DOC AIRBUS | AMM A320FAdjustment of the N/WS Zero Position for A/C with N/WS Feedback Sensor-Box P/N E21336000, Rudder Trim Angle as Reference
TASK 32-51-00-820-001-A-02
Adjustment of the N/WS Zero Position for A/C with N/WS Feedback Sensor-Box P/N E21336000, Rudder Trim Angle as Reference
Do this procedure when you have a sensor box P/N E21336000 installed on the NLG and when you use the rudder trim angle as reference for the adjustment.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Referenced Information
3. Job Set-up
Subtask 32-51-00-941-051-A
Subtask 32-51-00-220-051-A
Subtask 32-51-00-860-064-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 00:51:02 UTC
Adjustment of the N/WS Zero Position for A/C with N/WS Feedback Sensor-Box P/N E21336000, Rudder Trim Angle as Reference
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.
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:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
CAUTION:
IF THE SENSOR BOX HAS P/N E21336000, NEVER REMOVE THE SENSOR FROM THE GEARBOX. THE SENSOR AND THE GEARBOX ARE AN ASSEMBLY THAT YOU MUST NOT DISASSEMBLE ON THE AIRCRAFT.
IF YOU REMOVE THE SENSOR FROM THE GEARBOX:
1. Reason for the Job- YOU WILL CAUSE DAMAGE TO THE SENSOR BOX
- THE ADJUSTMENT OF THE SENSOR BOX WILL NO LONGER BE CORRECT.
Do this procedure when you have a sensor box P/N E21336000 installed on the NLG and when you use the rudder trim angle as reference for the adjustment.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | JACK - WHEEL CHANGE, MAIN/NOSE LANDING GEAR |
| No specific | AR | PLATE 1.2 M (4 FT) - STEEL, SQUARED |
| No specific | AR | SAFETY CLIP - CIRCUIT BREAKER |
| No specific | AR | SPATULA - NON METALLIC |
| No specific | AR | VOLTMETER - AC, 0-20 V MIN, 0,001 V, 50 TO 2000 HTZ |
| No specific | AR | WARNING NOTICE(S) |
| No specific | Torque wrench: range to between 0.25 and 0.21 m.daN (22.12 and 18.58 lbf.in )  | |
| F26792000 | 1 | SENSOR-VOLTAGE TEST |
| F26792000-1 | 1 | SENSOR-VOLTAGE TEST |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.03HBD9) | Synthetic Ester base Grease-General Purpose Low Temp - |
| (Material No.06ABF1) | Polysulfide Sealant-Fuel Tank Quick Curing - |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 07-11-00-581-003-A | Lifting of the Aircraft at the Forward Jacking Point, MLG Wheels on the Ground |
| TASK 07-11-00-586-001-A | Lowering of the Aircraft at Forward Jacking Point, MLG Wheels on the Ground |
| TASK 07-12-00-582-001-A | Jacking of the Nose Landing Gear |
| TASK 09-10-00-584-002-A | Towing by the Nose Landing Gear from the Front with a Towbar |
| 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 29-10-00-863-001-A | Pressurize the Green Hydraulic System with a Hydraulic Ground Power-Cart |
| TASK 29-10-00-863-002-A | Pressurize the Yellow Hydraulic System with a Hydraulic Ground Power-Cart |
| TASK 29-10-00-864-001-A | Depressurize the Green Hydraulic System |
| TASK 29-10-00-864-002-A | Depressurize the Yellow Hydraulic System |
| TASK 29-23-00-863-001-A | Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump |
| TASK 29-23-00-864-001-A | Depressurize the Green and Yellow Hydraulic Systems after Operation of the PTU |
| TASK 29-24-00-863-001-A | Pressurize the Yellow Hydraulic System with the Electric Pump |
| TASK 32-46-00-740-001-A | BITE Test of the BSCU |
| TSM 32-51-00-810-823 | Steering Deviation During Taxi |
NLG Shock Absorber - ClearanceSubtask 32-51-00-941-051-A
A. General
(1) Put a WARNING NOTICE(S) in the cockpit to tell persons not to operate the landing gear or the N/WS.
(2) On the panel 400VU, make sure that the L/G normal control lever is in the DOWN position.
(3) On the nose gear leg, on the nose wheel steering deactivation electrical box, make sure that the towing lever is in the normal position (engaged position).
(4) Make sure that the N/WS handwheels and the rudder pedals are in the neutral position.
