Low range Leak Test of the Standby Pneumatic circuits

TASK 34-22-25-790-001-A
Low range Leak Test of the Standby Pneumatic circuits

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 SAFETY DEVICES AND THE WARNING NOTICES ARE IN POSITION BEFORE YOU START A TASK ON OR NEAR:

THE FLIGHT CONTROLS
THE FLIGHT CONTROL SURFACES
THE LANDING GEAR AND RELATED DOORS
COMPONENTS THAT MOVE.

MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

WARNING: 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: TO PREVENT DAMAGE TO INSTRUMENTS, OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST:

THE PRESSURES SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR LESS THAN 115 hPa (3.39 in Hg)
CHANGES IN STATIC AND TOTAL PRESSURES MUST NOT BE MORE THAN 6000 FEET/MINUTE
DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE PRESSURE GENERATOR IS CONNECTED.

CAUTION: THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS THAN THE STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT AND THE STATIC PRESSURE CIRCUITS MUST NEVER BE MORE THAN 368 hPa (10.86 in Hg).

ZONE: 120
ZONE: 210

1. Reason for the Job
Refer to the MPD TASK: 342200-05
LOW RANGE LEAK TEST OF STANDBY PNEUMATIC CIRCUITS
To make sure that there are no leaks in the standby static and standby pitot circuits.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	AR	TAPE - ADHESIVE
No specific	AR	WARNING NOTICE(S)
ALT34100001	1	PITOT AND STATIC TEST SET

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
120	AVIONICS COMPARTMENT
210	CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD

C. Referenced Information

REFERENCE	DESIGNATION
TASK 24-41-00-861-002-A	Energize the Aircraft Electrical Circuits from the External Power
TASK 24-41-00-861-002-A-01	Energize the Aircraft Electrical Circuits from the APU
TASK 24-41-00-861-002-A-02	Energize the Aircraft Electrical Circuits from Engine 1(2)
TASK 24-41-00-862-002-A	De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 24-41-00-862-002-A-01	De-energize the Aircraft Electrical Circuits Supplied from the APU
TASK 24-41-00-862-002-A-02	De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)
TASK 27-50-00-866-009-A	Retraction of the Flaps on the Ground
TASK 27-50-00-866-009-A-01	Retraction of the Flaps/Slats on the Ground
TASK 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
TASK 34-11-15-200-001-A	Inspection/Check of the Pitot Probe
Static and Pitot Probes of the Standby System
Setting of the AOA Sensor Vane to the High Stop Position

3. Job Set-up
Subtask 34-22-25-860-053-A ** ON A/C NOT FOR ALL

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

Subtask 34-22-25-875-050-A ** ON A/C NOT FOR ALL

WARNING: OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED.

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	ANTI ICE/PROBES/AOA/1	4DA1	D04
49VU	ANTI ICE/PROBES/PITOT/1	3DA1	D02
105VU	ELEC/CSM/G /EV AUTO/SPLY	7XE	C01
122VU	ANTI ICE/PROBES/2/TAT	1DA2	Y15
122VU	ANTI ICE/PROBES/2/PITOT	3DA2	Y14
122VU	ANTI ICE/PROBES/2/AOA	4DA2	Y13
122VU	ANTI ICE/PROBES/2/STATIC	5DA2	Y11
122VU	ANTI ICE/PROBES/3/PITOT	3DA3	Z16
122VU	ANTI ICE/PROBES/3/AOA	4DA3	Z15
122VU	ANTI ICE/PROBES/3/STATIC	5DA3	Z14
122VU	ANTI ICE/PROBES/1/STATIC	5DA1	Z13
122VU	ANTI ICE/PROBES/1/TAT	1DA1	Z12

Subtask 34-22-25-875-050-B ** ON A/C NOT FOR ALL

WARNING: OPEN CIRCUIT BREAKER 7XE. THIS WILL PREVENT A POSSIBLE DEPLOYMENT OF THE RAT IF THE MAIN AC BUSBARS 1XP AND 2XP BECOME ISOLATED.

