrust Reverser System after Ground Maintenance

Job Set-up Subtask 30-21-00-861-083-A A.

Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-809-A - Deactivation of the Applicable Antiice Valve after a NAI SYSTEM FAILED CLOSED Fault

Subtask 30-21-00-941-070-A B.

Safety Precautions (1) Do the procedure to prevent engine motoring (Ref. AMM TASK 71-00-00-860-833) .

Subtask 30-21-00-865-121-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL FOR FIN 4020KM1 122VU FOR FIN 4020KM2 122VU

DESIGNATION FIN (POWER PLANT-DEMOUNTABLE, ENG 1) ANTI ICE/ENG/1 1DN1 (POWER PLANT-DEMOUNTABLE, ENG 2) ANTI ICE/ENG/2 1DN2

LOCATION X10 W10

Subtask 30-21-00-040-095-A D.

Deactivation of the Thrust Reverser for Maintenance 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) Do the deactivation of the thrust reverser system for ground maintenance (Ref. AMM TASK 78-3000-040-805) .

4.

Procedure Subtask 30-21-00-040-096-A A.

Deactivate the Applicable Anti-Ice Valve after a NAI SYSTEM FAILED CLOSED fault CAUTION:

REMOVE AND INSTALL PROTECTION COVERS AS NECESSARY TO PREVENT DAMAGE TO THE ENGINE AND ADJACENT COMPONENTS.

CAUTION:

WIPE CLEAN ALL PARTS AND TOOLS AS NECESSARY TO REMOVE UNWANTED DEBRIS AND PREVENT DAMAGE TO THE ENGINE.

(1) Deactivate the upper nacelle anti-ice valve (Ref. AMM TASK 30-21-00-040-803) . (2) Do the operational test of the engine air intake ice protection (Ref. AMM TASK 30-21-00-710-002) . (3) If the maintenance message does not show, keep the upper anti-ice valve in the deactivated position and continue to step 4.A.(7). (4) If the maintenance message shows, do the following : (a) Reactivate the upper nacelle anti-ice valve (Ref. AMM TASK 30-21-00-440-803) . (b) Deactivate the lower nacelle anti-ice valve (Ref. AMM TASK 30-21-00-040-804) . (5) Make an entry in the log book. 5.

Close-up Subtask 30-21-00-942-060-A A.

Put the aircraft back to its initial configuration. (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the WARNING NOTICE(S).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-21-00-040-809-A - Deactivation of the Applicable Antiice Valve after a NAI SYSTEM FAILED CLOSED Fault

Subtask 30-21-00-440-092-A B.

Do the reactivation of the thrust reverser system after ground maintenance (Ref. AMM TASK 78-30-00440-805) .

Subtask 30-21-00-865-122-A C.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL FOR FIN 4020KM1 122VU FOR FIN 4020KM2 122VU

DESIGNATION FIN (POWER PLANT-DEMOUNTABLE, ENG 1) ANTI ICE/ENG/1 1DN1 (POWER PLANT-DEMOUNTABLE, ENG 2) ANTI ICE/ENG/2 1DN2

LOCATION X10 W10

Subtask 30-21-00-862-084-A D.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-31-00-040-001-A - Check of the Operation of the Probe Heating Channel

** ON A/C ALL TASK 30-31-00-040-001-A Check of the Operation of the Probe Heating Channel WARNING:

DO NOT TOUCH THE PROBES IMMEDIATELY AFTER THE TEST. THEY ARE HOT AND CAN BURN YOU.

CAUTION:

REMOVE THE PROTECTIVE COVERS FROM THE PROBES BEFORE YOU DO THE TEST.

CAUTION:

DO NOT CONTINUE THE TEST FOR MORE THAN ONE MINUTE TO PREVENT DAMAGE TO THE PROBES.

FIN : 6DA1 , 6DA2 , 6DA3 1.

Reason for the Job MMEL 30-31-01A Probe Heat Computer (PHC) Check of the associated heating channel.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

QTY AR AR AR

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A).

3.

DESIGNATION ACCESS PLATFORM 3M (10 FT) THERMOMETER WARNING NOTICE(S)

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure

Job Set-up Subtask 30-31-00-941-052-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Put an ACCESS PLATFORM 3M (10 FT) in position near each probe. (3) On the panel 25VU:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-31-00-040-001-A - Check of the Operation of the Probe Heating Channel

· make sure that the PROBE/WINDOW HEAT pushbutton switch is released (the ON legend is off). (4) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) . WARNING:

4.

DO NOT TOUCH THE PROBES IMMEDIATELY AFTER THE TEST. THEY ARE HOT AND CAN BURN YOU.

Procedure Subtask 30-31-00-860-072-A A.

Aircraft Maintenance Configuration (1) On the ENG panel 115VU: (a) Put a WARNING NOTICE(S) to tell persons that a flight configuration will be simulated.

Subtask 30-31-00-865-058-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL DESIGNATION 49VU L/G/LGCIU/SYS1/NORM 49VU FWS/FWC1/SPLY 121VU HYDRAULIC/LGCIU/SYS2 121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 121VU EIS/FWC2/SPLY FOR FIN 6DA1 (PHC-1) 49VU ANTI ICE/PROBES/AOA/1 49VU ANTI ICE/PROBES/PHC/1 49VU ANTI ICE/PROBES/PITOT/1 122VU ANTI ICE/PROBES/1/STATIC 122VU ANTI ICE/PROBES/1/TAT FOR FIN 6DA2 (PHC-2) 122VU ANTI ICE/PROBES/2/TAT 122VU ANTI ICE/PROBES/2/PITOT 122VU ANTI ICE/PROBES/2/AOA 122VU ANTI ICE/PROBES/PHC/2 122VU ANTI ICE/PROBES/2/STATIC FOR FIN 6DA3 (PHC-3) 122VU ANTI ICE/PROBES/PHC/3 122VU ANTI ICE/PROBES/3/PITOT 122VU ANTI ICE/PROBES/3/AOA 122VU ANTI ICE/PROBES/3/STATIC

FIN 1GA 3WW 2GA 52GA 2WW

C09 F01 Q35 Q34 Q07

LOCATION

4DA1 2DA1 3DA1 5DA1 1DA1

D04 D03 D02 Z13 Z12

1DA2 3DA2 4DA2 2DA2 5DA2

Y15 Y14 Y13 Y12 Y11

2DA3 3DA3 4DA3 5DA3

Y16 Z16 Z15 Z14

Subtask 30-31-00-040-050-A CAUTION:

C.

DO NOT CONTINUE THE TEST FOR MORE THAN ONE MINUTE TO PREVENT DAMAGE TO THE PROBES.

Check of the Probe Heating ACTION 1.On the overhead circuit-breaker panel 49VU: · Open the circuit breaker 1GA. On the rear circuit-breaker panel 121VU:

RESULT On the lower ECAM DU: · The TAT temperature increases. On the upper ECAM DU:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-31-00-040-001-A - Check of the Operation of the Probe Heating Channel

ACTION · Open the circuit breaker 52GA · Open the circuit breaker 2GA.

RESULT · Make sure that no warning message related to the probes comes into view. NOTE: Ignore the aural warning message.

2.On the panel 49VU: · Close the circuit breaker 1GA. On the panel 121VU: · Close the circuit breaker 52GA · Close the circuit breaker 2GA. 3.Make sure that the heating of the probes related to the unserviceable PHC, is in operation. For 6DA1 PHC-1 - 7DA1, 8DA1, 9DA1, 3FP1, 11FP1 For 6DA2 PHC-2 - 7DA2, 8DA2, 9DA2, 3FP2, 11FP2 For 6DA3 PHC-3 - 7DA3, 8DA3, 9DA3, 3FP3.

On the lower ECAM DU: · The TAT temperature decreases.

On the upper ECAM DU: · make sure that no warning message related to the probes comes into view. · Make sure that the related probes are hot.

NOTE: You can use a THERMOMETER which can read up to 400 deg.C (752.00 deg.F) to do this check. On the lower ECAM DU: · Make sure that no status message comes into view.

On the panel 49VU: · Open and close the circuit breaker 3WW. On the panel 121VU: · Open and close the circuit breaker 2WW. 5.

On the lower ECAM DU, if the AC GEN indication comes into view: · It goes out at the next IDG connection. On the lower ECAM DU, if the AIR BLEED indication comes into view: · Do the step that follows. On the lower ECAM DU: · The AIR BLEED indication goes out of view.

Close-up Subtask 30-31-00-860-063-A A.

Put the aircraft back to its initial configuration. (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (3) Make an entry in the logbook. (4) Remove the warning notice(s).

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-31-00-040-002-A - Check of the ADRS, Heaters and Failure Alerts related to the Probes

** ON A/C ALL TASK 30-31-00-040-002-A Check of the ADRS, Heaters and Failure Alerts related to the Probes WARNING:

DO NOT TOUCH THE PROBES IMMEDIATELY AFTER THE TEST. THEY ARE HOT AND CAN BURN YOU.

CAUTION:

REMOVE THE PROTECTIVE COVERS FROM THE PROBES BEFORE YOU DO THE TEST.

1.

Reason for the Job MMEL 30-31-01B Probe Heat Computer (PHC) MMEL 30-31-01C Probe Heat Computer (PHC) MMEL 30-31-03B Static Ports Heater MMEL 30-31-03C Static Ports Heater MMEL 30-31-03D Static Ports Heater MMEL 30-31-04A Angle of Attack (AOA) Probes Heating MMEL 30-31-04B Angle of Attack (AOA) Probes Heating MMEL 30-31-04C Angle of Attack (AOA) Probes Heating MMEL 30-31-02A Pitot Heater MMEL 30-31-02B Pitot Heater MMEL 30-31-02C Pitot Heater

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

QTY AR AR AR

DESIGNATION SAFETY BARRIER(S) SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-31-00-040-002-A - Check of the ADRS, Heaters and Failure Alerts related to the Probes REFERENCE (Ref. 24-41-00-862-002-A-02). (Ref. 30-31-00-710-001-A). (Ref. 31-32-00-860-009-A). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 32-00-00-481-001-A). (Ref. 32-00-00-860-001-A). (Ref. 32-00-00-860-001-A-01). (Ref. 32-00-00-860-002-A). (Ref. 32-00-00-860-002-A-01). (Ref. 34-10-00-860-002-A). (Ref. 34-10-00-860-005-A). (Ref. 34-13-00-740-003-A). 3.

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Operational Test of the Probe Ice Protection Procedure to Get Access to the SYSTEM REPORT/TEST/L/G Page EIS Start Procedure EIS Stop Procedure Installation of the Safety Devices on the Landing Gears Flight Configuration Precautions with Electrical Power Flight Configuration Precautions without Electrical Power Ground Configuration after Flight Configuration with Electrical Power Ground Configuration after Flight Configuration without Electrical Power ADIRS Start Procedure ADIRS Stop Procedure SYSTEM TEST of the ADR

Job Set-up Subtask 30-31-00-861-065-A A.

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

Subtask 30-31-00-860-086-A B.

Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001)

Subtask 30-31-00-941-054-A C.

Safety Precautions (1) On the OVERHEAD CTL & IND Panel 25VU: · make sure that the PROBE/WINDOW HEAT pushbutton switch is released (the ON legend is off).

4.

Procedure Subtask 30-31-00-710-057-A A.

Test (1) Do an operational test of the available probe ice protection systems (Ref. AMM TASK 30-31-00-710001) . (2) Do a SYSTEM TEST of the ADR (Ref. AMM TASK 34-13-00-740-003) .

Subtask 30-31-00-750-051-A B.

Check of ECAM Warning Messages (1) Do a check of the ECAM warning messages related to the systems that operate correctly. NOTE: - If CAPT pitot heater system is operative, do the checks in steps C thru L. - If F/O pitot heater system is operative, do the checks in steps M thru V. - If STBY pitot heater system is operative, do the checks in steps W thru AF. Then continue the procedure from the step AG.

Subtask 30-31-00-865-080-A C.

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

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-31-00-040-002-A - Check of the ADRS, Heaters and Failure Alerts related to the Probes

PANEL DESIGNATION FOR FIN 6DA1 (PHC-1) 49VU ANTI ICE/PROBES/AOA/1 49VU ANTI ICE/PROBES/PITOT/1

FIN 4DA1 3DA1

LOCATION D04 D02

Subtask 30-31-00-869-083-A D.

Check (1) On the upper ECAM DU: · Make sure that the ANTI ICE CAPT PITOT ANTI ICE CAPT AOA indications come into view.

Subtask 30-31-00-865-081-A E.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 6DA1 (PHC-1) 49VU ANTI ICE/PROBES/AOA/1 49VU ANTI ICE/PROBES/PITOT/1

FIN 4DA1 3DA1

LOCATION D04 D02

Subtask 30-31-00-865-082-A F.

Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 6DA1 (PHC-1) 122VU ANTI ICE/PROBES/1/STATIC

FIN 5DA1

LOCATION Z13

Subtask 30-31-00-869-084-A G. Check (1) On the upper ECAM DU: · make sure that the ANTI ICE CAPT L(R) STAT indication comes into view. Subtask 30-31-00-865-083-A H.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 6DA1 (PHC-1) 122VU ANTI ICE/PROBES/1/STATIC

FIN 5DA1

LOCATION Z13

Subtask 30-31-00-865-084-A J.

Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 6DA1 (PHC-1) 49VU ANTI ICE/PROBES/AOA/1 49VU ANTI ICE/PROBES/PITOT/1 122VU ANTI ICE/PROBES/1/STATIC

FIN 4DA1 3DA1 5DA1

LOCATION D04 D02 Z13

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-31-00-040-002-A - Check of the ADRS, Heaters and Failure Alerts related to the Probes

Subtask 30-31-00-869-085-A K.

Check (1) On the upper ECAM DU: · Make sure that the ANTI ICE CAPT PROBES indication comes into view.

Subtask 30-31-00-865-085-A L.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 6DA1 (PHC-1) 49VU ANTI ICE/PROBES/AOA/1 49VU ANTI ICE/PROBES/PITOT/1 122VU ANTI ICE/PROBES/1/STATIC

FIN 4DA1 3DA1 5DA1

LOCATION D04 D02 Z13

Subtask 30-31-00-865-086-A M. Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 6DA2 (PHC-2) 122VU ANTI ICE/PROBES/2/PITOT 122VU ANTI ICE/PROBES/2/AOA

FIN 3DA2 4DA2

LOCATION Y14 Y13

Subtask 30-31-00-869-086-A N.

Check (1) On the upper ECAM DU: · Make sure that the ANTI ICE F/O PITOT ANTI ICE F/O AOA indications come into view.

Subtask 30-31-00-865-087-A P.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 6DA2 (PHC-2) 122VU ANTI ICE/PROBES/2/PITOT 122VU ANTI ICE/PROBES/2/AOA

FIN 3DA2 4DA2

LOCATION Y14 Y13

Subtask 30-31-00-865-088-A Q. Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 6DA2 (PHC-2) 122VU ANTI ICE/PROBES/2/STATIC

FIN 5DA2

LOCATION Y11

Subtask 30-31-00-869-087-A R.

Check (1) On the upper ECAM DU: · Make sure that the

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-31-00-040-002-A - Check of the ADRS, Heaters and Failure Alerts related to the Probes ANTI ICE F/O L(R) STAT indication comes into view. Subtask 30-31-00-865-089-A S.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 6DA2 (PHC-2) 122VU ANTI ICE/PROBES/2/STATIC

FIN 5DA2

LOCATION Y11

Subtask 30-31-00-865-090-A T.

Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 6DA2 (PHC-2) 122VU ANTI ICE/PROBES/2/PITOT 122VU ANTI ICE/PROBES/2/AOA 122VU ANTI ICE/PROBES/2/STATIC

FIN 3DA2 4DA2 5DA2

LOCATION Y14 Y13 Y11

Subtask 30-31-00-869-088-A U.

Check (1) On the upper ECAM DU: · make sure that the ANTI ICE F/O PROBES indication comes into view.

Subtask 30-31-00-865-091-A V.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 6DA2 (PHC-2) 122VU ANTI ICE/PROBES/2/PITOT 122VU ANTI ICE/PROBES/2/AOA 122VU ANTI ICE/PROBES/2/STATIC

FIN 3DA2 4DA2 5DA2

LOCATION Y14 Y13 Y11

Subtask 30-31-00-865-092-A W. Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 6DA3 (PHC-3) 122VU ANTI ICE/PROBES/3/PITOT 122VU ANTI ICE/PROBES/3/AOA

FIN 3DA3 4DA3

LOCATION Z16 Z15

Subtask 30-31-00-869-089-A X.

Check (1) On the upper ECAM DU: · Make sure that the ANTI ICE STBY PITOT ANTI ICE STBY AOA indications come into view.

Subtask 30-31-00-865-093-A

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-31-00-040-002-A - Check of the ADRS, Heaters and Failure Alerts related to the Probes

Y.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 6DA3 (PHC-3) 122VU ANTI ICE/PROBES/3/PITOT 122VU ANTI ICE/PROBES/3/AOA

FIN 3DA3 4DA3

LOCATION Z16 Z15

Subtask 30-31-00-865-094-A AA. Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 6DA3 (PHC-3) 122VU ANTI ICE/PROBES/3/STATIC

FIN 5DA3

LOCATION Z14

Subtask 30-31-00-869-090-A AB. Check (1) On the upper ECAM DU: · Make sure that the ANTI ICE STBY L(R) STAT indication comes into view. Subtask 30-31-00-865-095-A AC. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 6DA3 (PHC-3) 122VU ANTI ICE/PROBES/3/STATIC

FIN 5DA3

LOCATION Z14

Subtask 30-31-00-865-096-A AD. Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 6DA3 (PHC-3) 122VU ANTI ICE/PROBES/3/PITOT 122VU ANTI ICE/PROBES/3/AOA 122VU ANTI ICE/PROBES/3/STATIC

FIN 3DA3 4DA3 5DA3

LOCATION Z16 Z15 Z14

Subtask 30-31-00-869-091-A AE. Check (1) On the upper ECAM DU: · make sure that the ANTI ICE STBY PROBES indication comes into view. Subtask 30-31-00-865-097-A AF. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 6DA3 (PHC-3) 122VU ANTI ICE/PROBES/3/PITOT 122VU ANTI ICE/PROBES/3/AOA

FIN 3DA3 4DA3

LOCATION Z16 Z15

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-31-00-040-002-A - Check of the ADRS, Heaters and Failure Alerts related to the Probes PANEL 122VU

DESIGNATION ANTI ICE/PROBES/3/STATIC

FIN 5DA3

LOCATION Z14

Subtask 30-31-00-941-066-A AG. Safety Precautions 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: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/ OR EQUIPMENT. (1) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations. (2) Make sure that the ground safety locks are on the landing gear (Ref. AMM TASK 32-00-00-481001) . (3) On the right-center instrument panel 400VU: · Make sure that the landing-gear control-lever 6GA is in the DOWN position · Put a WARNING NOTICE(S) in position to tell persons not to operate the landing gear. Subtask 30-31-00-869-116-A AH. Flight Configuration Precautions (1) Do the flight configuration precautions procedure (Ref. AMM TASK 32-00-00-860-001) . Subtask 30-31-00-865-098-A AJ. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged: PANEL 121VU 121VU 122VU 122VU

DESIGNATION COM NAV/RAD ALTM/2 COM NAV/RAD ALTM/1 ANTI ICE/PROBES/2/TAT ANTI ICE/PROBES/1/TAT

FIN 1SA2 1SA1 1DA2 1DA1

LOCATION K12 K11 Y15 Z12

FIN 5WW 3WW 4WW 2WW

F10 F01 P08 Q07

4DA1 2DA1

D04 D03

Subtask 30-31-00-865-099-A AK. Make sure that this(these) circuit breaker(s) is(are) closed: PANEL DESIGNATION 49VU CAPT/LOUD/SPKR 49VU FWS/FWC1/SPLY 121VU EIS/F/O/LOUD/SPKR 121VU EIS/FWC2/SPLY FOR FIN 6DA1 (PHC-1) 49VU ANTI ICE/PROBES/AOA/1 49VU ANTI ICE/PROBES/PHC/1

LOCATION

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-31-00-040-002-A - Check of the ADRS, Heaters and Failure Alerts related to the Probes PANEL DESIGNATION 49VU ANTI ICE/PROBES/PITOT/1 122VU ANTI ICE/PROBES/1/STATIC FOR FIN 6DA2 (PHC-2) 122VU ANTI ICE/PROBES/2/PITOT 122VU ANTI ICE/PROBES/2/AOA 122VU ANTI ICE/PROBES/PHC/2 122VU ANTI ICE/PROBES/2/STATIC FOR FIN 6DA3 (PHC-3) 122VU ANTI ICE/PROBES/PHC/3 122VU ANTI ICE/PROBES/3/PITOT 122VU ANTI ICE/PROBES/3/AOA 122VU ANTI ICE/PROBES/3/STATIC

FIN 3DA1 5DA1

D02 Z13

LOCATION

3DA2 4DA2 2DA2 5DA2

Y14 Y13 Y12 Y11

2DA3 3DA3 4DA3 5DA3

Y16 Z16 Z15 Z14

Subtask 30-31-00-869-117-A AL. Simulation of the Flight Procedure (with the Aircraft on the Ground) (1) Do the ADIRS start procedure (Ref. AMM TASK 34-10-00-860-002) . ACTION RESULT 1.On the MCDU: On the MCDU: · Get access to the SYSTEM REPORT/TEST/L/ · The SYSTEM REPORT/TEST/L/G page comes G page (Ref. AMM TASK 31-32-00-860-009) . into view. 2.On the MCDU: · The LGCIU1 page comes into view. · Push the line key adjacent to the LGCIU1 indication. 3.Push the NEXT PAGE key. · The LGCIU1 page comes into view. 4.Push the line key adjacent to the LANDING · The LANDING GEAR SIMULATION page comes GEAR SIMULATION indication. into view. 5.Push the line key adjacent to the NOSE + LH + · The NOSE + LH + RH page comes into view. RH indication. 6.Push the line key adjacent to the EXTENDED · The '<' symbol goes out of view (flight simuindication. lated). On glareshield panels 130VU and 131VU: · The MASTER WARN lights come on. You can hear a continuous repetitive chime. Subtask 30-31-00-869-118-A CAUTION:

DO THE TEST AS QUICKLY AS POSSIBLE TO PREVENT DAMAGE TO THE PROBES.

AM. Check NOTE: ECAM warnings ANTI ICE CAPT TAT and ANTI ICE F/O TAT come on after 15 seconds.

ACTION 1.On the ECAM control panel: · Push the CLR key many times until the indications related to the ANTI ICE system come into view. 2.On the ECAM control panel:

RESULT On the upper ECAM DU: · The ANTI ICE CAPT TAT ANTI ICE F/O TAT messages come into view. On the lower ECAM DU, on the right of the display:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-31-00-040-002-A - Check of the ADRS, Heaters and Failure Alerts related to the Probes ACTION RESULT · If no ANTI ICE message comes into view on the · The upper ECAM after you push the CLR key many CAPT TAT times, push the STS key to show the indications F/O TAT related to the ANTI ICE system. messages come into view. 3.On the MCDU: On the MCDU: · Push the line key adjacent to the COMPRESSED · The '<' symbol goes out of view (aircraft on the indication. ground). On glareshield panels 130VU and 131VU: · The MASTER WARN lights go off. The continuous repetitive chime stops. 4.On the MCDU: · Push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. 5.Push the MCDU MENU key. The MCDU MENU page comes into view. 6.Fully decrease the brightness of the MCDU screen (display off). (1) Do the ADIRS stop procedure (Ref. AMM TASK 34-10-00-860-005) . Subtask 30-31-00-865-100-A AN. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU 122VU 122VU 5.

DESIGNATION COM NAV/RAD ALTM/2 COM NAV/RAD ALTM/1 ANTI ICE/PROBES/2/TAT ANTI ICE/PROBES/1/TAT

FIN 1SA2 1SA1 1DA2 1DA1

LOCATION K12 K11 Y15 Z12

Close-up Subtask 30-31-00-860-076-A A.

Aircraft Configuration (1) Do the ground configuration after flight configuration procedure (Ref. AMM TASK 32-00-00-860002) .

Subtask 30-31-00-942-060-A B.

Put the aircraft back to its initial configuration. (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) Make an entry in the log book. (3) Make sure that the work area is clean and clear of tools and other items. (4) Remove the safety barriers. (5) Remove the WARNING NOTICE(S). (6) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (7) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-31-00-040-002-A - Check of the ADRS, Heaters and Failure Alerts related to the Probes

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-42-00-040-001-A - Deactivation of the Window Heat Computer (WHC)

** ON A/C ALL TASK 30-42-00-040-001-A Deactivation of the Window Heat Computer (WHC)

FIN : 2DG1 , 2DG2 1.

Reason for the Job MMEL 30-42-01A Window Heat Computer To do the deactivation of one of the two WHCs and to do a check of the correct operation and monitoring of the WHC that stays in operation.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 30-42-00-710-001-A). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A).

3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Operational Test of the Windshield Anti-Icing and Defogging EIS Start Procedure EIS Stop Procedure

Job Set-up Subtask 30-42-00-861-052-A A.

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

Subtask 30-42-00-869-059-A B. 4.

Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) .

Procedure Subtask 30-42-00-710-056-A A.

Check of the Heaters of the Fixed and Sliding Windows related to the WHC in Operation (1) Do an operational test of the available windshield anti-icing and defogging system (Ref. AMM TASK 30-42-00-710-001) .

Subtask 30-42-00-865-056-A

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-42-00-040-001-A - Deactivation of the Window Heat Computer (WHC)

B.

Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 2DG1 (WHC-1) 122VU ANTI ICE/WINDOWS/L 122VU ANTI ICE/WHC/1 123VU ANTI ICE/L/WHSLD FOR FIN 2DG2 (WHC-2) 122VU ANTI ICE/WINDOWS/R 122VU ANTI ICE/WHC/2 123VU ANTI ICE/R/WHSLD

FIN

LOCATION

4DG1 5DG1 1DG1

X14 X13 AF10

4DG2 5DG2 1DG2

W14 W13 AF03

Subtask 30-42-00-210-050-A C.

Check of the Warning Messages of the Fixed and Sliding Windows related to the WHC in Operation (1) On the Upper ECAM DU make sure that these warning messages: · A.ICE L WSHLD HEAT · A.ICE R WSHLD HEAT · A.ICE L WINDOW HEAT · A.ICE R WINDOW HEAT come into view.

Subtask 30-42-00-860-058-A D.

Circuit Breaker Configuration (1) The circuit breakers of the WHC that does not operate, must stay open, safetied and tagged. (2) Remove the safety clip(s) and tag(s) and close this(these) circuit breaker(s) that follow of the WHC that stays in operation:

Subtask 30-42-00-865-057-A E.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 2DG1 (WHC-1) 122VU ANTI ICE/WINDOWS/L 122VU ANTI ICE/WHC/1 123VU ANTI ICE/L/WHSLD FOR FIN 2DG2 (WHC-2) 122VU ANTI ICE/WINDOWS/R 122VU ANTI ICE/WHC/2 123VU ANTI ICE/R/WHSLD

5.

FIN

LOCATION

4DG1 5DG1 1DG1

X14 X13 AF10

4DG2 5DG2 1DG2

W14 W13 AF03

Close-up Subtask 30-42-00-869-060-A A.

Make an entry in the log book.

Subtask 30-42-00-869-061-A B.

Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) .

Subtask 30-42-00-862-052-A C.

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

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-42-00-040-001-A - Deactivation of the Window Heat Computer (WHC)

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-45-00-040-003-A - Deactivation of the Windshield Wiper

** ON A/C ALL TASK 30-45-00-040-003-A Deactivation of the Windshield Wiper 1.

Reason for the Job MMEL 30-45-02B Windshield Wiper PARK Function

2

Job Set-up Information A.

Referenced Information REFERENCE (Ref. 30-45-52-000-002-A).

3.

DESIGNATION Removal of the Wiper Arm

Job Set-up Subtask 30-45-00-860-050-A A.

4.

Not Applicable

Procedure Subtask 30-45-00-040-051-A A.

Deactivation of the Windshield Wiper (1) Remove the defective windshield wiper arm (Ref. AMM TASK 30-45-52-000-002) .

5.

Close-up Subtask 30-45-00-860-052-A A.

Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-71-00-040-001-A - Deactivation of the Waste-Water Drain Mast Heating-System

** ON A/C ALL TASK 30-71-00-040-001-A Deactivation of the Waste-Water Drain Mast Heating-System Task Summary MMEL or CDL Ref MMEL 30-71-01A MMEL 30-71-01B

Access NO NO

Test NO NO

1.

Reason for the Job MMEL 30-71-01A Waste Water Drain Mast Heating System MMEL 30-71-01B Waste Water Drain Mast Heating System

2

Job Set-up Information A.

Mhr 00.3 00.3

E/T 00.3 00.3

Nb Men 1 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Specific Tools NO NO

QTY DESIGNATION 1 PLACARD AR SAFETY CLIP - CIRCUIT BREAKER

Referenced Information REFERENCE (Ref. 24-41-00-862-002-A).

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Potable Water Lavatory Shutoff Valve SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-71-00-040-001-A - Deactivation of the Waste-Water Drain Mast Heating-System

A TYPICAL

POTABLE WATER SHUTOFF-VALVE

CONTROL HANDLE

A

N_MM_307100_4_AAB0_01_02

Figure 30-71-00-991-00100-00-B / SHEET 1/1 - Potable Water Lavatory Shutoff Valve ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 30-71-00-040-001-A - Deactivation of the Waste-Water Drain Mast Heating-System

3.

Job Set-up Subtask 30-71-00-862-050-A A.

Make sure that the aircraft electrical circuits are isolated (Ref. AMM TASK 24-41-00-862-002) . NOTE: It is necessary to open only the related circuit breaker(s) of the defective drain mast.

Subtask 30-71-00-865-072-A B.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-214, 217-228, 230-234, 237-240, 242-250, 301-450, 500-600 2000VU WASTE WIP-DRAINMAST-FWD 1DU B06 ** ON A/C 215-216, 229-229, 235-236, 241-241 2000VU WASTE WIP-DRAINMAST-FWD

1DU

B02

** ON A/C 401-450 2000VU WASTE WIP-HEATER-CTL 2000VU WASTE WIP-HEATER-LINE

9DU 8DU

B05 B04

** ON A/C ALL 2001VU

11DU

E01

31DU

E04

WASTE WIP-DRAINMAST-AFT

** ON A/C 204-204, 219-220, 401-415 2001VU WASTE WIP-HEATER-LINE ** ON A/C ALL 4.

Procedure (Ref. Fig. Potable Water Lavatory Shutoff Valve SHEET 1) Subtask 30-71-00-040-051-E A.

Deactivation Procedure (1) Close the manual shutoff valve of the related lavatory water supply. The shutoff valve is installed below the wash basin. (2) Put a PLACARD on the related lavatory doors to show persons that the lavatories are not in use. (3) Close and lock the lavatory doors. (4) Close the shutoff valve of the related galley water supply. (5) Put a PLACARD on the related galley water supply to tell persons not to operate the water faucet.

5.

Close-up Subtask 30-71-00-860-054-A A.

Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 31-68-00-040-005-A - Deactivation of the DMC2 when AC ESS FEED control is operative

** ON A/C ALL TASK 31-68-00-040-005-A Deactivation of the DMC2 when AC ESS FEED control is operative 1.

Reason for the Job MMEL 31-62-02A DMC 2

2

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS 210

B.

Referenced Information REFERENCE (Ref. 24-25-00-710-001-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A).

3.

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

DESIGNATION Operational Test of the AC Essential-Generation Switching Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure

Job Set-up Subtask 31-68-00-860-071-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

4.

Procedure Subtask 31-68-00-710-056-A A.

Do the Operational Test of the AC Essential Generation Switching (Ref. AMM TASK 24-25-00-710-001)

Subtask 31-68-00-020-054-A B.

Deactivation of the EIS DMC selector switch (1) Do the EIS Start Procedure (Ref. AMM TASK 31-60-00-860-001) . (2) Make a mark on the panel 8VU close to the EIS DMC selector switch to ask the crew to set the EIS DMC selector switch in the position F/O 3.

5.

Close-up Subtask 31-68-00-860-077-A A.

Put the aircraft back to its initial configuration.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 31-68-00-040-005-A - Deactivation of the DMC2 when AC ESS FEED control is operative

(1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (2) Make an entry in the log book. (3) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 31-68-00-040-004-A - Deactivation of the ATT HDG Selector Switch

** ON A/C ALL TASK 31-68-00-040-004-A Deactivation of the ATT HDG Selector Switch 1.

Reason for the Job MMEL 31-68-02A ATT HDG Switching Selector on the Center Pedestal (FAA only)

2

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS 210

B.

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 34-10-00-860-005-A).

3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure ADIRS Stop Procedure

Job Set-up Subtask 31-68-00-860-053-A A.

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

Subtask 31-68-00-865-051-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 49VU 49VU 49VU 49VU 49VU 49VU 49VU

DESIGNATION L/G/LGCIU/SYS1/NORM EIS/DMC3/SWTG EIS/ECAM DU/UPPER/SWTG EIS/ECAM DU/UPPER/SPLY EIS/PFD CAPT/SWTG NAV PROBES/ADIRU 1/AND AOA 1/ 26VAC NAV PROBES/ADIRU1/115VAC NAV/DME/1 NAV/VOR/1

FIN 1GA 21WT3 24WT1 13WT1 22WT1 5FP1

LOCATION C09 E07 E06 E05 E04 F07

4FP1 1SD1 2RS1

F06 G14 G13

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 31-68-00-040-004-A - Deactivation of the ATT HDG Selector Switch

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-053, 204-205, 207-207, 210-210, 219-221, 227-228, 233-234, 240-240, 243-243 49VU NAV/STBY/ALTM 16FN F14 ** ON A/C 016-022, 024-063, 201-201, 203-222, 226-235, 237-237, 239-240, 242-250, 350-350 49VU NAV/VOR/DME/RMI 12FN F13 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 206-206, 208-209, 211-218, 221-226, 229-232, 235-239, 241-242, 244-250, 301-450, 500-600 EMB SB 34-1261 for A/C 237-237 EMB SB 34-1335 for A/C 237-237 49VU NAV/STBY/INST

5FN

F12

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU EIS/ECAM/CTL/PNL 15WT E12 49VU EIS/DMC1/SPLY 10WT1 E11 49VU EIS/DMC3/STBY/SPLY 14WT1 E10 49VU EIS/DMC1/SWTG 21WT1 E09 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP 49VU NAV/ADF/1 1RP1

F09 H14

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-232, 234-250, 301-450, 500-600 49VU EIS/PFD/CAPT/SPLY 11WT1 E03 ** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 233-233 49VU EIS/RLY/BOX/CAPT 17WT1 49VU EIS/PFD CAPT/SPLY 11WT1

E08 E03

** ON A/C 204-205, 207-207, 210-210, 219-220, 227-228, 233-234, 240-240, 243-243 49VU NAV/STBY/HORIZON 5FN F12 ** ON A/C 301-349, 351-450, 500-600 49VU NAV/ADF/1 49VU NAV PROBES/ADIRU3/PWR/SWTG

1RP1 8FP

F09 F08

** ON A/C 401-450 49VU 49VU 49VU 49VU

EIS/ECAM/CTL/PNL EIS/DMC1/SPLY EIS/DMC3/STBY/SPLY EIS/DMC1/SWTG

15WT 10WT1 14WT1 21WT1

E11 E10 E09 E08

** ON A/C ALL 105VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU1/28VDC COM NAV/RADAR/1 COM NAV/RAD ALTM/2 COM NAV/RAD ALTM/1 COM NAV/VOR/2 COM NAV/DME/2

6FP1 5SQ1 1SA2 1SA1 2RS2 1SD2

C02 K13 K12 K11 K08 K06

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 31-68-00-040-004-A - Deactivation of the ATT HDG Selector Switch

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C ALL EMB SB 23-1485 for A/C 210-210 121VU ADIRS/ADIRU/3PWR/SWTG 121VU ADIRS/ADIRU/2/26VAC AND AOA 121VU ADIRS/ADIRU/3/26VAC AND AOA 121VU ADIRS/ADIRU/2/115VAC 121VU ADIRS/ADIRU/3/115VAC 121VU ADIRS/ADIRU/2/28VDC 121VU ADIRS/ADIRU/3/28VDC

9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N09 N08 N07 N06 N05 N04 N03

** ON A/C ALL 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

2WZ 2GA 52GA 10WT3 10WT2 13WT2 24WT2 21WT2 22WT2 11WT2

P06 Q35 Q34 Q09 Q08 R11 R10 R08 R05 R03

EIS/GPWS/28VDC HYDRAULIC/LGCIU/SYS2 HYDRAULIC/LGCIU/SYS1/GRND SPLY EIS/DMC3/SPLY EIS/DMC2/SPLY EIS/ECAM DU/LOWER/SPLY EIS/ECAM DU/LOWER/SWTG EIS/DMC2/SWTG EIS/PFD/F/O/SWTG EIS/PFD/F/O

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-325, 331-332, 350-350 EMB SB 23-1485 for A/C 210-210 121VU ADIRS/ADIRU/2PWR/SHED

10FP

N10

** ON A/C 112-150, 201-201, 203-212, 217-220, 222-222, 227-230, 233-235, 238-240, 243-243, 301-450, 500-600 121VU COM NAV/TCAS 4SG K10 121VU EIS/GPWS/115VAC 3WZ P07 ** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 233-233 121VU EIS/RLY/BOX/F/O 17WT2

R07

** ON A/C 203-203, 206-206, 210-212, 227-228, 230-232, 237-237, 239-239, 242-242, 244-250, 350-350 EMB SB 34-1153 for A/C 206-206, 210-210 121VU COM NAV/ADF/2

1RP2

K02

** ON A/C 326-330, 333-349, 351-450, 500-600 121VU ADIRS/2PWR/SHED &/AOA2 MON

10FP

N10

** ON A/C ALL 122VU

17XN1

V25

ELEC/AC/BUS1/CTL

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 31-68-00-040-004-A - Deactivation of the ATT HDG Selector Switch

** ON A/C 016-021, 201-201, 203-207, 209-211, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 Subtask 31-68-00-860-054-A C.

Aircraft Maintenance Configuration (1) Do the EIS start procedure (PFDs and NDs only) (Ref. AMM TASK 31-60-00-860-001) . (2) On the overhead panel: on the ADIRS CDU, on the panel 20VU, make sure that the OFF/NAV/ATT selector switches for ADIRU1 and ADIRU2 are at NAV. (3) On the center pedestal, on the SWITCHING panel 8VU, check that the ATT HDG selector switch is in NORM position.

** ON A/C 022-022, 024-100, 112-150, 208-208, 212-214, 223-225, 236-236, 238-238, 241-241, 301-349, 351450, 500-600 Subtask 31-68-00-860-054-B C.

Aircraft Maintenance Configuration (1) Do the EIS start procedure (PFDs and NDs only) (Ref. AMM TASK 31-60-00-860-001) . (2) On the ADIRS MSU, on the panel 20VU, make sure that the OFF/NAV/ATT selector switches for ADIRU1 and ADIRU2 are set to NAV. (3) On the center pedestal, on the SWITCHING panel 8VU, make sure that the ATT HDG selector switch is set to NORM.

** ON A/C ALL 4.

Procedure

** ON A/C 016-021, 201-201, 203-207, 209-211, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 Subtask 31-68-00-710-051-A A.

Check of the ATT HDG switch ACTION RESULT 1.On the ADIRS CDU: · set the OFF/NAV/ATT selector switch for the IR1 On the CAPT PFD, check that the pitch and roll attito OFF tudes and the heading indications go out of view. The ATT flag comes into view. Ignore the related warnings. · set the OFF/NAV/ATT selector switch for the IR2 On the F/O PFD, check that the pitch and roll attito OFF tudes and the heading indications go out of view. The ATT flag comes into view. Ignore the related warnings.

** ON A/C 022-022, 024-100, 112-150, 208-208, 212-214, 223-225, 236-236, 238-238, 241-241, 301-349, 351450, 500-600 Subtask 31-68-00-710-051-B A.

Check of the ATT HDG Switch ACTION 1.On the ADIRS MSU:

RESULT

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 31-68-00-040-004-A - Deactivation of the ATT HDG Selector Switch

ACTION · Set the OFF/NAV/ATT selector switch for IR1 to OFF.

· Set the OFF/NAV/ATT selector switch for IR2 to OFF.

RESULT On the CAPT PFD, the pitch and roll attitudes and the heading indications go out of view. The ATT flag comes into view. Ignore the related warnings. On the F/O PFD, the pitch and roll attitudes and the heading indications go out of view. The ATT flag comes into view. Ignore the related warnings.

** ON A/C ALL Subtask 31-68-00-020-052-A B.

Deactivation of the ATT HDG selector switch (1) Make a mark on the panel 8VU close to the ATT HDG selector switch to forbid the crew to set the ATT HDG selector switch in any position except NORM which is the valid position.

5.

Close-up Subtask 31-68-00-860-055-A A.

Put the aircraft back to its initial configuration. (1) Do the EIS Stop Procedure (Ref. AMM TASK 31-60-00-860-002) (2) Do the ADIRS Stop Procedure (Ref. AMM TASK 34-10-00-860-005) (3) Make an entry in the log book. (4) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002)

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 31-68-00-040-002-A - Deactivation of the AIR DATA Selector Switch

** ON A/C ALL TASK 31-68-00-040-002-A Deactivation of the AIR DATA Selector Switch 1.

Reason for the Job MMEL 31-68-01A Air Data Switching Selector on the Center Pedestal (FAA only)

2

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS 210

B.

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 34-10-00-860-005-A).

3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure ADIRS Stop Procedure

Job Set-up Subtask 31-68-00-860-050-A A.

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

Subtask 31-68-00-865-050-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 49VU 49VU 49VU 49VU 49VU 49VU 49VU

DESIGNATION L/G/LGCIU/SYS1/NORM EIS/DMC3/SWTG EIS/ECAM DU/UPPER/SWTG EIS/ECAM DU/UPPER/SPLY EIS/PFD CAPT/SWTG NAV PROBES/ADIRU 1/AND AOA 1/ 26VAC NAV PROBES/ADIRU1/115VAC NAV/DME/1 NAV/VOR/1

FIN 1GA 21WT3 24WT1 13WT1 22WT1 5FP1

LOCATION C09 E07 E06 E05 E04 F07

4FP1 1SD1 2RS1

F06 G14 G13

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 31-68-00-040-002-A - Deactivation of the AIR DATA Selector Switch

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-053, 204-205, 207-207, 210-210, 219-221, 227-228, 233-234, 240-240, 243-243 49VU NAV/STBY/ALTM 16FN F14 ** ON A/C 016-022, 024-063, 201-201, 203-222, 226-235, 237-237, 239-240, 242-250, 350-350 49VU NAV/VOR/DME/RMI 12FN F13 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 206-206, 208-209, 211-218, 221-226, 229-232, 235-239, 241-242, 244-250, 301-450, 500-600 EMB SB 34-1261 for A/C 237-237 EMB SB 34-1335 for A/C 237-237 49VU NAV/STBY/INST

5FN

F12

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU EIS/ECAM/CTL/PNL 15WT E12 49VU EIS/DMC1/SPLY 10WT1 E11 49VU EIS/DMC3/STBY/SPLY 14WT1 E10 49VU EIS/DMC1/SWTG 21WT1 E09 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP 49VU NAV/ADF/1 1RP1

F09 H14

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-232, 234-250, 301-450, 500-600 49VU EIS/PFD/CAPT/SPLY 11WT1 E03 ** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 233-233 49VU EIS/RLY/BOX/CAPT 17WT1 49VU EIS/PFD CAPT/SPLY 11WT1

E08 E03

** ON A/C 204-205, 207-207, 210-210, 219-220, 227-228, 233-234, 240-240, 243-243 49VU NAV/STBY/HORIZON 5FN F12 ** ON A/C 301-349, 351-450, 500-600 49VU NAV/ADF/1 49VU NAV PROBES/ADIRU3/PWR/SWTG

1RP1 8FP

F09 F08

** ON A/C 401-450 49VU 49VU 49VU 49VU

EIS/ECAM/CTL/PNL EIS/DMC1/SPLY EIS/DMC3/STBY/SPLY EIS/DMC1/SWTG

15WT 10WT1 14WT1 21WT1

E11 E10 E09 E08

** ON A/C ALL 105VU 121VU 121VU 121VU 121VU 121VU

ADIRS/ADIRU1/28VDC COM NAV/RADAR/1 COM NAV/RAD ALTM/2 COM NAV/RAD ALTM/1 COM NAV/VOR/2 COM NAV/DME/2

6FP1 5SQ1 1SA2 1SA1 2RS2 1SD2

C02 K13 K12 K11 K08 K06

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 31-68-00-040-002-A - Deactivation of the AIR DATA Selector Switch

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C ALL EMB SB 23-1485 for A/C 210-210 121VU ADIRS/ADIRU/3PWR/SWTG 121VU ADIRS/ADIRU/2/26VAC AND AOA 121VU ADIRS/ADIRU/3/26VAC AND AOA 121VU ADIRS/ADIRU/2/115VAC 121VU ADIRS/ADIRU/3/115VAC 121VU ADIRS/ADIRU/2/28VDC 121VU ADIRS/ADIRU/3/28VDC

9FP 5FP2 5FP3 4FP2 4FP3 6FP2 6FP3

N09 N08 N07 N06 N05 N04 N03

** ON A/C ALL 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

2WZ 2GA 52GA 10WT3 10WT2 13WT2 24WT2 21WT2 22WT2 11WT2

P06 Q35 Q34 Q09 Q08 R11 R10 R08 R05 R03

EIS/GPWS/28VDC HYDRAULIC/LGCIU/SYS2 HYDRAULIC/LGCIU/SYS1/GRND SPLY EIS/DMC3/SPLY EIS/DMC2/SPLY EIS/ECAM DU/LOWER/SPLY EIS/ECAM DU/LOWER/SWTG EIS/DMC2/SWTG EIS/PFD/F/O/SWTG EIS/PFD/F/O

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-325, 331-332, 350-350 EMB SB 23-1485 for A/C 210-210 121VU ADIRS/ADIRU/2PWR/SHED

10FP

N10

** ON A/C 112-150, 201-201, 203-212, 217-220, 222-222, 227-230, 233-235, 238-240, 243-243, 301-450, 500-600 121VU COM NAV/TCAS 4SG K10 121VU EIS/GPWS/115VAC 3WZ P07 ** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 233-233 121VU EIS/RLY/BOX/F/O 17WT2

R07

** ON A/C 203-203, 206-206, 210-212, 227-228, 230-232, 237-237, 239-239, 242-242, 244-250, 350-350 EMB SB 34-1153 for A/C 206-206, 210-210 121VU COM NAV/ADF/2

1RP2

K02

** ON A/C 326-330, 333-349, 351-450, 500-600 121VU ADIRS/2PWR/SHED &/AOA2 MON

10FP

N10

** ON A/C ALL 122VU

17XN1

V25

ELEC/AC/BUS1/CTL

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 31-68-00-040-002-A - Deactivation of the AIR DATA Selector Switch

** ON A/C 016-021, 201-201, 203-207, 209-211, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 Subtask 31-68-00-860-052-A C.

Aircraft Maintenance Configuration (1) Do the EIS Start Procedure (PFDs and NDs only) (Ref. AMM TASK 31-60-00-860-001) (2) On the ADIRS CDU, on the panel 20VU, make sure that the OFF/NAV/ATT selector switches for the ADIRU1 and ADIRU2 are at NAV. (3) On the center pedestal, on the SWITCHING panel 8VU, make sure that the AIR DATA selector switch is in the NORM position.

** ON A/C 022-022, 024-100, 112-150, 208-208, 212-214, 223-225, 236-236, 238-238, 241-241, 301-349, 351450, 500-600 Subtask 31-68-00-860-052-B C.

Aircraft Maintenance Configuration (1) Do the EIS start procedure (PFDs and NDs only) (Ref. AMM TASK 31-60-00-860-001) . (2) On the ADIRS MSU, on the panel 20VU, make sure that the OFF/NAV/ATT selector switches for the ADIRU1 and ADIRU2 are set to NAV. (3) On the center pedestal, on the SWITCHING panel 8VU, make sure that the AIR DATA selector switch is set to NORM.

** ON A/C ALL 4.

Procedure

** ON A/C 016-021, 201-201, 203-207, 209-211, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 Subtask 31-68-00-710-050-A A.

ADR Test ACTION 1.On the ADIRS CDU: · push the ADR1 pushbutton switch.

· push the ADR2 pushbutton switch.

· push the ADR1 and ADR2 pushbutton switches again.

RESULT On the ADIRS CDU, the OFF legend of the ADR1 pushbutton switch comes on. On the CAPT PFD, the speed and altitude indications go out of view (ignore the related flag warnings). On the ADIRS CDU, the OFF legend of the ADR2 pushbutton switch comes on. On the F/O PFD, the speed and altitude indications go out of view (ignore the related flag warnings). On the ADIRS CDU, the OFF legend of the ADR1 and ADR2 pushbutton switches goes off. On the CAPT and F/O PFDs, the speed and altitude indications come into view.

** ON A/C 022-022, 024-100, 112-150, 208-208, 212-214, 223-225, 236-236, 238-238, 241-241, 301-349, 351450, 500-600 Subtask 31-68-00-710-050-B A.

ADR Test

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 31-68-00-040-002-A - Deactivation of the AIR DATA Selector Switch

ACTION 1.On the ADIRS MSU: · Push the ADR1 pushbutton switch.

· Push the ADR2 pushbutton switch.

· Push the ADR1 and ADR2 pushbutton switches again.

RESULT On the ADIRS MSU, the OFF legend of the ADR1 pushbutton switch comes on. On the CAPT PFD, the speed and altitude indications go out of view (ignore the related flag warnings). On the ADIRS MSU, the OFF legend of the ADR2 pushbutton switch comes on. On the F/O PFD, the speed and altitude indications go out of view (ignore the related flag warnings). On the ADIRS MSU, the OFF legend of the ADR1 and ADR2 pushbutton switches goes off. On the CAPT and F/O PFDs, the speed and altitude indications come into view.

** ON A/C ALL Subtask 31-68-00-020-050-A B.

Deactivation of the AIR DATA selector switch (1) Make a mark on the panel 8VU close to the AIR DATA selector switch to forbid the crew to set the AIR DATA selector switch in any position except NORM which is the valid position.

5.

Close-up Subtask 31-68-00-860-051-A A.

Put the aircraft back to its initial configuration. (1) Do the EIS Stop Procedure (Ref. AMM TASK 31-60-00-860-002) (2) Do the ADIRS Stop Procedure (Ref. AMM TASK 34-10-00-860-005) (3) Make an entry in the log book. (4) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002)

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 31-68-00-040-003-A - Deactivation of the EIS DMC Selector Switch

** ON A/C ALL TASK 31-68-00-040-003-A Deactivation of the EIS DMC Selector Switch 1.

Reason for the Job MMEL 31-68-04A EIS DMC Switching Selector on the Center Pedestal (FAA only)

2

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS 210

B.

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A).

3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure

Job Set-up Subtask 31-68-00-860-056-A A.

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

Subtask 31-68-00-865-052-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 49VU 49VU 49VU 49VU

DESIGNATION EIS/DMC3/SWTG EIS/ECAM DU/UPPER/SWTG EIS/ECAM DU/UPPER/SPLY EIS/PFD CAPT/SWTG EIS/ND CAPT/SWTG EIS/ND CAPT/SPLY

FIN 21WT3 24WT1 13WT1 22WT1 23WT1 12WT1

LOCATION E07 E06 E05 E04 E02 E01

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 49VU EIS/ECAM/CTL/PNL 15WT E12 49VU EIS/DMC1/SPLY 10WT1 E11 49VU EIS/DMC3/STBY/SPLY 14WT1 E10

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 31-68-00-040-003-A - Deactivation of the EIS DMC Selector Switch

PANEL 49VU

DESIGNATION EIS/DMC1/SWTG

FIN 21WT1

LOCATION E09

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-232, 234-250, 301-450, 500-600 49VU EIS/PFD/CAPT/SPLY 11WT1 E03 ** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 233-233 49VU EIS/RLY/BOX/CAPT 17WT1 49VU EIS/PFD CAPT/SPLY 11WT1

E08 E03

** ON A/C 401-450 49VU 49VU 49VU 49VU

EIS/ECAM/CTL/PNL EIS/DMC1/SPLY EIS/DMC3/STBY/SPLY EIS/DMC1/SWTG

15WT 10WT1 14WT1 21WT1

E11 E10 E09 E08

** ON A/C ALL 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU 121VU

EIS/DMC3/SPLY EIS/DMC2/SPLY EIS/ECAM DU/LOWER/SPLY EIS/ECAM DU/LOWER/SWTG EIS/DMC2/SWTG EIS/ND/F/O/SWTG EIS/PFD/F/O/SWTG EIS/ND/F/O EIS/PFD/F/O

10WT3 10WT2 13WT2 24WT2 21WT2 23WT2 22WT2 12WT2 11WT2

Q09 Q08 R11 R10 R08 R06 R05 R04 R03

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 233-233 121VU EIS/RLY/BOX/F/O 17WT2

R07

** ON A/C ALL 122VU

V25

ELEC/AC/BUS1/CTL

17XN1

Subtask 31-68-00-860-058-A C.

Aircraft Maintenance Configuration (1) Do the EIS Start Procedure (Ref. AMM TASK 31-60-00-860-001) (2) On the center pedestal, on the SWITCHING panel 8VU, make sure that the EIS DMC selector switch is in the NORM position.

4.

Procedure

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 233-233 Subtask 31-68-00-710-052-A A.

Check of the EIS DMC switch ACTION 1.On C/B panel 49VU: · open the circuit breaker 10WT1

· close the circuit breaker 10WT1

RESULT A diagonal line comes into view on the CAPT PFD and ND and on the upper ECAM DU. On the lower ECAM DU, the EIS DMC1 FAULT message is displayed. The related images of each DU come into view.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 31-68-00-040-003-A - Deactivation of the EIS DMC Selector Switch

ACTION 2.On C/B panel 121VU: · open the circuit breaker 10WT2

· close the circuit breaker 10WT2

RESULT A diagonal line comes into view on the F/O PFD and ND and on the lower ECAM DU. On the upper ECAM DU, the EIS DMC2 FAULT message is displayed. The related images of each DU come into view.

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-232, 234-250, 301-450, 500-600 Subtask 31-68-00-710-052-B A.

Check of the EIS DMC switch ACTION 1.On C/B panel 49VU: · open the circuit breaker 10WT1

· close the circuit breaker 10WT1 2.On C/B panel 121VU: · open the circuit breaker 10WT2

· close the circuit breaker 10WT2

RESULT An INVALID DATA message comes into view on the CAPT PFD and ND On the lower ECAM DU, the EIS DMC1 FAULT message is displayed. After 35s, the related images of each DU come into view. An INVALID DATA message comes into view on the F/O PFD and ND On the upper ECAM DU, the EIS DMC2 FAULT message is displayed. After 35s, the related images of each DU come into view.

** ON A/C ALL Subtask 31-68-00-020-053-A B.

Deactivation of the EIS DMC selector switch (1) Make a mark on the panel 8VU close to the EIS DMC selector switch to forbid the crew to set the EIS DMC selector switch in any position except NORM which is the valid position.

5.

Close-up Subtask 31-68-00-860-057-A A.

Put the aircraft back to its initial configuration. (1) Do the EIS Stop Procedure (Ref. AMM TASK 31-60-00-860-002) (2) Make an entry in the log book. (3) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002)

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 31-68-00-040-006-A - Deactivation of the Lower ECAM DU when AC ESS FEED control is operative

** ON A/C ALL TASK 31-68-00-040-006-A Deactivation of the Lower ECAM DU when AC ESS FEED control is operative 1.

Reason for the Job MMEL 31-63-05A SDU

2

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS 210

B.

Referenced Information REFERENCE (Ref. 24-25-00-710-001-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

3.

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

DESIGNATION Operational Test of the AC Essential-Generation Switching Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up Subtask 31-68-00-860-073-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

4.

Procedure Subtask 31-68-00-710-057-A A.

5.

Do the operational test of the AC essential generation switching (Ref. AMM TASK 24-25-00-710-001) .

Close-up Subtask 31-68-00-860-075-A A.

Aircraft Maintenance Configuration (1) Put a temporary placard in the cockpit to tell persons that the lower ECAM DU is deactivated. (2) Make an entry in the log book. (3) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-12-00-040-006-A - Preparation of the Aircraft for Flight with a Failed or Missing Ground Door Opening Cable

** ON A/C ALL TASK 32-12-00-040-006-A Preparation of the Aircraft for Flight with a Failed or Missing Ground Door Opening Cable 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.

1.

Reason for the Job MMEL 32-12-01A Main Gear Door Ground Opening Cable

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific (460005835) (98DNSA20208040)

B.

QTY AR AR AR AR AR 2 1

DESIGNATION ACCESS PLATFORM 2M (6 FT) SAFETY BARRIER(S) SAFETY CLIP - CIRCUIT BREAKER TIE WRAP WARNING NOTICE(S) SLEEVE - GROUND LOCK RIGGING PIN

Consumable Materials REFERENCE (Material No. 14QFB1)

DESIGNATION Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -

C. Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTION 734 MAIN DOOR 744 MAIN DOOR FOR 2804GM (CABLE CONTROL) 195BB FOR 2805GM (CABLE CONTROL) 196BB D. Referenced Information

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-12-00-040-006-A - Preparation of the Aircraft for Flight with a Failed or Missing Ground Door Opening Cable REFERENCE (Ref. 24-41-00-862-002-A).

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 29-00-00-910-002-A). Safety Procedures of the Hydraulic System (Ref. 29-10-00-863-001-A). Pressurize the Green Hydraulic System with a Hydraulic Ground Power-Cart (Ref. 29-10-00-864-001-A). Depressurize the Green Hydraulic System (Ref. 29-23-00-860-001-A). Disconnection of the Isolation Coupling of the Power Transfer Unit (PTU) (Ref. 29-23-00-860-002-A). Connection of the Isolation Coupling of the Power Transfer Unit (PTU) (Ref. 32-00-00-481-001-A). Installation of the Safety Devices on the Landing Gears (Ref. 32-00-00-481-002-A). Installation of the Safety Devices on the Landing Gear Doors (Ref. 32-00-00-860-001-A). Flight Configuration Precautions with Electrical Power (Ref. 32-00-00-860-001-A-01). Flight Configuration Precautions without Electrical Power (Ref. 32-00-00-860-002-A). Ground Configuration after Flight Configuration with Electrical Power (Ref. 32-00-00-860-002-A-01). Ground Configuration after Flight Configuration without Electrical Power (Ref. 32-12-16-000-001-A). Removal of the Control Cable (Ref. 32-31-35-000-001-A). Removal of the MLG Door Actuating-Cylinder (Ref. 32-31-35-400-001-A). Installation of the MLG Door Actuating-Cylinder (Ref. 32-33-00-720-001-A). Functional Check of Free-Fall Extension MLG Door Ground-Opening System SHEET 1 Door Bypass Valve - Lockwire Installation SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-12-00-040-006-A - Preparation of the Aircraft for Flight with a Failed or Missing Ground Door Opening Cable

D

E

A B

195BB 196BB

D

AS SHOWN

E

OPPOSITE VIEW

2517GM 2518GM

A

AS SHOWN

B

OPPOSITE VIEW

2 1

3 4 5

C

RIGGING PIN LOCATION

C 12

10 6

11

9

8 7 N_MM_321200_4_ADE0_01_00

Figure 32-12-00-991-01800-00-B / SHEET 1/1 - MLG Door Ground-Opening System ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-12-00-040-006-A - Preparation of the Aircraft for Flight with a Failed or Missing Ground Door Opening Cable

A B C

Z734 (Z744)

2517GM

B C 2518GM

A

PORT B

PORT A

LOCKWIRE 10 10

B

01

FORWARD VIEW

NOTE: 01 RH SHOWN, LH SYMMETRICAL

C

01

SIDE VIEW

N_MM_321200_4_ALM0_01_00

Figure 32-12-00-991-02200-00-A / SHEET 1/1 - Door Bypass Valve - Lockwire Installation ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-12-00-040-006-A - Preparation of the Aircraft for Flight with a Failed or Missing Ground Door Opening Cable

3.

Job Set-up (Ref. Fig. MLG Door Ground-Opening System SHEET 1) Subtask 32-12-00-941-067-A WARNING: A.

OBEY THE HYDRAULIC SAFETY PROCEDURES.

Safety Precautions (Ref. AMM TASK 29-00-00-910-002) . (1) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations. (2) On the panel 400VU: · make sure that the landing-gear control-lever 6GA is in the DOWN position · put a WARNING NOTICE(S) in position to tell persons not to operate the landing gear. (3) Put a WARNING NOTICE(S) in the cockpit to tell persons not to operate the Green and Yellow Hydraulic systems. (4) On the panel 110VU, make sure that the GRAVITY GEAR EXTN handle is folded into the center console. (5) Make sure that the ground safety locks are installed on the landing gear (Ref. AMM TASK 32-00-00481-001) .

Subtask 32-12-00-860-071-A B.

Aircraft Maintenance Configuration WARNING: MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. UNWANTED ELECTRICAL POWER CAN BE DANGEROUS. (1) Make sure that the aircraft electrical circuits are de-energized (Ref. AMM TASK 24-41-00-862-002) . (2) Depressurize the Green Hydraulic system (Ref. AMM TASK 29-10-00-864-001) .

Subtask 32-12-00-865-072-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU

DESIGNATION L/G/LGCIU/SYS1/NORM

** ON A/C 301-349, 351-450, 500-600 49VU HYDRAULIC/G HYD/PUMP ENG1/CTL ** ON A/C ALL 121VU 121VU

FIN 1GA

C09

1701GK

H12

HYDRAULIC/LGCIU/SYS2 2GA HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA

LOCATION

Q35 Q34

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU HYDRAULIC/G HYD/PUMP ENG1/ 1702GK R34 MONG ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-12-00-040-006-A - Preparation of the Aircraft for Flight with a Failed or Missing Ground Door Opening Cable PANEL DESIGNATION FIN LOCATION EMB SB 32-1346 for A/C 016-019, 021-021, 201-201, 203-207, 209-211, 215-222, 226-235, 237-237, 239-240, 242-244, 350-350 121VU LGCIU/BAT SPLY/SYS2 59GA R33 121VU LGCIU/BAT SPLY/SYS1 58GA R32 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 121VU HYDRAULIC/G HYD/PUMP ENG1/CTL 1701GK ** ON A/C 401-450 121VU HYDRAULIC/G HYD/PUMP ENG1/ MONG 121VU LGCIU/BAT SPLY/SYS2 121VU LGCIU/BAT SPLY/SYS1

R35

1702GK

R33

59GA 58GA

R32 R31

** ON A/C ALL Subtask 32-12-00-010-063-A D.

Get Access (1) Put an ACCESS PLATFORM 2M (6 FT) below the applicable zone 730(740). (2) Open the applicable access panel(s): (a) FOR 2804GM (CABLE CONTROL) - open 195BB (b) FOR 2805GM (CABLE CONTROL) - open 196BB. (3) If necessary, open the MLG doors by the free-fall system (Ref. AMM TASK 32-33-00-720-001) . (4) Install a SLEEVE - GROUND LOCK (460005835) on each MLG door actuating cylinder (Ref. AMM TASK 32-00-00-481-002) . (5) Disconnect the isolation coupling of the PTU (Ref. AMM TASK 29-23-00-860-001) .

4.

Procedure

** ON A/C ALL EMB SB 32-1346 for A/C 016-019, 021-021, 201-201, 203-207, 209-211, 215-222, 226-235, 237-237, 239-240, 242-244, 350-350 Subtask 32-12-00-020-067-B 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.

WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE LANDING GEAR DOORS ARE CLEAR.

A.

Deactivation of the MLG Ground Door Opening-Cable

** ON A/C ALL (Ref. Fig. MLG Door Ground-Opening System SHEET 1)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-12-00-040-006-A - Preparation of the Aircraft for Flight with a Failed or Missing Ground Door Opening Cable

** ON A/C ALL EMB SB 32-1346 for A/C 016-019, 021-021, 201-201, 203-207, 209-211, 215-222, 226-235, 237-237, 239-240, 242-244, 350-350 NOTE: The defective cable can be removed or can stay with the cable ends disconnected from the control handle and bypass valve. If disconnected, the cable ends must be safetied correctly. (1) Remove the defective cable (Ref. AMM TASK 32-12-16-000-001) , or disconnect the cable ends as follows: (a) Disconnect the cable end (2) from the control handle as follows: 1

Remove and discard the cotter pin (5).

2

Remove the nut (4), the washer (3) and the bolt (1).

3

Remove the cable end (2) from the control handle.

4

Safety the cable end (2) in position with a TIE WRAP.

(b) Disconnect the cable end (6) from the bypass valve as follows: 1

Remove and discard the cotter pin (8).

2

Remove the nut (7), the washer (9), the bush (11) and the bolt (12).

3

Remove the cable end (6) from the bypass valve operating-lever (10).

4

Safety the cable end (6) in position with a TIE WRAP.

(2) Make sure that a SLEEVE - GROUND LOCK (460005835) is installed on the applicable MLG door actuating- cylinder (Ref. AMM TASK 32-00-00-481-002) . (3) Disconnect the applicable MLG door actuating-cylinder from the MLG door (Ref. AMM TASK 32-3135-000-001) . (4) Hold the body of the MLG door actuating-cylinder to prevent damage caused by small movement of the ram. (5) Do the flight configuration precautions with electrical power (Ref. AMM TASK 32-00-00-860-001) . (6) Pressurize the Green hydraulic system (Ref. AMM TASK 29-10-00-863-001) . CAUTION:

DO NOT TURN THE GRAVITY GEAR EXTENSION HANDLE MORE THAN 3 FULL TURNS. THIS CAN CAUSE DAMAGE TO THE FREE FALL EXTENSION SYSTEM.

(7) Do the reset of the free-fall extension system as follows: (a) On panel 110VU: 1

Turn the GRAVITY GEAR EXTN handle three full turns counterclockwise at a rate of one full turn in five seconds.

2

Fold the GRAVITY GEAR EXTN handle into the center console.

3

Make sure that the MLG doors are closed and locked.

(8) Make sure that the bypass valve operating-lever (10) is in the correct position as follows: (a) Put the RIGGING PIN (98DNSA20208040) through the rigging pin holes in the operating lever (10) and the bypass valve.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-12-00-040-006-A - Preparation of the Aircraft for Flight with a Failed or Missing Ground Door Opening Cable

(b) If RIGGING PIN (98DNSA20208040) installation is not possible (because the rigging pin holes in the operating lever (10) and the bypass valve are not aligned), do the steps that follow: 1

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 1GA, 52GA 58GA.

2

Manually move the operating lever (10) until the rigging pin holes in the operating lever (10) and the bypass valve are aligned.

3

Put the RIGGING PIN (98DNSA20208040) through the rigging pin holes in the operating lever (10) and the bypass valve.

4

Open, safety and tag this(these) circuit breaker(s): 1GA, 52GA, 58GA.

(c) Remove the RIGGING PIN (98DNSA20208040) . (d) Safety the operating lever (10) in the rigged position with Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - (Material No. 14QFB1) as follows: ** ON A/C ALL (Ref. Fig. Door Bypass Valve - Lockwire Installation SHEET 1) ** ON A/C ALL EMB SB 32-1346 for A/C 016-019, 021-021, 201-201, 203-207, 209-211, 215-222, 226-235, 237-237, 239-240, 242-244, 350-350 1

Make sure that the rigging pin holes in the operating lever (10) and the bypass valve are aligned.

2

Make a loop of the lockwire around the union of port A.

3

Do the lockwire routing behind the unions and then above the union of port B.

4

Make a loop of the lockwire through the rigging pin hole of the operating lever (10).

5

Do the lockwire routing above the union of port B and make another loop of the lockwire around the union of port A.

6

Make a last loop of the lockwire through the rigging pin hole and safety the operating lever (10).

7

If necessary, cut and discard the unwanted length of the lockwire.

(9) Depressurize the Green hydraulic system (Ref. AMM TASK 29-10-00-864-001) . (10) On panel 110VU, turn the GRAVITY GEAR EXTN handle clockwise two full turns. (11) Connect the applicable MLG door actuating-cylinder (Ref. AMM TASK 32-31-35-400-001) . (12) Remove the SLEEVE - GROUND LOCK (460005835) from the MLG door actuating-cylinders. (13) Pressurize the Green hydraulic system (Ref. AMM TASK 29-10-00-863-001) . (14) Close the MLG doors as follows: (a) Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 1GA, 52GA, 58GA. (b) On panel 110VU, turn the GRAVITY GEAR EXTN handle counterclockwise two full turns at a rate of one full turn in five seconds. (c) Fold the GRAVITY GEAR EXTN handle into the center console.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-12-00-040-006-A - Preparation of the Aircraft for Flight with a Failed or Missing Ground Door Opening Cable

(15) Put the MLG door ground control-handle in the CLOSED position. (16) Make sure that the MLG doors are closed and locked correctly. WARNING: IF THE MLG DOOR CONTROLS DO NOT AGREE WITH THE POSITION OF THE MLG DOORS, YOU MUST KEEP CLEAR OF THE LANDING GEAR BAY UNTIL: - YOU DEPRESSURIZE THE GREEN HYDRAULIC SYSTEM - YOU INSTALL A GROUND LOCK SLEEVE ON THE ACTUATING CYLINDER OF THE APPLICABLE OPEN DOOR(S). IF THE DOOR IS OPEN AND NOT SAFETIED, THERE IS A RISK THAT IT CAN CLOSE AND CAUSE INJURY. (17) Depressurize the Green hydraulic system (Ref. AMM TASK 29-10-00-864-001) . ** ON A/C ALL 5.

Close-up Subtask 32-12-00-410-055-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the applicable access panel(s): (a) FOR 2804GM (CABLE CONTROL) - close 195BB (b) FOR 2805GM (CABLE CONTROL) - close 196BB.

Subtask 32-12-00-865-073-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 301-349, 351-450, 500-600 49VU HYDRAULIC/G HYD/PUMP ENG1/CTL

1701GK

H12

** ON A/C ALL 121VU

2GA

Q35

HYDRAULIC/LGCIU/SYS2

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU HYDRAULIC/G HYD/PUMP ENG1/ 1702GK R34 MONG ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 EMB SB 32-1346 for A/C 016-019, 021-021, 201-201, 203-207, 209-211, 215-222, 226-235, 237-237, 239-240, 242-244, 350-350 121VU LGCIU/BAT SPLY/SYS2 59GA R33 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 121VU HYDRAULIC/G HYD/PUMP ENG1/CTL 1701GK

R35

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-12-00-040-006-A - Preparation of the Aircraft for Flight with a Failed or Missing Ground Door Opening Cable PANEL

DESIGNATION

** ON A/C 401-450 121VU HYDRAULIC/G HYD/PUMP ENG1/ MONG 121VU LGCIU/BAT SPLY/SYS2

FIN

LOCATION

1702GK

R33

59GA

R32

** ON A/C ALL Subtask 32-12-00-860-072-A C.

Aircraft Maintenance Configuration (1) Connect the isolation coupling of the PTU (Ref. AMM TASK 29-23-00-860-002) . (2) Do the ground configuration after flight configuration with electrical power (Ref. AMM TASK 32-0000-860-002) . (3) Make an applicable entry in the aircraft technical log.

Subtask 32-12-00-942-065-A D.

Removal of Equipment (1) Remove the SAFETY BARRIER(S). (2) Remove the access platform(s). (3) Remove the WARNING NOTICE(S). (4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-31-00-040-803-A - Deactivation of the Landing Gear Retracting System

** ON A/C ALL TASK 32-31-00-040-803-A Deactivation of the Landing Gear Retracting System Task Summary MMEL or CDL Ref MMEL 32-31-02A

Access NO

1.

Reason for the Job MMEL 32-31-02A Landing Gear Retracting System

2

Job Set-up Information A.

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Referenced Information REFERENCE (Ref. 05-59-32-869-001-A).

3.

Test YES

DESIGNATION Preparation for Flight with Gear Down

Job Set-up Subtask 32-31-00-860-135-A A.

4.

There is no special job set-up for this task.

Procedure Subtask 32-31-00-040-054-A A.

Deactivate the Landing Gear Retraction System (1) Prepare for flight with the landing gear down (Ref. AMM TASK 05-59-32-869-001) . (2) Make an applicable entry in the aircraft technical log.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-46-00-040-001-A - Check of the BSCU after BRAKES N/WS MINOR FAULT Caution message shown on the Upper Ecam Display Unit

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 301450, 500-600 TASK 32-46-00-040-001-A Check of the BSCU after BRAKES N/WS MINOR FAULT Caution message shown on the Upper Ecam Display Unit WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

WARNING:

MAKE SURE THAT THE CONTROLS AGREE WITH THE POSITION OF THE ITEMS THEY OPERATE BEFORE YOU PRESSURIZE A HYDRAULIC SYSTEM. UNWANTED MOVEMENT OF HYDRAULICALLY OPERATED ITEMS CAN CAUSE SERIOUS INJURY AND/OR DAMAGE.

WARNING:

PRESSURIZE ONLY THE HYDRAULIC SYSTEM(S) THAT IS (ARE) NECESSARY FOR THE TASK. ISOLATE THE OTHER HYDRAULIC SYSTEM(S) BEFORE YOU SUPPLY HYDRAULIC POWER TO THE AIRCRAFT.

WARNING:

MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. UNWANTED ELECTRICAL POWER CAN BE DANGEROUS.

1.

Reason for the Job MMEL 32-09-01B BRAKES-N/WS MINOR FAULT Alert MMEL 32-09-01C BRAKES-N/WS MINOR FAULT Alert

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-32-00-860-009-A).

3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Procedure to Get Access to the SYSTEM REPORT/TEST/L/G Page

Job Set-up Subtask 32-46-00-860-067-A A.

Aircraft Maintenance Configuration

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-46-00-040-001-A - Check of the BSCU after BRAKES N/WS MINOR FAULT Caution message shown on the Upper Ecam Display Unit

(1) On the panel 400VU, make sure that the L/G normal control lever is at down. (2) On the panel 402VU, make sure that the A/SKID & NOSEWHEEL switch is at ON. (3) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (4) On the MCDU, get the SYSTEM REPORT/TEST/L/G page (Ref. AMM TASK 31-32-00-860-009) . Subtask 32-46-00-941-061-A B.

Safety precautions (1) Put a WARNING NOTICE(S) to tell persons not to: · operate the landing gear control lever, · operate the brake pedals, · pressurize the Green and the Yellow hydraulic systems.

Subtask 32-46-00-865-062-A C.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 121VU 121VU 121VU 121VU

4.

DESIGNATION HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY HYDRAULIC/BRAKING AND STEERING/SYS2/CTL HYDRAULIC/BRAKING AND STEERING/SYS1/CTL HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY

FIN 4GG

M36

LOCATION

3GG

M35

1GG

M34

2GG

M33

Procedure

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 301450, 500-600 EMB SB 32-1350 for A/C 016-021, 206-206, 209-209, 215-218, 221-222, 226-230, 235-235, 239-239, 242-242, 350-350 Subtask 32-46-00-740-056-B A.

Selection of the BSCU LAST LEG REPORT NOTE: You must do this test before each flight when the BRAKES-N/WS MINOR FAULT caution message is shown on the Upper ECAM Display Unit. NOTE: This test is for channel 1. For channel 2, use the indications between parentheses.

ACTION RESULT 1.On the MCDU, push the line key adjacent to the The BSCU CHAN 1(2) page comes into view. BSCU 1(2) indication. 2.Push the line key adjacent to the LAST LEG RE- The BSCU CHAN 1(2)/LAST LEG REPORT page PORT indication. comes into view. · Make sure that these CFDS fault messages are not shown: BRK ALTN PRESS TRANSDUCER (101GG) or (100GG)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-46-00-040-001-A - Check of the BSCU after BRAKES N/WS MINOR FAULT Caution message shown on the Upper Ecam Display Unit ACTION

RESULT ABCU (95GG)/BRK NORM SEL VALVE XDCR (96GG)

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 301450, 500-600 5.

Close-up Subtask 32-46-00-860-068-A A.

Put the aircraft back to its initial configuration. (1) On the MCDU, push the line select key adjacent to the RETURN indication until the CFDS menu page comes into view. (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (3) Make an entry in the logbook to tell persons that the BSCU is checked. (4) Remove the WARNING NOTICE(S).

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-47-00-040-001-A - Brake Temperature Sensor Deactivation

** ON A/C ALL TASK 32-47-00-040-001-A Brake Temperature Sensor Deactivation 1.

Reason for the Job MMEL 32-07-01B Brakes Temperature Indication on the WHEEL SD page

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

QTY AR AR AR AR

DESIGNATION CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER TAPE - ADHESIVE WARNING NOTICE(S)

Consumable Materials REFERENCE No specific

DESIGNATION lockwire-corrosion resistant steel dia. 0.8 mm (0.032 in.)

C. Referenced Information REFERENCE DESIGNATION Brake Temperature Sensor Deactivation/Reactivation SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-47-00-040-001-A - Brake Temperature Sensor Deactivation

A

A 6GW 4GW

7GW 5GW

A

1 2

N_MM_324700_4_ABM0_01_00

Figure 32-47-00-991-00100-00-A / SHEET 1/1 - Brake Temperature Sensor Deactivation/Reactivation ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-47-00-040-001-A - Brake Temperature Sensor Deactivation

3.

Job Set-up Subtask 32-47-00-941-050-A A.

Put a WARNING NOTICE(S) in position in the cockpit to tell persons not to operate the landing gear control lever and the brake pedals.

Subtask 32-47-00-865-051-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU

4.

DESIGNATION HYDRAULIC/BRK/TEMP/DET/UNIT HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY

FIN 1GW 4GG

LOCATION M37 M36

Procedure (Ref. Fig. Brake Temperature Sensor Deactivation/Reactivation SHEET 1) Subtask 32-47-00-040-050-A A.

Deactivation of the Brake Temperature Sensor 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. (1) Disconnect the connector (2) from the temperature sensor (1). (2) Put CAP - BLANKING on the two connectors. (3) Clean the electrical connector (2) of the brake temperature sensor and apply two or three turns of TAPE - ADHESIVE around the electrical connector (3). (4) Tightly wind 3 or 4 turns of lockwire-corrosion resistant steel dia. 0.8 mm (0.032 in.) around the tape on the electrical connector (2). Twist the lockwire and put it through the nearest locking hole. NOTE: Make sure that the lockwire cannot rub when the landing gear operates.

5.

Close-up Subtask 32-47-00-942-051-A A.

Remove the safety device. (1) Remove the warning notice. (2) Make an entry in the logbook.

Subtask 32-47-00-865-054-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU

DESIGNATION HYDRAULIC/BRK/TEMP/DET/UNIT HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY

FIN 1GW 4GG

LOCATION M37 M36

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-49-00-040-001-A - Deactivation of the Tire Pressure Indicating System (TPIS)

** ON A/C 236-236, 241-241 TASK 32-49-00-040-001-A Deactivation of the Tire Pressure Indicating System (TPIS) WARNING:

MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

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.

1.

Reason for the Job MMEL 32-09-02A WHEEL TYRE LO PR Alert

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific No specific

B.

QTY AR AR AR AR AR AR

DESIGNATION CAP - BLANKING GAGE - PRESSURE, TIRE PLACARD SAFETY BARRIER(S) SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S) Torque wrench: range to between 0.6 and 0.9 m.daN (53.10 and 79.65 lbf.in)

Consumable Materials REFERENCE No specific

DESIGNATION corrosion resistant steel lockwire dia 0.8 mm (0.032 in.)

C. Expendable Parts FIG.ITEM 5 7 7 5

DESIGNATION cotter pin seal plug cotter pin seal plug

IPC-CSN 32-49-15-01-010 32-49-15-01-070 32-49-16-01-010 32-49-16-01-070

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-49-00-040-001-A - Deactivation of the Tire Pressure Indicating System (TPIS)

D. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 31-60-00-860-001-A). EIS Start Procedure (Ref. 31-60-00-860-002-A). EIS Stop Procedure (Ref. 32-41-00-210-003-A). Functional Check of Tire Pressures (Ref. 32-48-51-000-002-A). Removal of the Impeller Assy (Ref. 32-48-51-400-002-A). Installation of the Impeller Assy Nose Landing Gear Tire Pressure-Transducer - Deactivation/Reactivation SHEET 1 Main Landing Gear Tire Pressure-Transducer - Deactivation/Reactivation SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-49-00-040-001-A - Deactivation of the Tire Pressure Indicating System (TPIS)

A 1

A

2

3

A

4 5 6

7

8

9

13

12

11 10

N_MM_324900_4_AAM0_01_00

Figure 32-49-00-991-00100-00-A / SHEET 1/1 - Nose Landing Gear Tire Pressure-Transducer - Deactivation/Reactivation ** ON A/C 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-49-00-040-001-A - Deactivation of the Tire Pressure Indicating System (TPIS)

A

A A A 1

A

B 2

B

5 3 4 PRESSURE SENSOR POSITION

1

6 MAIN GEAR WHEEL

7 8

N_MM_324900_4_AGM0_01_00

Figure 32-49-00-991-00200-00-C / SHEET 1/1 - Main Landing Gear Tire Pressure-Transducer - Deactivation/Reactivation ** ON A/C 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-49-00-040-001-A - Deactivation of the Tire Pressure Indicating System (TPIS)

3.

Job Set-up Subtask 32-49-00-941-052-A A.

Safety Precautions (1) In the cockpit, on panel 400VU, put WARNING NOTICE(S) in position to tell persons not to operate the landing gear control-lever. (2) On the steering handwheels (CAPT and F/O) and on the brake pedals, put WARNING NOTICE(S) in position to tell persons not to operate them. (3) Put the SAFETY BARRIER(S) in position.

Subtask 32-49-00-220-050-A B.

Dimensional Check (1) Use a GAGE - PRESSURE, TIRE to do a pressure check with the related WHEEL TIRE LO PR warning (Ref. AMM TASK 32-41-00-210-003) . (2) If the tire pressure is correct, do the procedure that follows.

Subtask 32-49-00-865-068-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU

4.

DESIGNATION HYDRAULIC/TIRE/PRESS

FIN 1GV

LOCATION M31

Procedure Subtask 32-49-00-040-050-A A.

Deactivation of the Nose Landing Gear Tire Pressure-Transducer (Ref. Fig. Nose Landing Gear Tire Pressure-Transducer - Deactivation/Reactivation SHEET 1) 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. (1) Cut and remove the lockwire from the screws (10). (2) Remove the screws (10) and the washers (11). (3) Release the grommet (12). (4) Remove the cover (8). (5) Disconnect the electrical connector from the connector (13). (6) Install CAP - BLANKING on the electrical connector (13). (7) Remove the grommet (12). (8) Remove the cotter pin (5) and discard it. (9) Remove the nut (6). (10) Remove the pressure transducer (4). (11) Put the IPC -CSN (32-49-15-01-070) seal plug (7) on the transducer holder (2) and attach it with the nut (6). (12) TORQUE the nut (6) to between 0.6 and 0.9 m.daN (53.10 and 79.65 lbf.in). (13) Safety the nut (6) with a new IPC -CSN (32-49-15-01-010) cotter pin (5).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-49-00-040-001-A - Deactivation of the Tire Pressure Indicating System (TPIS)

(14) Install the grommet (12). (15) Put the cover (8) in position. (16) Install the drive (9) in its housing. (17) Install the washers (11) and the screws (10). (18) Tighten the screws (10) and safety them with corrosion resistant steel lockwire dia 0.8 mm (0.032 in.) . Subtask 32-49-00-040-052-C B.

Deactivation of the Main Landing Gear Tire Pressure-Transducer (Ref. Fig. Main Landing Gear Tire Pressure-Transducer - Deactivation/Reactivation SHEET 1) (1) Remove the impeller assy (Ref. AMM TASK 32-48-51-000-002) . (2) Disconnect the electrical connector (2). (3) Install CAP - BLANKING on the electrical connector (2). (4) Remove and discard the cotter pin (7). (5) Remove the nut (8). (6) Remove the main landing gear tire pressure-transducer (6). (7) Put the IPC -CSN (32-49-16-01-070) seal plug (5) on the transducer holder and attach it with the nut (8). (8) TORQUE the nut (8) to between 0.6 and 0.9 m.daN (53.10 and 79.65 lbf.in). (9) Install a new IPC -CSN (32-49-16-01-010) cotter pin (7) on the nut (8). (10) Install the impeller assy (Ref. AMM TASK 32-48-51-400-002) .

Subtask 32-49-00-865-055-A C.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU

DESIGNATION HYDRAULIC/TIRE/PRESS

FIN 1GV

LOCATION M31

Subtask 32-49-00-860-054-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) On the lower ECAM DU, on the WHEEL page, make sure that the WHEEL TIRE LO PR warning message does not show. (4) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (5) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Subtask 32-49-00-869-052-A E.

Post-Flight Report Effects NOTE: Each Post Flight Report shows a fault for the TPIS. Although more than one TPIS sensor can be deactivated, one fault will show for ATA 32-49-00.

5.

Close-up

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-49-00-040-001-A - Deactivation of the Tire Pressure Indicating System (TPIS)

Subtask 32-49-00-942-050-A A.

Removal of Equipment (1) Remove the safety barriers. (2) Remove the warning notices. (3) Make sure that the work area is clean and clear of tools and other items. (4) Make an entry in the log book to tell persons to do a check of the pressure of the related tire at three day intervals (Ref. AMM TASK 32-41-00-210-003) . (5) Put a PLACARD in the cockpit to tell persons that the TPIS is deactivated for the related tire.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-49-00-040-002-A - Deactivation of the Tire Pressure Indicating Computer (TPIC)

** ON A/C 236-236, 241-241 TASK 32-49-00-040-002-A Deactivation of the Tire Pressure Indicating Computer (TPIC) 1.

Reason for the Job MMEL 32-09-02B WHEEL TYRE LO PR Alert

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

QTY AR AR AR

DESIGNATION GAGE - PRESSURE, TIRE SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 31-60-00-860-001-A). EIS Start Procedure (Ref. 31-60-00-860-002-A). EIS Stop Procedure (Ref. 32-41-00-210-003-A). Functional Check of Tire Pressures TPIS Cockpit Effects - Deactivation/Reactivation SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-49-00-040-002-A - Deactivation of the Tire Pressure Indicating Computer (TPIC)

WHEEL

UP LOCK

UP LOCK

UP LOCK XX

XX

NW STEER L/G CTL 140

°C

140

1

REL

2

XX

PSI

XX

ANTI SKID AUTO BRK

155

°C

3

REL

4

XX

PSI

XX

140

MED

TAT +19 °C SAT +18 °C

GMT 23:56

G.W. 60 3T C.G. 28 1 %

AFTER DEACTIVATION

WHEEL

UP LOCK

UP LOCK

UP LOCK 195

195

NW STEER L/G CTL 140

°C

140

1

REL

2

195

PSI

195

ANTI SKID AUTO BRK

155

°C

3

REL

4

195

PSI

195

140

MED

TAT +19 °C SAT +18 °C

GMT 23:56

G.W. 60 3T C.G. 28 1 %

AFTER REACTIVATION

NOTE: TYPICAL DISPLAY N_MM_324900_4_AKM0_01_00

Figure 32-49-00-991-00300-00-A / SHEET 1/1 - TPIS Cockpit Effects - Deactivation/Reactivation ** ON A/C 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-49-00-040-002-A - Deactivation of the Tire Pressure Indicating Computer (TPIC)

3.

Job Set-up Subtask 32-49-00-040-053-A A.

Dimensional Check (1) Use a GAGE - PRESSURE, TIRE to do a pressure check with the related WHEEL TIRE LO PR warning (Ref. AMM TASK 32-41-00-210-003) . (2) If the tire pressure is correct, do the procedure that follows.

Subtask 32-49-00-865-070-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU

4.

DESIGNATION HYDRAULIC/TIRE/PRESS

FIN 1GV

LOCATION M31

Procedure (Ref. Fig. TPIS Cockpit Effects - Deactivation/Reactivation SHEET 1) Subtask 32-49-00-040-051-A A.

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) On the lower ECAM DU, WHEEL page, the tire pressure indications show amber 'XX'. (4) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (5) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

5.

Close-up Subtask 32-49-00-942-051-A A.

Removal of Equipment (1) Make sure that the work area is clean and clear of tools and other items. (2) Make an entry in the log book to tell persons to do a check of the pressure of the tires at three day intervals (Ref. AMM TASK 32-41-00-210-003) . (3) Put a WARNING NOTICE(S) in the cockpit to tell persons that the TPIC is deactivated.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-31-00-040-003-A - Check of the System 2 Proximity Sensors of the Landing Gear and the Landing Gear Doors

** ON A/C ALL TASK 32-31-00-040-003-A Check of the System 2 Proximity Sensors of the Landing Gear and the Landing Gear Doors 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.

1.

Reason for the Job MMEL 32-32-02A LGCIU 2 RH L/G Shock Absorber Proximity Detector MMEL 32-32-03A LGCIU 2 LH L/G Shock Absorber Proximity Detector MMEL 32-32-04A LGCIU 2 Nose L/G Shock Absorber Proximity Detector MMEL 32-32-05A LGCIU 2 RH L/G Down Lock Proximity Detector MMEL 32-32-06A LGCIU 2 LH L/G Down Lock Proximity Detector MMEL 32-32-07A LGCIU 2 Nose L/G Down Lock Proximity Detector MMEL 32-32-08A LGCIU 2 RH L/G Up Lock Proximity Detector MMEL 32-32-09A LGCIU 2 LH L/G Up Lock Proximity Detector MMEL 32-32-10A LGCIU 2 Nose L/G Up Lock Proximity Detector MMEL 32-32-11A LGCIU 2 RH L/G Doors Open Proximity Detector MMEL 32-32-12A LGCIU 2 LH L/G Doors Open Proximity Detector MMEL 32-32-13A LGCIU 2 Nose L/G Doors Open Proximity Detector MMEL 32-32-14A LGCIU 2 RH L/G Doors Closed Proximity Detector MMEL 32-32-15A LGCIU 2 LH L/G Doors Closed Proximity Detector MMEL 32-32-16A LGCIU 2 Nose L/G Doors Closed Proximity Detector MMEL 32-32-17A LGCIU 2 Bogie Proximity Detector 11GA(10GA), 13GA, 17GA(16GA), 19GA, 23GA(22GA), 25GA, 29GA(28GA), 31GA, 35GA(34GA), 39GA(38GA).

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-31-00-040-003-A - Check of the System 2 Proximity Sensors of the Landing Gear and the Landing Gear Doors

REFERENCE No specific No specific No specific No specific No specific (98D32203502000) B.

QTY 1 1 AR AR AR AR

Referenced Information REFERENCE (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 32-00-00-481-001-A). (Ref. 32-00-00-481-002-A). (Ref. 32-00-00-860-001-A). (Ref. 32-00-00-860-001-A-01). (Ref. 32-12-00-010-001-A). (Ref. 32-12-00-410-001-A). (Ref. 32-22-00-010-001-A). (Ref. 32-22-00-410-001-A). (Ref. 32-69-00-740-001-A).

3.

DESIGNATION ACCESS PLATFORM 2M (6 FT) CAP - PROTECTION SAFETY BARRIER(S) SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S) SAFETY PIN - NLG DOOR

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Installation of the Safety Devices on the Landing Gears Installation of the Safety Devices on the Landing Gear Doors Flight Configuration Precautions with Electrical Power Flight Configuration Precautions without Electrical Power Open the Main Gear Doors for Access Close the Main Gear Doors after Access Nose Gear Doors - Ground Doors Opening Nose Gear Doors - Ground Doors Closing BITE Check of Landing-Gear Control Interface-Unit (LGCIU) With Use of MCDU to Ensure that Continuous BITE is Operative

Job Set-up Subtask 32-31-00-941-069-A A.

Safety Precautions (1) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations. (2) Make sure that the ground safety locks are on the landing gear (Ref. AMM TASK 32-00-00-481001) . (3) On the panel 400VU: · make sure that the landing-gear control-lever 6GA is in the DOWN position · put a WARNING NOTICE(S) in position to tell persons not to operate the landing gear/landing gear doors.

Subtask 32-31-00-010-064-A B.

Get Access (1) Open the applicable MLG door (Ref. AMM TASK 32-12-00-010-001) or the applicable NLG door (Ref. AMM TASK 32-22-00-010-001) . (2) Make sure that the GROUND LOCK SLEEVE is installed if you open the MLG doors on the applicable MLG door actuating-cylinder (Ref. AMM TASK 32-00-00-481-002) . (3) Make sure that the SAFETY PIN - NLG DOOR (98D32203502000) is installed, if you open the NLG doors, in the rigging holes of the left and right nose gear doors (Ref. AMM TASK 32-00-00-481-002) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-31-00-040-003-A - Check of the System 2 Proximity Sensors of the Landing Gear and the Landing Gear Doors

(4) Put the ACCESS PLATFORM 2M (6 FT) in position in zone 734/744 for the MLG. (5) Put the ACCESS PLATFORM 2M (6 FT) in position in zone 123 for the NLG. Subtask 32-31-00-869-100-A C.

Flight Configuration Precautions (1) If the electrical power is not necessary for other maintenance tasks, de-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . Thus it is not necessary to do the flight configuration precautions. (2) If the electrical power is necessary, do the precautions for flight configuration (Ref. AMM TASK 3200-00-860-001) before you open the LGCIU circuit breakers.

Subtask 32-31-00-865-089-A D.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU 121VU 121VU

DESIGNATION FIN L/G/LGCIU/SYS1/NORM 1GA HYDRAULIC/LGCIU/SYS2 2GA HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA

LOCATION C09 Q35 Q34

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 EMB SB 32-1346 for A/C 016-019, 021-021, 201-201, 203-207, 209-211, 215-222, 226-235, 237-237, 239-240, 242-244, 350-350 121VU LGCIU/BAT SPLY/SYS2 59GA R33 121VU LGCIU/BAT SPLY/SYS1 58GA R32 ** ON A/C 401-450 121VU LGCIU/BAT SPLY/SYS2 121VU LGCIU/BAT SPLY/SYS1

59GA 58GA

R32 R31

** ON A/C ALL 4.

Procedure Subtask 32-31-00-040-052-A A.

Check of the System 2 Proximity Sensors of the Landing Gear and Landing Gear Doors (1) Do a check of the related proximity sensor(s) and make sure that there is no damage. (a) If there is damage, a flight in this MMEL condition is not permitted. NOTE: This MMEL condition is only applicable when there is an electrical fault. (2) Disconnect the electrical connector from the unserviceable system 2 proximity sensor. (3) Put a CAP - PROTECTION on the disconnected electrical connector. (4) Safety the disconnected electrical connector to the applicable aircraft structure. (5) Do a BITE test (Ref. AMM TASK 32-69-00-740-001) to make sure that the correct system 2 proximity sensor has been electrically deactivated. (6) Make an entry in the aircraft technical log that the applicable system 2 proximity sensor is electrically deactivated.

Subtask 32-31-00-865-136-A

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-31-00-040-003-A - Check of the System 2 Proximity Sensors of the Landing Gear and the Landing Gear Doors

B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU 121VU 121VU

DESIGNATION FIN L/G/LGCIU/SYS1/NORM 1GA HYDRAULIC/LGCIU/SYS2 2GA HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA

LOCATION C09 Q35 Q34

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 EMB SB 32-1346 for A/C 016-019, 021-021, 201-201, 203-207, 209-211, 215-222, 226-235, 237-237, 239-240, 242-244, 350-350 121VU LGCIU/BAT SPLY/SYS2 59GA R33 121VU LGCIU/BAT SPLY/SYS1 58GA R32 ** ON A/C 401-450 121VU LGCIU/BAT SPLY/SYS2 121VU LGCIU/BAT SPLY/SYS1

59GA 58GA

R32 R31

** ON A/C ALL 5.

Close-up Subtask 32-31-00-410-062-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the access platform(s). (3) Close the MLG doors (Ref. AMM TASK 32-12-00-410-001) or the NLG doors (Ref. AMM TASK 3222-00-410-001) as applicable.

Subtask 32-31-00-942-076-A B.

Removal of Equipment (1) Remove the SAFETY BARRIER(S). (2) Remove the WARNING NOTICE(S). (3) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-31-00-040-802-A - Deactivation of the Landing Gear Gravity-Extension System

** ON A/C ALL TASK 32-31-00-040-802-A Deactivation of the Landing Gear Gravity-Extension System Task Summary MMEL or CDL Ref MMEL 32-33-01A

Access NO

Test YES

1.

Reason for the Job MMEL 32-33-01A Landing Gear Gravity Extension System

2

Job Set-up Information A.

Mhr 00.3

E/T 00.3

Nb Men 1

Referenced Information REFERENCE (Ref. 05-59-32-869-001-A).

3.

Specific Tools NO

DESIGNATION Preparation for Flight with Gear Down

Job Set-up Subtask 32-31-00-860-134-A A.

4.

There is no special job set-up for this task.

Procedure Subtask 32-31-00-040-053-A A.

Deactivate the Landing Gear Gravity-Extension System (1) Prepare for flight with the landing gear down (Ref. AMM TASK 05-59-32-869-001) . (2) Make an applicable entry in the aircraft technical log.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-41-00-040-002-A - Check of the Nose Wheel when one tie bolt is missing

** ON A/C ALL TASK 32-41-00-040-002-A Check of the Nose Wheel when one tie bolt is missing 1.

Reason for the Job MMEL 32-41-01A Nose Wheel Tie Bolt

2

Job Set-up Information A.

Referenced Information REFERENCE (Ref. 32-41-12-000-001-A). (Ref. 32-41-12-400-001-A).

3.

DESIGNATION Removal of the NLG Wheel (for corrective action) Installation of the NLG Wheel (for corrective action)

Job Set-up Subtask 32-41-00-941-056-A A.

4.

Not applicable

Procedure Subtask 32-41-00-210-073-A A.

Check of the related Nose Wheel (1) Make sure that no broken pieces of the tie bolt are in the wheel. If there are pieces of the tie bolt in the wheel, remove them. (2) Do a check of the wheel for damage, no damage is permitted. NOTE: If the wheel is damaged, refer to the AMM (Ref. AMM TASK 32-41-12-000-001) and (Ref. AMM TASK 32-41-12-400-001) to replace the wheel.

5.

Close-up Subtask 32-41-00-942-055-A A.

Aircraft Maintenance Configuration (1) Make sure that the work area is clean and clear of tools and other items. (2) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-41-00-040-003-A - Check of the Main Wheel when one tie bolt is missing

** ON A/C ALL TASK 32-41-00-040-003-A Check of the Main Wheel when one tie bolt is missing 1.

Reason for the Job MMEL 32-41-02A Main Wheel Tie Bolt

2

Job Set-up Information A.

Referenced Information REFERENCE (Ref. 32-41-11-000-006-A). (Ref. 32-41-11-400-006-A). (Ref. 32-41-11-000-006-A). (Ref. 32-41-11-400-006-A).

3.

DESIGNATION Removal of the MLG Wheel Installation of the MLG Wheel Removal of the MLG Wheel (for corrective action) Installation of the MLG Wheel (for corrective action)

Job Set-up Subtask 32-41-00-941-057-A A.

4.

Not applicable

Procedure Subtask 32-41-00-210-074-A A.

Check of the related Main Wheel (1) Remove the related main wheel (Ref. AMM TASK 32-41-11-000-006) . (2) Make sure that no broken pieces of the tie bolt are in the wheel. If there are pieces of the tie bolt in the wheel, remove them. (3) Do a check the wheel for damage, no damage is permitted. NOTE: If the wheel is damaged, refer to the AMM (Ref. AMM TASK 32-41-11-000-006) and (Ref. AMM TASK 32-41-11-400-006) to replace the wheel. (4) Install the main wheel (Ref. AMM TASK 32-41-11-400-006) .

5.

Close-up Subtask 32-41-00-942-056-A A.

Aircraft Maintenance Configuration (1) Make sure that the work area is clean and clear of tools and other items. (2) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

** ON A/C ALL TASK 32-42-00-040-003-A Deactivation of the Main Wheel Brakes WARNING:

MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

WARNING:

MAKE SURE THAT THE CONTROLS AGREE WITH THE POSITION OF THE ITEMS THEY OPERATE BEFORE YOU PRESSURIZE A HYDRAULIC SYSTEM. UNWANTED MOVEMENT OF HYDRAULICALLY OPERATED ITEMS CAN CAUSE SERIOUS INJURY AND/OR DAMAGE.

WARNING:

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

Task Summary MMEL or CDL Ref MMEL 32-42-01A 1.

Reason for the Job MMEL 32-42-01A Main Wheel Brake

2

Job Set-up Information A.

Access NO

Specific Tools YES

Mhr 01.0

E/T 02.0

Nb Men 2

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific

B.

Test YES

QTY AR AR AR AR AR AR

DESIGNATION CAP - BLANKING CONTAINER 5 L (1.32 USGAL) HOSE - VINYL PLACARD TAPE - WIDE SELF-ADHESIVE - FABRIC WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. 02ABA1) (Material No. 14QFB1) No specific

DESIGNATION Phosphate Ester Hydraulic Fluid-General Power - Wire-Locking Dia: 0.8 mm CRES Nickel Alloy corrosion-resistant steel lockwire dia 0.8 mm

C. Referenced Information REFERENCE (Ref. 12-12-29-611-001-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02).

DESIGNATION Fill the Hydraulic Fluid Reservoir with a Hand Pump Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

REFERENCE (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 29-10-00-864-001-A). (Ref. 29-10-00-864-002-A). (Ref. 29-14-00-614-001-A). (Ref. 29-14-00-614-002-A). (Ref. 29-14-00-614-002-A-01). (Ref. 29-23-00-863-001-A). (Ref. 29-24-00-863-001-A). (Ref. 32-11-12-000-001-A). (Ref. 32-41-11-400-006-A). (Ref. 32-42-00-710-001-A). (Ref. 32-42-00-720-002-A). (Ref. 32-42-00-720-003-A). (Ref. 32-42-27-000-001-A). (Ref. 32-43-00-710-001-A). (Ref. 32-46-00-740-001-A).