Subtask 32-51-00-860-063-A ** ON A/C NOT FOR ALL (1) Put a WARNING NOTICE(S) in the cockpit to tell persons not to operate the landing gear or the N/WS.
(2) On the panel 400VU, make sure that the L/G normal control lever is in the DOWN position.
(3) On the nose gear leg, on the nose wheel steering deactivation electrical box, make sure that the towing lever is in the normal position (engaged position).
(4) Make sure that the N/WS handwheels and the rudder pedals are in the neutral position.
B. Aircraft Maintenance Configuration
(1) Lift the aircraft and compress the NLG shock absorber
(a) Lift the front of the aircraft until the nosewheels are clear of the ground (Ref. AMM TASK 07-11-00-581-003).
(b) Compress the NLG shock absorber with a JACK - WHEEL CHANGE, MAIN/NOSE LANDING GEAR until the dimension H is less than 350 mm (14.0 in.) (Ref. AMM TASK 07-12-00-582-001).
(c) Make sure that there is a sufficient clearance between the jack and the nosewheels for the nosewheel steering to operate.
(d) Make sure that you cannot see more than 350 mm (14.0 in.) of the NLG shock absorber dimension H.
(Ref. AMM TASK 24-41-00-861-002).
(3) Pressurize the Green hydraulic system
(Ref. AMM TASK 29-10-00-863-001) or (Ref. AMM TASK 29-23-00-863-001).
Subtask 32-51-00-860-063-B ** ON A/C NOT FOR ALL (1) Lift the aircraft and compress the NLG shock absorber
(a) Lift the front of the aircraft until the nosewheels are clear of the ground (Ref. AMM TASK 07-11-00-581-003).
(b) Compress the NLG shock absorber with a JACK - WHEEL CHANGE, MAIN/NOSE LANDING GEAR until the dimension H is less than 350 mm (14.0 in.) (Ref. AMM TASK 07-12-00-582-001).
(c) Make sure that there is a sufficient clearance between the jack and the nosewheels for the nosewheel steering to operate.
(d) Make sure that you cannot see more than 350 mm (14.0 in.) of the NLG shock absorber dimension H.
NOTE: As an alternative solution, if only jack is not available you can use need two PLATE 1.2 M (4 FT) - STEEL, SQUARED, for this do as follows:
(2) Energize the aircraft electrical circuits- Position a steel plate in front of the nosewheels.
- Apply a thick layer of Synthetic Ester base Grease-General Purpose Low Temp - (Material No.03HBD9) to the upper surface of the steel plate.
- Put the other steel plate on the top of the greased steel plate.
- Move the aircraft and position the nosewheels on the greased steel plates (Ref. AMM TASK 09-10-00-584-002).
(Ref. AMM TASK 24-41-00-861-002).
(3) Pressurize the Green hydraulic system
(Ref. AMM TASK 29-10-00-863-001) or (Ref. AMM TASK 29-23-00-863-001).
B. Aircraft Maintenance Configuration
(1) Lift the aircraft and compress the NLG shock absorber
(a) Lift the front of the aircraft until the nosewheels are clear of the ground (Ref. AMM TASK 07-11-00-581-003).
(b) Compress the NLG shock absorber with a JACK - WHEEL CHANGE, MAIN/NOSE LANDING GEAR until the dimension H is less than 350 mm (14.0 in.) (Ref. AMM TASK 07-12-00-582-001).
(c) Make sure that there is a sufficient clearance between the jack and the nosewheels for the nosewheel steering to operate.
(d) Make sure that you cannot see more than 350 mm (14.0 in.) of the NLG shock absorber dimension H.
(Ref. AMM TASK 24-41-00-861-002).
(3) Pressurize the Yellow hydraulic system
(Ref. AMM TASK 29-10-00-863-002) or (Ref. AMM TASK 29-24-00-863-001).
Subtask 32-51-00-865-071-A (1) Lift the aircraft and compress the NLG shock absorber
(a) Lift the front of the aircraft until the nosewheels are clear of the ground (Ref. AMM TASK 07-11-00-581-003).
(b) Compress the NLG shock absorber with a JACK - WHEEL CHANGE, MAIN/NOSE LANDING GEAR until the dimension H is less than 350 mm (14.0 in.) (Ref. AMM TASK 07-12-00-582-001).
(c) Make sure that there is a sufficient clearance between the jack and the nosewheels for the nosewheel steering to operate.