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	ANTI ICE/PROBES/AOA/1	4DA1	D04
49VU	ANTI ICE/PROBES/PITOT/1	3DA1	D02
105VU	ELEC/CSM/G /EV AUTO/SPLY	7XE	C01
121VU	COM NAV/RAD ALTM/2	1SA2	K12
121VU	COM NAV/RAD ALTM/1	1SA1	K11
122VU	ANTI ICE/PROBES/2/TAT	1DA2	Y15
122VU	ANTI ICE/PROBES/2/PITOT	3DA2	Y14
122VU	ANTI ICE/PROBES/2/AOA	4DA2	Y13
122VU	ANTI ICE/PROBES/2/STATIC	5DA2	Y11
122VU	ANTI ICE/PROBES/3/PITOT	3DA3	Z16
122VU	ANTI ICE/PROBES/3/AOA	4DA3	Z15
122VU	ANTI ICE/PROBES/3/STATIC	5DA3	Z14
122VU	ANTI ICE/PROBES/1/STATIC	5DA1	Z13
122VU	ANTI ICE/PROBES/1/TAT	1DA1	Z12

Subtask 34-22-25-865-070-A ** ON A/C NOT FOR ALL

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	NAV/STBY/INST	5FN	F12
105VU	NAV/STBY/INST/BAT	23FN	J01
** ON A/C NOT FOR ALL
FOR FIN: 2CE1 (ELAC1)
49VU	FLIGHT CONTROLS/ELAC1/NORM/SPLY	15CE1	B11
** ON A/C NOT FOR ALL
49VU	FLIGHT CONTROLS/ELAC1/NORM/SPLY	15CE1	B06
** ON A/C NOT FOR ALL
105VU	FLT CTL/ELAC1/STBY SPLY	16CE1	A01
FOR FIN: 2CE2 (ELAC2)
105VU	FLIGHT CONTROLS/ELAC2/STBY SPLY	16CE2	A02
121VU	FLIGHT CONTROLS/ELAC2/NORM/SPLY	15CE2	R20

Subtask 34-22-25-420-050-A ** ON A/C NOT FOR ALL

D. Connection of the Ground Pressure Generator

Static and Pitot Probes of the Standby System ** ON A/C NOT FOR ALL

(1) Remove the slip on covers from static probes 7DA3, 8DA3 and pitot probe 9DA3 of the standby system.
(2) Connect the ALT34100001 PITOT AND STATIC TEST SET (1) to one standby static-probe with the ADAPTER STATIC PROBE (4).
(3) Connect the ALT34100001 PITOT AND STATIC TEST SET (1) to the standby pitot probe with ADAPTER PITOT PROBE (2) or (3).
(4) Seal the opposite standby static-probe with a piece of plastic and with the ADAPTER STATIC COVER.
(5) Turn the vane of Angle Of Attack (AOA) sensor 3FP3 to the high stop position.

Setting of the AOA Sensor Vane to the High Stop Position ** ON A/C NOT FOR ALL

Keep the vane in position with the color TAPE - ADHESIVE.

Subtask 34-22-25-860-067-A ** ON A/C NOT FOR ALL

E. Aircraft Maintenance Configuration
(1) Do the EIS start procedure (PFD only) (Ref. AMM TASK 31-60-00-860-001).
(2) Make sure that the flaps are in the fully retracted position (Ref. AMM TASK 27-50-00-866-009).
(3) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to NAV.
(4) Start the ALT34100001 PITOT AND STATIC TEST SET.

Subtask 34-22-25-860-067-C ** ON A/C NOT FOR ALL

E. Aircraft Maintenance Configuration
(1) Do the EIS start procedure (PFD only) (Ref. AMM TASK 31-60-00-860-001).
(2) Make sure that the flaps are in the fully retracted position (Ref. AMM TASK 27-50-00-866-009).
(3) On ADIRS MSU panel 41VU, set the OFF/NAV/ATT selector switches to NAV.
(4) Start the ALT34100001 PITOT AND STATIC TEST SET.

