Installation of the Angle of Attack (AOA) Sensor

TASK 34-11-19-400-001-A
Installation of the Angle of Attack (AOA) Sensor

WARNING: BEFORE YOU OPEN PHC CIRCUIT BREAKERS 2DA1(2,3), OPEN PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) AND 5DA1(2,3). IF YOU DO NOT OBEY THIS SEQUENCE: - THE PROBES WILL BECOME TOO HOT. - THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL.

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

CAUTION: DO NOT HOLD THE AOA SENSOR BY THE VANE WHEN YOU MOVE IT. IF YOU DO, YOU CAN CAUSE DAMAGE TO THE AOA SENSOR.

CAUTION: BE VERY CAREFUL WITH THE AOA SENSORS WHEN YOU REMOVE/INSTALL THEM:

DO NOT LET THEM FALL
DO NOT BEND THEM
DO NOT CAUSE THEM SCRATCHES.

AOA SENSORS CONTAIN SENSITIVE ELECTRONIC EQUIPMENT WHICH CAN EASILY BE DAMAGED.

CAUTION: DO NOT PAINT THE AOA BLANKING PLATE DIRECTLY ON AIRCRAFT WHEN IT IS INSTALLED ON THE AOA SENSOR. IF YOU PAINT IT DIRECTLY ON AIRCRAFT, CONTAMINATION TO THE AOA SENSOR CAN OCCUR.

CAUTION: DO NOT PAINT NEW AOA BLANKING PLATES P/N D3411013520200. THEY MUST STAY AS SUPPLIED. IF YOU PAINT THEM, CONTAMINATION TO THE AOA SENSOR CAN OCCUR.

ZONE: 127
ZONE: 128
ZONE: 231
ZONE: 232
FIN: 3FP1
FIN: 3FP2
FIN: 3FP3

1. Reason for the Job
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE
No specific	Torque wrench: range to between 0.48 and 0.37 m.daN (42.48 and 32.74 lbf.in )

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.06AAB1)	Polysulfide Sealant-General Purpose Fillet -
(Material No.06ABF1)	Polysulfide Sealant-Fuel Tank Quick Curing -
(Material No.08BAA9)	Non Aqueous Cleaner-General - -

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
127	REAR AVIONIC COMPARTMENT
128	REAR AVIONIC COMPARTMENT
231	FWD PASSENGER COMPARTMENT
232	FWD PASSENGER COMPARTMENT

D. Expendable Parts

FIG.ITEM	DESIGNATION	IPC-CSN
3	SEAL	AIPC 34-11-01-13-080
3	SEAL	AIPC 34-11-02-01-070
3	SEAL	AIPC 34-11-81-13-050
3	SEAL	AIPC 34-11-82-01-050

E. Referenced Information

REFERENCE	DESIGNATION
TASK 20-28-00-720-005-A	Check of the Electrical Bonding of the Different Components (but not the Fluid Systems and Components Installed on Composite materials)
TASK 20-28-00-912-802-A	Electrical Bonding - General Maintenance Procedure
TASK 20-28-00-912-803-A	Bonding Surface Preparation
TASK 30-31-00-710-001-A	Operational Test of the Probe Ice Protection
TASK 34-10-00-710-007-A	Test of the Angle of Attack (AOA) Warning
TASK 34-11-00-710-001-A	Test of the Monitoring of the ADR/AOA 26VAC Power Supply
Angle of Attack (AOA) Sensor
Angle of Attack (AOA) Sensor

3. Job Set-up
Subtask 34-11-19-860-051-A

A. Aircraft Maintenance Configuration
(1) Make sure that the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE is in position in zone 231 for 3FP1 (232 for 3FP2) (127 for 3FP3).
(2) Make sure that the protective covers of the sensors and probes (AOA, static Pitot and TAT) are removed.