(d) Make sure that you cannot see more than 350 mm (14.0 in.) of the NLG shock absorber dimension H.
NOTE: As an alternative solution, if only jack is not available you can use need two PLATE 1.2 M (4 FT) - STEEL, SQUARED, for this do as follows:
(2) Energize the aircraft electrical circuits- Position a steel plate in front of the nosewheels.
- Apply a thick layer of Synthetic Ester base Grease-General Purpose Low Temp - (Material No.03HBD9) to the upper surface of the steel plate.
- Put the other steel plate on the top of the greased steel plate.
- Move the aircraft and position the nosewheels on the greased steel plates (Ref. AMM TASK 09-10-00-584-002).
(Ref. AMM TASK 24-41-00-861-002).
(3) Pressurize the Yellow hydraulic system
(Ref. AMM TASK 29-10-00-863-002) or (Ref. AMM TASK 29-24-00-863-001).
C. Table of the circuit breakers used in this procedure:
Subtask 32-51-00-865-073-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 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 |
D. Open, safety and tag this(these) circuit breaker(s):
Subtask 32-51-00-860-094-A ** ON A/C NOT FOR ALL | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 121VU | ENGINE/ENG2/OIL/PRESS | 2EN2 | N42 |
| 121VU | ENGINE/ENG1/OIL/PRESS | 2EN1 | N40 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | OIL/PRESS/ENG2 | 10KC2 | N42 |
| 121VU | OIL/PRESS/ENG1 | 10KC1 | N40 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | ENGINE/ENG2/OIL/PRESS/AND REV SNSR/CHAN A | 2EN2 | N42 |
| 121VU | ENGINE/ENG1/OIL/PRESS/AND REV SNSR/CHAN A | 2EN1 | N40 |
E. Safety Precautions
(1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) in position to tell persons that both thrust reverser control levers are not operational.
(2) Put a WARNING NOTICE(S) in position in the cockpit to tell persons that circuit breakers 2EN1 and 2EN2 are open.
Subtask 32-51-00-860-094-B ** ON A/C NOT FOR ALL (1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) in position to tell persons that both thrust reverser control levers are not operational.
(2) Put a WARNING NOTICE(S) in position in the cockpit to tell persons that circuit breakers 2EN1 and 2EN2 are open.
NOTE: The open status of circuit breakers 2EN1 and 2EN2 makes the engine thrust reversers unserviceable.
E. Safety Precautions
(1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) in position to tell persons that both thrust reverser control levers are not operational.
(2) Put a WARNING NOTICE(S) in position in the cockpit to tell persons that circuit breakers 10KC1 and 10KC2 are open.
4. Procedure(1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) in position to tell persons that both thrust reverser control levers are not operational.
(2) Put a WARNING NOTICE(S) in position in the cockpit to tell persons that circuit breakers 10KC1 and 10KC2 are open.
NOTE: The open status of circuit breakers 10KC1 and 10KC2 makes the engine thrust reversers unserviceable.
Subtask 32-51-00-220-051-A
A. Check and record the secondary voltage at the sensor 3GC
(2) Disconnect the connector (4) from the RVDT 3GC (1).
(3) Connect the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) between the connector (4) and the RVDT 3GC (1).
(4) Connect an VOLTMETER - AC, 0-20 V MIN, 0,001 V, 50 TO 2000 HTZ to the SECONDARY VOLTAGE connections on the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3).
(5) Open the CBs of the BSCU SYS2 (3GG and 4GG).
(6) Make sure that the CBs of the BSCU SYS1 (1GG and 2GG) are closed.
(7) On panel 402VU, put the A/SKID & N/W STRG switch in ON position.
(8) With the captains handwheel, move the steering 75 degrees to the left then 75 degrees to the right then to the zero position.
(9) Stage 1:
(a) Make sure that the nose wheel steering handwheels and the rudder pedals are in neutral position. Do not operate them.
(b) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U1.
(c) Record the voltage (U1)(in AC voltage).
(d) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U2.
(e) Record the voltage (U2)(in AC voltage).
(f) Calculate the algebraic value x:
(10) Get the rudder trim calculated value X obtained during Trouble Shooting procedure TSM 32-51-00-810-823. On the panel 110VU, set the rudder trim switch to the same value.
(11) Stage 2:
(a) Make sure that the nose wheel steering handwheels and the rudder pedals are in neutral position. Do not operate them.
(b) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U1.
(c) Record the voltage (U1)(in AC voltage).