Subtask 34-22-25-860-067-E ** ON A/C NOT FOR ALL

Make sure that the ON legend of the ENG/FADEC GND PWR 1 and ENG/FADEC GND PWR2 pushbutton switches are off.
Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC system.

(4) On ADIRS MSU panel 41VU, set the OFF/NAV/ATT selector switches to NAV.
(5) Start the ALT34100001 PITOT AND STATIC TEST SET.

4. Procedure
Subtask 34-22-25-790-050-A ** ON A/C NOT FOR ALL

A. Leak Test

NOTE: The input parameters for the ground test (speed and altitude) and the values shown on the cockpit displays are different. This is because of the sum of the tolerances of the air data circuit (the ground test unit, Air Data Modules (ADMs) and Air Data/Inertial Reference Units (ADIRUs)).

ACTION	RESULT
1.On left center instrument-panel 401VU, on the ISIS indicator: Push and turn the barometric (BARO) selector knob to set the altitude reference to STD.	At the bottom of the ISIS indicator screen, the STD indication comes into view.
2.On the Flight Control Unit (FCU), pull the CAPT (F/O) PULL STD barometric-setting knob.	On the PFD, the STD indication comes into view below the altitude scale.
3.On the ground pressure generator: Do the pre-test that follows for a static pressure of 691.4 hPa (20.42 in.Hg) and an impact pressure of 59 hPa (1.74 in.Hg) (or a total pressure of 750.4 hPa (22.16 in.Hg) ). This pre-test is not as accurate as the leak test.
4.On SWITCHING panel 8VU, set the AIR DATA selector switch to the CAPT ON 3 (or the F/O ON 3) position.	On the CAPT (or the F/O) PFD, the indications from ADIRU3 are shown.
Make sure that: The CAPT (or the F/O) PFD shows 10237 -30 ft. or +30 ft. (3120.18 -9.14 m or +9.14 m) and 190 kts +/- 3 kts. The ISIS indicator shows 10201 -50 ft. or +50 ft. (3109.21 -15.24 m or +15.24 m) and an airspeed of 189 kts +/- 5 kts.	After 5 minutes: The change of altitude must not be more than 370 ft. (112.77 m). The change of airspeed must not be more than 10 kts.
5.On the ground pressure generator: Set a static pressure of 455.4 hPa (13.45 in.Hg).
Set an impact pressure of 186.4 hPa (5.50 in.Hg) (or a total pressure of 641.8 hPa (18.95 in.Hg) or 320 kts).
Close the electrovalves to isolate the static and the pitot circuits of the aircraft from the ground pressure generator.	Make sure that: - The CAPT (or the F/O) PFD shows 21371 -40 ft. or +40 ft. (6513.76 -12.19 m or +12.19 m) and 342 kts +/- 3 kts. - The ISIS indicator shows 20529 -85 ft. or +85 ft. (6257.12 -25.91 m or +25.91 m) and 329 kts +/- 8 kts. After 5 minutes, on the ISIS display and on the CAPT (or the F/O) PFD: Make sure that the change of altitude is not more than 500 ft. (152.40 m). After 10 minutes: Make sure that the change of airspeed is not more than 20 kts.
Open the electrovalves and slowly balance the pressure in the standby static and pitot circuits.	The rate of descent must not be more than 6000 ft/min.