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Depressurize the Green Hydraulic System Depressurize the Yellow Hydraulic System Depressurization of the Hydraulic Reservoirs Pressurization of the Hydraulic Reservoirs through the Ground Connector Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU) Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump Pressurize the Yellow Hydraulic System with the Electric Pump Removal of the MLG Hydraulic Dressings Installation of the MLG Wheel Operational Check of the Normal Braking System Functional Test of the Tachometers and the Anti-Skid System with the Normal Braking System ON Functional Test of the tachometers with the AIDS. Removal of the Brake Operational Check of Alternate Braking System BITE Test of the BSCU

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350, 377-400, 500-600 Deactivation without Brake Removal SHEET 1 ** ON A/C 301-349, 351-376 Deactivation with Brake Removal SHEET 1 ** ON A/C 401-450 Deactivation without Brake Removal SHEET 1 ** ON A/C 201-201, 205-207, 209-211, 217-220, 222-222, 226-235, 237-237, 239-240, 242-250, 350-350 PRE SB 32-1244 for A/C 209-209 Deactivation with Brake Removal SHEET 1 ** ON A/C 016-022, 024-100, 112-150, 203-204, 208-208, 212-216, 221-221, 223-225, 236-236, 238-238, 241-241, 377-400, 500-600 POST SB 32-1327 for A/C 211-211, 226-226, 231-232, 237-237, 240-240, 242-244 POST SB 32-1244 for A/C 209-209 Deactivation with Brake Removal SHEET 1 ** ON A/C 301-349, 351-376 Deactivation with Brake Removal SHEET 1 ** ON A/C 401-450 Deactivation with Brake Removal SHEET 1 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350, 377-450, 500-600 Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

REFERENCE

DESIGNATION

** ON A/C 301-349, 351-376 Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

NOTE:-THE YELLOW HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS BEHIND THE LEG GEAR. -THE GREEN HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS IN FRONT OF THE LEG GEAR.

A 2642GM

A A

2644GM 2641GM

A 6

A

5

2643GM

5 WHEEL SIDE

1

2

6

LEG GEAR SIDE

BRAKE TEMPERATURE SENSOR ELECTRIC CONNECTION

4

3

N_MM_324200_4_AAM0_01_00

Figure 32-42-00-991-00100-00-A / SHEET 1/1 - Deactivation without Brake Removal ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350, 377-400, 500-600 | EMB SB 32-1244 for A/C 204-204 | EMB SB 32-1327 for A/C 203-203 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

A

B

A 2641GM (2644GM) 2643GM (2642GM)

6 5

A LH SHOWN RH SYMMETRICAL

1

WHEEL SIDE

2

LEG GEAR SIDE

4 3 NOTE: - THE YELLOW HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS BEHIND THE LEG GEAR. - THE GREEN HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS IN FRONT OF THE LEG GEAR.

BRAKE TEMPERATURE SENSOR ELECTRIC CONNECTION

B TYPICAL N_MM_324200_4_ARM0_01_00

Figure 32-42-00-991-00100-00-F / SHEET 1/1 - Deactivation with Brake Removal ** ON A/C 301-349, 351-376 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

NOTE : -THE YELLOW HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS BEHIND THE GEAR LEG. -THE GREEN HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS IN FRONT OF THE GEAR LEG.

A 2642GM

A 2641GM

A 2644GM

A 6 6

A

2643GM

WHEEL SIDE 1 5

2

GEAR LEG SIDE

BRAKE TEMPERATURE SENSOR ELECTRICAL CONNECTION

4

3

N_MM_324200_4_YAM0_01_00

Figure 32-42-00-991-00100-00-H / SHEET 1/1 - Deactivation without Brake Removal ** ON A/C 401-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

NOTE: -THE YELLOW HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS BEHIND THE LEG GEAR. -THE GREEN HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS IN FRONT OF THE LEG GEAR.

A 2642GM

A A

2644GM 2641GM

A

3

2643GM 4 WHEEL SIDE 5 LEG GEAR SIDE 6 7

12

8

11

10

9

7 8 N_MM_324200_4_BBM0_01_00

Figure 32-42-00-991-00200-00-J / SHEET 1/1 - Deactivation with Brake Removal ** ON A/C 201-201, 205-207, 209-211, 217-220, 222-222, 226-235, 237237, 239-240, 242-250, 350-350 | PRE SB 32-1244 for A/C 209-209 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

NOTE: -THE YELLOW HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS BEHIND THE LEG GEAR. -THE GREEN HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS IN FRONT OF THE LEG GEAR.

A 2642GM

A A

2644GM 2641GM

A 3

A 2643GM

4 WHEEL SIDE 5

LEG GEAR SIDE 6 7

8

12

11

10

9

7 8 N_MM_324200_4_ABM0_01_00

Figure 32-42-00-991-00200-00-A / SHEET 1/1 - Deactivation with Brake Removal ** ON A/C 016-022, 024-100, 112-150, 203-204, 208-208, 212-216, 221-221, 223225, 236-236, 238-238, 241-241, 377-400, 500-600 | EMB SB 32-1244 for A/C 204204 | POST SB 32-1244 for A/C 209-209 | EMB SB 32-1327 for A/C 203-203 | POST SB 32-1327 for A/C 211-211, 226-226, 231-232, 237-237, 240-240, 242-244 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

A

B

A 2641GM (2644GM) 2643GM (2642GM)

A

3

LH SHOWN RH SYMMETRICAL

4

WHEEL SIDE 5

LEG GEAR SIDE 6 7 8

12

11 NOTE: - THE YELLOW HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS BEHIND THE LEG GEAR. - THE GREEN HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS IN FRONT OF THE LEG GEAR.

10

B

7 8

9

TYPICAL N_MM_324200_4_ASM0_01_00

Figure 32-42-00-991-00200-00-F / SHEET 1/1 - Deactivation with Brake Removal ** ON A/C 301-349, 351-376 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

NOTE : - THE YELLOW HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS BEHIND THE GEAR LEG. - THE GREEN HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS IN FRONT OF THE GEAR LEG.

A 2642GM

A 2641GM

A 2644GM

A

A

2643GM

3

4

WHEEL SIDE

5

GEAR LEG SIDE

6 7

8

12

11

10 9 7 8 N_MM_324200_4_YBM0_01_00

Figure 32-42-00-991-00200-00-H / SHEET 1/1 - Deactivation with Brake Removal ** ON A/C 401-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

B

A

B

2642GM

A A

2641GM

2644GM

A 2643GM

A

1

3 4

4 WHEEL SIDE

1

3

LEG GEAR SIDE 2 NOTE: - THE YELLOW HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS BEHIND THE LEG GEAR. -THE GREEN HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS IN FRONT OF THE LEG GEAR. 1

RH SHOWN LH SYMMETRICAL

N_MM_324200_4_AQM0_01_00

Figure 32-42-00-991-01000-00-A / SHEET 1/2 - Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350, 377-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

B

1

C

D

5

6

2

C D

7 5 8 6

NOTE: 1

RH SHOWN LH SYMMETRICAL N_MM_324200_4_AQM0_02_00

Figure 32-42-00-991-01000-00-A / SHEET 2/2 - Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350, 377-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 12 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

A

B C A 2641GM (2644GM) 2643GM (2642GM)

A

3

LH SHOWN RH SYMMETRICAL 4 WHEEL SIDE

1

LEG GEAR SIDE 2

NOTE: - THE YELLOW HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS BEHIND THE LEG GEAR. - THE GREEN HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS IN FRONT OF THE LEG GEAR.

B TYPICAL N_MM_324200_4_ATM0_01_00

Figure 32-42-00-991-01000-00-B / SHEET 1/2 - Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak ** ON A/C 301-349, 351-376 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 13 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

E

D

5 6

2

C LH SHOWN RH SYMMETRICAL 7 5

D

8 6

E

N_MM_324200_4_ATM0_02_00

Figure 32-42-00-991-01000-00-B / SHEET 2/2 - Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak ** ON A/C 301-349, 351-376 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 14 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

3.

Job Set-up Subtask 32-42-00-941-061-A A.

Safety Precautions (1) Put the WARNING NOTICE(S) in position to tell persons not to operate the landing gear control lever and the brake pedals.

Subtask 32-42-00-740-057-A B.

BITE Test (1) Do the BITE test of the BSCU (Ref. AMM TASK 32-46-00-740-001) . (a) If there is a fault message, make sure that it is not related to the tachometer of the serviceable brake.

Subtask 32-42-00-860-068-A C.

Aircraft Maintenance Configuration (1) Depressurize the Green and Yellow hydraulic systems (Ref. AMM TASK 29-10-00-864-001) (Ref. AMM TASK 29-10-00-864-002) . (2) Parking brake configuration CAUTION: MAKE SURE THAT ALL THE PISTONS OF THE BRAKE ARE IN THE RELEASED POSITION. (a) Make sure that the PARKING BRK control switch is set to OFF before you do the deactivation.

4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350, 377-400, 500-600 EMB SB 32-1244 for A/C 204-204 EMB SB 32-1327 for A/C 203-203 (Ref. Fig. Deactivation without Brake Removal SHEET 1) ** ON A/C 301-349, 351-376 (Ref. Fig. Deactivation with Brake Removal SHEET 1) ** ON A/C 401-450 (Ref. Fig. Deactivation without Brake Removal SHEET 1) ** ON A/C ALL Subtask 32-42-00-040-060-A A.

Deactivations of the Main Wheel Brakes NOTE: There are three procedures to deactivate a wheel brake: - Deactivation without removal of the wheel brake. - Deactivation with removal of the wheel brake system of the wheel brake. - Deactivation of the wheel brake with disconnection of flexible hoses from normal and alternate braking system if there is a leak. If the wheel brake cannot move and/or if the stators, rotors, torque tubes or heat shield are damaged, do the removal and the deactivation of the wheel brake. If you find no damage, do only the deactivation of the wheel brake.

Subtask 32-42-00-040-052-A

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 15 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

B.

Deactivation without Removal of the brake (1) Loosen the two knurled sleeves (1) and (4) of the half couplings (2) and (3). Turn and disconnect the half couplings. (2) Clean the sleeves (1) and (4) and apply two or three turns of the TAPE - WIDE SELF-ADHESIVE FABRIC 20 mm (0.7874 in.) to 30 mm (1.1811 in.). (3) Tightly wind three or four turns of the Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - (Material No. 14QFB1) around the tape on the sleeves (1) and (4). (4) Twist the lockwire and put it through the nearest locking hole you can get access to in the hexagonal head of the fixed half couplings (2) and (3). Tighten the lockwire and twist it. (5) Remove the two bleed screw plugs (6) from the bleed screw. (6) Connect a HOSE - VINYL to a bleed screw (5) and put the other end in a CONTAINER 5 L (1.32 USGAL) that contains Phosphate Ester Hydraulic Fluid-General Power - - (Material No. 02ABA1). (7) Slowly loosen the bleed screw (5) to release hydraulic residual pressure from the brake. (8) Tighten the bleed screw. (9) Disconnect the vinyl hose. (10) Install the bleed screw plug (6) on the bleed screw (5). (11) Do the same operations for the other bleed screw.

Subtask 32-42-00-910-052-A CAUTION:

C.

MAKE SURE THAT THE LOCKWIRE CANNOT WEAR DURING THE OPERATIONS OF THE LANDING GEAR.

Precaution:

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 EMB SB 32-1244 for A/C 204-204 EMB SB 32-1327 for A/C 203-203 Subtask 32-42-00-040-053-A D.

Deactivation with the Brake Removal

** ON A/C 201-201, 205-207, 209-211, 217-220, 222-222, 226-235, 237-237, 239-240, 242-250, 350-350 PRE SB 32-1244 for A/C 209-209 (Ref. Fig. Deactivation with Brake Removal SHEET 1) ** ON A/C 016-022, 024-100, 112-150, 203-204, 208-208, 212-216, 221-221, 223-225, 236-236, 238-238, 241-241, 377-400, 500-600 POST SB 32-1244 for A/C 209-209 POST SB 32-1327 for A/C 211-211, 226-226, 231-232, 237-237, 240-240, 242-244 EMB SB 32-1244 for A/C 204-204 EMB SB 32-1327 for A/C 203-203 (Ref. Fig. Deactivation with Brake Removal SHEET 1) ** ON A/C 301-349, 351-376 (Ref. Fig. Deactivation with Brake Removal SHEET 1)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 16 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 EMB SB 32-1244 for A/C 204-204 EMB SB 32-1327 for A/C 203-203 (1) Remove the brake (Ref. AMM TASK 32-42-27-000-001) . NOTE: Install the nuts (8) and the washers (7) on the brake unit bolts (10) when you remove the brake unit. (2) Clean the sleeves (4) and (12) and the electrical connector (9) of the brake temperature sensor. Apply two or three turns of the TAPE - WIDE SELF-ADHESIVE - FABRIC 20 mm (0.79 in.) to 30 mm (1.18 in.): · around the sleeves (4) and (12), · around the electrical connector (9) of the brake temperature sensor. (3) Tightly wind two or three turns of the corrosion-resistant steel lockwire dia 0.8 mm : · around the tape on the sleeves (4) and (12), · around the tape on the electrical connector (9). (4) Twist the lockwire. Put it through the nearest locking hole you can get access to. NOTE: Make sure that the lockwire cannot rub when the landing gear operates. (5) Remove the PROTECTIVE CONE (J47779) from the wheel axle (6). (6) Install the main landing-gear wheel (Ref. AMM TASK 32-41-11-400-006) . ** ON A/C 401-450 Subtask 32-42-00-040-053-G D.

Deactivation with the Brake Removal (Ref. Fig. Deactivation with Brake Removal SHEET 1) (1) Remove the brake (Ref. AMM TASK 32-42-27-000-001) . NOTE: Install the nuts (8) and the washers (7) on the brake unit bolts (10) when you remove the brake unit. (2) Clean the sleeves (4) and (12) and the electrical connector (9) of the brake temperature sensor. Apply two or three turns of the TAPE - WIDE SELF-ADHESIVE - FABRIC 20 mm (0.79 in.) to 30 mm (1.18 in.): · around the sleeves (4) and (12), · around the electrical connector (9) of the brake temperature sensor. (3) Tightly wind two or three turns of the corrosion-resistant steel lockwire dia 0.8 mm : · around the tape on the sleeves (4) and (12), · around the tape on the electrical connector (9). (4) Twist the lockwire. Put it through the nearest locking hole you can get access to. NOTE: Make sure that the lockwire cannot rub when the landing gear operates. (5) Remove the GUIDE CONE (Q47323-1) from the wheel axle (6). (6) Install the main landing-gear wheel (Ref. AMM TASK 32-41-11-400-006) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 17 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

** ON A/C ALL Subtask 32-42-00-040-058-A E.

Disconnect the flexible hoses from the normal and alternate braking system to do the deactivation of the wheel brake because of a leak

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350, 377-450, 500-600 (Ref. Fig. Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak) ** ON A/C 301-349, 351-376 (Ref. Fig. Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak) ** ON A/C ALL (1) Depressurize the Green and Yellow hydraulic reservoirs (Ref. AMM TASK 29-14-00-614-001) . (2) Removal of the normal and alternate braking-system flexible-hoses that have leaks (a) If you find a leak on the normal braking flexible-hose (2): 1

Remove the flexible hose (2) with its quick-release connector from the brake self-sealing connector.

2

Put a CAP - BLANKING P/N MS21914-6J or P/N MS21914-6K or P/N MS21914-6R or P/N MS21914-6S on the related union.

3

Clean the brake hydraulic self-sealing-coupling and apply two or three turns of TAPE - WIDE SELF-ADHESIVE - FABRIC 20 mm (0.79 in.) to 30 mm (1.18 in.).

(b) If you find no leak on the flexible hose (2), do not remove the hose and the quick-release connector from the brake unit. (c) If you find a leak on the normal braking flexible-hose (5): 1

Remove the flexible hose (5) from the upper and the lower unions (Ref. AMM TASK 32-1112-000-001) .

2

Put a CAP - BLANKING P/N MS21914-6J or P/N MS21914-6K or P/N MS21914-6R or P/N MS21914-6S on the related unions.

(d) If you find no leak on the flexible hose (5), do not remove the hose. (e) If you find a leak on the alternate braking flexible-hose (6):

(f)

1

Remove the flexible hose (6) from the flexible hose (1) connection and from the union (8) (Ref. AMM TASK 32-11-12-000-001) .

2

Put a CAP - BLANKING P/N MS21914-6J or P/N MS21914-6K or P/N MS21914-6R or P/N MS21914-6S on the related unions to make sure that there are no leaks.

If you find no leak on the flexible hose (6), do not remove the hose.

(g) If you find a leak on the alternate braking flexible-hose (1): 1

Remove the flexible hose (1) with its quick-release coupling from the brake hydraulic selfsealing-coupling (Ref. AMM TASK 32-11-12-000-001) .

2

Put a CAP - BLANKING P/N MS21914-6J or P/N MS21914-6K or P/N MS21914-6R or P/N MS21914-6S on the related union.

3

Clean the brake hydraulic self-sealing-coupling and apply two or three turns of TAPE - WIDE SELF-ADHESIVE - FABRIC 20 mm (0.79 in.) to 30 mm (1.18 in.).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 18 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

(h) If you find no leak on the flexible hose (1), do not remove the hose and the quick-release coupling from the brake unit. (3) Remove the bleed screw plug (3) from the related bleed screw (4). (4) Connect a HOSE - VINYL to the bleed screws (4) and put the other end in a CONTAINER 5 L (1.32 USGAL) that contains Phosphate Ester Hydraulic Fluid-General Power - - (Material No. 02ABA1). (5) Release the remaining hydraulic pressure from the wheel brake as follows: CAUTION: ONLY LOOSEN THE BLEED SCREW TO RELEASE THE HYDRAULIC PRESSURE FROM THE WHEEL BRAKE. DO NOT DO A FULL BLEEDING AND DO NOT TOUCH THE PISTONS WITH YOUR HAND. IF YOU DO NOT OBEY THESE INSTRUCTIONS, DAMAGE TO THE BRAKE CAN OCCUR. (a) Slowly loosen the bleed screw (4) to release the remaining hydraulic pressure from the wheel brake. (b) Tighten the bleed screw (4). (6) Disconnect the HOSE - VINYL. (7) Install the bleed screw plug (3) on the bleed screw (4). (8) Do the same procedure for the other bleed screw, if applicable. (9) Do a pressure test after the installation of the blanking caps to make sure that there is no leak: (a) For the normal braking-system deactivation, do the operational check of the normal braking system (Ref. AMM TASK 32-42-00-710-001) . Make sure that there is no leak. (b) For the alternate braking-system deactivation, do the operational check of the alternate braking system (Ref. AMM TASK 32-43-00-710-001) . Make sure that there is no leak. (10) Make sure that there are no signs of overstrain damage on the band clamps that connect the hydraulic pipes to the MLG. (11) Make sure that there are no signs of damage at the mounting locations between the two ends of the hydraulic pipes and the MLG. (12) Do a leak check at the blanking caps after each flight during the permitted repair intervals. (13) Do a detailed visual inspection of the adjacent brake hose and harness to make sure that there are no signs of chafing, damage or leak. Do this inspection after each flight during the permitted repair intervals. Subtask 32-42-00-865-063-A F.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 121VU 121VU 121VU 121VU

DESIGNATION HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY HYDRAULIC/BRAKING AND STEERING/SYS2/CTL HYDRAULIC/BRAKING AND STEERING/SYS1/CTL HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY

FIN 4GG

LOCATION M36

3GG

M35

1GG

M34

2GG

M33

Subtask 32-42-00-860-069-A G. Aircraft Maintenance Configuration

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 19 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

(1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Pressurize the Yellow hydraulic system with the Yellow electric pump. (Ref. AMM TASK 29-24-00863-001) (3) On the panel 402VU, make sure that the A/SKID & NOSE WHEEL switch is set to ON. Subtask 32-42-00-710-063-A H.

Tests (1) Do this test: ACTION RESULT 1.Fully push in the related brake pedals and hold Make sure that there are no leaks on the Yellow them in this position. hydraulic-pressure line you disconnected. 2.Release the brake pedals. 3.Pressurize the Green and Yellow hydraulic reservoirs (Ref. AMM TASK 29-14-00-614002) (Ref. AMM TASK 29-14-00-614-002) . 4.Pressurize the Green hydraulic system from the Make sure that there are no leaks on the Green hyYellow hydraulic system with the PTU (Ref. AMM draulic-pressure line you disconnected. TASK 29-23-00-863-001) . Fully push in the related brake pedals and hold them in this position. 5.Release the brake pedals. (2) Do the functional test of the tachometer (Ref. AMM TASK 32-42-00-720-002) or as an alternative (Ref. AMM TASK 32-42-00-720-003) and (Ref. AMM TASK 32-42-00-710-001) . NOTE: If you applied MMEL Item 32-42-06 before this brake deactivation, the functional test of the tachometer is not applicable.

Subtask 32-42-00-869-057-A J.

5.

System Consequences and Cockpit Effects in case of deactivation with the brake removal This deactivation procedure can cause the Wheel page of the Systems Display to show the message XX at the applicable brake temperature indication.

Close-up Subtask 32-42-00-860-070-A A.

Put the aircraft back to its initial configuration. (1) Depressurize the Green and Yellow hydraulic systems (Ref. AMM TASK 29-10-00-864-001) (Ref. AMM TASK 29-10-00-864-002) (2) Make sure that the level of the fluid in the Green and Yellow hydraulic reservoirs is correct. Add some fluid if it is necessary. (Ref. AMM TASK 12-12-29-611-001) (3) De-energize the aircraft electrical network (Ref. AMM TASK 24-41-00-862-002) . (4) Remove the WARNING NOTICE(S). (5) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (6) Make an entry in the logbook to tell persons that the main wheel brakes are deactivated. (7) In the cockpit, install a PLACARD placard to tell the crew: · that the brake unit No. 1 (2, 3, 4) is not operational or is removed.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 20 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-003-A - Deactivation of the Main Wheel Brakes

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 21 of 21

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-002-A - Deactivation of the Normal Braking - With disconnection of the Green Hydraulic Supply

** ON A/C ALL TASK 32-42-00-040-002-A Deactivation of the Normal Braking - With disconnection of the Green Hydraulic Supply WARNING:

MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

WARNING:

MAKE SURE THAT THE CONTROLS AGREE WITH THE POSITION OF THE ITEMS THEY OPERATE BEFORE YOU PRESSURIZE A HYDRAULIC SYSTEM. UNWANTED MOVEMENT OF HYDRAULICALLY OPERATED ITEMS CAN CAUSE SERIOUS INJURY AND/OR DAMAGE.

Task Summary MMEL or CDL Ref MMEL 32-42-02A 1.

Reason for the Job MMEL 32-42-02A Green System Brake

2

Job Set-up Information A.

Access NO

Specific Tools NO

Mhr 00.7

E/T 01.0

Nb Men 2

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific

B.

Test YES

QTY AR AR AR AR AR AR

DESIGNATION CONTAINER 5 L (1.32 USGAL) HOSE - VINYL PLACARD TAPE - ADHESIVE TAPE - WIDE SELF-ADHESIVE - FABRIC WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. 02ABA1) No specific

DESIGNATION Phosphate Ester Hydraulic Fluid-General Power - corrosion resistant steel lockwire dia 0.8 mm

C. Referenced Information REFERENCE (Ref. 12-12-29-611-001-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01).

DESIGNATION Fill the Hydraulic Fluid Reservoir with a Hand Pump Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-002-A - Deactivation of the Normal Braking - With disconnection of the Green Hydraulic Supply REFERENCE (Ref. 24-41-00-862-002-A-02). (Ref. 29-10-00-864-001-A). (Ref. 29-14-00-614-001-A). (Ref. 29-23-00-863-001-A). (Ref. 32-11-12-000-001-A). (Ref. 32-42-00-710-001-A).

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Depressurize the Green Hydraulic System Depressurization of the Hydraulic Reservoirs Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump Removal of the MLG Hydraulic Dressings Operational Check of the Normal Braking System

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350, 377-450, 500-600 Normal Brake Deactivation SHEET 1 ** ON A/C 301-349, 351-376 Normal Brake Deactivation SHEET 1 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350, 377-450, 500-600 Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak ** ON A/C 301-349, 351-376 Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-002-A - Deactivation of the Normal Braking - With disconnection of the Green Hydraulic Supply

NOTE: THE GREEN HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS IN FRONT OF THE LEG GEAR.

A 2642GM

A A

2644GM 2641GM

A

A 4

2643GM

3 WHEEL SIDE

YELLOW PRESSURE

GREEN PRESSURE

LEG GEAR SIDE

BRAKE TEMPERATURE SENSOR ELECTRIC CONNECTION

2

1

N_MM_324200_4_BAM0_01_00

Figure 32-42-00-991-00400-00-A / SHEET 1/1 - Normal Brake Deactivation ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350, 377-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-002-A - Deactivation of the Normal Braking - With disconnection of the Green Hydraulic Supply

A

B

A 2641GM (2644GM) 2643GM (2642GM)

A 4

LH SHOWN RH SYMMETRICAL

3

WHEEL SIDE

LEG GEAR SIDE 2

1

NOTE: THE GREEN HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS IN FRONT OF THE LEG GEAR.

BRAKE TEMPERATURE SENSOR ELECTRIC CONNECTION

B TYPICAL N_MM_324200_4_BDM0_01_00

Figure 32-42-00-991-00400-00-C / SHEET 1/1 - Normal Brake Deactivation ** ON A/C 301-349, 351-376 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-002-A - Deactivation of the Normal Braking - With disconnection of the Green Hydraulic Supply

B

A

B

2642GM

A A

2641GM

2644GM

A 2643GM

A

1 3 2

WHEEL SIDE

LEG GEAR SIDE

1 NOTE: -THE GREEN HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS IN FRONT OF THE LEG GEAR. 1

RH SHOWN LH SYMMETRICAL

N_MM_324200_4_BHM0_01_00

Figure 32-42-00-991-01100-00-A / SHEET 1/2 - Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350, 377-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-002-A - Deactivation of the Normal Braking - With disconnection of the Green Hydraulic Supply

B

1

C

4

1

C

5 4

NOTE: 1

RH SHOWN LH SYMMETRICAL N_MM_324200_4_BHM0_02_00

Figure 32-42-00-991-01100-00-A / SHEET 2/2 - Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350, 377-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-002-A - Deactivation of the Normal Braking - With disconnection of the Green Hydraulic Supply

A

B C A 2641GM (2644GM) 2643GM (2642GM)

A 3

LH SHOWN RH SYMMETRICAL

2

WHEEL SIDE

LEG GEAR SIDE 1

NOTE: - THE GREEN HYDRAULIC CONNECTION ON THE BRAKE UNITS IS ALWAYS IN FRONT OF THE LEG GEAR.

B TYPICAL N_MM_324200_4_BFM0_01_00

Figure 32-42-00-991-01100-00-B / SHEET 1/2 - Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak ** ON A/C 301-349, 351-376 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-002-A - Deactivation of the Normal Braking - With disconnection of the Green Hydraulic Supply

D

4

1

C LH SHOWN RH SYMMETRICAL

5 4

D N_MM_324200_4_BFM0_02_00

Figure 32-42-00-991-01100-00-B / SHEET 2/2 - Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak ** ON A/C 301-349, 351-376 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-002-A - Deactivation of the Normal Braking - With disconnection of the Green Hydraulic Supply

3.

Job Set-up Subtask 32-42-00-941-056-A A.

Safety Precautions (1) Put the WARNING NOTICE(S) in position to tell persons not to operate the landing gear control lever and the brake pedals.

Subtask 32-42-00-860-074-A B.

Aircraft Maintenance Configuration (1) Depressurize the Green hydraulic system (Ref. AMM TASK 29-10-00-864-001) . (2) Parking brake configuration CAUTION: MAKE SURE THAT ALL THE PISTONS OF THE BRAKE ARE IN THE RELEASED POSITION. (a) Make sure that the PARKING BRK control-switch is set to OFF before you do this procedure. (3) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002)

Subtask 32-42-00-865-057-A C.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 121VU 121VU 121VU 121VU

4.

DESIGNATION HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY HYDRAULIC/BRAKING AND STEERING/SYS2/CTL HYDRAULIC/BRAKING AND STEERING/SYS1/CTL HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY

FIN 4GG

M36

LOCATION

3GG

M35

1GG

M34

2GG

M33

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350, 377-450, 500-600 (Ref. Fig. Normal Brake Deactivation SHEET 1) ** ON A/C 301-349, 351-376 (Ref. Fig. Normal Brake Deactivation SHEET 1) ** ON A/C ALL Subtask 32-42-00-040-054-A A.

Deactivation with isolation of the Green hydraulic supply (1) Loosen the knurled sleeve (2) of the Green half-coupling (1). Turn and disconnect the coupling. (2) Clean the knurled sleeve (2). Apply 2 or 3 turns of the TAPE - ADHESIVE ( 20 mm (0.7874 in.) to 30 mm (1.1811 in.)) to the sleeve (2). (3) Tightly wind 3 or 4 turns of the corrosion resistant steel lockwire dia 0.8 mm around the middle of the sleeve (2) with the tape. (4) Twist the lockwire and put it through the nearest locking hole you can get access to in the hexagonal head of the fixed half-coupling (1). Tighten the lockwire and twist it.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-002-A - Deactivation of the Normal Braking - With disconnection of the Green Hydraulic Supply

(5) Remove the bleed screw plug (4) from the bleed screw (3). (6) Connect a HOSE - VINYL to the related bleed screw and put the other end in a CONTAINER 5 L (1.32 USGAL) that contains Phosphate Ester Hydraulic Fluid-General Power - (Material No. 02ABA1). (7) Slowly loosen the bleed screw (3) to release hydraulic residual pressure from the brake. (8) Tighten the bleed screw (3). (9) Disconnect the vinyl hose. (10) Install the bleed screw plug (4) on the bleed screw. Subtask 32-42-00-040-059-A B.

Deactivation of the Wheel Brake with Disconnection of the Flexible Hoses from the Normal Braking System if there is a Leak

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350, 377-450, 500-600 (Ref. Fig. Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak) ** ON A/C 301-349, 351-376 (Ref. Fig. Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak) ** ON A/C ALL (1) Depressurize the Green hydraulic reservoirs (Ref. AMM TASK 29-14-00-614-001) . (2) For one wheel brake only, remove the flexible hoses between the rigid MLG hydraulic pipes and the wheel brake, on the normal braking systems. (3) Remove the flexible hose (1) from the brake hydraulic self-sealing-coupling and from the flexible hose (4) connection (Ref. AMM TASK 32-11-12-000-001) . (4) Clean the brake hydraulic self-sealing-coupling and apply two or three turns of TAPE - WIDE SELFADHESIVE - FABRIC 20 mm (0.7874 in.) to 30 mm (1.1811 in.). (5) Remove the flexible hose (4) from the flexible hose (1) connection and from the union (5) (Ref. AMM TASK 32-11-12-000-001) . (6) Install blanking cap on the related union (5) to make sure that there is no leak. (7) Remove the bleed screw plug (3) from the related bleed screw (2). (8) Connect a HOSE - VINYL to the bleed screw (2) and put the other end in a CONTAINER 5 L (1.32 USGAL) that contains Phosphate Ester Hydraulic Fluid-General Power - - (Material No. 02ABA1). (9) Slowly loosen the bleed screw (2) to release the remaining hydraulic pressure from the wheel brake. (10) Tighten the bleed screw (2). (11) Disconnect the HOSE - VINYL. (12) Install the bleed screw plug (3) on the bleed screw (2). (13) Do the operational check of the normal braking system (Ref. AMM TASK 32-42-00-710-001) . Make sure that there is no leak. (14) Make sure that there is no sign of overstrain damage on the band clamps that connect the hydraulic pipe to the MLG. (15) Make sure that there are no signs of damage on the mounting locations between the two ends of the hydraulic pipes and the MLG. (16) Do a leak check at the blanking caps after each flight during the permitted repair intervals. Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-002-A - Deactivation of the Normal Braking - With disconnection of the Green Hydraulic Supply

(17) Do a detailed visual inspection of the adjacent brake hose and harness to make sure that there are no signs of chafing, damage or leak. Do this inspection after each flight during the permitted repair intervals. Subtask 32-42-00-910-053-A CAUTION:

C.

MAKE SURE THAT THE LOCKWIRE CANNOT WEAR DURING THE OPERATIONS OF THE LANDING GEAR.

Precaution

Subtask 32-42-00-860-073-A D.

Aircraft Maintenance Configuration (1) Pressurize the Green hydraulic system from the Yellow hydraulic system through the PTU with the electric pump (Ref. AMM TASK 29-23-00-863-001) . (2) On the panel 402VU, make sure that the A/SKID & NOSE WHEEL switch is set to ON.

Subtask 32-42-00-710-058-A E.

Test (1) Do this test: ACTION RESULT 1.Push in fully the related brake pedals and hold Make sure that there are no leaks on the hydraulthem pushed in. ic-pressure line you disconnected. 2.Release the brake pedals.

5.

Close-up Subtask 32-42-00-860-075-A A.

Put the aircraft back to its initial configuration. (1) Depressurize the Green hydraulic system (Ref. AMM TASK 29-10-00-864-001) . (2) Make sure that the level of the hydraulic fluid is correct in the Green hydraulic reservoir. Add some hydraulic fluid if it is necessary (Ref. AMM TASK 12-12-29-611-001) . (3) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (4) Remove the WARNING NOTICE(S). (5) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (6) Make an entry in the logbook to tell persons that the normal braking is deactivated. (7) In the cockpit, install a PLACARD to tell the crew that the normal braking on the wheel 1 (2, 3, 4) is not operational.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-007-A - Deactivation of the BSCU Channel/System 1 or 2

** ON A/C ALL TASK 32-42-00-040-007-A Deactivation of the BSCU Channel/System 1 or 2 1.

Reason for the Job MMEL 32-42-03A Braking/Steering Control Unit (BSCU) Channel 1 MMEL 32-42-04A Braking/Steering Control Unit (BSCU) Channel 2

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 31-32-00-860-009-A). (Ref. 31-60-00-860-001-A).

3.

DESIGNATION Procedure to Get Access to the SYSTEM REPORT/TEST/L/G Page EIS Start Procedure

Job Set-up Subtask 32-42-00-860-100-A A.

Aircraft Maintenance Configuration (1) On the panel 400VU, make sure that the landing gear control lever is in the DOWN position. (2) Make sure that the CAPT and F/O brake pedals are released. (3) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) . (4) On the panel 402VU, make sure that the A/SKID & N/W STRG switch is at ON. (5) Put the WARNING NOTICE(S) in position to tell persons not to operate: · the landing gear control-lever · the A/SKID & N/W STRG switch · the brake pedals.

Subtask 32-42-00-865-074-A B.

Table of the circuit breakers used in this procedure: PANEL 121VU 121VU

4.

DESIGNATION HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY

FIN 4GG

M36

LOCATION

2GG

M33

Procedure

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-007-A - Deactivation of the BSCU Channel/System 1 or 2

** ON A/C POST SB 32-1360 for A/C 201-201, 234-234 EMB SB 31-1257 for A/C 201-201 EMB SB 32-1350 for A/C 201-201, 234-234 Subtask 32-42-00-040-057-B A.

Deactivation of the BSCU System 1 or 2 (1) If there is loss of one BSCU system, on the upper ECAM DU, make sure that the BRAKES SYS 1 FAULT or BRAKES SYS 2 FAULT warning is shown. (a) Get access to the SYSTEM REPORT/TEST/L/G page (Ref. AMM TASK 31-32-00-860-009) . (b) Print the trouble shooting data, the ground scanning, the class 3 fault messages and the Post Flight Report (PFR) of the related BSCU as follows: ACTION RESULT - Push the line key adjacent to the BSCU1 or - The BSCU1 or BSCU2 page comes into view. BSCU2 indication. - Push the line key adjacent to the TROUBLE - The TROUBLE SHOOT DATA page comes inSHOOT DATA indication. to view. - Push the line key adjacent to the PRINT indication. - Push the line key adjacent to the RETURN in- - The BSCU1 or BSCU2 page comes into view. dication. - Push the line key adjacent to the GROUND - The GROUND SCANNING page comes into SCANNING indication. view. - Push the line key adjacent to the PRINT indication. - Push the line key adjacent to the RETURN in- - The BSCU1 or BSCU2 page comes into view. dication. - Push the line key adjacent to the CLASS 3 - The CLASS 3 FAULTS page comes into view. FAULTS indication. - Push the line key adjacent to the PRINT indication. - Push the line key adjacent to the RETURN in- - The CFDS MENU page comes into view. dication until you get the CFDS MENU page. - Push the line key adjacent to the POST FLIGHT REP PRINT indication.

NOTE: It is important to keep these documents to do the maintenance of the BSCU in shop. (c) On the upper ECAM DU, if the BRAKES SYS 1 FAULT warning is shown: · Open, safety and tag the circuit breaker 2GG. (d) On the upper ECAM DU, if the BRAKES SYS 2 FAULT warning is shown: · Open, safety and tag the circuit breaker 4GG. (2) After deactivation of one BSCU system and before each flight: · On the MCDU, get access to the CFDS MENU page. · Push the line key adjacent to the CFDS indication. · On the LAST LEG REPORT page, make sure that none of the following fault messages related to the L/G SYS DISAGREE caution message is recorded: Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-007-A - Deactivation of the BSCU Channel/System 1 or 2

R L/G DOOR CLOSED PROX SNSR 26GA TGT POS L L/G DOOR CLOSED PROX SNSR 27GA TGT POS R L/G DOOR CLOSED PROX SNSR 28GA TGT POS L L/G DOOR CLOSED PROX SNSR 29GA TGT POS N L/G DOOR CLOSED PROX SNSR 30GA TGT POS N L/G DOOR CLOSED PROX SNSR 31GA TGT POS R L/G DOOR OPEN PROX SNSR 32GA TGT POS L L/G DOOR OPEN PROX SNSR 33GA TGT POS R L/G DOOR OPEN PROX SNSR 34GA TGT POS L L/G DOOR OPEN PROX SNSR 35GA TGT POS N L/G R DOOR OPEN PROX SNSR 36GA TGT POS N L/G L DOOR OPEN PROX SNSR 37GA TGT POS N L/G R DOOR OPEN PROX SNSR 38GA TGT POS N L/G L DOOR OPEN PROX SNSR 39GA TGT POS (3) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. (4) Make an entry in the log book to tell persons that the BSCU system 1 or 2 is deactivated. ** ON A/C ALL PRE SB 32-1360 for A/C 201-201, 234-234 EMB SB 31-1257 for A/C 201-201, 203-205, 207-207, 210-211, 233-233, 240-240, 243-243 EMB SB 32-1350 for A/C 016-021, 201-201, 203-206, 209-209, 211-211, 215-222, 226-230, 233-235, 239-240, 242-244, 350-350 EMB SB 32-1360 for A/C 203-205, 211-211, 219-220 EMB SB 32-1361 for A/C 203-205, 207-207, 210-211, 219-220, 231-232, 237-237 Subtask 32-42-00-040-057-D A.

Deactivation of the BSCU System 1 or 2 (1) If there is loss of one BSCU system, on the upper ECAM DU, make sure that the BRAKES SYS 1 FAULT or BRAKES SYS 2 FAULT warning is shown. (a) Get access to the SYSTEM REPORT/TEST/L/G page (Ref. AMM TASK 31-32-00-860-009) . (b) Print the trouble shooting data, the ground report, the ground scanning, the class 3 fault messages, and the Post Flight Report (PFR) of the related BSCU as follows: ACTION RESULT - Push the line key adjacent to the BSCU1 or - The BSCU1 or BSCU2 page comes into view. BSCU2 indication. - Push the line key adjacent to the TROUBLE - The TROUBLE SHOOT DATA page comes inSHOOT DATA indication. to view. - Push the line key adjacent to the PRINT indication. - Push the line key adjacent to the RETURN in- - The BSCU1 or BSCU2 page comes into view. dication. - Push the line key adjacent to the GROUND - The GROUND REPORT page comes into view. REPORT indication. - Push the line key adjacent to the PRINT indication. - Push the line key adjacent to the RETURN in- - The BSCU1 or BSCU2 page comes into view. dication.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-007-A - Deactivation of the BSCU Channel/System 1 or 2

ACTION RESULT - Push the line key adjacent to the GROUND - The GROUND SCANNING page comes into SCANNING indication. view. - Push the line key adjacent to the PRINT indication. - Push the line key adjacent to the RETURN in- - The BSCU1 or BSCU2 page comes into view. dication. - Push the line key adjacent to the CLASS 3 - The CLASS 3 FAULTS page comes into view. FAULTS indication. - Push the line key adjacent to the PRINT indication. - Push the line key adjacent to the RETURN in- - The CFDS MENU page comes into view. dication until you get the CFDS MENU page. - Push the line key adjacent to the POST FLIGHT REP PRINT indication.

NOTE: It is important to keep these documents to do the maintenance of the BSCU in shop. (c) On the upper ECAM DU, if the BRAKES SYS 1 FAULT warning is shown: · Open, safety and tag the circuit breaker 2GG. (d) On the upper ECAM DU, if the BRAKES SYS 2 FAULT warning is shown: · Open, safety and tag the circuit breaker 4GG. (2) After deactivation of one BSCU system and before each flight: · On the MCDU, get access to the CFDS MENU page. · Push the line key adjacent to the CFDS indication. · Push the line key adjacent to the LAST LEG REPORT indication. · On the LAST LEG REPORT page, make sure that none of the following fault messages related to the L/G SYS DISAGREE caution message is recorded: R L/G DOOR CLOSED PROX SNSR 26GA TGT POS L L/G DOOR CLOSED PROX SNSR 27GA TGT POS R L/G DOOR CLOSED PROX SNSR 28GA TGT POS L L/G DOOR CLOSED PROX SNSR 29GA TGT POS N L/G DOOR CLOSED PROX SNSR 30GA TGT POS N L/G DOOR CLOSED PROX SNSR 31GA TGT POS R L/G DOOR OPEN PROX SNSR 32GA TGT POS L L/G DOOR OPEN PROX SNSR 33GA TGT POS R L/G DOOR OPEN PROX SNSR 34GA TGT POS L L/G DOOR OPEN PROX SNSR 35GA TGT POS N L/G R DOOR OPEN PROX SNSR 36GA TGT POS N L/G L DOOR OPEN PROX SNSR 37GA TGT POS N L/G R DOOR OPEN PROX SNSR 38GA TGT POS N L/G L DOOR OPEN PROX SNSR 39GA TGT POS (3) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view. (4) Make an entry in the log book to tell persons that the BSCU system 1 or 2 is deactivated. ** ON A/C ALL 5.

Close-up Subtask 32-42-00-860-101-A A.

Put the aircraft back to the serviceable condition.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-42-00-040-007-A - Deactivation of the BSCU Channel/System 1 or 2

(1) Remove the WARNING NOTICE(S).

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-43-00-040-001-A - Deactivation of the Alternate Braking with disconnection of the Yellow Hydraulic Supply

** ON A/C ALL TASK 32-43-00-040-001-A Deactivation of the Alternate Braking with disconnection of the Yellow Hydraulic Supply WARNING:

MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

WARNING:

MAKE SURE THAT THE CONTROLS AGREE WITH THE POSITION OF THE ITEMS THEY OPERATE BEFORE YOU PRESSURIZE A HYDRAULIC SYSTEM. UNWANTED MOVEMENT OF HYDRAULICALLY OPERATED ITEMS CAN CAUSE SERIOUS INJURY AND/OR DAMAGE.

Task Summary MMEL or CDL Ref MMEL 32-44-01A 1.

Reason for the Job MMEL 32-44-01A Yellow System Brake

2

Job Set-up Information A.

Access NO

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific

B.

Test YES

QTY AR AR AR AR AR AR

DESIGNATION CONTAINER 5 L (1.32 USGAL) HOSE - VINYL PLACARD TAPE - ADHESIVE TAPE - WIDE SELF-ADHESIVE - FABRIC WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. 02ABA1) (Material No. 14QFB1)

DESIGNATION Phosphate Ester Hydraulic Fluid-General Power - Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -

C. Referenced Information REFERENCE (Ref. 12-12-29-611-001-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01).

DESIGNATION Fill the Hydraulic Fluid Reservoir with a Hand Pump Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-43-00-040-001-A - Deactivation of the Alternate Braking with disconnection of the Yellow Hydraulic Supply REFERENCE (Ref. 24-41-00-862-002-A-02).

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 29-10-00-863-002-A). Pressurize the Yellow Hydraulic System with a Hydraulic Ground Power-Cart (Ref. 29-10-00-864-001-A). Depressurize the Green Hydraulic System (Ref. 29-10-00-864-002-A). Depressurize the Yellow Hydraulic System (Ref. 29-14-00-614-001-A). Depressurization of the Hydraulic Reservoirs (Ref. 29-24-00-863-001-A). Pressurize the Yellow Hydraulic System with the Electric Pump (Ref. 32-11-12-000-001-A). Removal of the MLG Hydraulic Dressings (Ref. 32-43-00-710-001-A). Operational Check of Alternate Braking System Alternate Brake Deactivation SHEET 1 Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-43-00-040-001-A - Deactivation of the Alternate Braking with disconnection of the Yellow Hydraulic Supply

2642GM

A 2644GM 2641GM

A

4

A 2643GM

WHEEL SIDE YELLOW PRESSURE 1

2

GREEN PRESSURE LEG GEAR SIDE

BRAKE TEMPERATURE SENSOR ELECTRIC CONNECTION

3

NOTE: THE YELLOW HYDRAULIC CONNECTION ON THE BRAKE UNIT IS ALWAYS BEHIND THE LEG GEAR N_MM_324300_4_AAM0_01_00

Figure 32-43-00-991-00100-00-A / SHEET 1/1 - Alternate Brake Deactivation ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-43-00-040-001-A - Deactivation of the Alternate Braking with disconnection of the Yellow Hydraulic Supply

B

A

B

2642GM

A A

2641GM

2644GM

A

A 1 2643GM

4 WHEEL SIDE YELLOW PRESSURE 1

2

LEG GEAR SIDE

3

NOTE: THE YELLOW HYDRAULIC CONNECTION ON THE BRAKE UNIT IS ALWAYS BEHIND THE LEG GEAR RH SHOWN 1 LH SYMMETRICAL

N_MM_324300_4_AFM0_01_00

Figure 32-43-00-991-00800-00-A / SHEET 1/2 - Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-43-00-040-001-A - Deactivation of the Alternate Braking with disconnection of the Yellow Hydraulic Supply

B

1

C

5

C

6 5

NOTE: 1

RH SHOWN LH SYMMETRICAL N_MM_324300_4_AFM0_02_00

Figure 32-43-00-991-00800-00-A / SHEET 2/2 - Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-43-00-040-001-A - Deactivation of the Alternate Braking with disconnection of the Yellow Hydraulic Supply

3.

Job Set-up Subtask 32-43-00-941-050-A A.

Safety Precautions (1) Put the WARNING NOTICE(S) in position to tell persons not to operate the landing gear control lever and the brake pedals.

Subtask 32-43-00-860-057-A B.

Aircraft Maintenance Configuration (1) Depressurize the yellow hydraulic system (Ref. AMM TASK 29-10-00-864-002) . (2) Parking brake configuration CAUTION: MAKE SURE THAT ALL THE PISTONS OF THE BRAKE ARE IN THE RELEASED POSITION. (a) Make sure that the parking brake control-switch is set to OFF before you do this procedure. (3) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002)

Subtask 32-43-00-865-050-A C.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 301-450, 500-600 49VU ABCU &/Y BRK/PRESS IND 61GG C10 ** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 49VU L/G/Y BRK/PRESS/IND 61GG C10 ** ON A/C ALL 121VU 121VU 121VU 121VU 4.

HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY HYDRAULIC/BRAKING AND STEERING/SYS2/CTL HYDRAULIC/BRAKING AND STEERING/SYS1/CTL HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY

4GG

M36

3GG

M35

1GG

M34

2GG

M33

Procedure (Ref. Fig. Alternate Brake Deactivation SHEET 1) Subtask 32-43-00-040-050-A A.

Deactivation with Isolation of Yellow Hydraulic Supply (1) Loosen the knurled sleeve (1) of the Yellow half-coupling (2). Turn and disconnect the coupling. (2) Clean the knurled sleeve (1). Apply 2 or 3 turns of the TAPE - ADHESIVE (20 to 30 mm wide) to the sleeve (1). (3) Tightly wind 3 or 4 turns of the lockwire around the middle of the sleeve (1) with the tape.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-43-00-040-001-A - Deactivation of the Alternate Braking with disconnection of the Yellow Hydraulic Supply

(4) Twist the Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - (Material No. 14QFB1) and put it through the nearest locking hole you can get access to in the hexagonal head of the fixed half-coupling (2). Tighten the lockwire and twist it. (5) Remove the bleed screw plug (4) from the bleed screw (3). (6) Connect a HOSE - VINYL to the bleed screw related to of the Yellow system and put the other end in a CONTAINER 5 L (1.32 USGAL) that contains Phosphate Ester Hydraulic Fluid-General Power - (Material No. 02ABA1). (7) Slowly loosen the bleed screw (3) to release hydraulic residual pressure from the brake. (8) Tighten the bleed screw (3). (9) Disconnect the vinyl hose. (10) Install the bleed screw plug (4) on the bleed screw (3). Subtask 32-43-00-040-051-A B.

Deactivation of the Wheel Brake with Disconnection of Flexible Hoses from the Alternate Braking System if there is a Leak (Ref. Fig. Deactivation/Reactivation of the Wheel Brake with Disconnection of the Flexible Hoses if there is a Leak) (1) Depressurize the Yellow hydraulic reservoir (Ref. AMM TASK 29-14-00-614-001) . (2) For one wheel brake only, remove the flexible hoses located between the rigid MLG hydraulic pipes and the wheel brake, on the alternate braking systems. (3) Remove the flexible hose (1) from the brake hydraulic self-sealing-coupling and from the flexible hose (5) connection (Ref. AMM TASK 32-11-12-000-001) . (4) Clean the brake hydraulic self-sealing-coupling and apply two or three turns of the TAPE - WIDE SELF-ADHESIVE - FABRIC 20 mm (0.79 in.) to 30 mm (1.18 in.). (5) Remove the flexible hose (5) from the flexible hose (1) connection and from the union (6) (Ref. AMM TASK 32-11-12-000-001) . (6) Install blanking cap on the related union (6) to make sure that there is no leak. (7) Remove the bleed screw plug (4) from the related bleed screw (3). (8) Connect a HOSE - VINYL to a bleed screw (3) and put the other end in a CONTAINER 5 L (1.32 USGAL) that contains Phosphate Ester Hydraulic Fluid-General Power - - (Material No. 02ABA1). (9) Slowly loosen the bleed screw (3) to release the remaining hydraulic pressure from the wheel brake. (10) Tighten the bleed screw (3). (11) Disconnect the HOSE - VINYL. (12) Install the bleed screw plug (4) on the bleed screw (3). (13) Do the operational check of the alternate braking system (Ref. AMM TASK 32-43-00-710-001) . Make sure that there is no leak. (14) Make sure that there is no sign of overstrain damage on the band clamps that connect the hydraulic pipe to the MLG. (15) Make sure that there are no signs of damage on the mounting locations between the two ends of the hydraulic pipes and the MLG. (16) Do a leak check at the blanking caps after each flight during the permitted repair intervals. (17) Do a detailed visual inspection of the adjacent brake hose and harness to make sure that there are no signs of chafing, damage or leak. Do this inspection after each flight during the permitted repair intervals.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-43-00-040-001-A - Deactivation of the Alternate Braking with disconnection of the Yellow Hydraulic Supply

Subtask 32-43-00-910-050-A CAUTION:

C.

MAKE SURE THAT THE LOCKWIRE CANNOT WEAR DURING THE OPERATIONS OF THE LANDING GEAR.

Precaution

Subtask 32-43-00-860-056-A D.

Aircraft Maintenance Configuration (1) Pressurize the Yellow hydraulic system (Ref. AMM TASK 29-10-00-863-002) or (Ref. AMM TASK 29-24-00-863-001) .

Subtask 32-43-00-710-050-A E.

Test (1) Do this test. NOTE: During this test, make sure that: the Green hydraulic system is depressurized (Ref. AMM TASK 29-10-00-864-001) , or, on the panel 402VU, the A/SKID & NOSE WHEEL switch is set to OFF.

ACTION RESULT 1.Push in fully the related brake pedals and hold Make sure that there are no leaks on the hydraulic them pushed in. pressure line you disconnected. 2.Release the brake pedals. 5.

Close-up Subtask 32-43-00-860-058-A A.

Put the aircraft back to its initial configuration. (1) Depressurize the Yellow hydraulic system (Ref. AMM TASK 29-10-00-864-002) . (2) Make sure that the level of the hydraulic fluid is correct in the Yellow hydraulic reservoir. Add some hydraulic fluid if it is necessary (Ref. AMM TASK 12-12-29-611-001) . (3) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (4) Remove the WARNING NOTICE(S). (5) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (6) Make an entry in the logbook to tell persons that the alternate braking is deactivated. (7) In the cockpit, install a PLACARD to tell the crew that the ALTERNATE BRAKING on the WHEEL 1 (2, 3, 4) is not operational.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-45-00-040-001-A - Parking Brake-One motor of the parking brake control valve is inoperative

** ON A/C ALL TASK 32-45-00-040-001-A Parking Brake-One motor of the parking brake control valve is inoperative WARNING:

MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

WARNING:

MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. UNWANTED ELECTRICAL POWER CAN BE DANGEROUS.

WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

WARNING:

MAKE SURE THAT THE CONTROLS AGREE WITH THE POSITION OF THE ITEMS THEY OPERATE BEFORE YOU PRESSURIZE A HYDRAULIC SYSTEM. UNWANTED MOVEMENT OF HYDRAULICALLY OPERATED ITEMS CAN CAUSE SERIOUS INJURY AND/OR DAMAGE.

1.

Reason for the Job MMEL 32-45-01A Parking Brake Control Valve Electrical Motor

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) AR WARNING NOTICE(S)

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 No specific Torque wrench: range to between 0.05 and 0.08 m.daN (4.42 and 7.08 lbf.in) ** ON A/C ALL B.

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 29-24-00-863-001-A). (Ref. 29-24-00-864-001-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Pressurize the Yellow Hydraulic System with the Electric Pump Depressurize the Yellow Hydraulic System

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-45-00-040-001-A - Parking Brake-One motor of the parking brake control valve is inoperative REFERENCE (Ref. 32-12-00-010-001-A). (Ref. 32-12-00-410-001-A).

DESIGNATION Open the Main Gear Doors for Access Close the Main Gear Doors after Access

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 Parking Brake Electrical Control Valve - Circuit Breakers SHEET 1 ** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 301-450, 500-600 Parking Brake Electrical Control Valve 102GG SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-45-00-040-001-A - Parking Brake-One motor of the parking brake control valve is inoperative

FR47

A B

Z744

A

B

1 2

72GG CTL VALVE - PARK BRK, ELEC.

N_MM_324500_4_AAM0_01_00

Figure 32-45-00-991-00200-00-A / SHEET 1/1 - Parking Brake Electrical Control Valve - Circuit Breakers ** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-45-00-040-001-A - Parking Brake-One motor of the parking brake control valve is inoperative

FR46

Z190 FR47

A

102GG

B A

B

102GG

N_MM_324500_4_AEM2_01_00

Figure 32-45-00-991-00200-00-C / SHEET 1/1 - Parking Brake Electrical Control Valve 102GG ** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212218, 221-230, 235-236, 238-239, 241-242, 301-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-45-00-040-001-A - Parking Brake-One motor of the parking brake control valve is inoperative

3.

Job Set-up Subtask 32-45-00-860-054-A A.

Aircraft Maintenance Configuration (1) On the panel 400VU, make sure that the landing gear control lever is in the DOWN position. (2) On the panel 110VU, make sure that the PARKING BRK control-switch is in the OFF position. (3) Make sure that the CAPT and F/O brake pedals are released. (4) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002)

Subtask 32-45-00-010-051-A B.

Get Access (1) Open the right MLG door (Ref. AMM TASK 32-12-00-010-001) . (2) Put the ACCESS PLATFORM 2M (6 FT) in position in zone 744.

Subtask 32-45-00-941-052-A C.

Safety Precautions (1) Put the WARNING NOTICE(S) to tell persons not to operate: · the landing gear control lever · the brake pedals.

Subtask 32-45-00-865-052-A D.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 301-450, 500-600 49VU ABCU &/Y BRK/PRESS IND 61GG C10 ** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 49VU L/G/Y BRK/PRESS/IND 61GG C10 ** ON A/C ALL 121VU 121VU 121VU

HYDRAULIC/PARK BRK/CTL/STBY HYDRAULIC/PARK BRK/CTL/NORM HYDRAULIC/SOL VALVES/G/Y/PTU

71GG 70GG 1801GL

N37 N36 N34

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU HYDRAULIC/HYD POWER/Y 3803GX N30 ** ON A/C 401-450 121VU HYDRAULIC/HYD POWER/Y

3803GX

N31

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 Subtask 32-45-00-210-052-A E.

In zone 744, on the parking-brake electrical control-valve 72GG, make sure that the two circuit breakers are closed: · circuit breaker closed, you must see a black tape through the transparent cover (2) · circuit breaker open, you must see a white tape through the transparent cover (2). (Ref. Fig. Parking Brake Electrical Control Valve - Circuit Breakers SHEET 1)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-45-00-040-001-A - Parking Brake-One motor of the parking brake control valve is inoperative

NOTE: If you cannot see the circuit breakers through the transparent covers (2) because they are in bad condition: - remove the transparent covers (2) with their packings (1) - make sure that the circuit breakers are closed - install the transparent covers (2) with their packings (1). - TORQUE the transparent covers (2) to between 0.05 and 0.08 m.daN (4.42 and 7.08 lbf.in) ** ON A/C ALL 4.

Procedure

** ON A/C 201-201, 203-205, 207-207, 210-211, 219-220, 231-234, 237-237, 240-240, 243-250 Subtask 32-45-00-710-051-A A.

Operational test of the electric motors of the parking brake control valve NOTE: The pressure value supplied to the brakes, when the parking brake is applied, is 145 bar plus or minus 10 bar (2100 PSI plus or minus 145 PSI).

ACTION 1.Pressurize the Yellow hydraulic system with the electric pump (Ref. AMM TASK 29-24-00-863001) . 2.Depressurize the Yellow hydraulic system (Ref. AMM TASK 29-24-00-864-001) . 3.On the panel 121VU: · open the circuit breaker 71GG.

RESULT Make sure that the pressure of the accumulator increases on the triple indicator until 206 bar (3000 PSI) (the indicator pointer is in the green range).

NOTE: To find the inoperative electric motor of the parking-brake control-valve, you must do the test in two steps: -with 70GG closed and 71GG open -with 71GG closed and 70GG open 4.On the panel 110VU: · put the PARKING BRK control switch 73GG in the ON position.

5.On the panel 110VU: · put the PARKING BRK control switch 73GG in the OFF position.

The triple indicator 60GG, shows the left and right pressure values. In the brake units, make sure that the pistons supplied by the Yellow hydraulic system are in the operating or extended position. On the nose landing-gear leg, on the N/W Steering Deactivation Electric-Box 5GC, the PARKING BRAKE indicator light is on. On the triple indicator 60GG, the pressure from the Yellow hydraulic system applied to the brakes is zero. In the brake units, the pistons supplied by the Yellow hydraulic system are in the released position. On the nose landing-gear leg, on the N/W Steering Deactivation Electric-Box 5GC, the PARKING BRK indicator light is off.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-45-00-040-001-A - Parking Brake-One motor of the parking brake control valve is inoperative ACTION

RESULT NOTE: If this test (step 3 to step 5) is not OK, the electric motor (NORM) supplied by the service bus 601PP is inoperative.

6.On the panel 121VU: · close the circuit breaker 71GG and open the circuit breaker 70GG. 7.On the panel 110VU: · put the PARKING BRK control switch 73GG in The triple indicator 60GG shows the left and right the ON position. pressure values. In the brake units, make sure that the pistons supplied by the Yellow hydraulic system are in the operating or extended position. On the nose landing-gear leg, on the N/W Steering Deactivation Electric-Box 5GC, the PARKING BRAKE indicator light is off. 8.On the panel 110VU: · put the PARKING BRK control switch 73GG in On the triple indicator 60GG, the pressure from the the OFF position. Yellow hydraulic system applied to the brakes is zero. In the brake units, the pistons supplied by the Yellow hydraulic system are in the released position. On the nose landing gear leg, on the N/W Steering Deactivation Electric-Box 5GC, the PARKING BRK indicator light is off. NOTE: If this test (step 6 to step 8) is not OK, the electric motor (STBY) supplied by the HOT BUS 701PP is inoperative. 9.On the panel 121VU: · close the circuit breaker 70GG.

NOTE: Only one inoperative electric motor of the parking-brake control valve is permitted. NOTE: If the electrical motor (STBY), supplied by the HOT BUS 701PP is inoperative, the parking brake valve will not operate if the aircraft is supplied by batteries only. NOTE: If the electric motor (STBY), supplied by the HOT BUS 701PP is inoperative, aircraft towing is not allowed if the aircraft is supplied by batteries only. ** ON A/C 016-022, 024-100, 112-150, 206-206, 208-209, 212-218, 221-230, 235-236, 238-239, 241-242, 301450, 500-600 Subtask 32-45-00-710-051-B A.

Operational test of the electric motors of the parking brake control valve (Ref. Fig. Parking Brake Electrical Control Valve 102GG SHEET 1) NOTE: The pressure value supplied to the brakes, when the parking brake is applied, is 145 bar plus or minus 10 bar (2100 PSI plus or minus 145 PSI).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-45-00-040-001-A - Parking Brake-One motor of the parking brake control valve is inoperative ACTION 1.Pressurize the Yellow hydraulic system with the electric pump (Ref. AMM TASK 29-24-00-863001) . 2.Depressurize the Yellow hydraulic system (Ref. AMM TASK 29-24-00-864-001) . 3.On the panel 121VU: · open the circuit breaker 71GG.

RESULT Make sure that the pressure of the accumulator increases on the triple indicator until 206 bar (3000 PSI) (the indicator pointer is in the green range).

NOTE: To find the inoperative electric motor of the parking-brake control-valve, you must do the test in two steps: -with 70GG closed and 71GG open -with 71GG closed and 70GG open 4.On the panel 110VU: · put the PARKING BRK control switch 73GG in the ON position.

5.On the panel 110VU: · put the PARKING BRK control switch 73GG in the OFF position.

The triple indicator 60GG, shows the left and right pressure values. In the brake units, make sure that the pistons supplied by the Yellow hydraulic system are in the operating or extended position. On the nose landing-gear leg, on the N/W Steering Deactivation Electric-Box 5GC, the PARKING BRAKE indicator light is on. On the triple indicator 60GG, the pressure from the Yellow hydraulic system applied to the brakes is zero. In the brake units, the pistons supplied by the Yellow hydraulic system are in the released position. On the nose landing-gear leg, on the N/W Steering Deactivation Electric-Box 5GC, the PARKING BRK indicator light is off. NOTE: If this test (step 3 to step 5) is not OK, the electric motor (NORM) supplied by the service bus 601PP is inoperative.

6.On the panel 121VU: · close the circuit breaker 71GG and open the circuit breaker 70GG. 7.On the panel 110VU: · put the PARKING BRK control switch 73GG in The triple indicator 60GG shows the left and right the ON position. pressure values. In the brake units, make sure that the pistons supplied by the Yellow hydraulic system are in the operating or extended position. On the nose landing-gear leg, on the N/W Steering Deactivation Electric-Box 5GC, the PARKING BRAKE indicator light is off. 8.On the panel 110VU: · put the PARKING BRK control switch 73GG in On the triple indicator 60GG, the pressure from the the OFF position. Yellow hydraulic system applied to the brakes is

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-45-00-040-001-A - Parking Brake-One motor of the parking brake control valve is inoperative ACTION

RESULT zero. In the brake units, the pistons supplied by the Yellow hydraulic system are in the released position. On the nose landing gear leg, on the N/W Steering Deactivation Electric-Box 5GC, the PARKING BRK indicator light is off. NOTE: If this test (step 6 to step 8) is not OK, the electric motor (STBY) supplied by the HOT BUS 701PP is inoperative.

9.On the panel 121VU: · close the circuit breaker 70GG.

NOTE: Only one inoperative electric motor of the parking-brake control valve is permitted. NOTE: If the electric motor (STBY), supplied by the HOT BUS 701PP is inoperative, the parking brake valve will not operate if the aircraft is supplied by batteries only. NOTE: If the electric motor (STBY), supplied by the HOT BUS 701PP is inoperative, aircraft towing is not allowed if the aircraft is supplied by batteries only. ** ON A/C ALL Subtask 32-45-00-860-055-A B.

Aircraft Maintenance Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002)

5.

Close-up Subtask 32-45-00-942-052-A A.

Removal of Equipment (1) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (2) Remove the WARNING NOTICE(S). (3) Remove the access platform(s).

Subtask 32-45-00-410-051-A B.

Close Access (1) Close the right MLG door (Ref. AMM TASK 32-12-00-410-001) . (2) Make an entry in the applicable logbook to tell the crew which electrical motor (NORM) or (STBY) is inoperative.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-51-00-040-002-A - Deactivation of the NoseWheel Steering Electrical Deactivation-Box (for Flight)

** ON A/C ALL TASK 32-51-00-040-002-A Deactivation of the Nose-Wheel Steering Electrical Deactivation-Box (for Flight) WARNING:

MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

WARNING:

MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

WARNING:

MAKE SURE THAT THE CONTROLS AGREE WITH THE POSITION OF THE ITEMS THEY OPERATE BEFORE YOU PRESSURIZE A HYDRAULIC SYSTEM. UNWANTED MOVEMENT OF HYDRAULICALLY OPERATED ITEMS CAN CAUSE SERIOUS INJURY AND/OR DAMAGE.

WARNING:

PRESSURIZE ONLY THE HYDRAULIC SYSTEM(S) THAT IS (ARE) NECESSARY FOR THE TASK. ISOLATE THE OTHER HYDRAULIC SYSTEM(S) BEFORE YOU SUPPLY HYDRAULIC POWER TO THE AIRCRAFT.

WARNING:

MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. UNWANTED ELECTRICAL POWER CAN BE DANGEROUS.

1.

Reason for the Job MMEL 32-51-03B NWS Electrical Deactivation Box

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

QTY AR AR AR AR

DESIGNATION CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER TIE WRAP WARNING NOTICE(S)

Referenced Information REFERENCE DESIGNATION Nose Wheel Steering Deactivation Electrical - Box - Deactivation/Reactivation SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-51-00-040-002-A - Deactivation of the NoseWheel Steering Electrical Deactivation-Box (for Flight)

A 5GC

A

2

1

TOWING POSITION

N_MM_325100_4_AAM0_01_00

Figure 32-51-00-991-04100-00-A / SHEET 1/1 - Nose Wheel Steering Deactivation Electrical - Box - Deactivation/Reactivation ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-51-00-040-002-A - Deactivation of the NoseWheel Steering Electrical Deactivation-Box (for Flight)

3.

Job Set-up Subtask 32-51-00-865-115-A A.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU 121VU 121VU

DESIGNATION HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY HYDRAULIC/BRAKING AND STEERING/SYS2/CTL HYDRAULIC/BRAKING AND STEERING/SYS1/CTL HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY

FIN 4GG

M36

LOCATION

3GG

M35

1GG

M34

2GG

M33

Subtask 32-51-00-941-062-A B.

Safety Precautions (1) Put WARNING NOTICE(S) on the panel 400VU to tell persons not to operate the nose landing gear. (2) On the center pedestal, in the cockpit, make sure that the free-fall control handle of the landing gear is in the normal position.

4.

Procedure (Ref. Fig. Nose Wheel Steering Deactivation Electrical - Box - Deactivation/Reactivation SHEET 1) Subtask 32-51-00-040-050-A A.

Deactivation of the Nose-Wheel Steering Electrical Deactivation-Box 5GC (1) On the nose-wheel steering electrical deactivation-box (1), set the lever to the non-towing (engaged) position. (2) Disconnect the electrical connector (2) from the nose-wheel steering electrical deactivation-box (1). (3) Put a CAP - BLANKING on the disconnected electrical connector (2). (4) Safety the blanking cap with TIE WRAP for flight. (5) Safety the electrical harness away from parts that move.

Subtask 32-51-00-865-116-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU 121VU 121VU

DESIGNATION HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY HYDRAULIC/BRAKING AND STEERING/SYS2/CTL HYDRAULIC/BRAKING AND STEERING/SYS1/CTL HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY

FIN 4GG

M36

LOCATION

3GG

M35

1GG

M34

2GG

M33

Subtask 32-51-00-869-060-A C.

System Consequences and Cockpit Effects (1) There is no electrical supply at the nose-wheel steering electrical deactivation-box. · The parking brake light on the nose-wheel steering electrical deactivation-box does not operate. · Persons will have to speak to confirm parking brake operation during towing operations.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-51-00-040-002-A - Deactivation of the NoseWheel Steering Electrical Deactivation-Box (for Flight)

5.

Close-up Subtask 32-51-00-942-069-A A.

Removal of Equipment (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the WARNING NOTICE(S). (3) Make an entry in the log book to tell persons that the nose-wheel steering electrical deactivation-box has been deactivated.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-61-00-040-001-A - Operational Check of the ECAM Landing Gear NOT DOWN Warning

** ON A/C ALL TASK 32-61-00-040-001-A Operational Check of the ECAM Landing Gear NOT DOWN Warning 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.

1.

Reason for the Job MMEL 32-61-02A DOWN Red Arrow on the Landing Gear

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

QTY AR AR AR

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 27-50-00-866-008-A). (Ref. 27-50-00-866-008-A-01). (Ref. 27-50-00-866-009-A). (Ref. 27-50-00-866-009-A-01). (Ref. 31-32-00-860-009-A). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 32-00-00-481-001-A). (Ref. 32-00-00-860-002-A). (Ref. 32-00-00-860-002-A-01).

3.

DESIGNATION SAFETY BARRIER(S) SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Extension of the Flaps on the Ground Extension of the Flaps/Slats on the Ground Retraction of the Flaps on the Ground Retraction of the Flaps/Slats on the Ground Procedure to Get Access to the SYSTEM REPORT/TEST/L/G Page EIS Start Procedure EIS Stop Procedure Installation of the Safety Devices on the Landing Gears Ground Configuration after Flight Configuration with Electrical Power Ground Configuration after Flight Configuration without Electrical Power

Job Set-up

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-61-00-040-001-A - Operational Check of the ECAM Landing Gear NOT DOWN Warning

Subtask 32-61-00-941-052-A A.

Safety Precautions (1) Put the SAFETY BARRIER(S) in position. (2) Make sure that the ground safety locks are on the landing gear (Ref. AMM TASK 32-00-00-481001) . (3) On panel 400VU: · Make sure that the landing-gear control-lever is in the DOWN position · Put a WARNING NOTICE(S) in position to tell persons not to operate the landing gear.

Subtask 32-61-00-860-052-A B.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Do the EIS start procedure (ECAM only) (Ref. AMM TASK 31-60-00-860-001) . (3) On the ECAM control panel (CP), push (in) the WHEEL pushbutton switch (P/BSW). Make sure that the WHEEL page shows on the ECAM lower display unit (DU). (4) Fully extend the flaps (Ref. AMM TASK 27-50-00-866-008) .

Subtask 32-61-00-865-053-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU 49VU 121VU

DESIGNATION ANTI ICE/PROBES/AOA/1 ANTI ICE/PROBES/PITOT/1 HYDRAULIC/LGCIU/SYS2

FIN 4DA1 3DA1 2GA

LOCATION D04 D02 Q35

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 EMB SB 32-1346 for A/C 016-019, 021-021, 201-201, 203-207, 209-211, 215-222, 226-235, 237-237, 239-240, 242-244, 350-350 121VU LGCIU/BAT SPLY/SYS2 59GA R33 ** ON A/C 401-450 121VU LGCIU/BAT SPLY/SYS2

59GA

R32

** ON A/C ALL 122VU 122VU 122VU 122VU 122VU 122VU 122VU 122VU 122VU

1DA2 3DA2 4DA2 5DA2 3DA3 4DA3 5DA3 5DA1 1DA1

Y15 Y14 Y13 Y11 Z16 Z15 Z14 Z13 Z12

ANTI ICE/PROBES/2/TAT ANTI ICE/PROBES/2/PITOT ANTI ICE/PROBES/2/AOA ANTI ICE/PROBES/2/STATIC ANTI ICE/PROBES/3/PITOT ANTI ICE/PROBES/3/AOA ANTI ICE/PROBES/3/STATIC ANTI ICE/PROBES/1/STATIC ANTI ICE/PROBES/1/TAT

Subtask 32-61-00-869-056-A D.

Cockpit Configuration (1) On the panel 115VU, make sure that the ENG MASTER 1 and MASTER 2 levers are in the OFF position.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-61-00-040-001-A - Operational Check of the ECAM Landing Gear NOT DOWN Warning

(2) On the panel 50VU, push (in) and release (out) the FADEC GND PWR 1 or 2 P/BSW. Make sure that the applicable P/BSW ON light goes off and then comes on. (3) On the center pedestal, put the throttle levers in the IDLE position. (4) Get access to the L/G page on the MCDU (Ref. AMM TASK 31-32-00-860-009) . 4.

Procedure Subtask 32-61-00-040-050-A A.

Operational Check of the ECAM Landing Gear NOT DOWN Warning (1) Do this test: ACTION RESULT 1.On the MCDU: On the MCDU: · push (in) the LGCIU1 P/BSW · the LGCIU1 menu shows · push (in) the NEXT PAGE P/BSW · the LGCIU1 Page 2 menu shows · push (in) the LANDING GEAR SIMULATION P/ · the LANDING GEAR SIMULATION page shows BSW · push (in) the NOSE+LH+RH P/BSW · the NOSE+LH+RH page menu shows · push (in) the UPLOCKED P/BSW. · the UPLOCKED '<' goes off. On the ECAM lower DU: · the WHEELS page shows the wheels in the UP position and L/G CTL in amber. NOTE : The amber crosses will stay on screen because the No. 2 LGCIU circuit breaker is open. On 402VU: - the UNLK (red) indicator lights show. On the ECAM upper DU: · the L/G GEAR NOT DOWN display comes into view and after 30 seconds, L/G GEAR NOT DOWNLOCKED shows. On the panels 130VU and 131VU: · the MASTER WARN lights flash · you can hear the warning chime. On the Landing-Gear Normal Control-Lever (6GA): · the red DOWN arrow light comes on. 2.On the ECAM CP: · push (in) the EMER CANC P/BSW.

The warning chime stops. On the panels 130VU and 131VU: · the MASTER WARN lights go off. On 402VU: - the UNLK (red) indicator lights stay on.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-61-00-040-001-A - Operational Check of the ECAM Landing Gear NOT DOWN Warning ACTION 3.On the MCDU: · push (in) the DOWNLOCKED P/BSW.

RESULT On the ECAM upper DU: · the L/G GEAR NOT DOWN and L/G GEAR NOT DOWNLOCKED display goes out of view - the UNLK (red) indicator lights go out and the LKD (green) indicator lights come on. On the Landing-Gear Normal Control-Lever (6GA): · the red DOWN arrow light goes off. On the ECAM lower DU: · the WHEELS page shows the wheels in the DOWN position.

NOTE : The amber crosses will stay on screen because the No 2 LGCIU circuit breaker is open. 4.Push (in) the RETURN P/BSW until the CFDS · the CFDS menu page shows. menu page shows. 5.Push in the MCDU MENU P/BSW. 5.

Close-up Subtask 32-61-00-865-055-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU

DESIGNATION HYDRAULIC/LGCIU/SYS2

FIN 2GA

LOCATION Q35

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 EMB SB 32-1346 for A/C 016-019, 021-021, 201-201, 203-207, 209-211, 215-222, 226-235, 237-237, 239-240, 242-244, 350-350 121VU LGCIU/BAT SPLY/SYS2 59GA R33 ** ON A/C 401-450 121VU LGCIU/BAT SPLY/SYS2

59GA

R32

** ON A/C ALL Subtask 32-61-00-860-053-A B.

Aircraft Maintenance Configuration (1) Put the aircraft back to the ground configuration (Ref. AMM TASK 32-00-00-860-002) . (2) Fully retract the flaps (Ref. AMM TASK 27-50-00-866-009) . (3) Cockpit Configuration (a) On the center pedestal: · Put the throttle levers in the 0 position. (b) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (c) On panel 50VU:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 32-61-00-040-001-A - Operational Check of the ECAM Landing Gear NOT DOWN Warning · Push (in) the FADEC GND PWR 1 or 2 P/BSW. Make sure that the applicable P/BSW ON light goes off. (4) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (5) Make an applicable entry in the aircraft technical log. (6) Put a placard in the cockpit to: · State that the DOWN red arrow light on the L/G lever does not operate. Subtask 32-61-00-942-052-A C.

Removal of Equipment (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the SAFETY BARRIER(S). (3) Remove the WARNING NOTICE(S). (4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 33-20-00-040-001-A - Deactivation of the Cabin NO SMOKING/FASTEN SEAT BELTS/RETURN TO SEAT (NS/FSB/RTS) or NO MOBILES/ FASTEN SEAT BELTS/RETURN TO SEAT (NM/FSB/RTS) Signs ** ON A/C ALL TASK 33-20-00-040-001-A Deactivation of the Cabin NO SMOKING/FASTEN SEAT BELTS/RETURN TO SEAT (NS/FSB/RTS) or NO MOBILES/FASTEN SEAT BELTS/RETURN TO SEAT (NM/FSB/RTS) Signs Task Summary MMEL or CDL Ref MMEL 33-20-02B

Access NO

Test NO

Specific Tools NO

Mhr 00.5

1.

Reason for the Job MMEL 33-20-02B Cabin Signs (No Smoking/No Electronic Devices/Fasten Seat Belt/Return to Seat)

2

Job Set-up Information A.

QTY DESIGNATION AR WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 23-73-00-710-017-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

3.

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

E/T 00.5

DESIGNATION Operational Test of the Cabin Signs Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up Subtask 33-20-00-861-051-A A.

4.

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

Procedure Subtask 33-20-00-040-051-A A.

Deactivation of the Cabin NS/FSB/RTS Signs (1) Do the operational test of the cabin signs (Ref. AMM TASK 23-73-00-710-017) and find the defective NS/FSB/RTS sign(s). (2) Find the passenger seats from which you cannot see the serviceable NS/FSB/RTS sign. (3) Put WARNING NOTICE(S) in position on these seats to tell the passengers not to use them.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 33-20-00-040-001-A - Deactivation of the Cabin NO SMOKING/FASTEN SEAT BELTS/RETURN TO SEAT (NS/FSB/RTS) or NO MOBILES/ FASTEN SEAT BELTS/RETURN TO SEAT (NM/FSB/RTS) Signs NOTE: It must be possible to see a serviceable NS/FSB/RTS sign from every passenger seat that is in use. (4) Make an entry in the aircraft technical logbook. 5.

Close-up Subtask 33-20-00-860-051-A A.

Aircraft Maintenance Configuration (1) Make sure that the work area is clean and clear of tools and other items. (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 33-51-00-040-001-A - Deactivation of the EMER SYSTEM TEST of the Cabin Emergency Lighting System

** ON A/C 201-201, 203-205, 207-207, 210-211, 217-217, 219-220, 231-234, 237-237, 240-240, 243-250 TASK 33-51-00-040-001-A Deactivation of the EMER SYSTEM TEST of the Cabin Emergency Lighting System Task Summary MMEL or CDL Ref MMEL 33-51-13A 1.

Reason for the Job MMEL 33-51-13A SYS TEST on the PTP

2

Job Set-up Information A.

Access NO

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

CAUTION:

3.

Test NO

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

DO NOT USE THE TEACH-IN PROCEDURE TO CLEAR EPSU FAILURE MESSAGES. THE TEACH-IN PROCEDURE IS NOT A SYSTEM RESET. IT CAN CHANGE THE EMERGENCY LIGHT CONFIGURATION AND CAUSE HIDDEN FAILURES.

Job Set-up NOTE: The teach-in procedure of the EPSUs measures and keeps the load values that are related to each EPSU. The EPSU controller refers to these load values when the BITE test of the emergency lighting system operates. Thus, it is necessary that the emergency lights of the related EPSUs operate correctly during the teach-in procedure. Subtask 33-51-00-861-057-A A.

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

Subtask 33-51-00-865-056-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 122VU

DESIGNATION LIGHTING/EMER LT/CABIN LIGHTING/EMER LT/CABIN LIGHTING/CABIN/EMER/LT

FIN 2WL 1WL 3WL

LOCATION H06 H05 V07

Subtask 33-51-00-860-055-A C.

Aircraft Maintenance Configuration

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 33-51-00-040-001-A - Deactivation of the EMER SYSTEM TEST of the Cabin Emergency Lighting System

(1) On the overhead panel 25VU, make sure that the EMER EXIT LT switch 4WL is in the OFF position. (2) On the overhead panel 25VU, make sure that the NO SMOKING switch 190RH is in the OFF position. (3) On the Forward Attendant Panel (FAP) 120RH, make sure that the LIGHT EMER pushbutton switch and its integral light are off. 4.

Procedure Subtask 33-51-00-710-060-A A.

Operational test of the Cabin Emergency-Lighting System NOTE: The time to do this test must not be more than 3 minutes, to prevent discharge of the emergency lighting batteries.

ACTION 1.In the cockpit, on the SIGNS panel 25VU: · set the EMER EXIT LT switch 4WL to the ARM position. 2.On the circuit breaker panel 49VU: · open the circuit breakers 1WL and 2WL.

RESULT In the cockpit, on the SIGNS panel 25VU: · the EMER EXIT LT OFF annunciator light 5WL is off. In the cabin: · · · ·

3.On the circuit breaker panel 49VU: · close the circuit breakers 1WL and 2WL.

all the cabin emergency lights come on all the exit marking signs come on all the exit location signs come on all the electrical lights of the Floor-Proximity Emergency-Escape-Path Marking-System come on · all the emergency-escape hatch-handle lights come on. In the cabin: · · · ·

4.In the cockpit, on the SIGNS panel 25VU: · set the EMER EXIT LT switch 4WL to the OFF position. 5.

all the cabin emergency lights go off all the exit marking signs go off all the exit location signs go off all the electrical lights of the Floor-Proximity Emergency-Escape-Path Marking-System go off · all the emergency-escape hatch-handle lights go off. In the cockpit, on the SIGNS panel 25VU: · the EMER EXIT LT OFF annunciator light 5WL comes on.

Close-up Subtask 33-51-00-862-056-A A.

Put the aircraft back to the serviceable condition. (1) Make an entry in the logbook. (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-10-00-040-001-A - OXY High Pressure Indication-Direct Reading

** ON A/C ALL TASK 35-10-00-040-001-A OXY High Pressure Indication-Direct Reading 1.

Reason for the Job MMEL 35-07-01A Crew OXY High Pressure Indication on the DOOR/OXY SD page

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE AR THERMOMETER

Work Zones and Access Panels ZONE/ACCESS 812

ZONE DESCRIPTION

C. Referenced Information REFERENCE

DESIGNATION

** ON A/C 201-201, 203-203, 206-207, 209-209, 211-211, 222-222, 236-236, 240-241, 243-243 (Ref. 12-14-35-600-001-A). Servicing of the Oxygen-Replenishing ** ON A/C ALL (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A).

Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power

** ON A/C 016-022, 024-100, 112-150, 204-205, 208-208, 210-210, 212-221, 223-235, 237-239, 242-242, 244-250, 350-350 (Ref. 35-11-41-000-001-A). Removal of the Crew Oxygen-Storage Cylinder ** ON A/C 301-349, 351-450, 500-600 (Ref. 35-11-41-000-802-A). Removal of the Crew Oxygen-Storage Cylinders ** ON A/C 016-022, 024-100, 112-150, 204-205, 208-208, 210-210, 212-221, 223-235, 237-239, 242-242, 244-250, 350-350 (Ref. 35-11-41-400-001-A). Installation of the Crew Oxygen-Storage Cylinder ** ON A/C 301-349, 351-450, 500-600 (Ref. 35-11-41-400-802-A). Installation of the Crew Oxygen-Storage Cylinders ** ON A/C ALL 3.

Job Set-up Subtask 35-10-00-861-051-A

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-10-00-040-001-A - OXY High Pressure Indication-Direct Reading

A.

Energize the Ground Service Network (Ref. AMM TASK 24-42-00-861-001) .

Subtask 35-10-00-010-053-A B.

Get Access (1) Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at access door 812. (2) Open access door 812.

4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 204-205, 208-208, 210-210, 212-221, 223-235, 237-239, 242-242, 244250, 350-350 Subtask 35-10-00-220-052-A A.

Check of the High Pressure of the Crew Oxygen-Storage Cylinder (1) Do a check of the oxygen pressure on the direct-reading pressure gage of the crew oxygen-storage cylinder (5750HM). (a) Record the oxygen pressure of the crew oxygen-storage cylinder (5750HM). (2) Measure the Outside Air Temperature (OAT) and the temperature in the cockpit with a THERMOMETER. (3) Calculate the reference temperature with this formula: OAT + COCKPIT TEMPERATURE ------------------------2 (4) Record the reference temperature. (5) Send the recorded values to the crew. (6) After the crew uses the Flight Crew Operating Manual (FCOM), if the oxygen pressure recorded at Step 4.A.(1).(a) is less than the minimum oxygen pressure found in the FCOM table: · Replace the crew oxygen-storage cylinder (5750HM) (Ref. AMM TASK 35-11-41-000-001) and (Ref. AMM TASK 35-11-41-400-001) .

** ON A/C 301-349, 351-450, 500-600 Subtask 35-10-00-220-052-B A.

Check of the High Pressure of the Crew Oxygen-Storage Cylinders (1) Do a check of the oxygen pressure on the direct-reading pressure gage of the crew oxygen-storage cylinders 5750HM1 and 5750HM2. (a) Record the oxygen pressure of the crew oxygen-storage cylinder 5750HM1 and record that this value is related to the Captain system. (b) Record the oxygen pressure of the crew oxygen-storage cylinder 5750HM2 and record that this value is related to the First Officer system. (2) Measure the Outside Air Temperature (OAT) and the temperature in the cockpit with a THERMOMETER. (3) Calculate the reference temperature with this formula: OAT + COCKPIT TEMPERATURE ------------------------2 (4) Record the reference temperature. (5) Send the recorded values to the crew.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-10-00-040-001-A - OXY High Pressure Indication-Direct Reading

(6) After the crew uses the Flight Crew Operating Manual (FCOM), if the oxygen pressure(s) recorded at Step 4.A.(1) is (are) less than the minimum oxygen pressure(s) found in the FCOM table: · Replace the crew oxygen-storage cylinder(s) (5750HM1) and/or (5750HM2) (Ref. AMM TASK 3511-41-000-802) and (Ref. AMM TASK 35-11-41-400-802) . ** ON A/C 201-201, 203-203, 206-207, 209-209, 211-211, 222-222, 236-236, 240-241, 243-243 Subtask 35-10-00-220-052-C A.

Check of the High Pressure of the Crew Oxygen-Storage Cylinder (1) Do a check of the oxygen pressure on the direct-reading pressure gage of the crew oxygen-storage cylinder (5750HM). (a) Record the oxygen pressure of the crew oxygen-storage cylinder (5750HM). (2) Measure the Outside Air Temperature (OAT) and the temperature in the cockpit with a THERMOMETER. (3) Calculate the reference temperature with this formula: OAT + COCKPIT TEMPERATURE ------------------------2 (4) Record the reference temperature. (5) Send the recorded values to the crew. (6) After the crew uses the Flight Crew Operating Manual (FCOM), if the oxygen pressure recorded at Step 4.A.(1).(a) is less than the minimum oxygen pressure found in the FCOM table: · Fill the crew oxygen-storage cylinder (5750HM) (Ref. AMM TASK 12-14-35-600-001) .

** ON A/C ALL 5.

Close-up Subtask 35-10-00-410-053-A A.

Close Access (1) Close access door 812. (2) Remove the access platform(s). (3) Make an entry in the logbook.

Subtask 35-10-00-862-051-A B.

De-energize the Ground Service Network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-10-00-040-002-A - Loss of REGUL LO PR Indication

** ON A/C ALL TASK 35-10-00-040-002-A Loss of REGUL LO PR Indication WARNING:

KEEP ALL HYDROCARBONS (FUELS, LUBRICANTS, ETC.) AWAY FROM ALL SOURCE OF OXYGEN. OXYGEN BECOMES EXPLOSIVE WHEN IT TOUCHES HYDROCARBONS.

WARNING:

CLEAN THE TOOLS AND MAKE SURE YOUR HANDS ARE CLEAN TO PREVENT CONTAMINATION OF THE OXYGEN SYSTEM.

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.

1.

Reason for the Job MMEL 35-07-02A Crew Oxygen REGUL LO PR Indication on the DOOR/OXY The crew-oxygen REGUL LO PR indication on the DOOR/OXY page is incorrect if: · The REGUL LO PR indication is continuously shown when the oxygen pressure is not low, or · The REGUL LO PR indication is not shown when there is a low pressure condition. This task is to make sure that there is sufficient oxygen pressure in the oxygen system before the flight.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific (110111-03) OR (802857-01)

QTY AR 1 AR 1 1

DESIGNATION ACCESS PLATFORM 2M (6 FT) GAGE 10 BAR (145 PSI) - PRESSURE WARNING NOTICE(S) COUPLING-OXYGEN QUICK DISCONNECT OR COUPLING

** ON A/C 301-349, 351-450, 500-600 (98D35208729001) 1 TOOL-DPRESS, TEST-O2 ** ON A/C ALL B.

Work Zones and Access Panels ZONE/ACCESS 123 125 210 812

ZONE DESCRIPTION NOSE GEAR WELL LATERAL AVIONIC COMPARTMENT CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-10-00-040-002-A - Loss of REGUL LO PR Indication

REFERENCE (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 35-00-00-860-001-A).

DESIGNATION Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Special Precautions When Working on a Gaseous Oxygen System

** ON A/C 301-349, 351-450, 500-600 (Ref. 52-41-00-010-002-A). Open the Avionics Compartment Doors for Access (Ref. 52-41-00-410-002-A). Close the Avionics Compartment Doors after Access ** ON A/C ALL ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 REGUL LO PR Indication SHEET 1 ** ON A/C 301-349, 351-450, 500-600 Component Location - Test Ports

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-10-00-040-002-A - Loss of REGUL LO PR Indication

ACCESS DOOR 812

A

A

Z115 FR16 FR9

5750HM

B B

5755HM

N_MM_351000_4_AAM0_01_00

Figure 35-10-00-991-00600-00-A / SHEET 1/1 - REGUL LO PR Indication ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-10-00-040-002-A - Loss of REGUL LO PR Indication

Z123

FR18

FR10

A

812

B

D C E FR11 FR12

FR16 FR17

A

N_MM_351000_4_AAN0_01_00

Figure 35-10-00-991-00600-00-B / SHEET 1/2 - Component Location - Test Ports ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-10-00-040-002-A - Loss of REGUL LO PR Indication

2

5750HM1

1

4

B

5750HM2

5

5755HM1 5755HM2

D E

3

C

6

D

E

TYPICAL N_MM_351000_4_AAN0_02_00

Figure 35-10-00-991-00600-00-B / SHEET 2/2 - Component Location - Test Ports ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-10-00-040-002-A - Loss of REGUL LO PR Indication

3.

Job Set-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 35-10-00-010-058-A A.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) in position at access door 812. (2) Open access door 812. (3) Fully close the valve of the oxygen storage cylinder (5750HM). (4) Put a WARNING NOTICE(S) in position to tell persons not to open the valve of the oxygen storage cylinder (5750HM).

** ON A/C 301-349, 351-450, 500-600 Subtask 35-10-00-010-058-B A.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) in position at access door 812. (2) Open access door 812 (Ref. AMM TASK 52-41-00-010-002) .

** ON A/C ALL Subtask 35-10-00-865-053-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU

DESIGNATION OXYGEN/CREW/OXY/SPLY

FIN 1HT

LOCATION HA01

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 35-10-00-860-061-A C.

Aircraft Maintenance Configuration (1) Obey the special precautions when you do work on a gaseous oxygen system (Ref. AMM TASK 3500-00-860-001) . (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) Bleed the oxygen system: (a) In the cockpit, on the OXYGEN section of the overhead control and indicating panel 21VU, push the CREW SUPPLY pushbutton switch (the OFF legend goes off). (b) Put a WARNING NOTICE(S) in position to tell persons not to release the CREW SUPPLY pushbutton switch. (c) On one oxygen-mask stowage box, push and hold the PRESS TO TEST AND RESET control lever. At the same time, push and hold the PRESS TO TEST/EMERGENCY knob on the mask regulator. 1

Keep them pushed for a minimum of three seconds. NOTE: During this time, the flow rate indicator changes from yellow to black and the volume of the sound of the oxygen flow decreases.

(d) When the flow rate indicator is black and when you no longer hear the sound of the oxygen flow:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-10-00-040-002-A - Loss of REGUL LO PR Indication

· Release the PRESS TO TEST/EMERGENCY knob. · Release the PRESS TO TEST AND RESET control lever. (e) Make sure that the PRESS TO TEST/EMERGENCY knob is not in the EMERGENCY position. If it is in the EMERGENCY position, there can be a leak of oxygen. ** ON A/C 301-349, 351-450, 500-600 Subtask 35-10-00-860-061-C C.

Aircraft Maintenance Configuration (1) Obey the special precautions when you do work on a gaseous oxygen system (Ref. AMM TASK 3500-00-860-001) . (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) On the crew oxygen-storage cylinder 5750HM1 (1): (a) Fully close the manual shutoff valve (2) of the crew oxygen-storage cylinder 5750HM1 (1). (b) Put a WARNING NOTICE(S) in position to tell persons not to open the manual shutoff valve (2) of the crew oxygen-storage cylinder 5750HM1 (1). (4) On the crew oxygen-storage cylinder 5750HM2 (3): (a) Fully close the manual shutoff valve (4) of the crew oxygen-storage cylinder 5750HM2 (3). (b) Put a WARNING NOTICE(S) in position to tell persons not to open the manual shutoff valve (4) of the crew oxygen-storage cylinder 5750HM2 (3).

Subtask 35-10-00-614-054-A D.

Bleeding of the Two Oxygen Systems (1) In the cockpit, on the OXYGEN section of the overhead control and indicating panel 21VU: · Push the CREW SUPPLY pushbutton switch (the OFF legend goes off). · Put a WARNING NOTICE(S) in position to tell persons not to release the CREW SUPPLY pushbutton switch. (2) On the Captain oxygen-mask stowage-box, push and hold the PRESS TO TEST AND RESET control button. At the same time, push and hold the PRESS TO TEST/EMERGENCY knob on the mask regulator. (a) Keep them pushed for a minimum of three seconds. NOTE: During this time, the flow rate indicator changes from yellow to black and the volume of the sound of the oxygen flow decreases. (b) When the flow rate indicator is black and when you can no longer hear the sound of the oxygen flow: · Release the PRESS TO TEST/EMERGENCY knob. · Release the PRESS TO TEST AND RESET control button. (c) Position of the PRESS TO TEST/EMERGENCY knob WARNING: MAKE SURE THAT THE PRESS TO TEST/EMERGENCY KNOB IS NOT IN THE EMERGENCY POSITION. IF IT IS IN THE EMERGENCY POSITION, THERE CAN BE A LEAK OF OXYGEN. 1

Make sure that the PRESS TO TEST/EMERGENCY knob is not in the EMERGENCY position.

(3) On the First-Officer oxygen-mask stowage-box, push and hold the PRESS TO TEST AND RESET control button. Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-10-00-040-002-A - Loss of REGUL LO PR Indication

At the same time, push and hold the PRESS TO TEST/EMERGENCY knob on the mask regulator. (a) Keep them pushed for a minimum of three seconds. NOTE: During this time, the flow rate indicator changes from yellow to black and the volume of the sound of the oxygen flow decreases. (b) When the flow rate indicator is black and when you can no longer hear the sound of the oxygen flow: · Release the PRESS TO TEST/EMERGENCY knob. · Release the PRESS TO TEST AND RESET control button. (c) Position of the PRESS TO TEST/EMERGENCY knob WARNING: MAKE SURE THAT THE PRESS TO TEST/EMERGENCY KNOB IS NOT IN THE EMERGENCY POSITION. IF IT IS IN THE EMERGENCY POSITION, THERE CAN BE A LEAK OF OXYGEN. 1

Make sure that the PRESS TO TEST/EMERGENCY knob is not in the EMERGENCY position.

** ON A/C ALL 4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (Ref. Fig. REGUL LO PR Indication SHEET 1) ** ON A/C 301-349, 351-450, 500-600 (Ref. Fig. Component Location - Test Ports) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 35-10-00-720-050-A A.

Check of the LP Oxygen of the Crew Oxygen Cylinder (1) Remove the blanking cap from the oxygen-system test-port 5755HM. (2) Connect the GAGE 10 BAR (145 PSI) - PRESSURE to the COUPLING-OXYGEN QUICK DISCONNECT (110111-03) or COUPLING (802857-01) or equivalent. (3) Connect the COUPLING-OXYGEN QUICK DISCONNECT (110111-03) or COUPLING (802857-01) or equivalent to the oxygen-system test-port 5755HM. (4) Fully open the valve of the oxygen storage cylinder 5750HM. (5) Make sure that the pressure on the pressure gage is more than 50 psi (3.45 bar). (6) Fully close the valve of the oxygen storage cylinder 5750HM. (7) Bleed the oxygen system: (a) On one oxygen-mask stowage box, push and hold the PRESS TO TEST AND RESET control lever. At the same time, push and hold the PRESS TO TEST/EMERGENCY knob on the mask regulator. 1

Keep them pushed for a minimum of three seconds. NOTE: During this time, the flow rate indicator changes from yellow to black and the volume of the sound of the oxygen flow decreases.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-10-00-040-002-A - Loss of REGUL LO PR Indication

(b) When the flow rate indicator is black and when you no longer hear the sound of the oxygen flow: · Release the PRESS TO TEST/EMERGENCY knob. · Release the PRESS TO TEST AND RESET control lever. (c) Make sure that the PRESS TO TEST/EMERGENCY knob is not in the EMERGENCY position. If it is in the EMERGENCY position, there can be a leak of oxygen. ** ON A/C 301-349, 351-450, 500-600 Subtask 35-10-00-720-050-C A.

Check of the Low Pressure Oxygen of the Crew Oxygen-Storage Cylinders (1) At oxygen-system test-port 5755HM1 (5): (a) Remove the blanking cap (6) from oxygen-system test-port 5755HM1 (5). (b) Connect one of these tools to oxygen-system test-port 5755HM1 (5): · Assemble the GAGE 10 BAR (145 PSI) - PRESSURE and the COUPLING-OXYGEN QUICK DISCONNECT (110111-03) or COUPLING (802857-01) (or equivalent) and connect this assembly to the test-port. Or connect this alternative tool: · Connect the TOOL-DPRESS, TEST-O2 (98D35208729001) to the test port. (c) On the pressure gage of the tool, make sure that the oxygen system is fully depressurized. (2) Do a check of the oxygen pressure as follows: (a) Turn the manual shutoff valve. CAUTION: WHEN YOU OPEN THE MANUAL SHUTOFF VALVE ON THE CREW OXYGEN-STORAGE CYLINDER, MAKE SURE THAT: - YOU TURN IT VERY SLOWLY - YOU TURN IT UNTIL IT IS FULLY OPEN. IF YOU TURN THE MANUAL SHUTOFF VALVE TOO QUICKLY, YOU CAN CAUSE DAMAGE TO THE EQUIPMENT. IF THE MANUAL SHUTOFF VALVE IS NOT FULLY OPEN, THE OXYGEN PRESSURE DATA CAN BE INCORRECT. 1

Turn the manual shutoff valve (2) of the crew oxygen-storage-cylinder 5750HM1 (1) very slowly until it is fully open.

(b) Wait one minute to make sure that the pressure is stable. (c) Make sure that the oxygen pressure on the pressure gage is more than 50 psi (3.45 bar). (3) Bleed the Captain oxygen system: (a) On the crew oxygen-storage-cylinder 5750HM1 (1): · Fully close the manual shutoff valve (2) of the crew oxygen-storage-cylinder 5750HM1 (1). (b) On the Captain oxygen-mask stowage-box, push and hold the PRESS TO TEST AND RESET control button. At the same time, push and hold the PRESS TO TEST/EMERGENCY knob on the mask regulator. 1

Keep them pushed for a minimum of three seconds. NOTE: During this time, the flow rate indicator changes from yellow to black and the volume of the sound of the oxygen flow decreases.

2

When the flow rate indicator is black and when you can no longer hear the sound of the oxygen flow:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-10-00-040-002-A - Loss of REGUL LO PR Indication

· Release the PRESS TO TEST/EMERGENCY knob. · Release the PRESS TO TEST AND RESET control button. 3

Position of the PRESS TO TEST/EMERGENCY knob WARNING: MAKE SURE THAT THE PRESS TO TEST/EMERGENCY KNOB IS NOT IN THE EMERGENCY POSITION. IF IT IS IN THE EMERGENCY POSITION, THERE CAN BE A LEAK OF OXYGEN. a

Make sure that the PRESS TO TEST/EMERGENCY knob is not in the EMERGENCY position.

(4) Disconnect the applicable tool from oxygen-system test-port 5755HM1 (5): · Disconnect the COUPLING-OXYGEN QUICK DISCONNECT (11011103) or COUPLING (802857-01) (or equivalent) from the test-port. NOTE: It is not necessary to disassemble the GAGE 10 BAR (145 PSI) - PRESSURE from the COUPLING-OXYGEN QUICK DISCONNECT (110111-03) or COUPLING (802857-01) (or equivalent) at this time. Or disconnect this alternative tool: · Disconnect the TOOL-DPRESS, TEST-O2 (98D35208729001) from the test-port. (a) Put the blanking cap (6) on the oxygen-system test-port 5755HM1 (5). (5) At oxygen-system test-port 5755HM2 (5): (a) Remove the blanking cap (6) from oxygen-system test-port 5755HM2 (5). (b) Connect one of these tools to oxygen-system test-port 5755HM2 (5): · Connect the COUPLING-OXYGEN QUICK DISCONNECT (11011103) or COUPLING (802857-01) (or equivalent) with its GAGE 10 BAR (145 PSI) PRESSURE to the test port. Or connect this alternative tool: · Connect the TOOL-DPRESS, TEST-O2 (98D35208729001) to the test port. (c) On the pressure gage of the tool, make sure that the oxygen system is fully depressurized. (6) Do a check of the oxygen pressure as follows: (a) Turn the manual shutoff valve. CAUTION: WHEN YOU OPEN THE MANUAL SHUTOFF VALVE ON THE CREW OXYGEN-STORAGE CYLINDER, MAKE SURE THAT: - YOU TURN IT VERY SLOWLY - YOU TURN IT UNTIL IT IS FULLY OPEN. IF YOU TURN THE MANUAL SHUTOFF VALVE TOO QUICKLY, YOU CAN CAUSE DAMAGE TO THE EQUIPMENT. IF THE MANUAL SHUTOFF VALVE IS NOT FULLY OPEN, THE OXYGEN PRESSURE DATA CAN BE INCORRECT. 1

Turn the manual shutoff valve (4) of crew oxygen-storage-cylinder 5750HM2 (3) very slowly until it is fully open.