(d) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U2.
(e) Record the voltage (U2)(in AC voltage).
(f) Calculate the algebraic value y:
(12) Stage 3:
(a) Calculate the algebraic value A:
(14) On panel 402VU, put the A/SKID & N/W STRG switch in OFF position.
(15) Remove the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) from the sensor 3GC.
Subtask 32-51-00-864-056-A ** ON A/C NOT FOR ALL NOTE: The voltages U1 and U2 are in volts (3V approximately).
(1) On panel 402VU, put the A/SKID & N/W STRG switch in OFF position. (2) Disconnect the connector (4) from the RVDT 3GC (1).
(3) Connect the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) between the connector (4) and the RVDT 3GC (1).
(4) Connect an VOLTMETER - AC, 0-20 V MIN, 0,001 V, 50 TO 2000 HTZ to the SECONDARY VOLTAGE connections on the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3).
(5) Open the CBs of the BSCU SYS2 (3GG and 4GG).
(6) Make sure that the CBs of the BSCU SYS1 (1GG and 2GG) are closed.
(7) On panel 402VU, put the A/SKID & N/W STRG switch in ON position.
(8) With the captains handwheel, move the steering 75 degrees to the left then 75 degrees to the right then to the zero position.
(9) Stage 1:
(a) Make sure that the nose wheel steering handwheels and the rudder pedals are in neutral position. Do not operate them.
(b) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U1.
(c) Record the voltage (U1)(in AC voltage).
(d) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U2.
(e) Record the voltage (U2)(in AC voltage).
(f) Calculate the algebraic value x:
| ----------------------- |
| ! x = (U1 - U2) ! |
| ----------------------- |
(10) Get the rudder trim calculated value X obtained during Trouble Shooting procedure TSM 32-51-00-810-823. On the panel 110VU, set the rudder trim switch to the same value.
(11) Stage 2:
(a) Make sure that the nose wheel steering handwheels and the rudder pedals are in neutral position. Do not operate them.
(b) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U1.
(c) Record the voltage (U1)(in AC voltage).
(d) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U2.
(e) Record the voltage (U2)(in AC voltage).
(f) Calculate the algebraic value y:
| ----------------------- |
| ! y = (U1 - U2) ! |
| ----------------------- |
(12) Stage 3:
(a) Calculate the algebraic value A:
| ----------------------- |
| ! A = (y - x) ! |
| ----------------------- |
NOTE: This voltage value correspond to the trim angle X
(13) On the panel 110VU, set the rudder trim at 0. (14) On panel 402VU, put the A/SKID & N/W STRG switch in OFF position.
(15) Remove the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) from the sensor 3GC.
B. Depressurize the Green hydraulic system (Ref. AMM TASK 29-10-00-864-001) or (Ref. AMM TASK 29-23-00-864-001).
Subtask 32-51-00-864-056-B ** ON A/C NOT FOR ALL Subtask 32-51-00-220-068-A C. Check and record the secondary voltage at the sensor 4GC
(2) Disconnect the connector (4) from the RVDT 4GC (1).
(3) Connect the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) between the connector (4) and the RVDT 4GC (1).
(4) Connect an VOLTMETER - AC, 0-20 V MIN, 0,001 V, 50 TO 2000 HTZ to the SECONDARY VOLTAGE connections on the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3).
(5) Make sure that the CBs of the BSCU SYS2 (3GG and 4GG) are open.
(6) On panel 402VU, put the A/SKID & N/W STRG switch in ON position.
(7) Stage 4:
(a) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U1.
(b) Record the voltage (U1)(in AC voltage).
(c) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U2.
(d) Record the voltage (U2)(in AC voltage).
(e) Calculate the algebraic value U:
(8) On panel 402VU, put the A/SKID & N/W STRG switch in OFF position.
(9) Remove the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) from the sensor 4GC.
Subtask 32-51-00-820-053-A NOTE: You must do a check of the sensor 4GC voltage to keep a reference position of the nose wheel if a problem occurs during the adjustment of the gearbox.
(1) On panel 402VU, make sure that the A/SKID & N/W STRG switch in OFF position. (2) Disconnect the connector (4) from the RVDT 4GC (1).
(3) Connect the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) between the connector (4) and the RVDT 4GC (1).
(4) Connect an VOLTMETER - AC, 0-20 V MIN, 0,001 V, 50 TO 2000 HTZ to the SECONDARY VOLTAGE connections on the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3).