Subtask 34-11-19-865-051-A

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
FOR FIN: 3FP1 (SENSORANGLE OF ATTACK, 1)
49VU	ANTI ICE/PROBES/AOA/1	4DA1	D04
49VU	ANTI ICE/PROBES/PITOT/1	3DA1	D02
49VU	NAV PROBES/ADIRU 1/AND AOA 1/26VAC	5FP1	F07
49VU	NAV PROBES/ADIRU1/115VAC	4FP1	F06
121VU	ADIRS/ADIRU/3PWR/SWTG	9FP	N09
122VU	ANTI ICE/PROBES/1/STATIC	5DA1	Z13
122VU	ANTI ICE/PROBES/1/TAT	1DA1	Z12
** ON A/C NOT FOR ALL
FOR FIN: 3FP2 (SENSORANGLE OF ATTACK, 2)
121VU	ADIRS/ADIRU/2PWR/SHED	10FP	N10
** ON A/C ALL
121VU	ADIRS/ADIRU/2/26VAC AND AOA	5FP2	N08
121VU	ADIRS/ADIRU/2/115VAC	4FP2	N06
** ON A/C NOT FOR ALL
121VU	ADIRS/2PWR/SHED &/AOA2 MON	10FP	N10
** ON A/C ALL
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
FOR FIN: 3FP3 (SENSORANGLE OF ATTACK, 3)
121VU	ADIRS/ADIRU/3PWR/SWTG	9FP	N09
121VU	ADIRS/ADIRU/3/26VAC AND AOA	5FP3	N07
121VU	ADIRS/ADIRU/3/115VAC	4FP3	N05
122VU	ANTI ICE/PROBES/3/PITOT	3DA3	Z16
122VU	ANTI ICE/PROBES/3/AOA	4DA3	Z15
122VU	ANTI ICE/PROBES/3/STATIC	5DA3	Z14
FOR FIN: 3FP1 (SENSORANGLE OF ATTACK, 1)
49VU	ANTI ICE/PROBES/PHC/1	2DA1	D03
FOR FIN: 3FP2 (SENSORANGLE OF ATTACK, 2)
122VU	ANTI ICE/PROBES/PHC/2	2DA2	Y12
FOR FIN: 3FP3 (SENSORANGLE OF ATTACK, 3)
122VU	ANTI ICE/PROBES/PHC/3	2DA3	Y16

4. Procedure
Subtask 34-11-19-420-050-A ** ON A/C NOT FOR ALL

A. Installation of the Angle of Attack (AOA) Sensor (3FP1, 3FP2, 3FP3)
(1) If the AOA sensor (6) is installed with a blanking plate that has no drain hole:

NOTE: The procedure is the same for AOA sensors 3FP1, 3FP2 and 3FP3.

(a) Clean the component interfaces and the adjacent area.
(b) Do an inspection of the component interfaces and the adjacent area.
(c) Remove the blanking caps from the connectors (1) and (4).
(d) Make sure that the connectors (1) and (4) are clean and in the correct condition.
(e) Install a new AIPC 34-11-02-01-070 SEAL (3) or the AIPC 34-11-01-13-080 SEAL (3) in its housing (2).

NOTE: If the seal (3) is in a good condition (no signs of cracks or missing parts), keep this seal for a maximum of eight flight cycles.

(f) Connect the electrical connector (1) to the AOA probe connector (4).
(g) Push the connector (1) into the fuselage.
(h) Put the AOA sensor (6) in position with the stud (5) and hold it.
(i) Tighten the screw (7).
(j) Do a check of the resistance of the bonding contact between one of the free countersinks of the AOA sensor (6) and the aircraft structure (2) (Ref. AMM TASK 20-28-00-720-005).

NOTE: You can use a bonding wire near the cabin door as a reference point for the aircraft structure.

(k) Install and hold the blanking plate (8).

NOTE: Carefully install the blanking plate (8) not to cause damage to the AOA sensor (6).

(l) Tighten the seven screws (9).
(m) TORQUE the screws (7) and (9) to between 0.48 and 0.37 m.daN (42.48 and 32.74 lbf.in )

.
(n) Before you apply the sealant, it is necessary to make sure that the surfaces are clean and in the correct condition (no moisture, dust, insects, sand, etc.).
1 If the surfaces are not clean, clean them with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(o) Apply Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) or Polysulfide Sealant-Fuel Tank Quick Curing - (Material No.06ABF1) (for a better curing time) on the head of the screw (7) and around the blanking plate (8).

