DOC AIRBUS | AMM A320FInstallation of the Logo Light Lens (Cover)
TASK 33-47-11-400-802-A
Installation of the Logo Light Lens (Cover)
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 33-47-11-860-061-A
Subtask 33-47-11-420-057-A
Subtask 33-47-11-942-055-A
[Rev.10 from 2021]
2026.04.01 00:56:11 UTC
Installation of the Logo Light Lens (Cover)
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 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 WARNING NOTICES IN THE COCKPIT TO TELL PERSONS NOT TO OPERATE THE FLIGHT CONTROLS.
THE MOVEMENT OF THE TRIMMABLE HORIZONTAL STABILIZER (THS) CAN CAUSE INJURY TO PERSONS.
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
NOTE: The procedure is the same for the two logo lights.
1. Reason for the JobSelf explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | Torque wrench: range to between 0.28 and 0.22 m.daN (24.78 and 19.47 lbf.in )  | |
| 98L12003001000 | AR | HARNESS,SAFETY |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.04JAA3) | Top Coat Polyurethane_- - External Structure |
| (Material No.04JMD3) | Top Coat Polyurethane-- Decorative External Structure |
| (Material No.05RAB9) | Adhesive Film Tape-- Aluminium Foil - |
| (Material No.06ABA1) | Polysulfide Sealant-Fuel Tank Brushable - |
| (Material No.06ACB1) | Polysulfide Sealant-Low Density Multi Purpose Fillet - |
| (Material No.08ABC1) | Aqueous Cleaner-Aircraft Exterior Pressure Spraying - |
| (Material No.08BBE1) | Non Aqueous Cleaner-- Methyl Alcohol - |
| (Material No.14DAB1) | Release Agent-- Water Base - |
| (Material No.14SBA1) | Textile-Lint free Cotton - |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 334 | THS TRAILING EDGE |
| 344 | THS TRAILING EDGE |
| FIG.ITEM | DESIGNATION | IPC-CSN |
|---|---|---|
| 2 | LENS ASSEMBLY | AIPC 33-47-11-01-010 |
| 2 | LENS ASSEMBLY | AIPC 33-47-11-01-020 |
| 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 27-00-00-080-001-A | Removal of the Pitch-Trim Control Locking Tool (98D27403500000) |
| TASK 27-00-00-480-001-A | Installation of the Pitch-Trim Control Locking Tool (98D27403500000) |
| 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 29-10-00-864-003-A | Depressurize the Blue Hydraulic System |
| TASK 33-47-00-710-002-A | Operational Test of the Logo Lights |
Logo Light Lens (GLS Filament Light)Subtask 33-47-11-860-061-A
A. Aircraft Maintenance Configuration
(1) In the cockpit, on overhead control and indicating panel 25VU, make sure that the NAV & LOGO switch is in the OFF position.
(2) Make sure that the aircraft electrical circuits are energized (Ref. AMM TASK 24-41-00-861-002).
Subtask 33-47-11-865-066-A (1) In the cockpit, on overhead control and indicating panel 25VU, make sure that the NAV & LOGO switch is in the OFF position.
(2) Make sure that the aircraft electrical circuits are energized (Ref. AMM TASK 24-41-00-861-002).
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
Subtask 33-47-11-941-056-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/ELAC1/NORM/SPLY | 15CE1 | B11 |
| 49VU | FLIGHT CONTROLS/THS/ACTR/MOT2 | 19CE2 | B09 |
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/ELAC1/NORM/SPLY | 15CE1 | B06 |
| 49VU | FLIGHT CONTROLS/THS/ACTR/MOT2 | 19CE2 | B04 |
| ** ON A/C ALL | |||
| 105VU | FLT CTL/ELAC1/STBY SPLY | 16CE1 | A01 |
| 121VU | FLIGHT CONTROLS/THS ACTR/MOT3 | 19CE3 | Q17 |
| 121VU | FLIGHT CONTROLS/THS ACTR/MOT1 | 19CE1 | Q16 |
| FOR FIN: 3LY (LOGO LIGHT) | |||
| 122VU | LIGHTING/LOGO/L | 2LY | V03 |
| FOR FIN: 4LY (LOGO LIGHT) | |||
| 122VU | LIGHTING/LOGO/R | 1LY | V02 |
C. Safety Precautions
(1) Make sure that the Green, Yellow and Blue hydraulic systems are depressurized (Ref. AMM TASK 29-10-00-864-001) (Ref. AMM TASK 29-10-00-864-002) (Ref. AMM TASK 29-10-00-864-003).