(5) Make sure that the CBs of the BSCU SYS2 (3GG and 4GG) are open.
(6) On panel 402VU, put the A/SKID & N/W STRG switch in ON position.
(7) Stage 4:
(a) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U1.
(b) Record the voltage (U1)(in AC voltage).
(c) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U2.
(d) Record the voltage (U2)(in AC voltage).
(e) Calculate the algebraic value U:
| ----------------------- |
| ! U = (U1 - U2) ! |
| ----------------------- |
(8) On panel 402VU, put the A/SKID & N/W STRG switch in OFF position.
(9) Remove the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) from the sensor 4GC.
D. Set the NWS Zero Position for the sensor 3GC
(1) On panel 402VU, make sure that the A/SKID & N/W STRG switch in OFF position.
(2) Disconnect the connector (4) from the RVDT 3GC (1).
(3) Connect the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) between the connector (4) and the RVDT 3GC (1).
(4) Connect an VOLTMETER - AC, 0-20 V MIN, 0,001 V, 50 TO 2000 HTZ to the SECONDARY VOLTAGE connections on the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3).
(5) Make sure that the CBs of the BSCU SYS2 (3GG and 4GG) are open.
(6) On panel 402VU, put the A/SKID & N/W STRG switch in ON position.
(7) Stage 5:
(a) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U1.
(b) Record the voltage (U1)(in AC voltage).
(c) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U2.
(d) Record the voltage (U2)(in AC voltage).
(e) Calculate the algebraic value B:
(8) Stage 6:
(a) Calculate the algebraic value C:
(9) Stage 7:
(a) Use a SPATULA - NON METALLIC to remove the sealant:
(c) On the sensor box, turn the worm screw (5) to get the algebraic difference between U1 and U2 secondary voltage: C
(10) TORQUE the screws (2) to between 0.25 and 0.21 m.daN (22.12 and 18.58 lbf.in ).
(11) Stage 8:
(a) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U1.
(b) Record the voltage (U1)(in AC voltage).
(c) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U2.
(d) Record the voltage (U2)(in AC voltage).
(e) Check that the algebraic value D:
(f) If the value D is not in the limits, do the procedure from stage 7 again.
(12) If the value is correct, on panel 402VU, put the A/SKID & N/W STRG switch in OFF position.
(13) Remove the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3).
(14) Connect the electrical connector (4) to the RVDT 3GC (1).
(15) Fill the housing of the worm screw (5) with Polysulfide Sealant-Fuel Tank Quick Curing - (Material No.06ABF1) .
(16) Apply a layer of Polysulfide Sealant-Fuel Tank Quick Curing - (Material No.06ABF1) at the areas identified S.
Subtask 32-51-00-820-054-A (1) On panel 402VU, make sure that the A/SKID & N/W STRG switch in OFF position.
(2) Disconnect the connector (4) from the RVDT 3GC (1).
(3) Connect the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) between the connector (4) and the RVDT 3GC (1).
(4) Connect an VOLTMETER - AC, 0-20 V MIN, 0,001 V, 50 TO 2000 HTZ to the SECONDARY VOLTAGE connections on the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3).
(5) Make sure that the CBs of the BSCU SYS2 (3GG and 4GG) are open.
(6) On panel 402VU, put the A/SKID & N/W STRG switch in ON position.
(7) Stage 5:
(a) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U1.
(b) Record the voltage (U1)(in AC voltage).
(c) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U2.
(d) Record the voltage (U2)(in AC voltage).
(e) Calculate the algebraic value B:
| ----------------------- |
| ! B = (U1 - U2) ! |
| ----------------------- |
(8) Stage 6:
(a) Calculate the algebraic value C:
| ----------------------- |
| ! C = B - A ! |
| ----------------------- |
(9) Stage 7:
(a) Use a SPATULA - NON METALLIC to remove the sealant:
- from the areas identified S
- from the housing of the worm screw (5)
NOTE: Do not cause damage to the surface protections on these parts.
(b) On the sensor box, loosen the screws (2) to release the sensor (1). (c) On the sensor box, turn the worm screw (5) to get the algebraic difference between U1 and U2 secondary voltage: C
| ----------------------- |
| ! (U1 - U2) = C ! |
| ----------------------- |
NOTE: When you turn the worm screw (5), the sensor moves and changes the secondary voltages U1 and U2.