(b) Wait one minute to make sure that the pressure is stable. (c) Make sure that the oxygen pressure on the pressure gage is more than 50 psi (3.45 bar). (7) Bleed the First-Officer oxygen system: (a) On crew oxygen-storage-cylinder 5750HM2 (3): · Fully close the manual shutoff valve (4) of crew oxygen-storage-cylinder 5750HM2 (3). Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-10-00-040-002-A - Loss of REGUL LO PR Indication

(b) In the cockpit, on the OXYGEN section of the overhead control and indicating panel 21VU: · Release the CREW SUPPLY pushbutton switch (the OFF legend comes on). (c) On the First-Officer oxygen-mask stowage-box, push and hold the PRESS TO TEST AND RESET control button. At the same time, push and hold the PRESS TO TEST/EMERGENCY knob on the mask regulator. 1

Keep them pushed for a minimum of three seconds. NOTE: During this time, the flow rate indicator changes from yellow to black and the volume of the sound of the oxygen flow decreases.

2

When the flow rate indicator is black and when you can no longer hear the sound of the oxygen flow: · Release the PRESS TO TEST/EMERGENCY knob. · Release the PRESS TO TEST AND RESET control button.

3

Position of the PRESS TO TEST/EMERGENCY knob WARNING: MAKE SURE THAT THE PRESS TO TEST/EMERGENCY KNOB IS NOT IN THE EMERGENCY POSITION. IF IT IS IN THE EMERGENCY POSITION, THERE CAN BE A LEAK OF OXYGEN. a

Make sure that the PRESS TO TEST/EMERGENCY knob is not in the EMERGENCY position.

(8) Disconnect and/or disassemble the applicable tool from oxygen-system test-port 5755HM2 (5): · Disconnect the COUPLING-OXYGEN QUICK DISCONNECT (11011103) or COUPLING (802857-01) (or equivalent) from the test port and disassemble it from the GAGE 10 BAR (145 PSI) - PRESSURE. Or disconnect this alternative tool: · Disconnect the TOOL-DPRESS, TEST-O2 (98D35208729001) from the test port. (a) Put the blanking cap (6) on oxygen-system test-port 5755HM2 (5). ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 35-10-00-020-050-A B.

Disconnect the Test Installation (1) Remove the COUPLING-OXYGEN QUICK DISCONNECT (110111-03) or COUPLING (802857-01) or equivalent from the oxygen-system test-port 5755HM. (2) Remove the GAGE 10 BAR (145 PSI) - PRESSURE from the COUPLING-OXYGEN QUICK DISCONNECT (110111-03) or COUPLING (802857-01) or equivalent. (3) Put the blanking cap on the oxygen-system test-port 5755HM.

** ON A/C ALL 5.

Close-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 35-10-00-860-062-A A.

Put the aircraft back to its initial configuration. (1) In the cockpit, on the OXYGEN section of the overhead control and indicating panel 21VU, release the OXYGEN/CREW SUPPLY pushbutton switch (the OFF legend comes on).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-10-00-040-002-A - Loss of REGUL LO PR Indication

(2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (3) Make sure that the work area is clean and clear of tools and other items. (4) Fully open the valve of the oxygen storage cylinder. (5) Remove the WARNING NOTICE(S). (6) Close the access door 812. (7) Remove the access platform(s). (8) Make an entry in the logbook. ** ON A/C 301-349, 351-450, 500-600 Subtask 35-10-00-860-062-B A.

Put the aircraft back to its initial configuration. (1) In the cockpit, on the OXYGEN section of the overhead control and indicating panel 21VU, make sure that the CREW SUPPLY pushbutton switch is released (the OFF legend is on). (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (3) Make sure that the work area is clean and clear of tools and other items. (4) Turn the manual shutoff valves CAUTION: TURN THE MANUAL SHUTOFF VALVES VERY SLOWLY ON ALL THE CREW OXYGEN-STORAGE CYLINDERS UNTIL THEY ARE FULLY OPEN. IF YOU TURN THE MANUAL SHUTOFF VALVES TOO QUICKLY, YOU CAN CAUSE DAMAGE TO THE EQUIPMENT. CAUTION: TURN THE HANDVALVES ON ALL OXYGEN BOTTLES UNTIL THEY ARE FULLY OPEN. IF THE HANDVALVES ARE NOT FULLY OPEN BEFORE FLIGHT, IT IS POSSIBLE THAT THE OXYGEN PRESSURE DATA ON THE ECAM DOOR/OXY PAGE WILL NOT BE CORRECT. (a) Turn the manual shutoff valve (2) of the crew oxygen-storage cylinder 5750HM1 (1) very slowly until it is fully open. (b) Turn the manual shutoff valve (4) of the crew oxygen-storage cylinder 5750HM2 (3) very slowly until it is fully open. (5) Remove the WARNING NOTICE(S). (6) Close access door 812 (Ref. AMM TASK 52-41-00-410-002) . (7) Remove the access platform(s). (8) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 12 of 12

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-001-A - Check of the MAN MASK pushbutton when the HI ALT system does not operate

** ON A/C 212-212 TASK 35-23-00-040-001-A Check of the MAN MASK pushbutton when the HI ALT system does not operate WARNING:

KEEP ALL HYDROCARBONS (FUELS, LUBRICANTS, ETC.) AWAY FROM ALL SOURCE OF OXYGEN. OXYGEN BECOMES EXPLOSIVE WHEN IT TOUCHES HYDROCARBONS.

WARNING:

CLEAN THE TOOLS AND MAKE SURE YOUR HANDS ARE CLEAN TO PREVENT CONTAMINATION OF THE OXYGEN SYSTEM.

WARNING:

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

Task Summary MMEL or CDL Ref MMEL 35-01-01-33A 1.

Reason for the Job MMEL 35-01-01-33A HI ALT LANDING pb-sw

2

Job Set-up Information A.

Access YES

Specific Tools YES

Mhr 01.8

E/T 01.8

Nb Men 2

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific (98A35207599000)

B.

Test NO

QTY 1 1 1

DESIGNATION LABEL - ADHESIVE, INOP VACUUM EQUIPMENT 0 TO 1 BAR (15 PSI) HOSE-ADAPTER,ALTITUDE SWITCH

Consumable Materials REFERENCE No specific

DESIGNATION vacuum source

C. Work Zones and Access Panels ZONE/ACCESS 120 200 824

ZONE DESCRIPTION AVIONICS COMPARTMENT UPPER HALF FUSELAGE

D. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-001-A - Check of the MAN MASK pushbutton when the HI ALT system does not operate REFERENCE (Ref. 24-41-00-862-002-A).

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 35-00-00-860-001-A). Special Precautions When Working on a Gaseous Oxygen System (Ref. 52-41-00-010-002-A). Open the Avionics Compartment Doors for Access (Ref. 52-41-00-410-002-A). Close the Avionics Compartment Doors after Access Altitude Pressure Switch 16WR SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-001-A - Check of the MAN MASK pushbutton when the HI ALT system does not operate

FR24

FR20

824

A Z127 80VU

A

1 16WR 3 2

N_MM_352300_4_BAM0_01_01

Figure 35-23-00-991-00600-00-A / SHEET 1/1 - Altitude Pressure Switch 16WR ** ON A/C 212-212 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-001-A - Check of the MAN MASK pushbutton when the HI ALT system does not operate

3.

Job Set-up Subtask 35-23-00-860-056-A A.

Aircraft Maintenance Configuration (1) Obey the special precautions when you work on a gaseous oxygen system (Ref. AMM TASK 35-0000-860-001) . (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) In the cockpit, on the OXYGEN section of overhead panel 21VU: (a) Put a WARNING NOTICE(S) in position to tell persons not to operate the emergency oxygen system. (4) Make sure that the HIGH ALT SWITCH ON pushbutton switch 899WR on overhead panel 21VU is set to the normal position. (5) On the emergency oxygen containers: (a) Set the test buttons to the TEST position.

Subtask 35-23-00-010-058-A B.

Get Access (Ref. Fig. Altitude Pressure Switch 16WR SHEET 1) (1) Get access to the altitude pressure switch 16WR (1): (a) Open the access door 824 (Ref. AMM TASK 52-41-00-010-002) .

Subtask 35-23-00-865-086-A C.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 49VU 49VU 49VU 49VU 49VU

DESIGNATION FIN OXYGEN/PASSENGER/ACTUATION 7WR OXYGEN/PASSENGER/ACTUATION 6WR OXYGEN/PASSENGER/ACTUATION 5WR OXYGEN/PASSENGER/ACTUATION 4WR OXYGEN/PASSENGER/CTL AND WARN 3WR OXYGEN/PASSENGER/CTL AND WARN 2WR OXYGEN/PASSENGER/CTL AND WARN 1WR

LOCATION HA08 HA07 HA06 HA05 HA04 HA03 HA02

Subtask 35-23-00-480-053-A D.

Connecting of the Vacuum Source (Ref. Fig. Altitude Pressure Switch 16WR SHEET 1) (1) Do not disconnect electrical connection from the altitude pressure switch 16WR (1). (2) Connect the VACUUM EQUIPMENT 0 TO 1 BAR (15 PSI) to the connector (3) of the altitude pressure switch 16WR (1) with the HOSE-ADAPTER,ALTITUDE SWITCH (98A35207599000) (2).

4.

Procedure

** ON A/C 212-212 PRE SB 35-1068 for A/C 212-212 Subtask 35-23-00-040-050-B A.

Check of the MAN MASK pushbutton when the HI ALT system does not operate (1) Do the functional test of the automatic mask release:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-001-A - Check of the MAN MASK pushbutton when the HI ALT system does not operate ACTION 1.At the vacuum source: · Slowly increase the pressure to 14800 ft. (4510.96 m).

2.At the vacuum source: · Slowly decrease the pressure to 0 ft. (0 m). 3.On the panel 50VU: · Push and hold the TMR RESET pushbutton switch.

· Release the TMR RESET pushbutton switch.

RESULT On the panel 21VU: · The SYS ON indicator light comes on at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or -228.60 m). On all the emergency oxygen containers: · The doors open to the maximum permitted by the test buttons.

On the panel 50VU: · The ON indicator light on the TMR RESET pushbutton switch comes on. On the panel 21VU: · The SYS ON indicator light goes off. On the panel 50VU: · The ON indicator light on the TMR RESET pushbutton switch goes off.

CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. 4.In the cabin at the first and second seat row close the door of the emergency oxygen containers: · Push the door of all related emergency oxygen container to the closed position · Push the door of all related emergency oxygen container, at both sides of the test button, to lock the latch mechanism. · Make sure that the door is flush with the adjacent panels. 5.On the overhead panel 21VU: On the overhead panel 21VU:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-001-A - Check of the MAN MASK pushbutton when the HI ALT system does not operate ACTION RESULT · Push the HIGH ALT SWITCH ON pushbutton · The ON legend in the HIGH ALT SWITCH ON switch. pushbutton switch comes on. 6.At the vacuum source: On the panel 21VU: · Slowly increase the pressure to 16800 ft. (5120 · The SYS ON indicator light comes on at 16000 m). -250 ft. or -750 ft. (4876.71 -76.20 m or -228.60 m). On all the emergency oxygen containers at the first and second seatrow: · The doors open to the maximum permitted by the test buttons. 7.At the vacuum source: · Slowly decrease the pressure to 0 ft. (0 m). 8.On the panel 50VU: On the panel 50VU: · Push and hold the TMR RESET pushbutton · The ON indicator light on the TMR RESET pushswitch. button switch comes on. On the panel 21VU: · The SYS ON indicator light goes off. · Release the TMR RESET pushbutton switch. On the panel 50VU: · The ON indicator light on the TMR RESET pushbutton switch goes off. 9.On the overhead panel 21VU: On the overhead panel 21VU: · Push to release the HIGH ALT SWITCH ON · The ON legend in the HIGH ALT SWITCH ON pushbutton switch. pushbutton switch goes off.

** ON A/C POST SB 35-1068 for A/C 212-212 Subtask 35-23-00-040-050-E A.

Check of the MAN MASK pushbutton when the HI ALT system does not operate (1) Do the functional test of the automatic mask release: ACTION 1.At the vacuum source: · Slowly decrease the pressure to 14800 ft. (4510.96 m).

RESULT On the panel 21VU: · The SYS ON indicator light comes on at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or -228.60 m). On the Engine/Warning Dispaly (EWD): · The OXY PAX ON indicator comes on at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or -228.60 m) On all the emergency oxygen containers: · The doors open to the maximum permitted by the test buttons. In the cabin: · The emergency announcement starts. NOTE: The emergency stops automatically when the recorded announcement is completed.

2.At the vacuum source:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-001-A - Check of the MAN MASK pushbutton when the HI ALT system does not operate ACTION · Slowly increase the pressure to 0 ft. (0 m). 3.On the panel 50VU: · Push and hold the TMR RESET pushbutton switch.

· Release the TMR RESET pushbutton switch.

RESULT On the panel 50VU: · The ON indicator light on the TMR RESET pushbutton switch comes on. On the panel 21VU: · The SYS ON indicator light goes off. On the EWD: · The OXY PAX ON indicator goes off. On the panel 50VU: · The ON indicator light on the TMR RESET pushbutton switch goes off.

CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. 4.In the cabin at the first and second seat row close the door of the emergency oxygen containers: · Push the door of all related emergency oxygen container to the closed position · Push the door of all related emergency oxygen container, at both sides of the test button, to lock the latch mechanism. · Make sure that the door is flush with the adjacent panels. 5.On the overhead panel 21VU: · Push the HIGH ALT SWITCH ON pushbutton switch. 6.At the vacuum source: · Slowly decrease the pressure to 16800 ft. (5120.55 m).

On the overhead panel 21VU: · The ON legend in the HIGH ALT SWITCH ON pushbutton switch comes on. On the panel 21VU: · The SYS ON indicator light comes on at 16000 +250 ft. or -750 ft. (4876.71 +76.20 m or -228.60 m). On the EWD:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-001-A - Check of the MAN MASK pushbutton when the HI ALT system does not operate ACTION

RESULT · The OXY PAX ON indicator comes on at 16000 +250 ft. or -750 ft. (4876.71 +76.20 m or -228.60 m) On all the emergency oxygen containers at the first and second seatrow: · The doors open to the maximum permitted by the test buttons. In the cabin: · The emergency announcement starts. NOTE: The emergency stops automatically when the recorded announcement is completed.

7.At the vacuum source: · Slowly increase the pressure to 0 ft. (0 m). 8.On the panel 50VU: · Push and hold the TMR RESET pushbutton switch.

· Release the TMR RESET pushbutton switch.

9.On the overhead panel 21VU: · Push to release the HIGH ALT SWITCH ON pushbutton switch.

On the panel 50VU: · The ON indicator light on the TMR RESET pushbutton switch comes on. On the panel 21VU: · The SYS ON indicator light goes off. On the EWD: · The OXY PAX ON indicator goes off. On the panel 50VU: · The ON indicator light on the TMR RESET pushbutton switch goes off. On the overhead panel 21VU: · The ON legend in the HIGH ALT SWITCH ON pushbutton switch goes off.

** ON A/C 212-212 5.

Close-up Subtask 35-23-00-080-053-B A.

Disconnecting of the Vacuum Source (Ref. Fig. Altitude Pressure Switch 16WR SHEET 1) (1) Disconnect the vacuum source and the HOSE-ADAPTER,ALTITUDE SWITCH (98A35207599000) (2) from the connector (3) of the altitude pressure switch 16WR (1).

Subtask 35-23-00-410-057-B B.

Close Access (1) Close all doors of the emergency oxygen containers: CAUTION: DO NOT USE TOO MUCH FORCE TO CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. (a) Push the door of the emergency oxygen container to the closed position.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-001-A - Check of the MAN MASK pushbutton when the HI ALT system does not operate

(b) Push the door of the emergency oxygen container, at both sides of the test button, to lock the latch mechanism. (c) Make sure that the door is flush with the adjacent panels. (2) Put the test buttons of the emergency oxygen containers to the normal position. NOTE: Spring tension will retract the test buttons when they are in the normal position. (3) If not installed, install a LABEL - ADHESIVE, INOP: (a) On the overhead panel, on the control panel 21VU, install the LABEL - ADHESIVE, INOP adjacent to the HIGH ALT SWITCH. (4) Make sure that the work area is clean and clear of tools and other items. (5) Close the access door 824 (Ref. AMM TASK 52-41-00-410-002) . (6) Make an applicable entry in the logbook. Subtask 35-23-00-860-077-A C.

Aircraft Maintenance Configuration (1) In the cockpit, on the OXYGEN section of overhead panel 21VU: (a) Remove the WARNING NOTICE(S). (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 9

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton

** ON A/C ALL TASK 35-23-00-040-008-A Check of the AUTO control function of the MASK MAN ON pushbutton WARNING:

KEEP ALL HYDROCARBONS (FUELS, LUBRICANTS, ETC.) AWAY FROM ALL SOURCE OF OXYGEN. OXYGEN BECOMES EXPLOSIVE WHEN IT TOUCHES HYDROCARBONS.

WARNING:

CLEAN THE TOOLS AND MAKE SURE YOUR HANDS ARE CLEAN TO PREVENT CONTAMINATION OF THE OXYGEN SYSTEM.

Task Summary MMEL or CDL Ref MMEL 35-01-01-31A

Access YES

Test NO

1.

Reason for the Job MMEL 35-01-01-31A MANUAL Control of the MASK MAN ON pb

2

Job Set-up Information A.

Mhr 02.0

E/T 02.0

Nb Men 2

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific (98A35207599000)

B.

Specific Tools YES

QTY 1 1 1

DESIGNATION LABEL - ADHESIVE, INOP VACUUM EQUIPMENT 0 TO 1 BAR (15 PSI) HOSE-ADAPTER,ALTITUDE SWITCH

Work Zones and Access Panels ZONE/ACCESS 120 200 812, 824

ZONE DESCRIPTION AVIONICS COMPARTMENT UPPER HALF FUSELAGE

C. Referenced Information REFERENCE

DESIGNATION

** ON A/C 201-201, 203-205, 207-207, 209-211, 217-217, 219-220, 226-226, 230-235, 237-237, 240-240, 242-250 (Ref. 23-73-00-861-001-A). Energize the Cabin Intercommunication Data System (CIDS) ** ON A/C ALL (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01).

Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton REFERENCE (Ref. 24-41-00-862-002-A-02). (Ref. 35-00-00-860-001-A). (Ref. 52-41-00-010-002-A). (Ref. 52-41-00-410-002-A).

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Special Precautions When Working on a Gaseous Oxygen System Open the Avionics Compartment Doors for Access Close the Avionics Compartment Doors after Access

** ON A/C 212-212 Altitude Pressure Switch 16WR SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton

FR24

FR20

824

A Z127 80VU

A

1 16WR 3 2

N_MM_352300_4_BAM0_01_01

Figure 35-23-00-991-00600-00-A / SHEET 1/1 - Altitude Pressure Switch 16WR ** ON A/C 212-212 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton

3.

Job Set-up

** ON A/C 016-022, 024-100, 112-150, 206-206, 208-208, 212-216, 218-218, 221-225, 227-229, 236-236, 238239, 241-241, 301-450, 500-600 Subtask 35-23-00-860-073-A A.

Aircraft Maintenance Configuration (1) Obey the special precautions when you work on a gaseous oxygen system (Ref. AMM TASK 35-0000-860-001) . (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) In the cockpit, on the OXYGEN section of overhead panel 21VU: (a) Put a WARNING NOTICE(S) in position to tell persons not to operate the emergency oxygen system. (4) On all the emergency oxygen containers: (a) Push the test buttons to the test position.

** ON A/C 201-201, 203-205, 207-207, 209-211, 217-217, 219-220, 226-226, 230-235, 237-237, 240-240, 242-250 Subtask 35-23-00-860-073-B A.

Aircraft Maintenance Configuration (1) Obey the special precautions when you work on a gaseous oxygen system (Ref. AMM TASK 35-0000-860-001) . (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) In the cockpit, on the OXYGEN section of overhead panel 21VU: (a) Put a WARNING NOTICE(S) in position to tell persons not to operate the emergency oxygen system. (4) Energize the CIDS system (Ref. AMM TASK 23-73-00-861-001) . (5) On all the emergency oxygen containers: (a) Push the test buttons to the test position.

** ON A/C ALL Subtask 35-23-00-010-075-A B.

Get Access to the Avionics Compartment (1) Open the access doors 812 and 824 (Ref. AMM TASK 52-41-00-010-002) .

Subtask 35-23-00-865-088-A C.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 49VU 49VU 49VU 49VU

DESIGNATION FIN OXYGEN/PASSENGER/ACTUATION 7WR OXYGEN/PASSENGER/ACTUATION 6WR OXYGEN/PASSENGER/ACTUATION 5WR OXYGEN/PASSENGER/ACTUATION 4WR OXYGEN/PASSENGER/CTL AND WARN 3WR OXYGEN/PASSENGER/CTL AND WARN 2WR

LOCATION HA08 HA07 HA06 HA05 HA04 HA03

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton PANEL 49VU

DESIGNATION FIN OXYGEN/PASSENGER/CTL AND WARN 1WR

LOCATION HA02

** ON A/C 201-201, 203-205, 207-207, 209-211, 217-217, 219-220, 226-228, 230-234, 237-237, 239-239, 242-242, 244-250, 350-350 2000VU PRAM 2RX E01 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-211, 213-250, 301-450, 500-600 Subtask 35-23-00-480-060-A D.

Connecting of the Vacuum Source (1) Connect the VACUUM EQUIPMENT 0 TO 1 BAR (15 PSI) to the altitude pressure switch 16WR with the HOSE-ADAPTER,ALTITUDE SWITCH (98A35207599000) .

** ON A/C 212-212 Subtask 35-23-00-480-060-B D.

Connecting of the Vacuum Source (Ref. Fig. Altitude Pressure Switch 16WR SHEET 1) (1) Do not disconnect electrical connection from the altitude pressure switch 16WR (1). (2) Connect the VACUUM EQUIPMENT 0 TO 1 BAR (15 PSI) to the connector (3) of the altitude pressure switch 16WR with the HOSE-ADAPTER,ALTITUDE SWITCH (98A35207599000) (2).

** ON A/C ALL 4.

Procedure

** ON A/C 016-022, 024-091, 112-150, 206-206, 209-209, 215-216, 221-222, 226-228, 230-230, 236-236, 238243, 350-350 PRE SB 35-1068 for A/C 016-022, 024-091, 112-115, 206-206, 209-209, 215-216, 221-222, 226-228, 230-230, 236-236, 238-243 Subtask 35-23-00-040-051-A A.

Functional Test of the Automatic Mask Release (1) Do the test: ACTION 1.On the circuit breaker panel 49VU: · Open the circuit breakers 2WR and 3WR. 2.At the vacuum source: · Slowly decrease the pressure to 14800 ft. (4500 m).

· Slowly increase the pressure to 0 ft. (0 m). 3.On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch.

RESULT

In the cabin: · The doors of all oxygen containers open at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or 228.60 m) to the maximum permitted by the test buttons. On the overhead panel 21VU: · The SYS ON indicator light comes on. On the maintenance panel 50VU: · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION 4.At the electronic rack 103VU: · Remove the SWITCH OFF relay 9WR. · Install a wire between pin A2 and A3 of the relay socket.

RESULT

CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. 5.In the cabin, at the first seat row, close the door of the emergency oxygen container: · Push the door of one emergency oxygen container to the closed position. · Push the door of the related emergency oxygen container, at both sides of the test button, to lock the latch mechanism. · Make sure that the door is flush with the adjacent panels. 6.At the vacuum source: In the cabin, at the first seatrow: · Slowly decrease the pressure to 14800 ft. · The door of the related oxygen container opens (4500 m) and hold it for not less than 30 sec. at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or -228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. In the cabin, at the first seat row: CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXY-

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION GEN CONTAINER IS CORRECTLY INSTALLED.

RESULT

CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. 7.In the cabin, at the first seat row, close the door of the emergency oxygen container: · After approximately 30 sec., push the door of · The door of the emergency oxygen container the related emergency oxygen container to the stays closed. closed position. · Push the door of the related oxygen container, at both sides of the test button, to lock the latch mechanism. · Make sure that the door is flush with the adjacent panels. 8.At the vacuum source: · Slowly increase the pressure to 0 ft. (0 m). 9.On the maintenance panel 50VU: On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch. · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. 10.At the electronic rack 103VU: · Remove the wire from pin A2 and A3 of the relay socket. · Install the SWITCH OFF relay 9WR. · Remove the SWITCH OFF relay 8WR. · Install a wire between pin A2 and A3 of the relay socket. 11.At the vacuum source: In the cabin, at the first seatrow: · Slowly decrease the pressure to 14800 ft. · The door of the related oxygen container opens (4500 m) and hold it for not less than 30 sec. at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or -228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. In the cabin, at the first seatrow: CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT EN-

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION GAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED.

RESULT

CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. 12.In the cabin, at the first seat row, close the door of the emergency oxygen container: · After approximately 30 sec., push the door of · The door of the emergency oxygen container the related emergency oxygen container to the stays closed. closed position. · Push the door of the related emergency oxygen container, at both sides of thetest button, to lock the latch mechanism. · Make sure that the door is flush with the adjacent panels. 13.At the vacuum source: · Slowly increase the pressure to 0 ft. (0 m). 14.On the maintenance panel 50VU: On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch. · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. 15.At the electronic rack 103VU: · Remove the wire from pin A2 and A3 of the relay socket. · Install the SWITCH OFF relay 8WR. 16.At the vacuum source: In the cabin, at the first seatrow: · Slowly decrease the pressure to and hold it at · The door of the related oxygen container opens 14800 ft. (4500 m) for not less than 30 sec. at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or -228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. 17.At the vacuum source: · Slowly increase the pressure to 0 ft. (0 m). 18.On the maintenance panel 50VU: On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch. · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION 19.On the circuit breaker panel 49VU: · Close the circuit breakers 2WR and 3WR.

RESULT

** ON A/C 201-201, 203-205, 207-208, 210-211, 213-214, 217-220, 223-225, 231-235, 237-237, 244-250 PRE SB 35-1068 for A/C 201-201, 203-205, 207-208, 210-211, 213-214, 217-220, 223-225, 233-235 Subtask 35-23-00-040-051-D A.

Functional Test of the Automatic Mask Release NOTE: The pre-recorded announcement is usually recorded by the operator. You can hear the emergency announcement only if it is recorded. (1) Do the test ACTION 1.On the circuit breaker panel 49VU: · Open the circuit breakers 2WR and 3WR. 2.At the vacuum source: · Slowly decrease the pressure to simulate an altitude of 14800 ft. (4500 m).

RESULT

In the cabin: · The doors of all oxygen containers open at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or 228.60 m) to the maximum permitted by the test buttons. · The emergency announcement starts. NOTE: The emergency announcement stops automatically when the recorded announcement is completed. On the overhead panel 21VU: · The SYS ON indicator light comes on.

· Slowly increase the pressure to simulate an altitude of 0 ft. (0 m). 3.On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch.

On the maintenance panel 50VU: · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off.

4.At the electronic rack 103VU: · Remove the SWITCH OFF relay 9WR. · Install a wire between pin A2 and A3 of the relay socket. CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXY-

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION GEN CONTAINER IS CORRECTLY INSTALLED.

RESULT

CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. 5.In the cabin, at the first seat row, close the door of the emergency oxygen container: · Push the door of one emergency oxygen container to the closed position. · Push the door of the emergency oxygen container, at both sides of the test button, to lock the latch mechanism. · Make sure that the door is flush with the adjacent panels. 6.At the vacuum source: In the cabin, at the first seat row: · Slowly decrease the pressure to simulate an · The door of the related oxygen container opens altitude of 14800 ft. (4500 m) and hold it for not at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m less than 30 sec. or -228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. In the cabin: · The emergency announcement starts. NOTE: The emergency announcement stops automatically when the recorded announcenment is completed. In the cabin, at the first seat row: CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENPrint Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION GAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED.

RESULT

7.In the cabin, at the first seat row, close the door of the emergency oxygen container: · After approximately 30 sec., push the door of · The door of the emergency oxygen container the related emergency oxygen container to the stays closed. closed position. · Push the door of the related emergency oxygen container, at both sides of the test button, to lock the latch mechanism. · Make sure the door is flush with the adjacent panels. 8.At the vacuum source: · Slowly increase the pressure to simulate an altitude of 0 ft. (0 m). 9.On the maintenance panel 50VU: On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch. · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. 10.At the electronic rack 103VU: · Remove the wire from pin A2 and A3 of the relay socket. · Install the SWITCH OFF relay 9WR. · Remove the SWITCH OFF relay 8WR. · Install a wire between pin A2 and A3 of the relay socket. 11.At the vacuum source: In the cabin, at the first seat row: · Slowly decrease the pressure to simulate an · The door of the related oxygen container opens altitude of 14800 ft. (4500 m) and hold it for not at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m less than 30 sec. or -228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. In the cabin: · The emergency announcement starts. NOTE: The emergency announcement stops automatically when the recorded announcement is completed. In the cabin, at the first seat row: CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED.

RESULT

CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. 12.In the cabin, at the first seat row, close the door of the emergency oxygen container: · After approximately 30 sec., push the door of · The door of the emergency oxygen container the related emergency oxygen container to the stays closed. closed position. · Push the door of the related emergency oxygen container, at both sides of the test button, to lock the latch mechanism. · Make sure that the door is flush with the adjacent panels. 13.At the vacuum source: · Slowly increase the pressure to simulate an altitude of 0 ft. (0 m). 14.On the maintenance panel 50VU: On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch. · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. 15.At the electronic rack 103VU: · Remove the wire from pin A2 and A3 of the relay socket. · Install the SWITCH OFF relay 8WR. 16.At the vacuum source: In the cabin, at the first seat row: · Slowly decrease the pressure to simulate an · The door of the related oxygen container opens altitude of 14800 ft. (4500 m) and hold it for not at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m less than 30 sec. or -228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. In the cabin: · The emergency announcement starts. NOTE: The emergency announcement stops automatically when the recorded announcement is completed. 17.At the vacuum source:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 12 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION · Slowly increase the pressure to simulate an altitude of 0 ft. (0 m). 18.On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch.

RESULT

On the maintenance panel 50VU: · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off.

19.On the circuit breaker panel 49VU: · Close the circuit breakers 2WR and 3WR.

** ON A/C 212-212 PRE SB 35-1068 for A/C 212-212 Subtask 35-23-00-040-051-E A.

Functional Test of the Automatic Mask Release ACTION 1.On the circuit breaker panel 49VU: · Open the circuit breakers 2WR and 3WR. 2.On the overhead panel 21VU: · Push the HIGH ALT SWITCH ON pushbutton switch. 3.At the vacuum source: · Slowly decrease the pressure to simulate an altitude of 16800 ft. (5120 m).

RESULT

On the overhead panel 21VU: · The ON legend in the HIGH ALT SWITCH ON pushbutton switch comes on. In the cabin: · The doors of all oxygen containers open at 16000 +250 ft. or -750 ft. (4876.71 +76.20 m or -228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on.

· Slowly increase the pressure to simulate an altitude of 0 ft. (0 m). 4.On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch.

On the maintenance panel 50VU: · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. 5.On the overhead panel 21VU: On the overhead panel 21VU: · Push to reset the HIGH ALT SWITCH ON push- · The ON legend in the HIGH ALT SWITCH ON button switch. pushbutton switch goes off. 6.At the electronic rack 103VU: · Remove the SWITCH OFF relay 9WR. · Install a wire between pin A2 and A3 of the relay socket. CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASPrint Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 13 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION ILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED.

RESULT

CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. 7.In the cabin at the first seat row, close the door of the emrgency oxygen container: · Push the door of one emergency oxygen container to the closed position. · Push the door of the related emergency oxygen container, at both sides of the test button, to lock the latch mechanism. · Make sure that the door is flush with the adjacent panels. 8.At the vacuum source: In the cabin, at the first seatrow: · Slowly decrease the pressure to simulate an alti- · The door of the related oxygen container opens at tude of 14800 ft. (4500 m) and hold it for not less 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or than 30 sec. 228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. In the cabin, at the first seat row: CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. 9.In the cabin, at the first seat row, close the door of the emergency oxygen conatainer:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 14 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION RESULT · After approximately 30 sec., push the door of the · The door of the emergency oxygen container stays related emergency oxygen container to the close closed. position. · Push the door of the related oxygen container, at both sides of the test button, to lock the latch mechanism. · Make sure that the door is flush with the adjacent panels. 10.At the vacuum source: · Slowly increase the pressure to simulate an altitude of 0 ft. (0 m). 11.On the maintenance panel 50VU: On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch. · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. 12.At the electronic rack 103VU: · Remove the wire from pin A2 and A3 of the relay socket. · Install the SWITCH OFF relay 9WR. · Remove the SWITCH OFF relay 8WR. · Install a wire between pin A2 and A3 of the relay socket. 13.At the vacuum source: In the cabin, at the first seatrow: · Slowly decrease the pressure to simulate an alti- · The door of the related oxygen container opens at tude of 14800 ft. (4500 m) and hold it for not less 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or than 30 sec. 228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. In the cabin, at the first seat row: CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 15 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION RESULT 14.In the cabin, at the first seat row, close the door of the emergency oxygen container: · After approximately 30 sec., push the door of · The door of the emergency oxygen container stays the related emergency oxygen container to the closed. closed position. · Push the door of the related emergency oxygen container, at both sides of the test button, to lock the latch mechanism. · Make sure that the door is flushed with the adjacent panels. 15.At the vacuum source: · Slowly increase the pressure to simulate an altitude of 0 ft. (0 m). 16.On the maintenance panel 50VU: On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch. · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. 17.At the electronic rack 103VU: · Remove the wire from pin A2 and A3 of the relay socket. · Install the SWITCH OFF relay 8WR. 18.At the vacuum source: In the cabin, at the first seatrow: · Slowly decrease the pressure to simulate an alti- · The door of the related oxygen container opens at tude of 14800 ft. (4500 m) and hold it for not less 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or than 30 sec. 228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. 19.At the vacuum source: · Slowly increase the pressure to simulate an altitude of 0 ft. (0 m). 20.On the maintenance panel 50VU: On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch. · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. 21.On the circuit breaker panel 49VU: · Close the circuit breakers 2WR and 3WR.

** ON A/C 092-100, 401-450 POST SB 35-1068 for A/C 112-113, 115-115, 236-236, 238-238, 241-241 Subtask 35-23-00-040-051-J A.

Functional Test of the Automatic Mask Release (1) Do the test: ACTION 1.On the circuit breaker panel 49VU:

RESULT

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 16 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION · Open the circuit breakers 2WR and 3WR. 2.At the vacuum source: · Slowly decrease the pressure to 14800 ft. (4500 m).

· Slowly increase the pressure to 0 ft. (0 m). 3.On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch.

RESULT In the cabin: · The doors of all oxygen containers open at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or 228.60 m) to the maximum permitted by the test buttons. On the overhead panel 21VU: · The SYS ON indicator light comes on. On the Engine/Warning Display (EWD): · The OXY PAX ON indication comes on. On the maintenance panel 50VU: · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. On the EWD: · The OXY PAX ON indicator goes off.

4.At the electronic rack 103VU: · Remove the SWITCH OFF relay 9WR. · Install a wire between pin A2 and A3 of the relay socket. CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. 5.In the cabin, at the first seat row, close the door of the emergency oxygen container: · Push the door of one emergency oxygen container to the closed position.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 17 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION RESULT · Push the door of the related emergency oxygen container, at both sides of the test button, to lock the latch mechanism. · Make sure that the door is flush with the adjacent panels. 6.At the vacuum source: In the cabin, at the first seatrow: · Slowly decrease the pressure to 14800 ft. · The door of the related oxygen container opens (4500 m) and hold it for not less than 30 sec. at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or -228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. On the EWD: · The OXY PAX ON indicator comes on. In the cabin, at the first seat row: CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. 7.In the cabin, at the first seat row, close the door of the emergency oxygen container: · After approximately 30 sec., push the door of · The door of the emergency oxygen container the related emergency oxygen container to the stays closed. closed position. · Push the door of the related oxygen container, at both sides of the test button, to lock the latch mechanism. · Make sure that the door is flush with the adjacent panels. 8.At the vacuum source: · Slowly increase the pressure to 0 ft. (0 m). 9.On the maintenance panel 50VU: On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch. · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 18 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION

RESULT · The SYS ON indicator light goes off. On the EWD: · The OXY PAX ON indicator goes off.

10.At the electronic rack 103VU: · Remove the wire from pin A2 and A3 of the relay socket. · Install the SWITCH OFF relay 9WR. · Remove the SWITCH OFF relay 8WR. · Install a wire between pin A2 and A3 of the relay socket. 11.At the vacuum source: In the cabin, at the first seatrow: · Slowly decrease the pressure to 14800 ft. · The door of the related oxygen container opens (4500 m) and hold it for not less than 30 sec. at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or -228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. On the EWD: · The OXY PAX ON indicator comes on. In the cabin, at the first seatrow: CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. 12.In the cabin, at the first seat row, close the door of the emergency oxygen container: · After approximately 30 sec., push the door of · The door of the emergency oxygen container the related emergency oxygen container to the stays closed. closed position. · Push the door of the related emergency oxygen container, at both sides of thetest button, to lock the latch mechanism. · Make sure that the door is flush with the adjacent panels. 13.At the vacuum source:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 19 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION · Slowly increase the pressure to 0 ft. (0 m). 14.On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch.

RESULT On the maintenance panel 50VU: · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. On the EWD: · The OXY PAX ON indicator goes off.

15.At the electronic rack 103VU: · Remove the wire from pin A2 and A3 of the relay socket. · Install the SWITCH OFF relay 8WR. 16.At the vacuum source: In the cabin, at the first seatrow: · Slowly decrease the pressure to and hold it at · The door of the related oxygen container opens 14800 ft. (4500 m) for not less than 30 sec. at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or -228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. On the EWD: · The OXY PAX ON indicator comes on. 17.At the vacuum source: · Slowly increase the pressure to 0 ft. (0 m). 18.On the maintenance panel 50VU: On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch. · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. On the EWD: · The OXY PAX ON indicator goes off. 19.On the circuit breaker panel 49VU: · Close the circuit breakers 2WR and 3WR.

** ON A/C 229-229, 301-349, 351-400, 500-600 POST SB 35-1068 for A/C 016-022, 024-091, 114-114, 201-201, 203-211, 213-228, 230-230, 233-235, 239-240, 242-243 EMB SB 23-1530 for A/C 229-229 Subtask 35-23-00-040-051-L A.

Functional Test of the Automatic Mask Release NOTE: The pre-recorded announcement is usually recorded by the operator. You can hear the emergency announcement only if it is recorded. (1) Do the test

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 20 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION 1.On the circuit breaker panel 49VU: · Open the circuit breakers 2WR and 3WR. 2.At the vacuum source: · Slowly decrease the pressure to simulate an altitude of 14800 ft. (4500 m).

RESULT

In the cabin: · The doors of all oxygen containers open at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or 228.60 m) to the maximum permitted by the test buttons. · The emergency announcement starts. NOTE: The emergency announcement stops automatically when the recorded announcement is completed. On the overhead panel 21VU: · The SYS ON indicator light comes on. On the Engine/Warning Dispaly (EWD): · The OXY PAX ON indicator comes on.

· Slowly increase the pressure to simulate an altitude of 0 ft. (0 m). 3.On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch.

On the maintenance panel 50VU: · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. On the EWD: · The OXY PAX ON indicator goes off.

4.At the electronic rack 103VU: · Remove the SWITCH OFF relay 9WR. · Install a wire between pin A2 and A3 of the relay socket. CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXY-

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 21 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION GEN CONTAINER IS CORRECTLY INSTALLED.

RESULT

5.In the cabin, at the first seat row, close the door of the emergency oxygen container: · Push the door of one emergency oxygen container to the closed position. · Push the door of the emergency oxygen container, at both sides of the test button, to lock the latch mechanism. · Make sure that the door is flush with the adjacent panels. 6.At the vacuum source: In the cabin, at the first seat row: · Slowly decrease the pressure to simulate an · The door of the related oxygen container opens altitude of 14800 ft. (4500 m) and hold it for not at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m less than 30 sec. or -228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. On the EWD: · The OXY PAX ON indicator comes on. In the cabin: · The emergency announcement starts. NOTE: The emergency announcement stops automatically when the recorded announcenment is completed. In the cabin, at the first seat row: CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. 7.In the cabin, at the first seat row, close the door of the emergency oxygen container:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 22 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION RESULT · After approximately 30 sec., push the door of · The door of the emergency oxygen container the related emergency oxygen container to the stays closed. closed position. · Push the door of the related emergency oxygen container, at both sides of the test button, to lock the latch mechanism. · Make sure the door is flush with the adjacent panels. 8.At the vacuum source: · Slowly increase the pressure to simulate an altitude of 0 ft. (0 m). 9.On the maintenance panel 50VU: On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch. · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. On the EWD: · The OXY PAX ON indicator goes off. 10.At the electronic rack 103VU: · Remove the wire from pin A2 and A3 of the relay socket. · Install the SWITCH OFF relay 9WR. · Remove the SWITCH OFF relay 8WR. · Install a wire between pin A2 and A3 of the relay socket. 11.At the vacuum source: In the cabin, at the first seat row: · Slowly decrease the pressure to simulate an · The door of the related oxygen container opens altitude of 14800 ft. (4500 m) and hold it for not at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m less than 30 sec. or -228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. On the EWD: · The OXY PAX ON indicator comes on. In the cabin: · The emergency announcement starts. NOTE: The emergency announcement stops automatically when the recorded announcement is completed. In the cabin, at the first seat row: CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXY-

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 23 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION GEN CONTAINER IS CORRECTLY INSTALLED.

RESULT

CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. 12.In the cabin, at the first seat row, close the door of the emergency oxygen container: · After approximately 30 sec., push the door of · The door of the emergency oxygen container the related emergency oxygen container to the stays closed. closed position. · Push the door of the related emergency oxygen container, at both sides of the test button, to lock the latch mechanism. · Make sure that the door is flush with the adjacent panels. 13.At the vacuum source: · Slowly increase the pressure to simulate an altitude of 0 ft. (0 m). 14.On the maintenance panel 50VU: On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch. · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. On the EWD: · The OXY PAX ON indicator goes off. 15.At the electronic rack 103VU: · Remove the wire from pin A2 and A3 of the relay socket. · Install the SWITCH OFF relay 8WR. 16.At the vacuum source: In the cabin, at the first seat row: · Slowly decrease the pressure to simulate an · The door of the related oxygen container opens altitude of 14800 ft. (4500 m) and hold it for not at 14000 +250 ft. or -750 ft. (4267.12 +76.20 m less than 30 sec. or -228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. On the EWD: · The OXY PAX ON indicator comes on. In the cabin: · The emergency announcement starts.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 24 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION

RESULT NOTE: The emergency announcement stops automatically when the recorded announcement is completed.

17.At the vacuum source: · Slowly increase the pressure to simulate an altitude of 0 ft. (0 m). 18.On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch.

On the maintenance panel 50VU: · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. On the EWD: · The OXY PAX ON indicator goes off.

19.On the circuit breaker panel 49VU: · Close the circuit breakers 2WR and 3WR.

** ON A/C POST SB 35-1068 for A/C 212-212 Subtask 35-23-00-040-051-M A.

Functional Test of the Automatic Mask Release ACTION 1.On the circuit breaker panel 49VU: · Open the circuit breakers 2WR and 3WR. 2.On the overhead panel 21VU: · Push the HIGH ALT SWITCH ON pushbutton switch. 3.At the vacuum source: · Slowly decrease the pressure to simulate an altitude of 16800 ft. (5120 m).

· Slowly increase the pressure to simulate an altitude of 0 ft. (0 m). 4.On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch.

5.On the overhead panel 21VU:

RESULT

On the overhead panel 21VU: · The ON legend in the HIGH ALT SWITCH ON pushbutton switch comes on. In the cabin: · The doors of all oxygen containers open at 16000 +250 ft. or -750 ft. (4876.71 +76.20 m or -228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. On the Engine/Warning Display (EWD): · The OXY PAX ON indicator comes on.

On the maintenance panel 50VU: · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. On the EWD: · The OXY PAX ON indicator goes off. On the overhead panel 21VU:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 25 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION RESULT · Push to reset the HIGH ALT SWITCH ON push- · The ON legend in the HIGH ALT SWITCH ON button switch. pushbutton switch goes off. 6.At the electronic rack 103VU: · Remove the SWITCH OFF relay 9WR. · Install a wire between pin A2 and A3 of the relay socket. CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. 7.In the cabin at the first seat row, close the door of the emrgency oxygen container: · Push the door of one emergency oxygen container to the closed position. · Push the door of the related emergency oxygen container, at both sides of the test button, to lock the latch mechanism. · Make sure that the door is flush with the adjacent panels. 8.At the vacuum source: In the cabin, at the first seatrow: · Slowly decrease the pressure to simulate an alti- · The door of the related oxygen container opens at tude of 14800 ft. (4500 m) and hold it for not less 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or than 30 sec. 228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. On the EWD: · The OXY PAX ON indicator comes on. In the cabin, at the first seat row: CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 26 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED.

RESULT

CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. 9.In the cabin, at the first seat row, close the door of the emergency oxygen conatainer: · After approximately 30 sec., push the door of the · The door of the emergency oxygen container stays related emergency oxygen container to the close closed. position. · Push the door of the related oxygen container, at both sides of the test button, to lock the latch mechanism. · Make sure that the door is flush with the adjacent panels. 10.At the vacuum source: · Slowly increase the pressure to simulate an altitude of 0 ft. (0 m). 11.On the maintenance panel 50VU: On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch. · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. On the EWD: · The OXY PAX ON indicator goes off. 12.At the electronic rack 103VU: · Remove the wire from pin A2 and A3 of the relay socket. · Install the SWITCH OFF relay 9WR. · Remove the SWITCH OFF relay 8WR. · Install a wire between pin A2 and A3 of the relay socket. 13.At the vacuum source: In the cabin, at the first seatrow: · Slowly decrease the pressure to simulate an alti- · The door of the related oxygen container opens at tude of 14800 ft. (4500 m) and hold it for not less 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or than 30 sec. 228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. On the EWD: · The OXY PAX ON indicator comes on. In the cabin, at the first seat row: CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 27 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED.

RESULT

CAU- DO NOT USE TOO MUCH FORCE TO TION: CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. 14.In the cabin, at the first seat row, close the door of the emergency oxygen container: · After approximately 30 sec., push the door of · The door of the emergency oxygen container stays the related emergency oxygen container to the closed. closed position. · Push the door of the related emergency oxygen container, at both sides of the test button, to lock the latch mechanism. · Make sure that the door is flushed with the adjacent panels. 15.At the vacuum source: · Slowly increase the pressure to simulate an altitude of 0 ft. (0 m). 16.On the maintenance panel 50VU: On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch. · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. On the EWD: · The OXY PAX ON indicator goes off. 17.At the electronic rack 103VU: · Remove the wire from pin A2 and A3 of the relay socket. · Install the SWITCH OFF relay 8WR. 18.At the vacuum source: In the cabin, at the first seatrow: · Slowly decrease the pressure to simulate an alti- · The door of the related oxygen container opens at tude of 14800 ft. (4500 m) and hold it for not less 14000 +250 ft. or -750 ft. (4267.12 +76.20 m or than 30 sec. 228.60 m). On the overhead panel 21VU: · The SYS ON indicator light comes on. On the EWD: · The OXY PAX ON indicator comes on. 19.At the vacuum source: Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 28 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton ACTION · Slowly increase the pressure to simulate an altitude of 0 ft. (0 m). 20.On the maintenance panel 50VU: · Push the TMR RESET pushbutton switch.

RESULT

On the maintenance panel 50VU: · The ON indicator light in the TMR RESET pushbutton switch comes on while the pushbutton is pushed. On the overhead panel 21VU: · The SYS ON indicator light goes off. On the EWD: · The OXY PAX ON indicator goes off.

21.On the circuit breaker panel 49VU: · Close the circuit breakers 2WR and 3WR.

** ON A/C ALL 5.

Close-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-211, 213-250, 301-450, 500-600 Subtask 35-23-00-080-060-A A.

Disconnecting of the Vacuum Source (1) Disconnect the VACUUM EQUIPMENT 0 TO 1 BAR (15 PSI) and the HOSE-ADAPTER,ALTITUDE SWITCH (98A35207599000) from the altitude pressure switch 16WR.

** ON A/C 212-212 Subtask 35-23-00-080-060-B A.

Disconnecting of the Vacuum Source (Ref. Fig. Altitude Pressure Switch 16WR SHEET 1) (1) Disconnect the VACUUM EQUIPMENT 0 TO 1 BAR (15 PSI) and the HOSE-ADAPTER,ALTITUDE SWITCH (98A35207599000) (2) from the connector (3) of the altitude pressure switch 16WR (1).

** ON A/C ALL Subtask 35-23-00-410-074-A B.

Close Access (1) Make sure that the switch guard is in position on the MASK MAN ON pushbutton switch. (2) If not installed, install a LABEL - ADHESIVE, INOP: (a) On the overhead panel, on the control panel 21VU, install the LABEL - ADHESIVE, INOP adjacent to the MASK MAN ON P/BSW 14WR. (3) On all emergency oxygen containers: (a) Close the doors of the emergency oxygen containers: CAUTION: DO NOT USE TOO MUCH FORCE TO CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. 1

Push the door of the emergency oxygen containers to the closed position.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 29 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-008-A - Check of the AUTO control function of the MASK MAN ON pushbutton

2

Push the door of the emergency oxygen containers, at both sides of the test button, to lock the latch mechanism.

3

Make sure that the doors are flush with the adjacent panels.

4

Do step (b) and/or step (c) as applicable.

(b) Turn the test buttons 90 degrees to normal position. (c) Push the test buttons back to the normal position and let them retract into their containers. NOTE: Spring tension retracts the test buttons when they are in the normal position. (4) Make sure that the work area is clean and clear of tools and other items. (5) Close the access doors 812 and 824 (Ref. AMM TASK 52-41-00-410-002) . (6) Make an applicable entry in the logbook. Subtask 35-23-00-860-078-A C.

Aircraft Maintenance Configuration (1) In the cockpit, on the OXYGEN section of overhead panel 21VU: (a) Remove the WARNING NOTICE(S). (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 30 of 30

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-802-A - Check of the MANUAL Control Function of the MASK MAN ON pushbutton

** ON A/C ALL TASK 35-23-00-040-802-A Check of the MANUAL Control Function of the MASK MAN ON pushbutton WARNING:

KEEP ALL HYDROCARBONS (FUELS, LUBRICANTS, ETC.) AWAY FROM ALL SOURCE OF OXYGEN. OXYGEN BECOMES EXPLOSIVE WHEN IT TOUCHES HYDROCARBONS.

WARNING:

CLEAN THE TOOLS AND MAKE SURE YOUR HANDS ARE CLEAN TO PREVENT CONTAMINATION OF THE OXYGEN SYSTEM.

Task Summary MMEL or CDL Ref MMEL 35-01-01-32A

Access NO

Test NO

Specific Tools NO

Mhr 02.0

E/T 02.0

Nb Men 2

1.

Reason for the Job MMEL 35-01-01-32A AUTO Control of the MASK MAN ON pb Do this task to make sure that the passenger oxygen system starts operation when the MASK MAN ON pushbutton is pushed.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION 1 LABEL - ADHESIVE, "INOP"

Work Zones and Access Panels ZONE/ACCESS 120 200

ZONE DESCRIPTION AVIONICS COMPARTMENT UPPER HALF FUSELAGE

C. Referenced Information REFERENCE (Ref. 21-31-00-710-002-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 35-00-00-860-001-A). (Ref. 23-32-00-00).

DESIGNATION Operational Test of the Pressure Control and Monitoring Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Special Precautions When Working on a Gaseous Oxygen System ANNOUNCEMENT - MUSIC TAPE REPRODUCER SYSTEM - DESCRIPTION AND OPERATION

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-802-A - Check of the MANUAL Control Function of the MASK MAN ON pushbutton

3.

Job Set-up Subtask 35-23-00-860-075-A A.

Aircraft Maintenance Configuration (1) Obey the special precautions when you work on a gaseous oxygen system (Ref. AMM TASK 35-0000-860-001) . (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (3) In the cockpit, on the OXYGEN section of overhead panel 21VU: (a) Put a WARNING NOTICE(S) in position to tell persons not to operate the emergency oxygen system. (4) On all of the emergency oxygen containers, set the test button to the TEST position.

Subtask 35-23-00-865-091-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 49VU 49VU 49VU 49VU 49VU

DESIGNATION FIN OXYGEN/PASSENGER/ACTUATION 7WR OXYGEN/PASSENGER/ACTUATION 6WR OXYGEN/PASSENGER/ACTUATION 5WR OXYGEN/PASSENGER/ACTUATION 4WR OXYGEN/PASSENGER/CTL AND WARN 3WR OXYGEN/PASSENGER/CTL AND WARN 2WR OXYGEN/PASSENGER/CTL AND WARN 1WR

LOCATION HA08 HA07 HA06 HA05 HA04 HA03 HA02

** ON A/C 201-201, 203-205, 207-207, 209-211, 217-217, 219-220, 226-228, 230-234, 237-237, 239-239, 242-242, 244-250, 350-350 2000VU PRAM 2RX E01 ** ON A/C ALL 4.

Procedure

** ON A/C 016-022, 024-091, 112-150, 201-201, 203-250, 350-350 PRE SB 35-1068 for A/C 016-022, 024-091, 112-115, 201-201, 203-230, 233-236, 238-243 Subtask 35-23-00-710-059-A A.

Operational Test of the Manual Mask Release and Cabin Pressure Controllers (1) Do the operational test of the manual mask release: NOTE: If the PRAM or I-PRAM is installed, the operator can record an emergency announcement. You can hear the emergency announcement through the passenger address system only if it is recorded. Additional information can be found in Para. System Description (Ref. AMM D/ O 23-32-00-00) .

ACTION RESULT 1.In the cockpit on the OXYGEN section of the In the cabin: overhead panel 21VU: · The door of all the emergency oxygen containers · Lift the switch guard and push the MASK MAN open in all areas of the cabin. ON pushbutton switch.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-802-A - Check of the MANUAL Control Function of the MASK MAN ON pushbutton ACTION

RESULT In the cockpit on the OXYGEN section of the overhead panel 21VU: · The SYS ON light comes on. On the passenger address system: · The emergency announcement starts (if installed). NOTE: The emergency announcement stops automatically when the recorded announcement is completed.

2.In the cockpit on the OXYGEN section of the In the cockpit on the OXYGEN section of the overmaintenance panel 50VU: head panel 21VU: · After 15 seconds push the TMR RESET push- · The SYS ON light goes off. button switch. In the cockpit on the OXYGEN section of the maintenance panel 50VU: · The ON light on the TMR RESET pushbutton switch comes on for a short time and goes off again. (2) Do the operational test of the cabin pressure controller (Ref. AMM TASK 21-31-00-710-002) . ** ON A/C 092-100, 301-349, 351-450, 500-600 POST SB 35-1068 for A/C 016-022, 024-091, 112-115, 201-201, 203-230, 233-236, 238-243 Subtask 35-23-00-710-059-D A.

Operational Test of the Manual Mask Release and Cabin Pressure Controllers (1) Do the operational test of the manual mask release: NOTE: If the PRAM or I-PRAM is installed, the operator can record an emergency announcement. You can hear the emergency announcement through the passenger address system only if it is recorded. Additional information can be found in Para. System Description (Ref. AMM D/ O 23-32-00-00) .

ACTION RESULT 1.In the cockpit on the OXYGEN section of the In the cabin: overhead panel 21VU: · The door of all the emergency oxygen containers · Lift the switch guard and push the MASK MAN open in all areas of the cabin. ON pushbutton switch. In the cockpit on the OXYGEN section of the overhead panel 21VU: · The SYS ON light comes on. In the cockpit on the Engine/Warning Display (EWD): · The OXY PAX ON indicator comes on. On the passenger address system: · The emergency announcement starts (if installed).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-802-A - Check of the MANUAL Control Function of the MASK MAN ON pushbutton ACTION

RESULT NOTE: The emergency announcement stops automatically when the recorded announcement is completed.

2.In the cockpit on the OXYGEN section of the In the cockpit on the OXYGEN section of the overmaintenance panel 50VU: head panel 21VU: · After 15 seconds push the TMR RESET push- · The SYS ON light goes off. button switch. On the EWD: · The OXY PAX ON indicator goes of. In the cockpit on the OXYGEN section of the maintenance panel 50VU: · The ON light on the TMR RESET pushbutton switch comes on for a short time and goes off again. (2) Do the operational test of the cabin pressure controller (Ref. AMM TASK 21-31-00-710-002) . ** ON A/C ALL 5.

Close-up Subtask 35-23-00-860-076-A A.

Aircraft Maintenance Configuration (1) Make sure that the switch guard is in position over the MASK MAN ON pushbutton switch. (2) Close all the door of the emergency oxygen containers: CAUTION: DO NOT USE TOO MUCH FORCE TO CLOSE THE EMERGENCY OXYGEN CONTAINER. IF YOU USE TOO MUCH FORCE, YOU CAN CAUSE DAMAGE TO THE LATCH MECHANISM. IF THE LATCH MECHANISM DOES NOT ENGAGE EASILY, MAKE SURE THAT THE EQUIPMENT IN THE EMERGENCY OXYGEN CONTAINER IS CORRECTLY INSTALLED. (a) Push the door of the emergency oxygen containers to the closed position. (b) Push the door of the emergency oxygen containers, at both sides of the test button, to lock the latch mechanism. (c) Make sure that the doors of the emergency oxygen container are flush with the adjacent panels. (3) Turn all the test buttons to the normal position and release them. NOTE: Spring tension retracts the test buttons when they are in the normal position. (4) Install a LABEL - ADHESIVE, "INOP" on the altitude switch 16WR . (5) Make an applicable entry in a logbook. (6) In the cockpit, on the OXYGEN section of overhead panel 21VU: (a) Remove the WARNING NOTICE(S). (7) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 35-23-00-040-802-A - Check of the MANUAL Control Function of the MASK MAN ON pushbutton

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 TASK 36-11-00-040-001-A Deactivation of the Bleed Pressure Regulator Valve 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.

FIN : 4001HA , 1000EM1 , 1000EM2 Task Summary MMEL or CDL Ref MMEL 36-11-02A

Access YES

1.

Reason for the Job MMEL 36-11-02A Engine Bleed Valve (PRV)

2

Job Set-up Information A.

Test YES

Mhr 00.4

E/T 00.4

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific

QTY AR AR AR 1

No specific

B.

Specific Tools NO

DESIGNATION ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S) WRENCH - HEXAGONAL Torque wrench: range to between 0.4 and 0.6 m.daN (35.40 and 53.10 lbf.in) Torque wrench: range to between 0.6 and 0.7 m.daN (53.10 and 61.95 lbf.in)

Work Zones and Access Panels ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 437AL, 438AR, 451AL

ZONE DESCRIPTION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 452AR ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 FOR 1000EM2 (ENGINE-2) 447AL, 448AR, 461AL

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

ZONE/ACCESS

ZONE DESCRIPTION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 462AR ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 36-22-00-790-001-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure Leak Check on all the Bleed Air Ducts and Packs Components

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 71-13-00-010-010-A). Opening of the Fan Cowls 437AL(447AL),438AR(448AR) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 71-13-00-010-040-B). Opening of the Fan Cowl Doors ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 71-13-00-410-010-A). Closing of the Fan Cowls 437AL(447AL),438AR(448AR) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 71-13-00-410-040-B). Closing of the Fan Cowl Doors ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 78-30-00-040-012-A). Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for Ground Maintenance ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 78-30-00-081-041-B). Make the Thrust Reverser Serviceable after Maintenance ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 78-30-00-440-012-A). Re-activation of the Thrust Reverser Hydraulic Control Unit (HCU) after Ground Maintenance ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 78-30-00-481-041-B). Make the Thrust Reverser Unserviceable for Maintenance

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

REFERENCE

DESIGNATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 78-32-00-010-010-A). Opening of the Thrust Reverser Halves (Ref. 78-32-00-410-010-A). Closing of the Thrust Reverser Halves ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 78-36-00-010-040-B). Opening of the Thrust Reverser Doors (Ref. 78-36-00-410-040-B). Closing of the Thrust Reverser Doors (Ref. 31-37-73-00). AIDS - ENGINE REPORTS - DESCRIPTION AND OPERATION ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 31-37-73-00-01). AIDS - ENGINE REPORTS - DESCRIPTION AND OPERATION ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 BLEED page of the ECAM Display Unit SHEET 1 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Bleed-Pressure Regulator Valve P/N 6774B02 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Bleed-Pressure Regulator Valve P/N 6774B02 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Bleed-Pressure Regulator Valve ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Bleed-Pressure Regulator Valve ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Bleed-Pressure Regulator Valve P/N 6714D07 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Bleed-Pressure Regulator Valve P/N 6714D07 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Bleed-Pressure Regulator Valve P/N 6774B03 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Bleed-Pressure Regulator Valve P/N 6774B03 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Bleed-Pressure Regulator Valve P/N 6774E ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Bleed-Pressure Regulator Valve P/N 6774E

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

REFERENCE

DESIGNATION

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Bleed-Pressure Regulator Valve P/N 6774G ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Bleed-Pressure Regulator Valve P/N 6774G ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Bleed-Pressure Regulator Valve P/N 6774F ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Bleed-Pressure Regulator Valve P/N 6774F

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

A

4VU

BLEED

200°C LO

200°C HI

ANTI ICE 30PSI 205°C

LO

HI ANTI ICE

GND

30PSI 205°C

APU

1

2

TAT+19°C SAT+18°C

HP

HP

23H56

IP G.W.60300KG C.G.28 1

°°

IP

LOWER ECAM DISPLAY UNIT

A N_MM_361100_4_ABM0_01_01

Figure 36-11-00-991-03300-00-A / SHEET 1/1 - BLEED page of the ECAM Display Unit ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

A

BLEED-PRESSURE REGULATOR VALVE

B

A N_MM_361100_4_BBM0_01_02

Figure 36-11-00-991-11700-00-A / SHEET 1/2 - Bleed-Pressure Regulator Valve P/N 6774B02 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

2

1

C

B

CLOSED

OPEN

C VISUAL INDICATOR N_MM_361100_4_BBM0_02_00

Figure 36-11-00-991-11700-00-A / SHEET 2/2 - Bleed-Pressure Regulator Valve P/N 6774B02 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

A

B BLEED-PRESSURE REGULATOR VALVE

A N_MM_361100_4_BRM0_01_00

Figure 36-11-00-991-11700-00-B / SHEET 1/2 - Bleed-Pressure Regulator Valve P/N 6774B02 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

2

1

C

B

CLOSED

OPEN

C VISUAL INDICATOR N_MM_361100_4_BRM0_02_00

Figure 36-11-00-991-11700-00-B / SHEET 2/2 - Bleed-Pressure Regulator Valve P/N 6774B02 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

A

BLEED-PRESSURE REGULATOR VALVE

B

A N_MM_361100_4_AAM0_01_03

Figure 36-11-00-991-00100-00-A / SHEET 1/2 - Bleed-Pressure Regulator Valve ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

2 1

C

B

CLOSED

OPEN

C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_AAM0_02_00

Figure 36-11-00-991-00100-00-A / SHEET 2/2 - Bleed-Pressure Regulator Valve ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

A

B BLEED-PRESSURE REGULATOR VALVE

A N_MM_361100_4_AEM0_01_00

Figure 36-11-00-991-00100-00-B / SHEET 1/2 - Bleed-Pressure Regulator Valve ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 12 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

2 1

C

B

CLOSED

OPEN

C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_AEM0_02_00

Figure 36-11-00-991-00100-00-B / SHEET 2/2 - Bleed-Pressure Regulator Valve ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 13 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

A

BLEED-PRESSURE REGULATOR VALVE

B

A N_MM_361100_4_BCM0_01_02

Figure 36-11-00-991-11900-00-A / SHEET 1/2 - Bleed-Pressure Regulator Valve P/N 6714D07 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 14 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

2

1

C

B

CLOSED

OPEN

C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_BCM0_02_00

Figure 36-11-00-991-11900-00-A / SHEET 2/2 - Bleed-Pressure Regulator Valve P/N 6714D07 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 15 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

A

B BLEED-PRESSURE REGULATOR VALVE

A N_MM_361100_4_BZM0_01_00

Figure 36-11-00-991-11900-00-B / SHEET 1/2 - Bleed-Pressure Regulator Valve P/N 6714D07 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 16 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

2

1

C

B CLOSED

OPEN

C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_BZM0_02_00

Figure 36-11-00-991-11900-00-B / SHEET 2/2 - Bleed-Pressure Regulator Valve P/N 6714D07 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 17 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

A

BLEED-PRESSURE REGULATOR VALVE

B

A N_MM_361100_4_BAM0_01_02

Figure 36-11-00-991-11800-00-A / SHEET 1/2 - Bleed-Pressure Regulator Valve P/N 6774B03 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 18 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

2

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C

B

CLOSED

OPEN

C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_BAM0_02_00

Figure 36-11-00-991-11800-00-A / SHEET 2/2 - Bleed-Pressure Regulator Valve P/N 6774B03 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 19 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

A

B BLEED-PRESSURE REGULATOR VALVE

A N_MM_361100_4_BAX0_01_00

Figure 36-11-00-991-11800-00-B / SHEET 1/2 - Bleed-Pressure Regulator Valve P/N 6774B03 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 20 of 40

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2

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C

B CLOSED

OPEN

C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_BAX0_02_00

Figure 36-11-00-991-11800-00-B / SHEET 2/2 - Bleed-Pressure Regulator Valve P/N 6774B03 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

A

BLEED-PRESSURE REGULATOR VALVE

B

A N_MM_361100_4_AAR0_01_04

Figure 36-11-00-991-12100-00-A / SHEET 1/2 - Bleed-Pressure Regulator Valve P/N 6774E ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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3 2 1

C

CLOSED

OPEN

B

C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_AAR0_02_00

Figure 36-11-00-991-12100-00-A / SHEET 2/2 - Bleed-Pressure Regulator Valve P/N 6774E ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 23 of 40

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A

B BLEED-PRESSURE REGULATOR VALVE

A N_MM_361100_4_AAA0_01_00

Figure 36-11-00-991-12100-00-B / SHEET 1/2 - Bleed-Pressure Regulator Valve P/N 6774E ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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3 2 1

C CLOSED

OPEN

B

C POSITION INDICATOR AND MANUAL OVERRIDE

N_MM_361100_4_AAA0_02_00

Figure 36-11-00-991-12100-00-B / SHEET 2/2 - Bleed-Pressure Regulator Valve P/N 6774E ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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A

BLEED-PRESSURE REGULATOR VALVE

B

A N_MM_361100_4_AAT0_01_03

Figure 36-11-00-991-12200-00-A / SHEET 1/2 - Bleed-Pressure Regulator Valve P/N 6774G ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 26 of 40

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2

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C CLOSED

OPEN

B

C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_AAT0_02_00

Figure 36-11-00-991-12200-00-A / SHEET 2/2 - Bleed-Pressure Regulator Valve P/N 6774G ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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A

B BLEED-PRESSURE REGULATOR VALVE

A N_MM_361100_4_ATA0_01_00

Figure 36-11-00-991-12200-00-B / SHEET 1/2 - Bleed-Pressure Regulator Valve P/N 6774G ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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B

C POSITION INDICATOR AND MANUAL OVERRIDE

N_MM_361100_4_ATA0_02_00

Figure 36-11-00-991-12200-00-B / SHEET 2/2 - Bleed-Pressure Regulator Valve P/N 6774G ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 29 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

A

BLEED-PRESSURE REGULATOR VALVE

B

A N_MM_361100_4_BDM0_01_02

Figure 36-11-00-991-12000-00-A / SHEET 1/2 - Bleed-Pressure Regulator Valve P/N 6774F ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 30 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

2

1

C

CLOSED

OPEN

B

C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_BDM0_02_00

Figure 36-11-00-991-12000-00-A / SHEET 2/2 - Bleed-Pressure Regulator Valve P/N 6774F ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 31 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

A

B BLEED-PRESSURE REGULATOR VALVE

A N_MM_361100_4_BDS0_01_00

Figure 36-11-00-991-12000-00-B / SHEET 1/2 - Bleed-Pressure Regulator Valve P/N 6774F ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 32 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

2

1

C

CLOSED

OPEN

B

C POSITION INDICATOR AND MANUAL OVERRIDE

N_MM_361100_4_BDS0_02_00

Figure 36-11-00-991-12000-00-B / SHEET 2/2 - Bleed-Pressure Regulator Valve P/N 6774F ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 33 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

3.

Job Set-up Subtask 36-11-00-861-065-A A.

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

Subtask 36-11-00-860-071-A B.

Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) .

Subtask 36-11-00-941-053-A C.

Safety Precautions (1) Make sure that the engine 1(2) is shut down occurred not less than 5 minutes. (2) On the ENG panel 115VU: · put a WARNING NOTICE(S) to tell persons not to start the engine 1(2). (3) On the MAINTENANCE panel 50VU: · make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off · install a warning notice to tell persons not to operate the FADEC SYSTEM. (4) On the AIR COND panel 30VU: · make sure that the ENG 1(2) BLEED pushbutton switch is released (the OFF legend is on) · make sure that the APU BLEED pushbutton switch is released (the ON legend is off) · put a warning notice to tell persons not to operate the pneumatic system. (5) On the HP ground connector: · put a warning notice to tell persons not to pressurize the pneumatic system.

Subtask 36-11-00-865-063-A D.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU 49VU 122VU 122VU

DESIGNATION AIR BLEED/ENG 1/CTL AIR BLEED/ENG 1/MONG AIR BLEED/ENG 2/CTL AIR BLEED/ENG 2/MONG

FIN 3HA1 2HA1 3HA2 2HA2

LOCATION D12 D11 Z23 Z22

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 Subtask 36-11-00-010-050-B E.

Get Access (1) Open the fan cowls (Ref. AMM TASK 71-13-00-010-010) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR (2) Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in to position below the engine.

Subtask 36-11-00-040-050-B F.

Deactivate the Thrust Reverser WARNING: MAKE SURE THAT THE THRUST REVERSER HYDRAULIC CONTROL UNIT (HCU) IS DEACTIVATED BEFORE YOU DO WORK ON OR AROUND THE THRUST REVERSER.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 34 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

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) Deactivate the thrust reverser Hydraulic Control Unit (HCU) (Ref. AMM TASK 78-30-00-040-012) . Subtask 36-11-00-010-071-B G. Open the thrust reverser halves (Ref. AMM TASK 78-32-00-010-010) : (1) FOR 1000EM1 (ENGINE-1) 451AL, 452AR (2) FOR 1000EM2 (ENGINE-2) 461AL, 462AR ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Subtask 36-11-00-010-050-C E.

Get Access (1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-040) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR. (2) Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position below the engine.

Subtask 36-11-00-040-050-C F.

Make the thrust reverser unserviceable (Ref. AMM TASK 78-30-00-481-041) .

Subtask 36-11-00-010-071-C G. Open the left thrust-reverser cowl door (Ref. AMM TASK 78-36-00-010-040) : (1) FOR 1000EM1 (ENGINE-1) 451AL (2) FOR 1000EM2 (ENGINE-2) 461AL. ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 4.

Procedure (Ref. Fig. BLEED page of the ECAM Display Unit SHEET 1) Subtask 36-11-00-040-056-A A.

Deactivation of the Bleed Pressure Regulator Valve CAUTION:

CAREFULLY ALIGN THE LOCKING PIN WITH THE DEACTIVATING HOUSING ON THE VALVE. IF YOU ALIGN IT INCORRECTLY OR IF YOU TIGHTEN IT TOO MUCH, THE LOCKING PIN CAN REMAIN IN POSITION AND YOU CAN CAUSE DAMAGE TO THE LOCKING PIN THREAD.

(1) On the bleed-pressure regulator valve P/N 6774B02 and P/N 6714D01 to 6714D06: ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. Bleed-Pressure Regulator Valve P/N 6774B02)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 35 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. Bleed-Pressure Regulator Valve P/N 6774B02) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. Bleed-Pressure Regulator Valve) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. Bleed-Pressure Regulator Valve) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (a) Use a WRENCH - HEXAGONAL to set the manual override control to the CLOSED position. (b) Removal of the lockwire 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. 1

Cut, remove and discard the lockwire from the knurled screw (1).

(c) Remove the knurled screw (1) from its storage port. 1

Keep the washer (2) to install it in the reactivation procedure.

(d) Lock the override control with the knurled screw (1). NOTE: The pressure of the valve is released when you remove the locking pin from its storage port. (e) Tighten the knurled screw (1) with your hand. (2) On the bleed-pressure regulator valve P/N 6774B03 and P/N 6714D07: ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. Bleed-Pressure Regulator Valve P/N 6714D07) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. Bleed-Pressure Regulator Valve P/N 6714D07) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. Bleed-Pressure Regulator Valve P/N 6774B03) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. Bleed-Pressure Regulator Valve P/N 6774B03) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (a) Use a WRENCH - HEXAGONAL to set the manual override control to the CLOSED position. (b) Removal of the lockwire WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMME-

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 36 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

DIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE. (c) Cut, remove and discard the lockwire from the safety screw (1). (d) Remove the safety screw (1) from its storage port. 1

Keep the washer (2) to install it in the reactivation procedure.

(e) Lock the override control with the safety screw (1). NOTE: The pressure of the valve is released when you remove the locking pin from its storage port. (f)

TORQUE the safety screw (1) to between 0.6 and 0.7 m.daN (53.10 and 61.95 lbf.in).

(3) On the bleed-pressure regulator valve P/N 6774E: ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. Bleed-Pressure Regulator Valve P/N 6774E) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. Bleed-Pressure Regulator Valve P/N 6774E) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (a) Use a WRENCH - HEXAGONAL to set the manual override control to the CLOSED position. (b) Removal of the lockwire 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. 1

Cut, remove and discard the lockwire from the special screw (1).

(c) Remove the special screw (1) from its storage port. 1

Keep the washer (2) to install it in the reactivation procedure.

(d) Remove and discard the packing (3). (e) Lock the override control with the special screw (1). NOTE: The pressure of the valve is released when you remove the locking pin from its storage port. (f)

Tighten the special screw (1) with your hand.

(4) On the bleed-pressure regulator valve P/N 6774F and P/N 6774G: ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. Bleed-Pressure Regulator Valve P/N 6774G) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. Bleed-Pressure Regulator Valve P/N 6774G) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 37 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

(Ref. Fig. Bleed-Pressure Regulator Valve P/N 6774F) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. Bleed-Pressure Regulator Valve P/N 6774F) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (a) Use a WRENCH - HEXAGONAL to set the manual override control to the CLOSED position. (b) Removal of the lockwire 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. 1

Cut,remove and discard the lockwire from the safety screw (1).

(c) Remove the safety screw (1) from its storage port. (d) Remove and discard the packing (2). (e) Lock the override control with the special screw (1). NOTE: The pressure of the valve is released when you remove the locking pin from its storage port. (f)

TORQUE the safety screw (1) to between 0.4 and 0.6 m.daN (35.40 and 53.10 lbf.in).

Subtask 36-11-00-865-089-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU 49VU 122VU 122VU

DESIGNATION AIR BLEED/ENG 1/CTL AIR BLEED/ENG 1/MONG AIR BLEED/ENG 2/CTL AIR BLEED/ENG 2/MONG

FIN 3HA1 2HA1 3HA2 2HA2

LOCATION D12 D11 Z23 Z22

Subtask 36-11-00-040-093-A C.

Deactivation of the Bleed Pressure Regulator Valve (1) On the ECAM control panel, push the BLEED key (on the lower ECAM DU, the BLEED page comes into view). (a) On the lower ECAM DU, on the BLEED page: · Make sure that the related bleed-pressure regulator-valve symbol shows closed in green.

Subtask 36-11-00-790-058-A D.

Check of the Bleed Air Ducts NOTE: This check is only applicable to aircraft with Overpressure Valve (OPV) P/N 6740G01XXXX. It is necessary to do a check of the valve reference because the valves are interchangeable. (1) Get the post flight report (Ref. AMM D/O 31-37-73-00) : (a) If the class 1 fault message PRESS REG-V 4001HA1(2) and the ECAM warning AIR ENG 1(2) BLEED FAULT comes into view during the flight phases 3, 4 or 5, get the ENG TAKE OFF REPORT in the MCDU and do a check of the pack values:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 38 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

1

5.

If the pack value is 00 or 01 (the pack was off during the last take off): a

Do the leak check of all the bleed air ducts and pack components (Ref. AMM TASK 3622-00-790-001) .

b

Do a visual inspection of the bleed air ducts and items of equipment downstream the OPV (along the pylon and center fuselage to the starter valves, flow control valves, HP ground connectors, pressure service check valves and APU check valve but not the wing ducting). Make sure that there is no deformation and be very careful when you do the check of the bellows. · If there is a damage or deformation, repair or replace the damaged duct or equipment.

Close-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 Subtask 36-11-00-410-050-B A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the thrust reverser halves (Ref. AMM TASK 78-32-00-410-010) : (a) FOR 1000EM1 (ENGINE-1) 451AL, 452AR (b) FOR 1000EM2 (ENGINE-2) 461AL, 462AR

Subtask 36-11-00-440-050-B B.

Activate the thrust reverser HCU (Ref. AMM TASK 78-30-00-440-012) .

Subtask 36-11-00-410-070-B C.

Close Access (1) Close the fan cowls (Ref. AMM TASK 71-13-00-410-010) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR (2) Remove the WARNING NOTICE(S). (3) Remove the access platform(s).

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Subtask 36-11-00-410-050-C A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the left thrust-reverser cowl door (Ref. AMM TASK 78-36-00-410-040) : (a) FOR 1000EM1 (ENGINE-1) 451AL (b) FOR 1000EM2 (ENGINE-2) 461AL.

Subtask 36-11-00-440-050-C Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 39 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-001-A - Deactivation of the Bleed Pressure Regulator Valve

B.

Make the thrust reverser serviceable (Ref. AMM TASK 78-30-00-081-041) .

Subtask 36-11-00-410-070-C C.

Close Access (1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-040) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR. (2) Remove the access platform(s). (3) Remove the WARNING NOTICE(S).

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 36-11-00-942-053-A D.

Put a warning notice in the cockpit to tell the crew that the left (right) bleed pressure regulator valve is closed and deactivated.

Subtask 36-11-00-865-064-A E.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU 49VU 122VU 122VU

DESIGNATION AIR BLEED/ENG 1/CTL AIR BLEED/ENG 1/MONG AIR BLEED/ENG 2/CTL AIR BLEED/ENG 2/MONG

FIN 3HA1 2HA1 3HA2 2HA2

LOCATION D12 D11 Z23 Z22

Subtask 36-11-00-860-072-A F.

Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) .

Subtask 36-11-00-869-112-A G. Make an entry in the logbook. Subtask 36-11-00-862-065-A H.

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

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 40 of 40

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 TASK 36-11-00-040-002-A Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve 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.

FIN : 4000HA , 7110HM , 1000EM1 , 1000EM2 Task Summary MMEL or CDL Ref MMEL 36-11-06B

Access YES

1.

Reason for the Job MMEL 36-11-06B Engine Bleed IP Check Valve

2

Job Set-up Information A.

Test YES

Mhr 01.4

E/T 01.4

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific

QTY AR AR AR 1

No specific

B.

Specific Tools NO

DESIGNATION ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S) WRENCH - HEXAGONAL Torque wrench: range to between 0.5 and 0.6 m.daN (44.25 and 53.10 lbf.in) Torque wrench: range to between 0.6 and 0.7 m.daN (53.10 and 61.95 lbf.in)

Work Zones and Access Panels ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 437AL, 438AR, 451AL

ZONE DESCRIPTION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 452AR ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 FOR 1000EM2 (ENGINE-2) 447AL, 448AR, 461AL

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve ZONE/ACCESS

ZONE DESCRIPTION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 462AR ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 71-13-00-010-010-A). Opening of the Fan Cowls 437AL(447AL),438AR(448AR) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 71-13-00-010-040-B). Opening of the Fan Cowl Doors ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 71-13-00-410-010-A). Closing of the Fan Cowls 437AL(447AL),438AR(448AR) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 71-13-00-410-040-B). Closing of the Fan Cowl Doors ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 78-30-00-040-012-A). Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for Ground Maintenance ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 78-30-00-081-041-B). Make the Thrust Reverser Serviceable after Maintenance ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 78-30-00-440-012-A). Re-activation of the Thrust Reverser Hydraulic Control Unit (HCU) after Ground Maintenance ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 78-30-00-481-041-B). Make the Thrust Reverser Unserviceable for Maintenance ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 78-32-00-010-010-A). Opening of the Thrust Reverser Halves

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve REFERENCE (Ref. 78-32-00-410-010-A).

DESIGNATION Closing of the Thrust Reverser Halves

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 78-36-00-010-040-B). Opening of the Thrust Reverser Doors (Ref. 78-36-00-410-040-B). Closing of the Thrust Reverser Doors ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 HP Bleed Valve P/N 6773B02 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 HP Bleed Valve P/N 6773B02 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 HP Bleed Valve P/N 6713D01-07 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 HP Bleed Valve P/N 6713D01-07 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 HP Bleed Valve P/N 6773B03 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 HP Bleed Valve P/N 6773B03 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 HP Bleed Valve P/N 6713D08 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 HP Bleed Valve P/N 6713D08 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 HP Bleed Valve P/N 6773E ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 HP Bleed Valve P/N 6773E ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 HP Bleed Valve P/N 6773F and 6773G ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 HP Bleed Valve P/N 6773F and 6773G

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_BFM0_01_02

Figure 36-11-00-991-11200-00-A / SHEET 1/2 - HP Bleed Valve P/N 6773B02 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

C

1

2

B CLOSED

OPEN

C VISUAL INDICATOR N_MM_361100_4_BFM0_02_00

Figure 36-11-00-991-11200-00-A / SHEET 2/2 - HP Bleed Valve P/N 6773B02 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_BMH0_01_00

Figure 36-11-00-991-11200-00-C / SHEET 1/2 - HP Bleed Valve P/N 6773B02 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

2

1

C

B

CLOSED

OPEN

C VISUAL INDICATOR N_MM_361100_4_BMH0_02_00

Figure 36-11-00-991-11200-00-C / SHEET 2/2 - HP Bleed Valve P/N 6773B02 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_ACM0_01_03

Figure 36-11-00-991-00300-00-A / SHEET 1/2 - HP Bleed Valve P/N 6713D01-07 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

C 1

2

B

CLOSED

OPEN

C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_ACM0_02_00

Figure 36-11-00-991-00300-00-A / SHEET 2/2 - HP Bleed Valve P/N 6713D01-07 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_ADF0_01_00

Figure 36-11-00-991-00300-00-C / SHEET 1/2 - HP Bleed Valve P/N 6713D01-07 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

1 2

C

B

CLOSED

OPEN

C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_ADF0_02_00

Figure 36-11-00-991-00300-00-C / SHEET 2/2 - HP Bleed Valve P/N 6713D01-07 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_BGM0_01_02

Figure 36-11-00-991-11300-00-A / SHEET 1/2 - HP Bleed Valve P/N 6773B03 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 12 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

C 1

2

B

OPEN

CLOSED

C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_BGM0_02_00

Figure 36-11-00-991-11300-00-A / SHEET 2/2 - HP Bleed Valve P/N 6773B03 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 13 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_BYP0_01_00

Figure 36-11-00-991-11300-00-C / SHEET 1/2 - HP Bleed Valve P/N 6773B03 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 14 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

2

C

1

B

OPEN

CLOSED

C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_BYP0_02_00

Figure 36-11-00-991-11300-00-C / SHEET 2/2 - HP Bleed Valve P/N 6773B03 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 15 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_BEM0_01_02

Figure 36-11-00-991-11400-00-A / SHEET 1/2 - HP Bleed Valve P/N 6713D08 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 16 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

C

1

2

B

OPEN

CLOSED

C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_BEM0_02_00

Figure 36-11-00-991-11400-00-A / SHEET 2/2 - HP Bleed Valve P/N 6713D08 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 17 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_BSM0_01_00

Figure 36-11-00-991-11400-00-C / SHEET 1/2 - HP Bleed Valve P/N 6713D08 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 18 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

2

1

C

B

OPEN

CLOSED

C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_BSM0_02_00

Figure 36-11-00-991-11400-00-C / SHEET 2/2 - HP Bleed Valve P/N 6713D08 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 19 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_ACP0_01_03

Figure 36-11-00-991-11500-00-A / SHEET 1/2 - HP Bleed Valve P/N 6773E ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 20 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

C 1

2 3

B

CLOSED

OPEN

C POSITION INDICATOR AND MANUAL OVERRIDE

N_MM_361100_4_ACP0_02_00

Figure 36-11-00-991-11500-00-A / SHEET 2/2 - HP Bleed Valve P/N 6773E ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 21 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_AFF0_01_00

Figure 36-11-00-991-11500-00-C / SHEET 1/2 - HP Bleed Valve P/N 6773E ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 22 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

3 2 1

C

B

CLOSED

OPEN

C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_AFF0_02_00

Figure 36-11-00-991-11500-00-C / SHEET 2/2 - HP Bleed Valve P/N 6773E ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 23 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_BHM0_01_02

Figure 36-11-00-991-11600-00-A / SHEET 1/2 - HP Bleed Valve P/N 6773F and 6773G ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 24 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

C

1 2

B

OPEN

CLOSED

C POSITION INDICATOR AND MANUAL OVERRIDE

N_MM_361100_4_BHM0_02_00

Figure 36-11-00-991-11600-00-A / SHEET 2/2 - HP Bleed Valve P/N 6773F and 6773G ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 25 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_BYH0_01_00

Figure 36-11-00-991-11600-00-C / SHEET 1/2 - HP Bleed Valve P/N 6773F and 6773G ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 26 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

2 1

C

B

OPEN

CLOSED

C POSITION INDICATOR AND MANUAL OVERRIDE

N_MM_361100_4_BYH0_02_00

Figure 36-11-00-991-11600-00-C / SHEET 2/2 - HP Bleed Valve P/N 6773F and 6773G ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 27 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

3.

Job Set-up Subtask 36-11-00-861-066-A A.

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

Subtask 36-11-00-941-063-A B.

Safety Precautions (1) Make sure that the engine 1(2) is shut down occurred not less than 5 minutes. (2) On the AIR COND panel 30VU: · make sure that the ENG 1(2) BLEED pushbutton switch is released (the OFF legend is on) · make sure that the APU BLEED pushbutton switch is released (the ON legend is off) · put a WARNING NOTICE(S) to tell persons not to operate the pneumatic system. (3) On the ENG panel 115VU: · put a WARNING NOTICE(S) to tell persons not to start the engine 1(2). (4) On the HP ground connector: · put a WARNING NOTICE(S) to tell persons not to pressurize the pneumatic system. (5) On the MAINTENANCE panel 50VU: · make sure that the ON legend of the ENG/FADEC GND PWR 1(2) pushbutton switch is off · put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).

Subtask 36-11-00-865-067-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU 49VU 122VU 122VU

DESIGNATION AIR BLEED/ENG 1/CTL AIR BLEED/ENG 1/MONG AIR BLEED/ENG 2/CTL AIR BLEED/ENG 2/MONG

FIN 3HA1 2HA1 3HA2 2HA2

LOCATION D12 D11 Z23 Z22

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 Subtask 36-11-00-010-054-B D.

Get Access (1) Open the fan cowls (Ref. AMM TASK 71-13-00-010-010) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR (2) Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in to position below the engine.

Subtask 36-11-00-040-052-B E.

Deactivate the Thrust Reverser 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.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 28 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

(1) Deactivate the thrust reverser Hydraulic Control Unit (HCU) (Ref. AMM TASK 78-30-00-040-012) . Subtask 36-11-00-010-073-B F.

Open the thrust reverser halves (Ref. AMM TASK 78-32-00-010-010) : (1) FOR 1000EM1 (ENGINE-1) 451AL, 452AR (2) FOR 1000EM2 (ENGINE-2) 461AL, 462AR

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Subtask 36-11-00-010-054-C D.

Get Access (1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-040) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR. (2) Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position below the engine.

Subtask 36-11-00-040-052-C E.

Make the thrust reverser unserviceable (Ref. AMM TASK 78-30-00-481-041) .

Subtask 36-11-00-010-073-C F.

Open the left thrust-reverser cowl door (Ref. AMM TASK 78-36-00-010-040) : (1) FOR 1000EM1 (ENGINE-1) 451AL (2) FOR 1000EM2 (ENGINE-2) 461AL.

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 4.

Procedure Subtask 36-11-00-040-057-A A.

Deactivation of the IP Bleed Check Valve CAUTION:

CAREFULLY ALIGN THE LOCKING PIN WITH THE DEACTIVATING HOUSING ON THE VALVE. IF YOU ALIGN IT INCORRECTLY OR IF YOU TIGHTEN IT TOO MUCH, THE LOCKING PIN CAN REMAIN IN POSITION AND YOU CAN CAUSE DAMAGE TO THE LOCKING PIN THREAD.

(1) On the HP bleed valve P/N 6773B02 and P/N 6713D01 to 6713D07: ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. HP Bleed Valve P/N 6773B02) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. HP Bleed Valve P/N 6773B02) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. HP Bleed Valve P/N 6713D01-07) Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 29 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. HP Bleed Valve P/N 6713D01-07) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (a) Use a WRENCH - HEXAGONAL to set the manual override control to the CLOSED position. (b) Removal of the lockwire: 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. 1

Cut, remove and discard the lockwire from the knurled screw (1).

(c) Remove the knurled screw from its the storage port. 1

Keep the washer (2) to install it in the reactivation procedure.

(d) Lock the override control with the knurled screw (1). NOTE: The pressure of the valve is released when you remove the locking pin from its storage port. (e) Tighten the knurled screw (1) with your hand. (2) On the HP bleed valve P/N 6773B03 and P/N 6713D08: ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. HP Bleed Valve P/N 6773B03) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. HP Bleed Valve P/N 6773B03) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. HP Bleed Valve P/N 6713D08) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. HP Bleed Valve P/N 6713D08) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (a) Use a WRENCH - HEXAGONAL to set the manual override control to the CLOSED position. (b) Removal of the lockwire: 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. 1

Cut, remove and discard the lockwire from the safety screw (1).

(c) Remove the safety screw (1) from its storage port. 1

Keep the washer (2) to install it in the reactivation procedure.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 30 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

(d) Lock the override control with the safety screw (1). NOTE: the pressure of the valve is released when you remove the locking pin from its storage port. (e) TORQUE the safety screw (1) to between 0.6 and 0.7 m.daN (53.10 and 61.95 lbf.in). (3) On the HP bleed valve P/N 6773E: ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. HP Bleed Valve P/N 6773E) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. HP Bleed Valve P/N 6773E) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (a) Use a WRENCH - HEXAGONAL to set the manual override control to the CLOSED position. (b) Removal of the lockwire: 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. 1

Cut, remove and discard the lockwire from the special screw (1).

(c) Remove the special screw (1) from it storage port. 1

Keep the washer (2) to install it in the reactivation procedure.

(d) Remove and discard the packing (3). (e) Lock the override control with the special screw (1). NOTE: The pressure of the valve is released when you remove the locking pin from its storage port. (f)

Tighten the special screw (1) with your hand.

(4) On the HP bleed valve P/N 6773F and P/N 6773G: ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. HP Bleed Valve P/N 6773F and 6773G) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. HP Bleed Valve P/N 6773F and 6773G) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (a) Use a WRENCH - HEXAGONAL to set the manual override control to the CLOSED position. (b) Removal the lockwire: WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DIS-

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 31 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve CARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE. 1

Cut, remove and discard the lockwire from the safety screw (1).

(c) Remove the safety screw (1) from its storage port. (d) Remove and discard the packing (2). (e) Lock the override control with the special screw (1). NOTE: the pressure of the valve is released when you remove the locking pin from its storage port. (f) 5.

TORQUE the safety screw (1) to between 0.5 and 0.6 m.daN (44.25 and 53.10 lbf.in)

Close-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 Subtask 36-11-00-410-054-B A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the thrust reverser halves (Ref. AMM TASK 78-32-00-410-010) : (a) FOR 1000EM1 (ENGINE-1) 451AL, 452AR (b) FOR 1000EM2 (ENGINE-2) 461AL, 462AR

Subtask 36-11-00-440-053-B B.

Activate the thrust reverser HCU (Ref. AMM TASK 78-30-00-440-012) .

Subtask 36-11-00-410-073-B C.

Close Access (1) Close the fan cowls (Ref. AMM TASK 71-13-00-410-010) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR (2) Remove the WARNING NOTICE(S). (3) Remove the access platform(s).

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Subtask 36-11-00-410-054-C A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the left thrust-reverser cowl door (Ref. AMM TASK 78-36-00-410-040) : (a) FOR 1000EM1 (ENGINE-1) 451AL (b) FOR 1000EM2 (ENGINE-2)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 32 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-002-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve 461AL. Subtask 36-11-00-440-053-C B.

Make the thrust reverser serviceable (Ref. AMM TASK 78-30-00-081-041) .

Subtask 36-11-00-410-073-C C.

Close Access (1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-040) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR. (2) Remove the access platform(s). (3) Remove the WARNING NOTICE(S).

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 36-11-00-941-065-A D.

Put a warning notice in the cockpit to tell the crew that the left (right) HP bleed valve is closed and deactivated.

Subtask 36-11-00-865-068-A E.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU 49VU 122VU 122VU

DESIGNATION AIR BLEED/ENG 1/CTL AIR BLEED/ENG 1/MONG AIR BLEED/ENG 2/CTL AIR BLEED/ENG 2/MONG

FIN 3HA1 2HA1 3HA2 2HA2

LOCATION D12 D11 Z23 Z22

Subtask 36-11-00-869-113-A F.

Make an entry in the logbook.

Subtask 36-11-00-862-066-A G. De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 33 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 TASK 36-11-00-040-003-A Deactivation of the HP Bleed Valve 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.

FIN : 4000HA , 1000EM1 , 1000EM2 Task Summary MMEL or CDL Ref MMEL 36-11-07B 1.

Reason for the Job MMEL 36-11-07B Engine Bleed HP Valve

2

Job Set-up Information A.

Access YES

Test YES

Mhr 02.4

E/T 02.4

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific

QTY AR AR AR 1

No specific

B.

Specific Tools NO

DESIGNATION ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S) WRENCH - HEXAGONAL Torque wrench: range to between 0.5 and 0.6 m.daN (44.25 and 53.10 lbf.in) Torque wrench: range to between 0.6 and 0.7 m.daN (53.10 and 61.95 lbf.in)

Work Zones and Access Panels ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 437AL, 438AR, 451AL

ZONE DESCRIPTION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 452AR ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 FOR 1000EM2 (ENGINE-2) 447AL, 448AR, 461AL

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

ZONE/ACCESS

ZONE DESCRIPTION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 462AR ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 71-13-00-010-010-A). Opening of the Fan Cowls 437AL(447AL),438AR(448AR) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 71-13-00-010-040-B). Opening of the Fan Cowl Doors ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 71-13-00-410-010-A). Closing of the Fan Cowls 437AL(447AL),438AR(448AR) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 71-13-00-410-040-B). Closing of the Fan Cowl Doors ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 78-30-00-040-012-A). Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for Ground Maintenance ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 78-30-00-081-041-B). Make the Thrust Reverser Serviceable after Maintenance ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 78-30-00-440-012-A). Re-activation of the Thrust Reverser Hydraulic Control Unit (HCU) after Ground Maintenance ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 78-30-00-481-041-B). Make the Thrust Reverser Unserviceable for Maintenance

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

REFERENCE

DESIGNATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 (Ref. 78-32-00-010-010-A). Opening of the Thrust Reverser Halves (Ref. 78-32-00-410-010-A). Closing of the Thrust Reverser Halves ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. 78-36-00-010-040-B). Opening of the Thrust Reverser Doors (Ref. 78-36-00-410-040-B). Closing of the Thrust Reverser Doors ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 HP Bleed Valve P/N 6773B02 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 HP Bleed Valve P/N 6773B02 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 HP Bleed Valve P/N 6713D01-07 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 HP Bleed Valve P/N 6713D01-07 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 HP Bleed Valve P/N 6773B03 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 HP Bleed Valve P/N 6773B03 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 HP Bleed Valve P/N 6713D08 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 HP Bleed Valve P/N 6713D08 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 HP Bleed Valve P/N 6773E ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 HP Bleed Valve P/N 6773E ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 HP Bleed Valve P/N 6773F and 6773G ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 HP Bleed Valve P/N 6773F and 6773G

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_BFM0_01_02

Figure 36-11-00-991-11200-00-A / SHEET 1/2 - HP Bleed Valve P/N 6773B02 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

C

1

2

B CLOSED

OPEN

C VISUAL INDICATOR N_MM_361100_4_BFM0_02_00

Figure 36-11-00-991-11200-00-A / SHEET 2/2 - HP Bleed Valve P/N 6773B02 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_BMH0_01_00

Figure 36-11-00-991-11200-00-C / SHEET 1/2 - HP Bleed Valve P/N 6773B02 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 33

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2

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C VISUAL INDICATOR N_MM_361100_4_BMH0_02_00

Figure 36-11-00-991-11200-00-C / SHEET 2/2 - HP Bleed Valve P/N 6773B02 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_ACM0_01_03

Figure 36-11-00-991-00300-00-A / SHEET 1/2 - HP Bleed Valve P/N 6713D01-07 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 33

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C 1

2

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C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_ACM0_02_00

Figure 36-11-00-991-00300-00-A / SHEET 2/2 - HP Bleed Valve P/N 6713D01-07 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_ADF0_01_00

Figure 36-11-00-991-00300-00-C / SHEET 1/2 - HP Bleed Valve P/N 6713D01-07 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 33

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1 2

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C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_ADF0_02_00

Figure 36-11-00-991-00300-00-C / SHEET 2/2 - HP Bleed Valve P/N 6713D01-07 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 33

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A

HP BLEED VALVE

B

A N_MM_361100_4_BGM0_01_02

Figure 36-11-00-991-11300-00-A / SHEET 1/2 - HP Bleed Valve P/N 6773B03 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 12 of 33

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C 1

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C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_BGM0_02_00

Figure 36-11-00-991-11300-00-A / SHEET 2/2 - HP Bleed Valve P/N 6773B03 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 13 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_BYP0_01_00

Figure 36-11-00-991-11300-00-C / SHEET 1/2 - HP Bleed Valve P/N 6773B03 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 14 of 33

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2

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C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_BYP0_02_00

Figure 36-11-00-991-11300-00-C / SHEET 2/2 - HP Bleed Valve P/N 6773B03 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 15 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_BEM0_01_02

Figure 36-11-00-991-11400-00-A / SHEET 1/2 - HP Bleed Valve P/N 6713D08 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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C

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CLOSED

C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_BEM0_02_00

Figure 36-11-00-991-11400-00-A / SHEET 2/2 - HP Bleed Valve P/N 6713D08 ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 17 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_BSM0_01_00

Figure 36-11-00-991-11400-00-C / SHEET 1/2 - HP Bleed Valve P/N 6713D08 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 18 of 33

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C POSITION INDICATOR AND MANUAL OVERRIDE N_MM_361100_4_BSM0_02_00

Figure 36-11-00-991-11400-00-C / SHEET 2/2 - HP Bleed Valve P/N 6713D08 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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A

HP BLEED VALVE

B

A N_MM_361100_4_ACP0_01_03

Figure 36-11-00-991-11500-00-A / SHEET 1/2 - HP Bleed Valve P/N 6773E ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 20 of 33

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C 1

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N_MM_361100_4_ACP0_02_00

Figure 36-11-00-991-11500-00-A / SHEET 2/2 - HP Bleed Valve P/N 6773E ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_AFF0_01_00

Figure 36-11-00-991-11500-00-C / SHEET 1/2 - HP Bleed Valve P/N 6773E ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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3 2 1

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Figure 36-11-00-991-11500-00-C / SHEET 2/2 - HP Bleed Valve P/N 6773E ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_BHM0_01_02

Figure 36-11-00-991-11600-00-A / SHEET 1/2 - HP Bleed Valve P/N 6773F and 6773G ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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C

1 2

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N_MM_361100_4_BHM0_02_00

Figure 36-11-00-991-11600-00-A / SHEET 2/2 - HP Bleed Valve P/N 6773F and 6773G ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

A

HP BLEED VALVE

B

A N_MM_361100_4_BYH0_01_00

Figure 36-11-00-991-11600-00-C / SHEET 1/2 - HP Bleed Valve P/N 6773F and 6773G ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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2 1

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N_MM_361100_4_BYH0_02_00

Figure 36-11-00-991-11600-00-C / SHEET 2/2 - HP Bleed Valve P/N 6773F and 6773G ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

3.

Job Set-up Subtask 36-11-00-861-067-A A.

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

Subtask 36-11-00-860-077-A B.

Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) .

Subtask 36-11-00-941-068-A C.

Safety Precautions (1) Make sure that the engine 1(2) is shut down occurred not less than 5 minutes. (2) On the AIR COND panel 30VU: · Make sure that the ENG 1(2) BLEED pushbutton switch is released (the OFF legend is on) · Make sure that the APU BLEED pushbutton switch is released (the ON legend is off) · Put a WARNING NOTICE(S) to tell persons not to operate the pneumatic system. (3) On the ENG panel 115VU: · Put a WARNING NOTICE(S) to tell persons not to start the engine 1(2). (4) On the HP ground connector: · Put a WARNING NOTICE(S) to tell persons not to pressurize the pneumatic system. (5) On the MAINTENANCE panel 50VU: · Make sure that the ON legend of the ENG/FADEC GND PWR 1(2) pushbutton switch is off · Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).

Subtask 36-11-00-865-071-A D.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU 49VU 122VU 122VU

DESIGNATION AIR BLEED/ENG 1/CTL AIR BLEED/ENG 1/MONG AIR BLEED/ENG 2/CTL AIR BLEED/ENG 2/MONG

FIN 3HA1 2HA1 3HA2 2HA2

LOCATION D12 D11 Z23 Z22

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 Subtask 36-11-00-010-056-B E.

Get Access (1) Open the fan cowls (Ref. AMM TASK 71-13-00-010-010) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR. (2) Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in to position below the engine.

Subtask 36-11-00-040-054-B F.

Deactivate the Thrust Reverser WARNING: MAKE SURE THAT THE THRUST REVERSER HYDRAULIC CONTROL UNIT (HCU) IS DEACTIVATED BEFORE YOU DO WORK ON OR AROUND THE THRUST REVERSER.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

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) Deactivate the thrust reverser Hydraulic Control Unit (HCU) (Ref. AMM TASK 78-30-00-040-012) . Subtask 36-11-00-010-075-B G. Open the thrust reverser halves (Ref. AMM TASK 78-32-00-010-010) : (1) FOR 1000EM1 (ENGINE-1) 451AL, 452AR (2) FOR 1000EM2 (ENGINE-2) 461AL, 462AR. ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Subtask 36-11-00-010-056-C E.