(2) Make sure that the 98D27403500000 PITCH TRIM CONTROL LOCKING is installed on the pitch-trim control wheel (Ref. AMM TASK 27-00-00-480-001).
(3) Make sure that the 98D27903500000 PIN-SIDE STICK LOCKING is installed on the CAPT and F/O side stick controllers.
(4) Make sure that the WARNING NOTICE(S) are in the cockpit to tell persons not to operate the flight controls.
(6) Make sure that the ACCESS PLATFORM 5M (16 FT) is in position at zone 334 for the left logo light and/or zone 344 for the right logo light.
4. Procedure(1) Make sure that the Green, Yellow and Blue hydraulic systems are depressurized (Ref. AMM TASK 29-10-00-864-001) (Ref. AMM TASK 29-10-00-864-002) (Ref. AMM TASK 29-10-00-864-003).
(2) Make sure that the 98D27403500000 PITCH TRIM CONTROL LOCKING is installed on the pitch-trim control wheel (Ref. AMM TASK 27-00-00-480-001).
(3) Make sure that the 98D27903500000 PIN-SIDE STICK LOCKING is installed on the CAPT and F/O side stick controllers.
(4) Make sure that the WARNING NOTICE(S) are in the cockpit to tell persons not to operate the flight controls.
WARNING:
YOU MUST PUT ON AND ATTACH A SAFETY HARNESS BEFORE YOU START WORK:
(5) Put on and attach the HARNESS, SAFETY before you start work in the work area.- ON THE THS OR IN THE REAR FUSELAGE
- ON TOP OF THE WINGS OR PYLONS.
(6) Make sure that the ACCESS PLATFORM 5M (16 FT) is in position at zone 334 for the left logo light and/or zone 344 for the right logo light.
Subtask 33-47-11-420-057-A
A. Installation of the Logo Light Lens (Cover)
(1) Make sure that the parts retained from the removed component are clean and in the correct condition.
(2) Do a visual inspection of the component interfaces and the adjacent area.
(3) If the lens assembly (2) is damaged:
(5) Apply Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) or Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) on the threads of the screws (1).
(6) Install the screws (1) on the lens assembly (2).
(7) TORQUE the screws (1) to between 0.28 and 0.22 m.daN (24.78 and 19.47 lbf.in ).
(8) Apply a fillet of Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) or Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) between the edge of the lens assembly (2) and the spar-box skin surface.
(9) If there is no time for the sealant to cure, do the procedure that follows:
(a) When the sealant is not tacky, apply Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) between the edge of the lens assembly (2) and the spar-box skin surface, as follows:
1 Apply Release Agent-- Water Base - (Material No.14DAB1) over the sealant. This will help to remove the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) after the cure time.
3 Put overlap strips of Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) around the lens assembly (2) to make sure that the surface is smooth. The minimum overlap length of the applied Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) must be 25 mm (1.0 in.).
4 Make sure that the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) is not applied on the glazing section of the lens assembly (2).
5 Do a visual check of the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) before each flight.
6 If the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) is damaged, then:
a Replace the damaged Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) .
b Do the operational test of the logo lights (Ref. AMM TASK 33-47-00-710-002).
7 Remove the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) in less than 50 flight cycles.
8 Clean the area around the logo light glazing area with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-- Methyl Alcohol - (Material No.08BBE1) or Aqueous Cleaner-Aircraft Exterior Pressure Spraying - (Material No.08ABC1) .
9 Make sure that there is no damage to the sealant.
Subtask 33-47-11-370-055-A (1) Make sure that the parts retained from the removed component are clean and in the correct condition.
(2) Do a visual inspection of the component interfaces and the adjacent area.
(3) If the lens assembly (2) is damaged:
- For the GLS filament light, get a new AIPC 33-47-11-01-010 LENS ASSEMBLY (2).
