DOC AIRBUS | AMM A320FInstallation of the Pedal Position Transducer Unit
TASK 27-92-15-400-001-A
Installation of the Pedal Position Transducer Unit
1. Reason for the Job
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Work Zones and Access Panels
D. Expendable Parts
E. Referenced Information
3. Job Set-up
Subtask 27-92-15-860-051-A
Subtask 27-92-15-420-050-A
Subtask 27-92-15-410-050-A
[Rev.10 from 2021]
2026.03.31 23:58:36 UTC
Installation of the Pedal Position Transducer Unit
1. Reason for the Job
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE |
| No specific | AR | WARNING NOTICE(S) |
| 98A27901002000 | 2 | PIN-RIGGING,RUDDER CONTROL |
| REFERENCE | DESIGNATION |
|---|---|
| No specific | lockwire corrosion resistant steel dia 0.8 mm (0.03 in.) |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 121 | AVIONICS COMPARTMENT |
| 122 | AVIONICS COMPARTMENT |
| 811, 822 |
| FIG.ITEM | DESIGNATION | IPC-CSN |
|---|---|---|
| 8 | COTTER PIN | AIPC 27-21-01-01-010 |
| 8 | COTTER PIN | AIPC 27-21-81-01-010 |
| 16 | COTTER PIN | AIPC 27-92-01-01-010 |
| 16 | COTTER PIN | AIPC 27-92-81-01-010 |
| 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 27-24-00-710-001-A | Operational Test of the Rudder Hydraulic Actuation |
Pedal Position Transducer UnitSubtask 27-92-15-860-051-A
A. Aircraft Maintenance Configuration
(1) Make sure that the WARNING NOTICE(S) to tell persons not to operate the pedals is in position.
(2) On the panel 110VU, make sure that the WARNING NOTICE(S) is in position to tell persons not to use the rudder trim.
(3) Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access door 811.
(4) Make sure that the access door 811 is open.
(5) Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access door 822.
(6) Make sure that the access door 822 is open.
(7) On the battery power center 105VU:
Subtask 27-92-15-865-051-A (1) Make sure that the WARNING NOTICE(S) to tell persons not to operate the pedals is in position.
(2) On the panel 110VU, make sure that the WARNING NOTICE(S) is in position to tell persons not to use the rudder trim.
(3) Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access door 811.
(4) Make sure that the access door 811 is open.
(5) Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position at the access door 822.
(6) Make sure that the access door 822 is open.
(7) On the battery power center 105VU:
- make sure that the protective cover is removed.
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
4. Procedure| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 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 ALL | |||
| 105VU | FLIGHT CONTROLS/ELAC2/STBY SPLY | 16CE2 | A02 |
| 105VU | FLT CTL/ELAC1/STBY SPLY | 16CE1 | A01 |
| 121VU | FLIGHT CONTROLS/ELAC2/NORM/SPLY | 15CE2 | R20 |
Subtask 27-92-15-420-050-A
A. Installation of the Transducer Unit
(1) Clean the component interfaces and the adjacent area.
(2) Do an inspection of the component interfaces and the adjacent area.
(3) Install the transducer unit (12) on its support (18) and install the bolts (1).
(4) Install the washers (17).
(5) Install and tighten the nuts (15) and safety with the new AIPC 27-92-01-01-010 COTTER PIN (16) or AIPC 27-92-81-01-010 COTTER PIN (16).
(6) Install the rod (5), bolt (2), washer (6) and nut (7) and tighten.
(7) Safety with the new AIPC 27-21-01-01-010 COTTER PIN (8) or AIPC 27-21-81-01-010 COTTER PIN (8).
(8) Push in and hold the pin:
(b) Loosen the nuts (3) and (10) and disengage the lockwashers (4) and (9).
(c) Adjust the length of the rod (5) until you can engage the bolt (2).
(d) Engage the lockwashers (4) and (9). Tighten the nuts (3) and (10) and safety them with lockwire corrosion resistant steel dia 0.8 mm (0.03 in.).
(e) Make sure that you can remove and install freely the 98A27901002000 PIN-RIGGING,RUDDER CONTROL (19) on the yaw/brake bellcranks. If you cannot, adjust the length of the rod (5) again. Install the 98A27901002000 PIN-RIGGING,RUDDER CONTROL (19) on the yaw/brake bellcranks.