Get Access (1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-040) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR. (2) Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position below the engine.

Subtask 36-11-00-040-054-C F.

Make the thrust reverser unserviceable (Ref. AMM TASK 78-30-00-481-041) .

Subtask 36-11-00-010-075-C G. Open the left thrust-reverser cowl door (Ref. AMM TASK 78-36-00-010-040) : (1) FOR 1000EM1 (ENGINE-1) 451AL (2) FOR 1000EM2 (ENGINE-2) 461AL. ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 4.

Procedure Subtask 36-11-00-040-058-A A.

Deactivation of the HP Bleed Valve CAUTION:

CAREFULLY ALIGN THE LOCKING PIN WITH THE DEACTIVATING HOUSING ON THE VALVE. IF YOU ALIGN IT INCORRECTLY OR IF YOU TIGHTEN IT TOO MUCH, THE LOCKING PIN CAN REMAIN IN POSITION AND YOU CAN CAUSE DAMAGE TO THE LOCKING PIN THREAD.

(1) On the HP bleed valve P/N 6773B02 and P/N 6713D01 to 6713D07: ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. HP Bleed Valve P/N 6773B02) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

(Ref. Fig. HP Bleed Valve P/N 6773B02) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. HP Bleed Valve P/N 6713D01-07) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. HP Bleed Valve P/N 6713D01-07) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (a) Use a WRENCH - HEXAGONAL to set the manual override control to the CLOSED position. (b) Removal of the lockwire: 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. 1

Cut, remove and discard the lockwire from the knurled screw (1).

(c) Remove the knurled screw (1) from its the storage port. 1

Keep the washer (2) to install it in the reactivation procedure.

(d) Lock the override control with the knurled screw (1). NOTE: The pressure of the valve is released when you remove the locking pin from its storage port. (e) Tighten the knurled screw (1) with your hand. (2) On the HP bleed valve P/N 6773B03 and P/N 6713D08: ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. HP Bleed Valve P/N 6773B03) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. HP Bleed Valve P/N 6773B03) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. HP Bleed Valve P/N 6713D08) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. HP Bleed Valve P/N 6713D08) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (a) Use a WRENCH - HEXAGONAL to set the manual override control to the CLOSED position. (b) Removal of the lockwire: 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.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

1

Cut, remove and discard the lockwire from the safety screw (1).

(c) Remove the safety screw (1) from its storage port. 1

Keep the washer (2) to install it in the reactivation procedure.

(d) Lock the override control with the safety screw (1). NOTE: the pressure of the valve is released when you remove the locking pin from its storage port. (e) TORQUE the safety screw (1) to between 0.6 and 0.7 m.daN (53.10 and 61.95 lbf.in). (3) On the HP bleed valve P/N 6773E: ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. HP Bleed Valve P/N 6773E) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. HP Bleed Valve P/N 6773E) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (a) Use a WRENCH - HEXAGONAL to set the manual override control to the CLOSED position. (b) Removal of the lockwire: 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. 1

Cut, remove and discard the lockwire from the special screw (1).

(c) Remove the special screw (1) from it storage port. 1

Keep the washer (2) to install it in the reactivation procedure.

(d) Remove and discard the packing (3). (e) Lock the override control with the special screw (1). NOTE: The pressure of the valve is released when you remove the locking pin from its storage port. (f)

Tighten the special screw (1) with your hand.

(4) On the HP bleed valve P/N 6773F and P/N 6773G: ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. HP Bleed Valve P/N 6773F and 6773G) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227233, 235-235, 237-240, 242-250, 350-350 (Ref. Fig. HP Bleed Valve P/N 6773F and 6773G) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 (a) Use a WRENCH - HEXAGONAL to set the manual override control to the CLOSED position. (b) Removal the lockwire:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 31 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

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. 1

Cut, remove and discard the lockwire from the safety screw (1).

(c) Remove the safety screw (1) from its storage port. (d) Remove and discard the packing (2). (e) Lock the override control with the safety screw (1). NOTE: the pressure of the valve is released when you remove the locking pin from its storage port. (f)

TORQUE the safety screw (1) to between 0.5 and 0.6 m.daN (44.25 and 53.10 lbf.in)

Subtask 36-11-00-865-085-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU 49VU 122VU 122VU

DESIGNATION AIR BLEED/ENG 1/CTL AIR BLEED/ENG 1/MONG AIR BLEED/ENG 2/CTL AIR BLEED/ENG 2/MONG

FIN 3HA1 2HA1 3HA2 2HA2

LOCATION D12 D11 Z23 Z22

Subtask 36-11-00-040-078-A C.

Deactivation of the HP Bleed Valve (1) On the ECAM control panel, push the BLEED key (on the lower ECAM DU, the BLEED page comes into view). (a) On the lower ECAM DU, on the BLEED page:

5.

1

Make sure that the related HP bleed-valve symbol shows closed in green.

2

Make sure that the related bleed-pressure regulator-valve symbol shows closed in green.

Close-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 Subtask 36-11-00-410-056-B A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the thrust reverser halves (Ref. AMM TASK 78-32-00-410-010) : (a) FOR 1000EM1 (ENGINE-1) 451AL, 452AR (b) FOR 1000EM2 (ENGINE-2) 461AL, 462AR.

Subtask 36-11-00-440-055-B B.

Activate the thrust reverser HCU (Ref. AMM TASK 78-30-00-440-012) .

Subtask 36-11-00-410-075-B Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 32 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-003-A - Deactivation of the HP Bleed Valve

C.

Close Access (1) Close the fan cowls (Ref. AMM TASK 71-13-00-410-010) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR. (2) Remove the WARNING NOTICE(S). (3) Remove the access platform(s).

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Subtask 36-11-00-410-056-C A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the left thrust-reverser cowl door (Ref. AMM TASK 78-36-00-410-040) : (a) FOR 1000EM1 (ENGINE-1) 451AL (b) FOR 1000EM2 (ENGINE-2) 461AL.

Subtask 36-11-00-440-055-C B.

Make the thrust reverser serviceable (Ref. AMM TASK 78-30-00-081-041) .

Subtask 36-11-00-410-075-C C.

Close Access (1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-040) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR. (2) Remove the access platform(s). (3) Remove the WARNING NOTICE(S).

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 36-11-00-860-079-A D.

Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) .

Subtask 36-11-00-869-115-A E.

Make an entry in the logbook.

Subtask 36-11-00-862-067-A F.

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

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 33 of 33

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-004-A - Check of the CFDS to Make Sure that the Pylon Leak Detection and APU Leak Detection Operates Correctly

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 TASK 36-11-00-040-004-A Check of the CFDS to Make Sure that the Pylon Leak Detection and APU Leak Detection Operates Correctly Task Summary MMEL or CDL Ref MMEL 36-00-01A MMEL 36-00-01A MMEL 36-00-01D MMEL 36-00-01D

Access NO NO NO NO

1.

Reason for the Job MMEL 36-00-01A AIR BLEED MAINTENANCE Message MMEL 36-00-01A AIR BLEED MAINTENANCE Message MMEL 36-00-01D AIR BLEED MAINTENANCE Message MMEL 36-00-01D AIR BLEED MAINTENANCE Message

2

Job Set-up Information A.

Specific Tools NO NO NO NO

Mhr 00.3 00.3 00.3 00.3

E/T 00.3 00.3 00.3 00.3

Nb Men 1 1 1 1

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 36-11-00-740-001-A).

3.

Test NO NO NO NO

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) BITE Test of the BMC 1(2)

Job Set-up Subtask 36-11-00-861-084-A A.

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

Subtask 36-11-00-865-084-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 49VU 122VU

DESIGNATION AIR BLEED/X FEED/VALVE/BAT AIR BLEED/ENG 1/CTL AIR BLEED/ENG 1/MONG AIR BLEED/ENG 2/CTL

FIN 2HV 3HA1 2HA1 3HA2

LOCATION D13 D12 D11 Z23

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-004-A - Check of the CFDS to Make Sure that the Pylon Leak Detection and APU Leak Detection Operates Correctly PANEL 122VU 122VU

DESIGNATION AIR BLEED/ENG 2/MONG AIR BLEED/X FEED VALVE/NORM

FIN 2HA2 1HV

LOCATION Z22 Z20

Subtask 36-11-00-860-075-A C.

Aircraft Maintenance Configuration (1) On the AIR COND panel: · Make sure that the ENG 1(2) BLEED pushbutton switches are pushed (OFF legends are off). · Make sure that the crossbleed selector switch is at AUTO position. · Make sure that the APU BLEED pushbutton switch is released (ON legend is off).

4.

Procedure

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 PRE SB 36-1062 for A/C 217-218, 233-233, 240-240, 242-243 Subtask 36-11-00-040-064-A A.

Check of the CFDS to Make Sure that the Pylon Leak Detection Operates Correctly (1) Do the BITE test of the BMC1 and BMC2 and print each TEST RESULT page (Ref. AMM TASK 3611-00-740-001) . (2) Make sure that the TEST RESULT pages do not show these maintenance messages: ATA 361100 361100 361100 361100 361134 361134 362215 362215 362217

MESSAGE CHECK BMC1 NO DATA FROM BMC2 CHECK BMC2 NO DATA FROM BMC1 BMC1 BMC2 ENG1 PYLON LOOP INOP ENG2 PYLON LOOP INOP APU LOOP INOP OR BMC IDENT CKT

CLASS FAULT 2 2 2 2 2 2 2 2 2

** ON A/C 027-100, 112-150, 208-208, 213-214, 223-225, 236-236, 238-238, 241-241 POST SB 36-1062 for A/C 217-218, 233-233, 240-240, 242-243 Subtask 36-11-00-040-064-B A.

Check of the CFDS to Make Sure that the Pylon Leak Detection Operates Correctly (1) Do the BITE test of the BMC1 and BMC2 and print each TEST RESULT page (Ref. AMM TASK 3611-00-740-001) . (2) Make sure that the TEST RESULT pages do not show this maintenance message: ATA 362217

MESSAGE APU LOOP INOP OR BMC IDENT CKT

CLASS FAULT 2

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 5.

Close-up Subtask 36-11-00-862-079-A A.

De-energize the aircraft electrical circuits

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-004-A - Check of the CFDS to Make Sure that the Pylon Leak Detection and APU Leak Detection Operates Correctly (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-807-A - Check of the CFDS to Make Sure that the Pylon Leak Detection and APU Leak Detection Loop Operates Correctly in LH Side

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 TASK 36-11-00-040-807-A Check of the CFDS to Make Sure that the Pylon Leak Detection and APU Leak Detection Loop Operates Correctly in LH Side 1.

Reason for the Job MMEL 36-00-01B AIR BLEED MAINTENANCE Message MMEL 36-00-01B AIR BLEED MAINTENANCE Message

2

Job Set-up Information A.

Referenced Information REFERENCE

DESIGNATION

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 PRE SB 36-1062 for A/C 217-218, 233-233, 240-240, 242-243 (Ref. 24-41-00-861-002-A). Energize the Aircraft Electrical Circuits from the External Power (Ref. 24-41-00-861-002-A-01). Energize the Aircraft Electrical Circuits from the APU (Ref. 24-41-00-861-002-A-02). Energize the Aircraft Electrical Circuits from Engine 1(2) (Ref. 24-41-00-862-002-A). De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 36-11-00-740-001-A). BITE Test of the BMC 1(2) ** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 3.

Job Set-up

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 PRE SB 36-1062 for A/C 217-218, 233-233, 240-240, 242-243 Subtask 36-11-00-861-141-A A.

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

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 Subtask 36-11-00-865-127-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 49VU 122VU 122VU

DESIGNATION AIR BLEED/X FEED/VALVE/BAT AIR BLEED/ENG 1/CTL AIR BLEED/ENG 1/MONG AIR BLEED/ENG 2/CTL AIR BLEED/ENG 2/MONG

FIN 2HV 3HA1 2HA1 3HA2 2HA2

LOCATION D13 D12 D11 Z23 Z22

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-807-A - Check of the CFDS to Make Sure that the Pylon Leak Detection and APU Leak Detection Loop Operates Correctly in LH Side PANEL 122VU

DESIGNATION AIR BLEED/X FEED VALVE/NORM

FIN 1HV

LOCATION Z20

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 PRE SB 36-1062 for A/C 217-218, 233-233, 240-240, 242-243 Subtask 36-11-00-860-109-A C.

Aircraft Maintenance Configuration (1) On the AIR COND panel: · Make sure that the ENG 1(2) BLEED pushbutton switches are pushed (OFF legends are off). · Make sure that the crossbleed selector switch is at AUTO position. · Make sure that the APU BLEED pushbutton switch is released (ON legend is off).

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 4.

Procedure

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 PRE SB 36-1062 for A/C 217-218, 233-233, 240-240, 242-243 Subtask 36-11-00-040-118-A A.

Check of the CFDS to Make Sure that the Pylon Leak Detection Operates Correctly (1) Do the BITE test of the BMC1 and BMC2 and print each TEST RESULT page (Ref. AMM TASK 3611-00-740-001) . (2) Make sure that the TEST RESULT pages do not show these maintenance messages: ATA 361100 361100 361134 362215 362217

MESSAGE CHECK BMC1 NO DATA FROM BMC1 BMC1 ENG1 PYLON LOOP INOP APU LOOP INOP OR BMC IDENT CKT

CLASS FAULT 2 2 2 2 2

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 5.

Close-up

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 PRE SB 36-1062 for A/C 217-218, 233-233, 240-240, 242-243 Subtask 36-11-00-862-124-A A.

Put the aircraft back to its initial configuration. (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-808-A - Check of the CFDS to Make Sure that the Pylon Leak Detection Operates Correctly in RH Side

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 TASK 36-11-00-040-808-A Check of the CFDS to Make Sure that the Pylon Leak Detection Operates Correctly in RH Side 1.

Reason for the Job MMEL 36-00-01C AIR BLEED MAINTENANCE Message MMEL 36-00-01C AIR BLEED MAINTENANCE Message

2

Job Set-up Information A.

Referenced Information REFERENCE

DESIGNATION

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 PRE SB 36-1062 for A/C 217-218, 233-233, 240-240, 242-243 (Ref. 24-41-00-861-002-A). Energize the Aircraft Electrical Circuits from the External Power (Ref. 24-41-00-861-002-A-01). Energize the Aircraft Electrical Circuits from the APU (Ref. 24-41-00-861-002-A-02). Energize the Aircraft Electrical Circuits from Engine 1(2) (Ref. 24-41-00-862-002-A). De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 36-11-00-740-001-A). BITE Test of the BMC 1(2) ** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 3.

Job Set-up

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 PRE SB 36-1062 for A/C 217-218, 233-233, 240-240, 242-243 Subtask 36-11-00-861-142-A A.

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

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 Subtask 36-11-00-865-128-A B.

Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU 49VU 49VU 122VU 122VU 122VU

DESIGNATION AIR BLEED/X FEED/VALVE/BAT AIR BLEED/ENG 1/CTL AIR BLEED/ENG 1/MONG AIR BLEED/ENG 2/CTL AIR BLEED/ENG 2/MONG AIR BLEED/X FEED VALVE/NORM

FIN 2HV 3HA1 2HA1 3HA2 2HA2 1HV

LOCATION D13 D12 D11 Z23 Z22 Z20

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-808-A - Check of the CFDS to Make Sure that the Pylon Leak Detection Operates Correctly in RH Side

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 PRE SB 36-1062 for A/C 217-218, 233-233, 240-240, 242-243 Subtask 36-11-00-860-110-A C.

Aircraft Maintenance Configuration (1) On the AIR COND panel: · Make sure that the ENG 1(2) BLEED pushbutton switches are pushed (OFF legends are off). · Make sure that the crossbleed selector switch is at AUTO position. · Make sure that the APU BLEED pushbutton switch is released (ON legend is off).

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 4.

Procedure

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 PRE SB 36-1062 for A/C 217-218, 233-233, 240-240, 242-243 Subtask 36-11-00-040-119-A A.

Check of the CFDS to Make Sure that the Pylon Leak Detection Operates Correctly (1) Do the BITE test of the BMC1 and BMC2 and print each TEST RESULT page (Ref. AMM TASK 3611-00-740-001) . (2) Make sure that the TEST RESULT pages do not show these maintenance messages: ATA 361100 361100 361134 362215

MESSAGE CHECK BMC2 NO DATA FROM BMC2 BMC2 ENG2 PYLON LOOP INOP

CLASS FAULT 2 2 2 2

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 5.

Close-up

** ON A/C 016-022, 024-026, 201-201, 203-207, 209-212, 215-222, 226-235, 237-237, 239-240, 242-250, 350-350 PRE SB 36-1062 for A/C 217-218, 233-233, 240-240, 242-243 Subtask 36-11-00-862-125-A A.

Put the aircraft back to its initial configuration. (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-803-A - Deactivation of the Bleed Valve

** ON A/C 301-349, 351-450, 500-600 TASK 36-11-00-040-803-A Deactivation of the Bleed Valve WARNING:

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

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 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:

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

1.

Reason for the Job MMEL 36-11-02A Engine Bleed Valve (PRV)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific

B.

QTY AR AR AR AR 1

DESIGNATION ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE PLACARD SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S) WRENCH - HEXAGONAL Torque wrench: range to between 0.4 and 0.5 m.daN (35.40 and 44.25 lbf.in)

Consumable Materials REFERENCE (Material No. 357500) (Material No. 357700)

DESIGNATION NEVERSEEZ REGULAR GRADE NEVER-SEEZ PURE NICKEL SPECIAL

C. Work Zones and Access Panels

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-803-A - Deactivation of the Bleed Valve

ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 437AL, 438AR, 452AR FOR 1000EM2 (ENGINE-2) 447AL, 448AR, 462AR

ZONE DESCRIPTION

D. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A). (Ref. 36-22-00-790-802-A). (Ref. 71-13-00-010-802-A). (Ref. 71-13-00-410-802-A). (Ref. 78-30-00-440-805-A). (Ref. 78-36-00-010-802-A). (Ref. 78-36-00-410-802-A). (Ref. 31-37-73-00-02). Bleed Valve SHEET 1

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) EIS Start Procedure EIS Stop Procedure Leak Check on all the Bleed Air Ducts and Packs Components Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Reactivation of the Thrust Reverser System after Ground Maintenance Opening of the Thrust Reverser Cowl-Doors Closing of the Thrust Reverser Cowl-Doors AIDS - ENGINE REPORTS - DESCRIPTION AND OPERATION

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-803-A - Deactivation of the Bleed Valve

A

B

4001HA

A

STORAGE PORT

C

LOCKING PIN

D

B

C

MANUAL OVERRIDE CONTROL LOCKING PIN

D N_MM_361100_4_UAM0_01_01

Figure 36-11-00-991-08900-21-A / SHEET 1/1 - Bleed Valve ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-803-A - Deactivation of the Bleed Valve

3.

Job Set-up Subtask 36-11-00-861-126-A A.

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

Subtask 36-11-00-860-094-A B.

Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860001) .

Subtask 36-11-00-941-129-A C.

Safety Precautions (1) Make sure that the ENG 1(2) shutdown occurred not less than five minutes before you do this procedure. (2) On the ENG panel 115VU: · Put a WARNING NOTICE(S) to tell persons not to start the ENG 1(2). (3) On the MAINTENANCE panel 50VU: · Make sure that the ON legend of the ENG/FADEC GND PWR 1(2) pushbutton switch is off. · Put a WARNING NOTICE(S) to tell persons not to operate the FADEC SYSTEM. (4) On the AIR COND panel 30VU: · Make sure that the ENG 1(2) BLEED pushbutton switch is released (the OFF legend is on). · Make sure that the APU BLEED pushbutton switch is released (the ON legend is off). · Put a WARNING NOTICE(S) to tell persons not to operate the pneumatic system. (5) On the HP ground connector: · Put a WARNING NOTICE(S) to tell persons not to pressurize the pneumatic system.

Subtask 36-11-00-865-095-A D.

Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 1000EM1 (ENGINE-1) 49VU AIR BLEED/APU BLEED VLV CTL/BMC1 OVRD 49VU AIR BLEED/X FEED/VALVE/BAT 49VU AIR BLEED/ENG 1/CTL 122VU AIR BLEED/ENG 1/MONG 122VU AIR BLEED/X FEED VALVE/NORM 122VU AIR BLEED/APU BLEED VLV CTL/BMC2 OVRD FOR FIN 1000EM2 (ENGINE-2) 49VU AIR BLEED/APU BLEED VLV CTL/BMC1 OVRD 49VU AIR BLEED/X FEED/VALVE/BAT 49VU AIR BLEED/ENG 2/MONG 122VU AIR BLEED/ENG 2/CTL 122VU AIR BLEED/X FEED VALVE/NORM 122VU AIR BLEED/APU BLEED VLV CTL/BMC2 OVRD

FIN

LOCATION

11HV

D14

2HV 2HA1 3HA1 1HV 12HV

D13 D11 Z23 Z20 Z19

11HV

D14

2HV 3HA2 2HA2 1HV 12HV

D13 D12 Z22 Z20 Z19

Subtask 36-11-00-010-151-A E.

Get Access

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-803-A - Deactivation of the Bleed Valve

(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-802) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR (2) Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position below the engine. Subtask 36-11-00-010-162-A F.

Open the right thrust-reverser cowl door (Ref. AMM TASK 78-36-00-010-802) : (1) FOR 1000EM1 (ENGINE-1) 452AR (2) FOR 1000EM2 (ENGINE-2) 462AR

4.

Procedure (Ref. Fig. Bleed Valve SHEET 1) Subtask 36-11-00-040-098-A A.

Deactivation of the Bleed Valve (4001HA) CAUTION:

CAREFULLY ALIGN THE LOCKING PIN WITH THE DEACTIVATING HOUSING ON THE VALVE. IF YOU ALIGN IT INCORRECTLY OR IF YOU TIGHTEN IT TOO MUCH, THE LOCKING PIN CAN REMAIN IN POSITION AND YOU CAN CAUSE DAMAGE TO THE LOCKING PIN THREAD.

(1) On the bleed valve (4001HA): (a) Use a WRENCH - HEXAGONAL to set the manual override control to the CLOSED position. (b) Use a WRENCH - HEXAGONAL to remove the locking pin from its storage port. (c) Apply NEVERSEEZ REGULAR GRADE (Material No. 357500) or NEVER-SEEZ PURE NICKEL SPECIAL (Material No. 357700) on the locking pin. (d) Lock the override control with the locking pin: 1

TORQUE the locking pin to between 0.4 and 0.5 m.daN (35.40 and 44.25 lbf.in).

(2) On the cockpit: (a) Put a PLACARD in the cockpit to tell the crew that the left (right) PRV is closed and deactivated. Subtask 36-11-00-790-067-A B.

Check of the Bleed Air Ducts (1) Get the post flight report (Ref. AMM D/O 31-37-73-00) . (a) If the class 1 fault message PRESS REG-V 4001HA1(2) and the ECAM warning AIR ENG 1(2) BLEED FAULT come into view during the flight phases 3, 4 or 5, get the ENG TAKE OFF REPORT on the MCDU and do a check of the pack values: 1

If the pack value is 00 or 01 (the pack was off during the last take off): a

Do the leak check of all the bleed air ducts and the pack components (Ref. AMM TASK 36-22-00-790-802) .

b

Do a visual inspection of the bleed air ducts and the equipment which are installed downstream of the Overpressure Valve (OPV) (along the pylon, wing and the center fuselage to the starter valves, flow control valves, wing anti-ice valves, HP ground

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-803-A - Deactivation of the Bleed Valve

connectors and the APU check valve but not the wing anti-ice ducting). Make sure that there is no deformation and be very careful when you do the check of the bellows. · If there is damage or deformation, repair or replace the damaged duct or equipment. 5.

Close-up Subtask 36-11-00-410-143-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the thrust-reverser cowl door (Ref. AMM TASK 78-36-00-410-802) : (a) FOR 1000EM1 (ENGINE-1) 452AR (b) FOR 1000EM2 (ENGINE-2) 462AR

Subtask 36-11-00-440-089-A B.

Make the thrust reverser serviceable (Ref. AMM TASK 78-30-00-440-805) .

Subtask 36-11-00-410-144-A C.

Close Access (1) Remove the access platform(s). (2) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-802) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR (3) Remove the WARNING NOTICE(S).

Subtask 36-11-00-865-096-A D.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 1000EM1 (ENGINE-1) 49VU AIR BLEED/APU BLEED VLV CTL/BMC1 OVRD 49VU AIR BLEED/X FEED/VALVE/BAT 49VU AIR BLEED/ENG 1/CTL 122VU AIR BLEED/ENG 1/MONG 122VU AIR BLEED/X FEED VALVE/NORM 122VU AIR BLEED/APU BLEED VLV CTL/BMC2 OVRD FOR FIN 1000EM2 (ENGINE-2) 49VU AIR BLEED/APU BLEED VLV CTL/BMC1 OVRD 49VU AIR BLEED/X FEED/VALVE/BAT 49VU AIR BLEED/ENG 2/MONG 122VU AIR BLEED/ENG 2/CTL 122VU AIR BLEED/X FEED VALVE/NORM 122VU AIR BLEED/APU BLEED VLV CTL/BMC2 OVRD

FIN

LOCATION

11HV

D14

2HV 2HA1 3HA1 1HV 12HV

D13 D11 Z23 Z20 Z19

11HV

D14

2HV 3HA2 2HA2 1HV 12HV

D13 D12 Z22 Z20 Z19

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-803-A - Deactivation of the Bleed Valve

Subtask 36-11-00-040-106-A E.

Deactivation of the Bleed Valve (1) On the ECAM control panel, push the BLEED key (on the lower ECAM DU, the BLEED page comes into view). (a) On the lower ECAM DU, on the BLEED page: · Make sure that the related bleed-valve symbol shows closed in amber.

Subtask 36-11-00-860-095-A F.

Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) .

Subtask 36-11-00-869-118-A G. Make an entry in the logbook. Subtask 36-11-00-862-112-A H.

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

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-804-A - Deactivation of the HP Bleed Valve

** ON A/C 301-349, 351-450, 500-600 TASK 36-11-00-040-804-A Deactivation of the HP Bleed Valve WARNING:

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

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 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:

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

1.

Reason for the Job MMEL 36-11-07B Engine Bleed HP Valve

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific

B.

QTY 1 AR AR 1

DESIGNATION ACCESS PLATFORM 1M(3 FT) SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S) WRENCH - HEXAGONAL Torque wrench: range to between 0.4 and 0.5 m.daN (35.40 and 44.25 lbf.in)

Consumable Materials REFERENCE (Material No. 357500) (Material No. 357700)

DESIGNATION NEVERSEEZ REGULAR GRADE NEVER-SEEZ PURE NICKEL SPECIAL

C. Work Zones and Access Panels

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-804-A - Deactivation of the HP Bleed Valve

ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 437AL, 438AR, 452AR FOR 1000EM2 (ENGINE-2) 447AL, 448AR, 462AR

ZONE DESCRIPTION

D. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 31-60-00-860-001-A). EIS Start Procedure (Ref. 31-60-00-860-002-A). EIS Stop Procedure (Ref. 71-13-00-010-802-A). Opening of the Fan Cowl Doors (Ref. 71-13-00-410-802-A). Closing of the Fan Cowl Doors (Ref. 78-36-00-010-802-A). Opening of the Thrust Reverser Cowl-Doors (Ref. 78-36-00-410-802-A). Closing of the Thrust Reverser Cowl-Doors High Pressure Regulator Valve SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-804-A - Deactivation of the HP Bleed Valve

A

B

C

4000HA

A LOCKING PIN

D

MANUAL OVERRIDE CONTROL

B

C

LOCKING PIN

STORAGE PORT

D N_MM_361100_4_UCM0_01_01

Figure 36-11-00-991-09000-21-A / SHEET 1/1 - High Pressure Regulator Valve ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-804-A - Deactivation of the HP Bleed Valve

3.

Job Set-up Subtask 36-11-00-861-127-A A.

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

Subtask 36-11-00-860-096-A B.

Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) .

Subtask 36-11-00-941-130-A C.

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 panel 30VU: · Make sure that the ENG 1(2) BLEED pushbutton switch is released (the OFF legend is on) · Make sure that the APU BLEED pushbutton switch is released (the ON legend is off) · Put a WARNING NOTICE(S) to tell persons not to operate the pneumatic system. (3) On the ENG panel 115VU: · Put a WARNING NOTICE(S) to tell persons not to start the engine 1(2). (4) On the HP ground connector: · put a WARNING NOTICE(S) to tell persons not to pressurize the pneumatic system. (5) On the MAINTENANCE panel 50VU: · Make sure that the ON legend of the ENG/FADEC GND PWR 1(2) pushbutton switch is off. · Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).

Subtask 36-11-00-865-120-A D.

Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 1000EM1 (ENGINE-1) 49VU AIR BLEED/APU BLEED VLV CTL/BMC1 OVRD 49VU AIR BLEED/X FEED/VALVE/BAT 49VU AIR BLEED/ENG 1/CTL 122VU AIR BLEED/ENG 1/MONG 122VU AIR BLEED/X FEED VALVE/NORM 122VU AIR BLEED/APU BLEED VLV CTL/BMC2 OVRD FOR FIN 1000EM2 (ENGINE-2) 49VU AIR BLEED/APU BLEED VLV CTL/BMC1 OVRD 49VU AIR BLEED/X FEED/VALVE/BAT 49VU AIR BLEED/ENG 2/MONG 122VU AIR BLEED/ENG 2/CTL 122VU AIR BLEED/X FEED VALVE/NORM 122VU AIR BLEED/APU BLEED VLV CTL/BMC2 OVRD

FIN

LOCATION

11HV

D14

2HV 2HA1 3HA1 1HV 12HV

D13 D11 Z23 Z20 Z19

11HV

D14

2HV 3HA2 2HA2 1HV 12HV

D13 D12 Z22 Z20 Z19

Subtask 36-11-00-010-152-A E.

Get Access

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-804-A - Deactivation of the HP Bleed Valve

(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-802) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR. (2) Put a ACCESS PLATFORM 1M(3 FT) in position. Subtask 36-11-00-010-153-A F.

Open the right thrust reverser cowl door (Ref. AMM TASK 78-36-00-010-802) : (1) FOR 1000EM1 (ENGINE-1) 452AR (2) FOR 1000EM2 (ENGINE-2) 462AR.

4.

Procedure (Ref. Fig. High Pressure Regulator Valve SHEET 1) Subtask 36-11-00-040-100-A A.

Deactivation of the HP Bleed Valve (HPV) (4000HA) CAUTION:

CAREFULLY ALIGN THE LOCKING PIN WITH THE DEACTIVATING HOUSING ON THE VALVE. IF YOU ALIGN IT INCORRECTLY OR IF YOU TIGHTEN IT TOO MUCH, THE LOCKING PIN CAN REMAIN IN POSITION AND YOU CAN CAUSE DAMAGE TO THE LOCKING PIN THREAD.

(1) On the HPV (4000HA): (a) Use a WRENCH - HEXAGONAL to set the manual override control to the CLOSED position. (b) Use a WRENCH - HEXAGONAL to remove the locking pin from its storage port. (c) Apply NEVERSEEZ REGULAR GRADE (Material No. 357500) or NEVER-SEEZ PURE NICKEL SPECIAL (Material No. 357700) on the locking pin. (d) Lock the manual override control with the locking pin. 1 5.

TORQUE the locking pin to between 0.4 and 0.5 m.daN (35.40 and 44.25 lbf.in).

Close-up Subtask 36-11-00-410-145-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the right thrust-reverser cowl door (Ref. AMM TASK 78-36-00-410-802) : (a) FOR 1000EM1 (ENGINE-1) 452AR (b) FOR 1000EM2 (ENGINE-2) 462AR.

Subtask 36-11-00-410-146-A B.

Close Access (1) Remove the access platform(s). (2) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-802) : (a) FOR 1000EM1 (ENGINE-1)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-804-A - Deactivation of the HP Bleed Valve

437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR. (3) Remove the WARNING NOTICE(S). Subtask 36-11-00-865-126-A C.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 1000EM1 (ENGINE-1) 49VU AIR BLEED/APU BLEED VLV CTL/BMC1 OVRD 49VU AIR BLEED/X FEED/VALVE/BAT 49VU AIR BLEED/ENG 1/CTL 122VU AIR BLEED/ENG 1/MONG 122VU AIR BLEED/X FEED VALVE/NORM 122VU AIR BLEED/APU BLEED VLV CTL/BMC2 OVRD FOR FIN 1000EM2 (ENGINE-2) 49VU AIR BLEED/APU BLEED VLV CTL/BMC1 OVRD 49VU AIR BLEED/X FEED/VALVE/BAT 49VU AIR BLEED/ENG 2/MONG 122VU AIR BLEED/ENG 2/CTL 122VU AIR BLEED/X FEED VALVE/NORM 122VU AIR BLEED/APU BLEED VLV CTL/BMC2 OVRD

FIN

LOCATION

11HV

D14

2HV 2HA1 3HA1 1HV 12HV

D13 D11 Z23 Z20 Z19

11HV

D14

2HV 3HA2 2HA2 1HV 12HV

D13 D12 Z22 Z20 Z19

Subtask 36-11-00-040-136-A D.

Deactivation of the HPV (1) On the ECAM control panel, push the BLEED key (on the lower ECAM DU, the BLEED page comes into view). (a) On the lower ECAM DU, on the BLEED page: · Make sure that the related bleed-valve symbol shows closed in amber.

Subtask 36-11-00-860-097-A E.

Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) .

Subtask 36-11-00-869-119-A F.

Make an entry in the logbook.

Subtask 36-11-00-862-113-A G. De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-806-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

** ON A/C 301-349, 351-450, 500-600 TASK 36-11-00-040-806-A Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve WARNING:

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

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 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:

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

1.

Reason for the Job MMEL 36-11-06B Engine Bleed IP Check Valve

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific

B.

QTY AR AR AR 1

DESIGNATION ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S) WRENCH - HEXAGONAL Torque wrench: range to between 0.4 and 0.5 m.daN (35.40 and 44.25 lbf.in)

Consumable Materials REFERENCE (Material No. 357500) (Material No. 357700)

DESIGNATION NEVERSEEZ REGULAR GRADE NEVER-SEEZ PURE NICKEL SPECIAL

C. Work Zones and Access Panels

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-806-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 437AL, 438AR, 452AR FOR 1000EM2 (ENGINE-2) 447AL, 448AR, 462AR

ZONE DESCRIPTION

D. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 31-60-00-860-001-A). EIS Start Procedure (Ref. 31-60-00-860-002-A). EIS Stop Procedure (Ref. 71-13-00-010-802-A). Opening of the Fan Cowl Doors (Ref. 71-13-00-410-802-A). Closing of the Fan Cowl Doors (Ref. 78-30-00-440-805-A). Reactivation of the Thrust Reverser System after Ground Maintenance (Ref. 78-36-00-010-802-A). Opening of the Thrust Reverser Cowl-Doors (Ref. 78-36-00-410-802-A). Closing of the Thrust Reverser Cowl-Doors High Pressure Regulator Valve SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-806-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

A

B

C

4000HA

A LOCKING PIN

D

MANUAL OVERRIDE CONTROL

B

C

LOCKING PIN

STORAGE PORT

D N_MM_361100_4_UCM0_01_01

Figure 36-11-00-991-09000-21-A / SHEET 1/1 - High Pressure Regulator Valve ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-806-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

3.

Job Set-up Subtask 36-11-00-861-133-A A.

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

Subtask 36-11-00-860-103-A B.

Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) .

Subtask 36-11-00-941-135-A C.

Safety Precautions (1) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (2) On the AIR COND panel 30VU: · Make sure that the ENG 1(2) BLEED pushbutton switch is released (the OFF legend is on). · Make sure that the APU BLEED pushbutton switch is released (the ON legend is off). · Put a WARNING NOTICE(S) in position to tell persons not to operate the pneumatic system. (3) On the ENG panel 115VU: · Put a WARNING NOTICE(S) in position to tell persons not to start the 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 the maintenance panel 50VU: · Make sure that the ON legend of the ENG/FADEC GND PWR 1(2) pushbutton switch is off. · Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

Subtask 36-11-00-865-112-A D.

Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 1000EM1 (ENGINE-1) 49VU AIR BLEED/APU BLEED VLV CTL/BMC1 OVRD 49VU AIR BLEED/X FEED/VALVE/BAT 49VU AIR BLEED/ENG 1/CTL 122VU AIR BLEED/ENG 1/MONG 122VU AIR BLEED/X FEED VALVE/NORM 122VU AIR BLEED/APU BLEED VLV CTL/BMC2 OVRD FOR FIN 1000EM2 (ENGINE-2) 49VU AIR BLEED/APU BLEED VLV CTL/BMC1 OVRD 49VU AIR BLEED/X FEED/VALVE/BAT 49VU AIR BLEED/ENG 2/MONG 122VU AIR BLEED/ENG 2/CTL 122VU AIR BLEED/X FEED VALVE/NORM 122VU AIR BLEED/APU BLEED VLV CTL/BMC2 OVRD

FIN

LOCATION

11HV

D14

2HV 2HA1 3HA1 1HV 12HV

D13 D11 Z23 Z20 Z19

11HV

D14

2HV 3HA2 2HA2 1HV 12HV

D13 D12 Z22 Z20 Z19

Subtask 36-11-00-010-163-A E.

Get Access

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-806-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-802) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR. (2) Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position below the engine. Subtask 36-11-00-010-164-A F.

Open the right thrust reverser cowl door (Ref. AMM TASK 78-36-00-010-802) : (1) FOR 1000EM1 (ENGINE-1) 452AR (2) FOR 1000EM2 (ENGINE-2) 462AR.

4.

Procedure (Ref. Fig. High Pressure Regulator Valve SHEET 1) Subtask 36-11-00-040-109-A A.

Deactivation of the IP Bleed Check Valve CAUTION:

CAREFULLY ALIGN THE LOCKING PIN WITH THE DEACTIVATING HOUSING ON THE VALVE. IF YOU ALIGN IT INCORRECTLY OR IF YOU TIGHTEN IT TOO MUCH, THE LOCKING PIN CAN REMAIN IN POSITION AND YOU CAN CAUSE DAMAGE TO THE LOCKING PIN THREAD.

(1) On the HPV (4000HA): (a) Use a WRENCH - HEXAGONAL to set the manual override control to the CLOSED position. (b) Use a WRENCH - HEXAGONAL to remove the locking pin from its storage port. (c) Apply NEVERSEEZ REGULAR GRADE (Material No. 357500) or NEVER-SEEZ PURE NICKEL SPECIAL (Material No. 357700) on the locking pin. (d) Lock this override control with the locking pin. (e) TORQUE the locking pin to between 0.4 and 0.5 m.daN (35.40 and 44.25 lbf.in). 5.

Close-up Subtask 36-11-00-410-155-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the right thrust-reverser cowl door (Ref. AMM TASK 78-36-00-410-802) : (a) FOR 1000EM1 (ENGINE-1) 452AR (b) FOR 1000EM2 (ENGINE-2) 462AR.

Subtask 36-11-00-440-098-A B.

Make the thrust reverser serviceable (Ref. AMM TASK 78-30-00-440-805) .

Subtask 36-11-00-410-156-A C.

Close Access (1) Remove the access platform(s).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-11-00-040-806-A - Deactivation of the HP Bleed Valve in the CLOSED Position to Isolate the IP Bleed Check-Valve

(2) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-802) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR. (3) Remove the WARNING NOTICE(S). Subtask 36-11-00-865-113-A D.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 1000EM1 (ENGINE-1) 49VU AIR BLEED/APU BLEED VLV CTL/BMC1 OVRD 49VU AIR BLEED/X FEED/VALVE/BAT 49VU AIR BLEED/ENG 1/CTL 122VU AIR BLEED/ENG 1/MONG 122VU AIR BLEED/X FEED VALVE/NORM 122VU AIR BLEED/APU BLEED VLV CTL/BMC2 OVRD FOR FIN 1000EM2 (ENGINE-2) 49VU AIR BLEED/APU BLEED VLV CTL/BMC1 OVRD 49VU AIR BLEED/X FEED/VALVE/BAT 49VU AIR BLEED/ENG 2/MONG 122VU AIR BLEED/ENG 2/CTL 122VU AIR BLEED/X FEED VALVE/NORM 122VU AIR BLEED/APU BLEED VLV CTL/BMC2 OVRD

FIN

LOCATION

11HV

D14

2HV 2HA1 3HA1 1HV 12HV

D13 D11 Z23 Z20 Z19

11HV

D14

2HV 3HA2 2HA2 1HV 12HV

D13 D12 Z22 Z20 Z19

Subtask 36-11-00-040-137-A E.

Deactivation of the HPV to isolate the IPCV (1) On the ECAM control panel, push the BLEED key (on the lower ECAM DU, the BLEED page comes into view). (a) On the lower ECAM DU, on the BLEED page: · Make sure that the related bleed-valve symbol shows closed in amber.

Subtask 36-11-00-860-104-A F.

Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) .

Subtask 36-11-00-869-123-A G. Make an entry in the logbook. Subtask 36-11-00-862-118-A H.

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

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-12-00-040-801-A - Deactivation of the APU Bleed Check-Valve

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 TASK 36-12-00-040-801-A Deactivation of the APU Bleed Check-Valve WARNING:

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

FIN : 7260HM 1.

Reason for the Job MMEL 36-22-03A APU Leak Detection Loop

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

QTY 1 AR AR

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S) Torque wrench: range to between 0.4 and 0.5 m.daN (35.40 and 44.25 lbf.in)

Work Zones and Access Panels ZONE/ACCESS 151CW, 151SW, 197BB

ZONE DESCRIPTION

C. Expendable Parts FIG.ITEM 10

DESIGNATION blanking cap

IPC-CSN 36-12-03-28-260

D. Referenced Information REFERENCE (Ref. 12-33-21-618-001-A-02). (Ref. 36-22-17-000-001-A). (Ref. 36-22-17-400-001-A). (Ref. 52-30-00-860-001-A). (Ref. 52-30-00-860-002-A).

DESIGNATION Pre-conditioning with the APU Removal of the APU Overheat Sensing-Elements Installation of the APU Overheat Sensing-Elements Open the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump Close the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump

AIPC 36120328 APU Bleed Check-Valve - Blanking Cap SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-12-00-040-801-A - Deactivation of the APU Bleed Check-Valve

Z190

197BB

A

10

1

2

9

8 7 x8 6 5 3

4

A N_MM_361200_4_AAN0_01_00

Figure 36-12-00-991-01200-00-A / SHEET 1/1 - APU Bleed Check-Valve - Blanking Cap ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-12-00-040-801-A - Deactivation of the APU Bleed Check-Valve

3.

Job Set-up Subtask 36-12-00-860-096-A A.

Aircraft Maintenance Configuration (1) Put the WARNING NOTICE(S) in position: · In the cockpit, on engine control panel 115VU, to tell persons not to start the engine(s) · In the cockpit, on AIR COND overhead control panel 30VU, to tell persons not to push the APU BLEED pushbutton switch · On the HP ground connector, to tell persons not to pressurize the pneumatic system.

Subtask 36-12-00-010-066-A B.

Get Access (1) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below access panel 197BB. (2) Remove access panel 197BB. (3) Open the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-001) . (4) In the aft cargo compartment, remove the sidewall panel: (a) If installed, remove sidewall panel 151CW, or (b) If installed, remove sidewall panel 151SW.

Subtask 36-12-00-865-089-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU 49VU 49VU 122VU 122VU 122VU

4.

DESIGNATION AIR BLEED/X FEED/VALVE/BAT AIR BLEED/ENG 1/CTL AIR BLEED/ENG 1/MONG AIR BLEED/ENG 2/CTL AIR BLEED/ENG 2/MONG AIR BLEED/X FEED VALVE/NORM

FIN 2HV 3HA1 2HA1 3HA2 2HA2 1HV

LOCATION D13 D12 D11 Z23 Z22 Z20

Procedure (Ref. Fig. APU Bleed Check-Valve - Blanking Cap SHEET 1) Subtask 36-12-00-020-063-A A.

Deactivation of the APU Bleed Check-Valve NOTE: Refer to AIPC 36120328 for the IPC -CSN (36-12-03-28-260) blanking cap (10) of the APU bleed check-valve (6) to do the procedure. (1) Disengage the overheat sensing elements that are near the APU bleed check-valve (6) from the ducts (9) and (4) (Ref. AMM TASK 36-22-17-000-001) . (2) Loosen the nut of the clamp (3) and remove the clamp (3). (3) Loosen the nut of the clamp (8) and remove the clamp (8). (4) Remove the nuts (2) and the washers (1). (5) Hold the APU bleed check-valve (6) and remove the bolts (7). (6) Remove the APU bleed check-valve (6) and the seal (5). (7) Make sure that no parts of the APU bleed check-valve (6) are missing (flaps, shaft and spring) when you remove it. If part(s) is (are) missing:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-12-00-040-801-A - Deactivation of the APU Bleed Check-Valve

· Do an inspection of the APU bleed-air system and the air conditioning system to find this (these) parts before you install the blanking cap (10). (8) Put the blanking cap (10) with the seal (5) in position. (9) Install the bolts (7), washers (1) and nuts (2). (10) Tighten the nuts (2). (11) Install the clamps (3) and (8). (12) TORQUE the nuts of the clamps (3) and (8) to between 0.4 and 0.5 m.daN (35.40 and 44.25 lbf.in). (13) Attach the overheat sensing elements that are near the APU bleed check-valve (6) to the ducts (9) and (4) (Ref. AMM TASK 36-22-17-400-001) . Subtask 36-12-00-865-090-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU 49VU 49VU 122VU 122VU 122VU

DESIGNATION AIR BLEED/X FEED/VALVE/BAT AIR BLEED/ENG 1/CTL AIR BLEED/ENG 1/MONG AIR BLEED/ENG 2/CTL AIR BLEED/ENG 2/MONG AIR BLEED/X FEED VALVE/NORM

FIN 2HV 3HA1 2HA1 3HA2 2HA2 1HV

LOCATION D13 D12 D11 Z23 Z22 Z20

Subtask 36-12-00-710-062-A C.

Leak Test of the Pneumatic Connections (1) Do the ground air pre-conditioning with the APU (Ref. AMM TASK 12-33-21-618-001) . (2) Make sure that there are no leaks between the connections of the blanking cap (10) and the ducts (4) and (9).

5.

Close-up Subtask 36-12-00-410-066-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install access panel 197BB. (3) In the aft cargo compartment, install the sidewall panel: (a) If removed, install sidewall panel 151CW, or (b) If removed, install sidewall panel 151SW. (4) Close the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-002) .

Subtask 36-12-00-860-098-A B.

Aircraft Maintenance Configuration (1) Put the aircraft back to the serviceable condition. (2) Remove the WARNING NOTICE(S). (3) Remove the access platform(s). (4) Make an entry in the logbook.

End of document Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-12-00-040-804-A - Inspection of the APU Bleed Check-Valve for Correct Condition

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 TASK 36-12-00-040-804-A Inspection of the APU Bleed Check-Valve for Correct Condition 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 USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

FIN : 7260HM 1.

Reason for the Job MMEL 36-22-03E APU Leak Detection Loop

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

QTY 1 AR AR

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. 14FAB1)

DESIGNATION Abrasive-- Scotch Brite Pads -

C. Work Zones and Access Panels ZONE/ACCESS 152 197BB

ZONE DESCRIPTION AFT CARGO COMPARTMENT

D. Referenced Information REFERENCE DESIGNATION (Ref. 36-12-51-000-001-A). Removal of the APU Bleed Check-Valve (Ref. 36-12-51-400-001-A). Installation of the APU Bleed Check-Valve APU Bleed Check-Valve SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-12-00-040-804-A - Inspection of the APU Bleed Check-Valve for Correct Condition

APU BLEED CHECK-VALVE 7260HM

HINGE PIN

SPRING

INTAKE RING

FLAPS

0.7619 mm (0.030 in)

N_MM_361200_4_AAM0_01_01

Figure 36-12-00-991-00800-00-A / SHEET 1/1 - APU Bleed Check-Valve ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 | EMB SB 31-1197 for A/C 231-232, 237-237, 244-244 | EMB SB 31-1257 for A/ C 201-201, 203-205, 207-207, 210-211, 233-233, 240-240, 243-243 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-12-00-040-804-A - Inspection of the APU Bleed Check-Valve for Correct Condition

3.

Job Set-up Subtask 36-12-00-865-083-A A.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU 49VU 49VU 122VU 122VU 122VU

DESIGNATION AIR BLEED/X FEED/VALVE/BAT AIR BLEED/ENG 1/CTL AIR BLEED/ENG 1/MONG AIR BLEED/ENG 2/CTL AIR BLEED/ENG 2/MONG AIR BLEED/X FEED VALVE/NORM

FIN 2HV 3HA1 2HA1 3HA2 2HA2 1HV

LOCATION D13 D12 D11 Z23 Z22 Z20

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 EMB SB 31-1197 for A/C 231-232, 237-237, 244-244 EMB SB 31-1257 for A/C 201-201, 203-205, 207-207, 210-211, 233-233, 240-240, 243-243 Subtask 36-12-00-860-090-A B.

Safety Precautions (1) On AIR COND panel 30VU: · Make sure that the ENG 1(2) BLEED pushbutton switch is pushed (OFF legend off). · Make sure that the APU BLEED pushbutton switch is released (ON legend off). · Put a WARNING NOTICE(S) in position to tell persons not to operate the pneumatic system. (2) On ENG panel 115VU: · Put a WARNING NOTICE(S) in position to tell persons not to start engine 1(2). (3) On the HP ground connector: · Put a WARNING NOTICE(S) in position to tell persons not to pressurize the pneumatic system.

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 36-12-00-010-063-A C.

Get Access (1) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position. (2) Remove access panel 197BB.

4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 EMB SB 31-1197 for A/C 231-232, 237-237, 244-244 EMB SB 31-1257 for A/C 201-201, 203-205, 207-207, 210-211, 233-233, 240-240, 243-243 (Ref. Fig. APU Bleed Check-Valve SHEET 1) Subtask 36-12-00-220-050-A A.

Detailed Inspection of the APU Bleed Check-Valve (1) Remove the APU bleed check-valve from its position (Ref. AMM TASK 36-12-51-000-001) . (2) Make sure that the APU bleed check-valve is in the correct condition: (a) Make sure that no parts are missing (flaps, hinge pin and/or spring). 1

If one or more part(s) is (are) missing:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-12-00-040-804-A - Inspection of the APU Bleed Check-Valve for Correct Condition

· Do a visual inspection of the APU bleed-air system and the air conditioning system to find and remove this (these) parts. Then replace the APU bleed check-valve (Ref. AMM TASK 36-12-51-400-001) . (b) Make sure that there are no cracks, dents, corrosion or wear by friction. 1

If the flaps and/or the stop on the APU bleed check-valve are worn: · Remove the signs of wear with a Abrasive-- Scotch Brite Pads - (Material No. 14FAB1).

(c) With your hand, make sure that the flaps open and close freely without stops. (d) Measure the play between the valve flaps and the intake ring in the radial direction. 1

Make sure that the play is not more than 0.7619 mm (0.030 in.).

(3) If the APU bleed check-valve is in the correct condition: · Install the APU bleed check-valve (Ref. AMM TASK 36-12-51-400-001) . (4) If the APU bleed check-valve is not in the correct condition: · Replace the APU bleed check-valve (Ref. AMM TASK 36-12-51-400-001) . ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 5.

Close-up Subtask 36-12-00-410-063-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install access panel 197BB. (3) Remove the access platform(s).

Subtask 36-12-00-865-084-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU 49VU 49VU 122VU 122VU 122VU

DESIGNATION AIR BLEED/X FEED/VALVE/BAT AIR BLEED/ENG 1/CTL AIR BLEED/ENG 1/MONG AIR BLEED/ENG 2/CTL AIR BLEED/ENG 2/MONG AIR BLEED/X FEED VALVE/NORM

FIN 2HV 3HA1 2HA1 3HA2 2HA2 1HV

LOCATION D13 D12 D11 Z23 Z22 Z20

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 EMB SB 31-1197 for A/C 231-232, 237-237, 244-244 EMB SB 31-1257 for A/C 201-201, 203-205, 207-207, 210-211, 233-233, 240-240, 243-243 Subtask 36-12-00-860-091-A C.

Aircraft Maintenance Configuration (1) Remove the WARNING NOTICE(S).

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-12-00-040-802-A - Deactivation of the APU Bleed Check-Valve

** ON A/C 301-349, 351-450, 500-600 TASK 36-12-00-040-802-A Deactivation of the APU Bleed Check-Valve WARNING:

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

FIN : 7260HM 1.

Reason for the Job MMEL 36-22-03A APU Leak Detection Loop

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

QTY 1 AR AR

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S) Torque wrench: range to between 0.4 and 0.5 m.daN (35.40 and 44.25 lbf.in)

Work Zones and Access Panels ZONE/ACCESS 151CW, 151SW, 197BB, 197KB

ZONE DESCRIPTION

C. Expendable Parts FIG.ITEM 10

DESIGNATION blanking cap

IPC-CSN 36-12-83-03-600

D. Referenced Information REFERENCE (Ref. 12-33-21-618-001-A-02). (Ref. 36-22-17-000-001-A). (Ref. 36-22-17-400-001-A). (Ref. 52-30-00-860-001-A). (Ref. 52-30-00-860-002-A).

DESIGNATION Pre-conditioning with the APU Removal of the APU Overheat Sensing-Elements Installation of the APU Overheat Sensing-Elements Open the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump Close the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump

AIPC 36128303 APU Bleed Check-Valve - Blanking Cap SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-12-00-040-802-A - Deactivation of the APU Bleed Check-Valve

Z190 197BB 01 197KB 02

A 10

1

2

9

8 7 x8 6

5 3

4

A NOTE: 01 FOR A319NEO AND A320NEO. 02 FOR A321NEO.

N_MM_361200_4_UAM0_01_01

Figure 36-12-00-991-00600-21-A / SHEET 1/1 - APU Bleed Check-Valve - Blanking Cap ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-12-00-040-802-A - Deactivation of the APU Bleed Check-Valve

3.

Job Set-up Subtask 36-12-00-860-069-A A.

Aircraft Maintenance Configuration (1) Put the WARNING NOTICE(S) in position: · In the cockpit, on engine control panel 115VU, to tell persons not to start the engine(s) · In the cockpit, on AIR COND overhead control panel 30VU, to tell persons not to push the APU BLEED pushbutton switch · On the HP ground connector, to tell persons not to pressurize the pneumatic system.

Subtask 36-12-00-010-056-A B.

Get Access (1) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position. (2) Remove access panel: (a) If installed, remove access panel 197BB (b) If installed, remove access panel 197KB. (3) Open the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-001) . (4) In the aft cargo compartment, remove the sidewall panel: (a) If installed, remove sidewall panel 151CW, or (b) If installed, remove sidewall panel 151SW.

Subtask 36-12-00-865-060-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU 49VU 49VU 122VU 122VU 122VU

4.

DESIGNATION AIR BLEED/X FEED/VALVE/BAT AIR BLEED/ENG 2/MONG AIR BLEED/ENG 1/CTL AIR BLEED/ENG 1/MONG AIR BLEED/ENG 2/CTL AIR BLEED/X FEED VALVE/NORM

FIN 2HV 3HA2 2HA1 3HA1 2HA2 1HV

LOCATION D13 D12 D11 Z23 Z22 Z20

Procedure (Ref. Fig. APU Bleed Check-Valve - Blanking Cap SHEET 1) Subtask 36-12-00-020-050-A A.

Deactivation of the APU Bleed Check-Valve NOTE: Refer to AIPC 36128303 for the IPC -CSN (36-12-83-03-600) blanking cap (10) of the APU bleed check-valve (6) to do the procedure. (1) Disengage the overheat sensing elements that are near the APU bleed check-valve (6) from the ducts (9) and (4) (Ref. AMM TASK 36-22-17-000-001) . (2) Loosen the nut of the clamp (3) and remove the clamp (3). (3) Loosen the nut of the clamp (8) and remove the clamp (8). (4) Remove the nuts (2) and the washers (1). (5) Hold the APU bleed check-valve (6) and remove the bolts (7). (6) Remove the APU bleed check-valve (6) and the seal (5).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-12-00-040-802-A - Deactivation of the APU Bleed Check-Valve

(7) Make sure that no parts of the APU bleed check-valve (6) are missing (flaps, shaft and spring) when you remove it. If part(s) is (are) missing: · Do an inspection of the APU bleed-air system and the air conditioning system to find this (these) parts before you install the blanking cap (10). (8) Put the blanking cap (10) with the seal (5) in position. (9) Install the bolts (7), washers (1) and nuts (2). (10) Tighten the nuts (2). (11) Install the clamps (3) and (8). (12) TORQUE the nuts of the clamps (3) and (8) to between 0.4 and 0.5 m.daN (35.40 and 44.25 lbf.in). (13) Attach the overheat sensing elements that are near the APU bleed check-valve (6) to the ducts (9) and (4) (Ref. AMM TASK 36-22-17-400-001) . Subtask 36-12-00-865-061-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU 49VU 49VU 122VU 122VU 122VU

DESIGNATION AIR BLEED/X FEED/VALVE/BAT AIR BLEED/ENG 2/MONG AIR BLEED/ENG 1/CTL AIR BLEED/ENG 1/MONG AIR BLEED/ENG 2/CTL AIR BLEED/X FEED VALVE/NORM

FIN 2HV 3HA2 2HA1 3HA1 2HA2 1HV

LOCATION D13 D12 D11 Z23 Z22 Z20

Subtask 36-12-00-710-057-A C.

Leak Test of the Pneumatic Connections (1) Do the ground air pre-conditioning with the APU (Ref. AMM TASK 12-33-21-618-001) . (2) Make sure that there are no leaks between the connections of the blanking cap (10) and the ducts (4) and (9).

5.

Close-up Subtask 36-12-00-410-056-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install access panel: (a) If removed, install access panel 197BB (b) If removed, install access panel 197KB. (3) In the aft cargo compartment, install the sidewall panel: (a) If removed, install sidewall panel 151CW, or (b) If removed, install sidewall panel 151SW. (4) Close the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-002) .

Subtask 36-12-00-942-051-A B.

Aircraft Maintenance Configuration (1) Put the aircraft back to the serviceable condition. (2) Remove the WARNING NOTICE(S).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-12-00-040-802-A - Deactivation of the APU Bleed Check-Valve

(3) Remove the access platform(s). (4) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-12-00-040-805-A - Inspection of the APU Bleed Check-Valve for Correct Condition

** ON A/C 301-349, 351-450, 500-600 TASK 36-12-00-040-805-A Inspection of the APU Bleed Check-Valve for Correct Condition 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 USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

FIN : 7260HM 1.

Reason for the Job MMEL 36-22-03E APU Leak Detection Loop

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

QTY 1 AR AR

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. 14FAB1)

DESIGNATION Abrasive-- Scotch Brite Pads -

C. Work Zones and Access Panels ZONE/ACCESS 152 197BB

ZONE DESCRIPTION AFT CARGO COMPARTMENT

D. Referenced Information REFERENCE DESIGNATION (Ref. 36-12-51-000-001-A). Removal of the APU Bleed Check-Valve (Ref. 36-12-51-400-001-A). Installation of the APU Bleed Check-Valve APU Bleed Check-Valve SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-12-00-040-805-A - Inspection of the APU Bleed Check-Valve for Correct Condition

APU BLEED CHECK-VALVE 7260HM

HINGE PIN

SPRING

INTAKE RING

FLAPS

0.7619 mm (0.030 in)

N_MM_361200_4_UBM0_01_01

Figure 36-12-00-991-00900-21-A / SHEET 1/1 - APU Bleed Check-Valve ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-12-00-040-805-A - Inspection of the APU Bleed Check-Valve for Correct Condition

3.

Job Set-up Subtask 36-12-00-865-085-A A.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU 49VU 49VU 122VU 122VU 122VU

DESIGNATION AIR BLEED/X FEED/VALVE/BAT AIR BLEED/ENG 2/MONG AIR BLEED/ENG 1/CTL AIR BLEED/ENG 1/MONG AIR BLEED/ENG 2/CTL AIR BLEED/X FEED VALVE/NORM

FIN 2HV 3HA2 2HA1 3HA1 2HA2 1HV

LOCATION D13 D12 D11 Z23 Z22 Z20

Subtask 36-12-00-860-092-A B.

Safety Precautions (1) On AIR COND panel 30VU: · Make sure that the ENG 1(2) BLEED pushbutton switch is pushed (OFF legend off). · Make sure that the APU BLEED pushbutton switch is released (ON legend off). · Put a WARNING NOTICE(S) in position to tell persons not to operate the pneumatic system. (2) On ENG panel 115VU: · Put a WARNING NOTICE(S) in position to tell persons not to start engine 1(2). (3) On the HP ground connector: · Put a WARNING NOTICE(S) in position to tell persons not to pressurize the pneumatic system.

Subtask 36-12-00-010-064-A C.

Get Access (1) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position. (2) Remove access panel 197BB.

4.

Procedure (Ref. Fig. APU Bleed Check-Valve SHEET 1) Subtask 36-12-00-220-051-A A.

Detailed Inspection of the APU Bleed Check-Valve (1) Remove the APU bleed check-valve from its position (Ref. AMM TASK 36-12-51-000-001) . (2) Make sure that the APU bleed check-valve is in the correct condition: (a) Make sure that no parts are missing (flaps, hinge pin and/or spring). 1

If one or more part(s) is (are) missing: · Do a visual inspection of the APU bleed-air system and the air conditioning system to find and remove this (these) parts. Then replace the APU bleed check-valve (Ref. AMM TASK 36-12-51-400-001) .

(b) Make sure that there are no cracks, dents, corrosion or wear by friction. 1

If the flaps and/or the stop on the APU bleed check-valve are worn: · Remove the signs of wear with a Abrasive-- Scotch Brite Pads - (Material No. 14FAB1).

(c) With your hand, make sure that the flaps open and close freely without stops. (d) Measure the play between the valve flaps and the intake ring in the radial direction. 1

Make sure that the play is not more than 0.7619 mm (0.030 in.).

(3) If the APU bleed check-valve is in the correct condition: Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-12-00-040-805-A - Inspection of the APU Bleed Check-Valve for Correct Condition

· Install the APU bleed check-valve (Ref. AMM TASK 36-12-51-400-001) . (4) If the APU bleed check-valve is not in the correct condition: · Replace the APU bleed check-valve (Ref. AMM TASK 36-12-51-400-001) . 5.

Close-up Subtask 36-12-00-410-064-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install access panel 197BB. (3) Remove the access platform(s).

Subtask 36-12-00-865-086-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU 49VU 49VU 122VU 122VU 122VU

DESIGNATION AIR BLEED/X FEED/VALVE/BAT AIR BLEED/ENG 2/MONG AIR BLEED/ENG 1/CTL AIR BLEED/ENG 1/MONG AIR BLEED/ENG 2/CTL AIR BLEED/X FEED VALVE/NORM

FIN 2HV 3HA2 2HA1 3HA1 2HA2 1HV

LOCATION D13 D12 D11 Z23 Z22 Z20

Subtask 36-12-00-860-093-A C.

Aircraft Maintenance Configuration (1) Remove the WARNING NOTICE(S).

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-22-00-040-001-A - Deactivation of the Pylon Overheat Sensing-Element

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 TASK 36-22-00-040-001-A Deactivation of the Pylon Overheat Sensing-Element 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.

FIN : 1HF1 , 1HF2 1.

Reason for the Job MMEL 36-22-01B Pylon Leak Detection System MMEL 36-22-01C Pylon Leak Detection System MMEL 36-22-01D Pylon Leak Detection System MMEL 36-22-01A Pylon Leak Detection System

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

QTY AR AR AR AR

DESIGNATION ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTION FOR 1HF1 (SNSG ELEM-OVHT, ENG 1 PYLON) ** ON A/C 201-201, 203-207, 209-211, 217-220, 222-222, 226-235, 237-237, 239-240, 242-250, 350-350 413CL, 413DL, 414CR, 414FR ** ON A/C 016-022, 024-100, 112-150, 208-208, 212-216, 221-221, 223-225, 236-236, 238-238, 241-241 413DT, 423DT, 471AL, 471AR, 481AL, 481AR ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 FOR 1HF2 (SNSG ELEM-OVHT, ENG 2 PYLON) ** ON A/C 016-022, 024-100, 112-150, 208-208, 212-216, 221-221, 223-225, 236-236, 238-238, 241-241 423DT, 481AL, 481AR ** ON A/C 201-201, 203-207, 209-211, 217-220, 222-222, 226-235, 237-237, 239-240, 242-250, 350-350 423CL, 423DL, 423FL, 424CR

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-22-00-040-001-A - Deactivation of the Pylon Overheat Sensing-Element

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 36-11-00-740-001-A). (Ref. 36-22-00-790-001-A). (Ref. 36-22-15-000-001-A).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) BITE Test of the BMC 1(2) Leak Check on all the Bleed Air Ducts and Packs Components Removal of the Pylon Overheat Sensing-Element

** ON A/C 201-201, 203-207, 209-211, 217-220, 222-222, 226-235, 237-237, 239-240, 242-250, 350-350 (Ref. 54-53-11-000-002-A). Removal of the Pylon-to-Wing Access Panels ** ON A/C 016-022, 024-100, 112-150, 208-208, 212-216, 221-221, 223-225, 236-236, 238-238, 241-241 (Ref. 54-53-11-000-002-B). Removal of the Pylon-to-Wing Access Panels ** ON A/C 201-201, 203-207, 209-211, 217-220, 222-222, 226-235, 237-237, 239-240, 242-250, 350-350 (Ref. 54-53-11-400-002-A). Installation of the Pylon-to-Wing Access Panels ** ON A/C 016-022, 024-100, 112-150, 208-208, 212-216, 221-221, 223-225, 236-236, 238-238, 241-241 (Ref. 54-53-11-400-002-B). Installation of the Pylon-to-Wing Access Panels ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 3.

Job Set-up Subtask 36-22-00-861-052-A A.

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

Subtask 36-22-00-941-052-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 the AIR COND panel 30VU: · Make sure that the ENG 1(2) BLEED pushbutton switch is released (the OFF legend is on). · Make sure that the APU BLEED pushbutton switch is released (the ON legend is off). · Put a WARNING NOTICE(S) in position to tell persons not to operate the pneumatic system. (3) On the ENG panel 115VU: · Put a WARNING NOTICE(S) in position to tell persons not to start the 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 the maintenance panel 50VU:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-22-00-040-001-A - Deactivation of the Pylon Overheat Sensing-Element

· Make sure that the ON legend of the ENG/FADEC GND PWR 1(2) pushbutton switch is off. · Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2). ** ON A/C 201-201, 203-207, 209-211, 217-220, 222-222, 226-235, 237-237, 239-240, 242-250, 350-350 Subtask 36-22-00-010-050-A C.

Get Access (1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at the pylon access. (2) Remove these access panels (Ref. AMM TASK 54-53-11-000-002) : (a) FOR 1HF1 (SNSG ELEM-OVHT, ENG 1 PYLON) 413CL, 414CR, 413DL, 414FR (b) FOR 1HF2 (SNSG ELEM-OVHT, ENG 2 PYLON) 423CL, 424CR, 423DL, 423FL.

** ON A/C 016-022, 024-100, 112-150, 208-208, 212-216, 221-221, 223-225, 236-236, 238-238, 241-241 Subtask 36-22-00-010-050-C C.

Get Access (1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at the pylon access. (2) Remove these access panels (Ref. AMM TASK 54-53-11-000-002) : (a) FOR 1HF1 (SNSG ELEM-OVHT, ENG 1 PYLON) 471AL, 471AR, 413DT (b) FOR 1HF2 (SNSG ELEM-OVHT, ENG 2 PYLON) 481AL, 481AR, 423DT.

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 36-22-00-865-057-A D.

Open, safety and tag this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 1HF1 (SNSG ELEM-OVHT, ENG 1 PYLON) 49VU AIR BLEED/ENG 1/CTL 49VU AIR BLEED/ENG 1/MONG FOR FIN 1HF2 (SNSG ELEM-OVHT, ENG 2 PYLON) 122VU AIR BLEED/ENG 2/CTL 122VU AIR BLEED/ENG 2/MONG

4.

FIN

LOCATION

3HA1 2HA1

D12 D11

3HA2 2HA2

Z23 Z22

Procedure Subtask 36-22-00-790-052-A A.

Leak Check (1) Do a leak check on the related pylon (Ref. AMM TASK 36-22-00-790-001) at the bleed air ducts. Make sure that there are no leaks, specially from the clamps and the connections. · If there is a leak, it will be a NO GO. Repair the bleed air duct. · If there is no leak, do the deactivation of the related sensing element (refer to Para. 4.B).

Subtask 36-22-00-040-050-A B.

Deactivation of the Pylon Overheat Sensing-Element · Remove the related pylon overheat sensing-element (Ref. AMM TASK 36-22-15-000-001) and put secured CAP - BLANKING on the connectors for protection against pollution.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-22-00-040-001-A - Deactivation of the Pylon Overheat Sensing-Element

5.

Close-up Subtask 36-22-00-865-054-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL DESIGNATION FOR FIN 1HF1 (SNSG ELEM-OVHT, ENG 1 PYLON) 49VU AIR BLEED/ENG 1/CTL 49VU AIR BLEED/ENG 1/MONG FOR FIN 1HF2 (SNSG ELEM-OVHT, ENG 2 PYLON) 122VU AIR BLEED/ENG 2/CTL 122VU AIR BLEED/ENG 2/MONG

FIN

LOCATION

3HA1 2HA1

D12 D11

3HA2 2HA2

Z23 Z22

Subtask 36-22-00-740-050-A B.

Do the BITE test of the BMC 1(2) (Ref. AMM TASK 36-11-00-740-001) . (1) The pylon loop 1(2) message ENG 1(2) PYLON LOOP INOP must come into view. (2) Make sure that the related ENG1(2) BLEED pushbutton switch stays released for the flight (the OFF legend is on). (3) Make an entry in the logbook.

** ON A/C 201-201, 203-207, 209-211, 217-220, 222-222, 226-235, 237-237, 239-240, 242-250, 350-350 Subtask 36-22-00-410-050-A C.

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 54-53-11-400-002) : (a) FOR 1HF1 (SNSG ELEM-OVHT, ENG 1 PYLON) 413CL, 414CR, 413DL, 414FR (b) FOR 1HF2 (SNSG ELEM-OVHT, ENG 2 PYLON) 423CL, 424CR, 423DL, 423FL. (3) Remove the WARNING NOTICE(S). (4) Remove the access platform(s).

** ON A/C 016-022, 024-100, 112-150, 208-208, 212-216, 221-221, 223-225, 236-236, 238-238, 241-241 Subtask 36-22-00-410-050-C C.

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 54-53-11-400-002) : (a) FOR 1HF1 (SNSG ELEM-OVHT, ENG 1 PYLON) 471AL, 471AR, 413DT (b) FOR 1HF1 (SNSG ELEM-OVHT, ENG 1 PYLON) 481AL, 481AR, 423DT. (3) Remove the WARNING NOTICE(S). (4) Remove the access platform(s).

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 Subtask 36-22-00-862-052-A Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 36-22-00-040-001-A - Deactivation of the Pylon Overheat Sensing-Element

D.

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

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-005-A - Deactivation of the APU by Circuit Breakers (GTCP 36-300)

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 TASK 49-10-00-040-005-A Deactivation of the APU by Circuit Breakers (GTCP 36-300) WARNING:

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

FIN : ** ON A/C 201-201, 233-233 4005KM ** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 Task Summary MMEL or CDL Ref MMEL 49-10-01C 1.

Reason for the Job MMEL 49-10-01C Power Plant (APU)

2

Job Set-up Information A.

Access NO

Test NO

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE

QTY DESIGNATION

** ON A/C 201-201, 233-233 No specific AR SAFETY CLIP - CIRCUIT BREAKER No specific 1 WARNING NOTICE(S) ** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 B.

Consumable Materials REFERENCE

DESIGNATION

** ON A/C 201-201, 233-233 (Material No. 03ABA1)

Synthetic base Lubricating Oil-Turbine Engine - -

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-005-A - Deactivation of the APU by Circuit Breakers (GTCP 36-300)

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 C. Referenced Information REFERENCE

DESIGNATION

** ON A/C 201-201, 233-233 (Ref. 49-90-00-600-002-A-03).

Brand/Type Oil Change (Flush Procedure) (GTCP 36-300)

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 3.

Job Set-up Subtask 49-10-00-860-072-A A.

4.

Not applicable

Procedure Subtask 49-10-00-612-050-A A.

Change to Preservation Oil CAUTION:

USE ONLY APPROVED TYPES/BRANDS OF LUBRICANTS.

(1) Do an APU oil type change to Synthetic base Lubricating Oil-Turbine Engine - (Material No. 03ABA1) (Ref. AMM TASK 49-90-00-600-002) . NOTE: It is not necessary to operate the APU after the preservation oil is in the reservoir. ** ON A/C 201-201, 233-233 PRE SB 49-1077 for A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 Subtask 49-10-00-040-056-A B.

Deactivation of the APU (1) On the panel 25VU: · Make sure that the APU MASTER SW pushbutton switch is set to OFF. · Make sure that the APU START pushbutton switch is set to OFF. · Put a WARNING NOTICE(S) 'APU INOP' in position. (2) On the panel 30VU, · Make sure that the APU BLEED pushbutton switch is set to OFF. (3) Make an entry in the technical logbook that the APU is deactivated.

** ON A/C POST SB 49-1077 for A/C 201-201, 233-233

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-005-A - Deactivation of the APU by Circuit Breakers (GTCP 36-300)

EMB SB 49-1058 for A/C 201-201, 233-233 Subtask 49-10-00-040-056-B B.

Deactivation of the APU (1) Make sure that the air intake flap is in the closed position. If the air intake flap is open, you must close it manually: CAUTION: BE CAREFUL WHEN YOU COME TO THE MECHANICAL STOP AT THE END OF TRAVEL. IF YOU TURN THE MANUAL DRIVE SHAFT WITH MORE TORQUE THAN THE LIMIT, DAMAGE TO THE AIR INTAKE FLAP ACTUATOR WILL OCCUR. (a) Turn the manual drive shaft on the air intake flap-actuator 4015KM until the air intake flap is in the fully closed position. NOTE: Make sure that the torque necessary to turn the manual drive shaft is not more than 0.3 m.daN (26.55 lbf.in) for the actuator 43-1-1100 Amendment 1, for the actuator 106-11100-02 not more than 0.4 m.daN (35.40 lbf.in). Be careful when you come to the mechanical stop at the end of travel. If you turn the manual drive shaft with more torque than the limit, damage to the air intake flap actuator will occur. NOTE: On the actuator 43-1-1100 Amendment 1, 47 turns are required for one full travel of the air intake flap actuator. On the actuator 106-1-1100-02, 87 turns are required. (b) Make sure that the air intake flap is in the correct position. (2) On the panel 25VU: · Make sure that the APU MASTER SW pushbutton switch is set to OFF. · Make sure that the APU START pushbutton switch is set to OFF. · Put a WARNING NOTICE(S) 'APU INOP' in position. (3) On the panel 30VU, · Make sure that the APU BLEED pushbutton switch is set to OFF. (4) Make an entry in the technical logbook that the APU is deactivated.

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 Subtask 49-10-00-865-060-A C.

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

DESIGNATION

** ON A/C 201-201, 233-233 121VU APU/APU/CTL 121VU APU/ECB/SPLY

FIN

2KD 1KD

LOCATION

L42 L41

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-005-A01 - Deactivation of the APU by Kit (GTCP 36-300)

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 TASK 49-10-00-040-005-A01 Deactivation of the APU by Kit (GTCP 36-300)

FIN : ** ON A/C 201-201, 233-233 4005KM ** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 Task Summary MMEL or CDL Ref MMEL 49-10-01C 1.

Reason for the Job MMEL 49-10-01C Power Plant (APU)

2

Job Set-up Information A.

Access NO

Test NO

Specific Tools NO

Mhr 16.0

E/T 08.0

Nb Men 2

Fixtures, Tools, Test and Support Equipment REFERENCE

QTY DESIGNATION

** ON A/C 201-201, 233-233 No specific 1

WARNING NOTICE(S)

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 B.

Referenced Information REFERENCE

DESIGNATION

** ON A/C 201-201, 233-233 (Ref. 49-11-00-400-001-A). (Ref. 49-11-11-000-001-A).

Installation of the APU Substitution Kit (GTCP 36-300) Removal of the Auxiliary Power Unit (APU) (GTCP 36-300)

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-005-A01 - Deactivation of the APU by Kit (GTCP 36-300)

3.

Job Set-up Subtask 49-10-00-860-073-A A.

Obey the Weight Impact and Effect on Balance for Flights without APU (1) A318 (a) Weight Impact: - 202.48 kg (- 446.4 lb) (b) Effect on Balance: - 6424.49 kgm (- 557621 lbin) (2) A319 (a) Weight Impact: - 202.48 kg (- 446.4 lb) (b) Effect on Balance: - 6991.43 kgm (- 606830 lbin) (3) A320 (a) Weight Impact: - 202.48 kg (- 446.4 lb) (b) Effect on Balance: - 7747.29 kgm (- 672435 lbin) (4) A321 (a) Weight Impact: - 202.48 kg (- 446.4 lb) (b) Effect on Balance: - 9151.49 kgm (- 794315 lbin)

4.

Procedure Subtask 49-10-00-040-057-A A.

Deactivation of APU (1) Remove the APU (Ref. AMM TASK 49-11-11-000-001) . (2) Install the APU Substitution Kit (Ref. AMM TASK 49-11-00-400-001) . (3) On the panel 25VU: · Put a WARNING NOTICE(S) 'APU INOP' in position. (4) Make an entry in the technical logbook that the APU is removed.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-007-A - Deactivation of the APU by Circuit Breaker Tagging (APS 3200)

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 TASK 49-10-00-040-007-A Deactivation of the APU by Circuit Breaker Tagging (APS 3200)

FIN : ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 4005KM ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 Task Summary MMEL or CDL Ref MMEL 49-10-01C 1.

Reason for the Job MMEL 49-10-01C Power Plant (APU)

2

Job Set-up Information A.

Access NO

Test NO

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE

QTY DESIGNATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 No specific AR SAFETY CLIP - CIRCUIT BREAKER No specific 1 WARNING NOTICE(S)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-007-A - Deactivation of the APU by Circuit Breaker Tagging (APS 3200)

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 3.

Job Set-up Subtask 49-10-00-860-078-A A.

4.

Not applicable

Procedure

** ON A/C 201-201, 204-204 EMB SB 49-1029 for A/C 201-201 EMB SB 49-1111 for A/C 204-204 Subtask 49-10-00-040-058-A A.

Deactivation of the APU (1) On the panel 25VU: · Make sure that the APU MASTER SW pushbutton switch is set to OFF. · Make sure that the APU START pushbutton switch is set to OFF. · Put a WARNING NOTICE(S) 'APU INOP' in position. (2) On the panel 30VU, · Make sure that the APU BLEED pushbutton switch is set to OFF. (3) Make an entry in the technical logbook that the APU is deactivated.

** ON A/C 016-022, 024-100, 112-150, 203-203, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 233-233 EMB SB 49-1070 for A/C 203-203, 217-217, 227-228, 231-233, 237-237, 240-240, 243-244 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 Subtask 49-10-00-040-058-B A.

Deactivation of the APU (1) Make sure that the air intake flap is in the closed position. (a) If the air intake flap is open, and there is no fault in the ECB (59KD), in the 28V DC motor of the air-intake flap actuator (4015KM), or in the wiring: 1

On the panel 121VU, open and then close the circuit breaker 1KD.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-007-A - Deactivation of the APU by Circuit Breaker Tagging (APS 3200)

2

On the panel 25VU, set the APU MASTER SW pushbutton switch to the ON position and then to the OFF position.

3

Make sure that the air intake flap is in the closed position.

CAUTION: BE CAREFUL WHEN YOU COME TO THE MECHANICAL STOP AT THE END OF TRAVEL. IF YOU TURN THE MANUAL DRIVE SHAFT WITH MORE TORQUE THAN THE LIMIT, DAMAGE TO THE AIR INTAKE FLAP ACTUATOR WILL OCCUR. (b) If the air intake flap is open, and there is a fault in the ECB (59KD), in the 28V DC motor of the air-intake flap actuator (4015KM), or in the wiring, you must close it manually: NOTE: You can close the air intake flap manually in all conditions. 1

Turn the manual drive shaft on the air-intake flap actuator (4015KM) until the air intake flap is in the fully closed position. NOTE: Make sure that the torque necessary to turn the manual drive shaft is not more than 0.3 m.daN (26.55 lbf.in) for the actuator 43-1-1100 Amendment 1, for the actuator 106-1-1100-02 not more than 0.4 m.daN (35.40 lbf.in). Be careful when you come to the mechanical stop at the end of travel. If you turn the manual drive shaft with more torque than the limit, damage to the air-intake flap actuator will occur. NOTE: On the actuator 43-1-1100 Amendment 1, 47 turns are required for one full travel of the air-intake flap actuator. On the actuator 106-1-1100-02, 87 turns are required.

2

Make sure that the air intake flap is in the correct position.

(2) On the panel 25VU: · Make sure that the APU MASTER SW pushbutton switch is set to OFF. · Make sure that the APU START pushbutton switch is set to OFF. · Put a WARNING NOTICE(S) 'APU INOP' in position. (3) On the panel 30VU, · Make sure that the APU BLEED pushbutton switch is set to OFF. (4) Make an entry in the technical logbook that the APU is deactivated. ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 Subtask 49-10-00-865-062-A B.

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

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-007-A - Deactivation of the APU by Circuit Breaker Tagging (APS 3200)

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 121VU APU/APU/CTL 2KD L42 121VU APU/ECB/SPLY 1KD L41

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-007-A01 - Deactivation of the APU by APU Substitution Kit (APS 3200)

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 TASK 49-10-00-040-007-A01 Deactivation of the APU by APU Substitution Kit (APS 3200)

FIN : ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 4005KM ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 Task Summary MMEL or CDL Ref MMEL 49-10-01C 1.

Reason for the Job MMEL 49-10-01C Power Plant (APU)

2

Job Set-up Information A.

Access NO

Test NO

Specific Tools NO

Mhr 16.0

E/T 08.0

Nb Men 2

Fixtures, Tools, Test and Support Equipment REFERENCE

QTY DESIGNATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 No specific 1 WARNING NOTICE(S)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-007-A01 - Deactivation of the APU by APU Substitution Kit (APS 3200)

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 B.

Referenced Information REFERENCE

DESIGNATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 (Ref. 49-11-00-400-003-A). Installation of the APU Substitution Kit (APS 3200) (Ref. 49-11-11-000-003-A). Removal of the Power Plant (APU) (APS 3200) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 3.

Job Set-up Subtask 49-10-00-860-079-A A.

Obey the Weight Impact and Effect on Balance for Flights without APU (1) A318 (a) Weight Impact: - 205.62 kg (- 453.3 lb) (b) Effect on Balance: - 6524.12 kgm (- 566269 lbin) (2) A319 (a) Weight Impact: - 205.62 kg (- 453.3 lb) (b) Effect on Balance: - 7099.85 kgm (- 616240 lbin) (3) A320 (a) Weight Impact: - 205.62 kg (- 453.3 lb) (b) Effect on Balance:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-007-A01 - Deactivation of the APU by APU Substitution Kit (APS 3200)

- 7867.43 kgm (- 682863 lbin) (4) A321 (a) Weight Impact: - 205.62 kg (- 453.3 lb) (b) Effect on Balance: - 9293.41 kgm (- 806633 lbin) 4.

Procedure Subtask 49-10-00-040-059-A A.

Deactivation of APU (1) Remove the APU (Ref. AMM TASK 49-11-11-000-003) . (2) Install the APU Substitution Kit (Ref. AMM TASK 49-11-00-400-003) . (3) On the panel 25VU: · Put a WARNING NOTICE(S) 'APU INOP' in position. (4) Make an entry in the technical logbook that the APU is removed.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-008-A - Deactivation of the APU by Circuit Breaker Tagging (131-9(A))

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 TASK 49-10-00-040-008-A Deactivation of the APU by Circuit Breaker Tagging (131-9(A)) WARNING:

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

FIN : ** ON A/C 201-201, 204-214, 217-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 4005KM ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 Task Summary MMEL or CDL Ref MMEL 49-10-01C 1.

Reason for the Job MMEL 49-10-01C Power Plant (APU)

2

Job Set-up Information A.

Access NO

Test NO

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE

QTY DESIGNATION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 No specific AR SAFETY CLIP - CIRCUIT BREAKER No specific 1 WARNING NOTICE(S)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-008-A - Deactivation of the APU by Circuit Breaker Tagging (131-9(A))

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 B.

Consumable Materials REFERENCE

DESIGNATION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 (Material No. 03ABA1) Synthetic base Lubricating Oil-Turbine Engine - ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 C. Referenced Information REFERENCE

DESIGNATION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 (Ref. 49-90-00-600-008-A-02). Brand/Type Oil Change (Flush Procedure) (131-(A)) ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 3.

Job Set-up Subtask 49-10-00-860-084-A A.

4.

Not applicable

Procedure Subtask 49-10-00-612-052-A A.

Change to Preservation Oil CAUTION:

USE ONLY APPROVED TYPES/BRANDS OF LUBRICANTS.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-008-A - Deactivation of the APU by Circuit Breaker Tagging (131-9(A))

(1) Do an APU oil type change to Synthetic base Lubricating Oil-Turbine Engine - (Material No. 03ABA1) (Ref. AMM TASK 49-90-00-600-008) . NOTE: This procedure is not applicable if the operator disconnects the APU for less than 30 days. NOTE: It is not necessary to operate the APU after the preservation oil is in the reservoir. ** ON A/C 205-205, 210-211, 222-222, 234-234 PRE SB 49-1067 for A/C 234-234 PRE SB 49-1075 for A/C 210-210, 234-234 POST SB 49-1082 for A/C 217-217 EMB SB 49-1082 for A/C 211-211 Subtask 49-10-00-040-060-A B.

Deactivation of the APU (1) On the panel 25VU: · Make sure that the APU MASTER SW pushbutton switch is set to OFF. · Make sure that the APU START pushbutton switch is set to OFF. · Put a WARNING NOTICE(S) 'APU INOP' in position. (2) On the panel 30VU, · Make sure that the APU BLEED pushbutton switch is set to OFF. (3) Make an entry in the technical logbook that the APU is deactivated.

** ON A/C 201-201, 204-204, 206-209, 212-214, 218-218, 223-226, 229-230, 235-235, 239-239, 301-349, 351385, 396-405, 416-450, 500-600 POST SB 49-1067 for A/C 234-234 POST SB 49-1075 for A/C 210-210, 234-234 EMB SB 49-1067 for A/C 206-206 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1075 for A/C 201-201, 207-207, 209-209, 218-218, 229-230, 235-235 EMB SB 49-1082 for A/C 201-201 Subtask 49-10-00-040-060-B B.

Deactivation of the APU (1) Make sure that the air intake flap is in the closed position. If the air intake flap is open, you must close it manually: CAUTION: BE CAREFUL WHEN YOU COME TO THE MECHANICAL STOP AT THE END OF TRAVEL. IF YOU TURN THE MANUAL DRIVE SHAFT WITH MORE TORQUE THAN THE LIMIT, DAMAGE TO THE AIR INTAKE FLAP ACTUATOR WILL OCCUR. (a) Turn the manual drive shaft on the air intake flap actuator 4015KM until the air intake flap is in the fully closed position. NOTE: Make sure that the torque necessary to turn the manual drive shaft is not more than 0.3 m.daN (26.55 lbf.in) for the actuator 43-1-1100 Amendment 1, for the actuator 106-11100-02 not more than 0.4 m.daN (35.40 lbf.in). Be careful when you come to the mechanical stop at the end of travel. If you turn the manual drive shaft with more torque than the limit, damage to the air intake flap actuator will occur.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-008-A - Deactivation of the APU by Circuit Breaker Tagging (131-9(A))

NOTE: On the actuator 43-1-1100 Amendment 1, 47 turns are required for one full travel of the air intake flap actuator. On the actuator 106-1-1100-02, 87 turns are required. (b) Make sure that the air intake flap is in the correct position. (2) On the panel 25VU: · Make sure that the APU MASTER SW pushbutton switch is set to OFF. · Make sure that the APU START pushbutton switch is set to OFF. · Put a WARNING NOTICE(S) 'APU INOP' in position. (3) On the panel 30VU, · Make sure that the APU BLEED pushbutton switch is set to OFF. (4) Make an entry in the technical logbook that the APU is deactivated. ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 Subtask 49-10-00-865-064-A C.

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

DESIGNATION

FIN

LOCATION

** ON A/C 201-201, 204-214, 217-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 121VU APU/APU/CTL 2KD L42 121VU APU/ECB/SPLY 1KD L41

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-008-A01 - Deactivation of the APU by APU Substitution Kit (131-9(A))

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 TASK 49-10-00-040-008-A01 Deactivation of the APU by APU Substitution Kit (131-9(A))

FIN : ** ON A/C 201-201, 204-214, 217-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 4005KM ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 Task Summary MMEL or CDL Ref MMEL 49-10-01C 1.

Reason for the Job MMEL 49-10-01C Power Plant (APU)

2

Job Set-up Information A.

Access NO

Test NO

Specific Tools NO

Mhr 16.0

E/T 08.0

Nb Men 2

Fixtures, Tools, Test and Support Equipment REFERENCE

QTY DESIGNATION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 No specific 1 WARNING NOTICE(S) ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-008-A01 - Deactivation of the APU by APU Substitution Kit (131-9(A))

B.

Referenced Information REFERENCE

DESIGNATION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 (Ref. 49-11-00-400-005-A). Installation of the APU Substitution Kit (131-9(A)) (Ref. 49-11-11-000-004-A). Removal of the Power Plant (APU) (131-9(A)) ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 3.

Job Set-up Subtask 49-10-00-860-085-A A.

Obey the Weight Impact and Effect on Balance for Flights without APU (1) A318 (a) Weight Impact: - 224.37 kg (- 494.7 lb) (b) Effect on Balance: - 7119.04 kgm (- 617906 lbin) (2) A319 (a) Weight Impact: - 224.37 kg (- 494.7 lb) (b) Effect on Balance: - 7747.27 kgm (- 672434 lbin) (3) A320 (a) Weight Impact: - 224.37 kg (- 494.7 lb) (b) Effect on Balance: - 8584.85 kgm (- 745132 lbin) (4) A321 (a) Weight Impact: - 224.37 kg (- 494.7 lb) (b) Effect on Balance: - 10140.85 kgm (- 880187 lbin)

4.

Procedure Subtask 49-10-00-040-061-A A.

Deactivation of APU (1) Remove the APU (Ref. AMM TASK 49-11-11-000-004) . (2) Install the APU Substitution Kit (Ref. AMM TASK 49-11-00-400-005) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-10-00-040-008-A01 - Deactivation of the APU by APU Substitution Kit (131-9(A))

(3) On the panel 25VU: · Put a WARNING NOTICE(S) 'APU INOP' in position. (4) Make an entry in the technical logbook that the APU is removed.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-001-A - Deactivation of the APU Air Intake Flap (GTCP 36-300)

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 TASK 49-16-00-040-001-A Deactivation of the APU Air Intake Flap (GTCP 36-300) WARNING:

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

CAUTION:

MAKE SURE THAT THE AIR INTAKE FLAP IS FULLY EXTENDED BEFORE YOU INSTALL THE TEMPORARY CONNECTOR. IF NOT, YOU WILL CAUSE DAMAGE TO THE APU.

Task Summary MMEL or CDL Ref MMEL 49-10-02B 1.

Reason for the Job MMEL 49-10-02B APU Air Intake Flap

2

Job Set-up Information A.

Access YES

Test YES

Specific Tools NO

Mhr 00.5

E/T 00.5

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE

QTY DESIGNATION

** ON A/C 201-201, 233-233 No specific No specific No specific No specific No specific No specific No specific No specific

1 AR AR AR AR AR AR AR

ACCESS PLATFORM 3M (10 FT) BACKSHELL ABS0638A14 CAP - BLANKING CONNECTOR E0052R14B12PNE JUMPER-WIRE SAFETY CLIP - CIRCUIT BREAKER TIE WRAP WARNING NOTICE(S)

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 B.

Consumable Materials REFERENCE

DESIGNATION

** ON A/C 201-201, 233-233 (Material No. 04JAA3)

Top Coat Polyurethane-- - External Structure

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-001-A - Deactivation of the APU Air Intake Flap (GTCP 36-300)

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 C. Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

** ON A/C 201-201, 233-233 314AR ** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 D. Referenced Information REFERENCE ** ON A/C 201-201, 233-233 (Ref. 52-41-23-000-001-A). (Ref. 52-41-23-400-001-A). Ref. ESPM 20-44-11 AIPC 24920467 AIPC 24920472

DESIGNATION

Removal of the Maintenance Door Installation of the Maintenance Door

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 ** ON A/C 201-201, 233-233 Air Intake Flap Actuator - Deactivation/Reactivation

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-001-A - Deactivation of the APU Air Intake Flap (GTCP 36-300)

Z313, Z314

A A

FR80 314AR

A DUMMY CONNECTOR

FR76

7527VCA

7527VC MANUAL DRIVE SHAFT

AIR INTAKE FLAP ACTUATOR 4015KM

A N_MM_491600_4_AAN0_01_01

Figure 49-16-00-991-00800-00-B / SHEET 1/2 - Air Intake Flap Actuator - Deactivation/Reactivation ** ON A/C 201-201, 233-233 | EMB SB 49-1058 for A/C 201-201, 233-233 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-001-A - Deactivation of the APU Air Intake Flap (GTCP 36-300)

AIR INTAKE FLAP ACTUATOR 4015KM FR78

CATWALK FR80 PANEL HOUSING

MANUAL DRIVE CONNECTOR

B

NOSE

AIR INTAKE FLAP (OPEN)

A A FWD

MAX DEVIATION " B "

AIR INTAKE FLAP AIR INTAKE FLAP IN OPEN POSITION

B

N_MM_491600_4_AAN0_02_00

Figure 49-16-00-991-00800-00-B / SHEET 2/2 - Air Intake Flap Actuator - Deactivation/Reactivation ** ON A/C 201-201, 233-233 | EMB SB 49-1058 for A/C 201-201, 233-233 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-001-A - Deactivation of the APU Air Intake Flap (GTCP 36-300)

3.

Job Set-up Subtask 49-16-00-010-051-A A.

Get Access 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. (1) Put on and attach a safety harness before you start work in the work area (2) Put the ACCESS PLATFORM 3M (10 FT) below the maintenance door 314AR. (3) Open access door 314AR and safety it in the open position. (Ref. AMM TASK 52-41-23-000-001) . (4) Set the light switch to on. (5) Release the fasteners of the catwalk panel and remove it from the service frame.

Subtask 49-16-00-865-054-A B.

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

DESIGNATION

** ON A/C 201-201, 233-233 121VU APU/APU/CTL 121VU APU/ECB/SPLY

FIN

2KD 1KD

LOCATION

L42 L41

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 4.

Procedure (Ref. Fig. Air Intake Flap Actuator - Deactivation/Reactivation) Subtask 49-16-00-040-051-A A.

Deactivation of the Air Intake Flap (1) Disconnect the electrical connectors 7527VC-A and 7527VC. (a) Disconnect the electrical connector 7527VC-A from the connector 7527VC. (b) Put a CAP - BLANKING on the electrical connector 7527VC-A. (c) Attach the electrical connector 7527VC-A to the service frame with a TIE WRAP. (2) Open the air intake flap manually if it is not in the fully open position. (a) Turn the manual drive shaft on the air intake flap-actuator 4015KM until the air intake flap is in the fully open position. NOTE: Make sure that the torque necessary to turn the manual drive shaft is not more than 0.3 mdaN (26.55 lbf.in) for the actuator 43-1-1100 Amendment 1, for the actuator 106-11100-02 not more than 0.4 mdaN (35.4 lbf.in). Be careful when you come to the mechanical stop at the end of travel. If you turn the manual drive shaft with more torque than the limit, damage to the air intake flap actuator will occur.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-001-A - Deactivation of the APU Air Intake Flap (GTCP 36-300)

NOTE: On the actuator 43-1-1100-Amendment 1, 47 turns are required for one full travel of the air intake flap actuator. On the actuator 106-1-1100 -02, 87 turns are required. (b) Make sure that the air intake flap is in the correct position. NOTE: The contour of the air intake flap must align with the contour of the air-channel upper wall. The TOLERANCE A in the flap close direction is max. 1 mm (0.0394 in.) at the aft edge of the air intake flap. No tolerance is permitted in the flap open direction. (3) Make a dummy connector with a jumper lead to close the ''FLAP OPEN'' and the ''FLAP CLOSE'' control circuit between the ECB 59KD and the air intake-flap actuator 4015KM. NOTE: Refer to Ref. ESPM 20-44-11 , AIPC 24920467 and AIPC 24920472 for information about the electrical connector (a) Connect a JUMPER-WIRE between the pins C and D of a CONNECTOR E0052R14B12PNE. (b) Hold the jumper lead in position on the dummy connector with a BACKSHELL ABS0638A14. (c) Paint the dummy connector red with Top Coat Polyurethane-- - External Structure (Material No. 04JAA3) to make sure that it is easily identified. (4) Connect the dummy connector to the connector 7527VC. (5) Put a WARNING NOTICE(S) in position in the cockpit to tell the flight crew that the air intake flap is deactivated in the open position. (6) Make an entry in the logbook to show that the air intake flap is deactivated in the open position and add the time which the MMEL 49-10-02 permits for the operation in this condition. 5.

Close-up Subtask 49-16-00-410-052-A A.

Close Access (1) Put the catwalk panel in position on the service frame and secure with the fasteners. (2) Make sure that the work area is clean and clear of tools and other items. (3) Set the light switch to off. (4) Close the maintenance door 314AR (Ref. AMM TASK 52-41-23-400-001) . (5) Remove the access platform(s).

Subtask 49-16-00-865-055-A B.

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

DESIGNATION

** ON A/C 201-201, 233-233 121VU APU/APU/CTL 121VU APU/ECB/SPLY

FIN

2KD 1KD

LOCATION

L42 L41

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-002-A - Deactivation of the APU Air Intake Flap (APS 3200)

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 TASK 49-16-00-040-002-A Deactivation of the APU Air Intake Flap (APS 3200) WARNING:

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

Task Summary MMEL or CDL Ref MMEL 49-10-02B 1.

Reason for the Job MMEL 49-10-02B APU Air Intake Flap

2

Job Set-up Information A.

Access YES

Test NO

Specific Tools NO

Mhr 00.5

E/T 00.5

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE

QTY DESIGNATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 No specific 1 ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE No specific AR BACKSHELL ABS0638A14 No specific AR CAP - BLANKING No specific AR CONNECTOR E0052R14B12PNE No specific AR JUMPER-WIRE No specific AR SAFETY CLIP - CIRCUIT BREAKER No specific AR TIE WRAP No specific AR WARNING NOTICE(S) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-002-A - Deactivation of the APU Air Intake Flap (APS 3200)

EMB SB 49-1111 for A/C 204-204 B.

Consumable Materials REFERENCE

DESIGNATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 (Material No. 04JAA3) Top Coat Polyurethane-- - External Structure ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 C. Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 314AR ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 D. Referenced Information REFERENCE

DESIGNATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 (Ref. 52-41-23-000-001-A). Removal of the Maintenance Door (Ref. 52-41-23-400-001-A). Installation of the Maintenance Door Ref. ESPM 20-44-11 AIPC 24920467

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-002-A - Deactivation of the APU Air Intake Flap (APS 3200)

REFERENCE AIPC 24920472

DESIGNATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 Air Intake Flap Actuator - Deactivation/Reactivation

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-002-A - Deactivation of the APU Air Intake Flap (APS 3200)

Z313, Z314

A A

FR80 314AR

A DUMMY CONNECTOR

FR76

7527VCA

7527VC MANUAL DRIVE SHAFT

AIR INTAKE FLAP ACTUATOR 4015KM

A N_MM_491600_4_LAN0_01_01

Figure 49-16-00-991-00900-12-B / SHEET 1/2 - Air Intake Flap Actuator - Deactivation/Reactivation ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231233, 236-238, 240-250, 350-350, 386-395, 406-415 | EMB SB 49-1029 for A/C 201-201, 233233 | EMB SB 49-1081 for A/C 215-216 | PRE SB 49-1082 for A/C 217-217 | EMB SB 491099 for A/C 219-220 | EMB SB 49-1105 for A/C 350-350 | EMB SB 49-1111 for A/C 204-204 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-002-A - Deactivation of the APU Air Intake Flap (APS 3200)

AIR INTAKE FLAP ACTUATOR 4015KM FR78

CATWALK FR80 PANEL HOUSING

MANUAL DRIVE CONNECTOR

B

NOSE

AIR INTAKE FLAP (OPEN)

A A FWD

MAX DEVIATION " B "

AIR INTAKE FLAP AIR INTAKE FLAP IN OPEN POSITION

B

N_MM_491600_4_LAN0_02_00

Figure 49-16-00-991-00900-12-B / SHEET 2/2 - Air Intake Flap Actuator - Deactivation/Reactivation ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231233, 236-238, 240-250, 350-350, 386-395, 406-415 | EMB SB 49-1029 for A/C 201-201, 233233 | EMB SB 49-1081 for A/C 215-216 | PRE SB 49-1082 for A/C 217-217 | EMB SB 491099 for A/C 219-220 | EMB SB 49-1105 for A/C 350-350 | EMB SB 49-1111 for A/C 204-204 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-002-A - Deactivation of the APU Air Intake Flap (APS 3200)

3.

Job Set-up Subtask 49-16-00-010-054-A A.

Get Access 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. (1) Put on and attach a safety harness before you start work in the work area (2) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE below the maintenance door 314AR. (3) Open access door 314AR and safety it in the open position. (Ref. AMM TASK 52-41-23-000-001) (4) Set the light switch to on. (5) Release the fasteners of the catwalk panel and remove it from the service frame.

Subtask 49-16-00-865-058-A B.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 121VU APU/APU/CTL 2KD L42 121VU APU/ECB/SPLY 1KD L41 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 4.

Procedure (Ref. Fig. Air Intake Flap Actuator - Deactivation/Reactivation) Subtask 49-16-00-040-050-A A.