Subtask 34-22-25-790-050-B ** ON A/C NOT FOR ALL

A. Leak Test

ACTION	RESULT
1.On left center instrument-panel 401VU, on the ISIS indicator: Push and turn the barometric (BARO) selector knob to set the altitude reference to STD.	At the bottom of the ISIS indicator screen, the STD indication comes into view.
2.On the Flight Control Unit (FCU), pull the CAPT (F/O) PULL STD barometric-setting knob.	On the PFD, the STD indication comes into view below the altitude scale.
3.On the ground pressure generator: Do the pre-test that follows for a static pressure of 690 hPa (20.38 in.Hg) and an impact pressure of 60.4 hPa (1.78 in.Hg) (or a total pressure of 750.4 hPa (22.16 in.Hg) ). This pre-test is not as accurate as the leak test.
4.On SWITCHING panel 8VU, set the AIR DATA selector switch to the CAPT ON 3 (or the F/O ON 3) position.	On the CAPT (or F/O) PFD, the indications from ADIRU3 are shown.
Make sure that: The CAPT (or the F/O) PFD shows 10225 -30 ft. or +30 ft. (3116.52 -9.14 m or +9.14 m) and 190 kts +/- 3 kts. The ISIS indicator shows 10253 -50 ft. or +50 ft. (3125.06 -15.24 m or +15.24 m) and an airspeed of 191 kts +/- 5 kts.	After 5 minutes: The change of altitude must not be more than 370 ft. (112.77 m). The change of airspeed must not be more than 10 kts.
5.On the ground pressure generator: Set a static pressure of 447.9 hPa (13.23 in.Hg).
Set an impact pressure of 193.9 hPa (5.73 in.Hg) (or a total pressure of 641.8 hPa (18.95 in.Hg) or 320 kts).
Close the electrovalves to isolate the static and the pitot circuits of the aircraft from the ground pressure generator.	Make sure that: - The CAPT (or the F/O) PFD shows 21896 -40 ft. or +40 ft. (6673.78 -12.19 m or +12.19 m) and 349 kts +/- 3 kts. - The ISIS indicator shows 20923 -85 ft. or +85 ft. (6377.21 -25.91 m or +25.91 m) and 335 kts +/- 8 kts. After 5 minutes, on the ISIS display and on the CAPT (or the F/O) PFD: Make sure that the change of altitude is not more than 500 ft. (152.40 m). After 10 minutes: Make sure that the change of airspeed is not more than 20 kts.
Open the electrovalves and slowly balance the pressure in the standby static and pitot circuits.	The rate of descent must not be more than 6000 ft/min.

Subtask 34-22-25-790-050-S ** ON A/C NOT FOR ALL

A. Leak Test

NOTE: The input parameters for the ground test (speed and altitude) and the values shown on the cockpit displays are different. This is because of the sum of the tolerances of the air data circuit (ground test unit, Air Data Modules (ADMs) and Air Data/Inertial Reference Units (ADIRUs)).

ACTION	RESULT
1.On left center instrument-panel 401VU, on the ISIS indicator: Push and turn the barometric (BARO) selector knob to set the altitude reference to STD.	At the bottom of the ISIS indicator screen, the STD indication comes into view.
2.On the Flight Control Unit (FCU), pull the CAPT (F/O) PULL STD barometric-setting knob.	On the PFD, the STD indication comes into view below the altitude scale.
3.On the ground pressure generator: Do the pre-test that follows for a static pressure of 690 hPa (20.38 in.Hg) and an impact pressure of 60.2 hPa (1.78 in.Hg) (or a total pressure of 750.2 hPa (22.15 in.Hg) ). This pre-test is not as accurate as the leak test.
4.On SWITCHING panel 8VU, set the AIR DATA selector switch to the CAPT ON 3 (or the F/O ON 3) position.	On the CAPT (or the F/O) PFD, the indications from ADIRU3 are shown.
Make sure that: The CAPT (or the F/O) PFD shows 10208 -30 ft. or +30 ft. (3111.34 -9.14 m or +9.14 m) and 189 kts +/- 3 kts. The ISIS indicator shows 10253 -50 ft. or +50 ft. (3125.06 -15.24 m or +15.24 m) and an airspeed of 191 kts +/- 5 kts.	After 5 minutes: The change of altitude must not be more than 370 ft. (112.77 m). The change of airspeed must not be more than 10 kts.
5.On the ground pressure generator: Set a static pressure of 447.9 hPa (13.23 in.Hg).
Set an impact pressure of 193.9 hPa (5.73 in.Hg) (or a total pressure of 641.8 hPa (18.95 in.Hg) or 334 kts).
Close the electrovalves to isolate the static and the pitot circuits of the aircraft from the ground pressure generator.	Make sure that: - The CAPT (or the F/O) PFD shows 21896 -30 ft. or +30 ft. (6673.78 -9.14 m or +9.14 m) and 349 kts +/- 3 kts. - The ISIS indicator shows 20923 -85 ft. or +85 ft. (6377.21 -25.91 m or +25.91 m) and 335 kts +/- 8 kts. After 5 minutes, on the ISIS display and on the CAPT (or the F/O) PFD: Make sure that the change of altitude is not more than 500 ft. (152.40 m). After 10 minutes: Make sure that the change of airspeed is not more than 20 kts.
Open the electrovalves and slowly balance the pressure in the standby static and pitot circuits.	The rate of descent must not be more than 6000 ft/min.