NOTE: If it is possible that the curing time of the sealant will cause a flight delay, the aircraft can operate without the sealant for a maximum period of 48 hours after the installation of the AOA sensor (6).

WARNING: MAKE SURE THAT THE DRAIN HOLE IS CLEAR AFTER YOU INSTALL AND SEAL THE AOA BLANKING PLATE.

(2) If the AOA sensor (6) is installed with a blanking plate that has a drain hole:

NOTE: The procedure is the same for AOA sensors 3FP1, 3FP2 and 3FP3.

NOTE: If the seal (3) is in a good condition (no signs of cracks or missing parts), keep this seal for a maximum of eight flight cycles.

(f) Connect the electrical connector (1) to the probe connector (4).
(g) Push the connector (1) into the fuselage.
(h) Put the AOA sensor (6) in position with the stud (5) and hold it.
(i) Tighten the screw (7).
(j) Do a check of the resistance of the bonding contact between one of the free countersinks of the AOA sensor (6) and the aircraft structure (2) (Ref. AMM TASK 20-28-00-720-005).

NOTE: You can use a bonding wire near the cabin door as a reference point for the aircraft structure.

(k) Install and hold the blanking plate (8).

NOTE: The blanking plate is made with a radius that is related to the fuselage curve. The rotation of the blanking plate around the AOA sensor (6) can also cause non-flush surface.

NOTE: Carefully install the blanking plate (8) not to cause damage to the AOA sensor (6).

(l) Tighten the seven screws (9).
(m) TORQUE the screws (7) and (9) to between 0.48 and 0.37 m.daN (42.48 and 32.74 lbf.in )

(p) Do a check of the drain hole (10).

Subtask 34-11-19-420-050-C ** ON A/C NOT FOR ALL

A. Installation of the Angle of Attack (AOA) Sensor (3FP1, 3FP2, 3FP3)

NOTE: The procedure is the same for AOA sensors 3FP1, 3FP2 and 3FP3.

(1) If the AOA sensor (6) is installed with a blanking plate that has no drain hole, do the steps that follow:
(a) Clean the component interfaces and the adjacent area.
(b) Do an inspection of the component interfaces and the adjacent area.
(c) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(d) Remove the blanking caps from the connectors (1) and (4).
(e) Make sure that the connectors (1) and (4) are clean and in the correct condition.
(f) Install the new AIPC 34-11-82-01-050 SEAL (3) or the new AIPC 34-11-81-13-050 SEAL (3) in its housing (2).

NOTE: If the new seal (3) is not available, you can install the seal (3) which was removed (if there are no signs of cracks or missing parts). The aircraft can operate with this old seal (3) for a maximum of eight flight cycles.

(g) Connect the electrical connector (1) to the AOA probe connector (4).
(h) Push the electrical connector (1) into the fuselage.
(i) Put the AOA sensor (6) in position with the stud (5) and hold it.
(j) Tighten the screw (7).
(k) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802):
1 Make sure that the bonding contact resistance (between one of the free countersinks of the AOA sensor (6) and the aircraft structure (2)) is not more than 5 milliohms.

NOTE: You can use a bonding wire near the cabin door as a reference point for the aircraft structure.

(l) Carefully install the blanking plate (8) and hold it. Make sure to not cause damage to the AOA sensor (6) when you install the blanking plate (8).
(m) Tighten the seven screws (9).
(n) Before you apply the sealant, make sure that the surfaces are clean and in the correct condition (there must be no moisture, dust, insects, sand, etc.).
1 If the surfaces are not clean, clean them with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(o) Apply Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) or Polysulfide Sealant-Fuel Tank Quick Curing - (Material No.06ABF1) (for a better curing time) on the head of the screw (7) and around the blanking plate (8).

NOTE: It is possible that the curing time of the sealant will cause a flight delay. The aircraft can operate without the sealant for a maximum period of 48 hours after the installation of the AOA sensor (6).