When you turn the worm screw (5):
- in one direction, U1 increases and U2 decreases,
- in the other direction, U2 increases and U1 decreases.
(d) Record the voltages U1 and U2 (in AC voltage). When you turn the worm screw (5):
- in one direction, U1 increases and U2 decreases,
- in the other direction, U2 increases and U1 decreases.
(10) TORQUE the screws (2) to between 0.25 and 0.21 m.daN (22.12 and 18.58 lbf.in )
. (11) Stage 8:
(a) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U1.
(b) Record the voltage (U1)(in AC voltage).
(c) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U2.
(d) Record the voltage (U2)(in AC voltage).
(e) Check that the algebraic value D:
| ------------------------------------- |
| ! (U1 - U2) = D = C +/- 20mV ! |
| ------------------------------------- |
(f) If the value D is not in the limits, do the procedure from stage 7 again.
(12) If the value is correct, on panel 402VU, put the A/SKID & N/W STRG switch in OFF position.
(13) Remove the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3).
(14) Connect the electrical connector (4) to the RVDT 3GC (1).
(15) Fill the housing of the worm screw (5) with Polysulfide Sealant-Fuel Tank Quick Curing - (Material No.06ABF1) .
(16) Apply a layer of Polysulfide Sealant-Fuel Tank Quick Curing - (Material No.06ABF1) at the areas identified S.
E. Set the NWS Zero Position for the sensor 4GC
(2) Connect the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) between the connector (4) and the RVDT 4GC (1).
(3) Connect an VOLTMETER - AC, 0-20 V MIN, 0,001 V, 50 TO 2000 HTZ to the SECONDARY VOLTAGE connections on the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3).
(4) On panel 402VU, put the A/SKID & N/W STRG switch in ON position.
(5) Stage 9:
(a) Use a SPATULA - NON METALLIC to remove the sealant:
(c) On the sensor box, turn the worm screw (5) to get the algebraic difference between U1 and U2 secondary voltage: C
(6) TORQUE the screws (2) to between 0.25 and 0.21 m.daN (22.12 and 18.58 lbf.in ).
(7) Stage 10:
(a) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (18) set the selector switch to U1.
(b) Record the voltage (U1)(in AC voltage).
(c) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U2.
(d) Record the voltage (U2)(in AC voltage).
(e) Check that the algebraic value E:
(f) If the value E is not in the limits, do the procedure from stage (9) again.
(8) If the value is correct, on panel 402VU, put the A/SKID & N/W STRG switch in OFF position.
(9) Remove the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3).
(10) Connect the electrical connector (4) to the RVDT 4GC (1).
(11) Fill the housing of the worm screw (5) with Polysulfide Sealant-Fuel Tank Quick Curing - (Material No.06ABF1) .
(12) Apply a layer of Polysulfide Sealant-Fuel Tank Quick Curing - (Material No.06ABF1) at the areas identified S.
Subtask 32-51-00-865-074-A NOTE: It is necessary to adjust the gear box/sensor 4GC at the same value as the gear box/sensor 3GC to prevent:
- differences between the command and monitoring acquisition thresholds,
- unwanted fault messages.
(1) On panel 402VU, make sure that the A/SKID & N/W STRG switch in OFF position. - differences between the command and monitoring acquisition thresholds,
- unwanted fault messages.
(2) Connect the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) between the connector (4) and the RVDT 4GC (1).
(3) Connect an VOLTMETER - AC, 0-20 V MIN, 0,001 V, 50 TO 2000 HTZ to the SECONDARY VOLTAGE connections on the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3).
(4) On panel 402VU, put the A/SKID & N/W STRG switch in ON position.
(5) Stage 9:
(a) Use a SPATULA - NON METALLIC to remove the sealant:
- from the areas identified S
- from the housing of the worm screw (5)
NOTE: Do not cause damage to the surface protections on these parts.
(b) On the sensor box, loosen the screws (2) to release the sensor (1). (c) On the sensor box, turn the worm screw (5) to get the algebraic difference between U1 and U2 secondary voltage: C
| ----------------------- |
| ! (U1 - U2) = C ! |
| ----------------------- |
NOTE: When you turn the worm screw (5), the sensor moves and changes the secondary voltages U1 and U2.
When you turn the worm screw (5):
- in one direction, U1 increases and U2 decreases,
- in the other direction, U2 increases and U1 decreases.
(d) Record the voltages U1 and U2 (in AC voltage). When you turn the worm screw (5):
- in one direction, U1 increases and U2 decreases,
- in the other direction, U2 increases and U1 decreases.