Subtask 34-22-25-790-050-T ** ON A/C NOT FOR ALL

A. Leak Test

ACTION	RESULT
1.On left center instrument-panel 401VU, on the ISIS indicator: Push and turn the barometric (BARO) selector knob to set the altitude reference to STD.	At the bottom of the ISIS indicator screen: The STD indication comes into view.
2.On the Flight Control Unit (FCU), pull the CAPT (F/O) PULL STD barometric-setting knob.	On the PFD: The STD indication comes into view below the altitude scale.
3.On the ground pressure generator: Do the pre-test that follows for a static pressure of 689 hPa (20.35 in.Hg) and an impact pressure of 61.3 hPa (1.81 in.Hg) (or a total pressure of 750.3 hPa (22.16 in.Hg) ). This pre-test is not as accurate as the leak test.
4.On SWITCHING panel 8VU: Set the AIR DATA selector switch to the CAPT ON 3 (or the F/O ON 3) position.	On the CAPT (or the F/O) PFD: The indications from ADIRU3 are shown.
Make sure that: The CAPT (or the F/O) PFD shows the altitude value of 10215 -30 ft. or +30 ft. (3113.47 -9.14 m or +9.14 m) and the airspeed value of 189 kts +/- 3 kts. The ISIS indicator shows the altitude value of 10290 -50 ft. or +50 ft. (3136.33 -15.24 m or +15.24 m) and the airspeed value of 192.5 kts +/- 5 kts.	After five minutes: The change of altitude must not be more than 370 ft. (112.77 m). The change of airspeed must not be more than 10 kts.
5.On the ground pressure generator: Set a static pressure of 455.2 hPa (13.44 in.Hg).
Set an impact pressure of 186.4 hPa (5.50 in.Hg) (or a total pressure of 641.6 hPa (18.95 in.Hg)).
Close the electrovalves to isolate the static and the pitot circuits of the aircraft from the ground pressure generator.	Make sure that: - The CAPT (or the F/O) PFD shows 21420 -40 ft. or +40 ft. (6528.70 -12.19 m or +12.19 m) and 342 kts +/- 3 kts. - The ISIS indicator shows 20540 -85 ft. or +85 ft. (6260.48 -25.91 m or +25.91 m) and 329 kts +/- 8 kts. After five minutes, on the ISIS display and on the CAPT (or the F/O) PFD: Make sure that the change of altitude is not more than 500 ft. (152.40 m). After ten minutes: Make sure that the change of airspeed is not more than 20 kts.
Open the electrovalves and slowly balance the pressure in the standby static and pitot circuits.	The rate of descent must not be more than 6000 ft/min.