WARNING: MAKE SURE THAT THE DRAIN HOLE IS CLEAR AFTER YOU INSTALL AND SEAL THE AOA BLANKING PLATE.

(2) If the AOA sensor (6) is installed with a blanking plate that has a drain hole, do the steps that follow:
(a) Clean the component interfaces and the adjacent area.
(b) Do an inspection of the component interfaces and the adjacent area.
(c) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(d) Remove the blanking caps from the connectors (1) and (4).
(e) Make sure that the connectors (1) and (4) are clean and in the correct condition.
(f) Install the new AIPC 34-11-82-01-050 SEAL (3) or the new AIPC 34-11-81-13-050 SEAL (3) in its housing (2).

(g) Connect the electrical connector (1) to the probe connector (4).
(h) Push the electrical connector (1) into the fuselage.
(i) Put the AOA sensor (6) in position with the stud (5) and hold it.
(j) Tighten the screw (7).
(k) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802):
1 Make sure that the bonding contact resistance (between one of the free countersinks of the AOA sensor (6) and the aircraft structure (2)) is not more than 5 milliohms.

NOTE: You can use a bonding wire near the cabin door as a reference point for the aircraft structure.

(l) Carefully install the blanking plate (8) and hold it. Make sure to not cause damage to the AOA sensor (6) when you install the blanking plate (8).

NOTE: The blanking plate is made with a radius that is related to the fuselage curve. The rotation of the blanking plate around the AOA sensor (6) can also cause a surface which is not flush.

(m) Tighten the seven screws (9).
(n) Before you apply the sealant, make sure that the surfaces are clean and in the correct condition (there must be no moisture, dust, insects, sand, etc.).
1 If the surfaces are not clean, clean them with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(o) Apply Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) or Polysulfide Sealant-Fuel Tank Quick Curing - (Material No.06ABF1) (for a better curing time) on the head of the screw (7) and around the blanking plate (8).

(p) Do a check of the drain hole (10) and make sure that it is clear.

Subtask 34-11-19-420-050-E ** ON A/C NOT FOR ALL

A. Installation of the Angle of Attack (AOA) Sensor (3FP1, 3FP2, 3FP3)

NOTE: The procedure is the same for AOA sensors 3FP1, 3FP2 and 3FP3.

(g) Connect the electrical connector (1) to the AOA probe connector (4).
(h) Push the electrical connector (1) into the fuselage.
(i) Put the AOA sensor (6) in position with the stud (5) and hold it.
(j) Tighten the screw (7).
(k) Carefully install the blanking plate (8) and hold it. Make sure to not cause damage to the AOA sensor (6) when you install the blanking plate (8).
(l) Tighten the screws (9).
(m) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802):
1 Make sure that the bonding contact resistance (between one of the free countersinks of the AOA sensor (6) and the aircraft structure (2)) is not more than 5 milliohms.
(n) Before you apply the sealant, make sure that the head of the screw (7) is clean and in the correct condition (there must be no moisture, dust, insects, sand, etc.).
1 If the head of the screw (7) is not clean, clean it with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(o) Apply Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) or Polysulfide Sealant-Fuel Tank Quick Curing - (Material No.06ABF1) (for a better curing time) on the head of the screw (7).

WARNING: MAKE SURE THAT THE DRAIN HOLE IS CLEAR AFTER YOU INSTALL AND SEAL THE AOA BLANKING PLATE.

(g) Connect the electrical connector (1) to the probe connector (4).
(h) Push the electrical connector (1) into the fuselage.
(i) Put the AOA sensor (6) in position with the stud (5) and hold it.
(j) Tighten the screw (7).
(k) Carefully install the blanking plate (8) and hold it. Make sure to not cause damage to the AOA sensor (6) when you install the blanking plate (8).

NOTE: The blanking plate is made with a radius that is related to the fuselage curve. The rotation of the blanking plate around the AOA sensor (6) can also cause a surface which is not flush.