(10) Release the pin (11) and make sure that it disengages freely.
(11) Remove the blanking caps from the electrical connectors (13) and (14).
(12) Make sure that all the electrical connections are clean and in the correct condition.
(13) Connect the electrical connectors (13) and (14) to the transducer unit (12).
Subtask 27-92-15-820-050-A (1) Clean the component interfaces and the adjacent area.
(2) Do an inspection of the component interfaces and the adjacent area.
(3) Install the transducer unit (12) on its support (18) and install the bolts (1).
(4) Install the washers (17).
(5) Install and tighten the nuts (15) and safety with the new AIPC 27-92-01-01-010 COTTER PIN (16) or AIPC 27-92-81-01-010 COTTER PIN (16).
(6) Install the rod (5), bolt (2), washer (6) and nut (7) and tighten.
(7) Safety with the new AIPC 27-21-01-01-010 COTTER PIN (8) or AIPC 27-21-81-01-010 COTTER PIN (8).
(8) Push in and hold the pin:
CAUTION:
BE CAREFUL WHEN YOU USE THE RIGGING PIN ON THE TRANSDUCER UNIT.
DO NOT USE FORCE TO ENGAGE THE RIGGING PIN IN THE TRANSDUCER UNIT. IF YOU USE FORCE, THE RIGGING PIN WILL NOT DISENGAGE FREELY AND DAMAGE TO THE TRANSDUCER UNIT CAN OCCUR.
(a) Push in and hold the pin (11) to lock the input lever of the transducer unit (12) in the zero position. NOTE: The pin (11) is a part of the transducer unit (12).
(9) If you cannot engage the pin (11) freely, adjust the length of the body (3) as follows: 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 remove the lockwire. (b) Loosen the nuts (3) and (10) and disengage the lockwashers (4) and (9).
(c) Adjust the length of the rod (5) until you can engage the bolt (2).
(d) Engage the lockwashers (4) and (9). Tighten the nuts (3) and (10) and safety them with lockwire corrosion resistant steel dia 0.8 mm (0.03 in.).
(e) Make sure that you can remove and install freely the 98A27901002000 PIN-RIGGING,RUDDER CONTROL (19) on the yaw/brake bellcranks. If you cannot, adjust the length of the rod (5) again. Install the 98A27901002000 PIN-RIGGING,RUDDER CONTROL (19) on the yaw/brake bellcranks.
(10) Release the pin (11) and make sure that it disengages freely.
(11) Remove the blanking caps from the electrical connectors (13) and (14).
(12) Make sure that all the electrical connections are clean and in the correct condition.
(13) Connect the electrical connectors (13) and (14) to the transducer unit (12).
B. Preparation for the Test
(1) Remove the 98A27901002000 PIN-RIGGING,RUDDER CONTROL (19).
(2) Make sure that the pin (11) is disengaged from the input lever of the transducer unit (12)
Subtask 27-92-15-861-050-A Subtask 27-92-15-865-052-A (1) Remove the 98A27901002000 PIN-RIGGING,RUDDER CONTROL (19).