Subtask 34-22-25-790-050-V ** ON A/C NOT FOR ALL

A. Leak Test

NOTE: The input parameters for the ground test (speed and altitude) and the values shown on the cockpit displays are different. This is because of the sum of the tolerances of the air data circuit (ground test unit, Air Data Modules (ADM) and Air Data/Inertial Reference Units (ADIRU)).

ACTION	RESULT
1.On left center instrument-panel 401VU, on the ISIS indicator: Push and turn the barometric (BARO) selector knob to set the altitude reference to STD.	At the bottom of the ISIS indicator screen: The STD indication comes into view.
2.On the Flight Control Unit (FCU), pull the CAPT (F/O) PULL STD barometric-setting knob.	On the PFD: The STD indication comes into view below the altitude scale.
3.On the ground pressure generator: Do the pre-test that follows for a static pressure of 690 hPa (20.38 in.Hg) and an impact pressure of 60.3 hPa (1.78 in.Hg) (or a total pressure of 750.3 hPa (22.16 in.Hg) ). This pre-test is not as accurate as the leak test.
4.On SWITCHING panel 8VU: Set the AIR DATA selector switch to the CAPT ON 3 (or the F/O ON 3) position.	On the CAPT (or the F/O) PFD: The indications from ADIRU3 are shown.
Make sure that: The CAPT (or the F/O) PFD shows the altitude value of 10210 -30 ft. or +30 ft. (3111.95 -9.14 m or +9.14 m) and the airspeed value of 189 kts +/- 3 kts. The ISIS indicator shows the altitude value of 10250 -50 ft. or +50 ft. (3124.14 -15.24 m or +15.24 m) and the airspeed value of 190 kts +/- 5 kts.	After five minutes: The change of altitude must not be more than 370 ft. (112.77 m). The change of airspeed must not be more than 10 kts.
5.On the ground pressure generator: Set a static pressure of 448.5 hPa (13.24 in.Hg).
Set an impact pressure of 193.1 hPa (5.70 in.Hg) (or a total pressure of 641.6 hPa (18.95 in.Hg) ).
Close the electrovalves to isolate the static and the pitot circuits of the aircraft from the ground pressure generator.	Make sure that: - The CAPT (or the F/O) PFD shows 21870 -40 ft. or +40 ft. (6665.85 -12.19 m or +12.19 m) and 349 kts +/- 3 kts. - The ISIS indicator shows 20890 -85 ft. or +85 ft. (6367.16 -25.91 m or +25.91 m) and 335 kts +/- 8 kts. After five minutes, on the ISIS display and on the CAPT (or the F/O) PFD: Make sure that the change of altitude is not more than 500 ft. (152.40 m). After ten minutes: Make sure that the change of airspeed is not more than 20 kts.
Open the electrovalves and slowly balance the pressure in the standby static and pitot circuits.	The rate of descent must not be more than 6000 ft/min.

5. Close-up
Subtask 34-22-25-020-050-A ** ON A/C NOT FOR ALL

A. Removal of the Ground Pressure Generator
(1) Stop the ALT34100001 PITOT AND STATIC TEST SET.
(2) Disconnect the ALT34100001 PITOT AND STATIC TEST SET (1).
(3) Remove the adaptors from the standby static probe and the standby pitot probe.
(4) Remove the 98D10103500001 COVER-STATIC PROBE from the opposite standby static probe.
(5) Remove the piece of plastic and the color adhesive tape from the drain holes of the standby pitot probe.
(6) Remove the color adhesive tape from the vane of the AOA.