Deactivation of the Air Intake Flap (1) Release the fasteners and remove the catwalk panel from the service frame. (2) Disconnect the electrical connectors 7527VC-A and 7527VC. (a) Disconnect the electrical connector 7527VC-A from the connector 7527VC. (b) Put a CAP - BLANKING on the electrical connector 7527VC-A. (c) Attach the electrical connector 7527VC-A to the air intake structure with a TIE WRAP. (3) Open the air intake flap manually if it is not in the fully open position. (a) Turn the manual drive shaft on the air intake flap-actuator 4015KM until the air intake flap is in the fully open position.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-002-A - Deactivation of the APU Air Intake Flap (APS 3200)

NOTE: Make sure that the torque necessary to turn the manual drive shaft is not more than 0.3 mdaN (26.55 lbf.in) for the actuator 43-1-1100 Amendment 1, for the actuator 106-11100-02 not more than 0.4 mdaN (35.4 lbf.in). Be careful when you come to the mechanical stop at the end of travel. If you turn the manual drive shaft with more torque than the limit, damage to the air intake flap actuator will occur. NOTE: On the actuator 43-1-1100-Amendment 1, 47 turns are required for one full travel of the air intake flap actuator. On the actuator 106-1-1100 -02, 87 turns are required. (b) Make sure that the air intake flap is in the correct position. NOTE: The contour of the air intake flap must align with the contour of the air-channel upper wall. The TOLERANCE A in the flap close direction is max. 1 mm (0.0394 in.) at the aft edge of the air intake flap. No tolerance is permitted in the flap open direction. (4) Make a dummy connector with a jumper lead to close the ''FLAP OPEN'' and the ''FLAP CLOSE'' control circuit between the ECB 59KD and the air intake-flap actuator 4015KM. NOTE: Refer to Ref. ESPM 20-44-11 , AIPC 24920467 and AIPC 24920472 for information about electrical connector identification. (a) Connect a JUMPER-WIRE between the pins C and D of a CONNECTOR E0052R14B12PNE. (b) Hold the jumper lead in position on the connector with a BACKSHELL ABS0638A14. (c) Paint the dummy connector red with Top Coat Polyurethane-- - External Structure (Material No. 04JAA3) to make sure that it is easily identified. (5) Connect the dummy connector to the connector 7527VC. (6) Put a WARNING NOTICE(S) in position in the cockpit to tell the flight crew that the air intake flap is deactivated in the open position. (7) Make an entry in the logbook to show that the air intake flap is deactivated in the open position and add the time which the MMEL 49-10-02 permits for the operation in this condition. 5.

Close-up Subtask 49-16-00-410-054-A A.

Close Access (1) Put the catwalk panel in position on the service frame and secure with the fasteners. (2) Make sure that the work area is clean and clear of tools and other items. (3) Set the light switch to off. (4) Close the maintenance door 314AR (Ref. AMM TASK 52-41-23-400-001) . (5) Remove the access platform(s).

Subtask 49-16-00-865-059-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 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 121VU APU/APU/CTL 2KD L42 121VU APU/ECB/SPLY 1KD L41 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-002-A - Deactivation of the APU Air Intake Flap (APS 3200)

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-003-A - Deactivation of the APU Air Intake Flap (131-9(A))

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 TASK 49-16-00-040-003-A Deactivation of the APU Air Intake Flap (131-9(A)) WARNING:

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

CAUTION:

MAKE SURE THAT THE AIR INTAKE FLAP IS FULLY EXTENDED BEFORE YOU INSTALL THE TEMPORARY CONNECTOR. IF NOT, YOU WILL CAUSE DAMAGE TO THE APU.

Task Summary MMEL or CDL Ref MMEL 49-10-02B 1.

Reason for the Job MMEL 49-10-02B APU Air Intake Flap

2

Job Set-up Information A.

Access YES

Test NO

Specific Tools NO

Mhr 00.5

E/T 00.5

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE

QTY DESIGNATION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 No specific 1 ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE No specific AR BACKSHELL ABS0638A14 No specific AR CAP - BLANKING No specific AR CONNECTOR E0052R14B12PNE No specific AR JUMPER-WIRE No specific AR SAFETY CLIP - CIRCUIT BREAKER No specific AR TIE WRAP No specific AR WARNING NOTICE(S) ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 B.

Consumable Materials

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-003-A - Deactivation of the APU Air Intake Flap (131-9(A))

REFERENCE

DESIGNATION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 (Material No. 04JAA3) Top Coat Polyurethane-- - External Structure ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 C. Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 314AR ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 D. Referenced Information REFERENCE

DESIGNATION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 (Ref. 52-41-23-000-001-A). Removal of the Maintenance Door (Ref. 52-41-23-400-001-A). Installation of the Maintenance Door Ref. ESPM 20-44-11 AIPC 24920467 AIPC 24920472 ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-003-A - Deactivation of the APU Air Intake Flap (131-9(A))

REFERENCE DESIGNATION EMB SB 49-1082 for A/C 201-201, 211-211 ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 Air Intake Flap Actuator - Deactivation/Reactivation

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-003-A - Deactivation of the APU Air Intake Flap (131-9(A))

Z313, Z314

A A

FR80 314AR

A DUMMY CONNECTOR

FR76

7527VCA

7527VC MANUAL DRIVE SHAFT

AIR INTAKE FLAP ACTUATOR 4015KM

A N_MM_491600_4_PAN0_01_01

Figure 49-16-00-991-01000-16-B / SHEET 1/2 - Air Intake Flap Actuator - Deactivation/Reactivation ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301349, 351-385, 396-405, 416-450, 500-600 | EMB SB 49-1069 for A/C 204-204 | EMB SB 49-1082 for A/C 201-201, 211-211 | POST SB 49-1082 for A/C 217-217 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-003-A - Deactivation of the APU Air Intake Flap (131-9(A))

AIR INTAKE FLAP ACTUATOR 4015KM CATWALK FR80 PANEL HOUSING

FR78

MANUAL DRIVE CONNECTOR

B

NOSE

AIR INTAKE FLAP (OPEN)

A A FWD

MAX DEVIATION " B "

AIR INTAKE FLAP AIR INTAKE FLAP IN OPEN POSITION

B

N_MM_491600_4_PAN0_02_00

Figure 49-16-00-991-01000-16-B / SHEET 2/2 - Air Intake Flap Actuator - Deactivation/Reactivation ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301349, 351-385, 396-405, 416-450, 500-600 | EMB SB 49-1069 for A/C 204-204 | EMB SB 49-1082 for A/C 201-201, 211-211 | POST SB 49-1082 for A/C 217-217 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-003-A - Deactivation of the APU Air Intake Flap (131-9(A))

3.

Job Set-up Subtask 49-16-00-010-062-A A.

Get Access 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. (1) Put on and attach a safety harness before you start work in the work area (2) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE below the maintenance door 314AR. (3) Open access door 314AR and safety it in the open position. (Ref. AMM TASK 52-41-23-000-001) (4) Set the light switch to on. (5) Release the fasteners of the catwalk panel and remove it from the service frame.

Subtask 49-16-00-865-071-A B.

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

DESIGNATION

FIN

LOCATION

** ON A/C 201-201, 204-214, 217-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 121VU APU/APU/CTL 2KD L42 121VU APU/ECB/SPLY 1KD L41 ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 4.

Procedure (Ref. Fig. Air Intake Flap Actuator - Deactivation/Reactivation) Subtask 49-16-00-040-052-A A.

Deactivation of the Air Intake Flap (1) Release the fasteners and remove the catwalk panel from the service frame. (2) Disconnect the electrical connectors 7527VC-A and 7527VC. (a) Disconnect the electrical connector 7527VC-A from the connector 7527VC. (b) Put a CAP - BLANKING on the electrical connector 7527VC-A. (c) Attach the electrical connector 7527VC-A to the air intake structure with a TIE WRAP. (3) Open the air intake flap manually if it is not in the fully open position. (a) Turn the manual drive shaft on the air intake flap-actuator 4015KM until the air intake flap is in the fully open position. NOTE: Make sure that the torque necessary to turn the manual drive shaft is not more than 0.3 mdaN (26.55 lbf.in) for the actuator 43-1-1100 Amendment 1, for the actuator 106-1-

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-003-A - Deactivation of the APU Air Intake Flap (131-9(A))

1100-02 not more than 0.4 mdaN (35.4 lbf.in). Be careful when you come to the mechanical stop at the end of travel. If you turn the manual drive shaft with more torque than the limit, damage to the air intake flap actuator will occur. NOTE: On the actuator 43-1-1100-Amendment 1, 47 turns are required for one full travel of the air intake flap actuator. On the actuator 106-1-1100 -02, 87 turns are required. (b) Make sure that the air intake flap is in the correct position. NOTE: The contour of the air intake flap must align with the contour of the air-channel upper wall. The TOLERANCE A in the flap close direction is max. 1 mm (0.0394 in.) at the aft edge of the air intake flap. No tolerance is permitted in the flap open direction. (4) Make a dummy connector with a jumper lead to close the ''FLAP OPEN''and ''FLAP CLOSE'' control circuit between the ECB 59KD and the air intake-flap actuator 4015KM. NOTE: Refer to Ref. ESPM 20-44-11 , AIPC 24920467 and AIPC 24920472 for information about electrical connector identifications. (a) Connect a JUMPER-WIRE between the pins C and D of a CONNECTOR E0052R14B12PNE. (b) Hold the jumper lead in position on the connector with a BACKSHELL ABS0638A14. (c) Paint the dummy connector red with Top Coat Polyurethane-- - External Structure (Material No. 04JAA3) to make sure that it is easily identified. (5) Connect the dummy connector to the connector 7527VC. (6) Put a WARNING NOTICE(S) in position in the cockpit to tell the flight crew that the air intake flap is deactivated in the open position. (7) Make an entry in the logbook to show that the air intake flap is deactivated in the open position and add the time which the MMEL 49-10-02 permits for the operation in this condition. 5.

Close-up Subtask 49-16-00-410-063-A A.

Close Access (1) Put the catwalk panel in position on the service frame and secure with the fasteners. (2) Make sure that the work area is clean and clear of tools and other items. (3) Set the light switch to off. (4) Close the maintenance door 314AR (Ref. AMM TASK 52-41-23-400-001) . (5) Remove the access platform(s).

Subtask 49-16-00-865-072-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 201-201, 204-214, 217-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 121VU APU/APU/CTL 2KD L42 121VU APU/ECB/SPLY 1KD L41

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-16-00-040-003-A - Deactivation of the APU Air Intake Flap (131-9(A))

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 8

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-51-00-040-001-A - Deactivation of the APU Bleed Load Control-Valve (GTCP 36-300)

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 TASK 49-51-00-040-001-A Deactivation of the APU Bleed Load Control-Valve (GTCP 36-300) WARNING:

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

Task Summary MMEL or CDL Ref MMEL 36-12-02A 1.

Reason for the Job MMEL 36-12-02A APU Bleed Valve

2

Job Set-up Information A.

Access YES

Test YES

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE

QTY DESIGNATION

** ON A/C 201-201, 233-233 No specific No specific No specific No specific

1 AR AR AR

ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 B.

Consumable Materials REFERENCE

DESIGNATION

** ON A/C 201-201, 233-233 (Material No. 05RAB9)

Adhesive Film Tape-- Aluminium Foil -

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 C. Work Zones and Access Panels

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-51-00-040-001-A - Deactivation of the APU Bleed Load Control-Valve (GTCP 36-300) ZONE/ACCESS

ZONE DESCRIPTION

** ON A/C 201-201, 233-233 315AL, 316AR ** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 D. Referenced Information REFERENCE ** ON A/C 201-201, 233-233 (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 29-00-00-864-001-A). (Ref. 52-41-00-010-001-A). (Ref. 52-41-00-410-001-A).

DESIGNATION

Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action Open the APU Doors for Access Close the APU Doors after Access

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 ** ON A/C 201-201, 233-233 Bleed Load Valve-Visual Position Indicator SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-51-00-040-001-A - Deactivation of the APU Bleed Load Control-Valve (GTCP 36-300)

FR80

B VISUAL POSITION INDICATOR FR84

OPEN

CLOSED OPEN

A

SHOWN IN THE CLOSED POSITION

316AR

A

315AL

EN

OP E

OP

CL

E OS

D

B N_MM_495100_4_AAM0_01_00

Figure 49-51-00-991-00100-00-A / SHEET 1/1 - Bleed Load Valve-Visual Position Indicator ** ON A/C 201-201, 233-233 | EMB SB 49-1058 for A/C 201-201, 233-233 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-51-00-040-001-A - Deactivation of the APU Bleed Load Control-Valve (GTCP 36-300)

3.

Job Set-up Subtask 49-51-00-860-054-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) On the panel 25VU, make sure that the APU MASTER SW pushbutton switch is off. (3) Put a warning notice in the cockpit to tell persons not to start the APU. (4) Make sure that the hydraulic systems are depressurized (Ref. AMM TASK 29-00-00-864-001) .

Subtask 49-51-00-865-050-A B.

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

DESIGNATION

** ON A/C 201-201, 233-233 121VU APU/APU/CTL 121VU APU/ECB/SPLY 122VU AIR BLEED/X FEED VALVE/NORM

FIN

2KD 1KD 1HV

LOCATION

L42 L41 Z20

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 Subtask 49-51-00-010-050-A C.

Get Access (1) Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position below the APU access doors 315AL and 316AR. (2) Open the APU access doors 315AL, 316AR (Ref. AMM TASK 52-41-00-010-001) . (3) Set the LIGHT control switch 11LJ to the ON position.

4.

Procedure (Ref. Fig. Bleed Load Valve-Visual Position Indicator SHEET 1) Subtask 49-51-00-040-050-A A.

Deactivation of the APU Bleed Load Control-Valve (8050KM) (1) Make sure that the APU bleed load control-valve position-indicator on the valve body shows the CLOSED position. (2) Disconnect the control-valve solenoid-valve electrical plug and attach it to the aircraft structure with Adhesive Film Tape-- Aluminium Foil - (Material No. 05RAB9). (3) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (4) Make sure that you put a WARNING NOTICE(S) in the cockpit to tell persons that the APU bleed load control-valve is isolated. (5) Make the following entry in the aircraft technical log: The APU bleed load control-valve is deactivated. The position indicator on the valve body shows the CLOSED position. Ignore the ECAM display which shows OPEN position.

5.

Close-up

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-51-00-040-001-A - Deactivation of the APU Bleed Load Control-Valve (GTCP 36-300)

Subtask 49-51-00-410-050-A A.

Close Access (1) Set the LIGHT control SW 11LJ to the OFF position. (2) Make sure that the work area is clean and clear of tools and other items. (3) Close the APU access doors 315AL, 316AR (Ref. AMM TASK 52-41-00-410-001) . (4) Remove the access platform(s).

Subtask 49-51-00-865-052-A B.

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

DESIGNATION

** ON A/C 201-201, 233-233 121VU APU/APU/CTL 121VU APU/ECB/SPLY 122VU AIR BLEED/X FEED VALVE/NORM

FIN

2KD 1KD 1HV

LOCATION

L42 L41 Z20

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 Subtask 49-51-00-860-055-A C.

Aircraft Maintenance Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (2) Put the related hydraulic system in the pressurized configuration (Ref. AMM TASK 29-00-00-864001) . (3) Remove the WARNING NOTICE(S).

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-51-00-040-002-A - Deactivation of the Bleed Control Valve (APS 3200)

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 TASK 49-51-00-040-002-A Deactivation of the Bleed Control Valve (APS 3200) WARNING:

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

Task Summary MMEL or CDL Ref MMEL 36-12-02A 1.

Reason for the Job MMEL 36-12-02A APU Bleed Valve

2

Job Set-up Information A.

Access YES

Test NO

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE

QTY DESIGNATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 No specific AR ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE No specific AR CAP - BLANKING No specific AR SAFETY CLIP - CIRCUIT BREAKER No specific 1 TIE WRAP No specific AR WARNING NOTICE(S) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 B.

Work Zones and Access Panels

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-51-00-040-002-A - Deactivation of the Bleed Control Valve (APS 3200)

ZONE/ACCESS

ZONE DESCRIPTION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 315AL, 316AR ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 C. Referenced Information REFERENCE

DESIGNATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 (Ref. 24-41-00-861-002-A). Energize the Aircraft Electrical Circuits from the External Power (Ref. 24-41-00-861-002-A-01). Energize the Aircraft Electrical Circuits from the APU (Ref. 24-41-00-861-002-A-02). Energize the Aircraft Electrical Circuits from Engine 1(2) (Ref. 24-41-00-862-002-A). De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 29-00-00-864-001-A). Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action (Ref. 52-41-00-010-001-A). Open the APU Doors for Access (Ref. 52-41-00-410-001-A). Close the APU Doors after Access ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 Bleed Control Valve-Visual Position Indicator SHEET 1 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-51-00-040-002-A - Deactivation of the Bleed Control Valve (APS 3200)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-51-00-040-002-A - Deactivation of the Bleed Control Valve (APS 3200)

FR80

A

FR84

SHOWN IN THE SURGE OPEN LOAD CLOSED POSITION OPEN

B

CLOSED

316AR

315AL

B EXAMPLE

A VISUAL POSITION INDICATOR

N_MM_495100_4_LAM0_01_00

Figure 49-51-00-991-00200-12-A / SHEET 1/1 - Bleed Control Valve-Visual Position Indicator ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231233, 236-238, 240-250, 350-350, 386-395, 406-415 | EMB SB 49-1029 for A/C 201-201, 233233 | EMB SB 49-1081 for A/C 215-216 | PRE SB 49-1082 for A/C 217-217 | EMB SB 491099 for A/C 219-220 | EMB SB 49-1105 for A/C 350-350 | EMB SB 49-1111 for A/C 204-204 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-51-00-040-002-A - Deactivation of the Bleed Control Valve (APS 3200)

3.

Job Set-up Subtask 49-51-00-860-050-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) On the panel 25VU, make sure that the APU MASTER SW pushbutton switch is off. (3) Put a warning notice in the cockpit to tell persons not to start the APU. (4) Make sure that the hydraulic systems are depressurized (Ref. AMM TASK 29-00-00-864-001) .

Subtask 49-51-00-865-053-A B.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 121VU APU/APU/CTL 2KD L42 121VU APU/ECB/SPLY 1KD L41 122VU AIR BLEED/X FEED VALVE/NORM 1HV Z20 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 Subtask 49-51-00-010-051-A C.

Get Access (1) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the APU access doors 315AL and 316AR. (2) Open the APU access doors 315AL, 316AR (Ref. AMM TASK 52-41-00-010-001) . (3) Set the LIGHT control switch 11LJ to the ON position.

4.

Procedure (Ref. Fig. Bleed Control Valve-Visual Position Indicator SHEET 1) Subtask 49-51-00-020-050-A A.

Deactivation (1) Make sure that the Bleed Control Valve position-indicator on the valve body shows the SURGE OPEN/LOAD CLOSED position. (2) Disconnect the Bleed-Control Valve (BCV) electrical-connector (P33). (3) Put a CAP - BLANKING on the electrical connector of the BCV. (4) Put a CAP - BLANKING on the (P33) harness electrical connector.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-51-00-040-002-A - Deactivation of the Bleed Control Valve (APS 3200)

(5) Secure the plug (P33) with TIE WRAP to aircraft structure. (6) Make sure that you put a WARNING NOTICE(S) in the cockpit to tell persons that the Bleed Control Valve is deactivated and the APU cannot supply bleed air. (7) Make an entry in the logbook. NOTE: When the APU bleed control-valve is deactivated: - The position indicator on the valve body is in the SURGE OPEN/LOAD CLOSED position. You can ignore the ECAM display which shows OPEN position. - You can ignore the Class 1 Fault BCV LVDT during compensation (FC138). It will no longer be shown after you disconnect and connect again the ECB. 5.

Close-up Subtask 49-51-00-410-052-A A.

Close Access (1) Set the LIGHT control switch 11LJ to the OFF position. (2) Make sure that the work area is clean and clear of tools and other items. (3) Close the APU access doors 315AL, 316AR (Ref. AMM TASK 52-41-00-410-001) . (4) Remove the access platform(s). (5) Remove the WARNING NOTICE(S).

Subtask 49-51-00-865-054-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 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 121VU APU/APU/CTL 2KD L42 121VU APU/ECB/SPLY 1KD L41 122VU AIR BLEED/X FEED VALVE/NORM 1HV Z20 ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 Subtask 49-51-00-860-051-A C.

Aircraft Maintenance Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-51-00-040-004-A - Deactivation of the APU Load Control-Valve (131-9(A))

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 TASK 49-51-00-040-004-A Deactivation of the APU Load Control-Valve (131-9(A)) WARNING:

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

Task Summary MMEL or CDL Ref MMEL 36-12-02A 1.

Reason for the Job MMEL 36-12-02A APU Bleed Valve

2

Job Set-up Information A.

Access YES

Test NO

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE

QTY DESIGNATION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 No specific 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE No specific AR CAP - BLANKING No specific AR SAFETY CLIP - CIRCUIT BREAKER No specific AR WARNING NOTICE(S) ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 B.

Consumable Materials REFERENCE

DESIGNATION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 (Material No. 05RAB9) Adhesive Film Tape-- Aluminium Foil Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-51-00-040-004-A - Deactivation of the APU Load Control-Valve (131-9(A))

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 C. Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 315AL, 316AR ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 D. Referenced Information REFERENCE

DESIGNATION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 (Ref. 24-41-00-862-002-A). De-energize the Aircraft Electrical Circuits Supplied from the External Power (Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU (Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) (Ref. 24-42-00-861-001-A). Energize the Ground Service Network from the External Power (Ref. 29-00-00-864-001-A). Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action (Ref. 52-41-00-010-001-A). Open the APU Doors for Access (Ref. 52-41-00-410-001-A). Close the APU Doors after Access ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-51-00-040-004-A - Deactivation of the APU Load Control-Valve (131-9(A))

REFERENCE DESIGNATION EMB SB 49-1082 for A/C 201-201, 211-211 ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 Load Control-Valve Position-Indicator SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-51-00-040-004-A - Deactivation of the APU Load Control-Valve (131-9(A))

FR80

Z315 Z316

FR84

A

A

316AR

315AL

B VISUAL POSITION INDICATOR SHOWN IN THE CLOSED POSISTION

B

N_MM_495100_4_PAM0_01_00

Figure 49-51-00-991-00300-16-A / SHEET 1/1 - Load Control-Valve Position-Indicator ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301349, 351-385, 396-405, 416-450, 500-600 | EMB SB 49-1069 for A/C 204-204 | EMB SB 49-1082 for A/C 201-201, 211-211 | POST SB 49-1082 for A/C 217-217 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-51-00-040-004-A - Deactivation of the APU Load Control-Valve (131-9(A))

3.

Job Set-up Subtask 49-51-00-860-057-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) . (2) On the panel 25VU, make sure that the APU MASTER SW p/bsw is OFF. (3) Put a warning notice in the cockpit to tell persons not to start the APU. (4) Make sure that the hydraulic systems are depressurized (Ref. AMM TASK 29-00-00-864-001) .

Subtask 49-51-00-865-056-A B.

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

DESIGNATION

FIN

LOCATION

** ON A/C 201-201, 204-214, 217-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 121VU APU/APU/CTL 2KD L42 121VU APU/ECB/SPLY 1KD L41 122VU AIR BLEED/X FEED VALVE/NORM 1HV Z20 ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 Subtask 49-51-00-010-054-A C.

Get Access (1) Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position below the APU access doors 315AL and 316AR. (2) Open the APU access doors 315AL, 316AR (Ref. AMM TASK 52-41-00-010-001) . (3) Set the LIGHT control SW 11LJ to the ON position.

4.

Procedure (Ref. Fig. Load Control-Valve Position-Indicator SHEET 1) Subtask 49-51-00-040-051-A A.

Deactivation of the APU Load Control-Valve (1) Make sure that the APU load control-valve position-indicator on the valve body shows the CLOSED position. (2) Disconnect the APU load control-valve electrical plug (P12) and attach it to the aircraft structure with Adhesive Film Tape-- Aluminium Foil - (Material No. 05RAB9). (3) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (4) Make sure that you put a WARNING NOTICE(S) in the cockpit to tell persons that the APU load control-valve is deactivated. (5) Make the following entry in the aircraft technical log:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-51-00-040-004-A - Deactivation of the APU Load Control-Valve (131-9(A))

The APU bleed load control-valve is deactivated. The position indicator on the valve body shows the CLOSED position. Ignore the ECAM display which shows OPEN position. 5.

Close-up Subtask 49-51-00-410-056-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Set the LIGHT control SW 11LJ to the OFF position. (3) Close the APU access doors 315AL, 316AR (Ref. AMM TASK 52-41-00-410-001) . (4) Remove the access platform(s).

Subtask 49-51-00-865-057-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 201-201, 204-214, 217-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 121VU APU/APU/CTL 2KD L42 121VU APU/ECB/SPLY 1KD L41 122VU AIR BLEED/X FEED VALVE/NORM 1HV Z20 ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 Subtask 49-51-00-860-058-A C.

Aircraft Maintenance Configuration (1) Put the related hydraulic system in the pressurized configuration (Ref. AMM TASK 29-00-00-864001) . (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (3) Remove the WARNING NOTICE(S).

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 6

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-70-00-040-001-A - APU LOW OIL LEVEL Indication on ECAM inoperative (GTCP 36-300)

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 TASK 49-70-00-040-001-A APU LOW OIL LEVEL Indication on ECAM inoperative (GTCP 36-300) Task Summary MMEL or CDL Ref MMEL 49-07-41A

Access YES

Test NO

Specific Tools NO

1.

Reason for the Job MMEL 49-07-41A Low Oil Level Message on the APU SD page (FAA only)

2

Job Set-up Information A.

Mhr 00.7

E/T 00.7

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE

QTY DESIGNATION

** ON A/C 201-201, 233-233 No specific 1

ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

** ON A/C 201-201, 233-233 315AL, 316AR ** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 C. Referenced Information REFERENCE

DESIGNATION

** ON A/C 201-201, 233-233 (Ref. 24-42-00-861-001-A). (Ref. 49-90-00-600-001-A). (Ref. 52-41-00-010-001-A). (Ref. 52-41-00-410-001-A).

Energize the Ground Service Network from the External Power Check Oil Level and Replenish (GTCP 36-300) Open the APU Doors for Access Close the APU Doors after Access

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-70-00-040-001-A - APU LOW OIL LEVEL Indication on ECAM inoperative (GTCP 36-300)

** ON A/C 201-201, 233-233 EMB SB 49-1058 for A/C 201-201, 233-233 3.

Job Set-up Subtask 49-70-00-860-050-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) . (2) On the panel 25VU, make sure that the APU MASTER SW p/bsw is OFF. (3) Put a warning notice in the cockpit to tell persons not to start the APU.

Subtask 49-70-00-010-050-A B.

Get Access (1) Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position below the APU access door 315AL and 316AR. (2) Open the APU access doors 315AL, 316AR (Ref. AMM TASK 52-41-00-010-001) . (3) Set the LIGHT control SW 11LJ to the ON position.

4.

Procedure Subtask 49-70-00-210-050-A A.

Maintenance Action (1) Do a check of the APU oil level on the oil sight glass. · Replenish, if necessary (Ref. AMM TASK 49-90-00-600-001) . (2) Examine the APU oil consumption: · If the oil consumption is more than 0.61 l (0.64 USquarts) per 10 APU operating-hours you have to monitor continuously the oil-consumption. (3) Visually inspect the APU and plumbing for oil leaks: · Leaks are not permitted.

5.

Close-up Subtask 49-70-00-860-051-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Set the LIGHT control switch 11LJ to the off position. (3) Close the APU access doors 316AR, 315AL (Ref. AMM TASK 52-41-00-410-001) . (4) Remove the access platform(s). (5) Remove the WARNING NOTICE(S). (6) Put a temporary placard in the cockpit to tell persons that the APU LOW OIL LEVEL Indication on the APU SD page is inoperative. (7) Make an applicable entry in the logbook.

End of document Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-70-00-040-002-A - APU LOW OIL LEVEL Indication on ECAM inoperative (APS 3200)

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 TASK 49-70-00-040-002-A APU LOW OIL LEVEL Indication on ECAM inoperative (APS 3200) Task Summary MMEL or CDL Ref MMEL 49-07-41A

Access YES

Test NO

Specific Tools NO

1.

Reason for the Job MMEL 49-07-41A Low Oil Level Message on the APU SD page (FAA only)

2

Job Set-up Information A.

Mhr 00.7

E/T 00.7

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE

QTY DESIGNATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 No specific 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 315AL, 316AR

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-70-00-040-002-A - APU LOW OIL LEVEL Indication on ECAM inoperative (APS 3200)

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 C. Referenced Information REFERENCE

DESIGNATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240-250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 (Ref. 24-42-00-861-001-A). Energize the Ground Service Network from the External Power (Ref. 49-90-00-600-004-A). Check Oil Level and Replenish (APS 3200) (Ref. 52-41-00-010-001-A). Open the APU Doors for Access (Ref. 52-41-00-410-001-A). Close the APU Doors after Access ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-204, 215-217, 219-221, 227-228, 231-233, 236-238, 240250, 350-350, 386-395, 406-415 PRE SB 49-1082 for A/C 217-217 EMB SB 49-1029 for A/C 201-201, 233-233 EMB SB 49-1081 for A/C 215-216 EMB SB 49-1099 for A/C 219-220 EMB SB 49-1105 for A/C 350-350 EMB SB 49-1111 for A/C 204-204 3.

Job Set-up Subtask 49-70-00-860-052-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) . (2) On the panel 25VU, make sure that the APU MASTER SW p/bsw is OFF. (3) Put a warning notice in the cockpit to tell persons not to start the APU.

Subtask 49-70-00-010-051-A B.

Get Access (1) Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position below the APU access door 315AL and 316AR. (2) Open the APU access doors 315AL, 316AR (Ref. AMM TASK 52-41-00-010-001) . (3) Set the LIGHT control SW 11LJ to the ON position.

4.

Procedure

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-70-00-040-002-A - APU LOW OIL LEVEL Indication on ECAM inoperative (APS 3200)

Subtask 49-70-00-210-051-A A.

Maintenance Action (1) Do a check of the APU oil level on the oil sight glass. · Replenish, if necessary (Ref. AMM TASK 49-90-00-600-004) . (2) Examine the APU oil consumption: · If the oil consumption is more than 0.9 l (0.95 USquarts) per 10 APU operating-hours you have to monitor continuously the oil-consumption. (3) Visually inspect the APU and plumbing for oil leaks: · Leaks are not permitted.

5.

Close-up Subtask 49-70-00-860-053-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Set the LIGHT control switch 11LJ to the off position. (3) Close the APU access doors 316AR, 315AL (Ref. AMM TASK 52-41-00-410-001) . (4) Remove the access platform(s). (5) Remove the WARNING NOTICE(S). (6) Put a temporary placard in the cockpit to tell persons that the APU LOW OIL LEVEL Indication on the APU SD page is inoperative. (7) Make an applicable entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-70-00-040-003-A - APU LOW OIL LEVEL Indication on ECAM inoperative (131-9(A))

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 TASK 49-70-00-040-003-A APU LOW OIL LEVEL Indication on ECAM inoperative (131-9(A)) Task Summary MMEL or CDL Ref MMEL 49-07-41A

Access YES

Test NO

Specific Tools NO

1.

Reason for the Job MMEL 49-07-41A Low Oil Level Message on the APU SD page (FAA only)

2

Job Set-up Information A.

Mhr 00.7

E/T 00.7

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE

QTY DESIGNATION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 No specific 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 315AL, 316AR ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-70-00-040-003-A - APU LOW OIL LEVEL Indication on ECAM inoperative (131-9(A)) EMB SB 49-1082 for A/C 201-201, 211-211 C. Referenced Information REFERENCE

DESIGNATION

** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416-450, 500-600 POST SB 49-1082 for A/C 217-217 (Ref. 24-42-00-861-001-A). Energize the Ground Service Network from the External Power (Ref. 49-90-00-600-007-A). Check Oil Level and Replenish (131-9(A)) (Ref. 52-41-00-010-001-A). Open the APU Doors for Access (Ref. 52-41-00-410-001-A). Close the APU Doors after Access ** ON A/C 201-201, 204-214, 218-218, 222-226, 229-230, 234-235, 239-239, 301-349, 351-385, 396-405, 416450, 500-600 POST SB 49-1082 for A/C 217-217 EMB SB 49-1069 for A/C 204-204 EMB SB 49-1082 for A/C 201-201, 211-211 3.

Job Set-up Subtask 49-70-00-860-054-A A.

Aircraft Maintenance Configuration (1) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) . (2) On the panel 25VU, make sure that the APU MASTER SW p/bsw is OFF. (3) Put a warning notice in the cockpit to tell persons not to start the APU.

Subtask 49-70-00-010-052-A B.

Get Access (1) Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position below the APU access door 315AL and 316AR. (2) Open the APU access doors 315AL, 316AR (Ref. AMM TASK 52-41-00-010-001) . (3) Set the LIGHT control SW 11LJ to the ON position.

4.

Procedure Subtask 49-70-00-210-052-A A.

Maintenance Action (1) Do a check of the APU oil level on the oil sight glass. · Replenish, if necessary (Ref. AMM TASK 49-90-00-600-007) . (2) Examine the APU oil consumption: · If the oil consumption is more than 0.93 l (0.99 USquarts) per 10 APU operating-hours you have to monitor continuously the oil-consumption. (3) Visually inspect the APU and plumbing for oil leaks: · Leaks are not permitted.

5.

Close-up

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 49-70-00-040-003-A - APU LOW OIL LEVEL Indication on ECAM inoperative (131-9(A))

Subtask 49-70-00-860-055-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Set the LIGHT control switch 11LJ to the off position. (3) Close the APU access doors 316AR, 315AL (Ref. AMM TASK 52-41-00-410-001) . (4) Remove the access platform(s). (5) Remove the WARNING NOTICE(S). (6) Put a temporary placard in the cockpit to tell persons that the APU LOW OIL LEVEL Indication on the APU SD page is inoperative. (7) Make an applicable entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-008-A - Deactivation of the Door Locking System Selector on the Back Up Panel

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 TASK 52-51-00-040-008-A Deactivation of the Door Locking System Selector on the Back Up Panel Task Summary MMEL or CDL Ref MMEL 52-01-03-34A

Access NO

Test NO

Specific Tools NO

Mhr 00.2

1.

Reason for the Job MMEL 52-01-03-34A OFF Function of the LKG SYS on the CKPT DOOR BK UP Overhead Panel

2

Job Set-up Information A.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-42-00-862-001-A).

3.

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

E/T 00.2

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Ground Service Network Supplied from the External Power

Job Set-up

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 EMB SB 52-1115 for A/C 237-237 Subtask 52-51-00-860-088-A A.

Aircraft Maintenance Configuration (1) Make sure that the aircraft electrical circuits are energized (Ref. AMM TASK 24-41-00-861-002) . (2) Make sure that access to the cockpit is available.

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 Subtask 52-51-00-865-075-A B.

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

DESIGNATION

** ON A/C 227-228 PRE SB 11-1047 for A/C 227-228 122VU DOORS/PAX/MONG

FIN

1MQ

LOCATION

T13

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-008-A - Deactivation of the Door Locking System Selector on the Back Up Panel PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 231-232, 237-237, 242-242, 244-250 POST SB 11-1047 for A/C 227-228 EMB SB 11-1047 for A/C 231-232, 237-237, 244-244 EMB SB 25-1326 for A/C 231-232, 237-237, 244-244 122VU DOORS CKPT LOCK

1MQ

T13

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 4.

Procedure

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 EMB SB 52-1115 for A/C 237-237 Subtask 52-51-00-040-059-A A.

Do the deactivation of the back-up control system NOTE: For maintenance purposes only, the normal and back-up systems can be deactivated when you do the related maintenance procedure.

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 Subtask 52-51-00-865-089-A B.

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

DESIGNATION

** ON A/C 227-228 PRE SB 11-1047 for A/C 227-228 122VU DOORS/PAX/MONG

FIN

LOCATION

1MQ

T13

4MQ

S10

1MQ

T13

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 EMB SB 52-1115 for A/C 237-237 122VU CKPT/OVRD SYS/SPLY ** ON A/C 231-232, 237-237, 242-242, 244-250 POST SB 11-1047 for A/C 227-228 EMB SB 11-1047 for A/C 231-232, 237-237, 244-244 EMB SB 25-1326 for A/C 231-232, 237-237, 244-244 122VU DOORS CKPT LOCK ** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 5.

Close-up

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-008-A - Deactivation of the Door Locking System Selector on the Back Up Panel EMB SB 52-1115 for A/C 237-237 Subtask 52-51-00-860-089-A A.

Put the aircraft back to the serviceable condition. (1) Make an entry into the aircraft technical log that the Back Up Control System is deactivated. (2) Make sure that the work area is clean and clear of tools and other items. (3) De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-011-A - Check of the Pressure Rate Sensor

** ON A/C ALL TASK 52-51-00-040-011-A Check of the Pressure Rate Sensor Task Summary MMEL or CDL Ref MMEL 52-01-01-03A

Access NO

Test NO

Specific Tools NO

1.

Reason for the Job MMEL 52-01-01-03A Pressure Rate Sensor on the CKPT DOOR CONT Overhead Panel

2

Job Set-up Information A.

Nb Men 1

QTY DESIGNATION 1 PUMP - VACUUM

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

3.

E/T 00.3

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Mhr 00.3

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up

** ON A/C ALL EMB SB 25-1305 for A/C 210-210 Subtask 52-51-00-860-097-A A.

Aircraft Maintenance Configuration (1) Make sure that the access to the cockpit is available. (2) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

** ON A/C ALL Subtask 52-51-00-865-083-A B.

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

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-011-A - Check of the Pressure Rate Sensor

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 204-205, 207-207, 210-210, 217-217, 222-222, 227-228 PRE SB 11-1047 for A/C 204-205, 207-207, 210-210, 217-217, 222-222, 227-228 EMB SB 25-1305 for A/C 210-210 122VU DOORS/PAX/MONG

1MQ

T13

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 206-206, 208-209, 211-216, 218-221, 223-226, 229-239, 241-242, 244-250, 301-450, 500-600 POST SB 11-1047 for A/C 204-204, 217-217, 222-222, 227-228 EMB SB 11-1047 for A/C 201-201, 203-203, 206-206, 209-209, 211-211, 218-220, 229-235, 237-237, 244-244 EMB SB 25-1326 for A/C 231-232, 237-237, 244-244 122VU DOORS CKPT LOCK 1MQ T13 ** ON A/C 240-240, 243-243 POST SB 11-1047 for A/C 205-205, 207-207, 210-210 EMB SB 11-1047 for A/C 240-240, 243-243 EMB SB 25-1305 for A/C 210-210 122VU COCKPIT DOOR LOCK SYSTEM

1MQ

T13

** ON A/C ALL 4.

Procedure

** ON A/C ALL EMB SB 25-1305 for A/C 210-210 Subtask 52-51-00-780-051-A A.

Verification of the remaining Pressure Rate Sensor (1) Do the test to make sure that the remaining pressure sensor in the control unit 24MQ operates correctly. (2) Simulate a rapid decompression of the cabin pressure with a PUMP - VACUUM. NOTE: If LED CHAN 1 is on, examine RH pressure sensor hole. If LED CHAN 2 is on, examine LH pressure sensor hole.

ACTION 1.On the CKPT DOOR CONT Panel 20VU: · put the vacuum pump in the applicable pressure sensor hole and operate it.

RESULT On the Cockpit Door: · you can hear a clacking noise from the solenoids of the electrical release strikes. · as soon as an equal pressure occurs the electrical release strikes operate automatically to lock the cockpit door.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-011-A - Check of the Pressure Rate Sensor

ACTION · remove the vacuum pump from the pressure sensor.

RESULT

** ON A/C ALL 5.

Close-up

** ON A/C ALL EMB SB 25-1305 for A/C 210-210 Subtask 52-51-00-860-098-A A.

Put the aircraft back to the serviceable condition. (1) Make sure that the work area is clean and clear of tools and other items. (2) Put an applicable placard in position in the cockpit (refer to your standard practices and local regulations). (3) Make an entry in the logbook. (4) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-012-A - Check of the Pressure Rate Sensor of the Back Up Control Panel

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 TASK 52-51-00-040-012-A Check of the Pressure Rate Sensor of the Back Up Control Panel Task Summary MMEL or CDL Ref MMEL 52-01-02-03A

Access NO

Test NO

Specific Tools NO

Mhr 00.3

1.

Reason for the Job MMEL 52-01-02-03A Pressure Rate Sensor on the CKPT DOOR CONT BK UP Overhead Panel

2

Job Set-up Information A.

QTY DESIGNATION 1 PUMP - VACUUM

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-42-00-862-001-A).

3.

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

E/T 00.3

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Ground Service Network Supplied from the External Power

Job Set-up

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 EMB SB 52-1115 for A/C 237-237 Subtask 52-51-00-860-099-A A.

Aircraft Maintenance Configuration (1) Make sure that the aircraft electrical circuits are energized (Ref. AMM TASK 24-41-00-861-002) . (2) Make sure that access to the cockpit is available.

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 Subtask 52-51-00-865-084-A B.

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

DESIGNATION

** ON A/C 227-228 PRE SB 11-1047 for A/C 227-228 122VU DOORS/PAX/MONG

FIN

1MQ

LOCATION

T13

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-012-A - Check of the Pressure Rate Sensor of the Back Up Control Panel PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 EMB SB 52-1115 for A/C 237-237 122VU CKPT/OVRD SYS/SPLY

4MQ

S10

1MQ

T13

** ON A/C 231-232, 237-237, 242-242, 244-250 POST SB 11-1047 for A/C 227-228 EMB SB 11-1047 for A/C 231-232, 237-237, 244-244 EMB SB 25-1326 for A/C 231-232, 237-237, 244-244 122VU DOORS CKPT LOCK ** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 4.

Procedure

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 EMB SB 52-1115 for A/C 237-237 Subtask 52-51-00-780-052-A A.

Verification of the remaining Pressure Rate Sensor (1) Do the test to make sure that the remaining pressure sensor in the back up control unit 28MQ operates correctly. (2) Simulate a rapid decompression of the cabin pressure with a PUMP - VACUUM. (3) Set the guarded toggle switch 21MQ on the back up control panel 271VU to the "BKUP" position. NOTE: If LED CHAN 1 is on, examine RH pressure sensor hole. If LED CHAN 2 is on, examine LH pressure sensor hole.

ACTION 1.On the Back Up Control Unit 295VU: · put the vacuum pump in the applicable pressure sensor hole and operate it.

RESULT On the Cockpit Door: · you can hear a clacking noise from the solenoids of the electrical release strikes. · as soon as an equal pressure occurs the electrical release strikes operate automatically to lock the cockpit door.

(4) Remove the vacuum pump from the pressure sensor. ** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 5.

Close-up

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 EMB SB 52-1115 for A/C 237-237 Subtask 52-51-00-860-100-A

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-012-A - Check of the Pressure Rate Sensor of the Back Up Control Panel

A.

Put the aircraft back to the serviceable condition. (1) Make sure that the work area is clean and clear of tools and other items. (2) Put an applicable placard in position in the cockpit (refer to your standard practices and local regulations). (3) Make an entry in the logbook. (4) De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-00-00-040-001-A - Check Pressure of Emergency Cylinder/Accumulator of the Passenger/Crew Doors after Programming and Test Panel (PTP) Inoperative

** ON A/C 201-201, 203-205, 207-207, 210-211, 217-217, 219-220, 231-234, 237-237, 240-240, 243-250 TASK 52-00-00-040-001-A Check Pressure of Emergency Cylinder/Accumulator of the Passenger/Crew Doors after Programming and Test Panel (PTP) Inoperative 1.

Reason for the Job MMEL 52-10-06A DOOR PRESS LOW Message on the Programming and Test Panel (PTP) STATUS Page (If Installed)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS 830 840 831, 832, 841, 842

ZONE DESCRIPTION L PASSENGER/CREW DOORS & EMERGENCY EXITS R PASSENGER/CREW DOORS & EMERGENCY EXITS

C. Referenced Information REFERENCE (Ref. 52-10-00-010-001-A). (Ref. 52-10-00-410-001-A).

DESIGNATION Opening of the Passenger/Crew Door Closing of the Passenger/Crew Door

** ON A/C 203-203, 211-211, 231-232, 237-237, 244-250 (Ref. 52-10-00-614-001-A). Discharging/Charging of the Door Damper and Emergency Operation Cylinder of the Passenger/Crew Doors ** ON A/C 201-201, 203-205, 207-207, 210-211, 217-217, 219-220, 231-234, 237-237, 240-240, 243-250 (Ref. 52-10-00-860-001-A). Special Precautions before Work on the Passenger/Crew Door (Ref. 52-10-00-860-002-A). Special Precautions after Work on the Passenger/Crew Door ** ON A/C 201-201, 204-205, 207-207, 210-210, 217-217, 219-220, 233-234, 240-240, 243-243 Check of the Pressure of the Door Damper SHEET 1 ** ON A/C 203-203, 211-211, 231-232, 237-237, 244-250 Check of the Pressure of the Door Damper SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-00-00-040-001-A - Check Pressure of Emergency Cylinder/Accumulator of the Passenger/Crew Doors after Programming and Test Panel (PTP) Inoperative

B

A

Z842

A

Z832

Z841

B Z831

A 1 2

D EXAMPLE

D

C

B

C

C

EXAMPLE TEMP

PRESSURE

(°C)

(PSI ±5%)

+50 +40 +30 +20 +10 0 -10 -20 -30 -40

1950 1880 1810 1740 1660 1610 1540 1465 1395 1325

2

D

N_MM_520000_4_DAR0_01_01

Figure 52-00-00-991-00200-00-A / SHEET 1/1 - Check of the Pressure of the Door Damper ** ON A/C 016-022, 024-100, 112-150, 201-201, 204-210, 212222, 226-230, 233-235, 238-240, 243-243, 301-400, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-00-00-040-001-A - Check Pressure of Emergency Cylinder/Accumulator of the Passenger/Crew Doors after Programming and Test Panel (PTP) Inoperative

A

A

Z842

EXAMPLE

A

Z832

Z841

A B

Z831

A

B

C

C

"GO AREA" "G" = GREEN "Y" = YELLOW

"Y"

"G" 1

1740

RED

0

RED

3000

N_MM_520000_4_DAS0_01_02

Figure 52-00-00-991-00200-00-B / SHEET 1/1 - Check of the Pressure of the Door Damper ** ON A/C 203-203, 211-211, 223-225, 231-232, 236-237, 241-242, 244-250 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-00-00-040-001-A - Check Pressure of Emergency Cylinder/Accumulator of the Passenger/Crew Doors after Programming and Test Panel (PTP) Inoperative

3.

Job Set-up Subtask 52-00-00-010-056-A A.

Get Access (1) Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position: (a) For the left passenger/crew door at zone 831 or 832. (b) For the right passenger/crew door, at zone 841 or 842. (2) Open the passenger/crew door 831, 841, 832 or 842 (Ref. AMM TASK 52-10-00-010-001) . (3) Obey the special precautions before you start work on the door (Ref. AMM TASK 52-10-00-860001) .

4.

Procedure

** ON A/C 201-201, 204-205, 207-207, 210-210, 217-217, 219-220, 233-234, 240-240, 243-243 (Ref. Fig. Check of the Pressure of the Door Damper SHEET 1) ** ON A/C 203-203, 211-211, 231-232, 237-237, 244-250 (Ref. Fig. Check of the Pressure of the Door Damper SHEET 1) ** ON A/C 201-201, 204-205, 207-207, 210-210, 217-217, 219-220, 233-234, 240-240, 243-243 Subtask 52-00-00-210-054-A A.

Inspection of the Pressure Indication of the Damper and Emergency Operation Cylinder (1) To get a correct pressure value, let the air bottle become stable at the ambient temperature before you do the inspection. (2) Do a check of the pointer in the pressure gauge (1) on the cylinder door bottle. (3) Read the pressure value shown on the pressure gauge (1). (a) Compare this value with the value on the placard (2) for the ambient temperature. (4) If the pressure is not correct, do not operate the door and refer to the MMEL document for dispatch conditions. (a) Make an entry in the logbook.

** ON A/C 203-203, 211-211, 231-232, 237-237, 244-250 Subtask 52-00-00-210-054-B A.

Inspection of the Pressure Indication of the Damper and Emergency Operation Cylinder (1) To get the correct pressure, let the cylinder become stable at ambient temperature before you do the inspection. (2) Do a check of the pointer of the pressure gauge (1) : (a) If the pointer of the pressure gauge (1) is in the green area (GO), you can use the door in emergency condition without limit. (b) If the pointer of the pressure gauge (1) is in the yellow area (GO IF), you can use the door in emergency condition until the next night stop. 1

At the next night stop, fill the cylinder until the pointer of the pressure gauge (1) is in the green area again (Ref. AMM TASK 52-10-00-614-001) .

(3) If the pointer in the pressure gauge (1) is in the red area (NO GO): (a) You cannot open the door in emergency condition. Refer to the MMEL for dispatch conditions. (b) Make an entry in the logbook. Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-00-00-040-001-A - Check Pressure of Emergency Cylinder/Accumulator of the Passenger/Crew Doors after Programming and Test Panel (PTP) Inoperative

** ON A/C 201-201, 203-205, 207-207, 210-211, 217-217, 219-220, 231-234, 237-237, 240-240, 243-250 5.

Close-up Subtask 52-00-00-410-052-A A.

Close Access (1) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (2) Obey the special precautions after work on the door (Ref. AMM TASK 52-10-00-860-002) . (3) Close the applicable passenger/crew door 831 or 841 or 832 or 842 (Ref. AMM TASK 52-10-00-410001) . (4) Remove the access platform(s). (5) Make sure that the work area is clean and clear of tools and other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-00-00-040-003-A - Check of the Pressure of the Emergency Cylinder/Accumulator of the Passenger/Crew Doors after the Flight Attendant Panel (FAP) Stops

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 TASK 52-00-00-040-003-A Check of the Pressure of the Emergency Cylinder/Accumulator of the Passenger/Crew Doors after the Flight Attendant Panel (FAP) Stops Task Summary MMEL or CDL Ref MMEL 52-10-06A

Access YES

Test YES

Specific Tools NO

Mhr

1.

Reason for the Job MMEL 52-10-06A CHECK DOOR PRESSURE Message on the Flight Attendant Panel (FAP) (If Installed)

2

Job Set-up Information A.

Nb Men

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

E/T

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS 830 840 831, 832, 841, 842

ZONE DESCRIPTION L PASSENGER/CREW DOORS & EMERGENCY EXITS R PASSENGER/CREW DOORS & EMERGENCY EXITS

C. Referenced Information REFERENCE (Ref. 52-10-00-010-001-A). (Ref. 52-10-00-410-001-A).

DESIGNATION Opening of the Passenger/Crew Door Closing of the Passenger/Crew Door

** ON A/C 203-203, 211-211, 223-225, 231-232, 236-237, 241-242, 244-250 (Ref. 52-10-00-614-001-A). Discharging/Charging of the Door Damper and Emergency Operation Cylinder of the Passenger/Crew Doors ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 (Ref. 52-10-00-860-001-A). Special Precautions before Work on the Passenger/Crew Door (Ref. 52-10-00-860-002-A). Special Precautions after Work on the Passenger/Crew Door ** ON A/C 016-022, 024-100, 112-150, 201-201, 204-210, 212-222, 226-230, 233-235, 238-240, 243-243, 301-400, 500-600 Check of the Pressure of the Door Damper SHEET 1 ** ON A/C 203-203, 211-211, 223-225, 231-232, 236-237, 241-242, 244-250 Check of the Pressure of the Door Damper SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-00-00-040-003-A - Check of the Pressure of the Emergency Cylinder/Accumulator of the Passenger/Crew Doors after the Flight Attendant Panel (FAP) Stops

B

A

Z842

A

Z832

Z841

B Z831

A 1 2

D EXAMPLE

D

C

B

C

C

EXAMPLE TEMP

PRESSURE

(°C)

(PSI ±5%)

+50 +40 +30 +20 +10 0 -10 -20 -30 -40

1950 1880 1810 1740 1660 1610 1540 1465 1395 1325

2

D

N_MM_520000_4_DAR0_01_01

Figure 52-00-00-991-00200-00-A / SHEET 1/1 - Check of the Pressure of the Door Damper ** ON A/C 016-022, 024-100, 112-150, 201-201, 204-210, 212222, 226-230, 233-235, 238-240, 243-243, 301-400, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-00-00-040-003-A - Check of the Pressure of the Emergency Cylinder/Accumulator of the Passenger/Crew Doors after the Flight Attendant Panel (FAP) Stops

A

A

Z842

EXAMPLE

A

Z832

Z841

A B

Z831

A

B

C

C

"GO AREA" "G" = GREEN "Y" = YELLOW

"Y"

"G" 1

1740

RED

0

RED

3000

N_MM_520000_4_DAS0_01_02

Figure 52-00-00-991-00200-00-B / SHEET 1/1 - Check of the Pressure of the Door Damper ** ON A/C 203-203, 211-211, 223-225, 231-232, 236-237, 241-242, 244-250 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-00-00-040-003-A - Check of the Pressure of the Emergency Cylinder/Accumulator of the Passenger/Crew Doors after the Flight Attendant Panel (FAP) Stops

3.

Job Set-up Subtask 52-00-00-010-053-A A.

Get Access (1) Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position: (a) For the left passenger/crew door, at zone 831 or 832. (b) For the right passenger/crew door, at zone 841 or 842. (2) Open passenger/crew door 831, 841, 832 or 842 (Ref. AMM TASK 52-10-00-010-001) . (3) Obey the special precautions before you start work on the door (Ref. AMM TASK 52-10-00-860001) .

4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 204-210, 212-222, 226-230, 233-235, 238-240, 243-243, 301400, 500-600 (Ref. Fig. Check of the Pressure of the Door Damper SHEET 1) ** ON A/C 203-203, 211-211, 223-225, 231-232, 236-237, 241-242, 244-250 (Ref. Fig. Check of the Pressure of the Door Damper SHEET 1) ** ON A/C 016-022, 024-100, 112-150, 201-201, 204-210, 212-222, 226-230, 233-235, 238-240, 243-243, 301400, 500-600 Subtask 52-00-00-210-056-A A.

Inspection of the Pressure Indication of the Damper and Emergency Operation Cylinder (1) To get a correct pressure value, let the air bottle become stable at ambient temperature before you do the inspection. (2) Do a check of the pointer of the pressure gauge (1) on the cylinder door bottle. (3) Read the pressure value shown on the pressure gauge (1). (a) Compare this value with the value on the placard (2) related to the ambient temperature. (4) If the pressure is not correct, do not operate the door and refer to the MMEL document for the dispatch conditions. (5) Make an entry in the logbook.

** ON A/C 203-203, 211-211, 223-225, 231-232, 236-237, 241-242, 244-250 Subtask 52-00-00-210-056-C A.

Inspection of the Pressure Indication of the Damper and Emergency Operation Cylinder (1) To get the correct pressure value, let the cylinder become stable at ambient temperature before you do the inspection. (2) Do a check of the pointer of the pressure gauge (1): (a) If the pointer of the pressure gauge (1) is in the green area (GO), you can use the door in emergency condition without limit. (b) If the pointer of the pressure gauge (1) is in the yellow area (GO IF), you can use the door in emergency condition until the end of the next night. 1

At the end of the next night, fill the cylinder until the pointer of the pressure gauge (1) is in the green area again (Ref. AMM TASK 52-10-00-614-001) .

(3) If the pointer of the pressure gauge (1) is in the red area (NO GO):

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-00-00-040-003-A - Check of the Pressure of the Emergency Cylinder/Accumulator of the Passenger/Crew Doors after the Flight Attendant Panel (FAP) Stops

(a) You cannot open the door in emergency condition (refer to the MMEL for dispatch conditions). (4) Make an entry in the logbook. ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 5.

Close-up Subtask 52-00-00-410-053-A A.

Close Access (1) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (2) Obey the special precautions after work on the door (Ref. AMM TASK 52-10-00-860-002) . (3) Close applicable passenger/crew door 831, 841, 832 or 842 (Ref. AMM TASK 52-10-00-410-001) . (4) Remove the access platform(s). (5) Make sure that the work area is clean and clear of tools and other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-00-00-040-003-B - Check of the Pressure of the Emergency Cylinder/ Accumulator of the Passenger/Crew Doors and Emergency Exits

** ON A/C 401-450 TASK 52-00-00-040-003-B Check of the Pressure of the Emergency Cylinder/Accumulator of the Passenger/Crew Doors and Emergency Exits Task Summary MMEL or CDL Ref MMEL 52-10-06A

Access YES

Test YES

Specific Tools NO

Mhr 00.3

1.

Reason for the Job MMEL 52-10-06A CHECK DOOR PRESSURE Message on the Flight Attendant Panel (FAP) (If Installed)

2

Job Set-up Information A.

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

E/T 00.3

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS 830 840 831, 832, 835, 841, 842, 845

ZONE DESCRIPTION L PASSENGER/CREW DOORS & EMERGENCY EXITS R PASSENGER/CREW DOORS & EMERGENCY EXITS

C. Referenced Information REFERENCE (Ref. 52-10-00-010-001-A). (Ref. 52-10-00-410-001-A). (Ref. 52-10-00-614-001-A).

DESIGNATION Opening of the Passenger/Crew Door Closing of the Passenger/Crew Door Discharging/Charging of the Door Damper and Emergency Operation Cylinder of the Passenger/Crew Doors (Ref. 52-10-00-860-001-A). Special Precautions before Work on the Passenger/Crew Door (Ref. 52-10-00-860-002-A). Special Precautions after Work on the Passenger/Crew Door (Ref. 52-22-00-010-001-A). Opening of the Emergency Exit Doors from the Passenger Compartment (Ref. 52-22-00-410-001-A). Closing of the Emergency Exit Doors from the Passenger Compartment (Ref. 52-22-00-860-003-A). Special Precaution before Maintenance on the Door Damper and Emergency Operation Cylinder (Ref. 52-22-00-860-004-A). Special Precaution after Maintenance on the Door Damper and Emergency Operation Cylinder Emergency Cylinder/Accumulator SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-00-00-040-003-B - Check of the Pressure of the Emergency Cylinder/ Accumulator of the Passenger/Crew Doors and Emergency Exits

Z842 Z845

A Z832

A

A

A

B

Z835

Z841

A Z831

C

A

01

1

"GO AREA" "Y"

"G"

D

1783

RE

RED

B

"G" = GREEN "Y" = YELLOW

3000

0

C NOTE: 01

LH SHOWN, RH SYMMETRICAL N_MM_520000_4_DAM1_01_00

Figure 52-00-00-991-00200-00-E / SHEET 1/1 - Emergency Cylinder/Accumulator ** ON A/C 401-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-00-00-040-003-B - Check of the Pressure of the Emergency Cylinder/ Accumulator of the Passenger/Crew Doors and Emergency Exits

3.

Job Set-up Subtask 52-00-00-010-055-B A.

Get Access (1) For the passenger/crew door: (a) Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position: 1

For the left passenger/crew door, at zone 831 or 832.

2

For the right passenger/crew door, at zone 841 or 842.

(b) Open passenger/crew door 831, 841, 832 or 842 (Ref. AMM TASK 52-10-00-010-001) . (c) Obey the special precautions before you start work on the door (Ref. AMM TASK 52-10-00-860001) . (2) For the emergency exit: (a) Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position at zone 835 or 845. (b) Open emergency exit 835 or 845 (Ref. AMM TASK 52-22-00-010-001) . (c) Obey the special precautions before you start work on the emergency exit door (Ref. AMM TASK 52-22-00-860-003) . 4.

Procedure (Ref. Fig. Emergency Cylinder/Accumulator SHEET 1) Subtask 52-00-00-210-057-A A.

Check of the Pressure Indication of the Damper and Emergency Operation Cylinder when the Flight Attendant Panel (FAP) does not operate (1) To get the correct pressure, let the cylinder become stable at ambient temperature before you do the inspection. (2) Do a check of the pointer of the pressure gauge (1): (a) If the pointer of the pressure gauge (1) is in the green area (GO), you can use the door in emergency condition without limit. (b) If the pointer of the pressure gauge (1) is in the yellow area (GO IF), you can use the door in emergency condition until the next night stop. 1

At the next night stop, fill the cylinder until the pointer of the pressure gauge (1) is in the green area again (Ref. AMM TASK 52-10-00-614-001) .

(3) If the pointer of the pressure gauge (1) is in the red area (NO GO): (a) You cannot open the door in emergency condition. Refer to the MMEL for dispatch conditions. (b) Make an entry in the logbook. 5.

Close-up Subtask 52-00-00-410-055-B A.

Close Access (1) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (2) For the passenger/crew door: (a) Obey the special precautions after work on the door (Ref. AMM TASK 52-10-00-860-002) . (b) Close applicable passenger/crew door 831, 841, 832 or 842 (Ref. AMM TASK 52-10-00-410001) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-00-00-040-003-B - Check of the Pressure of the Emergency Cylinder/ Accumulator of the Passenger/Crew Doors and Emergency Exits

(3) For the emergency exit: (a) Obey the special precautions after work on the emergency exit door (Ref. AMM TASK 52-22-00860-004) . (b) Close applicable emergency exit 835 or 845 (Ref. AMM TASK 52-22-00-410-001) . (4) Remove the access platform(s). (5) Make sure that the work area is clean and clear of tools and other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-803-A - Deactivation of the Cabin Doors

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 TASK 52-10-00-040-803-A Deactivation of the Cabin Doors 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.

Task Summary MMEL or CDL Ref MMEL 52-10-01A 1.

Reason for the Job MMEL 52-10-01A Cabin Door

2

Job Set-up Information A.

Access YES

Specific Tools NO

Mhr

E/T

Nb Men

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

Test YES

QTY 1 AR AR

DESIGNATION ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE PLACARD SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS 831, 832, 841, 842

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 52-10-00-010-001-A). (Ref. 52-10-00-410-001-A). (Ref. 52-10-00-860-001-A). (Ref. 52-10-00-860-002-A). 3.

DESIGNATION Opening of the Passenger/Crew Door Closing of the Passenger/Crew Door Special Precautions before Work on the Passenger/Crew Door Special Precautions after Work on the Passenger/Crew Door

Job Set-up Subtask 52-10-00-010-118-A A.

Get Access (1) Put on and attach a safety harness before you start work in the work area (2) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at zone 831 (841) or 832 (842). (3) Open applicable passenger/crew door 831 ( 841) or 832 ( 842) (Ref. AMM TASK 52-10-00-010001) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-803-A - Deactivation of the Cabin Doors

(4) Obey the special precautions before you start work on the passenger/crew door (Ref. AMM TASK 52-10-00-860-001) . Subtask 52-10-00-865-130-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU 121VU

4.

DESIGNATION EIS/SLIDES/ARM AND WARN/FLT EIS/SLIDES/ARM AND WARN/GND EIS/SDAC1 AND 2/DOOR/DET/PAX

FIN 15WN 13WN 48WV

LOCATION P11 P10 P05

Procedure Subtask 52-10-00-040-051-A A.

Deactivation of the Cabin Doors (1) Close the passenger/crew door from the inner side (Ref. AMM TASK 52-10-00-410-001) . (2) Put a temporary "DO NOT USE" PLACARD at the deactivated door to tell persons not to use it. (3) Put a temporary "DO NOT USE" PLACARD on each of the affected seats to tell persons not to use them. (4) Put a cover on each EXIT indication related to the deactivated exit.

5.

Close-up Subtask 52-10-00-865-131-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU 121VU

DESIGNATION EIS/SLIDES/ARM AND WARN/FLT EIS/SLIDES/ARM AND WARN/GND EIS/SDAC1 AND 2/DOOR/DET/PAX

FIN 15WN 13WN 48WV

LOCATION P11 P10 P05

Subtask 52-10-00-410-126-A B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Obey the special precautions after the work on the passenger/crew door (Ref. AMM TASK 52-10-00860-002) . (3) Close applicable passenger/crew door 831 ( 832) or 841 ( 842) (Ref. AMM TASK 52-10-00-410001) . (4) Remove the access platform(s). (5) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-803-D - Deactivation of the Cabin Doors

** ON A/C 401-450 TASK 52-10-00-040-803-D Deactivation of the Cabin Doors 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.

Task Summary MMEL or CDL Ref MMEL 52-10-01A 1.

Reason for the Job MMEL 52-10-01A Cabin Door

2

Job Set-up Information A.

Access YES

Specific Tools NO

Mhr

E/T

Nb Men

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

Test YES

QTY 1 AR AR

DESIGNATION ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE PLACARD SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTION 831, 832, 833, 834, 841, 842, 843, 844

C. Referenced Information REFERENCE (Ref. 52-10-00-010-001-A). (Ref. 52-10-00-410-001-A). (Ref. 52-10-00-860-001-A). (Ref. 52-10-00-860-002-A). 3.

DESIGNATION Opening of the Passenger/Crew Door Closing of the Passenger/Crew Door Special Precautions before Work on the Passenger/Crew Door Special Precautions after Work on the Passenger/Crew Door

Job Set-up Subtask 52-10-00-010-136-B A.

Get Access (1) Put on and attach a safety harness before you start work in the work area (2) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at zone 831 (841) or 832 (842) or 833 (843) or 834 (844). (3) Open applicable cabin door 831 ( 841) or 832 ( 842) or 833 ( 843) or 834 ( 844) (Ref. AMM TASK 5210-00-010-001) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-10-00-040-803-D - Deactivation of the Cabin Doors

(4) Obey the special precautions before you start work on the cabin door (Ref. AMM TASK 52-10-00860-001) . Subtask 52-10-00-865-126-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 121VU 121VU

4.

DESIGNATION EIS/SLIDES/ARM AND WARN/FLT EIS/SLIDES/ARM AND WARN/GND EIS/SDAC1 AND 2/DOOR/DET/PAX

FIN 15WN 13WN 48WV

LOCATION P11 P10 P05

Procedure Subtask 52-10-00-040-056-A A.

Deactivation of the Cabin Doors (1) Close the passenger/crew door from the inner side (Ref. AMM TASK 52-10-00-410-001) . (2) Put a temporary "DO NOT USE" PLACARD at the deactivated door to tell persons not to use it. (3) Put a temporary "DO NOT USE" PLACARD on each of the affected seats to tell persons not to use them. (4) Put a cover on each EXIT indication related to the deactivated exit.

5.

Close-up Subtask 52-10-00-865-127-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU 121VU 121VU

DESIGNATION EIS/SLIDES/ARM AND WARN/FLT EIS/SLIDES/ARM AND WARN/GND EIS/SDAC1 AND 2/DOOR/DET/PAX

FIN 15WN 13WN 48WV

LOCATION P11 P10 P05

Subtask 52-10-00-410-147-B B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Obey the special precautions after work on the cabin door (Ref. AMM TASK 52-10-00-860-002) . (3) Close applicable cabin door 831 ( 832) or 841 ( 842) or 833 ( 843) or 834 ( 844) (Ref. AMM TASK 52-10-00-410-001) . (4) Remove the access platform(s). (5) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-21-00-040-802-A - Deactivation of the Family Aircraft with One Pair of Cabin Overwing Exits and Aft Cabin Doors not Deactivated

** ON A/C 236-236, 241-241 TASK 52-21-00-040-802-A Deactivation of the Family Aircraft with One Pair of Cabin Overwing Exits and Aft Cabin Doors not Deactivated Task Summary MMEL or CDL Ref MMEL 52-10-02A 1.

Reason for the Job MMEL 52-10-02A Cabin Overwing Exit

2

Job Set-up Information A.

Access NO

Mhr 00.1

E/T 00.1

Nb Men 1

QTY DESIGNATION AR COVER - BLANKING AR PLACARD

Work Zones and Access Panels ZONE/ACCESS 833 834 843 844

3.

Specific Tools NO

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Test YES

ZONE DESCRIPTION EMERGENCY EXITS EMERGENCY EXITS EMERGENCY EXITS EMERGENCY EXITS

Procedure Subtask 52-21-00-040-050-B A.

Deactivation of the Cabin Overwing Exit (1) Put a temporary "DO NOT USE" PLACARD at each deactivated door to tell persons not to use them. (2) Put a temporary "DO NOT USE" PLACARD on each of the remaining seats to tell persons not to use them. (3) For the deactivated exit, put a COVER - BLANKING on the applicable arrow of the related EXIT marking sign and on the related wall-mounted EXIT marking sign. (a) Put a COVER - BLANKING on the applicable arrow of the EXIT location sign in the ceiling.

4.

Close-up Subtask 52-21-00-410-065-B A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-21-00-040-802-B - Deactivation of the Family Aircraft with One Pair of Cabin Overwing Exits

** ON A/C 409-415 TASK 52-21-00-040-802-B Deactivation of the Family Aircraft with One Pair of Cabin Overwing Exits Task Summary MMEL or CDL Ref MMEL 52-10-02A 1.

Reason for the Job MMEL 52-10-02A Cabin Overwing Exit

2

Job Set-up Information A.

Access NO

Mhr 00.3

E/T 00.3

Nb Men 1

QTY DESIGNATION AR COVER - BLANKING AR PLACARD

Work Zones and Access Panels ZONE/ACCESS 833 834 843 844

3.

Specific Tools NO

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Test YES

ZONE DESCRIPTION EMERGENCY EXITS EMERGENCY EXITS EMERGENCY EXITS EMERGENCY EXITS

Procedure Subtask 52-21-00-040-053-A A.

Deactivation of the Cabin Overwing Exit (1) Put a temporary "DO NOT USE" PLACARD at each deactivated door to tell persons not to use them. (2) Put a temporary "DO NOT USE" PLACARD on each of the remaining seats to tell persons not to use them. (3) For the deactivated exit, put a COVER - BLANKING on the applicable arrow of the related EXIT sign and on the related wall-mounted EXIT sign. (a) Put a COVER - BLANKING on the applicable arrow of the EXIT sign on the ceiling.

4.

Close-up Subtask 52-21-00-410-072-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-21-00-040-803-A - Deactivation of the Family Aircraft with Two Pairs of Cabin Overwing Exits and Aft Cabin Doors not Deactivated

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-235, 237-240, 242-250, 301-400, 500-600 TASK 52-21-00-040-803-A Deactivation of the Family Aircraft with Two Pairs of Cabin Overwing Exits and Aft Cabin Doors not Deactivated Task Summary MMEL or CDL Ref MMEL 52-10-02A 1.

Reason for the Job MMEL 52-10-02A Cabin Overwing Exit

2

Job Set-up Information A.

Access NO

Mhr 00.3

E/T 00.3

Nb Men 1

QTY DESIGNATION AR COVER - BLANKING AR PLACARD

Work Zones and Access Panels ZONE/ACCESS 833 834 843 844

3.

Specific Tools NO

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Test YES

ZONE DESCRIPTION EMERGENCY EXITS EMERGENCY EXITS EMERGENCY EXITS EMERGENCY EXITS

Procedure Subtask 52-21-00-040-051-A A.

Deactivation of the Cabin Overwing Exit (1) Put a temporary "DO NOT USE" PLACARD at each deactivated door to tell persons not to use them. (2) Put a temporary "DO NOT USE" PLACARD on each of the remaining seats to tell persons not to use them. (3) For the deactivated exit(s), put a COVER - BLANKING on the applicable arrow of the related EXIT marking sign and on the related wall-mounted EXIT marking sign. (4) If both cabin overwing exits are deactivated on one side: (a) Fully cover the related EXIT marking sign with a COVER - BLANKING. (b) Put a COVER - BLANKING on the related wall-mounted EXIT marking signs. (c) Put a COVER - BLANKING on the applicable arrow of the EXIT location sign in the ceiling.

4.

Close-up Subtask 52-21-00-410-068-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-21-00-040-803-A - Deactivation of the Family Aircraft with Two Pairs of Cabin Overwing Exits and Aft Cabin Doors not Deactivated

(2) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-21-00-040-803-B - Deactivation of the Family Aircraft with Two Pairs of Cabin Overwing Exits

** ON A/C 401-408, 416-450 TASK 52-21-00-040-803-B Deactivation of the Family Aircraft with Two Pairs of Cabin Overwing Exits Task Summary MMEL or CDL Ref MMEL 52-10-02A 1.

Reason for the Job MMEL 52-10-02A Cabin Overwing Exit

2

Job Set-up Information A.

Access NO

Mhr 00.3

E/T 00.3

Nb Men 1

QTY DESIGNATION AR COVER - BLANKING AR PLACARD

Work Zones and Access Panels ZONE/ACCESS 833 834 843 844

3.

Specific Tools NO

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

Test YES

ZONE DESCRIPTION EMERGENCY EXITS EMERGENCY EXITS EMERGENCY EXITS EMERGENCY EXITS

Procedure Subtask 52-21-00-040-054-A A.

Deactivation of the Cabin Overwing Exit (1) Put a temporary "DO NOT USE" PLACARD at each deactivated door to tell persons not to use them. (2) Put a temporary "DO NOT USE" PLACARD on each of the remaining seats to tell persons not to use them. (3) For the deactivated exit(s), put a COVER - BLANKING on the applicable arrow of the related EXIT sign and on the related wall-mounted EXIT sign. (4) If the two cabin overwing exits are deactivated on one side: (a) Put a COVER - BLANKING on the related EXIT sign. (b) Put a COVER - BLANKING on each related wall-mounted EXIT sign. (c) Put a COVER - BLANKING on the applicable arrow of the EXIT sign on the ceiling.

4.

Close-up Subtask 52-21-00-410-074-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-21-00-040-803-B - Deactivation of the Family Aircraft with Two Pairs of Cabin Overwing Exits

(2) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-22-71-040-801-A - Deactivation of the Flight Lock Actuator (FLA)

** ON A/C 401-450 TASK 52-22-71-040-801-A Deactivation of the Flight Lock Actuator (FLA) Task Summary MMEL or CDL Ref MMEL 52-10-09C 1.

Reason for the Job MMEL 52-10-09C Flight Lock Actuator

2

Job Set-up Information A.

Access YES

Specific Tools NO

Mhr 01.0

E/T 01.0

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Test NO

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS 833, 843

ZONE DESCRIPTION

** ON A/C 401-408, 416-450 834, 844 ** ON A/C 401-450 C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 25-23-47-000-803-A). (Ref. 25-23-47-400-803-A). (Ref. 52-22-00-410-802-A). (Ref. 52-22-71-000-801-A). 3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Removal of the Door Lining of the Overwing Emergency Exit Installation of the Door Lining of the Overwing Emergency Exit Closing of the Overwing Emergency-Exit Door from the Passenger Compartment Removal of the Flight Lock Actuator (FLA)

Job Set-up

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-22-71-040-801-A - Deactivation of the Flight Lock Actuator (FLA)

** ON A/C 401-408, 416-450 Subtask 52-22-71-860-069-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Make sure that applicable overwing emergency exit 833 ( 843) or 834 ( 844) is closed, latched and locked (Ref. AMM TASK 52-22-00-410-802) .

** ON A/C 409-415 Subtask 52-22-71-860-069-C A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) . (2) Make sure that applicable overwing emergency exit 833 ( 843) is closed, latched and locked (Ref. AMM TASK 52-22-00-410-802) .

** ON A/C 401-450 Subtask 52-22-71-865-071-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU 122VU

DESIGNATION EIS/SDAC1 AND 2/DOOR/DET/PAX FLIGHT LOCK OWD

FIN 48WV 40WN

LOCATION P05 U16

** ON A/C 401-408, 416-450 Subtask 52-22-71-010-058-A C.

Get Access (1) Remove the lining of applicable overwing emergency exit 833 ( 843) or 834 ( 844) (Ref. AMM TASK 25-23-47-000-803) .

** ON A/C 409-415 Subtask 52-22-71-010-058-C C.

Get Access (1) Remove the lining of applicable overwing emergency exit 833 ( 843) (Ref. AMM TASK 25-23-47-000803) .

** ON A/C 401-450 4.

Procedure Subtask 52-22-71-040-050-A A.

Deactivation of the FLA (1) Remove the FLA (Ref. AMM TASK 52-22-71-000-801) .

5.

Close-up Subtask 52-22-71-865-072-A A.

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

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-22-71-040-801-A - Deactivation of the Flight Lock Actuator (FLA)

PANEL 121VU 122VU

DESIGNATION EIS/SDAC1 AND 2/DOOR/DET/PAX FLIGHT LOCK OWD

FIN 48WV 40WN

LOCATION P05 U16

** ON A/C 401-408, 416-450 Subtask 52-22-71-410-058-A B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the lining of applicable overwing emergency exit 833 ( 843) or 834 ( 844) (Ref. AMM TASK 2523-47-400-803) .

** ON A/C 409-415 Subtask 52-22-71-410-058-C B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the lining of applicable overwing emergency exit 833 ( 843) (Ref. AMM TASK 25-23-47-400803) .

** ON A/C 401-450 Subtask 52-22-71-860-070-A C.

Aircraft Maintenance Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (2) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-30-00-040-001-A - Deactivation of Cargo Doors

** ON A/C ALL TASK 52-30-00-040-001-A Deactivation of Cargo Doors Task Summary MMEL or CDL Ref MMEL 52-30-01B

Access NO

Test NO

1.

Reason for the Job MMEL 52-30-01B Cargo Door (FWD, AFT and BULK (If Installed))

2

Job Set-up Information A.

Mhr 00.5

E/T 00.5

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

3.

Specific Tools NO

QTY DESIGNATION 1 ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE

Job Set-up Subtask 52-30-00-010-061-A A.

Get Access (1) Put an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the access panels of the FWD and/or Aft cargo-compartment doors.

4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-311, 315-315, 320-320, 324-325, 350-350 Subtask 52-30-00-210-050-C A.

Visual Check of the inoperative FWD and/or Aft Cargo-Compartment Doors (1) Push the handle flap in to release the door handle. (2) Pull the door handle up from the door structure in the UNLOCKED direction until the door handle is 65 degrees moved. NOTE: Do not unlock the cargo door at this time. (3) Make sure that you can see the red marks of each safety cam in the indication windows of the access panels. (4) Push the door handle down into the LOCKED position again. (5) Do a visual check of the external cargo door to make sure that: · The cargo door is aligned with the fuselage · The vent door is fully closed · The green marks of each safety cam are in view in the indication windows of the access panels at the lower cargo-door edge · The door handle is aligned with the cargo door contour.

** ON A/C 312-314, 316-319, 321-323, 326-349, 351-450, 500-600 Subtask 52-30-00-210-050-D Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-30-00-040-001-A - Deactivation of Cargo Doors

A.

Visual Check of the inoperative FWD and/or Aft Cargo-Compartment Doors (1) Release the door handle from the catch of the door structure as follows: (a) Push and hold the push-button. (b) Push the handle flap. (2) Pull the door handle away and up from the door structure in the UNLOCKED direction until the door handle is moved 65 degrees. NOTE: You must not unlock the cargo door at this time. (3) Make sure that you can see the red marks of each safety cam in the indication windows of the access panels. (4) Push the door handle down into the LOCKED position again. (5) Do a visual check of the external cargo door and make sure that: · The cargo door is aligned with the fuselage · The vent door is fully closed · The green marks of each safety cam are in view in the indication windows of the access panels at the lower cargo-door edge · The door handle is aligned with the cargo door contour.

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-222, 226-250, 301-450, 500-600 Subtask 52-30-00-210-051-A B.

Visual Check of the inoperative Bulk Cargo-Compartment Door (1) Push the button of the external door handle to release it from the recess. (2) Move the external door handle to the OPEN position and push the bulk cargo door in. (3) Pull the door down into the door opening and move the external door handle to the LOCKED position. (4) Push the external door handle into its recess. (5) Do a visual check of the surface of the external bulk cargo-door to make sure that: · The door handle aligns with the bulk cargo-door contour · The bulk cargo door is aligned with the fuselage.

** ON A/C ALL 5.

Close-up Subtask 52-30-00-860-057-A A.

Make an entry in the aircraft log that one or the two cargo door(s) is (are) inoperative but correctly closed and locked.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-31-00-040-003-A - Deactivation of the Locking Hooks and Spools

** ON A/C ALL TASK 52-31-00-040-003-A Deactivation of the Locking Hooks and Spools CAUTION:

IMMEDIATELY AFTER YOU OPEN THE CARGO COMPARTMENT DOOR, RECORD ON THE WORK CARD ON THE DOOR, THE DATE AND TIME WHEN YOU OPENED IT. IF THE CARGO COMPARTMENT DOOR STAYS OPEN FOR 12 HOURS OR MORE, YOU MUST BLEED THE HYDRAULIC SYSTEM RELATED TO IT. IF YOU DO NOT OBEY THESE PRECAUTIONS, THE DOOR CAN CLOSE SUDDENLY WHEN YOU SET THE DOOR TO "CLOSE". THIS CAN CAUSE DAMAGE TO THE DOOR AND TO THE AIRCRAFT STRUCTURE.

Task Summary MMEL or CDL Ref MMEL 52-30-04A

Access YES

Test NO

Specific Tools NO

1.

Reason for the Job MMEL 52-30-04A Cargo Door Locking Hooks and Spools (Rollers) (FAA only)

2

Job Set-up Information A.

E/T 01.0

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Mhr 01.0

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS 825AR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 52-30-00-860-001-A). (Ref. 52-30-00-860-002-A).

DESIGNATION Open the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump Close the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump

Locking Hooks and Spools

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-31-00-040-003-A - Deactivation of the Locking Hooks and Spools

A A

C

Z825

FR24A

B

FR28

B EXAMPLE

12 10 11

13

9

8

11 10 12

7 6 4 3 2 1

5 N_MM_523100_4_AAMA_01_01

Figure 52-31-00-991-00700-00-A / SHEET 1/2 - Locking Hooks and Spools ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-31-00-040-003-A - Deactivation of the Locking Hooks and Spools

C LOCKING UNIT EXAMPLE LATCHING SHAFT

LOCKING SHAFT

D LOCKING HOOK

D

15 16 18

17

19

21 22

20

23

25

24

26 N_MM_523100_4_AAMA_02_01

Figure 52-31-00-991-00700-00-A / SHEET 2/2 - Locking Hooks and Spools ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-31-00-040-003-A - Deactivation of the Locking Hooks and Spools

3.

Job Set-up Subtask 52-31-00-010-053-A A.

Get Access (1) Open the FWD cargo compartment door (referred to as cargo door) and safety it with the actuator safety locks (Ref. AMM TASK 52-30-00-860-001) . (2) Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position below the opened cargo door. (3) Remove the access panel 825AR from the cargo door.

Subtask 52-31-00-860-061-A B.

Aircraft Maintenance Configuration (1) Deactivate the interlock mechanism of the opened cargo door as follows: NOTE: This procedure is only necessary, if one of the locking hooks is damaged or inoperative. (a) Press the roller lever of the interlock mechanism outboard to release the blockage of the locking shaft. (b) Turn the locking handle up to the locked position and push it into the recess of the handle flap.

4.

Procedure Subtask 52-31-00-040-051-A A.

Deactivation of the Locking Hooks and Spools (Ref. Fig. Locking Hooks and Spools) (1) Deactivate the damaged or inoperative spool as follows: (a) Remove and discard the cotter pin (1) from the nut (2). (b) Remove the nut (2) and the washer (3) from the eccentric bolt (9). (c) Remove the nuts (10) and the washers (11) from the special bolts (12) of the door frame fitting (13). (d) Remove the serrated plate (4) from the adjusting bush (5). (e) Hold the spool (7) and remove the eccentric bolt (9) together with the serrated plate (8) from the door frame fitting (13). (f)

Disengage the serrated plate (8) from the eccentric bolt (9).

(g) Remove the eccentric bush (6) from the spool (7). (h) Remove the adjusting bush (5) from the door frame fitting (13). (2) Deactivate the damaged or inoperative locking hook as follows: (a) Remove and discard the cotter pin (15) from the nut (16). (b) Remove the nut (16), the washers (17) and (19) and the bolt (20) from the lower fork end of the linkage (18). (c) Move the linkage (18) to disconnect it from the locking hook (24). (d) Remove and discard the cotter pin (21) from the nut (22). (e) Remove the nut (22) and the washer (23) from the locking hook bolt (26). (f)

Hold the locking hook (24) and remove the washer (25) and the locking hook bolt (26) from the cargo door frame.

(g) Remove the locking hook (24) from the cargo door frame.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-31-00-040-003-A - Deactivation of the Locking Hooks and Spools

Subtask 52-31-00-210-050-A B.

Visual Inspection (1) Examine the remaining locking hooks as follows: (a) Make sure that the other locking hooks are not damaged. (b) Make sure that you cannot turn the other locking hook bolts manually. (2) Examine the remaining spools as follows: (a) Make sure that the other spools are not damaged. (b) Make sure that the other eccentric bolts and the eccentric bushes are in the correct condition. (c) Make sure that the other lock fittings are not damaged.

5.

Close-up Subtask 52-31-00-860-059-A A.

Put the aircraft back to the serviceable condition. (1) Close and lock the cargo door (Ref. AMM TASK 52-30-00-860-002) . (2) Examine the vent door to make sure that it is closed and aligns with the cargo door skin. (3) Make sure that the indications of the ECAM system in the cockpit shows that the cargo door is correct closed and locked. (4) Put a placard in the cockpit to tell the flight crew that one of the spools and/or locking hooks is deactivated. (5) Make an entry in the aircraft technical log that one of the spools and/or one of the locking hooks is deactivated.

Subtask 52-31-00-410-053-A B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the access panel 825AR on the cargo door. (3) Make sure that you can see the green mark of each safety cam through the indication windows of the door access panel 825AR. (4) Remove the access platform(s).

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-32-00-040-003-A - Deactivation of the Locking Hooks and Spools

** ON A/C ALL TASK 52-32-00-040-003-A Deactivation of the Locking Hooks and Spools Task Summary MMEL or CDL Ref MMEL 52-30-04A

Access YES

Test NO

Specific Tools NO

1.

Reason for the Job MMEL 52-30-04A Cargo Door Locking Hooks and Spools (Rollers) (FAA only)

2

Job Set-up Information A.

E/T 01.0

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Mhr 01.0

QTY DESIGNATION 1 ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS 826AR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 52-30-00-860-001-A). (Ref. 52-30-00-860-002-A).

DESIGNATION Open the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump Close the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump

Locking Hooks and Spools

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-32-00-040-003-A - Deactivation of the Locking Hooks and Spools

A

A C Z826

FR52A

B

FR56

B 12

EXAMPLE

10 11

13

9

8

11 10 12

7 6 4 3 2 1

5 N_MM_523200_4_AAMA_01_00

Figure 52-32-00-991-00700-00-A / SHEET 1/2 - Locking Hooks and Spools ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-32-00-040-003-A - Deactivation of the Locking Hooks and Spools

C LOCKING UNIT EXAMPLE

LOCKING SHAFT

SAFTEY SHAFT

D LOCKING HOOK

D

15 16 18

17

19

21 22

20

23

25

24

26 N_MM_523200_4_AAMA_02_00

Figure 52-32-00-991-00700-00-A / SHEET 2/2 - Locking Hooks and Spools ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-32-00-040-003-A - Deactivation of the Locking Hooks and Spools

3.

Job Set-up Subtask 52-32-00-010-055-A A.

Get Access CAUTION:

IMMEDIATELY AFTER YOU OPEN THE CARGO COMPARTMENT DOOR, RECORD ON THE WORK CARD ON THE DOOR, THE DATE AND TIME WHEN YOU OPENED IT. IF THE CARGO COMPARTMENT DOOR STAYS OPEN FOR 12 HOURS OR MORE, YOU MUST BLEED THE HYDRAULIC SYSTEM RELATED TO IT. IF YOU DO NOT OBEY THESE PRECAUTIONS, THE DOOR CAN CLOSE SUDDENLY WHEN YOU SET THE DOOR TO "CLOSE". THIS CAN CAUSE DAMAGE TO THE DOOR AND TO THE AIRCRAFT STRUCTURE.

(1) Open the AFT cargo compartment door (referred to as cargo door) and safety it with the actuator safety locks (Ref. AMM TASK 52-30-00-860-001) . (2) Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position below the opened cargo door. (3) Remove the access panel 826AR from the cargo door. Subtask 52-32-00-860-059-A B.

Aircraft Maintenance Configuration (1) Deactivate the interlock mechanism of the opened cargo door as follows: NOTE: This procedure is only necessary, if one of the locking hooks is damaged or inoperative. (a) Press the roller lever of the interlock mechanism outboard to release the blockage of the locking shaft. (b) Turn the locking handle up to the locked position and push it into the recess of the handle flap.

4.

Procedure Subtask 52-32-00-040-051-A A.

Deactivation of the Locking Hooks and Spools (Ref. Fig. Locking Hooks and Spools) (1) Deactivate the damaged or inoperative spool as follows: (a) Remove and discard the cotter pin (1) from the nut (2). (b) Remove the nut (2) and the washer (3) from the eccentric bolt (9). (c) Remove the nuts (10) and the washers (11) from the special bolts (12) of the door frame fitting (13). (d) Remove the serrated plate (4) from the adjusting bush (5). (e) Hold the spool (7) and remove the eccentric bolt (9) together with the serrated plate (8) from the door frame fitting (13). (f)

Disengage the serrated plate (8) from the eccentric bolt (9).

(g) Remove the eccentric bush (6) from the spool (7). (h) Remove the adjusting bush (5) from the door frame fitting (13). (2) Deactivate the damaged or inoperative locking hook as follows: (a) Remove and discard the cotter pin (15) from the nut (16). (b) Remove the nut (16), the washers (17) and (19) and the bolt (20) from the lower fork end of the linkage (18). Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-32-00-040-003-A - Deactivation of the Locking Hooks and Spools

(c) Move the linkage (18) to disconnect it from the locking hook (24). (d) Remove and discard the cotter pin (21) from the nut (22). (e) Remove the nut (22) and the washer (23) from the locking hook bolt (26). (f)

Hold the locking hook (24) and remove the washer (25) and the locking hook bolt (26) from the cargo door frame.

(g) Remove the locking hook (24) from the cargo door frame. Subtask 52-32-00-210-050-A B.

Visual Inspection (1) Examine the remaining locking hooks as follows: (a) Make sure that the other locking hooks are not damaged. (b) Make sure that you cannot turn the other locking hook bolts manually. (2) Examine the remaining spools as follows: (a) Make sure that the other spools are not damaged. (b) Make sure that the other eccentric bolts and the eccentric bushes are in the correct condition. (c) Make sure that the other lock fittings are not damaged.

5.

Close-up Subtask 52-32-00-860-060-A A.

Put the aircraft back to the serviceable condition. (1) Close and lock the cargo door (Ref. AMM TASK 52-30-00-860-002) . (2) Examine the vent door to make sure that it is closed and aligns with the cargo door skin. (3) Make sure that the indications of the ECAM system in the cockpit shows that the cargo door is correctly closed and locked. (4) Put a placard in the cockpit to tell the flight crew that one of the spools and/or locking hooks is deactivated. (5) Make an entry in the aircraft technical log that one of the spools and/or one of the locking hooks is deactivated.

Subtask 52-32-00-410-053-A B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Install the access panel 826AR on the cargo door. (3) Make sure that you can see the green mark of each safety cam through the indication windows of the door access panel 826AR. (4) Remove the access platform(s).

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-33-00-040-001-A - Operation of Bulk Cargo Compartment Door with an inoperative Balance Mechanism

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-222, 226-250, 301-450, 500-600 TASK 52-33-00-040-001-A Operation of Bulk Cargo Compartment Door with an inoperative Balance Mechanism CAUTION:

IMMEDIATELY AFTER YOU OPEN THE CARGO COMPARTMENT DOOR, RECORD ON THE WORK CARD ON THE DOOR, THE DATE AND TIME WHEN YOU OPENED IT. IF THE CARGO COMPARTMENT DOOR STAYS OPEN FOR 12 HOURS OR MORE, YOU MUST BLEED THE HYDRAULIC SYSTEM RELATED TO IT. IF YOU DO NOT OBEY THESE PRECAUTIONS, THE DOOR CAN CLOSE SUDDENLY WHEN YOU SET THE DOOR TO "CLOSE". THIS CAN CAUSE DAMAGE TO THE DOOR AND TO THE AIRCRAFT STRUCTURE.

Task Summary MMEL or CDL Ref MMEL 52-33-01A

Access NO

1.

Reason for the Job MMEL 52-33-01A Cargo Door Balance Mechanism

2

Job Set-up Information A.

Mhr 00.5

E/T 00.5

Nb Men 1

QTY 1 1 1 1

DESIGNATION ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE ROPE DIA 50 MM (2 IN) STRAP - LIFTING WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 827

3.

Specific Tools NO

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

Test NO

ZONE DESCRIPTION BULK CARGO COMPARTMENT DOOR

Job Set-up Subtask 52-33-00-010-050-A A.

Get Access (1) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the bulk cargo compartment door (referred to as the bulk door. (2) Attach a WARNING NOTICE(S) to the bulk door to tell persons that the door balance mechanism is inoperative.

4.

Procedure Subtask 52-33-00-869-050-A A.

Operation of Bulk Cargo Compartment Door with an Inoperative Balance Mechanism (1) Open the bulk cargo compartment door (referred to as bulk cargo door) as follows:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-33-00-040-001-A - Operation of Bulk Cargo Compartment Door with an inoperative Balance Mechanism

(a) If you must open the bulk cargo door from the outer side, push the button of the external door handle. NOTE: This causes the external door handle to release from its recess. (b) Move the internal or external door handle to the OPEN position. (c) Push the bulk cargo door inboard and put the door handle in the LOCKED position. (d) If you used the external door handle, push it into its recess again. (e) Move the bulk cargo door manually inboard until the hook engages with the hook arrester of the fuselage crossbeam. (f)

Safety the bulk cargo door with a ROPE DIA 50 MM (2 IN) or a STRAP - LIFTING to the hook arrester of the fuselage. NOTE: This makes sure that the bulk cargo door does not fall when you release the hook during the closing procedure.

(2) Close the bulk cargo door as follows: (a) Push the button of the external door handle to release it from its recess. (b) Move the external door handle to the OPEN position and hold the bulk cargo door so that it does not fall. (c) If you close the bulk cargo door from the inner side, continue as follows: 1

Move the bulk cargo door slowly down until the hook is free from the hook arrester.

2

Move the external door handle to the LOCKED position and push it into its recess.

3

Make sure that the internal door handle is in the UNLOCKED position.

(d) Move the bulk cargo door down into the door opening and put the applicable door handle in the LOCKED position. (e) If you close the bulk cargo door from the outer side, push the external door handle into its recess. 5.

Close-up Subtask 52-33-00-860-050-A A.

Close Access (1) Remove the access platform(s). (2) Make an entry in the aircraft logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-36-00-040-001-A - Deactivation of the Cargo Door Actuator(s)

** ON A/C ALL TASK 52-36-00-040-001-A Deactivation of the Cargo Door Actuator(s) CAUTION:

IMMEDIATELY AFTER YOU OPEN THE CARGO COMPARTMENT DOOR, RECORD ON THE WORK CARD ON THE DOOR, THE DATE AND TIME WHEN YOU OPENED IT. IF THE CARGO COMPARTMENT DOOR STAYS OPEN FOR 12 HOURS OR MORE, YOU MUST BLEED THE HYDRAULIC SYSTEM RELATED TO IT. IF YOU DO NOT OBEY THESE PRECAUTIONS, THE DOOR CAN CLOSE SUDDENLY WHEN YOU SET THE DOOR TO "CLOSE". THIS CAN CAUSE DAMAGE TO THE DOOR AND TO THE AIRCRAFT STRUCTURE.

FIN : 2502MJ , 2503MJ , 2505MJ , 2506MJ Task Summary MMEL or CDL Ref MMEL 52-30-02B MMEL 52-30-02C 1.

Reason for the Job MMEL 52-30-02B Cargo Door Actuator MMEL 52-30-02C Cargo Door Actuator

2

Job Set-up Information A.

Access NO NO

Specific Tools YES YES

Mhr 01.0 01.0

E/T 01.0 01.0

Nb Men 1 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific No specific (98A52008509000)

B.

Test NO NO

QTY 1 AR 1 AR AR AR AR 1

DESIGNATION ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE CAP - BLANKING CONTAINER 5 L (1.32 USGAL) PLUG - BLANKING PLUG - BLANKING, PRESSURE SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S) SLING-UNIVERSAL,DOORS

Referenced Information REFERENCE (Ref. 12-12-29-611-001-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01).

DESIGNATION Fill the Hydraulic Fluid Reservoir with a Hand Pump Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-36-00-040-001-A - Deactivation of the Cargo Door Actuator(s)

REFERENCE (Ref. 24-41-00-862-002-A-02). (Ref. 29-10-00-864-002-A). (Ref. 29-14-00-614-001-A). (Ref. 29-14-00-614-002-A). (Ref. 29-14-00-614-002-A-01). (Ref. 31-60-00-860-001-A). (Ref. 52-30-00-860-002-A).

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Depressurize the Yellow Hydraulic System Depressurization of the Hydraulic Reservoirs Pressurization of the Hydraulic Reservoirs through the Ground Connector Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU) EIS Start Procedure Close the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump Open the FWD or Aft Cargo-Compartment Door with the Crane Close the FWD or Aft Cargo-Compartment Door with the Crane

(Ref. 52-30-00-860-005-A). (Ref. 52-30-00-860-009-A). Cargo Door Actuator SHEET 1 Closing of the Cargo Door with the Crane SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-36-00-040-001-A - Deactivation of the Cargo Door Actuator(s)

1 2

3

A

A

2 4

5

6 FR24A FR52A FR55A FR28 FR56 FR59

A

10

7 8 9

11 18

19

17

22

11

20 21 16

14

15

12 14 13 N_MM_523600_4_AAM0_01_00

Figure 52-36-00-991-00300-00-A / SHEET 1/1 - Cargo Door Actuator ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-36-00-040-001-A - Deactivation of the Cargo Door Actuator(s)

A

A

B

31

B 35 34

32

33

33

N_MM_523600_4_ACM0_01_00

Figure 52-36-00-991-00400-00-A / SHEET 1/1 - Closing of the Cargo Door with the Crane ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-36-00-040-001-A - Deactivation of the Cargo Door Actuator(s)

3.

Job Set-up Subtask 52-36-00-010-052-A A.

Get Access (1) Make sure that the FWD or Aft cargo-compartment door (referred to as cargo door) is fully opened and safetied with the support struts (Ref. AMM TASK 52-30-00-860-005) . (2) Open the access panel 134AR or 154AR to get access to the service panel of the applicable cargo door. (3) Put the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position below the opened cargo door.

Subtask 52-36-00-865-054-A B.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU HYDRAULIC/HYD POWER/Y 3803GX N30 ** ON A/C 401-450 121VU HYDRAULIC/HYD POWER/Y

3803GX

N31

** ON A/C ALL 122VU 123VU 123VU

1MJ 3802GX 3801GX

T12 AB06 AB03

DOORS/CARGO Y HYD/ELEC/PUMP Y HYD/ELEC/ELEC PUMP/NORM

Subtask 52-36-00-860-055-A C.

Aircraft Maintenance Configuration (1) Depressurize the Yellow hydraulic system (Ref. AMM TASK 29-10-00-864-002) . (2) Depressurize the reservoir of the Yellow hydraulic system (Ref. AMM TASK 29-14-00-614-001) . (3) Put a WARNING NOTICE(S) in the cockpit on overhead panel 40VU to prevent the operation of the Yellow hydraulic system. (4) Put a WARNING NOTICE(S) on the ground service panel to prevent the operation of the Yellow hydraulic system. (5) Put a CONTAINER 5 L (1.32 USGAL) below the hydraulic connections of the door actuator(s) to collect the hydraulic fluid.

4.

Procedure Subtask 52-36-00-040-050-A A.

Deactivation of the Door Actuator(s) (Ref. Fig. Cargo Door Actuator SHEET 1) (Ref. Fig. Closing of the Cargo Door with the Crane SHEET 1) CAUTION:

USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT HYDRAULIC LINES ON UNIONS. IF YOU DO NOT USE THE SECOND WRENCH, THERE IS A RISK THAT YOU WILL LOOSEN OR TIGHTEN THE UNION TOO MUCH.

(1) Remove the flexible hoses from the defective door actuator as follows: (a) Loosen the union and remove the flexible hose (22) from port A of the door actuator (11). Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-36-00-040-001-A - Deactivation of the Cargo Door Actuator(s)

(b) Loosen the union and remove the flexible hose (21) from port B of the door actuator (11). (c) Install the PLUG - BLANKING on the open ends of the door actuator ports. (d) Install the PLUG - BLANKING, PRESSURE on the open ends of the flexible hoses. (2) If necessary, remove the damaged door actuator as follows: (a) Remove the electrical connector (20) from the receptacle of the proximity switch. (b) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (c) Remove the screw (7), the washer (8), the nut (10) and disconnect the bonding jumper (9) from the bonding angle of the piston eye-end (6). (d) Remove the screw (17) and the washer (18) and disconnect the bonding jumper (19) from the door actuator (11). (e) Remove and discard the cotter pin (5) from the nut (4). (f)

Remove the nut (4) and the washer (2) from the bolt (1).

(g) Support the door actuator (16) and remove the bolt (1) with the washer (2) from the actuator attachment fitting (3). (h) Remove the piston eye-end (6) from the actuator attachment fitting (3). (i)

Remove and discard the cotter pin (12) from the nut (13).

(j)

Remove the nut (13) and the washer (14) from the bolt (16).

(k) Support the door actuator (11) and remove the bolt (16) and the washer (14) from the actuator beam (15). (l)

Remove the door actuator (11) from the actuator beam (15).

Subtask 52-36-00-865-055-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 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU HYDRAULIC/HYD POWER/Y 3803GX N30 ** ON A/C 401-450 121VU HYDRAULIC/HYD POWER/Y

3803GX

N31

** ON A/C ALL 122VU 123VU 123VU

1MJ 3802GX 3801GX

T12 AB06 AB03

DOORS/CARGO Y HYD/ELEC/PUMP Y HYD/ELEC/ELEC PUMP/NORM

Subtask 52-36-00-860-054-A C.

Aircraft Maintenance Configuration (1) Make sure that the aircraft electrical circuits are energized (Ref. AMM TASK 24-41-00-861-002) . (2) Set the Electronic Centralized Aircraft Monitor (ECAM) system to ON (Ref. AMM TASK 31-60-00860-001) . (3) Remove the WARNING NOTICE(S) from the ground service panel and the cockpit. (4) Pressurize the reservoir of the Yellow hydraulic system (Ref. AMM TASK 29-14-00-614-002) .

Subtask 52-36-00-790-050-A

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-36-00-040-001-A - Deactivation of the Cargo Door Actuator(s)

D.

Leak Check of the Door Hydraulic System (if one door actuator is deactivated) (1) Turn the selector of the service panel to the OPEN position and hold it for three seconds to bleed the door actuator. (2) Remove the support struts from the cargo door structure and the door frame of the fuselage. (3) Turn the selector of the service panel to the CLOSE position and hold it until the cargo door moves down. (4) Open and close the cargo door three times. Make sure that the cargo door is fully opened. (5) Do a visual inspection of the door actuators, the pipes, the hoses and the related valves. Make sure that there are no leaks. NOTE: If necessary, disconnect the hydraulic pipes from the defective components and attach correct pressure plugs to the open ends. (6) Examine the Yellow reservoir level on the HYD page of the lower display unit of the ECAM system. If necessary, fill the Yellow reservoir to its normal fill level (Ref. AMM TASK 12-12-29-611-001) .

Subtask 52-36-00-790-051-A E.