(6) TORQUE the screws (2) to between 0.25 and 0.21 m.daN (22.12 and 18.58 lbf.in )
. (7) Stage 10:
(a) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (18) set the selector switch to U1.
(b) Record the voltage (U1)(in AC voltage).
(c) On the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3) set the selector switch to U2.
(d) Record the voltage (U2)(in AC voltage).
(e) Check that the algebraic value E:
| ------------------------------------- |
| ! (U1 - U2) = E = C +/- 20mV ! |
| ------------------------------------- |
(f) If the value E is not in the limits, do the procedure from stage (9) again.
(8) If the value is correct, on panel 402VU, put the A/SKID & N/W STRG switch in OFF position.
(9) Remove the F26792000 SENSOR-VOLTAGE TEST or F26792000-1 SENSOR-VOLTAGE TEST (3).
(10) Connect the electrical connector (4) to the RVDT 4GC (1).
(11) Fill the housing of the worm screw (5) with Polysulfide Sealant-Fuel Tank Quick Curing - (Material No.06ABF1) .
(12) Apply a layer of Polysulfide Sealant-Fuel Tank Quick Curing - (Material No.06ABF1) at the areas identified S.
F. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
5. Close-up| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 121VU | ENGINE/ENG2/OIL/PRESS | 2EN2 | N42 |
| 121VU | ENGINE/ENG1/OIL/PRESS | 2EN1 | N40 |
| ** ON A/C ALL | |||
| 121VU | HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY | 4GG | M36 |
| 121VU | HYDRAULIC/BRAKING AND STEERING/SYS2/CTL | 3GG | M35 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | OIL/PRESS/ENG2 | 10KC2 | N42 |
| 121VU | OIL/PRESS/ENG1 | 10KC1 | N40 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | ENGINE/ENG2/OIL/PRESS/AND REV SNSR/CHAN A | 2EN2 | N42 |
| 121VU | ENGINE/ENG1/OIL/PRESS/AND REV SNSR/CHAN A | 2EN1 | N40 |
Subtask 32-51-00-860-064-A ** ON A/C NOT FOR ALL
A. Aircraft Maintenance Configuration
(1) Make sure that circuit breakers 2EN1 and 2EN2 are closed.
(3) If the front of the aircraft is lifted off the ground, lower the aircraft to the ground (Ref. AMM TASK 07-11-00-586-001).
(4) If the nosewheels are on grease plates, move the aircraft to remove the grease plates (Ref. AMM TASK 09-10-00-584-002).
Subtask 32-51-00-860-064-B ** ON A/C NOT FOR ALL (1) Make sure that circuit breakers 2EN1 and 2EN2 are closed.
NOTE: The open status of circuit breakers 2EN1 and 2EN2 makes the engine thrust reversers unserviceable.
(2) Remove the warning notice(s) from circuit breakers 2EN1 and 2EN2. (3) If the front of the aircraft is lifted off the ground, lower the aircraft to the ground (Ref. AMM TASK 07-11-00-586-001).
(4) If the nosewheels are on grease plates, move the aircraft to remove the grease plates (Ref. AMM TASK 09-10-00-584-002).
A. Aircraft Maintenance Configuration
(1) Make sure that circuit breakers 10KC1 and 10KC2 are closed.
(3) If the front of the aircraft is lifted off the ground, lower the aircraft to the ground (Ref. AMM TASK 07-11-00-586-001).
(4) If the nosewheels are on grease plates, move the aircraft to remove the grease plates (Ref. AMM TASK 09-10-00-584-002).
Subtask 32-51-00-740-051-A Subtask 32-51-00-942-058-A (1) Make sure that circuit breakers 10KC1 and 10KC2 are closed.
NOTE: The open status of circuit breakers 10KC1 and 10KC2 makes the engine thrust reversers unserviceable.
(2) Remove the warning notice(s) from circuit breakers 10KC1 and 10KC2. (3) If the front of the aircraft is lifted off the ground, lower the aircraft to the ground (Ref. AMM TASK 07-11-00-586-001).
(4) If the nosewheels are on grease plates, move the aircraft to remove the grease plates (Ref. AMM TASK 09-10-00-584-002).
C. Remove the Equipment
(1) Make sure that the work area is clean and clear of tools and other items.
(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.
(1) Make sure that the work area is clean and clear of tools and other items.
(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.