(l) Tighten the screws (9).
(m) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802):
1 Make sure that the bonding contact resistance (between one of the free countersinks of the AOA sensor (6) and the aircraft structure (2)) is not higher than 5 milliohms.
(n) Before you apply the sealant, make sure that the head of the screw (7) is clean and in the correct condition (there must be no moisture, dust, insects, sand, etc.).
1 If the head of the screw (7) is not clean, clean it with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(o) Apply Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) or Polysulfide Sealant-Fuel Tank Quick Curing - (Material No.06ABF1) (for a better curing time) on the head of the screw (7).

(p) Do a check of the drain hole (10) and make sure that it is clear.

Subtask 34-11-19-865-055-A

B. Table of the circuit breakers used in this procedure:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
49VU	ENGINE/2/FADEC A/AND EIU 2	2KS2	A05
49VU	ENGINE/1/FADEC A/AND EIU 1	2KS1	A04

Subtask 34-11-19-942-050-A

C. Safety Precautions
(1) In the cockpit, on overhead control and indicating panel 25VU:
(a) Make sure that the PROBE/WINDOW HEAT pushbutton switch is released (the ON legend is off).
(b) Make sure that this(these) circuit breaker(s) is(are) closed:

2KS1
2KS2.

Subtask 34-11-19-865-052-A

D. Remove the safety clips and tags and close these circuit breakers in this sequence:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
FOR FIN: 3FP1 (SENSORANGLE OF ATTACK, 1)
49VU	ANTI ICE/PROBES/PHC/1	2DA1	D03
FOR FIN: 3FP2 (SENSORANGLE OF ATTACK, 2)
122VU	ANTI ICE/PROBES/PHC/2	2DA2	Y12
FOR FIN: 3FP3 (SENSORANGLE OF ATTACK, 3)
122VU	ANTI ICE/PROBES/PHC/3	2DA3	Y16
FOR FIN: 3FP1 (SENSORANGLE OF ATTACK, 1)
49VU	NAV PROBES/ADIRU1/115VAC	4FP1	F06
49VU	NAV PROBES/ADIRU 1/AND AOA 1/26VAC	5FP1	F07
121VU	ADIRS/ADIRU/3PWR/SWTG	9FP	N09
122VU	ANTI ICE/PROBES/1/TAT	1DA1	Z12
49VU	ANTI ICE/PROBES/PITOT/1	3DA1	D02
49VU	ANTI ICE/PROBES/AOA/1	4DA1	D04
122VU	ANTI ICE/PROBES/1/STATIC	5DA1	Z13
FOR FIN: 3FP2 (SENSORANGLE OF ATTACK, 2)
121VU	ADIRS/ADIRU/2/115VAC	4FP2	N06
121VU	ADIRS/ADIRU/2/26VAC AND AOA	5FP2	N08
** ON A/C NOT FOR ALL
121VU	ADIRS/ADIRU/2PWR/SHED	10FP	N10
** ON A/C NOT FOR ALL
121VU	ADIRS/2PWR/SHED &/AOA2 MON	10FP	N10
** ON A/C ALL
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
FOR FIN: 3FP3 (SENSORANGLE OF ATTACK, 3)
121VU	ADIRS/ADIRU/3/115VAC	4FP3	N05
121VU	ADIRS/ADIRU/3/26VAC AND AOA	5FP3	N07
121VU	ADIRS/ADIRU/3PWR/SWTG	9FP	N09
122VU	ANTI ICE/PROBES/3/PITOT	3DA3	Z16
122VU	ANTI ICE/PROBES/3/AOA	4DA3	Z15
122VU	ANTI ICE/PROBES/3/STATIC	5DA3	Z14

Subtask 34-11-19-710-050-A

E. Test
(1) Do the operational test of the Probe Ice Protection
(Ref. AMM TASK 30-31-00-710-001).
(2) Do the test of the angle of attack warning.
(Ref. AMM TASK 34-10-00-710-007).

NOTE: As an alternative procedure, you can do an operational test without the CFDS.
(Ref. AMM TASK 34-11-00-710-001).

5. Close-up
Subtask 34-11-19-860-052-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) Install the protective covers on the sensors and probes (AOA, static, Pitot and TAT).
(3) Remove the access platform(s).

[Rev.10 from 2021] 2026.04.02 06:42:04 UTC