Leak Check of the Door Hydraulic System (if two door actuators are deactivated) (1) Install the SLING-UNIVERSAL,DOORS (98A52008509000) to the cargo door and to the crane (Ref. AMM TASK 52-30-00-860-009) . (2) Remove the support struts from the cargo door structure and the door frame of the fuselage. (3) Turn the selector of the service panel to the OPEN position and hold it for three seconds to bleed the extension line. (4) Turn the selector of the service panel to the CLOSE position and hold it for three seconds to bleed the retraction line. (5) Examine the Yellow reservoir level on the HYD page of the lower display unit of the ECAM system. If necessary, fill the Yellow reservoir to its normal fill level (Ref. AMM TASK 12-12-29-611-001) .

5.

Close-up Subtask 52-36-00-410-052-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) If one door actuator is deactivated, close the cargo door hydraulically (Ref. AMM TASK 52-30-00860-002) . (3) If the two door actuators are deactivated, close the cargo door with the crane (Ref. AMM TASK 5230-00-860-009) . (4) Close the access panel 134AR or 154AR. (5) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (6) Remove the access platform(s). (7) Make an entry in the aircraft technical log.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-36-00-040-002-A - Deactivation of the Hand Pump

** ON A/C ALL TASK 52-36-00-040-002-A Deactivation of the Hand Pump

FIN : 3009GM Task Summary MMEL or CDL Ref MMEL 52-30-05A

Access YES

Test NO

1.

Reason for the Job MMEL 52-30-05A Cargo Door Hand Pump (FAA only)

2

Job Set-up Information A.

Mhr 01.0

E/T 01.0

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific

B.

Specific Tools NO

QTY 1 1 AR AR 1

DESIGNATION ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE CONTAINER 5 L (1.32 USGAL) PLUG - BLANKING SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 198CB, 198DB

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 12-12-29-611-001-A). (Ref. 29-00-00-910-002-A). (Ref. 29-10-00-863-002-A). (Ref. 29-10-00-864-002-A). (Ref. 29-14-00-614-001-A). (Ref. 29-14-00-614-002-A). (Ref. 29-14-00-614-002-A-01). (Ref. 52-30-00-860-002-A).

DESIGNATION Fill the Hydraulic Fluid Reservoir with a Hand Pump Safety Procedures of the Hydraulic System Pressurize the Yellow Hydraulic System with a Hydraulic Ground Power-Cart Depressurize the Yellow Hydraulic System Depressurization of the Hydraulic Reservoirs Pressurization of the Hydraulic Reservoirs through the Ground Connector Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU) Close the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump

Hand Pump SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-36-00-040-002-A - Deactivation of the Hand Pump

A

FR48

FR47

A B 198DB GROUND SERVICE PANEL OF YELLOW HYDRAULIC SYSTEM

198CB 7 6

1 2

B

5 3

4 BACK OF GROUND SERVICE PANEL

N_MM_523600_4_AEM0_01_00

Figure 52-36-00-991-00200-00-A / SHEET 1/1 - Hand Pump ** ON A/C ALL Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-36-00-040-002-A - Deactivation of the Hand Pump

3.

Job Set-up Subtask 52-36-00-010-054-A A.

Get Access (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position below the Yellow ground service panel. (2) Open the access door 198CB to get access to the hand pump. (3) Remove the access panel 198DB to get access to the hydraulic connections of the hand pump.

Subtask 52-36-00-865-056-A B.

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

DESIGNATION

FIN

LOCATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU HYDRAULIC/HYD POWER/Y 3803GX N30 ** ON A/C 401-450 121VU HYDRAULIC/HYD POWER/Y

3803GX

N31

** ON A/C ALL 122VU 123VU 123VU

1MJ 3802GX 3801GX

T12 AB06 AB03

DOORS/CARGO Y HYD/ELEC/PUMP Y HYD/ELEC/ELEC PUMP/NORM

Subtask 52-36-00-860-057-A C.

Aircraft Maintenance Configuration (1) Depressurize the Yellow hydraulic system (Ref. AMM TASK 29-10-00-864-002) . (2) Depressurize the reservoir of the Yellow hydraulic system (Ref. AMM TASK 29-14-00-614-001) . (3) Put WARNING NOTICE(S) in position to tell persons not to pressurize the Yellow hydraulic system: · In the cockpit on the hydraulic section 40VU of the overhead panel · On the ground service panel of the Yellow hydraulic system. (4) Obey the hydraulic safety procedures (Ref. AMM TASK 29-00-00-910-002) . (5) Push the PTU P/B switch on the overhead panel 40VU to prevent the unwanted operation of the power transfer unit. (6) Put a CONTAINER 5 L (1.32 USGAL) below the hydraulic connections of the hand pump to collect hydraulic fluid.

4.

Procedure Subtask 52-36-00-040-051-A A.

Deactivation of the Handpump (Ref. Fig. Hand Pump SHEET 1) CAUTION:

USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT HYDRAULIC LINES ON UNIONS. IF YOU DO NOT USE THE SECOND WRENCH, THERE IS A RISK THAT YOU WILL LOOSEN OR TIGHTEN THE UNION TOO MUCH.

(1) Loosen the union nut (2) from the union (3) and carefully disconnect the suction line (1) from the port "C" of the hand pump (4). Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-36-00-040-002-A - Deactivation of the Hand Pump

(2) Loosen the union nut (6) from the union (5) and carefully disconnect the pressure line (7) from the port "A" of the hand pump (4). (3) Put the PLUG-BLANKING in each disconnected line end. (4) Put blanking caps on the ports "A" and "C" of the hand pump (4) to prevent all contamination. Subtask 52-36-00-865-057-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 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU HYDRAULIC/HYD POWER/Y 3803GX N30 ** ON A/C 401-450 121VU HYDRAULIC/HYD POWER/Y

3803GX

N31

** ON A/C ALL 122VU 123VU 123VU

1MJ 3802GX 3801GX

T12 AB06 AB03

DOORS/CARGO Y HYD/ELEC/PUMP Y HYD/ELEC/ELEC PUMP/NORM

Subtask 52-36-00-860-058-A C.

Preparation for the Test (1) Remove the warning notices from the overhead panel of the cockpit. (2) Pressurize the reservoir of the Yellow hydraulic system (Ref. AMM TASK 29-14-00-614-002) . (3) Pressurize the Yellow hydraulic system (Ref. AMM TASK 29-10-00-863-002) . (4) Push the PTU P/B switch on the overhead panel 40VU to activate the power transfer unit.

Subtask 52-36-00-790-052-A D.

Leak Check of the Door Hydraulic System (1) Turn the selector of the service panel to the OPEN position and hold it until the cargo door is fully opened. (2) Turn the selector of the service panel to the CLOSE position and hold it until the cargo door is closed. (3) Open and close the cargo door ten times to bleed the door hydraulic system. (4) Do a visual inspection to make sure that there are no leaks at the disconnected hydraulic lines. (5) Examine the level of the Yellow reservoir on the HYD page of the lower display unit of the ECAM system. If necessary, fill the Yellow reservoir (Ref. AMM TASK 12-12-29-611-001) .

5.

Close-up Subtask 52-36-00-410-053-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the container. (3) Make sure that the FWD or AFT cargo door is correctly closed (Ref. AMM TASK 52-30-00-860-002) . (4) Install the access panel 198DB. (5) Close the access door 198CB of the Yellow ground service panel. (6) Remove the access platform(s).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-36-00-040-002-A - Deactivation of the Hand Pump

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-002-A - Deactivation of the Key Pad

** ON A/C ALL TASK 52-51-00-040-002-A Deactivation of the Key Pad

FIN : ** ON A/C ALL EMB SB 25-1305 for A/C 210-210 25MQ ** ON A/C ALL Task Summary MMEL or CDL Ref MMEL 52-53-03A

Access NO

Test NO

1.

Reason for the Job MMEL 52-53-03A Lock Function of the Cockpit Door Sw (FAA only)

2

Job Set-up Information A.

Mhr 00.3

E/T 00.3

Nb Men 1

Referenced Information REFERENCE (Ref. 52-51-00-040-007-A).

3.

Specific Tools NO

DESIGNATION Deactivation of the Key Pad

Job Set-up

** ON A/C ALL EMB SB 25-1305 for A/C 210-210 Subtask 52-51-00-860-053-A A.

There is no special job set-up for this task.

** ON A/C ALL 4.

Procedure

** ON A/C ALL EMB SB 25-1305 for A/C 210-210 Subtask 52-51-00-040-050-A A.

Do the deactivation of the key pad (Ref. AMM TASK 52-51-00-040-007) .

End of document Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-003-A - Deactivation of the Key Pad

** ON A/C ALL TASK 52-51-00-040-003-A Deactivation of the Key Pad

FIN : ** ON A/C ALL EMB SB 25-1305 for A/C 210-210 23MQ ** ON A/C ALL Task Summary MMEL or CDL Ref MMEL 52-51-03A

Access NO

1.

Reason for the Job MMEL 52-51-03A CDLS Buzzer (FAA only)

2

Job Set-up Information A.

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Referenced Information REFERENCE (Ref. 52-51-00-040-007-A).

3.

Test NO

DESIGNATION Deactivation of the Key Pad

Job Set-up

** ON A/C ALL EMB SB 25-1305 for A/C 210-210 Subtask 52-51-00-010-052-A A.

There is no special job set-up for this task.

** ON A/C ALL 4.

Procedure

** ON A/C ALL EMB SB 25-1305 for A/C 210-210 Subtask 52-51-00-040-053-A A.

Do the deactivation procedure (Ref. AMM TASK 52-51-00-040-007) .

End of document Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-006-A - Deactivation of the CDLS Normal System

** ON A/C ALL TASK 52-51-00-040-006-A Deactivation of the CDLS Normal System Task Summary MMEL or CDL Ref MMEL 52-51-01B 1.

Reason for the Job MMEL 52-51-01B CDLS Normal System

2

Job Set-up Information A.

Access NO

Mhr 00.3

E/T 00.3

Nb Men 1

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

3.

Specific Tools NO

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Test YES

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up

** ON A/C ALL EMB SB 25-1305 for A/C 210-210 Subtask 52-51-00-861-051-A A.

Energize the Aircraft Electrical Circuits (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

** ON A/C ALL Subtask 52-51-00-865-066-A B.

Table of the circuit breakers used in this procedure:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-006-A - Deactivation of the CDLS Normal System

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 204-205, 207-207, 210-210, 217-217, 222-222, 227-228 PRE SB 11-1047 for A/C 204-205, 207-207, 210-210, 217-217, 222-222, 227-228 EMB SB 25-1305 for A/C 210-210 122VU DOORS/PAX/MONG

1MQ

T13

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 206-206, 208-209, 211-216, 218-221, 223-226, 229-239, 241-242, 244-250, 301-450, 500-600 POST SB 11-1047 for A/C 204-204, 217-217, 222-222, 227-228 EMB SB 11-1047 for A/C 201-201, 203-203, 206-206, 209-209, 211-211, 218-220, 229-235, 237-237, 244-244 EMB SB 25-1326 for A/C 231-232, 237-237, 244-244 122VU DOORS CKPT LOCK 1MQ T13 ** ON A/C 240-240, 243-243 POST SB 11-1047 for A/C 205-205, 207-207, 210-210 EMB SB 11-1047 for A/C 240-240, 243-243 EMB SB 25-1305 for A/C 210-210 122VU COCKPIT DOOR LOCK SYSTEM

1MQ

T13

** ON A/C ALL 4.

Procedure

** ON A/C ALL EMB SB 25-1305 for A/C 210-210 Subtask 52-51-00-040-055-A A.

Deactivation of the CDLS Normal System (1) Open, safety and tag this(these) circuit breaker(s): · 1MQ. NOTE: All parts of the CDLS (normal and back-up system, if installed) can be inoperative if the complete system is deactivated in the unlocked position and adjustment is not required by regulations for the intended flight. NOTE: If CKPT DOOR BKUP panel 45VU is installed on overhead panel 20VU and the switch LKG SYS (21MQ) is in the BKUP position: - Toggle switch COCKPIT DOOR (26MQ) on center pedestal panel 119VU and keypad 25MQ on the flight attendant panel are inoperative. These cannot be used to unlock and open the cockpit door. NOTE: If CKPT DOOR BKUP panel 45VU is installed on overhead panel 20VU and the switch LKG SYS (21MQ) is in the BKUP position:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-006-A - Deactivation of the CDLS Normal System

- The cockpit door can be unlocked and opened from the cockpit side only and cannot be unlocked and opened from the cabin side. You must not close the cockpit door when there is no person inside the cockpit. ** ON A/C ALL 5.

Close-up

** ON A/C ALL EMB SB 25-1305 for A/C 210-210 Subtask 52-51-00-860-076-A A.

Aircraft Maintenance Configuration (1) Put the aircraft back to the serviceable condition. (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (3) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-007-A - Deactivation of the Key Pad

** ON A/C ALL TASK 52-51-00-040-007-A Deactivation of the Key Pad

FIN : ** ON A/C ALL EMB SB 25-1305 for A/C 210-210 25MQ ** ON A/C ALL Task Summary MMEL or CDL Ref MMEL 52-51-04A 1.

Reason for the Job MMEL 52-51-04A CDLS Keypad

2

Job Set-up Information A.

Access NO

Specific Tools NO

Mhr 00.3

E/T 00.3

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

Test NO

QTY AR AR AR AR

DESIGNATION CAP - BLANKING SAFETY CLIP - CIRCUIT BREAKER TIE WRAP WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). Control Unit 24MQ SHEET 1

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-007-A - Deactivation of the Key Pad

20VU

Z210

B

A

4 3

1

24MQ

2

N_MM_525100_4_AAM0_01_00

Figure 52-51-00-991-00100-00-A / SHEET 1/1 - Control Unit 24MQ ** ON A/C ALL | EMB SB 25-1305 for A/C 210-210 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-007-A - Deactivation of the Key Pad

3.

Job Set-up

** ON A/C ALL EMB SB 25-1305 for A/C 210-210 Subtask 52-51-00-860-078-A A.

Aircraft Maintenance Configuration (1) Make sure that the aircraft electrical circuits are energized (Ref. AMM TASK 24-41-00-861-002) . (2) Make sure that access to the cockpit is available.

** ON A/C ALL Subtask 52-51-00-865-109-A B.

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

DESIGNATION

FIN

LOCATION

** ON A/C 204-205, 207-207, 210-210, 217-217, 222-222, 227-228 PRE SB 11-1047 for A/C 204-205, 207-207, 210-210, 217-217, 222-222, 227-228 EMB SB 25-1305 for A/C 210-210 122VU DOORS/PAX/MONG

1MQ

T13

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 206-206, 208-209, 211-216, 218-221, 223-226, 229-239, 241-242, 244-250, 301-450, 500-600 POST SB 11-1047 for A/C 204-204, 217-217, 222-222, 227-228 EMB SB 11-1047 for A/C 201-201, 203-203, 206-206, 209-209, 211-211, 218-220, 229-235, 237-237, 244-244 EMB SB 25-1326 for A/C 231-232, 237-237, 244-244 122VU DOORS CKPT LOCK 1MQ T13 ** ON A/C 240-240, 243-243 POST SB 11-1047 for A/C 205-205, 207-207, 210-210 EMB SB 11-1047 for A/C 240-240, 243-243 EMB SB 25-1305 for A/C 210-210 122VU COCKPIT DOOR LOCK SYSTEM

1MQ

T13

** ON A/C ALL 4.

Procedure

** ON A/C ALL EMB SB 25-1305 for A/C 210-210 Subtask 52-51-00-040-056-A A.

Deactivation of the Key Pad (Ref. Fig. Control Unit 24MQ SHEET 1)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-007-A - Deactivation of the Key Pad

NOTE: If the cockpit door closes during the deactivation procedure and no person is in the cockpit, de-energize the aircraft electrical circuits. This will let you open the cockpit door from the cabin. (1) Hold the front face of the control unit (1) and loosen the captive screws (2). (2) Carefully remove the control unit (1) until you get access to the electrical connector (4). (3) Disconnect the electrical connector (4) from the receptacle (3). (4) Put the CAP-BLANKING on each disconnected electrical connector and receptacle. (5) Safety the electrical connector (4) with TIE WRAPS on the adjacent fuselage structure. (6) Carefully install the control unit (1) and tighten the captive screws (2). (7) Put a WARNING NOTICE(S) on the overhead panel to tell the persons that the keypad is deactivated. ** ON A/C ALL 5.

Close-up Subtask 52-51-00-865-068-A A.

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

DESIGNATION

FIN

LOCATION

** ON A/C 204-205, 207-207, 210-210, 217-217, 222-222, 227-228 PRE SB 11-1047 for A/C 204-205, 207-207, 210-210, 217-217, 222-222, 227-228 EMB SB 25-1305 for A/C 210-210 122VU DOORS/PAX/MONG

1MQ

T13

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 206-206, 208-209, 211-216, 218-221, 223-226, 229-239, 241-242, 244-250, 301-450, 500-600 POST SB 11-1047 for A/C 204-204, 217-217, 222-222, 227-228 EMB SB 11-1047 for A/C 201-201, 203-203, 206-206, 209-209, 211-211, 218-220, 229-235, 237-237, 244-244 EMB SB 25-1326 for A/C 231-232, 237-237, 244-244 122VU DOORS CKPT LOCK 1MQ T13 ** ON A/C 240-240, 243-243 POST SB 11-1047 for A/C 205-205, 207-207, 210-210 EMB SB 11-1047 for A/C 240-240, 243-243 EMB SB 25-1305 for A/C 210-210 122VU COCKPIT DOOR LOCK SYSTEM

1MQ

T13

** ON A/C ALL EMB SB 25-1305 for A/C 210-210 Subtask 52-51-00-860-079-A B.

Put the system back to the serviceable condition.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-007-A - Deactivation of the Key Pad

(1) Put the aircraft back to the serviceable condition. (2) Make an entry in the aircraft technical log that the keypad is deactivated.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-010-A - Deactivation of the Electrical Release Strikes

** ON A/C ALL TASK 52-51-00-040-010-A Deactivation of the Electrical Release Strikes

FIN : ** ON A/C ALL EMB SB 25-1305 for A/C 210-210 30MQ , 31MQ , 32MQ ** ON A/C ALL Task Summary MMEL or CDL Ref MMEL 52-51-06A MMEL 52-51-06B

Access NO NO

Test NO NO

Specific Tools NO NO

1.

Reason for the Job MMEL 52-51-06A CDLS Door Release Strike (Catch, Spring, Solenoid, Bolt) MMEL 52-51-06B CDLS Door Release Strike (Catch, Spring, Solenoid, Bolt)

2

Job Set-up Information A.

Mhr 00.5 00.5

E/T 00.5 00.5

Nb Men 1 1

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Operational Test of the Routine Access Removal of the Electrical Release Strike

(Ref. 52-51-00-710-001-A). (Ref. 52-51-12-000-001-A). Ref. ESPM 20-48-25 Ref. AWM 52-51-02 Electrical Release Strikes SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-010-A - Deactivation of the Electrical Release Strikes

Z220

A

A

COCKPIT DOOR LAVATORY DOOR

FR23

FR11

B B ELECTRICAL RELEASE STRIKE

B

B SOLENOID HOUSING

PLUNGER CATCH SPRING

HOUSING N_MM_525100_4_ACM0_01_00

Figure 52-51-00-991-01100-00-A / SHEET 1/1 - Electrical Release Strikes ** ON A/C ALL | EMB SB 25-1305 for A/C 210-210 | EMB SB 52-1115 for A/C 237-237 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-010-A - Deactivation of the Electrical Release Strikes

3.

Job Set-up

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 EMB SB 52-1115 for A/C 237-237 Subtask 52-51-00-010-055-A A.

Aircraft Maintenance Configuration (1) Make sure that the aircraft electrical circuits are energized (Ref. AMM TASK 24-41-00-861-002) . (2) Make sure that access to the flight compartment is available. (3) Make sure that the toggle switch 21MQ is set to the NORM position.

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-226, 229-230, 233-236, 238-241, 243-243, 301-450, 500-600 EMB SB 25-1305 for A/C 210-210 Subtask 52-51-00-010-055-B A.

Aircraft Maintenance Configuration (1) Make sure that the aircraft electrical circuits are energized (Ref. AMM TASK 24-41-00-861-002) . (2) Make sure that access to the flight compartment is available.

** ON A/C ALL Subtask 52-51-00-865-081-A B.

Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged: PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 204-205, 207-207, 210-210, 217-217, 222-222, 227-228 PRE SB 11-1047 for A/C 204-205, 207-207, 210-210, 217-217, 222-222, 227-228 EMB SB 25-1305 for A/C 210-210 122VU DOORS/PAX/MONG

1MQ

T13

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 206-206, 208-209, 211-216, 218-221, 223-226, 229-239, 241-242, 244-250, 301-450, 500-600 POST SB 11-1047 for A/C 204-204, 217-217, 222-222, 227-228 EMB SB 11-1047 for A/C 201-201, 203-203, 206-206, 209-209, 211-211, 218-220, 229-235, 237-237, 244-244 EMB SB 25-1326 for A/C 231-232, 237-237, 244-244 122VU DOORS CKPT LOCK 1MQ T13 ** ON A/C 240-240, 243-243 POST SB 11-1047 for A/C 205-205, 207-207, 210-210 EMB SB 11-1047 for A/C 240-240, 243-243 EMB SB 25-1305 for A/C 210-210 122VU COCKPIT DOOR LOCK SYSTEM

1MQ

T13

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-010-A - Deactivation of the Electrical Release Strikes

** ON A/C ALL 4.

Procedure

** ON A/C ALL EMB SB 25-1305 for A/C 210-210 EMB SB 52-1115 for A/C 237-237 Subtask 52-51-00-040-058-A A.

Deactivation of the Electrical Release Strike (Ref. Fig. Electrical Release Strikes SHEET 1) (1) Turn the D-ring of the latch mechanism and open the cockpit door. (2) Manually move the catch of the defective electrical release strike to make sure that it moves freely. (3) If the plunger causes a blockage of the catch, remove the defective electrical release strike (Ref. AMM TASK 52-51-12-000-001) . NOTE: It is important to keep the jiffi junction connectors at the A/C wire harness. This is because of the isolation necessary to prevent a short circuit. (4) If the catch moves freely, disconnect the A/C wire harness from the applicable electrical release strike cables Ref. ESPM 20-48-25 and Ref. AWM 52-51-02. NOTE: It is important to keep the jiffi junction connectors at the A/C wire harness. This is because of the isolation necessary to prevent a short circuit. NOTE: The A/C wires 4 and 7 of the center electrical release strike must stay connected. This is to keep the OPEN light of the indication light 22MQ. (5) Make sure that the remaining electrical release strikes operate satisfactorily (Ref. AMM TASK 52-5100-710-001) . (6) Put a warning notice on the door post to tell persons that the applicable electrical release strike is deactivated or removed.

** ON A/C ALL Subtask 52-51-00-865-086-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 204-205, 207-207, 210-210, 217-217, 222-222, 227-228 PRE SB 11-1047 for A/C 204-205, 207-207, 210-210, 217-217, 222-222, 227-228 EMB SB 25-1305 for A/C 210-210 122VU DOORS/PAX/MONG

1MQ

T13

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 206-206, 208-209, 211-216, 218-221, 223-226, 229-239, 241-242, 244-250, 301-450, 500-600 POST SB 11-1047 for A/C 204-204, 217-217, 222-222, 227-228

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-010-A - Deactivation of the Electrical Release Strikes

PANEL DESIGNATION FIN LOCATION EMB SB 11-1047 for A/C 201-201, 203-203, 206-206, 209-209, 211-211, 218-220, 229-235, 237-237, 244-244 EMB SB 25-1326 for A/C 231-232, 237-237, 244-244 122VU DOORS CKPT LOCK 1MQ T13 ** ON A/C 240-240, 243-243 POST SB 11-1047 for A/C 205-205, 207-207, 210-210 EMB SB 11-1047 for A/C 240-240, 243-243 EMB SB 25-1305 for A/C 210-210 122VU COCKPIT DOOR LOCK SYSTEM

1MQ

T13

** ON A/C ALL 5.

Close-up

** ON A/C ALL EMB SB 25-1305 for A/C 210-210 EMB SB 52-1115 for A/C 237-237 Subtask 52-51-00-860-095-A A.

Put the aircraft back to its initial configuration. (1) Make sure that the work area is clean and clear of tools and other items. (2) Make sure that the aircraft electrical circuits are de-energized (Ref. AMM TASK 24-41-00-862-002) . (3) Make an entry in the aircraft technical log that the electrical release strike is deactivated.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-803-A - Deactivation of the Buzzer of the Cockpit-Door Locking System

** ON A/C ALL TASK 52-51-00-040-803-A Deactivation of the Buzzer of the Cockpit-Door Locking System

FIN : ** ON A/C ALL EMB SB 25-1305 for A/C 210-210 32MQ ** ON A/C ALL Task Summary MMEL or CDL Ref MMEL 52-51-03A 1.

Access YES

Test YES

Specific Tools NO

Mhr 00.5

E/T 00.5

Nb Men 1

Reason for the Job MMEL 52-51-03A CDLS Buzzer NOTE: This procedure is only necessary if the buzzer of the cockpit-door locking system operates permanently.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION AR CAP - BLANKING AR SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS 210 211HC

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-803-A - Deactivation of the Buzzer of the Cockpit-Door Locking System

REFERENCE (Ref. 24-41-00-862-002-A-02).

DESIGNATION De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Installation of the Ceiling Panels Operational Test of the Cockpit-Door Locking System (CDLS) Removal of the Buzzer of the Cockpit-Door Locking System

(Ref. 25-13-41-400-001-A). (Ref. 52-51-00-710-002-A). (Ref. 52-51-13-000-001-A). 3.

Job Set-up

** ON A/C ALL EMB SB 25-1305 for A/C 210-210 Subtask 52-51-00-860-118-A A.

Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

** ON A/C ALL Subtask 52-51-00-865-139-A B.

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

DESIGNATION

FIN

LOCATION

** ON A/C 204-205, 207-207, 210-210, 217-217, 222-222, 227-228 PRE SB 11-1047 for A/C 204-205, 207-207, 210-210, 217-217, 222-222, 227-228 EMB SB 25-1305 for A/C 210-210 122VU DOORS/PAX/MONG

1MQ

T13

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 206-206, 208-209, 211-216, 218-221, 223-226, 229-239, 241-242, 244-250, 301-450, 500-600 POST SB 11-1047 for A/C 204-204, 217-217, 222-222, 227-228 EMB SB 11-1047 for A/C 201-201, 203-203, 206-206, 209-209, 211-211, 218-220, 229-235, 237-237, 244-244 EMB SB 25-1326 for A/C 231-232, 237-237, 244-244 122VU DOORS CKPT LOCK 1MQ T13 ** ON A/C 240-240, 243-243 POST SB 11-1047 for A/C 205-205, 207-207, 210-210 EMB SB 11-1047 for A/C 240-240, 243-243 EMB SB 25-1305 for A/C 210-210 122VU COCKPIT DOOR LOCK SYSTEM

1MQ

T13

** ON A/C ALL 4.

Procedure

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-803-A - Deactivation of the Buzzer of the Cockpit-Door Locking System

** ON A/C ALL EMB SB 25-1305 for A/C 210-210 Subtask 52-51-00-040-062-A A.

Deactivation of the Buzzer of the Cockpit-Door Locking System (1) Remove the buzzer of the cockpit-door locking system (Ref. AMM TASK 52-51-13-000-001) . (a) Put the CAP-BLANKING on each disconnected electrical connector and receptacle.

** ON A/C ALL 5.

Close-up Subtask 52-51-00-865-140-A A.

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

DESIGNATION

FIN

LOCATION

** ON A/C 204-205, 207-207, 210-210, 217-217, 222-222, 227-228 PRE SB 11-1047 for A/C 204-205, 207-207, 210-210, 217-217, 222-222, 227-228 EMB SB 25-1305 for A/C 210-210 122VU DOORS/PAX/MONG

1MQ

T13

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-203, 206-206, 208-209, 211-216, 218-221, 223-226, 229-239, 241-242, 244-250, 301-450, 500-600 POST SB 11-1047 for A/C 204-204, 217-217, 222-222, 227-228 EMB SB 11-1047 for A/C 201-201, 203-203, 206-206, 209-209, 211-211, 218-220, 229-235, 237-237, 244-244 EMB SB 25-1326 for A/C 231-232, 237-237, 244-244 122VU DOORS CKPT LOCK 1MQ T13 ** ON A/C 240-240, 243-243 POST SB 11-1047 for A/C 205-205, 207-207, 210-210 EMB SB 11-1047 for A/C 240-240, 243-243 EMB SB 25-1305 for A/C 210-210 122VU COCKPIT DOOR LOCK SYSTEM

1MQ

T13

** ON A/C ALL EMB SB 25-1305 for A/C 210-210 Subtask 52-51-00-710-066-A B.

Operational Test (1) Do the Operational Test of the Cockpit-Door Locking System (CDLS) (Ref. AMM TASK 52-51-00710-002) .

Subtask 52-51-00-410-055-A

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-803-A - Deactivation of the Buzzer of the Cockpit-Door Locking System

C.

Close Access (1) Install ceiling panel 211HC (Ref. AMM TASK 25-13-41-400-001) . (2) Make sure that the work area is clean and clear of tools and other items.

Subtask 52-51-00-860-119-A D.

Aircraft Maintenance Configuration (1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (2) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-001-A - Visual Check to Make Sure that the Cargo Compartment Doors are Correctly Closed

** ON A/C ALL TASK 52-70-00-040-001-A Visual Check to Make Sure that the Cargo Compartment Doors are Correctly Closed 1.

Reason for the Job MMEL 52-07-05A Cargo Door Indication on the DOOR/OXY SD page

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

3.

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Job Set-up Subtask 52-70-00-010-050-A A.

Get Access (1) Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the applicable cargo compartment door.

4.

Procedure Subtask 52-70-00-210-050-G A.

Visual Check of the inoperative FWD and/or AFT Cargo Compartment Doors (1) Push the handle flap in, to release the door handle. (2) Pull the door handle up from the door structure in the UNLOCKED direction until the door handle moves 65 degrees. NOTE: Do not unlock the cargo door at this time. (3) Make sure that you can see the red marks of each safety in the indication windows of the access panels. (4) Push the door handle down into the LOCKED position again. (5) Do a visual check of the external cargo door to make sure that: · The cargo door is aligned with the fuselage. · The vent door is fully closed. · The green marks of each safety cam are in view in the indication windows of the access panels at the lower cargo-door edge. · The door handle is aligned with the cargo door contour.

Subtask 52-70-00-970-050-A B.

Entry in the Log Book. (1) Make an entry in the aircraft log book to record that: · the CARGO indication is defective on the lower ECAM DU · the cargo-compartment door is closed and locked.

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-224, 226-250, 301-450, 500-600 Subtask 52-70-00-210-051-A

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-001-A - Visual Check to Make Sure that the Cargo Compartment Doors are Correctly Closed

C.

Visual Check to Make Sure that the Bulk Cargo-Compartment Door is Correctly Closed (1) Do this visual check on the bulk cargo-compartment door: (a) Push the button of the external door handle to release it from the recess. (b) Move the external door handle to the OPEN position and push the bulk cargo-compartment door in. (c) Move the internal or the external door handle to the LOCKED position and examine the lateral barrel locks. NOTE: The barrel locks turn until their slots cannot engage with the latch spigots at the door frame. (d) Move the applicable door handle back to the OPEN position. (e) Pull the door down into the door opening and move the external door handle to the LOCKED position. NOTE: The bulk cargo-compartment door is aligned with the fuselage. (f)

Push the external door handle into its recess.

Subtask 52-70-00-970-051-A D.

Entry in the log book. (1) Make an entry in the aircraft log book to record that: · the BULK indication is defective on the lower ECAM DU · the bulk cargo-compartment door is closed and correctly locked.

** ON A/C 225-225 Subtask 52-70-00-210-051-B C.

Not Applicable

Subtask 52-70-00-970-051-B D.

Not Applicable

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-004-A - Visual Check to Make Sure that the Avionics-Compartment Access Doors are Correctly Closed

** ON A/C ALL TASK 52-70-00-040-004-A Visual Check to Make Sure that the Avionics-Compartment Access Doors are Correctly Closed 1.

Reason for the Job MMEL 52-07-06A Avionics Compartment Access Door Indication on the DOOR/OXY SD page

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

Work Zones and Access Panels ZONE/ACCESS 811, 812, 822, 824

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 52-41-00-410-002-A). 3.

DESIGNATION Close the Avionics Compartment Doors after Access

Job Set-up Subtask 52-70-00-010-054-A A.

Get Access (1) Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the applicable avionicscompartment access door 811 or 812 or 822 or 824. (2) Manually open the related avionics-compartment access door 811 or 812 or 822 or 824.

4.

Procedure Subtask 52-70-00-210-056-A A.

Visual Check to Make Sure that the Avionics-Compartment Access Door is Correctly Closed (1) With the door open, move the handle so as to operate the locking system. (2) Make sure that the locks get out of their housing and operate correctly. (3) Put the handle in the door open position. (4) Close the avionics-compartment access door and lock it.

Subtask 52-70-00-970-056-A B.

Entry in the Log Book. (1) Make an entry in the aircraft log book to record that: · the AVIONICS indication is defective on the lower ECAM DU · the avionics-compartment access door(s) are closed and locked.

5.

Close-up Subtask 52-70-00-410-054-A

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-004-A - Visual Check to Make Sure that the Avionics-Compartment Access Doors are Correctly Closed

A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Manually close the concerned avionics-compartment access door 811 or 812 or 822 or 824 (Ref. AMM TASK 52-41-00-410-002) . (3) Remove the access platform(s).

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-010-A - Visual Check of the Emergency Exit Closure and the Slide Arming

** ON A/C ALL TASK 52-70-00-040-010-A Visual Check of the Emergency Exit Closure and the Slide Arming Task Summary MMEL or CDL Ref MMEL 52-07-03A MMEL 52-07-03B MMEL 52-07-03C MMEL 52-07-03D

Access YES YES YES YES

Test YES YES YES YES

Specific Tools NO NO NO NO

Mhr 00.3 00.3 00.3 00.3

1.

Reason for the Job MMEL 52-07-03A Cabin Overwing Exit Permanently Indicated Open on the DOOR/OXY SD page MMEL 52-07-03B Cabin Overwing Exit Permanently Indicated Open on the DOOR/OXY SD page MMEL 52-07-03C Cabin Overwing Exit Permanently Indicated Open on the DOOR/OXY SD page MMEL 52-07-03D Cabin Overwing Exit Permanently Indicated Open on the DOOR/OXY SD page

2

Job Set-up Information A.

E/T 00.3 00.3 00.3 00.3

Nb Men 1 1 1 1

Fixtures, Tools, Test and Support Equipment REFERENCE

QTY DESIGNATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 No specific 1 WRENCH - HEXAGONAL ** ON A/C ALL B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 831, 841 ** ON A/C ALL C. Referenced Information REFERENCE (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A).

DESIGNATION EIS Start Procedure EIS Stop Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 (Ref. 52-10-00-010-001-A). Opening of the Passenger/Crew Door (Ref. 52-10-00-410-001-A). Closing of the Passenger/Crew Door

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 17

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-010-A - Visual Check of the Emergency Exit Closure and the Slide Arming REFERENCE (Ref. 52-21-11-000-001-A). (Ref. 52-21-11-400-001-A). ** ON A/C 401-450 (Ref. 52-22-00-010-802-A).

DESIGNATION Removal of the Emergency Exit Hatch Installation of the Emergency Exit Hatch

Opening of the Overwing Emergency-Exit Door from the Passenger Compartment

** ON A/C ALL ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 EMERGENCY EXIT Closure ** ON A/C 401-408, 416-450 Emergency Overwing Door - Slide Release Mechanism ** ON A/C 409-415 Emergency Overwing Door - Slide Release Mechanism ** ON A/C 401-408, 416-450 Emergency Overwing Door - Visual Indicator SHEET 1 ** ON A/C 409-415 Emergency Overwing Door - Visual Indicator SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 17

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-010-A - Visual Check of the Emergency Exit Closure and the Slide Arming

Z844

A

A

Z834

A

A

B

FR41 FR39

C

1

2

B

C

4 3

N_MM_527000_4_AEM0_01_01

Figure 52-70-00-991-00200-00-A / SHEET 1/2 - EMERGENCY EXIT Closure ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 17

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-010-A - Visual Check of the Emergency Exit Closure and the Slide Arming

SECTION

A-A

FUSELAGE CONTOUR

5

6

HATCH CONTOUR

N_MM_527000_4_AEM0_02_01

Figure 52-70-00-991-00200-00-A / SHEET 2/2 - EMERGENCY EXIT Closure ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 17

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-010-A - Visual Check of the Emergency Exit Closure and the Slide Arming

B A

Z834 (Z844) Z833 (Z843)

C D

1

A

01

NOTE: 01 LH SHOWN, RH SYMMETRICAL N_MM_527000_4_AJM0_01_00

Figure 52-70-00-991-00200-00-E / SHEET 1/3 - Emergency Overwing Door - Slide Release Mechanism ** ON A/C 401-408, 416-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 17

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-010-A - Visual Check of the Emergency Exit Closure and the Slide Arming

2

E F

1

3

B

(3) 01

4

(2)

(1) 5

C

02

NOTE: 01 LH SHOWN, RH SYMMETRICAL 02

STEPS (1), (2) AND (3) ARE THE NECESSARY STEPS TO DISARM THE SLIDE RELEASE MECHANISM N_MM_527000_4_AJM0_02_00

Figure 52-70-00-991-00200-00-E / SHEET 2/3 - Emergency Overwing Door - Slide Release Mechanism ** ON A/C 401-408, 416-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 17

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-010-A - Visual Check of the Emergency Exit Closure and the Slide Arming

3 4 (4)

(6)

(5) 5

D

03

3 4 (3) (2) (1) 5

E

02

4 (4) (5) (6) 3

5

F

03

NOTE: 02

STEPS (1), (2) AND (3) ARE THE NECESSARY STEPS TO DISARM THE SLIDE RELEASE MECHANISM

03

STEPS (4), (5) AND (6) ARE THE NECESSARY STEPS TO ARM THE SLIDE RELEASE MECHANISM N_MM_527000_4_AJM0_03_00

Figure 52-70-00-991-00200-00-E / SHEET 3/3 - Emergency Overwing Door - Slide Release Mechanism ** ON A/C 401-408, 416-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 17

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-010-A - Visual Check of the Emergency Exit Closure and the Slide Arming

A

Z833 (Z843)

2

B C

1

A

01

NOTE: 01 LH SHOWN, RH SYMMETRICAL N_MM_527000_4_AMM0_01_00

Figure 52-70-00-991-00200-00-G / SHEET 1/2 - Emergency Overwing Door - Slide Release Mechanism ** ON A/C 409-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 17

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-010-A - Visual Check of the Emergency Exit Closure and the Slide Arming

3 (3) 4

(2)

(1) 5

B

02

3 4 (4)

(6)

(5) 5

C

03

NOTE: 02

STEPS (1), (2) AND (3) ARE THE NECESSARY STEPS TO DISARM THE SLIDE RELEASE MECHANISM

03

STEPS (4), (5) AND (6) ARE THE NECESSARY STEPS TO ARM THE SLIDE RELEASE MECHANISM N_MM_527000_4_AMM0_02_00

Figure 52-70-00-991-00200-00-G / SHEET 2/2 - Emergency Overwing Door - Slide Release Mechanism ** ON A/C 409-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 17

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-010-A - Visual Check of the Emergency Exit Closure and the Slide Arming

A

Z844 Z843

Z834 Z833

B

A

01

B

22

22

21

23 23 23

B FWD

NOTE: 01 LH SHOWN, RH SYMMETRICAL

N_MM_527000_4_AJN0_01_00

Figure 52-70-00-991-00500-00-A / SHEET 1/1 - Emergency Overwing Door - Visual Indicator ** ON A/C 401-408, 416-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 17

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-010-A - Visual Check of the Emergency Exit Closure and the Slide Arming

A

Z844 Z843

Z834 Z833

B

A

22

01

22

21

23 23 23

B FWD

NOTE: 01 LH SHOWN, RH SYMMETRICAL

N_MM_527000_4_AMN0_01_00

Figure 52-70-00-991-00500-00-C / SHEET 1/1 - Emergency Overwing Door - Visual Indicator ** ON A/C 409-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 17

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-010-A - Visual Check of the Emergency Exit Closure and the Slide Arming

3.

Job Set-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 52-70-00-010-064-A A.

Get Access (1) Put the access platform in position at the applicable FWD passenger/crew door 831 or 841. (2) Open the applicable passenger/crew door (Ref. AMM TASK 52-10-00-010-001) . (3) Do an EIS start procedure (Ref. AMM TASK 31-60-00-860-001) .

** ON A/C 401-450 Subtask 52-70-00-010-064-C A.

Aircraft Maintenance Configuration (1) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) .

** ON A/C ALL 4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 (Ref. Fig. EMERGENCY EXIT Closure) ** ON A/C 401-408, 416-450 (Ref. Fig. Emergency Overwing Door - Slide Release Mechanism) ** ON A/C 409-415 (Ref. Fig. Emergency Overwing Door - Slide Release Mechanism) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 52-70-00-210-069-A A.

Visual Check to Make Sure that the Emergency Exit is Correctly Closed and SLIDE ARMED (1) Visual check to make sure that the applicable emergency exit hatch is correctly closed. (a) Pull down the cover flap (3) from the hatch (4) and remove it. (b) Examine the locking hooks (6) to make sure that they are engaged with the upper roller fittings (5) in the hatch frame. (c) Install the cover flap (3) on the hatch (4) and push it against the hatch (4). (d) On the ECAM control panel, push the DOOR key: · On the lower ECAM DU, the DOOR/OXY page comes into view. (e) If the EMER EXIT indication stays on on the lower ECAM DU, examine the hatch (4) position from the outboard side. NOTE: The hatch (4) must be flush with the fuselage. (f)

If the hatch position is not correct, remove the hatch (4) (Ref. AMM TASK 52-21-11-000-001) and install it again (Ref. AMM TASK 52-21-11-400-001) .

(2) Visual check to make sure that the applicable emergency exit hatch is in the ARMED mode (a) Make sure that the escape-slide release mechanism is not in the MAINTENANCE mode. 1

Pull down the cover flap (3) from the hatch (4) and remove it.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 12 of 17

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-010-A - Visual Check of the Emergency Exit Closure and the Slide Arming

2

Make sure that the latch pin (1) is not in the DISARMED position (latch pin retracted).

(b) If the latch pin (1) is in the DISARMED position (escape-slide release mechanism in MAINTENANCE mode), arm the slide release mechanism as follows: 1

With a WRENCH - HEXAGONAL, push the latch pin (1) against the spring (2).

2

Turn the head of the latch pin (1) a quarter turn clockwise to extend the latch pin (1).

3

Make sure that the white SLIDE ARMED indicator light, located in the cabin lining near the emergency exits, is on.

(c) Install the cover flap (3) on the hatch (4) and push it against the hatch (4). NOTE: The white SLIDE ARMED indicator light goes off. (d) If the latch pin (1) is in the extended position, make sure that the indication is correct on the lower ECAM DU. (3) Entry in the log book (a) If the indication is not correct, make an entry in the aircraft log book to record that: · The SLIDE indication of the hatch (4) is defective on the lower ECAM DU. · The hatch is in the ARMED mode. · The EMER EXIT indication is defective on the lower ECAM DU. · The hatch (4) is correctly installed and locked. ** ON A/C 401-450 Subtask 52-70-00-210-069-C A.

Visual Check of the Emergency Exit Closure and the Slide Arming NOTE: This procedure is applicable only to MMEL 52-07-03A. (1) Do a visual check to make sure that the applicable emergency overwing door is correctly closed:

** ON A/C 401-408, 416-450 (Ref. Fig. Emergency Overwing Door - Visual Indicator SHEET 1) ** ON A/C 409-415 (Ref. Fig. Emergency Overwing Door - Visual Indicator SHEET 1) ** ON A/C 401-450 (a) On the visual lock indicator (21): 1

Make sure that the black arrows (23) are aligned with the black lines (22) from the green segment.

(b) On the lower ECAM DU, on the DOOR/OXY page: 1

Push the DOOR key.

2

Make sure that the DOOR/OXY page comes into view.

3

If the "EMER EXIT" message stays on, examine the emergency overwing-door position from the outboard side. NOTE: The emergency overwing door must be flush with the fuselage.

(c) If the position of the emergency overwing door is not correct: 1

Close the emergency overwing door (Ref. AMM TASK 52-22-00-010-802) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 13 of 17

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-010-A - Visual Check of the Emergency Exit Closure and the Slide Arming

(2) Do a visual check to make sure that the applicable emergency overwing door is in the ARMED mode: ** ON A/C 401-408, 416-450 (Ref. Fig. Emergency Overwing Door - Slide Release Mechanism) ** ON A/C 409-415 (Ref. Fig. Emergency Overwing Door - Slide Release Mechanism) ** ON A/C 401-450 (a) Remove the handle cover (1). (b) If the lever (3) is behind the disarm bracket (4), arm the slide release mechanism: 1

2

On the forward left emergency-overwing-door or the aft right emergency-overwing-door: a

Pull the slide release shaft (5) to the right side to release it from the disarm bracket (4).

b

Turn the slide release shaft (5) counterclockwise and push it to the left side.

On the aft left emergency-overwing-door or the forward right emergency-overwing-door: a

Pull the slide release shaft (5) to the left side to release it from the disarm bracket (4).

b

Turn the slide release shaft (5) clockwise and push it to the right side.

(c) Make sure that the SLIDE ARMED indicator light (2) comes on. (d) Install the handle cover (1). (e) The SLIDE ARMED indicator light (2) goes off. (f)

On the lower ECAM DU, on the DOOR/OXY page: 1

Push the DOOR key.

2

Make sure that the DOOR/OXY page comes into view.

3

Make sure that the message SLIDE in white color is shown for the applicable overwing doors.

(3) Make an entry in the logbook. Subtask 52-70-00-210-071-A B.

Visual Check of the Emergency Exit Closure and the Slide Arming NOTE: This procedure is applicable only to MMEL 52-07-03B and MMEL 52-07-03C. (1) Do a visual check to make sure that the applicable emergency overwing door is correctly closed:

** ON A/C 401-408, 416-450 (Ref. Fig. Emergency Overwing Door - Visual Indicator SHEET 1) ** ON A/C 409-415 (Ref. Fig. Emergency Overwing Door - Visual Indicator SHEET 1) ** ON A/C 401-450 (a) On the visual lock indicator (21): 1

Make sure that the black arrows (23) are aligned with the black lines (22) from the green segment.

(b) On the lower ECAM DU, on the DOOR/OXY page: 1

Push the DOOR key.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 14 of 17

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-010-A - Visual Check of the Emergency Exit Closure and the Slide Arming

2

Make sure that the DOOR/OXY page comes into view.

3

If the "EMER EXIT" message stays on, examine the emergency overwing-door position from the outboard side. NOTE: The emergency overwing door must be flush with the fuselage.

(c) If the position of the emergency overwing door is not correct: 1

Close the emergency overwing door (Ref. AMM TASK 52-22-00-010-802) .

(2) Do a visual check to make sure that the applicable emergency overwing door is in the ARMED mode: ** ON A/C 401-408, 416-450 (Ref. Fig. Emergency Overwing Door - Slide Release Mechanism) ** ON A/C 409-415 (Ref. Fig. Emergency Overwing Door - Slide Release Mechanism) ** ON A/C 401-450 (a) Remove the handle cover (1). (b) If the lever (3) is behind the disarm bracket (4), arm the slide release mechanism: 1

2

On the forward left emergency-overwing-door or the aft right emergency-overwing-door: a

Pull the slide release shaft (5) to the right side to release it from the disarm bracket (4).

b

Turn the slide release shaft (5) counterclockwise and push it to the left side.

On the aft left emergency-overwing-door or the forward right emergency-overwing-door: a

Pull the slide release shaft (5) to the left side to release it from the disarm bracket (4).

b

Turn the slide release shaft (5) clockwise and push it to the right side.

(c) Make sure that the SLIDE ARMED indicator light (2) comes on. (d) Install the handle cover (1). NOTE: The SLIDE ARMED indicator light (2) can stay on after the installation of the handle cover (1). (3) Make an entry in the logbook. Subtask 52-70-00-210-072-A C.

Visual Check of the Emergency Exit Closure and the Slide Disarming NOTE: This procedure is applicable only to MMEL 52-07-03D. (1) Do a visual check to make sure that the applicable emergency overwing door is correctly closed:

** ON A/C 401-408, 416-450 (Ref. Fig. Emergency Overwing Door - Visual Indicator SHEET 1) ** ON A/C 409-415 (Ref. Fig. Emergency Overwing Door - Visual Indicator SHEET 1) ** ON A/C 401-450 (a) On the visual lock indicator (21):

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 15 of 17

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-010-A - Visual Check of the Emergency Exit Closure and the Slide Arming

1

Make sure that the black arrows (23) are aligned with the black lines (22) from the green segment.

(b) On the lower ECAM DU, on the DOOR/OXY page: 1

Push the DOOR key.

2

Make sure that the DOOR/OXY page comes into view.

3

If the "EMER EXIT" message stays on, examine the emergency overwing-door position from the outboard side. NOTE: The emergency overwing door must be flush with the fuselage.

(c) If the position of the emergency overwing door is not correct: 1

Close the emergency overwing door (Ref. AMM TASK 52-22-00-010-802) .

(2) Do a visual check to make sure that the two emergency overwing doors on the same side are in the DISARMED mode: ** ON A/C 401-408, 416-450 (Ref. Fig. Emergency Overwing Door - Slide Release Mechanism) ** ON A/C 409-415 (Ref. Fig. Emergency Overwing Door - Slide Release Mechanism) ** ON A/C 401-450 (a) Remove the handle cover (1) of the two emergency overwing doors on the same side. (b) Disarm the slide release mechanism of the two emergency overwing doors on the same side: 1

On the forward left emergency-overwing-door or the aft right emergency-overwing-door: a

2

Pull the slide release shaft (5) to the right side, turn it clockwise and engage it behind the disarm bracket (4).

On the aft left emergency-overwing-door or the forward right emergency-overwing-door: a

Pull the slide release shaft (5) to the left side, turn it counterclockwise and engage it behind the disarm bracket (4).

(c) Install the handle cover (1) of the two emergency overwing doors on the same side. NOTE: The SLIDE ARMED indicator light (2) can stay on after the installation of the handle cover (1). (d) Put a PLACARD in position on the two disarmed emergency overwing doors on the same side to tell people not to use the two doors in an emergency situation. (3) Make an entry in the logbook. ** ON A/C ALL 5.

Close-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 52-70-00-410-064-A A.

Close Access (1) Remove all the ground support equipment, maintenance equipment, standard and special tools and all other items.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 16 of 17

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-010-A - Visual Check of the Emergency Exit Closure and the Slide Arming

(2) Do an EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (3) Close the applicable passenger/crew door 831 or 841 (Ref. AMM TASK 52-10-00-410-001) . (4) Remove the access platform(s). ** ON A/C 401-450 Subtask 52-70-00-410-064-C A.

Aircraft Maintenance Configuration (1) Make sure that the work area is clean and clear of tools and other items. (2) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 17 of 17

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-011-A - Visual Check of the Emergency Exit Closure and the Slide Arming

** ON A/C ALL TASK 52-70-00-040-011-A Visual Check of the Emergency Exit Closure and the Slide Arming Task Summary MMEL or CDL Ref MMEL 52-07-04A MMEL 52-07-04B

Access YES YES

Test YES YES

Specific Tools NO NO

Mhr 00.3 00.3

1.

Reason for the Job MMEL 52-07-04A Cabin Overwing Exit Permanently Indicated Closed on the DOOR/OXY SD page MMEL 52-07-04B Cabin Overwing Exit Permanently Indicated Closed on the DOOR/OXY SD page

2

Job Set-up Information A.

E/T 00.3 00.3

Nb Men 1 1

Fixtures, Tools, Test and Support Equipment REFERENCE

QTY DESIGNATION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 No specific 1 WRENCH - HEXAGONAL ** ON A/C ALL B.

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 831, 841 ** ON A/C ALL C. Referenced Information REFERENCE (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A).

DESIGNATION EIS Start Procedure EIS Stop Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 (Ref. 52-10-00-010-001-A). Opening of the Passenger/Crew Door (Ref. 52-10-00-410-001-A). Closing of the Passenger/Crew Door (Ref. 52-21-11-000-001-A). Removal of the Emergency Exit Hatch (Ref. 52-21-11-400-001-A). Installation of the Emergency Exit Hatch ** ON A/C 401-450 (Ref. 52-22-00-010-802-A).

Opening of the Overwing Emergency-Exit Door from the Passenger Compartment

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 15

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-011-A - Visual Check of the Emergency Exit Closure and the Slide Arming REFERENCE

DESIGNATION

** ON A/C ALL ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 EMERGENCY EXIT Closure ** ON A/C 401-408, 416-450 Emergency Overwing Door - Slide Release Mechanism ** ON A/C 409-415 Emergency Overwing Door - Slide Release Mechanism ** ON A/C 401-408, 416-450 Emergency Overwing Door - Visual Indicator SHEET 1 ** ON A/C 409-415 Emergency Overwing Door - Visual Indicator SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 15

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-011-A - Visual Check of the Emergency Exit Closure and the Slide Arming

Z844

A

A

Z834

A

A

B

FR41 FR39

C

1

2

B

C

4 3

N_MM_527000_4_AEM0_01_01

Figure 52-70-00-991-00200-00-A / SHEET 1/2 - EMERGENCY EXIT Closure ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 15

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-011-A - Visual Check of the Emergency Exit Closure and the Slide Arming

SECTION

A-A

FUSELAGE CONTOUR

5

6

HATCH CONTOUR

N_MM_527000_4_AEM0_02_01

Figure 52-70-00-991-00200-00-A / SHEET 2/2 - EMERGENCY EXIT Closure ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 15

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-011-A - Visual Check of the Emergency Exit Closure and the Slide Arming

B A

Z834 (Z844) Z833 (Z843)

C D

1

A

01

NOTE: 01 LH SHOWN, RH SYMMETRICAL N_MM_527000_4_AJM0_01_00

Figure 52-70-00-991-00200-00-E / SHEET 1/3 - Emergency Overwing Door - Slide Release Mechanism ** ON A/C 401-408, 416-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 15

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-011-A - Visual Check of the Emergency Exit Closure and the Slide Arming

2

E F

1

3

B

(3) 01

4

(2)

(1) 5

C

02

NOTE: 01 LH SHOWN, RH SYMMETRICAL 02

STEPS (1), (2) AND (3) ARE THE NECESSARY STEPS TO DISARM THE SLIDE RELEASE MECHANISM N_MM_527000_4_AJM0_02_00

Figure 52-70-00-991-00200-00-E / SHEET 2/3 - Emergency Overwing Door - Slide Release Mechanism ** ON A/C 401-408, 416-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 15

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-011-A - Visual Check of the Emergency Exit Closure and the Slide Arming

3 4 (4)

(6)

(5) 5

D

03

3 4 (3) (2) (1) 5

E

02

4 (4) (5) (6) 3

5

F

03

NOTE: 02

STEPS (1), (2) AND (3) ARE THE NECESSARY STEPS TO DISARM THE SLIDE RELEASE MECHANISM

03

STEPS (4), (5) AND (6) ARE THE NECESSARY STEPS TO ARM THE SLIDE RELEASE MECHANISM N_MM_527000_4_AJM0_03_00

Figure 52-70-00-991-00200-00-E / SHEET 3/3 - Emergency Overwing Door - Slide Release Mechanism ** ON A/C 401-408, 416-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 15

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-011-A - Visual Check of the Emergency Exit Closure and the Slide Arming

A

Z833 (Z843)

2

B C

1

A

01

NOTE: 01 LH SHOWN, RH SYMMETRICAL N_MM_527000_4_AMM0_01_00

Figure 52-70-00-991-00200-00-G / SHEET 1/2 - Emergency Overwing Door - Slide Release Mechanism ** ON A/C 409-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 15

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-011-A - Visual Check of the Emergency Exit Closure and the Slide Arming

3 (3) 4

(2)

(1) 5

B

02

3 4 (4)

(6)

(5) 5

C

03

NOTE: 02

STEPS (1), (2) AND (3) ARE THE NECESSARY STEPS TO DISARM THE SLIDE RELEASE MECHANISM

03

STEPS (4), (5) AND (6) ARE THE NECESSARY STEPS TO ARM THE SLIDE RELEASE MECHANISM N_MM_527000_4_AMM0_02_00

Figure 52-70-00-991-00200-00-G / SHEET 2/2 - Emergency Overwing Door - Slide Release Mechanism ** ON A/C 409-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 15

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-011-A - Visual Check of the Emergency Exit Closure and the Slide Arming

A

Z844 Z843

Z834 Z833

B

A

01

B

22

22

21

23 23 23

B FWD

NOTE: 01 LH SHOWN, RH SYMMETRICAL

N_MM_527000_4_AJN0_01_00

Figure 52-70-00-991-00500-00-A / SHEET 1/1 - Emergency Overwing Door - Visual Indicator ** ON A/C 401-408, 416-450 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 15

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-011-A - Visual Check of the Emergency Exit Closure and the Slide Arming

A

Z844 Z843

Z834 Z833

B

A

22

01

22

21

23 23 23

B FWD

NOTE: 01 LH SHOWN, RH SYMMETRICAL

N_MM_527000_4_AMN0_01_00

Figure 52-70-00-991-00500-00-C / SHEET 1/1 - Emergency Overwing Door - Visual Indicator ** ON A/C 409-415 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 15

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-011-A - Visual Check of the Emergency Exit Closure and the Slide Arming

3.

Job Set-up

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 52-70-00-010-065-A A.

Get Access (1) Put the access platform in position at the applicable FWD passenger/crew door 831 or 841. (2) Open the applicable passenger/crew door (Ref. AMM TASK 52-10-00-010-001) . (3) Do an EIS start procedure (Ref. AMM TASK 31-60-00-860-001) .

** ON A/C 401-450 Subtask 52-70-00-010-065-C A.

Aircraft Maintenance Configuration (1) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001) .

** ON A/C ALL 4.

Procedure

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 (Ref. Fig. EMERGENCY EXIT Closure) ** ON A/C 401-408, 416-450 (Ref. Fig. Emergency Overwing Door - Slide Release Mechanism) ** ON A/C 409-415 (Ref. Fig. Emergency Overwing Door - Slide Release Mechanism) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 52-70-00-210-070-A A.

Visual Check to Make Sure that the Emergency Exit is Correctly Closed (1) Visual check to make sure that the applicable emergency exit hatch is correctly closed. (a) Pull down the cover flap (3) from the hatch (4) and remove it. (b) Examine the locking hooks (6) to make sure that they are engaged with the upper roller fittings (5) in the hatch frame. (c) Install the cover flap (3) on the hatch (4) and push it against the hatch (4). (d) On the ECAM control panel, push the DOOR key: · On the lower ECAM DU, the DOOR/OXY page comes into view. (e) If the EMER EXIT indication stays on on the lower ECAM DU, examine the hatch position from the outboard side. NOTE: The hatch (4) must be flush with the fuselage. (f)

If the hatch position is not correct, remove the hatch (4) (Ref. AMM TASK 52-21-11-000-001) and install it again (Ref. AMM TASK 52-21-11-400-001) .

(2) Visual check to make sure that the applicable emergency exit hatch is in the ARMED mode (a) Make sure that the escape-slide release mechanism is not in the MAINTENANCE mode. 1

Pull down the cover flap (3) from the hatch (4) and remove it.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 12 of 15

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-011-A - Visual Check of the Emergency Exit Closure and the Slide Arming

2

Make sure that the latch pin (1) is not in the DISARMED position (latch pin retracted).

(b) If the latch pin (1) is in the DISARMED poisition (escape-slide release mechanism in MAINTENANCE mode), arm the slide release mechanism as follows: 1

With a WRENCH - HEXAGONAL, push the latch pin (1) against the spring (2).

2

Turn the head of the latch pin (1) a quarter turn clockwise to extend the latch pin (1).

3

Make sure that the white SLIDE ARMED white indicator light, located in the cabin lining near the emergency exits, is on.

(c) Install the cover flap (3) on the hatch (4) and push it against the hatch (4). NOTE: The white SLIDE ARMED indicator light goes off. (d) If the latch pin (1) is the extended position, make sure that the indication is correct on the lower ECAM DU. (3) Entry in the log book (a) If the indication is not correct, make an entry in the aircraft log book to record that: · The SLIDE indication of the hatch is defective on the lower ECAM DU. · The hatch (4) is in the ARMED mode. · The EMER EXIT indication is defective on the lower ECAM DU. · The hatch (4) is correctly installed and locked. ** ON A/C 401-450 Subtask 52-70-00-210-070-C A.

Visual Check of the Emergency Exit Closure and the Slide Arming NOTE: This procedure is applicable only to MMEL 52-07-04A. (1) Do a visual check to make sure that the applicable emergency overwing door is correctly closed:

** ON A/C 401-408, 416-450 (Ref. Fig. Emergency Overwing Door - Visual Indicator SHEET 1) ** ON A/C 409-415 (Ref. Fig. Emergency Overwing Door - Visual Indicator SHEET 1) ** ON A/C 401-450 (a) On the visual lock indicator (21): 1

Make sure that the black arrows (23) are aligned with the black lines (22) from the green segment.

2

If the black arrows (23) are not aligned with the black lines (22) from the green segment, then close the emergency overwing door (Ref. AMM TASK 52-22-00-010-802) .

3

Examine the emergency overwing door position from the outboard side.

4

Make sure that the emergency overwing door is flush with the fuselage.

(2) Do a visual check to make sure that the applicable emergency overwing door is in the ARMED mode: ** ON A/C 401-408, 416-450 (Ref. Fig. Emergency Overwing Door - Slide Release Mechanism) ** ON A/C 409-415

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 13 of 15

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-011-A - Visual Check of the Emergency Exit Closure and the Slide Arming (Ref. Fig. Emergency Overwing Door - Slide Release Mechanism) ** ON A/C 401-450 (a) Remove the handle cover (1). (b) If the lever (3) is behind the disarm bracket (4), arm the slide release mechanism: 1

2

On the forward left emergency-overwing-door: a

Pull the slide release shaft (5) to the right side to release it from the disarm bracket (4).

b

Turn the slide release shaft (5) counterclockwise and push it to the left side.

On the forward right emergency-overwing-door: a

Pull the slide release shaft (5) to the left side to release it from the disarm bracket (4).

b

Turn the slide release shaft (5) clockwise and push it to the right side.

(c) Install the handle cover (1). NOTE: The SLIDE ARMED indicator light (2) can stay on after the installation of the handle cover (1). (3) Make an entry in the logbook. Subtask 52-70-00-210-073-A B.

Visual Check of the Emergency Exit Closure NOTE: This procedure is applicable only to MMEL 52-07-04B. (1) Do a visual check to make sure that the two applicable emergency overwing doors on the same side are correctly closed:

** ON A/C 401-408, 416-450 (Ref. Fig. Emergency Overwing Door - Visual Indicator SHEET 1) ** ON A/C 409-415 (Ref. Fig. Emergency Overwing Door - Visual Indicator SHEET 1) ** ON A/C 401-450 (a) On the visual lock indicator (21): 1

Make sure that the black arrows (23) are aligned with the black lines (22) from the green segment.

2

If the black arrows (23) are not aligned with the black lines (22) from the green segment, then close the emergency overwing door (Ref. AMM TASK 52-22-00-010-802) .

3

Examine the emergency overwing door position from the outboard side.

4

Make sure that the emergency overwing door is flush with the fuselage.

(b) Put a PLACARD in position on the two emergency overwing doors on the same side to tell people not to use the two doors in an emergency situation. (2) Make an entry in the logbook. ** ON A/C ALL 5.

Close-up

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 14 of 15

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-70-00-040-011-A - Visual Check of the Emergency Exit Closure and the Slide Arming

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Subtask 52-70-00-410-065-A A.

Close Access (1) Remove all the ground support equipment, maintenance equipment, standard and special tools and all other items. (2) Do an EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) . (3) Close the applicable passenger/crew door 831 or 841 (Ref. AMM TASK 52-10-00-410-001) . (4) Remove the access platform(s).

** ON A/C 401-450 Subtask 52-70-00-410-065-C A.

Aircraft Maintenance Configuration (1) Make sure that the work area is clean and clear of tools and other items. (2) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 15 of 15

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 56-10-00-040-001-A - Deactivation of the Front Windshield

** ON A/C ALL TASK 56-10-00-040-001-A Deactivation of the Front Windshield WARNING:

MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER RADAR ARE OPENED, SAFETIED AND TAGGED.

FIN : 3DG1 , 3DG2 1.

Reason for the Job MMEL 56-10-01A Front Windshield MMEL 56-10-01B Front Windshield MMEL 56-10-01C Front Windshield MMEL 56-10-01D Front Windshield

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION AR ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE AR SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS 210 211 212

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD COCKPIT COCKPIT

C. Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A). (Ref. 56-11-11-200-001-A). 3.

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power Inspection of the Windshields

Job Set-up Subtask 56-10-00-861-050-A A.

Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Subtask 56-10-00-941-052-A B.

Get Access

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 56-10-00-040-001-A - Deactivation of the Front Windshield

(1) Put an ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at the zone 210. Subtask 56-10-00-865-058-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL 121VU

DESIGNATION COM NAV/RADAR/1

FIN 5SQ1

LOCATION K13

** ON A/C 205-205, 209-209, 215-216, 218-218, 231-232, 236-237, 241-242, 244-250

4.

EMB SB 34-1221 for A/C 218-218 121VU COM NAV/RADAR/2

5SQ2

K14

** ON A/C ALL 122VU 122VU 122VU 122VU 123VU 123VU

4DG2 5DG2 4DG1 5DG1 1DG1 1DG2

W14 W13 X14 X13 AF10 AF03

ANTI ICE/WINDOWS/R ANTI ICE/WHC/2 ANTI ICE/WINDOWS/L ANTI ICE/WHC/1 ANTI ICE/L/WHSLD ANTI ICE/R/WHSLD

Procedure Subtask 56-10-00-220-052-A A.

Deactivation of the Windshield (1) Do an inspection of the windshield for: · scratches, cracks, chips, bubbles, delamination, discoloration, interlayer microflakes, transparency, burn spots, burning and damage on the soft liner (self-healing liner) (Ref. AMM TASK 56-11-11200-001) . NOTE: The damage on the soft liner is only applicable to the windshield that has a soft liner on the inner surface (SGS (formerly SPS) supplier, P/N SPSA320...).

5.

Close-up Subtask 56-10-00-865-059-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU

DESIGNATION COM NAV/RADAR/1

FIN 5SQ1

LOCATION K13

** ON A/C 205-205, 209-209, 215-216, 218-218, 231-232, 236-237, 241-242, 244-250 EMB SB 34-1221 for A/C 218-218 121VU COM NAV/RADAR/2

5SQ2

K14

** ON A/C ALL 122VU 122VU 122VU 122VU

4DG2 5DG2 4DG1 5DG1

W14 W13 X14 X13

ANTI ICE/WINDOWS/R ANTI ICE/WHC/2 ANTI ICE/WINDOWS/L ANTI ICE/WHC/1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 56-10-00-040-001-A - Deactivation of the Front Windshield

PANEL 123VU 123VU

DESIGNATION ANTI ICE/L/WHSLD ANTI ICE/R/WHSLD

FIN 1DG1 1DG2

LOCATION AF10 AF03

Subtask 56-10-00-040-050-A B.

Deactivation of the Windshield De-Icing (1) If the windshield outer ply has cracks or if the windshield has burn spots that are equal to or more than the permitted limit: (a) Open, safety and tag this(these) circuit breaker(s): · for the left side: 1DG1 · for the right side: 1DG2. (2) Make an entry in the aircraft technical logbook.

Subtask 56-10-00-942-052-A C.

Close Access (1) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (2) Remove the access platform(s).

Subtask 56-10-00-862-052-A D.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 56-10-00-040-002-A - Deactivation of the Lateral Fixed or Sliding Window

** ON A/C ALL TASK 56-10-00-040-002-A Deactivation of the Lateral Fixed or Sliding Window WARNING:

MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER RADAR ARE OPENED, SAFETIED AND TAGGED.

FIN : 7DG1 , 7DG2 , 8DG1 , 8DG2 1.

Reason for the Job MMEL 56-10-02A Lateral Fixed/Sliding Window

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION AR ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE AR SAFETY CLIP - CIRCUIT BREAKER

Work Zones and Access Panels ZONE/ACCESS 211 212

ZONE DESCRIPTION COCKPIT COCKPIT

C. Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A). (Ref. 56-11-12-200-001-A). (Ref. 56-12-11-200-001-A). 3.

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power Inspection of the Fixed Windows Inspection of the Sliding Windows

Job Set-up Subtask 56-10-00-861-051-A A.

Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Subtask 56-10-00-941-057-A B.

Get Access (1) Put an ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at the zone 210.

Subtask 56-10-00-865-060-A C.

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

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 56-10-00-040-002-A - Deactivation of the Lateral Fixed or Sliding Window

PANEL 121VU

DESIGNATION COM NAV/RADAR/1

FIN 5SQ1

LOCATION K13

** ON A/C 205-205, 209-209, 215-216, 218-218, 231-232, 236-237, 241-242, 244-250

4.

EMB SB 34-1221 for A/C 218-218 121VU COM NAV/RADAR/2

5SQ2

K14

** ON A/C ALL 122VU 122VU 122VU 122VU 123VU 123VU

4DG2 5DG2 4DG1 5DG1 1DG1 1DG2

W14 W13 X14 X13 AF10 AF03

ANTI ICE/WINDOWS/R ANTI ICE/WHC/2 ANTI ICE/WINDOWS/L ANTI ICE/WHC/1 ANTI ICE/L/WHSLD ANTI ICE/R/WHSLD

Procedure Subtask 56-10-00-220-053-A A.

Deactivation of the Window (1) Inspection of the fixed windows (a) Do an inspection of the acrylic fixed windows for: Scratches, cracks, chips, bubbles, delamination, discoloration, crazing, burn spots and transparency (Ref. AMM TASK 56-11-12-200-001) . (b) Do an inspection of the glass fixed windows for: Scratches, cracks, chips, bubbles, interlayer microflakes, delamination, discoloration, crazing, burn spots and transparency (Ref. AMM TASK 56-11-12-200-001) . (2) Inspection of the sliding windows (a) Do an inspection of the acrylic sliding windows for: Scratches, cracks, chips, bubbles, delamination, discoloration, crazing, burn spots and transparency (Ref. AMM TASK 56-12-11-200-001) . (b) Do an inspection of the glass sliding windows for: Scratches, cracks, chips, bubbles, interlayer microflakes, delamination, discoloration, crazing, burn spots and transparency (Ref. AMM TASK 56-12-11-200-001) .

5.

Close-up Subtask 56-10-00-865-061-A A.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 121VU

DESIGNATION COM NAV/RADAR/1

FIN 5SQ1

LOCATION K13

** ON A/C 205-205, 209-209, 215-216, 218-218, 231-232, 236-237, 241-242, 244-250 EMB SB 34-1221 for A/C 218-218 121VU COM NAV/RADAR/2

5SQ2

K14

** ON A/C ALL 122VU

4DG2

W14

ANTI ICE/WINDOWS/R

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 56-10-00-040-002-A - Deactivation of the Lateral Fixed or Sliding Window

PANEL 122VU 122VU 122VU 123VU 123VU

DESIGNATION ANTI ICE/WHC/2 ANTI ICE/WINDOWS/L ANTI ICE/WHC/1 ANTI ICE/L/WHSLD ANTI ICE/R/WHSLD

FIN 5DG2 4DG1 5DG1 1DG1 1DG2

LOCATION W13 X14 X13 AF10 AF03

Subtask 56-10-00-040-051-A B.

Deactivation of the Fixed or Sliding Window De-Icing (1) If the fixed or sliding window outer ply has cracks or if the fixed or sliding window has burn spots that are less than the permitted limit: (a) Open, safety and tag this(these) circuit breaker(s): · for the left side: 4DG1 · for the right side: 4DG2. (2) Make an entry in the aircraft technical logbook.

Subtask 56-10-00-942-057-A C.

Close Access (1) Remove the ground support and maintenance equipment, the special and standard tools and all other items. (2) Remove the access platform(s).

Subtask 56-10-00-862-053-A D.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 73-29-00-040-001-A - CHECK OF THE ENG FADEC MAINTENANCE MESSAGES DISPLAYED ON ECAM STATUS PAGE

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 TASK 73-29-00-040-001-A CHECK OF THE ENG FADEC MAINTENANCE MESSAGES DISPLAYED ON ECAM STATUS PAGE 1.

Reason for the Job MMEL 70-00-01C ENG FADEC MAINTENANCE Message This taks is only applicable for CFM 56-5B /3 engines.

2

Job Set-up Information A.

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 73-29-00-710-040-B).

3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Operational Test of the FADEC on the Ground (with Engine Motoring)

Job Set-up Subtask 73-29-00-869-057-A A.

Not applicable

Subtask 73-29-00-861-058-A B. 4.

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

Procedure Subtask 73-29-00-040-050-A A.

Do an operational test of the FADEC 1 Channels A/B and FADEC 2 Channels A/B with printing of each TEST RESUSLT page (Ref. AMM TASK 73-29-00-710-040) . (1) Make sure that the TEST RESULT PAGE do not show these maintenance messages: ATA 73-21-40 73-21-40 73-21-40 73-21-40 73-21-40 73-21-40

5.

MESSAGE T12 SNSR, J10, ECU T12 SNSR, J9, ECU T12 SNSR, J10, ECU ENG1B T12 SNSR, J9, ECU ENG1A T12 SNSR, J10, ECU ENG2B T12 SNSR, J9, ECU ENG2A

CLASS FAULT 1 1 2 2 2 2

Close-up Subtask 73-29-00-862-058-A A.

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

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 73-29-00-040-001-A - CHECK OF THE ENG FADEC MAINTENANCE MESSAGES DISPLAYED ON ECAM STATUS PAGE

Subtask 73-29-00-869-058-A B.

Make an entry in the log book to record the operational test of the FADEC.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 73-30-00-040-043-A - Replacement of the Fuel Filter Cartridge

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 TASK 73-30-00-040-043-A Replacement of the Fuel Filter Cartridge

FIN : 1000EM1 , 1000EM2 1.

Reason for the Job MMEL 73-09-01A ENG 1(2) FUEL FILTER CLOG Alert

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 437AL, 438AR FOR 1000EM2 (ENGINE-2) 447AL, 448AR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 71-00-00-710-006-B). (Ref. 71-13-00-010-040-B). (Ref. 71-13-00-410-040-B). (Ref. 73-11-10-000-004-A). (Ref. 73-11-10-400-004-A). 3.

DESIGNATION Minimum Idle Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Removal of the Fuel Filter Element Installation of the Fuel Filter Element

Job Set-up Subtask 73-30-00-941-050-A A.

Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a WARNING NOTICE(S) to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead 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) to tell persons not to energize the FADEC 1(2).

Subtask 73-30-00-010-050-A B.

Open the fan cowl doors: (Ref. AMM TASK 71-13-00-010-040)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 73-30-00-040-043-A - Replacement of the Fuel Filter Cartridge

(1) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (2) FOR 1000EM2 (ENGINE-2) 447AL, 448AR 4.

Procedure Subtask 73-30-00-020-050-A A.

Replace the fuel filter cartridge (Ref. AMM TASK 73-11-10-000-004) and (Ref. AMM TASK 73-11-10400-004) .

Subtask 73-30-00-869-050-A B.

Make sure that the work area is clean and clear of tools and other items.

Subtask 73-30-00-942-050-A C.

Remove the WARNING NOTICE(S).

Subtask 73-30-00-710-050-A D.

Do this test (1) Do a minimum idle check (Ref. AMM TASK 71-00-00-710-006) . (2) Make sure that there are no fuel leaks at the filter.

5.

Close-up Subtask 73-30-00-410-050-A A.

Close the fan cowl doors: (Ref. AMM TASK 71-13-00-410-040) (1) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (2) FOR 1000EM2 (ENGINE-2) 447AL, 448AR

Subtask 73-30-00-941-051-A B.

Put a WARNING NOTICE(S) in the cockpit to tell persons that the fuel filter CLOG indication (on the lower ECAM display unit) does not operate. (1) Do an entry in the log book

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 73-30-00-040-042-A - Fuel Filter CLOG Warning - Filter Servicing

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 TASK 73-30-00-040-042-A Fuel Filter CLOG Warning - Filter Servicing

FIN : 1000EM1 , 1000EM2 Task Summary MMEL or CDL Ref MMEL 73-09-01A

Access YES

Test YES

1.

Reason for the Job MMEL 73-09-01A ENG 1(2) FUEL FILTER CLOG Alert

2

Job Set-up Information A.

Mhr 00.8

E/T 00.8

Nb Men 1

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Specific Tools NO

QTY DESIGNATION AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 437AL, 438AR FOR 1000EM2 (ENGINE-2) 451AL, 452AR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 71-00-00-710-012-B). (Ref. 71-13-00-010-010-A). (Ref. 71-13-00-410-010-A). (Ref. 73-12-42-000-010-B). (Ref. 73-12-42-400-010-B). 3.

DESIGNATION Test No.3 : Idle Leak Check Opening of the Fan Cowls 437AL(447AL),438AR(448AR) Closing of the Fan Cowls 437AL(447AL),438AR(448AR) Removal of the Fuel Filter Element Installation of the Fuel Filter Element

Job Set-up Subtask 73-30-00-941-054-A A.

Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a WARNING NOTICE(S) to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 73-30-00-040-042-A - Fuel Filter CLOG Warning - Filter Servicing

(3) On the overhead 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) to tell persons not to energize the FADEC 1(2). Subtask 73-30-00-010-052-A B.

Open the fan cowls : (Ref. AMM TASK 71-13-00-010-010) (1) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (2) FOR 1000EM2 (ENGINE-2) 451AL, 452AR

4.

Procedure Subtask 73-30-00-020-052-B A.

Remove the fuel filter element (Ref. AMM TASK 73-12-42-000-010) .

Subtask 73-30-00-420-050-B B.

Install the fuel filter element (Ref. AMM TASK 73-12-42-400-010) .

Subtask 73-30-00-860-050-A C.

Aircraft Maintenance Configuration (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the WARNING NOTICE(S).

Subtask 73-30-00-710-052-B D.

Do this test: (1) Do an idle leak check (Ref. AMM TASK 71-00-00-710-012) . (2) Make sure that there are no fuel leaks at the filter.

5.

Close-up Subtask 73-30-00-410-052-A A.

Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-010) . (1) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (2) FOR 1000EM2 (ENGINE-2) 451AL, 452AR

Subtask 73-30-00-941-055-A B.

Indicating system (1) Put a WARNING NOTICE(S) in the cockpit to tell persons that the fuel filter clog indication (on the lower ECAM DISPLAY UNIT) does not operate. (2) Make an entry in the log book to record the replacement of the filter.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 73-21-00-040-801-A - Check of the Bypass Directional Control Valve (BDCV) Counter Alert Message

** ON A/C 301-349, 351-450, 500-600 TASK 73-21-00-040-801-A Check of the Bypass Directional Control Valve (BDCV) Counter Alert Message 1.

Reason for the Job MMEL 73-09-05B ENG 1(2) HEAT SYS DEGRADED Alert

2.

Job Set-up Subtask 73-21-00-860-082-A A.

3.

Not Applicable

Procedure Subtask 73-21-00-040-058-A A.

Check for no exceedance of the Bypass Directional Control Valve (BDCV) auto-test aborted counter. (1) Make sure that maintenance messages related to Bypass Directional Control Valve (BDCV) electrical failure on dual channels is not reported in Electronic Engine Control (EEC) interactive mode fault reports on Multipurpose Control and Display Unit (MCDU). (a) Check on GROUNG report, LAST LEG REPORT or Post Flight Report (PFR).

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 73-34-00-040-802-A - Engine Fuel Filter Change

** ON A/C 301-349, 351-450, 500-600 TASK 73-34-00-040-802-A Engine Fuel Filter Change 1.

Reason for the Job MMEL 73-09-01A ENG 1(2) FUEL FILTER CLOG Alert MMEL 73-09-03B ENG 1(2) FUEL FILTER DEGRAD Alert MMEL 73-09-04B ENG 1(2) FUEL SENSOR FAULT Alert

2

Job Set-up Information A.

Referenced Information REFERENCE (Ref. 73-11-06-000-801-A). (Ref. 73-11-06-400-801-A).

3.

DESIGNATION Removal of the Fuel Filter Element Installation of the Fuel Filter Element

Job Set-up Subtask 73-34-00-000-050-A A.

4.

Remove the Fuel Filter Element (Ref. AMM TASK 73-11-06-000-801)

Procedure Subtask 73-34-00-400-050-A A.

5.

Install the new Fuel Filter Element (Ref. AMM TASK 73-11-06-400-801)

Close-up Subtask 73-34-00-860-050-A A.

Aircraft Maintenance Configuration (1) Make an entry in the logbook to record that the Fuel Filter element has been changed

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 74-31-00-040-001-A - Check of the Ignition System

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 TASK 74-31-00-040-001-A Check of the Ignition System 1.

Reason for the Job MMEL 74-09-01B ENG 1(2) IGN A(B)(A+B) FAULT Alert MMEL 74-09-01C ENG 1(2) IGN A(B)(A+B) FAULT Alert

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 74-00-00-710-043-A). (Ref. 74-00-00-710-043-A-01).

3.

DESIGNATION Operational Test of the Ignition System Operational Test of the Ignition System without CFDS

Job Set-up Subtask 74-31-00-869-052-A A.

4.

Not Applicable

Procedure Subtask 74-31-00-710-051-A A.

Do the operational test of the ignition system (Ref. AMM TASK 74-00-00-710-043) and make sure that the ignition system is operative.

Subtask 74-31-00-941-051-A B.

Safety Precautions (1) Put a WARNING NOTICE(S) in the cockpit to tell persons that the ignition warning system does not operate. (2) Make an entry in the log book.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 74-31-00-040-002-A - Check of Ignition Fault Warning

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 TASK 74-31-00-040-002-A Check of Ignition Fault Warning 1.

Reason for the Job MMEL 74-07-01A Selected Igniter Indication on the ENGINE SD page (FAA only)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER AR WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A). (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A).

3.

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power EIS Start Procedure EIS Stop Procedure

Job Set-up Subtask 74-31-00-861-051-A A.

Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Subtask 74-31-00-865-051-A B.

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

DESIGNATION 49VU ENGINE/1 AND 2/IGN/SYS A FOR FIN 1000EM1 (ENGINE-1) 121VU ENGINE/IGN/ENG1/SYS B 121VU ENGINE/IGN/ENG1/SYS A BAT FOR FIN 1000EM2 (ENGINE-2) 121VU ENGINE/IGN/ENG2/SYS B 121VU ENGINE/IGN/ENG2/SYS A BAT

FIN 1JH

LOCATION A03

3JH1 2JH1

P41 P39

3JH2 2JH2

P42 P40

Subtask 74-31-00-860-050-A C.

Aircraft Maintenance Configuration (1) On the MAINTENANCE PNL 50VU: (a) Release the ENG / FADEC GND PWR / 1(2) pushbutton switch. The ON legend of this pushbutton switch comes on. (2) On the ENG PNL 115VU, make sure that: (a) The ENG/MODE/CRANK/NORM/IGN START selector switch is set to NORM.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 74-31-00-040-002-A - Check of Ignition Fault Warning

(b) The ENG/MASTER 1(2) control switch is set to OFF. (3) On the OVERHEAD CTL & IND PNL 22VU: · Make sure that the ON legend of the ENG/MAN START/1(2) pushbutton switch is off (the pushbutton switch is released out). (4) On the HYD/FUEL PNL 40VU: (a) Make sure that the OFF legends of all the FUEL/PUMPS pushbutton switches are on (the pushbutton switches are released out). (5) Do the EIS start procedure: (Ref. AMM TASK 31-60-00-860-001) . 4.

Procedure Subtask 74-31-00-200-050-A A.

Check for ignition fault warning ACTION RESULT 1.On the ENG PNL 115VU: On the upper ECAM display unit: · Set the ENG/MODE/CRANK/NORM/IGN START · The primary engine parameters come into view. selector switch to IGN START. WAR MAKE SURE THAT THE INLET PRESNING: SURE INDICATION FOR THE STARTER VALVE IS ZERO BEFORE YOU PUSH THE ENG/MAN START/1 (2) PUSHBUTTON SWITCH. WAR MAKE SURE THAT THE INLET PRESNING: SURE INDICATION FOR THE STARTER VALVE IS ZERO BEFORE YOU PUSH THE ENG/MAN START/1 (2) PUSHBUTTON SWITCH. 2.On the OVERHEAD CTL & IND CTL 22VU: · Push the ENG/MAN START/1(2) pushbutton · The ON legend of this pushbutton switch comes switch. on. 3.On the ENG PNL 115VU: On the upper ECAM display unit, on the ENGINE · Set the ENG/MASTER 1(2) control switch to ON. page: make sure that IGN A+B FAULT warning comes into view. 4.On the OVERHEAD CTL & IND CTL 22VU: · Release the ENG/MAN START/1(2) pushbutton switch. 5.On the ENG PNL 115VU: · Set the ENG/MASTER 1(2) control switch to OFF. 6.On the ENG PNL 115VU: · Set the ENG/MODE/CRANK/NORM/IGN START selector switch to NORM. NOTE: The ECU stays electrically supplied for 5 minutes after you set: - the ENG/MASTER 1(2) lever to OFF.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 74-31-00-040-002-A - Check of Ignition Fault Warning

ACTION - The ENG/MODE/CRANK/NORM/IGN START rotary selector to NORM.

RESULT

NOTE: The WARNING messages that appears during this procedure can be cleared by an ON/ OFF switching of the ENG/MASTER 1(2) control switch.

5.

Close-up Subtask 74-31-00-860-051-A A.

Put the aircraft back to its initial configuration. (1) On the MAINTENANCE PNL 50VU: (a) Push the ENG / FADEC GND PWR / 1(2) pushbutton switch. The ON legend goes off. (2) Do the EIS stop procedure: (Ref. AMM TASK 31-60-00-860-002) . (3) Make an entry in the log book. (4) Put a WARNING NOTICE(S) to tell person that igniter indication is selected on the ENGINE SD page (FAA only).

Subtask 74-31-00-865-054-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU FOR FIN 1000EM1 121VU 121VU FOR FIN 1000EM2 121VU 121VU

DESIGNATION ENGINE/1 AND 2/IGN/SYS A (ENGINE-1) ENGINE/IGN/ENG1/SYS B ENGINE/IGN/ENG1/SYS A BAT (ENGINE-2) ENGINE/IGN/ENG2/SYS B ENGINE/IGN/ENG2/SYS A BAT

FIN 1JH

A03

LOCATION

3JH1 2JH1

P41 P39

3JH2 2JH2

P42 P40

Subtask 74-31-00-862-051-A C.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 74-31-00-040-005-A - Temporary Modification of the JH1 and JH2 Routing for Aircraft Dispatch Requirements

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 TASK 74-31-00-040-005-A Temporary Modification of the JH1 and JH2 Routing for Aircraft Dispatch Requirements WARNING:

BEFORE YOU START WORK ON THE IGNITION SYSTEM, MAKE SURE THAT THE IGNITION EXCITERS ARE DE-ENERGIZED FOR A MINIMUM OF FIVE MINUTES. ALSO DO NOT TOUCH THE ELECTRICAL CONTACTS. THE IGNITION SYSTEM VOLTAGE IS VERY HIGH, AND THE IGNITION EXCITERS CAN HAVE AN ELECTRICAL CHARGE EVEN WHEN NOT ENERGIZED. IF YOU DO NOT OBEY THESE PRECAUTIONS, INJURY CAN OCCUR.

CAUTION:

BE CAREFUL WITH THE IGNITION LEAD TO PREVENT DAMAGE TO THE CONDUIT AND THE INTERNAL WIRES.

FIN : 1000EM1 , 1000EM2 1.

Reason for the Job MMEL 74-31-01A Ignition System A (FAA only) left ignition lead on aircraft battery bus. MMEL743101

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

QTY AR AR AR AR

DESIGNATION ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE PLIERS - NOSE, SOFT, LONG SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 437AL, 438AR FOR 1000EM2 (ENGINE-2) 447AL, 448AR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 74-31-00-040-005-A - Temporary Modification of the JH1 and JH2 Routing for Aircraft Dispatch Requirements REFERENCE DESIGNATION (Ref. 71-13-00-010-040-B). Opening of the Fan Cowl Doors (Ref. 71-13-00-410-040-B). Closing of the Fan Cowl Doors (Ref. 74-00-00-710-043-A). Operational Test of the Ignition System (Ref. 74-00-00-710-043-A-01). Operational Test of the Ignition System without CFDS (Ref. 78-30-00-081-041-B). Make the Thrust Reverser Serviceable after Maintenance (Ref. 78-30-00-481-041-B). Make the Thrust Reverser Unserviceable for Maintenance Temporary Modification of the JH1 and JH2 Harnesses Routing and Connection

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 74-31-00-040-005-A - Temporary Modification of the JH1 and JH2 Routing for Aircraft Dispatch Requirements

A A

FLANGE STA 199 (A2)

B

C1M-355-00

N_MM_743100_4_RAM0_01_00

Figure 74(CFMB)-31-00-991-30000-06-A / SHEET 1/3 - Temporary Modification of the JH1 and JH2 Harnesses Routing and Connection ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 74-31-00-040-005-A - Temporary Modification of the JH1 and JH2 Routing for Aircraft Dispatch Requirements

B IGN EXCITER A

4000JH1

4000JH2

IGN EXCITER B

C1M-356-00

N_MM_743100_4_RAM0_02_00

Figure 74(CFMB)-31-00-991-30000-06-A / SHEET 2/3 - Temporary Modification of the JH1 and JH2 Harnesses Routing and Connection ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 74-31-00-040-005-A - Temporary Modification of the JH1 and JH2 Routing for Aircraft Dispatch Requirements

B IGN EXCITER A

4000JH2

4000JH1

IGN EXCITER B

C1M-357-00

N_MM_743100_4_RAM0_03_00

Figure 74(CFMB)-31-00-991-30000-06-A / SHEET 3/3 - Temporary Modification of the JH1 and JH2 Harnesses Routing and Connection ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 74-31-00-040-005-A - Temporary Modification of the JH1 and JH2 Routing for Aircraft Dispatch Requirements

3.

Job Set-up Subtask 74-31-00-861-052-A A.

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

Subtask 74-31-00-941-054-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 the center pedestal, on the ENG panel 115VU: (a) Put a WARNING NOTICE(S) to tell persons not to start the engine. (3) On the overhead 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) to tell persons not to energize the FADEC 1(2).

Subtask 74-31-00-865-059-A C.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU FOR FIN 1000EM1 121VU 121VU FOR FIN 1000EM2 121VU 121VU

DESIGNATION ENGINE/1 AND 2/IGN/SYS A (ENGINE-1) ENGINE/IGN/ENG1/SYS B ENGINE/IGN/ENG1/SYS A BAT (ENGINE-2) ENGINE/IGN/ENG2/SYS B ENGINE/IGN/ENG2/SYS A BAT

FIN 1JH

A03

LOCATION

3JH1 2JH1

P41 P39

3JH2 2JH2

P42 P40

Subtask 74-31-00-010-052-A D.

Get Access (1) Open the fan cowl doors: (Ref. AMM TASK 71-13-00-010-040) (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR (2) Put an ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position.

Subtask 74-31-00-040-051-A E. 4.

Make the thrust reverser unserviceable (Ref. AMM TASK 78-30-00-481-041) .

Procedure (Ref. Fig. Temporary Modification of the JH1 and JH2 Harnesses Routing and Connection) Subtask 74-31-00-020-051-A A.

Put the 4000JH1 and 4000JH2 wiring harness routings and connections to the modified configuration as follows: (1) Disconnect the 4000JH1 harness connector from the upper ignition exciter-A. (2) Disconnect the 4000JH2 harness connector from the lower ignition exciter-B. (3) Make sure that the electrical connections are clean and in the correct condition. (4) Route the 4000JH2 as follows:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 74-31-00-040-005-A - Temporary Modification of the JH1 and JH2 Routing for Aircraft Dispatch Requirements

(a) Connect the 4000JH2 harness connector to the upper ignition exciter-A by hand. Use PLIERS NOSE, SOFT, LONG only if necessary. (5) Route the 4000JH1 harness as follows: (a) Connect the 4000JH1 harness connector to the lower ignition exciter-B by hand. Use PLIERS NOSE, SOFT, LONG only if necessary. (6) Make sure that no contact of the harnesses with the ignition exciter can occur. Subtask 74-31-00-865-060-A B.

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

DESIGNATION 49VU ENGINE/1 AND 2/IGN/SYS A FOR FIN 1000EM1 (ENGINE-1) 121VU ENGINE/IGN/ENG1/SYS B 121VU ENGINE/IGN/ENG1/SYS A BAT FOR FIN 1000EM2 (ENGINE-2) 121VU ENGINE/IGN/ENG2/SYS B 121VU ENGINE/IGN/ENG2/SYS A BAT

FIN 1JH

LOCATION A03

3JH1 2JH1

P41 P39

3JH2 2JH2

P42 P40

Subtask 74-31-00-710-054-A C. 5.

Do an operational test of the ignition system (Ref. AMM TASK 74-00-00-710-043) .

Close-up Subtask 74-31-00-440-054-A A.

Make the thrust reverser serviceable (Ref. AMM TASK 78-30-00-081-041) .

Subtask 74-31-00-410-052-A B.

Close Access (1) Close the fan cowl doors: (Ref. AMM TASK 71-13-00-410-040) (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR (2) Remove the access platform(s). (3) Remove the WARNING NOTICE(S). (4) Make an entry in the logbook. (5) Put a WARNING NOTICE(S) to tell persons that the ignition leads are routed to opposite ignition exciters to allow dispatch with the left ignition lead on aircraft battery bus.

Subtask 74-31-00-862-052-A C.

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

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 7

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 74-31-00-040-044-A - Check of the Ignition Fault Warning

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 TASK 74-31-00-040-044-A Check of the Ignition Fault Warning 1.

Reason for the Job MMEL 74-07-01A Selected Igniter Indication on the ENGINE SD page (FAA only)

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER AR WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 31-60-00-860-001-A). (Ref. 31-60-00-860-002-A).

3.

DESIGNATION EIS Start Procedure EIS Stop Procedure

Job Set-up Subtask 74-31-00-865-052-A A.

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

DESIGNATION 49VU ENGINE/1 AND 2/IGN/SYS A FOR FIN 1000EM1 (ENGINE-1) 121VU ENGINE/IGN/ENG1/SYS B 121VU ENGINE/IGN/ENG1/SYS A BAT FOR FIN 1000EM2 (ENGINE-2) 121VU ENGINE/IGN/ENG2/SYS B 121VU ENGINE/IGN/ENG2/SYS A BAT

FIN 1JH

LOCATION A03

3JH1 2JH1

P41 P39

3JH2 2JH2

P42 P40

Subtask 74-31-00-860-052-A B.

Aircraft Maintenance Configuration (1) On the MAINTENANCE PNL 50VU: (a) Release the ENG / FADEC GND PWR / 1(2) pushbutton switch. The ON legend of this pushbutton switch comes on. (2) On the ENG PNL 115VU, make sure that: (a) The ENG/MODE/CRANK/NORM/IGN START selector switch is set to NORM. (b) The ENG/MASTER 1(2) control switch is set to OFF. (3) On the OVERHEAD CTL & IND PNL 22VU: · Make sure that the ON legend of the ENG/MAN START/1(2) pushbutton switch is off (the pushbutton switch is released out).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 74-31-00-040-044-A - Check of the Ignition Fault Warning

(4) On the HYD/FUEL PNL 40VU: (a) Make sure that the OFF legends of all the FUEL/PUMPS pushbutton switches are on (the pushbutton switches are released out). (5) Do the EIS start procedure: (Ref. AMM TASK 31-60-00-860-001) . 4.

Procedure Subtask 74-31-00-200-051-A A.

Check for ignition fault warning ACTION RESULT 1.On the ENG PNL 115VU: On the upper ECAM display unit: · Set the ENG/MODE/CRANK/NORM/IGN START · The primary engine parameters come into view. selector switch to IGN START. WAR MAKE SURE THAT THE INLET PRESNING: SURE INDICATION FOR THE STARTER VALVE IS ZERO BEFORE YOU PUSH THE ENG/MAN START/1 (2) PUSHBUTTON SWITCH. WAR MAKE SURE THAT THE INLET PRESNING: SURE INDICATION FOR THE STARTER VALVE IS ZERO BEFORE YOU PUSH THE ENG/MAN START/1 (2) PUSHBUTTON SWITCH. 2.On the OVERHEAD CTL & IND CTL 22VU: · Push the ENG/MAN START/1(2) pushbutton · The ON legend of this pushbutton switch comes switch. on. 3.On the ENG PNL 115VU: On the lower ECAM display unit, on the ENGINE · Set the ENG/MASTER 1(2) control switch to ON. page: ENG1(2) START VALVE FAULT warning comes into view. START VALVE NOT OPEN · after about 15s make sure that IGN A+B FAULT warning comes into view. 4.On the OVERHEAD CTL & IND CTL 22VU: · Release the ENG/MAN START/1(2) pushbutton switch. 5.On the ENG PNL 115VU: · Set the ENG/MASTER 1(2) control switch to OFF. 6.On the ENG PNL 115VU: · Set the ENG/MODE/CRANK/NORM/IGN START selector switch to NORM. NOTE: The ECU stays electrically supplied for 5 minutes after you set: - the ENG/MASTER 1(2) lever to OFF. - The ENG/MODE/CRANK/NORM/IGN START rotary selector to NORM.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 74-31-00-040-044-A - Check of the Ignition Fault Warning

ACTION

RESULT

NOTE: The WARNING messages that appears during this procedure can be cleared by an ON/ OFF switching of the ENG/MASTER 1(2) control switch.

5.

Close-up Subtask 74-31-00-860-053-A A.

Put the aircraft back to its initial configuration. (1) On the MAINTENANCE PNL 50VU: (a) Push the ENG / FADEC GND PWR / 1(2) pushbutton switch. The ON legend goes off. (2) Do the EIS stop procedure: (Ref. AMM TASK 31-60-00-860-002) . (3) Make an entry in the logbook. (4) Put a WARNING NOTICE(S) to tell persons that igniter indication is selected on the ENGINE SD page (FAA only).

Subtask 74-31-00-865-053-A B.

Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL 49VU FOR FIN 1000EM1 121VU 121VU FOR FIN 1000EM2 121VU 121VU

DESIGNATION ENGINE/1 AND 2/IGN/SYS A (ENGINE-1) ENGINE/IGN/ENG1/SYS B ENGINE/IGN/ENG1/SYS A BAT (ENGINE-2) ENGINE/IGN/ENG2/SYS B ENGINE/IGN/ENG2/SYS A BAT

FIN 1JH

A03

LOCATION

3JH1 2JH1

P41 P39

3JH2 2JH2

P42 P40

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 75-32-00-040-801-A - Check for no failure of the Low Pressure Compressor (LPC) (2.5) Bleed Valve LVDT on CFDS

** ON A/C 301-349, 351-450, 500-600 TASK 75-32-00-040-801-A Check for no failure of the Low Pressure Compressor (LPC) (2.5) Bleed Valve LVDT on CFDS 1.

Reason for the Job MMEL 70-00-01A ENG FADEC MAINTENANCE Message

2.

Job Set-up Subtask 75-32-00-941-054-A A.

3.

Not Applicable

Procedure Subtask 75-32-00-040-054-A A.

Check for no failure of the Low Pressure Compressor (LPC) (2.5) Bleed Valve LVDT on CFDS (1) Make sure that maintenance messages related to bleed valve LVDT electrical failure on channel A and/or channel B are not reported in EEC interactive mode fault reports on MCDU. (a) Check on GROUNG report, LAST LEG REPORT or Post Flight Report.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-040-B - Deactivation of the Thrust Reverser System

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 TASK 78-30-00-040-040-B Deactivation of the Thrust Reverser System 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.

CAUTION:

NEVER BLANK OFF HYDRAULIC CONTROL UNIT (HCU) RETURN HOSE AND RELEASE AIRCRAFT (EVEN IF THRUST REVERSER IS DEACTIVATED). THIS ACTION MAY RESULT IN THRUST REVERSER SYSTEM PRESSURIZATION.

FIN : 1000EM1 , 1000EM2 1.

Reason for the Job MMEL 78-30-01A Thrust Reverser

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific

B.

QTY DESIGNATION AR ACCESS PLATFORM 1M(3 FT) AR WARNING NOTICE(S) Torque wrench: range to between 0.16 and 0.19 m.daN (14.16 and 16.81 lbf.in) Torque wrench: range to between 0.33 and 0.45 m.daN (29.20 and 39.82 lbf.in) Torque wrench: range to between 0.65 and 0.70 m.daN (57.52 and 61.95 lbf.in)

Work Zones and Access Panels ZONE/ACCESS 210 400 FOR 1000EM1 (ENGINE-1) 437AL, 438AR FOR 1000EM2 (ENGINE-2) 447AL, 448AR

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD POWER PLANT, NACELLES AND PYLONS

C. Referenced Information REFERENCE (Ref. 71-13-00-010-040-B). (Ref. 71-13-00-410-040-B). (Ref. 73-29-00-710-040-B-02). (Ref. 73-29-00-860-801-A).

DESIGNATION Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Operational Test of the FADEC on the Ground (with Engine Non motoring) Change of the Inhibition Status of the Thrust Reverser System

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-040-B - Deactivation of the Thrust Reverser System

REFERENCE DESIGNATION (Ref. 78-31-00-710-042-A). Operational Test of the Thrust Reverser System (Ref. 78-31-17-000-001-A). Removal of the Blocker Door Deploy Switch (Ref. 78-31-17-400-001-A). Installation of the Blocker Door Deploy Switch (Ref. 78-31-18-000-001-A). Removal of the Blocker Door Stow-switch (Ref. 78-31-18-400-001-A). Installation of the Blocker Door Stow-switch Hydraulic-Control-Unit (HCU) Operating Control Lever (Operational/Inhibit Position) Lockout Fairing and Storage Bracket SHEET 1 Lockout Bolt and Lockplate SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-040-B - Deactivation of the Thrust Reverser System

B

HYDRAULIC CONTROL UNIT

QUICK-RELEASE PIN ASSEMBLY OPERATIONAL POSITION

INHIBIT LEVER IN OFF POSITION

INHIBIT LEVER IN OPERATIONAL POSITION

C1M-385-00

B

N_MM_783000_4_REM0_01_00

Figure 78(CFMB)-30-00-991-30000-06-A / SHEET 1/2 - HydraulicControl-Unit (HCU) Operating Control Lever (Operational/Inhibit Position) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-040-B - Deactivation of the Thrust Reverser System

A

HYDRAULIC CONTROL UNIT

QUICK-RELEASE PIN ASSEMBLY IN OFF POSITION

INHIBIT LEVER IN OFF POSITION

A C1M-309-01

INHIBIT LEVER IN OPERATIONAL POSITION

N_MM_783000_4_REM0_02_00

Figure 78(CFMB)-30-00-991-30000-06-A / SHEET 2/2 - HydraulicControl-Unit (HCU) Operating Control Lever (Operational/Inhibit Position) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-040-B - Deactivation of the Thrust Reverser System

A BLOCKER DOOR

A

SCREW (5)

B

LOCKOUT FAIRING (6)

B

BLOCKER DOOR ACTUATOR PIVOTING DOOR LATCH

BLOCKER DOOR ACTUATOR

BOLT (3) STORAGE BRACKET (4) LOCKOUT BOLT (1) LOCKPLATE (2)

C1M-241-01 N_MM_783000_4_RCM0_01_00

Figure 78(CFMB)-30-00-991-30200-06-A / SHEET 1/1 - Lockout Fairing and Storage Bracket ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-040-B - Deactivation of the Thrust Reverser System

A A

BLOCKER DOOR

LOCKOUT BOLT (1)

A

BOLT (3)

LOCKPLATE (2)

A

SECTION

A-A BLOCKER DOOR

LOCKOUT BOLT

C1M-242-00 N_MM_783000_4_RDM0_01_00

Figure 78(CFMB)-30-00-991-30300-06-A / SHEET 1/1 - Lockout Bolt and Lockplate ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-040-B - Deactivation of the Thrust Reverser System

3.