(2) Make sure that the pin (11) is disengaged from the input lever of the transducer unit (12)
D. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 27-92-15-865-053-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 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 ALL | |||
| 105VU | FLIGHT CONTROLS/ELAC2/STBY SPLY | 16CE2 | A02 |
| 105VU | FLT CTL/ELAC1/STBY SPLY | 16CE1 | A01 |
| 121VU | FLIGHT CONTROLS/ELAC2/NORM/SPLY | 15CE2 | R20 |
E. Make sure that this(these) circuit breaker(s) is(are) closed:
Subtask 27-92-15-710-050-C | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/ELAC1/NORM/SPLY | 15CE1 | B11 |
| 49VU | FLIGHT CONTROLS/FCDC1/SPLY | 20CE1 | B10 |
| 49VU | FLIGHT CONTROLS/SEC1/NORM/SPLY | 21CE1 | B08 |
| 49VU | AUTO FLT/FAC1/28VDC | 5CC1 | B04 |
| 49VU | AUTO FLT/FAC1/26VAC | 14CC1 | B03 |
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/ELAC1/NORM/SPLY | 15CE1 | B06 |
| 49VU | FLIGHT CONTROLS/FCDC1/SPLY | 20CE1 | B05 |
| 49VU | FLIGHT CONTROLS/SEC1/NORM/SPLY | 21CE1 | B03 |
| 49VU | AUTO FLT/FAC1/28VDC | 5CC1 | H10 |
| 49VU | AUTO FLT/FAC1/26VAC | 14CC1 | H09 |
| ** ON A/C ALL | |||
| 105VU | FLIGHT CONTROLS/ELAC2/STBY SPLY | 16CE2 | A02 |
| 105VU | FLT CTL/ELAC1/STBY SPLY | 16CE1 | A01 |
| 105VU | FLT CTL/SEC1/STBY SPLY | 22CE | B01 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | PTR/SPLY | 6TW | J21 |
| 121VU | CFDS/TEST PLUG/2 | 10TW | J20 |
| 121VU | CFDS/TEST PLUG/1 | 9TW | J19 |
| 121VU | CFDS/CFDIU/SPLY | 2TW | J18 |
| 121VU | CFDS/CFDIU/BACK/UP | 8TW | J17 |
| 121VU | AUTO FLT/STICK/LOCK | 13CA | N16 |
| ** ON A/C ALL | |||
| 121VU | AUTO FLT/FAC2/28VDC | 5CC2 | M19 |
| 121VU | AUTO FLT/FAC2/26VAC | 14CC2 | M18 |
| 121VU | FLIGHT CONTROLS/FCDC2/SPLY | 20CE2 | Q20 |
| 121VU | FLIGHT CONTROLS/SEC3/SPLY | 21CE3 | Q19 |
| 121VU | FLIGHT CONTROLS/SEC2/SPLY | 21CE2 | Q18 |
| 121VU | FLIGHT CONTROLS/ELAC2/NORM/SPLY | 15CE2 | R20 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | PTR/SPLY | 6TW | J44 |
| 121VU | CFDS/TEST PLUG/2 | 10TW | J43 |
| 121VU | CFDS/TEST PLUG/1 | 9TW | J42 |
| 121VU | CFDS/CFDIU/SPLY | 2TW | J41 |
| 121VU | CFDS/CFDIU/BACK/UP | 8TW | J40 |
| 121VU | AUTO FLT/STICK/LOCK | 13CA | N18 |
F. Test
(1) On the overhead panel 23VU make sure that:
(4) Do the operational test of the rudder hydraulic actuation (Ref. AMM TASK 27-24-00-710-001).
5. Close-up(1) 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 FAULT and OFF legends are off).
- The FLT CTL/ELAC 2, FLT CTL/SEC 2 and FLT CTL/SEC 3 pushbutton switches are pushed (on these pushbutton switches, the FAULT and OFF legends are off).
| ACTION | RESULT |
|---|---|
| 1.On the center pedestal, on one MCDU, push the MCDU MENU mode key. | The MCDU shows the MCDU MENU page. |
| 2.Push the line key adjacent to the CFDS indication. | The MCDU shows the CFDS MENU page. |
| 3.Push the line key adjacent to the SYSTEM REPORT/TEST indication. | The MCDU shows the SYSTEM REPORT/TEST page. |
| 4.Push the line key adjacent to the F/CTL indication. | The MCDU shows the F/CTL page. |
| 5.Push the line key adjacent to the EFCS 1 indication. | The MCDU shows the EFCS 1 page. |
| 6.Push the line key adjacent to the GROUND SCAN indication. | The MCDU shows the EFCS 1 GROUND SCAN page. |
| 7.Push the line key adjacent to the START GROUND SCAN indication and wait two minutes. | |
| 8.Push the line key adjacent to the GROUND SCAN STOP indication. | |
| 9.Push the line key adjacent to the GROUND REPORT indication. | Make sure that the MCDU shows no fault of the transducer units (25CE1,25CE2). |
| 10.On the MCDU, push the line select key adjacent to the RETURN indication until the CFDS menu page comes into view. | The MCDU shows the MCDU MENU page. |
Subtask 27-92-15-410-050-A
A. Close Access
(1) Remove the WARNING NOTICE(S).
(2) Make sure that the work area is clean and clear of tools and other items.
(3) Close the access door 811.
(4) Remove the access platform(s).
(5) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002).
(1) Remove the WARNING NOTICE(S).
(2) Make sure that the work area is clean and clear of tools and other items.
(3) Close the access door 811.
(4) Remove the access platform(s).
(5) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002).