Subtask 34-22-25-875-051-A ** ON A/C NOT FOR ALL

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	ANTI ICE/PROBES/AOA/1	4DA1	D04
49VU	ANTI ICE/PROBES/PITOT/1	3DA1	D02
105VU	ELEC/CSM/G /EV AUTO/SPLY	7XE	C01
122VU	ANTI ICE/PROBES/2/TAT	1DA2	Y15
122VU	ANTI ICE/PROBES/2/PITOT	3DA2	Y14
122VU	ANTI ICE/PROBES/2/AOA	4DA2	Y13
122VU	ANTI ICE/PROBES/2/STATIC	5DA2	Y11
122VU	ANTI ICE/PROBES/3/PITOT	3DA3	Z16
122VU	ANTI ICE/PROBES/3/AOA	4DA3	Z15
122VU	ANTI ICE/PROBES/3/STATIC	5DA3	Z14
122VU	ANTI ICE/PROBES/1/STATIC	5DA1	Z13
122VU	ANTI ICE/PROBES/1/TAT	1DA1	Z12

Subtask 34-22-25-875-051-B ** ON A/C NOT FOR ALL

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	ANTI ICE/PROBES/AOA/1	4DA1	D04
49VU	ANTI ICE/PROBES/PITOT/1	3DA1	D02
105VU	ELEC/CSM/G /EV AUTO/SPLY	7XE	C01
121VU	COM NAV/RAD ALTM/2	1SA2	K12
121VU	COM NAV/RAD ALTM/1	1SA1	K11
122VU	ANTI ICE/PROBES/2/TAT	1DA2	Y15
122VU	ANTI ICE/PROBES/2/PITOT	3DA2	Y14
122VU	ANTI ICE/PROBES/2/AOA	4DA2	Y13
122VU	ANTI ICE/PROBES/2/STATIC	5DA2	Y11
122VU	ANTI ICE/PROBES/3/PITOT	3DA3	Z16
122VU	ANTI ICE/PROBES/3/AOA	4DA3	Z15
122VU	ANTI ICE/PROBES/3/STATIC	5DA3	Z14
122VU	ANTI ICE/PROBES/1/STATIC	5DA1	Z13
122VU	ANTI ICE/PROBES/1/TAT	1DA1	Z12

Subtask 34-22-25-860-054-A ** ON A/C NOT FOR ALL

C. Put the aircraft back to its initial configuration.
(1) On SWITCHING panel 8VU, set the AIR DATA selector switch to the NORMAL position.
(2) Do the EIS stop procedure (PFD only) (Ref. AMM TASK 31-60-00-860-002).
(3) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF.
(4) Do a reset of each Elevator Aileron Computer (ELAC):
(a) FOR [2CE1] (ELAC-1)
1 Open, then close circuit breakers 15CE1 and 16CE1.
(b) FOR [2CE2] (ELAC-2)
1 Open, then close circuit breakers 15CE2 and 16CE2.
(5) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
(6) Install the slip-on covers on the standby static probes and the standby pitot probe.
(7) Make sure that the work area is clean and clear of tools and other items.
(8) Make sure that there is no blockage of the drain holes on the pitot probes because of unwanted materials (Ref. AMM TASK 34-11-15-200-001)

Subtask 34-22-25-860-054-C ** ON A/C NOT FOR ALL

C. Put the aircraft back to its initial configuration.
(1) On SWITCHING panel 8VU, set the AIR DATA selector switch to the NORMAL position.
(2) Do the EIS stop procedure (PFD only) (Ref. AMM TASK 31-60-00-860-002).
(3) On ADIRS MSU panel 41VU, set the OFF/NAV/ATT selector switches to OFF.
(4) Do a reset of each Elevator Aileron Computer (ELAC):
(a) FOR [2CE1] (ELAC-1)
1 Open, then close circuit breakers 15CE1 and 16CE1.
(b) FOR [2CE2] (ELAC-2)
1 Open, then close circuit breakers 15CE2 and 16CE2.
(5) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
(6) Install the slip-on covers on the standby static probes and the standby pitot probe.
(7) Make sure that the work area is clean and clear of tools and other items.
(8) Make sure that there is no blockage of the drain holes on the pitot probes because of unwanted materials (Ref. AMM TASK 34-11-15-200-001).

[Rev.10 from 2021] 2026.04.01 04:47:41 UTC