Job Set-up Subtask 78-30-00-941-050-A A.

Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a WARNING NOTICE(S) to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead 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) to tell persons not to energize the FADEC 1(2).

Subtask 78-30-00-010-050-A B.

Get Access (1) Open the fan cowl doors: (Ref. AMM TASK 71-13-00-010-040) (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR (2) Put the ACCESS PLATFORM 1M(3 FT) in position.

4.

Procedure (Ref. Fig. Hydraulic-Control-Unit (HCU) Operating Control Lever (Operational/Inhibit Position)) (Ref. Fig. Lockout Fairing and Storage Bracket SHEET 1) (Ref. Fig. Lockout Bolt and Lockplate SHEET 1)

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 EMB SB 73-1077 for A/C 210-210 Subtask 78-30-00-040-050-B A.

Thrust Reverser Deactivation. WARNING: MAKE SURE THAT THE THRUST REVERSER IS LOCKED. IF NOT, THE THRUST REVERSER CAN OPERATE ACCIDENTALLY AND CAUSE INJURY TO PERSONNEL AND/ OR DAMAGE TO THE REVERSER. (1) Do a check of the primary lock, as follows: (a) Make sure the blocker doors are closed and flush with the thrust reverser structure. (b) Pull the blocker door with your hand to make sure the door cannot open. (2) Make the Thrust Reverser Unserviceable.

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. Hydraulic-Control-Unit (HCU) Operating Control Lever (Operational/Inhibit Position)) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-040-B - Deactivation of the Thrust Reverser System

EMB SB 73-1077 for A/C 210-210 (a) Remove the quick-release pin from the operational position on the HCU (see sheet.1). (b) Move the inhibit lever from the operational position to the OFF position. (c) Install the quick-release pin to hold the inhibit lever in the OFF position (see sheet.2). (3) Do a test of the deploy switches and make sure that they are operative. (a) Do an operational test of the thrust reverser system through the Centralized Fault Display System (CFDS) (Ref. AMM TASK 78-31-00-710-042) and when the throttle control lever is in the reverse position: · check that the green or amber REV indication in the N1 indicator of the engine 1(2) does not appears · the ECAM warning ENG 1(2) REVERSER FAULT appears · check the T/R test report: 1

If the following message is present, replace the four deploy switches (Ref. AMM TASK 7831-17-000-001) and (Ref. AMM TASK 78-31-17-400-001) and do the test again: · "DEPL SW, J5/J6,ECU"

2

If the following message is present, replace the four stow switches (Ref. AMM TASK 78-3118-000-001) and (Ref. AMM TASK 78-31-18-400-001) and do the test again: · "STOW SW, J5/J6,ECU"

3

If the following message is present, replace the four deploy switches (Ref. AMM TASK 7831-17-000-001) , (Ref. AMM TASK 78-31-17-400-001) and the four stow switches (Ref. AMM TASK 78-31-18-000-001) , (Ref. AMM TASK 78-31-18-000-001) and do the test again: · "DPLSTW SW,J5/6,ECU"

4

If the ECAM warning ENG 1(2) REV PRESSURIZED appears together with one of the following messages, do the troubleshooting procedure relative to the triggered warning (TSM 78PB101). · "HCU(TRPV OPEN)" or "HCU(TRPV), HYD"

5

If one of the following messages is present, troubleshoot and do the test again: · "EIU,HCU" or "TR LOCK, TR ACT"

6

If the message "HCU (TRPV), HYD" or "HCU, TRSOV, HYD" is present and if there is no other message above mentioned, continue the deactivation procedure. NOTE: The maintenance messages linked to the fault(s) occurred before the deactivation, can be recorded in this T/R test report.

(4) Deactivation of the thrust reverser. ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. Lockout Fairing and Storage Bracket SHEET 1) (Ref. Fig. Lockout Bolt and Lockplate SHEET 1) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 EMB SB 73-1077 for A/C 210-210 (a) Remove the bolts (3) that attach the lockplates (2) to the storage bracket (4). (b) Remove the lockplates (2) from the storage bracket (4). (c) Remove the lockout bolts (1) from the storage bracket (4). (d) Remove the screws (5) that attach the lockout fairings (6) to the blocker doors. Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-040-B - Deactivation of the Thrust Reverser System

(e) Attach the lockout fairings (6) to the storage bracket (4) with the screws (5). (f)

TORQUE screws (5) to between 0.16 and 0.19 m.daN (14.16 and 16.81 lbf.in)

(g) Install the lockout bolts (1) on the blocker doors. ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 (Ref. Fig. Lockout Bolt and Lockplate SHEET 1) ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 EMB SB 73-1077 for A/C 210-210 NOTE: Make sure that a conical washer is installed on the lockout bolt (1). (h) TORQUE the lockout bolts (1) to between 0.65 and 0.70 m.daN (57.52 and 61.95 lbf.in). (5) Put the lockplates (2) over the lockout bolts (1) and install the bolts (3). (6) TORQUE the bolts (3) to between 0.33 and 0.45 m.daN (29.20 and 39.82 lbf.in). ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Subtask 78-30-00-410-050-A B.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the access platform(s). (3) Close the fan cowl doors: (Ref. AMM TASK 71-13-00-410-040) (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR (4) Remove the WARNING NOTICE(S).

Subtask 78-30-00-710-051-A C.

Do a FADEC ground test (Engine Non Motoring) (Ref. AMM TASK 73-29-00-710-040) . (1) Make sure that these fault messages are not in view: · "STOW SW, J5/J6,ECU" or "DEPL SW,J5/J6,ECU" or "DPLSTW SW,J5/6,ECU"

Subtask 78-30-00-710-072-A D.

Do an operational test of the thrust reverser system through the CFDS (Ref. AMM TASK 78-31-00-710042) . (1) Make sure that the ENG1(2) REVERSE UNLOCKED and the ENG1(2) REV PRESSURIZED warnings do not come into view.

Subtask 78-30-00-710-059-A E.

Change the Rev Inhibition Status CAUTION:

MAKE SURE THAT THE AIRCRAFT IS FITTED WITH ECU 5BS OR SUBSEQUENT, AND WITH FWC H2F6 OR SUBSEQUENT.

(1) Change the rev inhibition status of the thrust reverser system from NOT INHIBITED to INHIBITED (Ref. AMM TASK 73-29-00-860-801) .

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-040-B - Deactivation of the Thrust Reverser System

5.

Close-up Subtask 78-30-00-941-051-A A.

Safety Precautions (1) In the cockpit, install a WARNING NOTICE(S) to show the reverser cannot operate. (2) Make an entry in the log book.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-013-A - Deactivation of the Thrust Reverser System for Flight

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 TASK 78-30-00-040-013-A Deactivation of the Thrust Reverser System for Flight 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:

DO NOT CAUSE A BLOCKAGE OF THE HYDRAULIC CONTROL UNIT (HCU) RETURN PORT TO DEACTIVATE THE HCU. IF YOU CAUSE A BLOCKAGE OF THE HCU RETURN PORT THE THRUST REVERSER CAN OPERATE ACCIDENTLY AND CAUSE INJURY OR DAMAGE.

WARNING:

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

FIN : 4101KS1 , 4101KS2 Task Summary MMEL or CDL Ref MMEL 78-30-01A

Access YES

Test YES

Specific Tools NO

Mhr 00.8

E/T 00.8

Nb Men 1

1.

Reason for the Job MMEL 78-30-01A Thrust Reverser This procedure supplies the data to deactivate (lockout) the thrust reverser system to release an aircraft with a thrust reverser that does not operate.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION AR ACCESS PLATFORM 1M(3 FT) AR WARNING NOTICE(S)

Consumable Materials REFERENCE (Material No. V01-076) (Material No. V10-094) (Material No. 14SBA1)

DESIGNATION Methyl Ethyl Ketone, Technical grade anti-seize compound Textile-Lint free Cotton -

C. Work Zones and Access Panels ZONE/ACCESS 400 FOR 1000EM1 (ENGINE-1) 437AL, 438AR

ZONE DESCRIPTION POWER PLANT, NACELLES AND PYLONS

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-013-A - Deactivation of the Thrust Reverser System for Flight

ZONE/ACCESS FOR 1000EM2 (ENGINE-2) 447AL, 448AR

ZONE DESCRIPTION

D. Referenced Information REFERENCE (Ref. 71-13-00-010-010-A). (Ref. 71-13-00-410-010-A). (Ref. 73-22-00-860-010-A). (Ref. 78-30-00-820-010-A). (Ref. 78-31-00-710-041-A). (Ref. 78-31-00-710-041-A-02).

DESIGNATION Opening of the Fan Cowls 437AL(447AL),438AR(448AR) Closing of the Fan Cowls 437AL(447AL),438AR(448AR) Change of the Inhibition Status of the Thrust Reverser System Rigging of the Thrust Reverser System Operational Test of the Thrust Reverser System with the CFDS Operational test of the Thrust Reverser without the CFDS and Engine Running Manual Retraction of the Thrust Reverser Translating Sleeves

(Ref. 78-32-00-860-011-A). Hydraulic Control Unit SHEET 1 Paragraph 4A to 4D Flowchart SHEET 1 Thrust Reverser Lockout SHEET 1 Thrust Reverser Lockout SHEET 1 Comparison Between Correct and Incorrect Installation of Lock Pin SHEET 1 Reverser Test "Faults Detected" Page (A5 Only) (Menu#11f) SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-013-A - Deactivation of the Thrust Reverser System for Flight

A

A PYLON

1 HCU

2 LOCKOUT PIN

3 LOCKOUT LEVER N_MM_783000_4_XBM0_01_00

Figure 78(IAE)-30-00-991-18000-13-A / SHEET 1/1 - Hydraulic Control Unit ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-013-A - Deactivation of the Thrust Reverser System for Flight

DEACTIVATION OF THE THRUST REVERSER SYSTEM FOR FLIGHT AMM 78-30-00-040-013 - Paragraphs 4A to 4D SUBTASKS 78-30-00-040-055-A, 78-30-00-860-054-A, 78-30-00-04-056-A & 78-30-00-860-059-A

Deactivate the T/R HCU with the storage lockout pin attached to the HCU

Is the translating sleeve in the fully retracted position ?

Manually move the translating sleeves to the fully retracted position

NO

YES Measure the distance between the translating sleeve leading edge and the fan cowl aft edge

Is the distance within the tolerance ?

NO

Move the translating sleeve forward until 1 or the 2 actuator rod ends can be put in the mounting brackets. If only 1 rod end can be put in the mounting bracket, the other one must be adjusted

YES

Remove the plug from the lockout assembly on the outside of each translating sleeve Remove the lockout pin from the pin stowage bracket assembly on the outside of each translating sleeve Clean the plug & the lockout pin

Install the lockout pin in the lockout assembly

Is the lockout pin correctly installed in the lockout assembly ?

NO

Do a check of the rigging of the translating sleeve actuators In AMM 78-30-00-820-010 - Rig of Thrust Reverser system Paragraph 4C / SUBTASK 78-30-00-820-052-A

YES Install the plug in the pin stowage bracket assembly of each translating sleeve

gc0a5m8424

Do an operational test of the LVDTs to be sure that they operate correctly on the deactivated reverser

Change the inhibition status of the T/R system from NOT INHIBITED to INHIBITED

End of procedure

N_MM_783000_4_XYZ2_01_00

Figure 78(IAE)-30-00-991-94200-13-A / SHEET 1/1 - Paragraph 4A to 4D Flowchart ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-013-A - Deactivation of the Thrust Reverser System for Flight

A

A

17 PIN STOWAGE BRACKET ASSEMBLY 15 LOCKOUT ASSEMBLY

18 PLUG

16 LOCKOUT PIN

13481C N_MM_783000_4_XCM0_01_00

Figure 78(IAE)-30-00-991-15100-13-A / SHEET 1/1 - Thrust Reverser Lockout ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-013-A - Deactivation of the Thrust Reverser System for Flight

A

A

17 PIN STOWAGE BRACKET ASSEMBLY 15 LOCKOUT ASSEMBLY

18 PLUG

16 LOCKOUT PIN

B8369 N_MM_783000_4_XEM0_01_00

Figure 78(IAE)-30-00-991-15900-13-A / SHEET 1/1 - Thrust Reverser Lockout ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-013-A - Deactivation of the Thrust Reverser System for Flight

MISALIGNMENT OF THE TRANSLATING SLEEVE WITH THE C-DUCT BEFORE LOCKOUT PIN INSTALLATION

LOCKOUT PIN INSTALLED IN A MISALIGNED ASSEMBLY

CAUTION RED PIN = THRUST REVERSER MANUALLY DEACTIVATED

gc0a5m8425

COMPARISON BETWEEN CORRECT AND INCORRECT INSTALLATION

C-DUCT STRUCTURE RED PIN = THRUST REVERSER MANUALLY DEACTIVATED N_MM_783000_4_XYZ1_01_00

Figure 78(IAE)-30-00-991-94100-13-A / SHEET 1/1 - Comparison Between Correct and Incorrect Installation of Lock Pin ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-013-A - Deactivation of the Thrust Reverser System for Flight

F AD E C X RE VE RS E R

TES T

1L

1R T / R

TES T

CL OSE

UP

2L

2R

3L

3R

4L

F AU L T D E T E CT ED S E E GR OU ND S CANN I N G

4R

5L 6L

5R

R E TURN

6R

N_MM_783000_4_XFM0_01_00

Figure 78(IAE)-30-00-991-91100-13-A / SHEET 1/1 Reverser Test "Faults Detected" Page (A5 Only) (Menu#11f) ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-013-A - Deactivation of the Thrust Reverser System for Flight

3.

Job Set-up Subtask 78-30-00-941-058-A A.

Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a WARNING NOTICE(S) to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred 5 minutes or more before you do this procedure. (3) On the overhead 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) to tell persons not to energize the FADEC 1(2).

Subtask 78-30-00-010-058-A B.

Get Access (1) Open the fan cowls (Ref. AMM TASK 71-13-00-010-010) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR (2) Put the ACCESS PLATFORM 1M(3 FT) in position.

4.

Procedure Subtask 78-30-00-040-055-A A.

Deactivation of the Thrust Reverser HCU (Ref. Fig. Hydraulic Control Unit SHEET 1) (Ref. Fig. Paragraph 4A to 4D Flowchart SHEET 1) 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) Deactivate the thrust reverser HCU with the storage lockout pin (2) attached to the HCU. (a) Set the lockout lever (3) on the HCU (1) to the lockout position. (b) Install the lockout pin (2) attached to the HCU (1) in the lockout hole of the HCU (1).

Subtask 78-30-00-860-054-A B.

Retract the Left and Right Translating Sleeves (1) Make sure the translating sleeve is in the fully retracted position. If it is not, manually move the translating sleeves to the fully retracted position (Ref. AMM TASK 78-32-00-860-011) . (2) Measure the distance between the translating sleeve leading edge and the fan cowl aft edge (Ref. AMM TASK 78-30-00-820-010) Para. 4.C.(8).

Subtask 78-30-00-040-056-A C.

Lock the Left and Right Translating Sleeves (Ref. Fig. Thrust Reverser Lockout SHEET 1) (Ref. Fig. Thrust Reverser Lockout SHEET 1) (Ref. Fig. Comparison Between Correct and Incorrect Installation of Lock Pin SHEET 1)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-013-A - Deactivation of the Thrust Reverser System for Flight

(1) Remove the plug (18) from the lockout assembly (15) on the outside of each translating sleeve (14). (2) Remove the lockout pin (16) from the pin stowage bracket assembly (17) on the outside of each translating sleeve. (3) Clean the components: (a) Clean the lockout pin (16) and the plug (18) with Methyl Ethyl Ketone, Technical grade (Material No. V01-076). Wipe dry with a Textile-Lint free Cotton - (Material No. 14SBA1) before the methylethylketone evaporates. (b) Apply anti-seize compound (Material No. V10-094) to the lockout pin (16) and the plug (18). CAUTION:

MAKE SURE THAT THE HOLES IN THE C-DUCT AND THE TRANSLATING SLEEVE ARE CORRECTLY ALIGNED AND THE LOCKOUT PIN IS INSTALLED CORRECTLY. THERE IS A RISK THAT THE LOCKOUT PIN WILL NOT BE FULLY INSTALLED AND WILL NOT MECHANICALLY INHIBIT THE REVERSER.

(4) Install the lockout pin (16) in the lockout assembly (15) as shown on the figure. (a) If the lockout pin cannot be fully installed because the holes are not aligned, align them: · Do a check of the rigging of the translating sleeve actuators (Ref. AMM TASK 78-30-00-820010) Para. 4.C. NOTE: The lockout pin will be above the receptacle when the pin is installed. (5) Install the plug (18) into the pin stowage bracket assembly (17) of each translating sleeve as shown on the figure. (6) Do a test of the LVDTs and make sure that they operate correctly on the deactivated reverser. (a) Do the operational test of the thrust reverser system with the CFDS (Ref. AMM TASK 78-31-00710-041) on EEC channels A and B: 1

During the operational test, make sure that the green or amber REV indication in the EPR indicator of engine 1(2) does not show.

2

When the FAULT DETECTED page comes into view on MCDU screen, push two times the return key and show the GROUND SCANNING menu. (Ref. Fig. Reverser Test "Faults Detected" Page (A5 Only) (Menu#11f) SHEET 1)

(b) Make sure that these faults are not reported by GROUND SCANNING: · REV LVDT CHA/HC/EEC 1(2) · REV LVDT CHB/HC/EEC 1(2) · REV POS OR LVDT FAULT 1(2) NOTE: You can ignore the T/R SOV/HCU/EEC 1(2) or HYD CONT UNIT/HC/EEC 1(2) fault. (c) Return the throttle lever to the IDLE position. WARNING: MAKE SURE THAT THE "ENG 1(2) REVERSE UNLOCKED" AND "ENG 1(2) REV PRESSURIZED" ECAM WARNINGS ARE NOT SHOWN. THEY ARE SHOWN WHEN THE THRUST REVERSER DEACTIVATION IS NOT CORRECT AND THERE IS NO MECHANICAL OR HYDRAULIC INHIBITION OF THE THRUST REVERSER. THIS CAN CAUSE AN IN-FLIGHT DEPLOYMENT OF THE THRUST REVERSER. (d) Push the return key until you exit the interactive mode and make sure that the ECAM warnings ENG 1(2) REVERSE UNLOCKED and ENG1(2) REV PRESSURIZED are not shown.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-013-A - Deactivation of the Thrust Reverser System for Flight

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 EMB SB 31-1373 for A/C 016-022, 024-072, 112-115, 201-201, 208-209, 215-216, 219-222, 227-233, 235-235, 237-239, 242-242, 244-244, 350-350 EMB SB 31-1414 for A/C 016-022, 024-072, 112-115, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-244, 350-350 EMB SB 73-1097 for A/C 022-022, 025-027, 029-029, 031-050, 052-052, 114-115, 203-206, 209-209, 211-211, 219-221, 227-232, 237-238, 244-244 Subtask 78-30-00-860-059-A D.

Change the inhibition status of the thrust reverser system from NOT INHIBITED to INHIBITED (POST SBE 73-0222 only) (Ref. AMM TASK 73-22-00-860-010) .

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 5.

Close-up Subtask 78-30-00-410-057-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the fan cowls (Ref. AMM TASK 71-13-00-410-010) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR (3) Remove the access platform(s). (4) Remove the WARNING NOTICE(S). (5) Put a WARNING NOTICE(S) in the cockpit above the throttle levers to tell persons that the Thrust Reverser HCU is deactivated. (6) Make an entry in the log book.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 11

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-30-00-040-812-A - Deactivation of the Thrust Reverser System after Flight and ECAM warning REV INHIBITED

** ON A/C 301-349, 351-450, 500-600 TASK 78-30-00-040-812-A Deactivation of the Thrust Reverser System after Flight and ECAM warning REV INHIBITED 1.

Reason for the Job MMEL 78-30-01A Thrust Reverser

2

Job Set-up Information A.

Referenced Information REFERENCE (Ref. 78-30-00-040-806-A).

3.

DESIGNATION Deactivation of the Thrust Reverser System for Flight

Job Set-up Subtask 78-30-00-860-073-A A.

4.

Not applicable

Procedure Subtask 78-30-00-040-079-A A.

Deactivate the Trhust Reverser for Flight (Ref. AMM TASK 78-30-00-040-806)

Subtask 78-30-00-710-068-A B.

Do an operational test of the thrust reverser with the MCDU. (1) Check for the warning of the thrust reverser inhibition on the upper ECAM display unit. (a) On the ENG section of the maintenance panel 50VU: · Release the FADEC GND PWR/1(2) pushbutton switch (the ON legend comes on). (b) On the upper ECAM display unit: · Make sure that the REV INHIBITED warning comes into view and the ENG1(2) REVERSE UNLOCKED and ENG1(2) REV PRESSURIZED warnings do not come into view.

5.

Close-up Subtask 78-30-00-860-074-A A.

Aircraft Maintenance Configuration (1) Make an entry in the logbook to record that the Thrust Reverser has been deactivated.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-37-00-040-801-A - Deactivation of the TRAS Track Lock

** ON A/C 301-349, 351-450, 500-600 TASK 78-37-00-040-801-A Deactivation of the TRAS Track Lock 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.

1.

Reason for the Job MMEL 78-30-04B Thrust Reverser Door Tertiary Lock

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

QTY DESIGNATION 1 EXTENSION 1/4 IN - SQUARE DRIVE 1 WRENCH - FLAT Torque wrench: range to between 45 and 50 lbf.in (0.51 and 0.57 m.daN)

Work Zones and Access Panels ZONE/ACCESS 400

ZONE DESCRIPTION POWER PLANT, NACELLES AND PYLONS

C. Referenced Information REFERENCE (Ref. 71-00-00-860-833-A). (Ref. 78-30-00-040-805-A). (Ref. 78-30-00-440-805-A). (Ref. 78-32-37-000-801-A). TRAS Track Lock

DESIGNATION Procedure to Prevent Engine Motoring Deactivation of the Thrust Reverser System for Ground Maintenance Reactivation of the Thrust Reverser System after Ground Maintenance Removal of the TRAS Track Lock Pin Access Panel

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-37-00-040-801-A - Deactivation of the TRAS Track Lock

A B

1 x2

2

ICN-GRAA320NEO-A-783700-G-51563-02531-A-003-01

C E

1 x2

D F

2

3 OR 4 01

A

02

TRACK LOCK COVER SHOWN WHEN TRAS TRACK LOCK IS IN THE LOCKED POSITION

NOTE: 01 ITEM 3 IS FOR CONFIGURATION 1. ITEM 4 IS FOR CONFIGURATION 2. 02 LH SHOWN, RH OPPOSITE

B

02

TRACK LOCK COVER SHOWN WHEN TRAS TRACK LOCK IS IN THE UNLOCKED POSITION

N_MM_783700_4_NAM0_01_02

Figure 78(PW11)-37-00-991-00200-21-A / SHEET 1/2 - TRAS Track Lock ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-37-00-040-801-A - Deactivation of the TRAS Track Lock

TRAS TRACK LOCK LOCKOUT LEVER

TRAS TRACK LOCK LOCKOUT LEVER

3

C

02

D

02

TRAS TRACK LOCK

VIEW LOOKING DOWN TRAS TRACK LOCK SHOWN IN THE LOCKED POSITION

VIEW LOOKING DOWN TRAS TRACK LOCK SHOWN IN THE UNLOCKED AND PINNED POSITION

CONFIGURATION 1

CONFIGURATION 1

TRAS TRACK LOCK LOCKOUT LEVER ICN-GRAA320NEO-A-783700-G-51563-02532-A-003-01

TRAS TRACK LOCK

TRAS TRACK LOCK LOCKOUT LEVER 4

TRAS TRACK LOCK

E

02

VIEW LOOKING DOWN TRAS TRACK LOCK SHOWN IN THE LOCKED POSITION CONFIGURATION 2 NOTE: 02 LH SHOWN, RH OPPOSITE

F

02

TRAS TRACK LOCK

VIEW LOOKING DOWN TRAS TRACK LOCK SHOWN IN THE UNLOCKED AND PINNED POSITION CONFIGURATION 2

N_MM_783700_4_NAM0_02_03

Figure 78(PW11)-37-00-991-00200-21-A / SHEET 2/2 - TRAS Track Lock ** ON A/C 301-349, 351-450, 500-600 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-37-00-040-801-A - Deactivation of the TRAS Track Lock

3.

Job Set-up Subtask 78-37-00-941-050-A A.

Safety Precautions (1) Do the procedure to prevent engine motoring (Ref. AMM TASK 71-00-00-860-833) .

Subtask 78-37-00-040-050-A B.

Deactivation of the Thrust Reverser for Maintenance 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) Do the deactivation of the thrust reverser system for maintenance (Ref. AMM TASK 78-30-00-040805) .

4.

Procedure (Ref. Fig. TRAS Track Lock) Subtask 78-37-00-040-051-A WARNING:

A.

WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE) WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ, UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS NECESSARY.

Deactivation of the TRAS Track Lock for the Applicable Thrust Reverser Half NOTE: If you deactivate/reactivate the TRAS track lock for one thrust reverser door, you must deactivate/reactivate the TRAS track lock for the opposite thrust reverser door. (1) Remove the two bolts (1) and the track lock cover (2) to get access to the lockout hole (Ref. AMM TASK 78-32-37-000-801) . CONFIGURATION 1 (2) Remove the lockout pin (3) from the latch beam. END OF CONFIGURATION 1 CONFIGURATION 2 (3) Remove the lockout pin (4) from the latch beam. END OF CONFIGURATION 2 (4) Turn the TRAS track lock lockout-lever approximately 72 degrees to the unlocked position. (a) Keep the lockout lever in the unlocked position. (b) Use the applicable WRENCH - FLAT and the EXTENSION 1/4 IN - SQUARE DRIVE. NOTE: For the TRAS track lock on the left thrust reverser, turn the lockout lever counterclockwise. For the TRAS track lock on the right thrust reverser, turn the lockout lever clockwise. CONFIGURATION 1 (5) Install the lockout pin (3) in the TRAS track lock. END OF CONFIGURATION 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 78-37-00-040-801-A - Deactivation of the TRAS Track Lock

CONFIGURATION 2 (6) Install the lockout pin (4) in the TRAS track lock. END OF CONFIGURATION 2 (7) Remove the WRENCH - FLAT and the EXTENSION 1/4 IN - SQUARE DRIVE from the TRAS track lock lockout-lever. (8) Let the TRAS track lock lockout-lever move against the lockout pin (3) or (4) to keep the TRAS track lock lockout-lever in the unlocked position. (9) Install the track lock cover (2) back on the latch beam with the two bolts (1). (a) Make sure that the track lock cover (2) pin is on the top side. (10) TORQUE the bolts (1) to between 45 and 50 lbf.in (0.51 and 0.57 m.daN). 5.

Close-up Subtask 78-37-00-440-057-A A.

Do the reactivation of the thrust reverser system after ground maintenance (Ref. AMM TASK 78-30-00440-805) .

Subtask 78-37-00-942-052-A B.

Put the aircraft back to its initial configuration. (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the WARNING NOTICE(S).

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 5

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-802-A - Deactivation of the CDLS Back-up System

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 TASK 52-51-00-040-802-A Deactivation of the CDLS Back-up System Task Summary MMEL or CDL Ref N MMELR00577 1.

Reason for the Job N MMELR00577

2

Job Set-up Information A.

Access NO

Mhr 00.3

E/T 00.3

Nb Men 1

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER

Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02).

3.

Specific Tools NO

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

Test YES

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 EMB SB 52-1115 for A/C 237-237 Subtask 52-51-00-861-050-A A.

Energize the Aircraft Electrical Circuits (1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 Subtask 52-51-00-865-136-A B.

Table of the circuit breakers used in this procedure:

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 52-51-00-040-802-A - Deactivation of the CDLS Back-up System

PANEL

DESIGNATION

FIN

LOCATION

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 EMB SB 52-1115 for A/C 237-237 122VU CKPT/OVRD SYS/SPLY

4MQ

S10

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 4.

Procedure

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 EMB SB 52-1115 for A/C 237-237 Subtask 52-51-00-040-060-A A.

Deactivation of the CDLS Back-up System (1) Open, safety and tag this(these) circuit breaker(s): · 4MQ. (2) On overhead panel 20VU, on CKPT DOOR BKUP panel 45VU, make sure that the switch LKG SYS (21MQ) is in the NORM position. NOTE: All parts of the CDLS (normal and back-up system, if installed) can be inopertive if the complete system is deactivated in the unlocked position and adjustment is not required by regulations for the intended flight.

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 5.

Close-up

** ON A/C 227-228, 231-232, 237-237, 242-242, 244-250 EMB SB 52-1115 for A/C 237-237 Subtask 52-51-00-860-113-A A.

Put the Aircraft back to the Serviceable Condition (1) Make sure that the work area is clean and clear of tools and other items. (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) . (3) Make an entry in the logbook.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 79-30-00-040-001-B - Operational Test of the Oil Pressure Indicating System

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 TASK 79-30-00-040-001-B Operational Test of the Oil Pressure Indicating System 1.

Reason for the Job MMEL 79-07-02A Oil Pressure Indication and Advisory on the ENGINE SD page

2

Job Set-up Information A.

Referenced Information REFERENCE (Ref. 78-31-00-710-042-A).

3.

DESIGNATION Operational Test of the Thrust Reverser System

Job Set-up Subtask 79-30-00-860-052-A A.

4.

Not applicable

Procedure Subtask 79-30-00-710-052-A A.

Operational Test of the Thrust Reverser System (1) Do an operational test of the thrust reverser system (Ref. AMM TASK 78-31-00-710-042) . (a) If the ECAM WARNING "ENG 1(2) REVERSER FAULT" is triggered, the thrust reverser has to be considered inoperative.

5.

Close-up Subtask 79-30-00-869-052-A A.

Make an entry in the log book to record the operational test of the thrust reverser system.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 79-31-00-040-042-A - Check of the Oil System for Oil Quantity

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 TASK 79-31-00-040-042-A Check of the Oil System for Oil Quantity 1.

Reason for the Job MMEL 79-07-03A Oil Quantity Indication on the ENGINE SD page

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION AR SAFETY CLIP - CIRCUIT BREAKER AR WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 12-13-79-610-002-A). (Ref. 12-13-79-610-002-A-01). (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A).

3.

DESIGNATION Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) Check oil level and replenish (Pressure Filling) Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power

Job Set-up Subtask 79-31-00-861-050-A A.

Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Subtask 79-31-00-941-050-A B.

Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a WARNING NOTICE(S) to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead 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) to tell persons not to energize the FADEC 1(2).

4.

Procedure Subtask 79-31-00-210-050-A A.

Do a Check of the Oil Quantity (1) Do a check of the oil level in the tank and fill it to the correct level if necessary (Ref. AMM TASK 1213-79-610-002) . NOTE: The necessary quantity is the minimum quantity plus the consumption estimate for the flight.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 79-31-00-040-042-A - Check of the Oil System for Oil Quantity

5.

Close-up Subtask 79-31-00-941-051-A A.

Indicating system (1) Put a WARNING NOTICE(S) in the cockpit to tell persons that the oil quantity indication does not operate. (2) Make an entry in the log book to record the check.

Subtask 79-31-00-865-050-A B.

Open, safety and tag this(these) circuit breaker(s): PANEL FOR FIN 1000EM1 121VU FOR FIN 1000EM2 121VU

DESIGNATION (ENGINE-1) ENGINE/ENG1/OIL/QTY (ENGINE-2) ENGINE/ENG2/OIL/QTY

FIN

LOCATION

1EN1

N39

1EN2

N41

Subtask 79-31-00-862-050-A C.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 79-35-00-040-042-A - Replacement of the Main Oil Supply Filter and Check of the Electrical Chip Detector Visual Indicator (pop-out)

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 TASK 79-35-00-040-042-A Replacement of the Main Oil Supply Filter and Check of the Electrical Chip Detector Visual Indicator (pop-out) 1.

Reason for the Job MMEL 79-09-02B ENG 1(2) OIL FILTER CLOG Alert

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 437AL, 438AR FOR 1000EM2 (ENGINE-2) 447AL, 448AR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 24-41-00-862-002-A). (Ref. 24-41-00-862-002-A-01). (Ref. 24-41-00-862-002-A-02). (Ref. 71-00-00-710-006-B). (Ref. 71-13-00-010-040-B). (Ref. 71-13-00-410-040-B). (Ref. 79-00-00-281-002-A). (Ref. 79-21-10-920-002-B). (Ref. 79-21-30-000-001-A). (Ref. 79-21-30-400-001-A). (Ref. 79-21-30-440-001-A). 3.

DESIGNATION Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) De-energize the Aircraft Electrical Circuits Supplied from the External Power De-energize the Aircraft Electrical Circuits Supplied from the APU De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) Minimum Idle Check Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Check of the Electrical Master Chip Detector (EMCD) for Particles Remove and Discard Supply Filter Removal of the Visual Indicator Installation of the Visual Indicator Resetting of the Visual Indicator

Job Set-up Subtask 79-35-00-861-050-A A.

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

Subtask 79-35-00-941-050-A B.

Safety Precautions

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 79-35-00-040-042-A - Replacement of the Main Oil Supply Filter and Check of the Electrical Chip Detector Visual Indicator (pop-out)

(1) On the center pedestal, on the ENG panel 115VU: (a) Put a WARNING NOTICE(S) to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the pushbutton switch of the ENG/FADEC GND PWR/1(2) is off. (b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2). Subtask 79-35-00-010-050-A C.

Open the fan cowl doors: (Ref. AMM TASK 71-13-00-010-040) (1) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (2) FOR 1000EM2 (ENGINE-2) 447AL, 448AR

4.

Procedure Subtask 79-35-00-040-050-A A.

Replacement of the Main Oil Filter and check of the Visual indicator (pop out) (1) Replace the main oil filter element (Ref. AMM TASK 79-21-10-920-002) . (2) Check that the visual indicator (pop out) of the electrical chip detector is not extended (popped out). (3) Check the Electrical Master Chip Detector (EMCD) for particles (Ref. AMM TASK 79-00-00-281-002)

Subtask 79-35-00-720-050-A B.

Visual indicator (pop out) functional Check (1) Disconnect the DPM electrical harness connector B from the visual indicator. (2) Close the circuit between pin N°2 and N°3 of connector B with jumper metallic for 1 second minimum. (3) Check the visual red pop out indicator must extend (extension time < 1 second). (a) If the red pop out has not extended, replace the visual indicator (Ref. AMM TASK 79-21-30-000001) and (Ref. AMM TASK 79-21-30-400-001) . (b) If red pop out indicator has extended, do the resetting of the visual indicator (Ref. AMM TASK 79-21-30-440-001) , then go to the next step.

Subtask 79-35-00-790-050-A C.

Test (1) Do a Minimum Idle leak Check (Ref. AMM TASK 71-00-00-710-006) and make sure that there is no leakage from main oil supply filter.

Subtask 79-35-00-941-051-A D. 5.

Install WARNING NOTICE(S) in the cockpit to tell that the oil filter clog warning is inoperative.

Close-up Subtask 79-35-00-410-050-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the fan cowl doors: (Ref. AMM TASK 71-13-00-410-040) (a) FOR 1000EM1 (ENGINE-1)

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 79-35-00-040-042-A - Replacement of the Main Oil Supply Filter and Check of the Electrical Chip Detector Visual Indicator (pop-out) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR (3) Remove the WARNING NOTICE(S). (4) Remove the warning notices from the panels 115VU and 50VU. (5) Make an entry in the log book. Subtask 79-35-00-862-050-A B.

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

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 79-35-00-040-044-A - Replacement of the Main Oil Supply Filter and Check of the Electrical Master Chip Detector

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 TASK 79-35-00-040-044-A Replacement of the Main Oil Supply Filter and Check of the Electrical Master Chip Detector 1.

Reason for the Job MMEL 79-09-02C ENG 1(2) OIL FILTER CLOG Alert

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 437AL, 438AR FOR 1000EM2 (ENGINE-2) 447AL, 448AR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 24-42-00-861-001-A). (Ref. 24-42-00-862-001-A). (Ref. 71-13-00-010-040-B). (Ref. 71-13-00-410-040-B). (Ref. 79-00-00-281-002-A). (Ref. 79-21-10-920-002-B). 3.

DESIGNATION Energize the Ground Service Network from the External Power De-energize the Ground Service Network Supplied from the External Power Opening of the Fan Cowl Doors Closing of the Fan Cowl Doors Check of the Electrical Master Chip Detector (EMCD) for Particles Remove and Discard Supply Filter

Job Set-up Subtask 79-35-00-861-051-A A.

Energize the ground service network (Ref. AMM TASK 24-42-00-861-001) .

Subtask 79-35-00-941-056-A B.

Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a WARNING NOTICE(S) to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead maintenance panel 50VU: (a) Make sure that the pushbutton switch of the ENG/FADEC GND PWR/1(2) is off. (b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 79-35-00-040-044-A - Replacement of the Main Oil Supply Filter and Check of the Electrical Master Chip Detector

Subtask 79-35-00-010-053-A C.

Open the fan cowl doors: (Ref. AMM TASK 71-13-00-010-040) (1) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (2) FOR 1000EM2 (ENGINE-2) 447AL, 448AR

4.

Procedure Subtask 79-35-00-040-054-A A.

Replacement of the Main Oil Filter (1) Replace the main oil filter element (Ref. AMM TASK 79-21-10-920-002) .

Subtask 79-35-00-040-052-A B.

Replacement of the Electric Master Chip Detector (1) Remove the Electric Master Chip Detector (Ref. AMM TASK 79-00-00-281-002) .

Subtask 79-35-00-040-053-A C.

Inspection of the Electric Master Chip Detector (1) Examine the Electric Master Chip Detector plug for debris presence (Ref. AMM TASK 79-00-00-281002) . (a) Check for debris build-up within the gap between the 2 magnet poles. If presence of particles then keep them for laboratory analysis as required. (2) Clean the Electric Master Chip Detector (Ref. AMM TASK 79-00-00-281-002) . (3) Install the Electric Master Chip Detector (Ref. AMM TASK 79-00-00-281-002) .

5.

Close-up Subtask 79-35-00-410-053-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the fan cowl doors: (Ref. AMM TASK 71-13-00-410-040) (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR (3) Remove the WARNING NOTICE(S). (4) Make an entry in the log book.

Subtask 79-35-00-862-051-A B.

De-energize the ground service network (Ref. AMM TASK 24-42-00-862-001) .

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 79-31-00-040-041-A - Oil Quantity Indication - Quantity Check

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 TASK 79-31-00-040-041-A Oil Quantity Indication - Quantity Check

FIN : 1000EM1 , 1000EM2 1.

Reason for the Job MMEL 79-07-03A Oil Quantity Indication on the ENGINE SD page

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR WARNING NOTICE(S)

Referenced Information REFERENCE (Ref. 12-13-79-610-011-A).

3.

DESIGNATION Check Oil Level and Replenish

Job Set-up Subtask 79-31-00-941-054-A A.

Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a WARNING NOTICE(S) to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead 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) to tell persons not to energize the FADEC 1(2).

4.

Procedure Subtask 79-31-00-210-052-A A.

Make sure that there is no evidence of oil leakage at the equipment, lines and connections. (1) Do a check of the oil level in the tank and fill it to the correct level if necessary (Ref. AMM TASK 1213-79-610-011) .

5.

Close-up Subtask 79-31-00-941-055-A A.

Put a WARNING NOTICE(S) in the cockpit to tell persons that the oil quantity indication does not operate. (1) Do an entry in the log book.

End of document Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 79-35-00-040-041-A - Deactivation of the Oil Filter Clog Warning System

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 TASK 79-35-00-040-041-A Deactivation of the Oil Filter Clog Warning System

FIN : 1000EM1 , 1000EM2 1.

Reason for the Job MMEL 79-07-01A CLOG Indication on the ENGINE SD page (FAA only) This TASK is applicable for engines V2500-A5 having embodied Number 3 FAG Bearing P/N 2A1165.

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 437AL, 438AR FOR 1000EM2 (ENGINE-2) 447AL, 448AR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 71-00-00-710-012-B). (Ref. 71-13-00-010-010-A). (Ref. 71-13-00-410-010-A). (Ref. 79-00-00-200-014-A). (Ref. 79-22-44-000-010-A). (Ref. 79-22-44-400-010-A). 3.

DESIGNATION Test No.3 : Idle Leak Check Opening of the Fan Cowls 437AL(447AL),438AR(448AR) Closing of the Fan Cowls 437AL(447AL),438AR(448AR) Inspection of the Master Magnetic Chip Detector Removal of the Scavenge Oil Filter Element Installation of the Scavenge Oil Filter Element

Job Set-up Subtask 79-35-00-941-054-A A.

Safety Precautions (1) On the center pedestal, on the ENG panel 115VU: (a) Put a WARNING NOTICE(S) to tell persons not to start the engine. (2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure. (3) On the overhead 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) to tell persons not to energize the FADEC 1(2).

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 79-35-00-040-041-A - Deactivation of the Oil Filter Clog Warning System

Subtask 79-35-00-010-052-A B.

Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-010) : (1) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (2) FOR 1000EM2 (ENGINE-2) 447AL, 448AR.

4.

Procedure Subtask 79-35-00-040-055-A A.

Do the following: (1) Replace the oil filter element (Ref. AMM TASK 79-22-44-000-010) and (Ref. AMM TASK 79-22-44400-010) once each day. (2) Inspect the Master Magnetic Chip Detector (Ref. AMM TASK 79-00-00-200-014) . (3) Put a warning notice in the cockpit to tell persons that the oil filter clog indication does not operate.

Subtask 79-35-00-710-050-A B.

Do an idle leak check (Ref. AMM TASK 71-00-00-710-012) .

Subtask 79-35-00-210-050-A C. 5.

Make sure that there are no oil leaks at the filter and the Master Magnetic Chip Detector.

Close-up Subtask 79-35-00-410-052-A A.

Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the fan cowls (Ref. AMM TASK 71-13-00-410-010) : (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR (3) Remove the WARNING NOTICE(S). (4) Make an entry in the log book.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 79-31-00-040-802-A - Check of the Oil System for Oil Quantity

** ON A/C 301-349, 351-450, 500-600 TASK 79-31-00-040-802-A Check of the Oil System for Oil Quantity 1.

Reason for the Job MMEL 79-07-03A Oil Quantity Indication on the ENGINE SD page

2

Job Set-up Information A.

Referenced Information REFERENCE (Ref. 79-00-00-210-810-A). (Ref. 79-00-00-610-801-A).

3.

DESIGNATION Visual Inspection of the Engine Oil System Check and Fill the Engine Oil

Job Set-up Subtask 79-31-00-860-050-A A.

4.

Not Applicable

Procedure Subtask 79-31-00-210-055-A A.

Do a visual inspection of the engine oil system to check the leakage (Ref. AMM TASK 79-00-00-210810)

Subtask 79-31-00-610-050-A B. 5.

Do a check of the oil level in the tank and fill it to the correct level if necessary (Ref. AMM TASK 79-0000-610-801) .

Close-up Subtask 79-31-00-860-051-A A.

Make an applicable entry in the log book.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 79-35-00-040-802-A - Engine Oil Filter Change and Magnetic Chip Detector Inspection

** ON A/C 301-349, 351-450, 500-600 TASK 79-35-00-040-802-A Engine Oil Filter Change and Magnetic Chip Detector Inspection 1.

Reason for the Job MMEL 79-09-02A ENG 1(2) OIL FILTER CLOG Alert MMEL 79-09-04B ENG 1(2) OIL FILTER DEGRAD Alert MMEL 79-09-05B ENG 1(2) OIL SENSOR FAULT Alert

2

Job Set-up Information A.

Referenced Information REFERENCE (Ref. 79-00-00-281-802-A). (Ref. 79-21-06-960-801-A).

3.

DESIGNATION Inspection of the Magnetic Chip Collectors for Oil Contamination Replacement of the Oil Filter Element

Job Set-up Subtask 79-35-00-860-050-A A.

4.

Non Applicable

Procedure Subtask 79-35-00-960-050-A A.

Do the replacement of the Oil Filter Element (Ref. AMM TASK 79-21-06-960-801)

Subtask 79-35-00-281-050-A B. 5.

Do the oil analysis of the Magnetic Chip Collector (Ref. AMM TASK 79-00-00-281-802)

Close-up Subtask 79-35-00-860-054-A A.

Aircraft Maintenance Configuration (1) Make an entry in the logbook to record that the Oil Filter element has been changed and the Magnetic Chip Detector inspected

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 79-35-00-040-803-A - Engine Oil Filter Change and Magnetic Chip Detector Operation Check

** ON A/C 301-349, 351-450, 500-600 TASK 79-35-00-040-803-A Engine Oil Filter Change and Magnetic Chip Detector Operation Check 1.

Reason for the Job MMEL 79-09-02D ENG 1(2) OIL FILTER CLOG Alert MMEL 79-09-04C ENG 1(2) OIL FILTER DEGRAD Alert MMEL 79-09-05C ENG 1(2) OIL SENSOR FAULT Alert

2

Job Set-up Information A.

Referenced Information REFERENCE (Ref. 79-21-06-960-801-A). (Ref. 79-22-01-720-801-A).

3.

DESIGNATION Replacement of the Oil Filter Element Functional Test of the Magnetic Chip Collectors

Job Set-up Subtask 79-35-00-860-051-A A.

4.

Non Applicable

Procedure Subtask 79-35-00-960-051-A A.

Do the replacement of the Oil Filter Element (Ref. AMM TASK 79-21-06-960-801)

Subtask 79-35-00-720-051-A B. 5.

Do the functional test of the Magnetic Chip Collectors (Ref. AMM TASK 79-22-01-720-801)

Close-up Subtask 79-35-00-860-055-A A.

Aircraft Maintenance Configuration (1) Make an entry in the logbook to record that the Oil Filter element has been changed and the Magnetic Chip Detector checked

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 79-35-00-040-804-A - Magnetic Chip Detector Inspection

** ON A/C 301-349, 351-450, 500-600 TASK 79-35-00-040-804-A Magnetic Chip Detector Inspection 1.

Reason for the Job MMEL 79-09-02E ENG 1(2) OIL FILTER CLOG Alert

2

Job Set-up Information A.

Referenced Information REFERENCE (Ref. 79-00-00-281-802-A).

3.

DESIGNATION Inspection of the Magnetic Chip Collectors for Oil Contamination

Job Set-up Subtask 79-35-00-860-052-A A.

4.

Non Applicable

Procedure Subtask 79-35-00-200-051-A A.

5.

Do the Magnetic Chip Detector Inspection (Ref. AMM TASK 79-00-00-281-802)

Close-up Subtask 79-35-00-860-056-A A.

Aircraft Maintenance Configuration (1) Make an entry in the logbook to record that the Magnetic Chip Detector has been inspected

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 79-35-00-040-805-A - Magnetic Chip Detector Operational Test

** ON A/C 301-349, 351-450, 500-600 TASK 79-35-00-040-805-A Magnetic Chip Detector Operational Test 1.

Reason for the Job MMEL 79-09-02F ENG 1(2) OIL FILTER CLOG Alert

2

Job Set-up Information A.

Referenced Information REFERENCE (Ref. 79-22-01-720-801-A).

3.

DESIGNATION Functional Test of the Magnetic Chip Collectors

Job Set-up Subtask 79-35-00-860-053-A A.

4.

Non Applicable

Procedure Subtask 79-35-00-710-051-A A.

5.

Do the Magnetic Chip Detector Operational Test (Ref. AMM TASK 79-22-01-720-801)

Close-up Subtask 79-35-00-860-057-A A.

Aircraft Maintenance Configuration (1) Make an entry in the logbook to record that the Magnetic Chip Detector has been operationally tested

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 1

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-044-A - Check of the Starter Valve Manual Handle Position after Engine Start

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 TASK 80-11-00-040-044-A Check of the Starter Valve Manual Handle Position after Engine Start

FIN : 1000EM1 , 1000EM2 1.

Reason for the Job MMEL 80-07-01A Start Valve Position Indication on the ENGINE SD page

2

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 438CR FOR 1000EM2 (ENGINE-2) 448CR

B.

ZONE DESCRIPTION

Referenced Information REFERENCE DESIGNATION Starter Valve Access Panel SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-044-A - Check of the Starter Valve Manual Handle Position after Engine Start

448CR (438CR)

N_MM_801100_4_RAM0_01_00

Figure 80(CFMB)-11-00-991-30000-06-A / SHEET 1/1 - Starter Valve Access Panel ** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-044-A - Check of the Starter Valve Manual Handle Position after Engine Start

3.

Job Set-up (Ref. Fig. Starter Valve Access Panel SHEET 1) Subtask 80-11-00-010-050-A A.

Open the access door on fan cowl : (1) FOR 1000EM1 (ENGINE-1) 438CR (2) FOR 1000EM2 (ENGINE-2) 448CR

4.

Procedure Subtask 80-11-00-210-050-A A.

5.

After engine start cycle check on starter valve that the manual handle is in closed position.

Close-up Subtask 80-11-00-410-050-A A.

Close the access door on fan cowl (1) FOR 1000EM1 (ENGINE-1) 438CR (2) FOR 1000EM2 (ENGINE-2) 448CR

Subtask 80-11-00-941-050-A B.

Safety Precautions (1) Tell the crew to make an entry in the log book.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-045-A - Manually Operate the Starter Valve

** ON A/C 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 TASK 80-11-00-040-045-A Manually Operate the Starter Valve

FIN : 1000EM1 , 1000EM2 1.

Reason for the Job MMEL 80-11-01A Start Valve

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 438CR FOR 1000EM2 (ENGINE-2) 448CR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 71-00-00-710-003-B). (Ref. 80-11-00-040-044-A). 3.

DESIGNATION Engine Automatic Start Check of the Starter Valve Manual Handle Position after Engine Start

Job Set-up Subtask 80-11-00-010-051-A A.

Open the access door : (1) FOR 1000EM1 (ENGINE-1) 438CR (2) FOR 1000EM2 (ENGINE-2) 448CR

4.

Procedure Subtask 80-11-00-869-050-A A.

Manual Control of the Starter Valve. WARNING: BE CAREFUL WHEN YOU OPERATE THE STARTER SHUTOFF VALVE WITH THE ENGINE RUNNING. OBEY THE SAFETY PRECAUTIONS.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-045-A - Manually Operate the Starter Valve

CAUTION:

DO NOT OPERATE THE MANUAL HANDLE OF THE PNEUMATIC STARTER VALVE IF THE STARTER SYSTEM IS NOT PRESSURIZED. IF YOU DO, DAMAGE TO THE PNEUMATIC STARTER VALVE CAN OCCUR.

(1) Perform an engine start (Ref. AMM TASK 71-00-00-710-003) by operating the starter valve manually (Ref. FCOM PRO-SUP-70). (2) After engine start cycle, check on starter valve that manual handle is in closed position (Ref. AMM TASK 80-11-00-040-044) . If not manually close the starter shutoff valve. 5.

Close-up Subtask 80-11-00-410-051-A A.

Close the access door on fan cowl : (1) FOR 1000EM1 (ENGINE-1) 438CR (2) FOR 1000EM2 (ENGINE-2) 448CR

Subtask 80-11-00-941-051-A B.

Safety Precautions (1) Install a WARNING NOTICE(S) in the cockpit to tell the persons that the pneumatic starter valve system is inoperative. (2) Tell the crew to make an entry in the log book

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 2

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-042-A - Start Valve Position Indication - Position Check

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 TASK 80-11-00-040-042-A Start Valve Position Indication - Position Check

FIN : 1000EM1 , 1000EM2 1.

Reason for the Job MMEL 80-07-01A Start Valve Position Indication on the ENGINE SD page

2

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 437AL, 438AR, 438BR FOR 1000EM2 (ENGINE-2) 447AL, 448AR, 448BR

B.

ZONE DESCRIPTION

Referenced Information REFERENCE DESIGNATION (Ref. 71-13-00-010-010-A). Opening of the Fan Cowls 437AL(447AL),438AR(448AR) (Ref. 71-13-00-410-010-A). Closing of the Fan Cowls 437AL(447AL),438AR(448AR) Doors SHEET 1 Pneumatic and Valve System SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-042-A - Start Valve Position Indication - Position Check

A

A

438 AR (448 AR) 438 BR (448 BR) N_MM_801100_4_XAM0_01_00

Figure 80(IAE)-11-00-991-90200-13-A / SHEET 1/1 - Doors ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-042-A - Start Valve Position Indication - Position Check

A

A

EXTENSION FOR 0.375 IN SQUARE SOCKET

CONNECTOR 4005KS - A

N_MM_801100_4_XCM0_01_00

Figure 80(IAE)-11-00-991-90300-13-A / SHEET 1/1 - Pneumatic and Valve System ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-042-A - Start Valve Position Indication - Position Check

3.

Job Set-up Subtask 80-11-00-010-054-A A.

Get Access (1) Open access door on right fan cowl doors (Ref. AMM TASK 71-13-00-010-010) (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR. 438BR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR. 448BR

4.

Procedure (Ref. Fig. Doors SHEET 1) (Ref. Fig. Pneumatic and Valve System SHEET 1) Subtask 80-11-00-210-051-A A.

5.

After the engine start cycle, check on the starter valve that the manual handle is in the closed position.

Close-up Subtask 80-11-00-410-054-A A.

Close Access (1) Close access door on the cowl doors (Ref. AMM TASK 71-13-00-410-010) . (a) FOR 1000EM1 (ENGINE-1) 437AL, 438AR, 438BR (b) FOR 1000EM2 (ENGINE-2) 447AL, 448AR, 448BR.

Subtask 80-11-00-941-054-A B.

Indicating system (1) Tell the crew to make an entry in the log book to record the check on the starter that the manual handle is in the closed position.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 4

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-043-A - Starter Valve - Manual Control

** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235235, 237-240, 242-250, 350-350 TASK 80-11-00-040-043-A Starter Valve - Manual Control

FIN : 1000EM1 , 1000EM2 1.

Reason for the Job MMEL 80-11-01A Start Valve

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION AR WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 438BR FOR 1000EM2 (ENGINE-2) 448BR

ZONE DESCRIPTION

C. Referenced Information REFERENCE (Ref. 71-00-00-860-012-A). Doors SHEET 1

DESIGNATION Engine Safety Precautions

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-043-A - Starter Valve - Manual Control

A

A

438 AR (448 AR) 438 BR (448 BR) N_MM_801100_4_XAM0_01_00

Figure 80(IAE)-11-00-991-90200-13-A / SHEET 1/1 - Doors ** ON A/C 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-043-A - Starter Valve - Manual Control

3.

Job Set-up Subtask 80-11-00-010-055-A A.

Get Access (1) Open access door: (a) FOR 1000EM1 (ENGINE-1) 438BR (b) FOR 1000EM2 (ENGINE-2) 448BR

Subtask 80-11-00-860-050-A B. 4.

For starter motor keep away zone refer to (Ref. AMM TASK 71-00-00-860-012) .

Procedure (Ref. Fig. Doors SHEET 1) Subtask 80-11-00-210-052-A A.

Start the Engine: CAUTION:

DO NOT OPERATE THE MANUAL HANDLE OF THE PNEUMATIC STARTER VALVE IF THE STARTER SYSTEM IS NOT PRESSURIZED. IF YOU DO, DAMAGE TO THE PNEUMATIC STARTER VALVE CAN OCCUR.

(1) Start the engine by operating manually the pneumatic starter valve through the access door with 0.375 in. (9.5 mm) square drive. (2) After engine start cycle, position the pneumatic starter valve manually in closed position (clockwise). 5.

Close-up Subtask 80-11-00-410-055-A A.

Close Access (1) Close the access door on fan cowl: (a) FOR 1000EM1 (ENGINE-1) 438BR. (b) FOR 1000EM2 (ENGINE-2) 448BR.

Subtask 80-11-00-941-055-A B.

Indicating system (1) Install WARNING NOTICE(S) in the cockpit to tell persons that the pneumatic starter valve system does not operate. (2) Tell the crew to make an entry in the log book to record the position of the pneumatic starter valve.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-803-A - Starter Air Control Valve Manual Override

** ON A/C 301-349, 351-450, 500-600 TASK 80-11-00-040-803-A Starter Air Control Valve Manual Override 1.

Reason for the Job MMEL 80-11-01A Start Valve

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION 1 DRIVE 3/8 IN - SQUARE

Referenced Information REFERENCE DESIGNATION Starter Air Control Valve Manual Override SHEET 1 MCDU Screen

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-803-A - Starter Air Control Valve Manual Override

A

SAV MANUAL STARTER OVERRIDE ACCESS PORT

A

N_MM_801100_4_QAA0_01_00

Figure 80(PW11)-11-00-991-90400-21-A / SHEET 1/1 - Starter Air Control Valve Manual Override ** ON A/C 301-349, 351-450, 500-600 | EMB SB 73-1108 for A/C 301-307, 309-313 | EMB SB 73-1109 for A/C 301-314 | EMB SB 73-1111 for A/C 301314 | EMB SB 73-1122 for A/C 301-325 | EMB SB 73-1123 for A/C 301-336 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-803-A - Starter Air Control Valve Manual Override

FM 1

IND

RDY

FM 2

EIUi S P E C I F I C

< D I SCRE T E

D A T A

I NP U T S

< D I SCRE T E OU T P U T S S I MU L . < S A V MAN U A L OVERR I DE

RE T URN

NEXT PAGE

PR I N T

PREV PAGE

SEE SHEET 2 OR SEE SHEET 3

N_MM_801100_4_QAB0_01_00

Figure 80(PW11)-11-00-991-91000-21-D / SHEET 1/5 - MCDU Screen ** ON A/C 301-349, 351-450, 500-600 | EMB SB 73-1108 for A/C 301-307, 309-313 | EMB SB 73-1109 for A/C 301-314 | EMB SB 73-1111 for A/C 301314 | EMB SB 73-1122 for A/C 301-325 | EMB SB 73-1123 for A/C 301-336 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-803-A - Starter Air Control Valve Manual Override

SEE SHEET 1

FM 1

IND

RDY

FM 2

E NG x S A V M A NUA L

1/ 1

OV ERR I D E

S T A R T V A L V E CAN B E MAN U A L L Y OP E N

RE T URN

NEXT PAGE

PR I N T

PREV PAGE

N_MM_801100_4_QAB0_02_00

Figure 80(PW11)-11-00-991-91000-21-D / SHEET 2/5 - MCDU Screen ** ON A/C 301-349, 351-450, 500-600 | EMB SB 73-1108 for A/C 301-307, 309-313 | EMB SB 73-1109 for A/C 301-314 | EMB SB 73-1111 for A/C 301314 | EMB SB 73-1122 for A/C 301-325 | EMB SB 73-1123 for A/C 301-336 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-803-A - Starter Air Control Valve Manual Override

SEE SHEET 1

FM 1

IND

RDY

FM 2

E NG x S A V M A NUA L

1/ 1

OV ERR I D E

DO NOT OP E N S T A R T V A L V E MAN U A L L Y B E F ORE 0 8 H OUR S 2 2 M I N

RE T URN

NEXT PAGE

PR I N T

PREV PAGE

N_MM_801100_4_QAB0_03_00

Figure 80(PW11)-11-00-991-91000-21-D / SHEET 3/5 - MCDU Screen ** ON A/C 301-349, 351-450, 500-600 | EMB SB 73-1108 for A/C 301-307, 309-313 | EMB SB 73-1109 for A/C 301-314 | EMB SB 73-1111 for A/C 301314 | EMB SB 73-1122 for A/C 301-325 | EMB SB 73-1123 for A/C 301-336 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-803-A - Starter Air Control Valve Manual Override

FM 1

IND

RDY

FM 2

E NG x S A V M A NUA L

1/ 1

OV ERR I D E

DO NOT OP E N S T A R T V A L V E MAN U A L L Y B E F ORE - - H OUR S - - M I N ( T I ME N OT A V A I L A B L E )

RE T URN

NEXT PAGE

PR I N T

PREV PAGE SEE SHEET 5

N_MM_801100_4_QAB0_04_00

Figure 80(PW11)-11-00-991-91000-21-D / SHEET 4/5 - MCDU Screen ** ON A/C 301-349, 351-450, 500-600 | EMB SB 73-1108 for A/C 301-307, 309-313 | EMB SB 73-1109 for A/C 301-314 | EMB SB 73-1111 for A/C 301314 | EMB SB 73-1122 for A/C 301-325 | EMB SB 73-1123 for A/C 301-336 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-803-A - Starter Air Control Valve Manual Override

SEE SHEET 4

FM 1

IND

RDY

FM 2

E NG x CO L I N G T I ME

1/ 1

0 2M I N 3 1 SE C

RE T URN

NEXT PAGE

PR I N T

PREV PAGE

N_MM_801100_4_QAB0_05_00

Figure 80(PW11)-11-00-991-91000-21-D / SHEET 5/5 - MCDU Screen ** ON A/C 301-349, 351-450, 500-600 | EMB SB 73-1108 for A/C 301-307, 309-313 | EMB SB 73-1109 for A/C 301-314 | EMB SB 73-1111 for A/C 301314 | EMB SB 73-1122 for A/C 301-325 | EMB SB 73-1123 for A/C 301-336 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-803-A - Starter Air Control Valve Manual Override

3.

Job Set-up

** ON A/C 301-349, 351-450, 500-600 EMB SB 73-1108 for A/C 301-307, 309-313 EMB SB 73-1109 for A/C 301-314 EMB SB 73-1111 for A/C 301-314 EMB SB 73-1122 for A/C 301-325 EMB SB 73-1123 for A/C 301-336 Subtask 80-11-00-941-058-A A.

Safety Precautions (1) During the engine start procedure, obey all the engine safety precautions.

** ON A/C 301-349, 351-450, 500-600 CAUTION:

4.

WIPE CLEAN ALL PARTS AND TOOLS AS NECESSARY TO REMOVE UNWANTED DEBRIS AND PREVENT DAMAGE TO THE ENGINE.

Procedure

** ON A/C 301-349, 351-450, 500-600 EMB SB 73-1108 for A/C 301-307, 309-313 EMB SB 73-1109 for A/C 301-314 EMB SB 73-1111 for A/C 301-314 EMB SB 73-1122 for A/C 301-325 EMB SB 73-1123 for A/C 301-336 (Ref. Fig. Starter Air Control Valve Manual Override SHEET 1) Subtask 80-11-00-860-051-D CAUTION:

A.

MAKE SURE THAT YOU WAITED FOR THE TIME SHOWN ON THE MCDU AFTER ENGINE SHUTDOWN BEFORE YOU START THE ENGINE WITH THE MANUAL OVERRIDE. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE ENGINE CAN OCCUR.

Wait the necessary time after engine shutdown. (Ref. Fig. MCDU Screen) (1) On the EIU 1(2)/TEST/SPECIFIC DATA page of the MCDU, select SAV MANUAL OVERRIDE. See the Sheet 1 of the Figure: (Ref. Fig. MCDU Screen) (2) On the ENG 1(2) SAV MANUAL OVERRIDE page, make sure that the START VALVE CAN BE MANUALLY OPEN indication is shown. See the Sheet 2 of the Figure: (Ref. Fig. MCDU Screen) NOTE: The ENG 1(2) SAV MANUAL OVERRIDE page (See the Sheet 3 of the Figure) gives the indication of the time until you can manually open the starter valve. If no indication of time is shown (See the Sheet 4 of the Figure), push the 3R key to know the necessary cooling time (See the Sheet 5 of the Figure). (Ref. Fig. MCDU Screen) When cooling time is NULL, make sure that the start valve can be manually open as described in paragraph 4.B.

Subtask 80-11-00-210-055-A

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-803-A - Starter Air Control Valve Manual Override

B.

Check of the Starter Air Control Valve System (1) If the manual override is permitted on MCDU (See the Sheet 2 of the Figure), find the access port at the three o'clock position on the right thrust reverser inner fixed structure. See the figure: (Ref. Fig. MCDU Screen) (Ref. Fig. Starter Air Control Valve Manual Override SHEET 1) (2) Use the maintenance interphone jack (or alternative mode) and make sure that you can communicate with the cockpit crew from the access port location. (3) Find the DRIVE 3/8 IN - SQUARE (manual override drive) of the starter air control valve through the access port. NOTE: Use a 31.5 in. (0.8 m) or more extension to turn the manual override drive. (4) Make sure that the valve is in the closed position. NOTE: The valve is spring-loaded to the closed position. Rotate the square drive clockwise to CLOSE if required. (5) Obey all the safety instructions and warnings in the engines safety precautions procedure. (6) Start the engine. WARNING: STAY AWAY FROM THE DANGER AREAS AT THE FRONT AND THE SIDES OF THE ENGINE DURING OPERATION. THE SUCTION IS SUFFICIENT AT THE AIR INTAKE COWL TO PULL A PERSON INTO (IN PART OR FULLY) THE ENGINE. THIS CAN KILL A PERSON OR CAUSE A BAD INJURY. (a) Tell the cockpit crew that you are ready for the engine start. (7) When directed by the cockpit crew, turn the manual override counterclockwise to OPEN until you feel the stop. (8) Hold the valve open. (9) When directed by the cockpit crew, allow the valve to return to the closed position. (10) Tell the cockpit crew to make sure that on the ECAM WD, the warning message ENG 1(2) START VALVE FAULT/START VALVE NOT CLOSED does not come into view.

** ON A/C 301-349, 351-450, 500-600 5.

Close-up

** ON A/C 301-349, 351-450, 500-600 EMB SB 73-1108 for A/C 301-307, 309-313 EMB SB 73-1109 for A/C 301-314 EMB SB 73-1111 for A/C 301-314 EMB SB 73-1122 for A/C 301-325 EMB SB 73-1123 for A/C 301-336 Subtask 80-11-00-940-052-A A.

Aircraft Maintenance Configuration (1) Make sure that the work area is clean and clear of tools and other items. (2) Tell the cockpit crew that the valve is closed and that you will now leave the area.

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-803-A - Starter Air Control Valve Manual Override

(3) Tell the cockpit crew to make an entry in the log book to record that valve has been closed. (4) Disconnect the interphone from the intake cowl (if connected) and go away from the engine. (5) Signal to the cockpit crew that you are away from the aircraft.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 10

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-806-A - Check of the Position of the Manual Handle of the Starter Air Control Valve after the Engine Start

** ON A/C 301-349, 351-450, 500-600 TASK 80-11-00-040-806-A Check of the Position of the Manual Handle of the Starter Air Control Valve after the Engine Start

FIN : 4005KS 1.

Reason for the Job MMEL 80-07-01A Start Valve Position Indication on the ENGINE SD page

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific

B.

QTY DESIGNATION 1 DRIVE 3/8 IN - SQUARE 1 EXTENSION

Work Zones and Access Panels ZONE/ACCESS 454 464

ZONE DESCRIPTION HOT SECTION HOT SECTION

C. Referenced Information REFERENCE DESIGNATION Starter Air Control Valve Manual Override SHEET 1

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-806-A - Check of the Position of the Manual Handle of the Starter Air Control Valve after the Engine Start

A

SAV MANUAL STARTER OVERRIDE ACCESS PORT

A

N_MM_801100_4_QAA0_01_00

Figure 80(PW11)-11-00-991-90400-21-A / SHEET 1/1 - Starter Air Control Valve Manual Override ** ON A/C 301-349, 351-450, 500-600 | EMB SB 73-1108 for A/C 301-307, 309-313 | EMB SB 73-1109 for A/C 301-314 | EMB SB 73-1111 for A/C 301314 | EMB SB 73-1122 for A/C 301-325 | EMB SB 73-1123 for A/C 301-336 Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 3

Customer : IGO Manual : AMM Type : A318/A319/A320/A321 Selected applicability : ALL Rev. Date : Aug 01, 2019 80-11-00-040-806-A - Check of the Position of the Manual Handle of the Starter Air Control Valve after the Engine Start

3.

Job Set-up Subtask 80-11-00-941-067-A A.

Safety Precautions (1) During the engine start procedure, obey all the engine safety precautions.

4.

Procedure Subtask 80-11-00-040-056-A A.

Check of the Position of the Manual Handle of the Starter Air Control Valve after the Engine Start (1) Find the access port at the three o'clock position on the right thrust reverser inner fixed structure.

** ON A/C 301-349, 351-450, 500-600 EMB SB 73-1108 for A/C 301-307, 309-313 EMB SB 73-1109 for A/C 301-314 EMB SB 73-1111 for A/C 301-314 EMB SB 73-1122 for A/C 301-325 EMB SB 73-1123 for A/C 301-336 (Ref. Fig. Starter Air Control Valve Manual Override SHEET 1) ** ON A/C 301-349, 351-450, 500-600 (2) Use the maintenance interphone jack (or an alternative) and make sure that you can communicate with the cockpit crew from the access port location. (3) Find the 3/8 in. square drive (manual override drive) of the starter air control valve through the access port. (4) Use a DRIVE 3/8 IN - SQUARE with a 31.5 in. (0.80 m) EXTENSION or more to turn the manual override drive. NOTE: To close the square drive, it is necessary to turn it clockwise. To open the square drive, it is necessary to turn it counterclockwise. (5) Make sure that the valve is in the closed position. NOTE: The valve is spring-loaded to the closed position. (a) Make sure that you cannot rotate the square drive clockwise. (6) Tell the cockpit crew to make sure that on the ECAM WD, the warning message ENG 1(2) START VALVE FAULT/START VALVE NOT CLOSED does not come into view. 5.

Close-up Subtask 80-11-00-869-059-A A.

Aircraft Maintenance Configuration (1) Make sure that the work area is clean and clear of tools and other items. (2) Make an entry in the logbook to record the check of the closed position of the starter manual handle.

End of document

Print Date: September 03, 2019 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 3

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 12-11-28-650-004-A - Pressure Refuel with Manual Control

CUSTOMIZATION

AIRCRAFT TYPES

A318 A319 A321 A320

IGO

DOCTYPES

REVISION DATE

AMM

01-Aug- 12-11-28-650-004-A - Pressure 2019 Refuel with Manual Control

TITLE

TAIL NUMBER MSN - FSN

** ON A/C FSN ALL TASK 12-11-28-650-004-A Pressure Refuel with Manual Control WARNING: OBEY THE FUEL SAFETY PROCEDURES. WARNING: STOP THE FUEL TANKER 60 m (196.85 ft) FROM THE AIRCRAFT NOSE WHILE THE WEATHER RADAR OPERATES. DO NOT OPERATE THE FUEL TANKER/PUMP UNIT UNTIL YOU STOP THE OPERATION OF THE WEATHER RADAR. WARNING: MAKE SURE THE AREA AROUND THE AIRCRAFT IS SAFE BEFORE YOU START THE REFUEL/DEFUEL PROCEDURE. IN THE SAFETY AREA, DO NOT: SMOKE MAKE SPARKS OR FIRE USE ANY EQUIPMENT WHICH IS NOT APPROVED FOR REFUEL/DEFUEL PROCEDURES. AIRCRAFT FUEL IS FLAMMABLE. WARNING: DO NOT SPILL FUEL ON THE ENGINES OR THE BRAKES. IF YOU SPILL FUEL ON ENGINES OR BRAKES THAT ARE HOT, IT CAN CAUSE FIRES. 1.

Reason for the Job NOTE: It is recommended that you keep to one type of fuel. Although approved types can be mixed if necessary to continue operation. Refer to Section 2 of your Flight Manual (Ref. FM Section 2) for a complete list of approved fuels. Refer to Airbus Cold Weather Operations Information and Operations Policy Fueling Procedures for safety precautions with mixed fuel.

2.

Job Set-up Information A.

Referenced Information REFERENCE

DESIGNATION

Ref. 12-34-24-869-001-A

Aircraft Bonding and Grounding (Earthing) for the Refuel/Defuel or Oxygen Servicing Operations

Ref. 24-41-00-861-002-A

Energize the Aircraft Electrical Circuits from the External Power

Ref. 24-41-00-861-002-A01

Energize the Aircraft Electrical Circuits from the APU

Ref. 24-41-00-861-002-A02

Energize the Aircraft Electrical Circuits from Engine 1(2)

** ON A/C FSN 401-450 Ref. 24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

Ref. 24-41-00-862-002-A01

De-energize the Aircraft Electrical Circuits Supplied from the APU

Ref. 24-41-00-862-002-A02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 12-11-28-650-004-A - Pressure Refuel with Manual Control

REFERENCE

DESIGNATION

** ON A/C FSN ALL Ref. 28-25-00-650-001-A

Pressure Defuel

Ref. 28-25-00-869-001-A

Fuel Transfer

Ref. 31-60-00-860-001-A

EIS Start Procedure

Ref. 31-60-00-860-002-A

EIS Stop Procedure

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-203, 205-250, 350-350 Ref. Fig. Refuel/Defuel Control Panel 800VU, Preselector 5QT and Indicator 6QT

** ON A/C FSN 016-022, 024-100, 112-150, 203-205, 208-208, 210-221, 223226, 229-235, 237-240, 242-250, 301-450, 500-600 Ref. Fig. Refuel Safety Area Ref. Fig. Refuel/Defuel Coupling

** ON A/C FSN 201-201, 206-207, 209-209, 222-222, 227-228, 236-236, 241-241 Ref. Fig. Refuel Safety Area Ref. Fig. Refuel/Defuel Coupling

** ON A/C FSN 204-204 Ref. Fig. Refuel/Defuel Control Panel 800VU, Preselector 5QT and Indicator 6QT

** ON A/C FSN 301-349, 351-400, 416-450, 500-600 Ref. Fig. Refuel/Defuel Control Panel 800VU and 801VU, Preselector 5QT and Indicator 6QT

** ON A/C FSN ALL 3.

Job Set-up

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-203, 205-250, 350-350 EMB SB 31-1211 for A/C 219-220

Ref. Fig. Refuel/Defuel Control Panel 800VU, Preselector 5QT and Indicator 6QT

** ON A/C FSN 016-022, 024-100, 112-150, 203-205, 208-208, 210-221, 223-226, 229-235, 237-240, 242-250, 301-450, 500-600 Ref. Fig. Refuel Safety Area Ref. Fig. Refuel/Defuel Coupling

** ON A/C FSN 201-201, 206-207, 209-209, 222-222, 227-228, 236-236, 241-241 EMB SB 28-1030 for A/C 209-209 Ref. Fig. Refuel Safety Area Ref. Fig. Refuel/Defuel Coupling

** ON A/C FSN 204-204

Ref. Fig. Refuel/Defuel Control Panel 800VU, Preselector 5QT and Indicator 6QT

** ON A/C FSN 301-349, 351-400, 416-450, 500-600

Ref. Fig. Refuel/Defuel Control Panel 800VU and 801VU, Preselector 5QT and Indicator 6QT

** ON A/C FSN ALL SUBTASK 12-11-28-941-052-A DELETED SUBTASK 12-11-28-941-052-B DELETED SUBTASK 12-11-28-281-052-A A. Drain the Water from the Fuel (1) Make sure that a fuel sampling for water contamination check is done to the fuel in the fuel tanker/pump unit.

** ON A/C FSN 016-022, 024-100, 112-150, 203-205, 208-208, 210-221, 223-226, 229-235, 237-240, 242-250, 301-450, 500-600 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 2/17

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 12-11-28-650-004-A - Pressure Refuel with Manual Control

SUBTASK 12-11-28-860-053-A B. Aircraft Maintenance Configuration WARNING: MAKE SURE THAT THE FUEL SUPPLY HOSE IS CORRECTLY CONNECTED TO THE COUPLING BEFORE YOU REFUEL/DEFUEL THE AIRCRAFT. DO NOT CONNECT THE FUEL SUPPLY HOSE IF THERE ARE SIGNS OF DAMAGE TO THE AIRCRAFT COUPLING LUGS OR SLOTS. WARNING: MAKE SURE THAT YOU BOND THE FUEL TANKER TO THE AIRCRAFT. IF YOU DO NOT, AN ELECTRICAL DISCHARGE CAN OCCUR WHICH CAN CAUSE AN EXPLOSION OR FIRE. (1) Obey the local regulations for grounding (earthing) the aircraft. If you must ground (earth) the aircraft: Ground (earth) the fuel tanker and the aircraft correctly Ref. AMM TASK 12-3424-869-001.

(2) (3) (4) (5) (6) (7)

NOTE: You must bond the fuel tanker to the aircraft. Obey the local regulations for grounding (earthing). Bond the fuel tanker to the aircraft Ref. AMM TASK 12-34-24-869-001. Remove the refuel coupling cap 41QM. Make sure that the coupling of the fuel-supply hose is clean, then connect it to the aircraft refuel coupling. Energize the aircraft electrical circuits Ref. AMM TASK 24-41-00-861-002. Do the Electronic Instrument System (EIS) (Electronic Centralized Aircraft Monitoring - ECAM only) start procedure Ref. AMM TASK 31-60-00-860-001. On the panel 11VU, push (in) the FUEL pushbutton switch.

** ON A/C FSN 201-201, 206-207, 209-209, 222-222, 227-228, 236-236, 241-241 EMB SB 28-1030 for A/C 209-209 SUBTASK 12-11-28-860-053-B B. Aircraft Maintenance Configuration WARNING: MAKE SURE THAT THE FUEL SUPPLY HOSE IS CORRECTLY CONNECTED TO THE COUPLING BEFORE YOU REFUEL/DEFUEL THE AIRCRAFT. DO NOT CONNECT THE FUEL SUPPLY HOSE IF THERE ARE SIGNS OF DAMAGE TO THE AIRCRAFT COUPLING LUGS OR SLOTS. WARNING: MAKE SURE THAT YOU BOND THE FUEL TANKER TO THE AIRCRAFT. IF YOU DO NOT, AN ELECTRICAL DISCHARGE CAN OCCUR WHICH CAN CAUSE AN EXPLOSION OR FIRE. (1) Obey the local regulations for grounding (earthing) the aircraft. If you must ground (earth) the aircraft: Ground (earth) the fuel tanker and the aircraft correctly Ref. AMM TASK 12-3424-869-001.

(2) (3) (4) (5) (6)

NOTE: You must bond the fuel tanker to the aircraft. Obey the local regulations for grounding (earthing). Bond the fuel tanker to the aircraft Ref. AMM TASK 12-34-24-869-001. Remove the applicable refuel coupling cap 101QM(41QM). Make sure that the coupling of the fuel supply-hose is clean, then connect it to the aircraft refuel coupling. If you have external power available, energize the aircraft electrical circuits Ref. AMM TASK 24-41-00-861-002. If you have external power available: do the EIS (ECAM only) start procedure Ref. AMM TASK 31-60-00-860-001 on the panel 11VU, push (in) the FUEL pushbutton switch.

** ON A/C FSN ALL SUBTASK 12-11-28-010-053-A C. Get Access (1) Open the access door 192MB. NOTE: If operating in battery power: put the MODE SELECT switch to the OFF and guarded position do not keep the door open longer than necessary because the battery can discharge. © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 3/17

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 12-11-28-650-004-A - Pressure Refuel with Manual Control

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 SUBTASK 12-11-28-860-057-A D. Aircraft Maintenance Configuration (1) If you do not have ground power available: WARNING: WHEN YOU REFUEL THE AIRCRAFT WITH BATTERY POWER, IT IS NOT ALWAYS POSSIBLE TO REFUEL TO FULL CAPACITY. THIS IS BECAUSE THE INTERCELL TRANSFER VALVES ARE NOT ALWAYS IN THE CORRECT POSITION. (a) On the refuel/defuel control panel (800VU), put the BATT POWER switch to the ON position and release. NOTE: The HOT BUSS 701PP is energized for ten minutes only (this is to prevent discharge of the aircraft batteries), unless you put the MODE SELECT switch (on the refuel/defuel panel) to REFUEL.

** ON A/C FSN 401-450

SUBTASK 12-11-28-860-057-B D. Aircraft Maintenance Configuration (1) If you do not have ground power available: (a)

On the refuel/defuel control panel (800VU), put the BATT POWER switch to the ON position and release. NOTE: The HOT BUSS 701PP is energized for ten minutes only (this is to prevent discharge of the aircraft batteries), unless you put the MODE SELECT switch (on the refuel/defuel panel) to REFUEL.

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 416-450, 500-600 SUBTASK 12-11-28-740-051-A E. Test of the Refuel Panel 800VU (1) Do this test: ACTION

RESULT

1.On the panel 800VU:

On the panel 800VU:

-

-

put the TEST switch to the LTS position and hold it there

-

release the TEST switch

-

the High (HI) Level (LVL) lights and the DEFUEL/XFR OPEN lights are on and the CKPT and END lights come on the FUEL QTY, PRESELECTED and ACTUAL displays show all 8's. the lights go back to their initial condition the FUEL QTY, PRESELECTED and ACTUAL displays go back to their initial condition

-

put the TEST switch to the HIGH position and hold it there

-

the HI LVL lights change their condition. If they were on, they will go off. If they were off, they will come on

-

release the TEST switch.

-

the HI LVL lights go back to their initial condition.

** ON A/C FSN 401-415 SUBTASK 12-11-28-740-051-C E. Test of the Refuel Panel 800VU and 801VU NOTE: The HI LVL lights of the ACTs that are not installed will not come on during this test. (1) Do this test: ACTION

RESULT

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

4/17

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 12-11-28-650-004-A - Pressure Refuel with Manual Control

ACTION On the panel 800VU: put the TEST switch to the LTS position and hold it there

RESULT On the panels 800VU and 801VU: the HI LVL lights, the DEFUEL XFR OPEN light and the AFMS FAULT light come on. On the preselector 5QT: the PRESELECTED and ACTUAL displays show all eights the CKPT and END lights come on. On the indicator 6QT: the FUEL QTY displays show all eights.

-

release the TEST switch.

On the panels 800VU and 801VU: the HI LVL lights, the DEFUEL XFR OPEN light and the AFMS FAULT light go off. On the preselector 5QT: the CKPT and END lights go off the PRESELECTED and ACTUAL displays show the tank quantities. On the indicator 6QT: the FUEL QTY displays show the tank quantities.

** ON A/C FSN ALL WARNING: MAKE SURE THAT YOU DO THE REFUEL PANEL TEST BEFORE THE REFUEL PROCEDURE OR BEFORE THE FUEL TANK IS 70 PERCENT FULL. DEFECTIVE HIGHLEVEL SENSORS CAN CAUSE FUEL TO SPILL OVERBOARD. 4. Procedure

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-203, 205-250, 350-350 EMB SB 31-1211 for A/C 219-220

Ref. Fig. Refuel/Defuel Control Panel 800VU, Preselector 5QT and Indicator 6QT

** ON A/C FSN 016-022, 024-100, 112-150, 203-205, 208-208, 210-221, 223-226, 229-235, 237-240, 242-250, 301-450, 500-600 Ref. Fig. Refuel/Defuel Coupling

** ON A/C FSN 201-201, 206-207, 209-209, 222-222, 227-228, 236-236, 241-241 EMB SB 28-1030 for A/C 209-209 Ref. Fig. Refuel/Defuel Coupling

** ON A/C FSN 204-204

Ref. Fig. Refuel/Defuel Control Panel 800VU, Preselector 5QT and Indicator 6QT

** ON A/C FSN 301-349, 351-400, 416-450, 500-600

Ref. Fig. Refuel/Defuel Control Panel 800VU and 801VU, Preselector 5QT and Indicator 6QT

** ON A/C FSN 016-022, 024-094, 112-150, 201-201, 203-250, 350-350 SUBTASK 12-11-28-650-054-B WARNING: BEFORE YOU DO THIS REFUEL PROCEDURE, MAKE SURE THAT: ALL THE FUEL PUMPS ARE OFF, OR THE FUEL PUMPS ARE ON WITH MODE SEL PUSHBUTTON-SWITCH 48QA IN THE AUTO POSITION. IF THE FUEL PUMPS ARE ON AND MODE SEL PUSHBUTTON-SWITCH 48QA IS NOT IN THE AUTO POSITION, THERE IS A RISK THAT FUEL WILL SPILL. CAUTION: BEFORE YOU START THE WING TANK PUMPS, MAKE SURE THAT: THERE IS A MINIMUM OF 750 KG (1653 LB) OF FUEL IN THE APPLICABLE WING TANKS THE MODE SEL PUSHBUTTON SWITCH 48QA IS IN THE AUTO

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 12-11-28-650-004-A - Pressure Refuel with Manual Control

POSITION. THIS WILL PREVENT DRY RUNNING AND SUBSEQUENT DAMAGE TO THE WING AND CENTER TANK PUMPS. CAUTION: BEFORE YOU CLOSE THE CROSSFEED VALVE, MAKE SURE THAT THE FUEL PUMP(S) IS(ARE) OFF. THIS WILL PREVENT DAMAGE TO THE CROSSFEED VALVE. A. Pressure Refuel with Manual Control NOTE: If it becomes necessary, defuel Ref. AMM TASK 28-25-00-650-001 or transfer fuel Ref. AMM TASK 28-25-00-869-001. (1) To prevent a fuel spill, on the panel 40VU, make sure that: X FEED P/BSW 4QE is released out (OFF) MODE SEL P/BSW 48QA is in the AUTO position CTR TK PUMP 1 & 2 P/BSW are released out (OFF). (2) On the refuel/defuel control panel 800VU: (a)

Put the MODE SELECT switch to the REFUEL position.

(b)

Put the REFUEL VALVES switch(es) for the applicable fuel tank(s) to the OPEN position.

(c) (3) (4)

Put the REFUEL VALVES switch(es) for the tank(s) which will not be refueled to the SHUT position. Before refuel, record actual fuel quantity indicated on preselector 5QT and fuel tanker. When refuel is complete do a discrepancy check. Start the pump on the fuel tanker/pump unit.

CAUTION: DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM PRESSURE OF 50 PSI (3.45 BARS). IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE AIRCRAFT OR EQUIPMENT CAN OCCUR. (5) On the refuel/defuel control panel 800VU: (a)

Make sure that the numbers on the ACTUAL and the FUEL QTY displays increase.

(b)

Monitor the FUEL QTY displays. NOTE: Refer to the fuel tables for the maximum capacity of each fuel tank and for the total fuel capacity. NOTE: If necessary, to dispatch with full fuel load, use the ECAM to make sure the outer cell is full. This will prevent the risk of structural damage.

(c) (6) (7)

When each tank has the correct fuel quantity put its REFUEL VALVE switch to the SHUT position. When the fuel tank quantities are correct stop the pump on the fuel tanker/pump unit. On the refuel/defuel control panel 800VU: (a)

Put the MODE SELECT switch to the OFF position and put the guard on the switch.

(b) (8)

Put the applicable REFUEL VALVES switch(es) to the NORM position and put the guard(s) on the switch(es). If you have ground power available, make sure that the ECAM lower DU shows the correct fuel quantities.

** ON A/C FSN 401-450 SUBTASK 12-11-28-650-054-D WARNING: BEFORE YOU DO THIS REFUEL PROCEDURE, MAKE SURE THAT: ALL THE FUEL PUMPS ARE OFF, OR THE FUEL PUMPS ARE ON WITH MODE SEL PUSHBUTTON-SWITCH 48QA IN THE AUTO POSITION. IF THE FUEL PUMPS ARE ON AND MODE SEL PUSHBUTTON-SWITCH 48QA IS NOT IN THE AUTO POSITION, THERE IS A RISK THAT FUEL WILL SPILL. CAUTION: BEFORE YOU START THE WING TANK PUMPS, MAKE SURE THAT THERE IS A MINIMUM OF 750 KG (1653 LB) OF FUEL IN THE APPLICABLE WING TANKS. © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 12-11-28-650-004-A - Pressure Refuel with Manual Control

THIS WILL PREVENT DRY RUNNING AND SUBSEQUENT DAMAGE TO THE FUEL PUMPS. CAUTION: BEFORE YOU CLOSE THE CROSSFEED VALVE, MAKE SURE THAT THE FUEL PUMP(S) IS(ARE) OFF. THIS WILL PREVENT DAMAGE TO THE CROSSFEED VALVE. A. Pressure Refuel with Manual Control NOTE: If it becomes necessary, defuel Ref. AMM TASK 28-25-00-650-001 or transfer fuel Ref. AMM TASK 28-25-00-869-001. (1) To prevent a fuel spill, on the panel 40VU, make sure that: X FEED P/BSW 4QE is released out (OFF) MODE SEL P/BSW 48QA is in the AUTO position the CTR TK L and R XFR P/BSW are released out (OFF). (2) On the refuel/defuel control panel 800VU: (a)

Put the MODE SELECT switch to the REFUEL position.

(b)

Put the REFUEL VALVES switch(es) for the applicable fuel tank(s) to the OPEN position.

(c) (3) (4)

Put the REFUEL VALVES switch(es) for the tank(s) which will not be refueled to the SHUT position. Before refuel, record actual fuel quantity indicated on preselector 5QT and fuel tanker. When refuel is complete do a discrepancy check. Start the pump on the fuel tanker/pump unit.

CAUTION: DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM PRESSURE OF 50 PSI (3.45 BARS). IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE AIRCRAFT OR EQUIPMENT CAN OCCUR. (5) On the refuel/defuel control panel 800VU: (a)

Make sure that the numbers on the ACTUAL and the FUEL QTY displays increase.

(b)

Monitor the FUEL QTY displays. NOTE: Refer to the fuel tables for the maximum capacity of each fuel tank and for the total fuel capacity.

(c) (6) (7)

When each tank has the correct fuel quantity put its REFUEL VALVE switch to the SHUT position. When the fuel tank quantities are correct stop the pump on the fuel tanker/pump unit. On the refuel/defuel control panel 800VU: (a)

Put the MODE SELECT switch to the OFF position and put the guard on the switch.

(b) (8)

Put the applicable REFUEL VALVES switch(es) to the NORM position and put the guard(s) on the switch(es). If you have ground power available, make sure that the ECAM lower DU shows the correct fuel quantities.

** ON A/C FSN 095-100, 301-349, 351-400, 500-600 SUBTASK 12-11-28-650-054-E CAUTION: BEFORE YOU START THE WING TANK PUMPS, MAKE SURE THAT THERE IS A MINIMUM OF 750 KG (1653 LB) OF FUEL IN THE APPLICABLE WING TANKS. THIS WILL PREVENT DRY RUNNING AND SUBSEQUENT DAMAGE TO THE FUEL PUMPS. CAUTION: BEFORE YOU DO THIS REFUEL PROCEDURE, MAKE SURE THAT: ALL THE FUEL PUMPS ARE OFF, OR THE FUEL PUMPS ARE ON WITH THE MODE SEL PUSHBUTTON SWITCH 4QL IN THE AUTO POSITION. IF THE FUEL PUMPS ARE ON AND THE MODE SEL PUSHBUTTON SWITCH 4QL IS NOT IN THE AUTO POSITION, THERE IS A RISK THAT FUEL WILL SPILL. CAUTION: BEFORE YOU CLOSE THE CROSSFEED VALVE, MAKE SURE THAT THE FUEL © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

7/17

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 12-11-28-650-004-A - Pressure Refuel with Manual Control

A.

PUMP(S) IS(ARE) OFF. THIS WILL PREVENT DAMAGE TO THE CROSSFEED VALVE. Pressure Refuel with Manual Control NOTE: If it becomes necessary, defuel Ref. AMM TASK 28-25-00-650-001 or transfer fuel Ref. AMM TASK 28-25-00-869-001. (1) To prevent a fuel spill, on the panel 40VU, make sure that: the X FEED P/BSW 4QE is released out (OFF) the MODE SEL P/BSW 4QL is in the AUTO position the CTR TK L and R XFR P/BSW are released out (OFF). (2) On the refuel/defuel control panel 800VU: (a)

Put the MODE SELECT switch to the REFUEL position.

(b)

Put the REFUEL VALVES switch(es) for the applicable fuel tank(s) to the OPEN position.

(c) (3) (4)

Put the REFUEL VALVES switch(es) for the tank(s) which will not be refueled to the SHUT position. Before refuel, record actual fuel quantity indicated on preselector 5QT and fuel tanker. When refuel is complete do a discrepancy check. Start the pump on the fuel tanker/pump unit.

CAUTION: DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM PRESSURE OF 50 PSI (3.45 BARS). IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE AIRCRAFT OR EQUIPMENT CAN OCCUR. (5) On the refuel/defuel control panel 800VU: (a)

Make sure that the numbers on the ACTUAL and the FUEL QTY displays increase.

(b)

Monitor the FUEL QTY displays. NOTE: Refer to the fuel tables for the maximum capacity of each fuel tank and for the total fuel capacity.

(c) (6) (7)

When each tank has the correct fuel quantity put its REFUEL VALVE switch to the SHUT position. When the fuel tank quantities are correct stop the pump on the fuel tanker/pump unit. On the refuel/defuel control panel 800VU: (a)

Put the MODE SELECT switch to the OFF position and put the guard on the switch.

(b) (8)

Put the applicable REFUEL VALVES switch(es) to the NORM position and put the guard(s) on the switch(es). If you have ground power available, make sure that the ECAM lower DU shows the correct fuel quantities.

** ON A/C FSN 401-415 SUBTASK 12-11-28-650-083-D CAUTION: BEFORE YOU START THE WING TANK PUMPS, MAKE SURE THAT THERE IS A MINIMUM OF 750 KG (1653 LB) OF FUEL IN THE APPLICABLE WING TANKS. THIS WILL PREVENT DRY RUNNING AND SUBSEQUENT DAMAGE TO THE FUEL PUMPS. CAUTION: BEFORE YOU DO THIS REFUEL PROCEDURE, MAKE SURE THAT: ALL THE FUEL PUMPS ARE OFF, OR THE FUEL PUMPS ARE ON WITH THE MODE SEL PUSHBUTTON SWITCH 4QL IN THE AUTO POSITION. IF THE FUEL PUMPS ARE ON AND THE MODE SEL PUSHBUTTON SWITCH 4QL IS NOT IN THE AUTO POSITION, THERE IS A RISK THAT FUEL WILL SPILL. CAUTION: BEFORE YOU CLOSE THE CROSSFEED VALVE, MAKE SURE THAT THE FUEL PUMP(S) IS(ARE) OFF. THIS WILL PREVENT DAMAGE TO THE CROSSFEED VALVE. © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

8/17

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 12-11-28-650-004-A - Pressure Refuel with Manual Control

B.

Pressure Refuel with Manual Control (with ACT(s) provision) NOTE: If it becomes necessary, defuel Ref. AMM TASK 28-25-00-650-001 or transfer fuel Ref. AMM TASK 28-25-00-869-001. (1) To prevent a fuel spill, on the panel 40VU, make sure that: the X FEED P/BSW 4QE is released out (OFF) the MODE SEL P/BSW 4QL is in the AUTO position the CTR TK L and R XFR P/BSW are released out (OFF). (2) On the refuel/defuel control panel 800VU/801VU: put the MODE SELECT switch to the REFUEL position put the REFUEL VALVES switch(es) for the applicable fuel tank(s) to the OPEN position put the REFUEL VALVES switches for the tanks which will not be refueled to the SHUT position. (a)

Before refuel, record actual fuel quantity indicated on preselector 5QT and fuel tanker. When refuel is complete do a discrepancy check.

(b)

Start the pump on the fuel tanker/pump unit.

CAUTION: DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM PRESSURE OF 50 PSI (3.45 BARS). IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE AIRCRAFT OR EQUIPMENT CAN OCCUR. (c) On the refuel/defuel control panel 800VU: make sure that the numbers on the ACTUAL and the FUEL QTY displays increase monitor the FUEL QTY displays. (d)

On the refuel/defuel control panel 801VU: set the ACT rotary selector to each applicable ACT in turn make sure that the numbers on the ACT FUEL QTY display increases for each applicable ACT monitor the ACT FUEL QTY display. NOTE: Refer to the fuel tables for the maximum capacity of each fuel tank and for the total fuel capacity.

(e)

When each tank has the correct fuel quantity, put its REFUEL VALVE switch to the SHUT position.

(f)

When the fuel tank quantities are correct, stop the pump on the fuel tanker/pump unit.

(g)

On the refuel/defuel control panel 800VU/801VU: put the MODE SELECT switch to the OFF and guarded position put all the REFUEL VALVES switches to the NORM and guarded position.

(h)

If you have ground power available: make sure that the ECAM lower DU shows the correct total fuel quantities make sure that the fuel indicators on the panel 28VU show the correct quantity for each ACT.

** ON A/C FSN ALL 5.

Close-up

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 SUBTASK 12-11-28-860-058-A A. Aircraft Configuration (1) Make an entry in the aircraft technical log, to check the fuel configuration before the subsequent flight. (2) Do the EIS stop procedure Ref. AMM TASK 31-60-00-860-002. (3) Disconnect the coupling of the fuel supply-hose from the aircraft refuel/defuel coupling. (4) Install the coupling cap. CAUTION: MAKE SURE THAT THE HANDLE OF THE REFUEL COUPLING CAP POINTS AFT WHEN THE CAP IS CLOSED AND LOCKED. (5) Install the refuel coupling cap 41QM.

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

9/17

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 12-11-28-650-004-A - Pressure Refuel with Manual Control

** ON A/C FSN 401-450 SUBTASK 12-11-28-860-058-B A. Aircraft Configuration (1) If you have external power available, do the EIS stop procedure Ref. AMM TASK 3160-00-860-002 then de-energize the aircraft electrical circuits Ref. AMM TASK 24-4100-862-002. (2) Disconnect the coupling of the fuel supply-hose from the aircraft refuel/defuel coupling. (3) Install the coupling cap. CAUTION: MAKE SURE THAT THE HANDLE OF THE REFUEL COUPLING CAP POINTS AFT WHEN THE CAP IS CLOSED AND LOCKED. (4) Install the applicable refuel coupling cap 101QM(41QM).

** ON A/C FSN ALL SUBTASK 12-11-28-410-052-A B. Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access door 192MB. SUBTASK 12-11-28-942-053-A C. Removal of Equipment (1) Disconnect the bonding and grounding (earthing) cables: Between the aircraft and the fuel tanker/pump unit If applicable, between the fuel tanker/pump unit and the ground If applicable, between the aircraft and the ground. (2) Remove the safety barriers. (3) Remove the WARNING NOTICE(S). (4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

10/17

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 12-11-28-650-004-A - Pressure Refuel with Manual Control

192MB

A

A

INDICATOR 6QT

PRESELECTOR 5QT

N_MM_121128_3_AKM0_01_00

Figure 12-11-28-991-00400-00-G (SHEET 1) - Refuel/Defuel Control Panel 800VU, Preselector 5QT and Indicator 6QT ** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-203, 205-250, 350-350 EMB SB 31-1211 for A/C 219-220

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

11/17

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 12-11-28-650-004-A - Pressure Refuel with Manual Control

NOTE: AREA IN FRONT OF THE TANKER MUST BE KEPT CLEAR TO LET THE TANKER MOVE AWAY IN CASE OF AN EMERGENCY. IF THE TANKER CANNOT BE PARKED BELOW THE WING DUE TO ITS SIZE, IT CAN BE PARKED PARALLEL TO THE WING.

15 m (50 ft)

15 m (50 ft)

FUEL TANKER FUEL TANK VENT

15 m (50 ft)

15 m (50 ft) RH REFUEL/ DEFUEL-COUPLING

FUEL TANK VENT

15 m (50 ft)

15 m (50 ft)

NOTE: ALL SAFETY ZONE CLEARANCES CAN CHANGE, REFER TO LOCAL OR AIRPORT REGULATIONS. 3 m (10 ft) FUEL SPILL ZONE AROUND FUEL COUPLINGS AND FUEL TANK VENTS. 3 m (10 ft) EQUIPMENT HAZARD ZONE DURING FUELING. N_MM_121128_3_AAM0_01_02

Figure 12-11-28-991-00100-00-A (SHEET 1) - Refuel Safety Area ** ON A/C FSN 016-022, 024-100, 112-150, 203-205, 208-208, 210-221, 223-226, 229-235, 237-240, 242-250, 301-450, 500-600

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

12/17

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 12-11-28-650-004-A - Pressure Refuel with Manual Control

STA7792/RIB 14 40QM

A STA8268/RIB 15

A LEADING EDGE

WING FRONT SPAR

40QM

41QM

N_MM_121128_3_ACM0_01_00

Figure 12-11-28-991-00200-00-A (SHEET 1) - Refuel/Defuel Coupling ** ON A/C FSN 016-022, 024-100, 112-150, 203-205, 208-208, 210-221, 223-226, 229-235, 237-240, 242-250, 301-450, 500-600

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

13/17

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 12-11-28-650-004-A - Pressure Refuel with Manual Control

RH REFUEL/DEFUEL-COUPLING AND OVERPRESSURE PROTECTOR

15 m (50 ft)

LH REFUEL/DEFUEL-COUPLING AND OVERPRESSURE PROTECTOR 01 OVERPRESSURE PROTECTOR

15 m (50 ft)

FUEL TANKER

15 m (50 ft)

15 m (50 ft) FUEL TANK VENT AND OVERPRESSURE PROTECTOR

FUEL TANK VENT AND OVERPRESSURE PROTECTOR

15 m (50 ft)

15 m (50 ft)

NOTE: ALL SAFETY ZONE CLEARANCES CAN CHANGE, REFER TO LOCAL OR AIRPORT REGULATIONS 01

AREA IN FRONT OF THE TANKER MUST BE KEPT CLEAR TO LET THE TANKER MOVE AWAY IN CASE OF AN EMERGENCY IF THE TANKER CANNOT BE PARKED BELOW THE WING DUE TO ITS SIZE, IT CAN BE PARKED PARALLEL TO THE WING 3 m (10 ft) FUEL SPILL ZONE AROUND FUEL COUPLINGS, FUEL TANK VENTS AND OVERPRESSURE PROTECTORS 3 m (10 ft) EQUIPMENT HAZARD ZONE DURING FUELING N_MM_121128_3_AAM1_01_01

Figure 12-11-28-991-00100-00-B (SHEET 1) - Refuel Safety Area ** ON A/C FSN 201-201, 206-207, 209-209, 222-222, 227-228, 236-236, 241-241 EMB SB 28-1030 for A/C 209-209

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

14/17

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 12-11-28-650-004-A - Pressure Refuel with Manual Control

STA7792/RIB 14 100QM (40QM)

A STA8268/RIB 15

A LEADING EDGE

WING FRONT SPAR

100QM (40QM)

101QM (41QM)

N_MM_121128_3_AEM0_01_00

Figure 12-11-28-991-00200-00-B (SHEET 1) - Refuel/Defuel Coupling ** ON A/C FSN 201-201, 206-207, 209-209, 222-222, 227-228, 236-236, 241-241 EMB SB 28-1030 for A/C 209-209

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

15/17

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 12-11-28-650-004-A - Pressure Refuel with Manual Control

REFUEL DEFUEL CONTROL PANEL 800VU ACCESS DOOR 192MB

A

A

INDICATOR 6QT

PRESELECTOR 5QT

N_MM_121128_3_CVM0_01_00

Figure 12-11-28-991-00400-00-H (SHEET 1) - Refuel/Defuel Control Panel 800VU, Preselector 5QT and Indicator 6QT ** ON A/C FSN 204-204

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 12-11-28-650-004-A - Pressure Refuel with Manual Control

A

192MB

INDICATOR 6QT

FUEL Q T Y kg x 1000

LEFT

RIGHT

CTR

LV L

HI LEFT

RIGHT

CTR

VALVES

REFUEL OPEN

OPEN

OPEN

NORM

NORM

NORM

SHUT

SHUT

TEST

MODE SELECT

HI LVL

REFUEL

SHUT

BATT POWER ON

800VU

OFF

DEFUEL / XFR

OPEN

LT S

NORM

REFUEL

PRESELECTED

ACTUAL

kg x 1000

DEC

CKPT

INC

END

PRESELECTOR 5QT

A

N_MM_121128_3_AKM1_01_00

Figure 12-11-28-991-00400-00-Q (SHEET 1) - Refuel/Defuel Control Panel 800VU and 801VU, Preselector 5QT and Indicator 6QT ** ON A/C FSN 301-349, 351-400, 416-450, 500-600

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

17/17

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 23-73-00-040-001-A - Deactivation of the CIDS Director

CUSTOMIZATION

AIRCRAFT TYPES

A318 A319 A321 A320

IGO

DOCTYPES

REVISION DATE

AMM

01-Aug- 23-73-00-040-001-A 2019 Deactivation of the CIDS Director

TITLE

TAIL NUMBER MSN - FSN

** ON A/C FSN ALL TASK 23-73-00-040-001-A Deactivation of the CIDS Director FIN: 101RH 102RH 1.

Reason for the Job The purpose of this AMM task is to deactivate the CIDS director to recover the normal operation of the CIDS function. For further information, refer to MMEL 23-73-01-01A.

2.

Job Set-up Information A.

Referenced Information REFERENCE

DESIGNATION

** ON A/C FSN 016-022, 024-100, 112-150, 206-206, 208-209, 212-216, 218218, 221-230, 235-236, 238-239, 241-242, 301-450, 500-600 Ref. 23-73-00-740-005-B

Interface and Power-Up Test of the Cabin Intercommunication Data System (CIDS) through the CFDS

** ON A/C FSN 203-205, 211-211, 219-220, 231-234, 237-237, 240-240, 243-250 Ref. 23-73-00-861-001-A

Energize the Cabin Intercommunication Data System (CIDS)

Ref. 23-73-34-000-001-A

Removal of the Cabin Intercommunication Data System (CIDS) Director

** ON A/C FSN ALL Ref. 24-41-00-861-002-A

Energize the Aircraft Electrical Circuits from the External Power

Ref. 24-41-00-861-002-A01

Energize the Aircraft Electrical Circuits from the APU

Ref. 24-41-00-861-002-A02

Energize the Aircraft Electrical Circuits from Engine 1(2)

** ON A/C FSN 016-022, 024-100, 112-150, 206-206, 208-209, 212-216, 218218, 221-230, 235-236, 238-239, 241-242, 301-450, 500-600 Ref. 31-60-00-860-001-A

EIS Start Procedure

** ON A/C FSN ALL 3.

Job Set-up

** ON A/C FSN 201-201, 203-205, 207-207, 210-211, 217-217, 219-220, 231-234, 237-237, 240-240, 243-250 SUBTASK 23-73-00-860-146-A A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits Ref. AMM TASK 24-41-00-861-002 (2) Get access to the avionics compartment.

** ON A/C FSN 016-022, 024-100, 112-150, 206-206, 208-209, 212-216, 218-218, 221-230, 238-239, 241-242, 301-450, 500-600 © AIRBUS S.A.S.235-236, ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 1/4

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 23-73-00-040-001-A - Deactivation of the CIDS Director

SUBTASK 23-73-00-860-146-C A. 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) Make sure that a minimum of one cabin door is open.

** ON A/C FSN ALL 4.

Procedure

** ON A/C FSN 203-205, 211-211, 219-220, 231-234, 237-237, 240-240, 243-250 SUBTASK 23-73-00-875-050-A A. Open, safety and tag these circuit breakers in this sequence: PANEL

DESIGNATION

FIN

LOCATION

** ON A/C FSN 204-204, 219-220 121VU

COM/CIDS/DIR 1 AND 2/BAT

140RH

N11

** ON A/C FSN 203-205, 211-211, 219-220, 231-234, 237-237, 240-240, 243-250 FOR FIN 101RH(DIR-CIDS, 1) 49VU

COM/CIDS/DIR 1 AND 2/ESS

150RH

G02

121VU

COM NAV/CIDS/DIR 1 AND 2/NORM

151RH

M05

FOR FIN 102RH(DIR-CIDS, 2) 49VU

COM/CIDS/DIR 1 AND 2/ESS

150RH

G02

121VU

COM NAV/CIDS/DIR 1 AND 2/NORM

151RH

M05

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 206-210, 212-218, 221-230, 235-236, 238-239, 241-242, 301-450, 500-600 EMB SB 23-1544 for A/C 210-210 SUBTASK 23-73-00-875-050-B A. Open, safety and tag these circuit breakers in this sequence: PANEL

DESIGNATION

FIN

LOCATION

FOR FIN 101RH(DIR-CIDS, 1)

** ON A/C FSN 210-210, 227-228 EMB SB 23-1485 for A/C 210-210 121VU

COM/CIDS/DIR 1/BAT

147RH

P13

150RH

G01

** ON A/C FSN 401-450 49VU

COM NAV/CIDS/DIR1 ESS

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 206-210, 212-218, 221230, 235-236, 238-239, 241-242, 301-400, 500-600 EMB SB 23-1544 for A/C 210-210 49VU

COM/CIDS/DIR ESS/1

150RH

G01

151RH

M05

** ON A/C FSN 401-450 121VU

COM NAV/CIDS/DIR1 NORM

** ON A/C FSN 217-217 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 23-73-00-040-001-A - Deactivation of the CIDS Director

PANEL 121VU

DESIGNATION COM NAV/CIDS/DIR 1 AND 2/NORM

FIN 151RH

LOCATION M05

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 206-210, 212-216, 218218, 221-230, 235-236, 238-239, 241-242, 301-400, 500-600 EMB SB 23-1544 for A/C 210-210 121VU

COM NAV/CIDS/DIR NORM/1

151RH

M05

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 206-210, 212-218, 221230, 235-236, 238-239, 241-242, 301-450, 500-600 EMB SB 23-1544 for A/C 210-210 FOR FIN 102RH(DIR-CIDS, 2)

** ON A/C FSN 210-210, 227-228 EMB SB 23-1485 for A/C 210-210 121VU

COM/CIDS/DIR 2/BAT

146RH

P14

157RH

G02

** ON A/C FSN 401-450 49VU

COM NAV/CIDS/DIR2 ESS

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 206-210, 212-218, 221230, 235-236, 238-239, 241-242, 301-400, 500-600 EMB SB 23-1544 for A/C 210-210 49VU

COM/CIDS/DIR ESS/2

157RH

G02

156RH

M06

** ON A/C FSN 401-450 121VU

COM NAV/CIDS/DIR2 NORM

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 206-210, 212-218, 221230, 235-236, 238-239, 241-242, 301-400, 500-600 EMB SB 23-1544 for A/C 210-210 121VU

COM NAV/CIDS/DIR NORM/2

156RH

M06

** ON A/C FSN 203-205, 211-211, 219-220, 231-234, 237-237, 240-240, 243-250 SUBTASK 23-73-00-040-050-A B. Procedure NOTE: The steps that follow are only necessary, if you want to release the aircraft with only one CIDS Director installed. (1) Remove the related CIDS director 1 (2) Ref. AMM TASK 23-73-34-000-001. (2) On the rack 87VU (88VU) of the removed CIDS director 1 (2): Install plugs to close the ventilation holes. (See IPC-Figure 23-73-08-11-110) Open two ventilation holes. Make match marks on the components that you disconnect/remove to record their connections/positions. This is important for the subsequent installation procedure. (3) Energize the CIDS Ref. AMM TASK 23-73-00-861-001. (4) On the Programming and Test Panel (PTP) 110RH: Make sure that the SYS STATUS page shows the message 'CIDS OK'. (5) Make an entry in the logbook. (6) Close Access

** ON A/C FSN 201-201, 207-207, 210-210, 217-217 EMB SB 23-1544 A/C CONFIDENTIAL 210-210 AND PROPRIETARY DOCUMENT. © AIRBUS S.A.S. ALL RIGHTSfor RESERVED. 3/4

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 23-73-00-040-001-A - Deactivation of the CIDS Director

SUBTASK 23-73-00-040-050-B B. Procedure (1) On the Programming and Test Panel (PTP) 110RH: Make sure that the SYS STATUS page shows the message 'CIDS OK'. (2) Make an entry in the logbook.

** ON A/C FSN 016-022, 024-100, 112-150, 206-206, 208-209, 212-216, 218-218, 221-230, 235-236, 238-239, 241-242, 301-450, 500-600 SUBTASK 23-73-00-040-050-C B. Procedure (1) In the cockpit, on the MCDU: Do the Interface and Power-Up test of the CIDS through the CFDS. Ref. AMM TASK 23-73-00-740-005

(2) (3) (4)

NOTE: The circuit breakers related to the deactivated CIDS director must stay open (pulled). Make sure that only DIR 1 (2) related failure messages show. In the cockpit: Lift the handset from the cradle. Push and hold the PTT pushbutton switch and make an announcement. In the cabin: Make sure that you hear the announcement. Make an entry in the logbook.

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 28-25-00-040-004-A - Deactivation of the Transfer Defuel Valve

CUSTOMIZATION

AIRCRAFT TYPES

A318 A319 A321 A320

IGO

DOCTYPES

REVISION DATE

AMM

01-Aug- 28-25-00-040-004-A - Deactivation 2019 of the Transfer Defuel Valve

TITLE

TAIL NUMBER MSN - FSN

** ON A/C FSN ALL TASK 28-25-00-040-004-A Deactivation of the Transfer Defuel Valve FIN: 11QM Personnel Required. Minimum Number of Person

1

Manhours

01.0

Elapsed Time

01.0

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. 1.

Reason for the Job MMEL 28-25-04A Transfer Defuel Valve

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE

B.

QT Y

DESIGNATION

No specific

AR ACCESS PLATFORM 3M (10 FT)

No specific

AR BAG - POLYTHENE

No specific

AR CAP - BLANKING

No specific

AR SAFETY BARRIER(S)

No specific

AR SAFETY CLIP - CIRCUIT BREAKER

No specific

AR WARNING NOTICE(S)

T720456

1

TOOL - VALVE LOCKING

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

192MB C.

Referenced Information REFERENCE

DESIGNATION

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 28-25-00-040-004-A - Deactivation of the Transfer Defuel Valve

REFERENCE

DESIGNATION

Ref. 28-00-00-910-001-A

Fuel Safety Procedures

Ref. 28-25-53-000-001-A

Removal of the Center-Tank Defuel/Transfer Valve-Actuator

Ref. 28-25-53-400-001-A

Installation of the Center-Tank Defuel/Transfer ValveActuator

Ref. 32-12-00-010-001-A

Open the Main Gear Doors for Access

Ref. 32-12-00-410-001-A

Close the Main Gear Doors after Access

Ref. Fig. Transfer Defuel Valve (11QM) - Location and Detail

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-203, 205-250, 350-350 Ref. Fig. Refuel/Defuel Control Panel

** ON A/C FSN 204-204 Ref. Fig. Refuel/Defuel Control Panel

** ON A/C FSN 301-349, 351-400, 416-450, 500-600 Ref. Fig. Refuel/Defuel Control Panel

** ON A/C FSN 401-415 Ref. Fig. Refuel/Defuel Panels 800VU and 801VU

** ON A/C FSN ALL 3.

Job Set-up Ref. Fig. Transfer Defuel Valve (11QM) - Location and Detail

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-203, 205-250, 350-350 EMB SB 31-1211 for A/C 219-220

Ref. Fig. Refuel/Defuel Control Panel

** ON A/C FSN 204-204

Ref. Fig. Refuel/Defuel Control Panel

** ON A/C FSN 301-349, 351-400, 416-450, 500-600 Ref. Fig. Refuel/Defuel Control Panel

** ON A/C FSN 401-415

Ref. Fig. Refuel/Defuel Panels 800VU and 801VU

** ON A/C FSN ALL SUBTASK 28-25-00-941-072-A A. Safety Precautions WARNING: OBEY THE FUEL SAFETY PROCEDURES. (1) You must obey the fuel safety procedures when you do work on the fuel system Ref. AMM TASK 28-00-00-910-001. (2) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations. (3) Put a WARNING NOTICE(S) in position to tell persons not to operate the MLG doors. SUBTASK 28-25-00-010-072-A B. Get Access (1) Open the MLG doors Ref. AMM TASK 32-12-00-010-001. (2) Make sure that the SLEEVE - GROUND LOCK (460005835) is on the applicable MLG door actuator. (3) Put an ACCESS PLATFORM 3M (10 FT) below the transfer defuel valve (11QM). (4) Open the access panel 192MB. NOTE: If operating in battery power, do not keep the door open longer than necessary because the battery can discharge. SUBTASK 28-25-00-860-054-A C. Aircraft Maintenance Configuration (1) On the panel 800VU, make sure that the MODE SELECT switch is in the OFF and guarded position.

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 28-25-00-040-004-A - Deactivation of the Transfer Defuel Valve

SUBTASK 28-25-00-865-057-A D. Open, safety and tag this(these) circuit breaker(s): PANEL

DESIGNATION

FIN

LOCATION

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU

FUEL/RFL/DFL/XFR/DEFUEL/VALVE 1QU

L23

** ON A/C FSN 401-450 121VU

FUEL/RFL/DFL/XFR/DEFUEL/VALVE 1QU

L22

** ON A/C FSN ALL 4.

Procedure Ref. Fig. Transfer Defuel Valve (11QM) - Location and Detail

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-203, 205-250, 350-350 EMB SB 31-1211 for A/C 219-220

Ref. Fig. Refuel/Defuel Control Panel

** ON A/C FSN 204-204

Ref. Fig. Refuel/Defuel Control Panel

** ON A/C FSN 301-349, 351-400, 416-450, 500-600 Ref. Fig. Refuel/Defuel Control Panel

** ON A/C FSN 401-415

Ref. Fig. Refuel/Defuel Panels 800VU and 801VU

** ON A/C FSN ALL SUBTASK 28-25-00-040-050-A A. Transfer Defuel Valve - Closure Procedure (1) If the actuator (11QU) shows the transfer defuel valve (11QM) in the open position (see/feel indicator in-line): (a)

Remove the actuator (11QU) from the drive shaft of the transfer defuel valve (11QM) Ref. AMM TASK 28-25-53-000-001.

(b)

Manually turn the drive shaft to the valve-closed position (indicator groove vertical).

(c)

Make sure that the actuator (11QU) shaft is in the correct position (see/feel indicator cross-line) to align with the valve drive shaft.

(d)

If necessary, close the circuit breaker 1QU on the panel 121VU, and operate the actuator (11QU) to get the correct position. Open the circuit breaker 1QU.

(e)

Disconnect the electrical connector (1) from the actuator (11QU).

(f)

Put the CAP-BLANKING on each disconnected electrical connector and receptacle.

(g)

Seal the disconnected cable in a BAG - POLYTHENE.

(h) (2)

(3)

Install the actuator (11QU) Ref. AMM TASK 28-25-53-400-001. Do not connect the electrical connector (1) to the actuator. If the actuator (11QU) shows the transfer defuel valve (11QM) in the closed position (see/feel indicator cross-line): (a)

Disconnect the electrical connector (1) from the actuator (11QU).

(b)

Put the CAP-BLANKING on each disconnected electrical connector and receptacle.

(c) Seal the disconnected cable in a BAG - POLYTHENE. If the actuator (11QU) is unserviceable: (a)

Disconnect the electrical connector (1) from the actuator (11QU).

(b)

Put the CAP-BLANKING on each disconnected electrical connector and receptacle.

(c)

Seal the disconnected cable in a BAG - POLYTHENE.

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 28-25-00-040-004-A - Deactivation of the Transfer Defuel Valve

(d)

Remove the actuator (11QU) Ref. AMM TASK 28-25-53-000-001.

(e)

Put the actuator (11QU) in a BAG - POLYTHENE and keep in a safe location. NOTE: Keep the V-band clamp (82QM) safe. You will need it to clamp the TOOL - VALVE LOCKING (T720456) to the mounting flange of the valve drive shaft.

(4) (5)

5.

(f)

Make sure that the transfer defuel valve (11QM) is in the closed position (indicator groove vertical).

(g)

Install the TOOL - VALVE LOCKING (T720456) onto the face plate of the drive shaft to lock the drive shaft so that it will not turn. Make sure that the dowel (3) is correctly installed between the TOOL - VALVE LOCKING (T720456) and the face plate of the drive shaft. Put the V-band clamp (82QM) around the mounting flange of the drive shaft and the TOOL - VALVE LOCKING (T720456) and tighten the screw (2).

NOTE: The dowel (3) will stop the TOOL - VALVE LOCKING (T720456) from rotating on the face plate of the drive shaft. Write an applicable entry in the aircraft technical logbook. Attach a WARNING NOTICE(S) (to tell persons that the transfer defuel valve (11QM) is deactivated) to: The MODE SELECT switch on the panel 800VU The circuit breaker 1QU in the cockpit.

Close-up SUBTASK 28-25-00-410-066-A A. Close Access (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the access panel 192MB. (3) Remove the access platform(s). (4) Close the MLG doors Ref. AMM TASK 32-12-00-410-001. SUBTASK 28-25-00-942-075-A B. Removal of Equipment (1) Remove the safety barriers. (2) Remove the access platform(s). (3) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 28-25-00-040-004-A - Deactivation of the Transfer Defuel Valve

A

B A STA18694/FR42 Z141-Z142 STA15900/FR36

TRANSFER DEFUEL VALVE 11 Q M

C

1

B DRIVE SHAFT

D TO ENGINE FEED LINE

REAR SPAR

2

ACTUATOR

V-BAND CLAMP

11 Q U

82QM

VALVE 11 Q M

3

TO REFUEL LINE

D OPEN

VALVE LOCKING TOOL T720456

C SEE/FEEL INDICATOR CLOSED

OPEN

CLOSED

N_MM_282500_4_AEM0_01_00

Figure 28-25-00-991-01600-00-A (SHEET 1) - Transfer Defuel Valve (11QM) - Location and Detail ** ON A/C FSN ALL

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 28-25-00-040-004-A - Deactivation of the Transfer Defuel Valve

A

REFUEL COUPLING REFUEL/DEFUEL CONTROL PANEL

A

FUEL QTY kg x 1000 LEFT

CTR

H I .

I N D I C AT O R

RIGHT

6QT

LV L .

LEFT

CTR

RIGHT

REFUEL VALVES OPEN NORM SHUT MODE

OPEN NORM SHUT

SELECT REFUEL

OPEN NORM SHUT

TEST BATT POWER H I . LV L ON

REFUEL DEFUEL CONTROL PANEL 800VU

OFF DEFUEL XFR PRESELECTED

DEC

OPEN L T S

REFUEL kg x 1000

I N C CKPT

NORM ACTUAL

END

PRESELECTOR 5QT

N_MM_282500_4_CAM0_01_00

Figure 28-25-00-991-02400-00-G (SHEET 1) - Refuel/Defuel Control Panel ** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-203, 205-250, 350-350 EMB SB 31-1211 for A/C 219-220

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 28-25-00-040-004-A - Deactivation of the Transfer Defuel Valve

A

REFUEL COUPLING REFUEL/DEFUEL CONTROL PANEL

A

FUEL QTY lbs x 1000 CTR

LEFT

H I .

CTR

RIGHT

REFUEL VALVES OPEN NORM SHUT

OPEN NORM SHUT

SELECT REFUEL

6QT

LV L .

LEFT

MODE

I N D I C AT O R

RIGHT

OPEN NORM SHUT

TEST BATT POWER H I . LV L ON

REFUEL DEFUEL CONTROL PANEL 800VU

OFF DEFUEL XFR PRESELECTED

DEC

OPEN L T S

REFUEL lbs x 1000

I N C CKPT

NORM ACTUAL

END

PRESELECTOR 5QT

N_MM_282500_4_CVM0_01_00

Figure 28-25-00-991-02400-00-H (SHEET 1) - Refuel/Defuel Control Panel ** ON A/C FSN 204-204

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 28-25-00-040-004-A - Deactivation of the Transfer Defuel Valve

REFUEL COUPLING

A

REFUEL/DEFUEL CONTROL PANEL

A FUEL QTY kg X 1000 LEFT

CTR

HI. LEFT

INDICATOR 6QT

RIGHT

LVL. CTR

RIGHT

REFUEL VALVES OPEN NORM SHUT

OPEN NORM SHUT

MODE SELECT REFUEL

TEST HI. LVL

OPEN NORM SHUT BATT POWER ON

OFF DEFUEL XFR PRESELECTED

DEC

OPEN LTS REFUEL kg X 1000

NORM ACTUAL

CKPT

INC

REFUEL/DEFUEL CONTROL PANEL 800VU

END

PRESELECTOR 5QT

N_MM_282500_4_CAM2_01_00

Figure 28-25-00-991-02400-00-S (SHEET 1) - Refuel/Defuel Control Panel ** ON A/C FSN 301-349, 351-400, 416-450, 500-600

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 28-25-00-040-004-A - Deactivation of the Transfer Defuel Valve

REFUEL COUPLING 40QM

A

622HB 192MB

REFUEL/DEFUEL CONTROL PANEL

INDICATOR 6QT

FUEL QTY

ACT

TOTAL ACT

kg x 1000

LEFT

RIGHT

CTR

LVL

HI LEFT

VALVES

REFUEL SW POS = OPEN

CTR

= NORM

AFT1

UP

REFUEL VALVE

DOWN = SHUT

RIGHT

CTR

OPEN

OPEN

OPEN

NORM

NORM

NORM

SHUT

SHUT

TEST

MODE SELECT

HI LVL

REFUEL

HI LVL

SHUT

BATT POWER ON

REFUEL/DEFUEL CONTROL PANEL 800VU

OFF

DEFUEL / XFR

OPEN

LTS

REFUEL

PRESELECTED

NORM ACTUAL

kg x 1000

801VU REFUEL/DEFUEL CONTROL PANEL

DEC

INC

CKPT

END

5QT PRESELECTOR

A

N_MM_282500_4_EEM1_01_00

Figure 28-25-00-991-03800-00-C (SHEET 1) - Refuel/Defuel Panels 800VU and 801VU ** ON A/C FSN 401-415

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

9/9

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 29-10-00-710-004-A - Operational Check of EDP Depressurization

CUSTOMIZATION

AIRCRAFT TYPES

A318 A319 A321 A320

IGO

DOCTYPES

REVISION DATE

AMM

01-Aug- 29-10-00-710-004-A - Operational 2019 Check of EDP Depressurization

TITLE

TAIL NUMBER MSN - FSN

** ON A/C FSN ALL TASK 29-10-00-710-004-A Operational Check of EDP Depressurization 1.

Reason for the Job Refer to the MPD TASK: 291000-20 OPERATIONAL CHECK OF EDP DEPESSURIZATION

2.

Job Set-up Information A.

Work Zones and Access Panels ZONE/ACCESS 210

B.

ZONE DESCRIPTION CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

Referenced Information REFERENCE

DESIGNATION

Ref. 12-12-29-611-001-A

Fill the Hydraulic Fluid Reservoir with a Hand Pump

Ref. 12-12-29-611-002-A

Fill the Hydraulic Fluid Reservoir with a Hydraulic Service Cart

Ref. 24-41-00-861-002-A

Energize the Aircraft Electrical Circuits from the External Power

Ref. 24-41-00-861-002-A01

Energize the Aircraft Electrical Circuits from the APU

Ref. 24-41-00-861-002-A02

Energize the Aircraft Electrical Circuits from Engine 1(2)

Ref. 24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

Ref. 24-41-00-862-002-A01

De-energize the Aircraft Electrical Circuits Supplied from the APU

Ref. 24-41-00-862-002-A02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Ref. 29-14-00-614-002-A

Pressurization of the Hydraulic Reservoirs through the Ground Connector

Ref. 29-14-00-614-002-A01

Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU)

Ref. 31-60-00-860-001-A

EIS Start Procedure

Ref. 31-60-00-860-002-A

EIS Stop Procedure

** ON A/C FSN 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236236, 241-241 Ref. 71-00-00-710-001-B

Dry Motoring Check

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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REFERENCE Ref. 71-00-00-710-045-A

DESIGNATION Test No.1 : Dry Motor Leak Check

** ON A/C FSN 301-349, 351-450, 500-600 Ref. 71-00-00-860-817-A

Motor the Engine (Dry Method)

** ON A/C FSN ALL 3.

Job Set-up SUBTASK 29-10-00-865-106-A A. Make sure that this(these) circuit breaker(s) is(are) closed: PANEL

DESIGNATION

FIN

LOCATION

** ON A/C FSN 301-349, 351-450, 500-600 HYDRAULIC/G HYD/PUMP ENG1/CTL

1701G K

121VU

HYDRAULIC/SOL VALVES/G/Y/PTU

1801GL N34

121VU

HYDRAULIC/Y HYD/PUMP ENG2/MONG

3700G D

Q37

121VU

HYDRAULIC/Y HYD/PUMP ENG2/CTL

3701G D

Q36

49VU

H12

** ON A/C FSN ALL

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 121VU

HYDRAULIC/G HYD/PUMP ENG1/MONG

1702G K

R34

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-250, 350-350 121VU

HYDRAULIC/G HYD/PUMP ENG1/CTL

1701G K

R35

1702G K

R33

** ON A/C FSN 401-450 121VU

HYDRAULIC/G HYD/PUMP ENG1/MONG

** ON A/C FSN ALL SUBTASK 29-10-00-860-118-A B. 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) On the ECAM control panel on the center pedestal, press the HYD pushbutton. Make sure that the HYD page is shown on the ECAM lower Display Unit (DU) (4) Make sure that the ECAM does not show these conditions: Low air pressure in the Green and Yellow reservoir Low fluid level in the Green and Yellow reservoir. (5) If necessary, pressurize the reservoir Ref. AMM TASK 29-14-00-614-002. (6) If necessary, add fluid to the reservoir Ref. AMM TASK 12-12-29-611-001 or Ref. AMM TASK 12-12-29-611-002. (7) On the overhead panel 40VU, press the PTU/AUTO P/BSW (the OFF light comes on). (8) On the overhead panel 40VU, make sure that the GREEN/ENG 1 PUMP and the YELLOW/ENG 2 PUMP P/BSWs are set to on (FAULT and OFF lights are off). 4.

Procedure

** ON A/C FSN 207-207, 210-210, 212-214, 217-218, 223-226, 234-234, 236-236, 241-241 SUBTASK 29-10-00-710-058-B WARNING: MAKE SURE THAT THE TRAVEL RANGES OF © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

THE FLIGHT CONTROLS 2/5

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 29-10-00-710-004-A - Operational Check of EDP Depressurization

SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. CAUTION: DO NOT START OR DRY MOTOR THE ENGINES WITH A HYDRAULIC GROUND POWER SUPPLY CONNECTED TO THE AIRCRAFT. IF YOU DO, YOU CAN CAUSE DAMAGE TO THE ENGINE PUMPS. A. Operational Check of EDP Depressurization ACTION

RESULT

1.Dry-motor the left (No. 1) engine and the The left (No. 1) engine and the right (No. 2) right (No. 2) engine Ref. AMM TASK 71-00- engine turns and causes the engine-driven 00-710-001. pump of the Green and Yellow hydraulic system to turn. On the ECAM upper DU: The speed of the left (No. 1) engine and the right (No. 2) engine is approximately 20% N2. On the ECAM lower DU: The pressure in the Green and Yellow hydraulic system is 3000 +100 -100 psi. 2.On the overhead panel 40VU: Press the GREEN/ENG 1 PUMP and the YELLOW/ENG 2 PUMP P/BSWs.

On the overhead panel 40VU: The GREEN/ENG 1 PUMP and the YELLOW/ENG 2 PUMP OFF lights come on. On the ECAM lower DU: The vertical line between the EDP box and the system indication changes from green to amber The engine pump symbol of the Green and Yellow hydraulic systems change from green in-line to amber cross-line The pressure in the Green and Yellow hydraulic systems decreases to 0 psi.

3.On the overhead panel 40VU: Press the GREEN/ENG 1 PUMP and the YELLOW/ENG 2 PUMP P/BSWs.

On the overhead panel 40VU: The GREEN/ENG 1 PUMP and the YELLOW/ENG 2 PUMP OFF lights go off. On the ECAM lower DU: The pressure in the Green and Yellow hydraulic systems increases to 3000 +100 -100 psi The engine pump symbol of the Green and Yellow hydraulic systems changes from amber cross-line to green in-line The vertical line between the EDP box and the system indication changes from amber to green.

4.Stop the dry-motoring of the left (No. 1) engine and the right (No. 2) engine Ref. AMM TASK 71-00-00-710-001.

On the ECAM lower DU: The pressure in the Green and the Yellow hydraulic systems decreases to 0 psi.

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-206, 208-209, 211-211, 215-216, 219-222, 227-233, 235-235, 237-240, 242-250, 350-350 SUBTASK 29-10-00-710-058-C WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 29-10-00-710-004-A - Operational Check of EDP Depressurization

CAUTION: DO NOT START OR DRY MOTOR THE ENGINES WITH A HYDRAULIC GROUND POWER SUPPLY CONNECTED TO THE AIRCRAFT. IF YOU DO, YOU CAN CAUSE DAMAGE TO THE ENGINE PUMPS. A. Operational Check of EDP Depressurization ACTION

RESULT

1.Dry-motor the left (No. 1) engine and the The left (No. 1) engine and the right (No. 2) right (No. 2) engine Ref. AMM TASK 71-00- engine turns and causes the engine-driven 00-710-045. pump of the Green and Yellow hydraulic system to turn. On the ECAM upper DU: The speed of the left (No. 1) engine and the right (No. 2) engine is approximately 20% N2. On the ECAM lower DU: The pressure in the Green and Yellow hydraulic system is 3000 +100 -100 psi. 2.On the overhead panel 40VU: Press the GREEN/ENG 1 PUMP and the YELLOW/ENG 2 PUMP P/BSWs.

On the overhead panel 40VU: The GREEN/ENG 1 PUMP and the YELLOW/ENG 2 PUMP OFF lights come on. On the ECAM lower DU: The vertical line between the EDP box and the system indication changes from green to amber The engine pump symbol of the Green and Yellow hydraulic systems change from green in-line to amber cross-line The pressure in the Green and Yellow hydraulic systems decreases to 0 psi.

3.On the overhead panel 40VU: Press the GREEN/ENG 1 PUMP and the YELLOW/ENG 2 PUMP P/BSWs.

On the overhead panel 40VU: The GREEN/ENG 1 PUMP and the YELLOW/ENG 2 PUMP OFF lights go off. On the ECAM lower DU: The pressure in the Green and Yellow hydraulic systems increases to 3000 +100 -100 psi The engine pump symbol of the Green and Yellow hydraulic systems changes from amber cross-line to green in-line The vertical line between the EDP box and the system indication changes from amber to green.

4.Stop the dry-motoring of the left (No. 1) engine and the right (No. 2) engine Ref. AMM TASK 71-00-00-710-045.

On the ECAM lower DU: The pressure in the Green and the Yellow hydraulic systems decreases to 0 psi.

** ON A/C FSN 301-349, 351-450, 500-600 SUBTASK 29-10-00-710-058-D WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. CAUTION: DO NOT START OR DRY MOTOR THE ENGINES WITH A HYDRAULIC GROUND POWER SUPPLY CONNECTED TO THE AIRCRAFT. IF YOU DO, YOU CAN CAUSE DAMAGE TO THE ENGINE PUMPS. A. Operational Check of EDP Depressurization © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 29-10-00-710-004-A - Operational Check of EDP Depressurization

ACTION

RESULT

1.Dry-motor the left (No. 1) engine and the The left (No. 1) engine and the right (No. 2) right (No. 2) engine Ref. AMM TASK 71-00- engine turns and causes the engine-driven 00-860-817. pump of the Green and Yellow hydraulic system to turn. On the ECAM upper DU: The speed of the left (No. 1) engine and the right (No. 2) engine is approximately 20% N2. On the ECAM lower DU: The pressure in the Green and Yellow hydraulic system is 3000 +100 -100 psi. 2.On the overhead panel 40VU: Press the GREEN/ENG 1 PUMP and the YELLOW/ENG 2 PUMP P/BSWs.

On the overhead panel 40VU: The GREEN/ENG 1 PUMP and the YELLOW/ENG 2 PUMP OFF lights come on. On the ECAM lower DU: The vertical line between the EDP box and the system indication changes from green to amber The engine pump symbol of the Green and Yellow hydraulic systems change from green in-line to amber cross-line The pressure in the Green and Yellow hydraulic systems decreases to 0 psi.

3.On the overhead panel 40VU: Press the GREEN/ENG 1 PUMP and the YELLOW/ENG 2 PUMP P/BSWs.

On the overhead panel 40VU: The GREEN/ENG 1 PUMP and the YELLOW/ENG 2 PUMP OFF lights go off. On the ECAM lower DU: The pressure in the Green and Yellow hydraulic systems increases to 3000 +100 -100 psi The engine pump symbol of the Green and Yellow hydraulic systems changes from amber cross-line to green in-line The vertical line between the EDP box and the system indication changes from amber to green.

4.Stop the dry-motoring of the left (No. 1) engine and the right (No. 2) engine Ref. AMM TASK 71-00-00-860-817.

On the ECAM lower DU: The pressure in the Green and the Yellow hydraulic systems decreases to 0 psi.

** ON A/C FSN ALL 5.

Close-up SUBTASK 29-10-00-860-119-A A. Put the aircraft back to the serviceable condition. (1) On the overhead panel 40VU, press and release the PTU/AUTO P/BSW (the OFF light goes off). (2) Do the EIS stop procedure Ref. AMM TASK 31-60-00-860-002. (3) De-energize the aircraft electrical circuits Ref. AMM TASK 24-41-00-862-002.

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

5/5

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 32-46-00-740-003-A - BITE Test of the BSCU - LRU Identification

CUSTOMIZATION

AIRCRAFT TYPES

A318 A319 A321 A320

IGO

DOCTYPES

REVISION DATE

AMM

01-Aug- 32-46-00-740-003-A - BITE Test of 2019 the BSCU - LRU Identification

TITLE

TAIL NUMBER MSN - FSN

** ON A/C FSN ALL TASK 32-46-00-740-003-A BITE Test of the BSCU - LRU Identification 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QT Y

DESIGNATION

AR WARNING NOTICE(S)

Referenced Information REFERENCE

3.

DESIGNATION

Ref. 24-41-00-861-002-A

Energize the Aircraft Electrical Circuits from the External Power

Ref. 24-41-00-861-002-A01

Energize the Aircraft Electrical Circuits from the APU

Ref. 24-41-00-861-002-A02

Energize the Aircraft Electrical Circuits from Engine 1(2)

Ref. 24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

Ref. 24-41-00-862-002-A01

De-energize the Aircraft Electrical Circuits Supplied from the APU

Ref. 24-41-00-862-002-A02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Ref. 31-32-00-860-009-A

Procedure to Get Access to the SYSTEM REPORT/TEST/L/G Page

Job Set-up SUBTASK 32-46-00-860-056-A A. Aircraft Maintenance Configuration (1) On the panel 400VU, make sure that the L/G normal control-lever is set to DOWN. (2) On the panel 402VU, make sure that the A/SKID & NOSE WHEEL switch is at ON. (3) Energize the aircraft electrical circuits Ref. AMM TASK 24-41-00-861-002. (4) On one MCDU, get the SYSTEM REPORT/TEST/L/G page Ref. AMM TASK 31-32-00860-009. SUBTASK 32-46-00-941-056-A B. Safety Precautions (1) Put WARNING NOTICE(S) on the L/G normal control lever to tell persons not to move it. SUBTASK 32-46-00-865-053-A C. Make sure that this(these) circuit breaker(s) is(are) closed:

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 32-46-00-740-003-A - BITE Test of the BSCU - LRU Identification

PANEL

4.

DESIGNATION

FIN

LOCATION

121VU

HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY

4GG

M36

121VU

HYDRAULIC/BRAKING AND STEERING/SYS2/CTL

3GG

M35

121VU

HYDRAULIC/BRAKING AND STEERING/SYS1/CTL

1GG

M34

121VU

HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY

2GG

M33

Procedure

** ON A/C FSN ALL EMB SB 32-1336 for A/C 207-207, 210-210, 231-232, 237-237 EMB SB 32-1350 for A/C 016-021, 201-201, 203-206, 209-209, 211-211, 215-222, 226-230, 233-235, 239-240, 242-244, 350-350 EMB SB 32-1360 for A/C 203-205, 211-211, 219-220 EMB SB 32-1361 for A/C 203-205, 207-207, 210-211, 219-220, 231-232, 237-237 SUBTASK 32-46-00-740-052-B A. Do this test: NOTE: This test is for CHAN/SYS 1. For CHAN/SYS 2, use the indications between parentheses. ACTION

RESULT

1.On the MCDU, push the line key adjacent to the BSCU 1(2) indication.

the BSCU CHAN/SYS 1(2) page comes into view.

2.Push the line key adjacent to the LRU IDENT indication.

the BSCU CHAN/SYS 1(2)/LRU IDENTIFICATION page comes into view. This page gives: . the Part Number of the BSCU . the Serial Number of the BSCU . the pin programming reference (wheel diameter and type of brake).

-

3.Push the line key adjacent to the RETURN indication to get the SYSTEM REPORT/TEST/L/G page.

** ON A/C FSN ALL 5.

Close-up SUBTASK 32-46-00-860-057-A A. Put the aircraft back to its initial configuration. (1) On the MCDU, push the line select key adjacent to the RETURN indication until the CFDS menu page comes into view. (2) De-energize the aircraft electrical circuits Ref. AMM TASK 24-41-00-862-002. (3) Remove the WARNING NOTICE(S).

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 34-57-00-040-801-A - Deactivation of the Digital Distance and Radio Magne…

AIRCRAFT REVISION DOCTYPES TYPES DATE

CUSTOMIZATION

A318 A319 A321 A320

IGO

AMM

TAIL NUMBER MSN - FSN

TITLE

34-57-00-040-801-A - Deactivation of 01-Augthe Digital Distance and Radio 2019 Magnetic Indicator (DDRMI)

** ON A/C FSN 016-022, 024-063, 201-201, 203-222, 226-235, 237-237, 239-240, 242-250, 350-350 TASK 34-57-00-040-801-A Deactivation of the Digital Distance and Radio Magnetic Indicator (DDRMI) 1.

Reason for the Job NOTE: This deactivation task is not related to an AFM-CDL/MMEL item.

2.

Job Set-up Information A.

Referenced Information REFERENCE

3.

DESIGNATION

Ref. 24-41-00-861-002-A

Energize the Aircraft Electrical Circuits from the External Power

Ref. 24-41-00-861-002-A01

Energize the Aircraft Electrical Circuits from the APU

Ref. 24-41-00-861-002-A02

Energize the Aircraft Electrical Circuits from Engine 1(2)

Ref. 24-41-00-862-002-A

De-energize the Aircraft Electrical Circuits Supplied from the External Power

Ref. 24-41-00-862-002-A01

De-energize the Aircraft Electrical Circuits Supplied from the APU

Ref. 24-41-00-862-002-A02

De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)

Job Set-up SUBTASK 34-57-00-860-050-A A. Aircraft Maintenance Configuration (1) Energize the aircraft electrical circuits Ref. AMM TASK 24-41-00-861-002. SUBTASK 34-57-00-865-050-A B. Make sure that this(these) circuit breaker(s) is(are) closed: PANEL 49VU

4.

DESIGNATION NAV/VOR/DME/RMI

FIN 12FN

LOCATION F13

Procedure SUBTASK 34-57-00-040-050-A A. Deactivation of the DDRMI (1) Open, safety and tag circuit breaker 12FN of the DDRMI.

5.

Close-up SUBTASK 34-57-00-860-051-A

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 34-57-00-040-801-A - Deactivation of the Digital Distance and Radio Magne…

A.

Put the aircraft back to its initial configuration. (1) Make an entry in the logbook. (2) De-energize the aircraft electrical circuits Ref. AMM TASK 24-41-00-862-002. (3) Make sure that the work area is clean and clear of tools and other items.

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

2/2

9/4/2019

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 52-70-00-040-007-A - Test of the Proximity Switches of the Doors

CUSTOMIZATION

AIRCRAFT TYPES

A318 A319 A321 A320

IGO

DOCTYPES

REVISION DATE

AMM

01-Aug- 52-70-00-040-007-A - Test of the 2019 Proximity Switches of the Doors

TITLE

TAIL NUMBER MSN - FSN

** ON A/C FSN ALL TASK 52-70-00-040-007-A Test of the Proximity Switches of the Doors WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS. 1.

Reason for the Job NOTE: This procedure must agree with the note related to MMEL item 25-07-0X. This is applicable when there is an incorrect "ARMED" or "NOT ARMED" indication on the slide for the passenger doors. This procedure gives the instructions necessary to: Clean the related switch Get the correct "SLIDE ARMED" indication on the ECAM DOOR/OXY page.

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE

B.

QT Y

DESIGNATION

No specific

AR ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE

No specific

AR SAFETY CLIP - CIRCUIT BREAKER

Consumable Materials REFERENCE

C.

DESIGNATION

08BBD1

Non Aqueous Cleaner-- Isopropyl Alcohol -

14SBA1

Textile-Lint free Cotton -

Work Zones and Access Panels ZONE/ACCESS

ZONE DESCRIPTION

831, 832, 841, 842

** ON A/C FSN 401-450 835, 845

** ON A/C FSN ALL D.

Referenced Information REFERENCE

DESIGNATION

Ref. 52-10-00-010-001-A

Opening of the Passenger/Crew Door

Ref. 52-10-00-410-001-A

Closing of the Passenger/Crew Door

Ref. 52-10-00-860-001-A

Special Precautions before Work on the Passenger/Crew Door

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 52-70-00-040-007-A - Test of the Proximity Switches of the Doors

REFERENCE Ref. 52-10-00-860-002-A

DESIGNATION Special Precautions after Work on the Passenger/Crew Door

** ON A/C FSN 401-450 Ref. 52-22-00-010-002-A

Opening of the Emergency Exit Doors from the Outside

Ref. 52-22-00-410-002-A

Closing of the Emergency Exit Doors from the Outside

Ref. 52-22-00-860-003-A

Special Precaution before Maintenance on the Door Damper and Emergency Operation Cylinder

Ref. 52-22-00-860-004-A

Special Precaution after Maintenance on the Door Damper and Emergency Operation Cylinder

** ON A/C FSN ALL Ref. 52-70-00-040-004-A

Visual Check to Make Sure that the Avionics-Compartment Access Doors are Correctly Closed

Ref. 52-71-00-710-001-A

Operational Test of the Door Warning System

Ref. 52-71-14-000-001-A

Removal of the Proximity Switches of the Avionics Compartment Doors

Ref. 52-73-11-000-001-A

Removal of the Proximity Switches of the FWD Passenger/Crew Doors

Ref. 52-73-11-000-002-A

Removal of the Proximity Switches of the Aft Passenger/Crew Doors

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-235, 237-240, 242250, 301-400, 500-600 Ref. 52-73-11-000-003-A

Removal of the Proximity Switches of the FWD Emergency Exits

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Ref. 52-73-11-000-004-A

Removal of the Proximity Switches of the Aft Emergency Exits

** ON A/C FSN 401-450 Ref. 52-73-11-000-004-E

Removal of the Proximity Switches of the Aft Emergency Exits

** ON A/C FSN ALL Ref. 52-73-11-400-001-A

Installation of the Proximity Switches of the FWD Passenger/Crew Doors

Ref. 52-73-11-400-002-A

Installation of the Proximity Switches of the Aft Passenger/Crew Doors

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-235, 237-240, 242250, 301-400, 500-600 Ref. 52-73-11-400-003-A

Installation of the Proximity Switches of the FWD Emergency Exits

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Ref. 52-73-11-400-004-A

Installation of the Proximity Switches of the Aft Emergency Exits

** ON A/C FSN 401-450 Ref. 52-73-11-400-004-E

Installation of the Proximity Switches of the Aft Emergency Exits

** ON A/C FSN ALL © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 52-70-00-040-007-A - Test of the Proximity Switches of the Doors

REFERENCE

DESIGNATION

FOR 4WN1(PROX SW-HANDLE, L FWD ESC SLIDE) Ref. 25-23-46-000-001-A

Removal of the Door Linings at the Forward Passenger/Crew Doors

Ref. 25-23-46-400-001-A

Installation of the Door Linings at the Forward Passenger/Crew Doors

FOR 4WN2(PROX SW-HANDLE, R FWD ESC SLIDE) Ref. 25-23-46-000-001-A

Removal of the Door Linings at the Forward Passenger/Crew Doors

Ref. 25-23-46-400-001-A

Installation of the Door Linings at the Forward Passenger/Crew Doors

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 FOR 5WN1(PROX SW-HANDLE, L FWD EMER EXIT ESC SLIDE) Ref. 25-23-47-000-002-A

Removal of the Upper Sidewall Panel Assy 241LW, (242LW), 241CW, (242CW) and 241FW, (242FW)

Ref. 25-23-47-400-002-A

Installation of the Upper Sidewall Panel Assy 241LW, (242LW), 241CW, (242CW) and 241FW, (242FW)

FOR 5WN2(PROX SW-HANDLE, R FWD EMER EXIT ESC SLIDE) Ref. 25-23-47-000-002-A

Removal of the Upper Sidewall Panel Assy 241LW, (242LW), 241CW, (242CW) and 241FW, (242FW)

Ref. 25-23-47-400-002-A

Installation of the Upper Sidewall Panel Assy 241LW, (242LW), 241CW, (242CW) and 241FW, (242FW)

** ON A/C FSN ALL FOR 6WN1(PROX SW-HANDLE, L AFT EMER EXIT ESC SLIDE)

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Ref. 25-23-47-000-002-A

Removal of the Upper Sidewall Panel Assy 241LW, (242LW), 241CW, (242CW) and 241FW, (242FW)

Ref. 25-23-47-400-002-A

Installation of the Upper Sidewall Panel Assy 241LW, (242LW), 241CW, (242CW) and 241FW, (242FW)

** ON A/C FSN ALL FOR 6WN2(PROX SW-HANDLE, R AFT EMER EXIT ESC SLIDE)

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 Ref. 25-23-47-000-002-A

Removal of the Upper Sidewall Panel Assy 241LW, (242LW), 241CW, (242CW) and 241FW, (242FW)

Ref. 25-23-47-400-002-A

Installation of the Upper Sidewall Panel Assy 241LW, (242LW), 241CW, (242CW) and 241FW, (242FW)

** ON A/C FSN ALL FOR 7WN1(PROX SW-HANDLE, L AFT ESC SLIDE) Ref. 25-23-46-000-002-A

Removal of the Door Linings at the Aft Passenger/Crew Doors

Ref. 25-23-46-400-002-A

Installation of the Door Linings at the Aft Passenger/Crew Doors

FOR 7WN2(PROX SW-HANDLE, R AFT ESC SLIDE) Ref. 25-23-46-000-002-A

Removal of the Door Linings at the Aft Passenger/Crew Doors

Ref. 25-23-46-400-002-A

Installation of the Door Linings at the Aft Passenger/Crew Doors

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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3.

IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 52-70-00-040-007-A - Test of the Proximity Switches of the Doors

Job Set-up

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 SUBTASK 52-70-00-941-055-A A. Identification of the Proximity Switches in Relation to the Door (1) The identification of the proximity switches is as follows: (a)

4WN1 for the left-forward passenger/crew door

(b)

4WN2 for the right-forward passenger/crew door

(c)

7WN1 for the left-aft passenger/crew door

(d)

7WN2 for the right-aft passenger/crew door

(e)

5WN1 for the left-forward emergency exit

(f)

5WN2 for the right-forward emergency exit

(g)

6WN1 for the left-aft emergency exit

(h)

6WN2 for the right-aft emergency exit.

SUBTASK 52-70-00-010-057-A B. Get Access (1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at applicable passenger/crew door 831 or 841 or 832 or 842. (2) Open the applicable passenger/crew door Ref. AMM TASK 52-10-00-010-001. (3) Obey the special precautions before you start work on the passenger/crew door Ref. AMM TASK 52-10-00-860-001.

** ON A/C FSN 401-450 SUBTASK 52-70-00-941-055-B A. Identification of the Proximity Switches in Relation to the Door (1) The identification of the proximity switches is as follows: (a)

4WN1 for the left-forward passenger/crew door

(b)

4WN2 for the right-forward passenger/crew door

(c)

7WN1 for the left-aft passenger/crew door

(d)

7WN2 for the right-aft passenger/crew door

(e)

6WN1 for the left-aft emergency exit

(f)

6WN2 for the right-aft emergency exit.

SUBTASK 52-70-00-010-057-C B. Get Access (1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at applicable passenger/crew door 831 or 841 or 832 or 842. (2) Open the applicable passenger/crew door Ref. AMM TASK 52-10-00-010-001. (3) Obey the special precautions before you start work on the passenger/crew door Ref. AMM TASK 52-10-00-860-001. (4) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at applicable emergency exit 835 or 845. (5) Open the applicable emergency exit Ref. AMM TASK 52-22-00-010-002. (6) Obey the special precautions before you start work on the emergency exit Ref. AMM TASK 52-22-00-860-003.

** ON A/C FSN ALL SUBTASK 52-70-00-865-058-A C. Open, safety and tag this(these) circuit breaker(s): PANEL

DESIGNATION

FIN

LOCATION

121VU

EIS/SLIDES/ARM AND WARN/FLT

15WN

P11

121VU

EIS/SLIDES/ARM AND WARN/GND

13WN

P10

121VU

EIS/SDAC1 AND 2/DOOR/DET/PAX

48WV

P05

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 52-70-00-040-007-A - Test of the Proximity Switches of the Doors

SUBTASK 52-70-00-020-053-A D. Removal of the Door Lining Panels (1) Remove the lining panels: (2) FOR 4WN1 (PROX SW-HANDLE, L FWD ESC SLIDE) 831CZ Ref. AMM TASK 25-23-46-000-001 (3) FOR 4WN2 (PROX SW-HANDLE, R FWD ESC SLIDE) 841CZ Ref. AMM TASK 25-23-46-000-001 (4) FOR 7WN1 (PROX SW-HANDLE, L AFT ESC SLIDE) 832CZ Ref. AMM TASK 25-23-46-000-002 (5) FOR 7WN2 (PROX SW-HANDLE, R AFT ESC SLIDE) 842CZ Ref. AMM TASK 25-23-46-000-002 (6) FOR 5WN1 (PROX SW-HANDLE, L FWD EMER EXIT ESC SLIDE) 241LW Ref. AMM TASK 25-23-47-000-002 (7) FOR 5WN2 (PROX SW-HANDLE, R FWD EMER EXIT ESC SLIDE) 242LW Ref. AMM TASK 25-23-47-000-002 (8) FOR 6WN1 (PROX SW-HANDLE, L AFT EMER EXIT ESC SLIDE) 241LW Ref. AMM TASK 25-23-47-000-002 (9) FOR 6WN2 (PROX SW-HANDLE, R AFT EMER EXIT ESC SLIDE) 242LW Ref. AMM TASK 25-23-47-000-002. (10) Remove the insulation blankets.

** ON A/C FSN 401-450 SUBTASK 52-70-00-020-053-C D. Removal of the Door Lining Panels (1) Remove the lining panels: (2) FOR 4WN1 (PROX SW-HANDLE, L FWD ESC SLIDE) 831CZ Ref. AMM TASK 25-23-46-000-001 (3) FOR 4WN2 (PROX SW-HANDLE, R FWD ESC SLIDE) 841CZ Ref. AMM TASK 25-23-46-000-001 (4) FOR 7WN1 (PROX SW-HANDLE, L AFT ESC SLIDE) 832CZ Ref. AMM TASK 25-23-46-000-002 (5) FOR 7WN2 (PROX SW-HANDLE, R AFT ESC SLIDE) 842CZ Ref. AMM TASK 25-23-46-000-002 (6) FOR 6WN1 (PROX SW-HANDLE, L AFT EMER EXIT ESC SLIDE) 835CZ Ref. AMM TASK 25-23-47-000-013 (7) FOR 6WN2 (PROX SW-HANDLE, R AFT EMER EXIT ESC SLIDE) 845CZ Ref. AMM TASK 25-23-47-000-013. (8) Remove the insulation blankets.

** ON A/C FSN ALL 4.

Procedure

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-235, 237-240, 242-250, 301-400, 500-600 SUBTASK 52-70-00-040-055-A A. Check of the Defective Proximity Switch (1) Clean the defective proximity switch with Non Aqueous Cleaner-- Isopropyl Alcohol (Material Ref. 08BBD1) and the Textile-Lint free Cotton - (Material Ref. 14SBA1). (2) If the fault continues: (a)

Replace the defective proximity switch. 1

If a new proximity switch is available: Remove the defective proximity switch Ref. AMM TASK 52-73-11-000001, Ref. AMM TASK 52-73-11-000-002, Ref. AMM TASK 52-73-11000-003 or Ref. AMM TASK 52-73-11-000-004. Install the new proximity switch Ref. AMM TASK 52-73-11-400-001, Ref. AMM TASK 52-73-11-400-002, Ref. AMM TASK 52-73-11-400003 or Ref. AMM TASK 52-73-11-400-004.

2

If no proximity switch are available, replace the defective proximity switch by a proximity switch removed from the avionics compartment doors.

NOTE: If a proximity switch from the avionics compartment was used, the MMEL for the avionics-compartment door indication Ref. AMM TASK 52-70-00-040-004 will be applicable if the avionics-compartment door indication is incorrect. © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 5/8

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 52-70-00-040-007-A - Test of the Proximity Switches of the Doors

-

(b)

Do a check of the proximity switch that you will remove. To do this, do an operational test of the door warning system of the related avionics compartment doors Ref. AMM TASK 52-71-00-710-001. Remove the proximity switch from the avionics compartment door Ref. AMM TASK 52-71-14-000-001. Install this proximity switch on the applicable passenger/crew door Ref. AMM TASK 52-73-11-400-001, Ref. AMM TASK 52-73-11-400002 or emergency exit Ref. AMM TASK 52-73-11-400-003, Ref. AMM TASK 52-73-11-400-004.

If the fault continues: Refer to the MMEL document for dispatch conditions.

** ON A/C FSN 236-236, 241-241 SUBTASK 52-70-00-040-055-C A. Check of the Defective Proximity Switch (1) Clean the defective proximity switch with Non Aqueous Cleaner-- Isopropyl Alcohol (Material Ref. 08BBD1) and the Textile-Lint free Cotton - (Material Ref. 14SBA1). (2) If the fault continues: (a)

Replace the defective proximity switch. 1

If a new proximity switch is available: Remove the defective proximity switch Ref. AMM TASK 52-73-11-000001, Ref. AMM TASK 52-73-11-000-002 or Ref. AMM TASK 52-73-11000-004. Install the new proximity switch Ref. AMM TASK 52-73-11-400-001, Ref. AMM TASK 52-73-11-400-002 or Ref. AMM TASK 52-73-11-400004.

2

If no proximity switch are available, replace the defective proximity switch by a proximity switch from the avionics compartment doors. NOTE: If a proximity switch from the avionics compartment was used, the MMEL for the avionics-compartment door indication Ref. AMM TASK 52-70-00-040-004 will be applicable if the avionics-compartment door indication is incorrect. Do a check of the proximity switch that you will remove. To do this, do an operational test of the door warning system of the related avionics compartment doors Ref. AMM TASK 52-71-00-710-001. Remove the proximity switch from the avionics compartment door Ref. AMM TASK 52-71-14-000-001. Install this proximity switch on the applicable passenger/crew door Ref. AMM TASK 52-73-11-400-001, Ref. AMM TASK 52-73-11-400002 or emergency exit Ref. AMM TASK 52-73-11-400-004.

(b)

If the fault continues: Refer to the MMEL document for dispatch conditions.

** ON A/C FSN 401-450 SUBTASK 52-70-00-040-055-D A. Check of the Defective Proximity Switch (1) Clean the defective proximity switch with Non Aqueous Cleaner-- Isopropyl Alcohol (Material Ref. 08BBD1) and the Textile-Lint free Cotton - (Material Ref. 14SBA1). (2) If the fault continues: (a)

Replace the defective proximity switch. 1

If a new proximity switch is available: Remove the defective proximity switch Ref. AMM TASK 52-73-11-000001, Ref. AMM TASK 52-73-11-000-002 or Ref. AMM TASK 52-73-11000-004. Install the new proximity switch Ref. AMM TASK 52-73-11-400-001, Ref. AMM TASK 52-73-11-400-002 or Ref. AMM TASK 52-73-11-400004.

2

If no proximity switch are available, replace the defective proximity switch by a proximity switch from the avionics compartment doors. NOTE: If a proximity switch from the avionics compartment was used, the

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 52-70-00-040-007-A - Test of the Proximity Switches of the Doors

-

(b)

MMEL for the avionics-compartment door indication Ref. AMM TASK 52-70-00-040-004 will be applicable if the avionics-compartment door indication is incorrect. Do a check of the proximity switch that you will remove. To do this, do an operational test of the door warning system of the related avionics compartment doors Ref. AMM TASK 52-71-00-710-001. Remove the proximity switch from the avionics compartment door Ref. AMM TASK 52-71-14-000-001. Install this proximity switch on the applicable passenger/crew door Ref. AMM TASK 52-73-11-400-001, Ref. AMM TASK 52-73-11-400002 or emergency exit Ref. AMM TASK 52-73-11-400-004.

If the fault continues: Refer to the MMEL document for dispatch conditions.

** ON A/C FSN ALL 5.

Close-up

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 SUBTASK 52-70-00-420-053-A A. Installation of the Lining Panels (1) Install the insulation blankets. (2) Install the lining panels: (3) FOR 4WN1 (PROX SW-HANDLE, L FWD ESC SLIDE) 831CZ Ref. AMM TASK 25-23-46-400-001 (4) FOR 4WN2 (PROX SW-HANDLE, R FWD ESC SLIDE) 841CZ Ref. AMM TASK 25-23-46-400-001 (5) FOR 7WN1 (PROX SW-HANDLE, L AFT ESC SLIDE) 832CZ Ref. AMM TASK 25-23-46-400-002 (6) FOR 7WN2 (PROX SW-HANDLE, R AFT ESC SLIDE) 842CZ Ref. AMM TASK 25-23-46-400-002 (7) FOR 5WN1 (PROX SW-HANDLE, L FWD EMER EXIT ESC SLIDE) 241LW Ref. AMM TASK 25-23-47-400-002 (8) FOR 5WN2 (PROX SW-HANDLE, R FWD EMER EXIT ESC SLIDE) 242LW Ref. AMM TASK 25-23-47-400-002 (9) FOR 6WN1 (PROX SW-HANDLE, L AFT EMER EXIT ESC SLIDE) 241LW Ref. AMM TASK 25-23-47-400-002 (10) FOR 6WN2 (PROX SW-HANDLE, R AFT EMER EXIT ESC SLIDE) 242LW Ref. AMM TASK 25-23-47-400-002.

** ON A/C FSN 401-450 SUBTASK 52-70-00-420-053-C A. Installation of the Lining Panels (1) Install the insulation blankets. (2) Install the lining panels: (3) FOR 4WN1 (PROX SW-HANDLE, L FWD ESC SLIDE) 831CZ Ref. AMM TASK 25-23-46-400-001 (4) FOR 4WN2 (PROX SW-HANDLE, R FWD ESC SLIDE) 841CZ Ref. AMM TASK 25-23-46-400-001 (5) FOR 7WN1 (PROX SW-HANDLE, L AFT ESC SLIDE) 832CZ Ref. AMM TASK 25-23-46-400-002 (6) FOR 7WN2 (PROX SW-HANDLE, R AFT ESC SLIDE) 842CZ Ref. AMM TASK 25-23-46-400-002 (7) FOR 6WN1 (PROX SW-HANDLE, L AFT EMER EXIT ESC SLIDE) 835CZ Ref. AMM TASK 25-23-47-400-013 (8) FOR 6WN2 (PROX SW-HANDLE, R AFT EMER EXIT ESC SLIDE) 845CZ Ref. AMM TASK 25-23-47-400-013.

** ON A/C FSN ALL SUBTASK 52-70-00-865-059-A B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): PANEL

DESIGNATION

FIN

LOCATION

121VU

EIS/SLIDES/ARM AND WARN/FLT

15WN

P11

121VU

EIS/SLIDES/ARM AND WARN/GND

13WN

P10

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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PANEL 121VU

DESIGNATION EIS/SDAC1 AND 2/DOOR/DET/PAX

FIN 48WV

LOCATION P05

** ON A/C FSN 016-022, 024-100, 112-150, 201-201, 203-250, 301-400, 500-600 SUBTASK 52-70-00-410-057-A C. Close Access (1) Remove all the ground support equipment, the maintenance equipment, the standard and special tools and all other items from the inspection area. (2) Obey the special precautions after the work on the passenger/crew door Ref. AMM TASK 52-10-00-860-002. (3) Close applicable passenger/crew door 831 or 841 or 832 or 842 Ref. AMM TASK 5210-00-410-001. (4) Make sure that the work area is clean and clear of tools and other items. (5) Remove the access platform(s).

** ON A/C FSN 401-450 SUBTASK 52-70-00-410-057-C C. Close Access (1) Remove all the ground support equipment, the maintenance equipment, the standard and special tools and all other items from the inspection area. (2) Obey the special precautions after the work on the passenger/crew door Ref. AMM TASK 52-10-00-860-002. (3) Close applicable passenger/crew door 831 or 841 or 832 or 842 Ref. AMM TASK 5210-00-410-001. (4) Obey the special precautions after the work on the emergency exit Ref. AMM TASK 52-22-00-860-004. (5) Make sure that the work area is clean and clear of tools and other items. (6) Close applicable emergency exit 835 or 845 Ref. AMM TASK 52-22-00-410-002. (7) Remove the access platform(s).

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 78-30-00-040-806-A - Deactivation of the Thrust Reverser System for Flight

CUSTOMIZATION

AIRCRAFT TYPES

DOCTYPES

A318 A319 AMM A321 A320

IGO

REVISION DATE

TITLE

TAIL NUMBER MSN - FSN

78-30-00-040-806-A - Deactivation 01-Augof the Thrust Reverser System for 2019 Flight

** ON A/C FSN 301-349, 351-450, 500-600 TASK 78-30-00-040-806-A Deactivation of the Thrust Reverser System for Flight 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: WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE) WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ, UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS NECESSARY. 1.

Reason for the Job Self explanatory

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific

QT Y AR WARNING NOTICE(S)

No specific B.

DESIGNATION

Torque wrench: range to between 31.5 and 35 lbf.in (0.36 and 0.40 m.daN)

Referenced Information REFERENCE

DESIGNATION

Ref. 71-00-00-860-833-A

Procedure to Prevent Engine Motoring

Ref. 71-13-00-010-802-A

Opening of the Fan Cowl Doors

Ref. 71-13-00-410-802-A

Closing of the Fan Cowl Doors

Ref. 78-30-00-040-805-A

Deactivation of the Thrust Reverser System for Ground Maintenance

Ref. 78-31-00-710-805-A

Operational Test of Thrust Reverser with MCDU

Ref. 78-31-00-710-805-A01

Thrust Reverser Cycling Test (Engine Running)

Ref. 78-32-36-000-801-A

Removal of the TRAS Lockout Pin Access Panel

Ref. 78-32-36-400-801-A

Installation of the TRAS Lockout Pin Access Panel

Ref. Fig. Deactivation/Reactivation of the Thrust Reverser for Flight Ref. Fig. Deactivation of the Thrust Reverser for Flight - Lockout Cover 3.

Job Set-up

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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SUBTASK 78-30-00-941-086-A A. Safety Precautions (1) Do the procedure to prevent engine motoring Ref. AMM TASK 71-00-00-860-833. SUBTASK 78-30-00-040-069-A B. Deactivation of the Thrust Reverser for Ground Maintenance 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) Do the deactivation of the thrust reverser system for ground maintenance Ref. AMM TASK 78-30-00-040-805. SUBTASK 78-30-00-010-105-A C. Get Access (1) Open the fan cowl doors Ref. AMM TASK 71-13-00-010-802 or the oil tank access door on the left fan cowl door. 4.

Procedure Ref. Fig. Deactivation/Reactivation of the Thrust Reverser for Flight Ref. Fig. Deactivation of the Thrust Reverser for Flight - Lockout Cover SUBTASK 78-30-00-040-070-A A. Deactivation of the Thrust Reverser for Flight WARNING: MAKE SURE THAT YOU DEACTIVATE THE TWO THRUST REVERSER DOORS ON THE SAME ENGINE FOR FLIGHT. IF ONE THRUST REVERSER DOOR DEPLOYS DURING FLIGHT, INJURY AND/OR DEATH CAN OCCUR. (1) Remove the screw (1) that attaches the translating sleeve lockout pins (2) in the double-clamp (3). (2) Open the double-clamp (3) and remove the translating sleeve lockout pins (2) from the fan case. (3) Install the screw (1) back on the double-clamp (3). (4) TORQUE the screw (1) to between 31.5 and 35 lbf.in (0.36 and 0.40 m.daN). (5) Remove the two bolts (4) and the lockout cover (5) from the latch beam Ref. AMM TASK 78-32-36-000-801. (6) Put the translating sleeve lockout pin (2) in the latch beam. (7) Turn the lockout cover (5) so the lockout pin hole lines up with the translating sleeve lockout pin (2). See Sheet 1 of the figure: Ref. Fig. Deactivation/Reactivation of the Thrust Reverser for Flight (8) Install the lockout cover (5) on the translating sleeve lockout pin (2) and the latch beam with the two bolts (4) Ref. AMM TASK 78-32-36-400-801. NOTE: The lockout cover (5) will not be flush with the surface of the latch beam. This is the correct configuration. See the figure: Ref. Fig. Deactivation of the Thrust Reverser for Flight - Lockout Cover (9) Do steps 4.A.(5) thru 4.A.(8) for the other thrust reverser door on the same engine. (10) Put the Hydraulic Control Unit (HCU) in the inhibited position. WARNING: MAKE SURE THE HYDRAULIC CONTROL UNIT (HCU) IS IN THE INHIBITED POSITION WHILE THE THRUST REVERSER IS DEACTIVATED FOR FLIGHT. IF THE HCU IS NOT IN THE INHIBITED POSITION, THE TWO TRANSLATING SLEEVES ON THE THRUST REVERSER CAN DEPLOY AND INJURY AND/OR DEATH CAN OCCUR. (a) Make sure the HCU stays in the inhibited position and the locking pin keeps it in place Ref. AMM TASK 78-30-00-040-805.

5.

Close-up

SUBTASK 78-30-00-860-064-A A. Put the aircraft back to its initial configuration. (1) Make sure that the work area is clean and clear of tools and other items. (2) Close the oil tank access door on the left fan cowl-door or the fan cowl doors Ref. AMM TASK 71-13-00-410-802. (3) Remove the WARNING NOTICE(S) mentioned in the job set-up. © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 2/6

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 78-30-00-040-806-A - Deactivation of the Thrust Reverser System for Flight

SUBTASK 78-30-00-710-070-A B. Test (1) Do the operational test of the thrust reverser with the MCDU. Ref. AMM TASK 78-3100-710-805 (a)

Make sure that the thrust reverser does not operate.

SUBTASK 78-30-00-860-063-A C. Aircraft Maintenance Configuration (1) Make an entry in the logbook to record the deactivation of the thrust reverser system. (2) Put a WARNING NOTICE(S) in position in the cockpit to show that the thrust reverser system is not serviceable for the dedicated engine.

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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1

A 2 x2

C

3

B FWD

A320NEO-AMM-783000-00015-00

ICN-GRAA320NEO-A-783000-G-51563-02457-A-002-01

OIL TANK ACCESS DOOR

B

A

N_MM_783000_4_QBM0_01_02

Figure 78-30-00-991-91500-21-A (SHEET 1/2) - Deactivation/Reactivation of the Thrust Reverser for Flight ** ON A/C FSN 301-349, 351-450, 500-600

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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4 x2 5

LATCH BEAM

4 x2

5

LATCH BEAM

2

A320NEO-AMM-783000-00016-00

ICN-GRAA320NEO-A-783000-G-51563-02458-A-001-01

ACTIVATED POSITION LH SHOWN; RH OPPOSITE

C

DEACTIVATED POSITION LH SHOWN; RH OPPOSITE

N_MM_783000_4_QBM0_02_02

Figure 78-30-00-991-91500-21-A (SHEET 2/2) - Deactivation/Reactivation of the Thrust Reverser for Flight ** ON A/C FSN 301-349, 351-450, 500-600

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 78-30-00-040-806-A - Deactivation of the Thrust Reverser System for Flight

4 5

LATCH BEAM

A

A 2

A

ICN-GRAA320NEO-A-783000-G-51563-03103-A-001-01

A DEACTIVATED POSITION LH SHOWN; RH OPPOSITE 2

4 5 LATCH BEAM

A A VIEW LOOKING FORWARD N_MM_783000_4_QCM0_01_00

Figure 78-30-00-991-93100-21-A (SHEET 1) - Deactivation of the Thrust Reverser for Flight - Lockout Cover ** ON A/C FSN 301-349, 351-450, 500-600

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

6/6

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IGO - A318 / A319 / A320 / A321 - AMM - 01-Aug-2019 - 79-00-00-281-802-A - Inspection of the Magnetic Chip Collectors for Oil Con…

CUSTOMIZATION

AIRCRAFT TYPES

DOCTYPES

A318 A319 AMM A321 A320

IGO

REVISION DATE

TITLE

TAIL NUMBER MSN - FSN

79-00-00-281-802-A - Inspection of 01-Augthe Magnetic Chip Collectors for Oil 2019 Contamination

** ON A/C FSN 301-349, 351-450, 500-600 TASK 79-00-00-281-802-A Inspection of the Magnetic Chip Collectors for Oil Contamination WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE AND THE ADJACENT COMPONENTS AFTER ENGINE SHUTDOWN. THE ENGINE, THE ENGINE OIL AND THE ADJACENT COMPONENTS CAN STAY HOT FOR A LONG TIME. IF YOU DO NOT OBEY THIS INSTRUCTION, INJURY CAN OCCUR. WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS. WARNING: WAIT FIVE MINUTES MINIMUM TO MAKE SURE THAT THE OIL SYSTEM IS NOT PRESSURIZED BEFORE YOU DO THIS PROCEDURE. IF YOU DO NOT OBEY THIS WARNING, INJURY CAN OCCUR. 1.

Reason for the Job Use this procedure to do an inspection of the six magnetic chip collectors. Five of the chip collectors are located on the lubrication and scavenge pump attached to the front of the Main Gearbox (MGB). The sixth chip collector is located on the No. 4 bearing compartment scavenge line. The lubrication and scavenge pump has bearing compartment designations to identify which chip collector is for which bearing compartment as follows: MGB Main Gearbox AGB Angle Gearbox FBC Forward Bearing Compartment (No. 1, 1.5 and 2 Bearing Compartments) and Fan Drive Gear System (FDGS) BC3 Bearing Compartment No. 3 BC4 Bearing Compartment No. 4 - Chip collector located on the scavenge line BC5 Bearing Compartment (No. 5 and 6).

2.

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE

B.

QT Y

DESIGNATION

No specific

1

ACCESS PLATFORM 1M(3 FT)

No specific

1

BOTTLE - SQUEEZE

No specific

1

CONTAINER 20L (5 USGAL)

No specific

1

MAGNIFYING GLASS POWER 20X

No specific

1

MICROSCOPE-BINOCULAR

PWA107802

1

PHOTOGRAPH, INSPECTION

Consumable Materials REFERENCE P03-001

DESIGNATION lubricant, aircraft turbine engine

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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REFERENCE

C.

DESIGNATION

P05-005

lint-free cotton cloth

P05-126

Brush, short bristle nylon

P05-181

Filter, paper

P11-014

isopropyl alcohol

P11-027

Petroleum Solvent

Work Zones and Access Panels ZONE/ACCESS 400

ZONE DESCRIPTION POWER PLANT, NACELLES AND PYLONS

FOR 4020KM1(POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR, 451AL, 452AR FOR 4020KM2(POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR, 461AL, 462AR D.

Expendable Parts FIG.ITEM 1

E.

DESIGNATION

IPC-CSN

packing

79-22-01-01 ITEM 020

Referenced Information REFERENCE

DESIGNATION

Ref. 71-00-00-860-833-A

Procedure to Prevent Engine Motoring

Ref. 71-13-00-010-802-A

Opening of the Fan Cowl Doors

Ref. 71-13-00-410-802-A

Closing of the Fan Cowl Doors

Ref. 78-30-00-040-805-A

Deactivation of the Thrust Reverser System for Ground Maintenance

Ref. 78-30-00-440-805-A

Reactivation of the Thrust Reverser System after Ground Maintenance

Ref. 78-36-00-010-802-A

Opening of the Thrust Reverser Cowl-Doors

Ref. 78-36-00-410-802-A

Closing of the Thrust Reverser Cowl-Doors

Ref. 79-00-00-210-811-A

Laboratory Analysis of the Engine Oil for Contamination

Ref. 79-21-06-960-801-A

Replacement of the Oil Filter Element

Ref. 79-22-01-000-801-A

Removal and Inspection of the Magnetic Chip Collector Assemblies

Ref. 79-22-01-400-801-A

Installation of the Magnetic Chip Collector Assemblies

Ref. 79-22-01-720-801-A

Functional Test of the Magnetic Chip Collectors

Ref. 80-11-00-200-801-A

Inspection of the Starter Magnetic Drain Plug for Oil Contamination

Ref. Fig. Inspection of the Magnetic Chip Collectors for Oil Contamination Ref. Fig. Inspection of the Magnetic Chip Collectors for Oil Contamination - (Chips, Flakes and Fines Troubleshooting) 3.

Job Set-up SUBTASK 79-00-00-941-084-A

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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A.

Safety Precautions (1) Do the procedure to prevent engine motoring Ref. AMM TASK 71-00-00-860-833.

SUBTASK 79-00-00-010-089-A B. Get Access (1) Open the fan cowl doors Ref. AMM TASK 71-13-00-010-802: (a)

FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR

(b) (2)

FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR Put an ACCESS PLATFORM 1M(3 FT) in position.

SUBTASK 79-00-00-040-059-A C. Deactivation of the Thrust Reverser for Ground Maintenance 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) Do the deactivation of the thrust reverser system for ground maintenance Ref. AMM TASK 78-30-00-040-805. SUBTASK 79-00-00-010-090-A D. Get Access (1) Open the thrust reverser cowl-doors Ref. AMM TASK 78-36-00-010-802: (a)

FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) - 451AL, 452AR

(b)

FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) - 461AL, 462AR.

CAUTION: WIPE CLEAN ALL PARTS AND TOOLS AS NECESSARY TO REMOVE UNWANTED DEBRIS AND PREVENT DAMAGE TO THE ENGINE. 4. Procedure Ref. Fig. Inspection of the Magnetic Chip Collectors for Oil Contamination Ref. Fig. Inspection of the Magnetic Chip Collectors for Oil Contamination - (Chips, Flakes and Fines Troubleshooting) SUBTASK 79-00-00-281-058-A A. Oil Analysis (1) Find the five magnetic chip collectors (2) on the lubrication and scavenge pump located on the left front side of the Main Gearbox (MGB) and the magnetic chip collector (2) on the no. 4 bearing compartment scavenge line. See sheet 1 and 2 of the figure: Ref. Fig. Inspection of the Magnetic Chip Collectors for Oil Contamination (2) Do the inspection of each chip collector (2) one at a time so that you know what the bearing compartment each collector (2) belongs to. The lubrication and scavenge pump is marked with the bearing compartment number next to each chip collector. CAUTION: WHEN YOU REMOVE CHIP COLLECTORS, DO NOT LET THEM TOUCH EACH OTHER. IF YOU DO, THE CHIP COLLECTORS CAN BECOME DEMAGNETIZED. (3) Make sure the magnetic chip collectors (2) do not touch each other. (4) Keep accurate records of all contamination on each chip collector (2). (5) If the engine or the MGB cannot continue in service, you must send the contamination and/or the analysis of the contamination with the engine or the MGB to the repair facility. (6) Push in and turn the chip collector (2) counterclockwise to disengage it from the valve. (7) If any of the chip collector valves leak oil continuously after the removal of the chip collector (2), replace the applicable magnetic-chip collector assembly as follows: NOTE: A few drops of oil may appear immediately after the chip collector (2) is removed. Wipe these drops away. If no additional drops appear the chip collector assembly does not need to be replaced. © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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(a)

If necessary, remove the magnetic-chip collector assemblies Ref. AMM TASK 7922-01-000-801.

(b) (8)

If necessary, install the magnetic-chip collector assemblies Ref. AMM TASK 7922-01-400-801. Do a visual inspection of each chip collector (2) for the contamination as follows. Use the PHOTOGRAPH, INSPECTION (PWA107802) to help identify the contamination. See sheets 3, 4 and 5 of the figure: Ref. Fig. Inspection of the Magnetic Chip Collectors for Oil Contamination (a)

Examine the chip collectors (2) with the MAGNIFYING GLASS POWER 20X. NOTE: You can use the MAGNIFYING GLASS POWER 20X however it is recommended you use the MICROSCOPE-BINOCULAR.

(b)

This procedure gives instructions on how to interpret the debris contamination that is on the magnetic chip collectors (2). For information on the methods of quantitative analysis and on the composition of the contamination, refer to Ref. AMM TASK 79-00-00-281-803. NOTE: If there is a question about the type of contamination you see, obey the action that follows the stricter interpretation.

(c)

(d)

There are four main types of the contamination: 1

Contamination from the assembly of the engine - build debris: Build debris collects during the early stages of engine operation after assembly of the engine. Build debris can look like strands of curly steel wool, shaving or burrs.

2

Fines: These are very small steel particles which show as a black sludge on the MCD. When the oil is removed they show as dull hair like slivers. Fines come from permitted engine wear. Bearing skid can also make fines, but the increased quantity will show during the analysis of the MCD samples. Fines are usually found on the engines that have operated for only a short time since new, repair or overhaul.

3

Chip: These are very thick flakes or pieces of metal which usually have one smooth machined surface and the opposite surface is rough and irregular.

4

Flakes: Flakes have irregular shapes, but are usually flat and shiny on both sides. You must do an analysis of them to know their source.

Examine the chip collector (2) with suitable magnification. If there is debris contamination, make a record of the quantity and type of debris contamination found and the pump location of the collector (2): 1

If the collector (2) is covered by oil, add a few drops of isopropyl alcohol (Material Ref. P11-014) to the collector tip. The alcohol should help break the surface tension of the oil and allow any metallic particles to be seen. NOTE: This condition where the collector tip is covered by a drop of oil is shown in the PHOTOGRAPH, INSPECTION (PWA107802) Photo Aid (Condition C). This condition is usually the result of fine metallic particles holding the oil near the collector (2) and the reason for performing the preceding step whenever these conditions are found.

2

If the chip collector (2) is clean with no contamination, it can be cleaned and reinstalled. Refer to steps in this task.

3

The types of debris contamination, their source and the corrective action necessary is as follows: Ref. Fig. Inspection of the Magnetic Chip Collectors for Oil Contamination (Chips, Flakes and Fines Troubleshooting)

4

Build debris contamination. See the sheet 3 of the figure: Ref. Fig. Inspection of the Magnetic Chip Collectors for Oil Contamination

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a

5

Action: The engine can continue in service. Operation is decreased to ten flight hours or five flight cycles, the lesser of the two, until the source of the debris contamination material can be identified. Do a spectroscopic analysis of the chips and flakes per Section G of the oil system oil analysis procedure Ref. AMM TASK 79-00-00-210-811. If the debris is from the bearing, gear or carbon seal carrier material, remove the engine from service and disassemble the engine enough to find the source of the material. If the debris is not from the bearing, gear or carbon seal material, return the engine to service. If the debris on FBC MCC is identified as AISI 52100 (AMS 6440), remove the engine in 50 flight hours unless the other debris results warrant more restrictive action.

Magnetic fines. See sheet 3 and 4 of the figure: Ref. Fig. Inspection of the Magnetic Chip Collectors for Oil Contamination NOTE: Fines are usually from the low time engines. Small quantities are serviceable. a

If there are fines on the chip collector (2) do the evaluation of the quantity, area and type of material. See the figure: Ref. Fig. Inspection of the Magnetic Chip Collectors for Oil Contamination - (Chips, Flakes and Fines Troubleshooting) If fines are found on the MGB chip collector probe surface, examine the starter-magnetic drain plug Ref. AMM TASK 8011-00-200-801.

b

If the fines are on 100 percent of the probe surface then remove the engine from service: If the fines are on 100 percent of the no. 3 bearing compartment probe surface, remove the engine in ten hours or five flight cycles, whichever is less. NOTE: If the no. 3 bearing compartment probe surface shows 100 percent coverage, it is not unusual to find equivalent unwanted fine coverage on the AGB probe and some coverage of the MGB probe. The ten hour or five flight cycle limit is also applicable to these conditions.

c

If the quantity of fines is more than 25 percent of the collector (2) tip perimeter but less than 100 percent of the probe surface, do a visual inspection of the main oil filter element for contamination as follows: If the MGB probe fines are greater than 25 percent of the probe tip perimeter bus less than 100 percent of the probe surface, do the steps that follow: 1. If replacement of the starter was necessary by Ref. AMM TASK 80-11-00-200-801, clean the MGB probe, drain the MGB oil, replace the oil filter and continue in service. 2. If replacement of the starter was not necessary, do an analysis of the fines. If bearing or gear material is found, remove the engine from service. Do a visual inspection of the main oil filter element for the contamination as follows. Remove the oil filter Ref. AMM TASK 79-21-06-960-801. Hold the oil filter over a clean CONTAINER 20L (5 USGAL). Use Petroleum Solvent (Material Ref. P11-027) with the Brush, short bristle nylon (Material Ref. P05-126) to remove any contamination from the outside screen area of the filter element. Petroleum Solvent (Material Ref. P11-027) may also be applied to the inside of the filter to back flush contamination to the outside screen area. Allow the Petroleum Solvent (Material Ref. P11-027) and the contamination to fall into the CONTAINER 20L (5 USGAL). Slowly put the Petroleum Solvent (Material Ref. P11-027), which

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-

-

-

6

is caught in the CONTAINER 20L (5 USGAL), through a Filter, paper (Material Ref. P05-181) or equivalent to catch the contamination in the Petroleum Solvent (Material Ref. P11-027). Try to keep the contamination in one area of the Filter, paper (Material Ref. P05-181) within a 0.5 in. (12.7 mm) diameter circle. Use the BOTTLE - SQUEEZE and more clean Petroleum Solvent (Material Ref. P11-027) to rinse all the contamination into the Filter, paper (Material Ref. P05-181) if necessary. If the collected main oil filter element debris contamination is across an area greater than a 0.5 in. (12.7 mm) diameter circle then remove the engine from service. If the debris contamination area on from the main oil filter element is less than a 0.5 in. (12.7 mm) diameter circle, do a spectroscopic analysis of the chips and flakes Ref. AMM TASK 79-00-00-210-811. Operation is decreased to ten flight hours or five flight cycles, the lesser of the two, until the source of the debris contamination material can be identified. If the fines from the chip collector and the filter are the same bearing, gear or carbon-seal carrier material, remove the engine from service and disassemble the engine enough to find the source of the material. If the fines from the chip collector and the filter are not the same bearing, gear or carbon-seal carrier material, install a new oil filter and return the engine to service. 1. Examine the chip collectors and filter again in 15 hours or less. 2. After the 15 hours or less inspection, you can install the filter again. If the debris on FBC MCC is identified as AISI 52100 (AMS 6440), remove the engine in 50 flight hours unless the other debris results warrant more restrictive action.

Chips or flakes. See sheet 5 of the figure: Ref. Fig. Inspection of the Magnetic Chip Collectors for Oil Contamination a

If there are chips or flakes on the chip collector (2) do the evaluation of the quantity, area and type: Ref. Fig. Inspection of the Magnetic Chip Collectors for Oil Contamination - (Chips, Flakes and Fines Troubleshooting) If five or less chips or flakes are found on the MGB chip collector probe surface, examine the starter magnetic drain plug Ref. AMM TASK 80-11-00-200-801.

b

If the main gearbox probe (2) has five or less chips or flakes on the chip collector, do the procedure that follows: If replacement of the starter was necessary Ref. AMM TASK 8011-00-200-801, clean the MGB probe, drain the MGB oil, replace the oil filter and continue in service. If replacement of the starter was not necessary, do an analysis of the chips and flakes. If bearing or gear material is found, remove the engine from service.

c

If there are six or more chips or flakes then remove the engine from service.

d

If the quantity of chips or flakes is less than six, do a visual inspection of the main oil filter element for debris or contamination by the procedure that follows: Remove the oil filter Ref. AMM TASK 79-21-06-960-801. Hold the oil filter over a clean CONTAINER 20L (5 USGAL). Use the Petroleum Solvent (Material Ref. P11-027) with the Brush, short bristle nylon (Material Ref. P05-126) to remove any contamination from the outside screen area of the filter element. Petroleum Solvent (Material Ref. P11-027) may also be

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(9)

applied to the inside of the filter to back flush contamination to the outside screen area. Allow the Petroleum Solvent (Material Ref. P11-027) and contamination to fall into the CONTAINER 20L (5 USGAL). Slowly put the Petroleum Solvent (Material Ref. P11-027) through a Filter, paper (Material Ref. P05-181) or equivalent to catch the contamination in the Petroleum Solvent (Material Ref. P11-027) . Try to keep the contamination in one area of the Filter, paper (Material Ref. P05-181) within a 0.5 in. (12.7 mm) diameter circle. Use the BOTTLE - SQUEEZE and more clean Petroleum Solvent (Material Ref. P11-027) to rinse all the contamination into the Filter, paper (Material Ref. P05-181) if necessary. If the collected main oil filter element debris contamination is across an area greater than a 0.5 in. (12.7 mm) diameter circle then remove the engine from service. If the debris contamination area on from the main oil filter element is less than a 0.5 in. (12.7 mm) diameter circle, do a spectroscopic analysis of the chips and flakes per Section G of Ref. AMM TASK 79-00-00-210-811. Operation is decreased to ten flight hours or five flight cycles, the lesser of the two, until the source of the debris contamination material can be identified. If the chips or flakes from the chip collector and the filter are the same bearing, gear or carbon-seal carrier material, remove the engine from service and disassemble the engine enough to find the source of the material. If the chips or flakes from the chip collector and the filter are not the same bearing, gear or carbon-seal carrier material, install a new oil filter and return the engine to service. 1. Examine the chip collectors and filter again in 15 hours or less. 2. After the 15 hours or less inspection, you can install the filter again. If the debris on FBC MCC is identified as AISI 52100 (AMS 6440), remove the engine in 50 flight hours unless the other debris results warrant more restrictive action. Examination of the Magnetic Chip Collectors (MCC)s with no ECAM alert: (a)

Use this section of the manual when the MCCs are examined for reasons other than when ECAM message ENGX OIL CHIP DETECTED and CLM ENGXD-0631OIL DEBRISOVERLIMIT DETECTED BY OD is shown and debris is found on the MCCs.

(b)

When you do normal engine operation, it is possible that small quantities of material from the gear, seal and bearing hardware can collect on the MCCs at a very low rate. This will not cause an ECAM alert. MCCs with fines less than 25 percent or build debris are normal and are not cause for the engine removal.

(c)

The Oil Debris Monitoring (ODM) system monitors debris in the oil system during engine operation and will set the "chip detected" alert when the rate of debris detected is more than the approved limit.

(d)

If debris is found on the MCCs without the ODM indication, do the procedure as follows: 1

Chips or flakes: If more than five chips or flakes, obey the current MCC inspection criteria.

2

Fines: If less than 25 percent of the collector (2) tip perimeter has fines, clean the MCC and return the engine to service. If debris coverage is less than 25 percent and an analysis shows the material to be the bearing, gear or carbon seal assembly material, the engine removal is not necessary. Examine the MCCs again by the current MCC inspection criteria in 25 flight hours or less.

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-

If debris is found at the next inspection, do an analysis of the material in ten hours or five cycles, that which occurs first. If debris is the bearing, gear or carbon seal material, remove the engine. If no debris is found at the next inspection, the engine can continue in service and you can install the filter again. If more than 25 percent of the collector (2) tip perimeter has fines, do an analysis of the material in ten hours or five cycles, that which occurs first. Obey the current MCC inspection criteria. (10) Prepare the chip collectors (2) for installation as follows. See sheet 1 and 2 of the figure: Ref. Fig. Inspection of the Magnetic Chip Collectors for Oil Contamination (a)

Use lint-free cotton cloth (Material Ref. P05-005) to remove all the contamination from the chip collectors (2).

(b)

Examine the packing (1) on each chip collector (2) for damage or wear.

(c)

If no visual damage or wear is found to the packing (1), you do not have to remove or replace the packing (1).

(d)

If you see any damage or wear, you must replace the packing as follows: 1

Discard the packing (1) form the chip collector (2).

2

Apply lubricant, aircraft turbine engine (Material Ref. P03-001) to the new PIPC-CSN(79-22-01-01 ITEM 020) packing (1).

3

Install the packing (1) to the chip collector (2).

(e)

If you think that the magnetic chip collector (2) is not functioning correctly, do a functional check of the magnetic chip collector Ref. AMM TASK 79-22-01-720801. (11) Install the six compartment-magnetic chip collectors (2) as follows. See the sheet 1 and 2 of the figure: Ref. Fig. Inspection of the Magnetic Chip Collectors for Oil Contamination (a)

Install the chip collectors (2) to the chip collector valves in the lubrication and scavenge pump.

(b)

Push in and turn each chip collector (2) clockwise to engage into the valve completely.

(c)

Pull on each chip collector (2) to make sure that it is fully engaged and locked in position. Table 601 - Inspection of the Magnetic Chip Collectors for Oil Contamination (Chips, Flakes and Fines Troubleshooting Chart) Reference Number

Instructions For Combined Chart For Chips, Flakes and Fine

(1)

Make sure that the debris is metallic. Coke or carbon particles are not the debris (crush if necessary to find composition of the debris).

(2)

If chips/flakes and fines are found, use the more careful path.

(3)

Build debris is usually found during the first 1000 hours of operation.

(4)

During this 50 flight hour period, the ECAM message ENGX OIL CHIP DETECTED can possibly come on. If it does, obey current AMM and Troubleshooting procedures to make sure debris source is not from other bearing compartments and new results do not warrant more restrictive action.

(12) Examine the assembly for foreign objects, damage and correct assembly. 5.

Close-up

SUBTASK 79-00-00-410-076-A A. Close Access (1) Make sure that the work area is clean and clear of tools and other items. © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 8/15

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(2)

Close the thrust reverser cowl-doors Ref. AMM TASK 78-36-00-410-802: (a)

FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 451AL, 452AR

(b)

FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 461AL, 462AR

SUBTASK 79-00-00-440-059-A B. Do the reactivation of the thrust reverser system after ground maintenance Ref. AMM TASK 78-30-00-440-805. SUBTASK 79-00-00-410-077-A C. Close Access (1) Close the fan cowl doors Ref. AMM TASK 71-13-00-410-802: (a)

FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1) 437AL, 438AR

(b) (2) (3)

FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2) 447AL, 448AR Remove the access platform(s). Remove the WARNING NOTICE(S).

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B A

ICN-PW1000G-C-790000-P-77445-05993-A-003-01 H-05993 (0418) PW V

MAGNETIC CHIP COLLECTOR

LUBRICATION AND SCAVENGE PUMP

ALIGNMENT INDICATOR

C

MAGNETIC CHIP COLLECTOR TYPICAL 5 LOCATIONS

A N_MM_790000_3_QAM0_01_02

Figure 79-00-00-991-48200-21-A (SHEET 1/5) - Inspection of the Magnetic Chip Collectors for Oil Contamination ** ON A/C FSN 301-349, 351-450, 500-600

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HIGH PRESSURE TURBINE CASE OIL TUBE (LR40)

ALIGNMENT INDICATOR

C

MAGNETIC CHIP COLLECTOR

ICN-PW1000G-C-790000-P-77445-05994-A-003-01 H-05994 (0418) PW V

B

D 1 PACKING 2 MAGNETIC CHIP COLLECTOR

C TYPICAL 6 LOCATIONS N_MM_790000_3_QAM0_02_02

Figure 79-00-00-991-48200-21-A (SHEET 2/5) - Inspection of the Magnetic Chip Collectors for Oil Contamination ** ON A/C FSN 301-349, 351-450, 500-600

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BUILD DEBRIS BUILD DEBRIS

MACHINE CURL

MAGNETIC TIP OF THE CHIP COLLECTOR

ICN-PW1000G-C-790000-P-77445-05995-A-001-01 PW-R

MAGNETIC FINES

MAGNETIC TIP OF THE CHIP COLLECTOR

(OPTIONAL VIEW)

D N_MM_790000_3_QAM0_03_03

Figure 79-00-00-991-48200-21-A (SHEET 3/5) - Inspection of the Magnetic Chip Collectors for Oil Contamination ** ON A/C FSN 301-349, 351-450, 500-600

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25% TIP PERIMETER MAGNETIC TIP TIP PERIMETER

MAGNETIC FINES

ICN-PW1000G-C-790000-P-77445-05989-A-001-01 PW-R

MAGNETIC BODY

D (OPTIONAL VIEW)

N_MM_790000_3_QAM0_04_02

Figure 79-00-00-991-48200-21-A (SHEET 4/5) - Inspection of the Magnetic Chip Collectors for Oil Contamination ** ON A/C FSN 301-349, 351-450, 500-600

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METALLIC FLAKES

SLIVER

MAGNETIC TIP OF THE CHIP COLLECTOR

ICN-PW1000G-C-790000-P-77445-06149-A-001-01 PW-R

CHIP (SMOOTH SURFACE)

CHIP (ROUGH SURFACE) MAGNETIC TIP OF THE CHIP COLLECTOR

MAGNETIC TIP OF THE CHIP COLLECTOR

D (OPTIONAL VIEW)

N_MM_790000_3_QAM0_05_03

Figure 79-00-00-991-48200-21-A (SHEET 5/5) - Inspection of the Magnetic Chip Collectors for Oil Contamination ** ON A/C FSN 301-349, 351-450, 500-600

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TYPE OF METALLIC (1) FOR NON - ODM MCC RESULTS, REFER TO STEP 10.D.7 DEBRIS IDENTIFIED (2)

EXAMINE ALL CHIP COLLECTORS

CHIPS OR FLAKES ARE IDENTIFIED

A ARE THERE MORE THAN 5 CHIPS OR FLAKES

NO

YES

IS THE DEBRIS ON MORE THAN 25% OF THE PROBE TIP PERIMETER

FINES ARE IDENTIFIED

BUILD DEBRIS (3)

IS THE DEBRIS ON 100% OF THE PROBE TIP SURFACE

NO

YES

IS THE DEBRIS ON THE NO. 3 PROBE

YES

NO

NO

EXAMINE THE OIL FILTER AND HOUSING FOR DEBRIS CONTAMINATION

YES

REMOVE THE ENGINE IN 10 FLIGHT HOURS OR 5 FLIGHT CYCLES, WHICH EVER IS LESS

NO

A

YES

DISASSEMBLE THE ENGINE OR DAMAGED COMPONENT TO FIND THE SOURCE OF THE MATERIAL

NO

IS THE DEBRIS YES

FROM THE CHIP COLLECTOR AND FILTER THE SAME BEARING, GEAR, OR CARBON SEAL CARRIER MATERIAL

NO

IF THE DEBRIS ON FBC MCC IS IDENTIFIED AS AISI 52100 (AMS 6440), REMOVE THE ENGINE IN 50 FLIGHT HOURS UNLESS OTHER DEBRIS RESULTS WARRANT MORE RESTRICTIVE ACTION.

(4)

EXAMINE MCCS AND OIL FILTER AGAIN IN 15 FLIGHT HOURS OR LESS

NOTE: See the table titled Inspection Of The Magnetic Chip Collectors For Oil Contamination - (Chips, Flakes, And Fines Troubleshooting Chart) for (1), (2), (3), and (4). PW-R

ICN-PW1000G-C-790000-P-77445-05991-A-012-01

REMOVE THE ENGINE

IS THE DEBRIS CONTAMINATION ACROSS AN AREA LARGER THAN A 0.500 INCH (12.700 mm) DIAMETER CIRCLE

ANALYZE THE COMPOSITION OF THE DEBRIS CONTAMINATION ON THE CHIP COLLECTORS AND FILTER IN 10 FLIGHT HOURS OR 5 FLIGHT CYCLES, WHICHEVER IS LESS.

CLEAN CHIP COLLECTORS AND RETURN TO SERVICE N_MM_790000_3_QBM0_01_05

Figure 79-00-00-991-48300-21-A (SHEET 1) - Inspection of the Magnetic Chip Collectors for Oil Contamination - (Chips, Flakes and Fines Troubleshooting) ** ON A/C FSN 301-349, 351-450, 500-600

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AIRCRAFT MAINTENANCE MANUAL

ADVANCE COPY THE DATA GIVEN IN THIS ADVANCE COPY IS APPROVED FOR USE PENDING ISSUE OF THE REVISION DATED Nov 01/2019

Subject

79-35-00-04 CONF 03 / 79-35-00-040-809-A

NOTE: AIRBUS OIT 999.0134/03 dated 14 NOV 2003 outlines the regulatory aspects of advance data, which are authorized for temporary use till the data are released at the indicated issue date of the regular revision service

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A318/A319/A320/A321

AIRCRAFT MAINTENANCE MANUAL ** ON A/C FSN 516-600 TASK 79-35-00-040-809-AReplacement of the Engine Oil Filter and Inspection of the Scavenge Screen Plug 1.

Reason for the Job MMEL 79-09-02A ENG 1(2) OIL FILTER CLOG ALERT MMEL 79-09-04B ENG 1(2) OIL FILTER DEGRAD ALERT MMEL 79-09-05B ENG 1(2) OIL SENSOR FAULT ALERT MMEL 79-09-07B ENG 1(2) OIL FILTER - PARTLY CLOGGED ALERT

2.

Job Set-up Information A. Referenced Information REFERENCE

3.

DESIGNATION

79-00-00-200-806

Visual Inspection of the A, B and C Sumps, the Accessory Gearbox (AGB) and the Transfer Gearbox (TGB) Sump Scavenge Screen Plugs for Debris

79-21-05-000-803

Removal of the Oil Filter Cartridge

79-21-05-400-803

Installation of the Oil Filter Cartridge

Job Set-up SUBTASK 79-35-00-860-064-A A. Non Applicable

4.

Procedure SUBTASK 79-35-00-960-053-A A. Do the replacement of the Oil Filter Ref. AMM TASK 79-21-05-000-803 and Ref. AMM TASK 79-21-05-400-803. SUBTASK 79-35-00-281-051-A B. Do the inspection of the scavenge screen plugs Ref. AMM TASK 79-00-00-200-806 . (1)

5.

Check that there is no presence of chips

Close-up SUBTASK 79-35-00-860-065-A A. Aircraft Maintenance Configuration (1)

IGO

Make an entry in the logbook to record that the Oil Filter has been changed.

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A318/A319/A320/A321

AIRCRAFT MAINTENANCE MANUAL

ADVANCE COPY THE DATA GIVEN IN THIS ADVANCE COPY IS APPROVED FOR USE PENDING ISSUE OF THE REVISION DATED Nov 01/2019

Subject

79-35-00-04 CONF 03 / 79-35-00-040-808-A

NOTE: AIRBUS OIT 999.0134/03 dated 14 NOV 2003 outlines the regulatory aspects of advance data, which are authorized for temporary use till the data are released at the indicated issue date of the regular revision service

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A318/A319/A320/A321

AIRCRAFT MAINTENANCE MANUAL ** ON A/C FSN 516-600 TASK 79-35-00-040-808-AEngine Oil Filter and Oil Debris Monitoring System (ODMS) Operational Check 1.

Reason for the Job MMEL 79-09-02D ENG 1(2) OIL FILTER CLOG ALERT MMEL 79-09-04C ENG 1(2) OIL FILTER DEGRAD ALERT MMEL 79-09-05C ENG 1(2) OIL SENSOR FAULT ALERT MMEL 79-09-07C ENG 1(2) OIL FILTER - PARTLY CLOGGED ALERT

2.

Job Set-up Information A. Referenced Information REFERENCE

3.

DESIGNATION

73-29-00-710-802

FADEC Test (Menu Mode)

79-21-05-000-803

Removal of the Oil Filter Cartridge

79-21-05-400-803

Installation of the Oil Filter Cartridge

Job Set-up SUBTASK 79-35-00-860-062-A A. Not applicable

4.

Procedure SUBTASK 79-35-00-960-052-A A. Do the replacement of the Oil Filter Ref. AMM TASK 79-21-05-000-803 and Ref. AMM TASK 79-21-05-400-803. SUBTASK 79-35-00-720-052-A B. Do a FADEC Test Ref. AMM TASK 73-29-00-710-802. (1)

5.

Make sure that the message "ENGXB ODMS SENSOR MONITOR" does not come into view.

Close-up SUBTASK 79-35-00-860-063-A A. Aircraft Maintenance Configuration (1)

IGO

Make an entry in the logbook to record that the Oil Filter has been changed and the ODMS checked operational.

Issue date: Oct 10/2019 Page 2 of 2