- For the GLS LEDs light-unit, get a new AIPC 33-47-11-01-020 LENS ASSEMBLY (2).
(5) Apply Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) or Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) on the threads of the screws (1).
(6) Install the screws (1) on the lens assembly (2).
(7) TORQUE the screws (1) to between 0.28 and 0.22 m.daN (24.78 and 19.47 lbf.in )
. (8) Apply a fillet of Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) or Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) between the edge of the lens assembly (2) and the spar-box skin surface.
(9) If there is no time for the sealant to cure, do the procedure that follows:
(a) When the sealant is not tacky, apply Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) between the edge of the lens assembly (2) and the spar-box skin surface, as follows:
1 Apply Release Agent-- Water Base - (Material No.14DAB1) over the sealant. This will help to remove the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) after the cure time.
CAUTION:
BEFORE YOU APPLY THE TAPE, MAKE SURE THAT THE SEALANT IS NOT TACKY. IF IT IS TACKY, THE TAPE CAN CAUSE DAMAGE TO THE SEALANT.
2 Put a strip of Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) of the applicable length along the edge of the lens assembly (2) and the spar-box skin surface. 3 Put overlap strips of Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) around the lens assembly (2) to make sure that the surface is smooth. The minimum overlap length of the applied Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) must be 25 mm (1.0 in.).
4 Make sure that the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) is not applied on the glazing section of the lens assembly (2).
5 Do a visual check of the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) before each flight.
6 If the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) is damaged, then:
a Replace the damaged Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) .
b Do the operational test of the logo lights (Ref. AMM TASK 33-47-00-710-002).
7 Remove the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) in less than 50 flight cycles.
8 Clean the area around the logo light glazing area with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-- Methyl Alcohol - (Material No.08BBE1) or Aqueous Cleaner-Aircraft Exterior Pressure Spraying - (Material No.08ABC1) .
9 Make sure that there is no damage to the sealant.
B. Painting
(1) Apply Top Coat Polyurethane-- Decorative External Structure (Material No.04JMD3) or Top Coat Polyurethane_- - External Structure (Material No.04JAA3) to the heads of the screws (1).
Subtask 33-47-11-865-067-A (1) Apply Top Coat Polyurethane-- Decorative External Structure (Material No.04JMD3) or Top Coat Polyurethane_- - External Structure (Material No.04JAA3) to the heads of the screws (1).
NOTE: It is recommended to do this step, but it is not necessary if there is no time for the paint to dry.
C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 33-47-11-710-054-A 5. Close-up| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| FOR FIN: 3LY (LOGO LIGHT) | |||
| 122VU | LIGHTING/LOGO/L | 2LY | V03 |
| FOR FIN: 4LY (LOGO LIGHT) | |||
| 122VU | LIGHTING/LOGO/R | 1LY | V02 |
Subtask 33-47-11-942-055-A
A. Removal of the Equipment
(1) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(2) Remove the access platform(s).
(3) Remove the WARNING NOTICE(S).
(4) Make sure that the work area is clean and clear of tools and other items.
Subtask 33-47-11-081-052-A (1) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(2) Remove the access platform(s).
(3) Remove the WARNING NOTICE(S).
(4) Make sure that the work area is clean and clear of tools and other items.
B. Removal of the Locking Devices
(1) Remove the 98D27403500000 PITCH TRIM CONTROL LOCKING from the pitch-trim control wheel (Ref. AMM TASK 27-00-00-080-001).
(2) Remove the 98D27903500000 PIN-SIDE STICK LOCKING from the CAPT and F/O side stick controllers.
Subtask 33-47-11-865-068-A (1) Remove the 98D27403500000 PITCH TRIM CONTROL LOCKING from the pitch-trim control wheel (Ref. AMM TASK 27-00-00-080-001).
(2) Remove the 98D27903500000 PIN-SIDE STICK LOCKING from the CAPT and F/O side stick controllers.
C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 33-47-11-860-062-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/ELAC1/NORM/SPLY | 15CE1 | B11 |
| 49VU | FLIGHT CONTROLS/THS/ACTR/MOT2 | 19CE2 | B09 |
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/ELAC1/NORM/SPLY | 15CE1 | B06 |
| 49VU | FLIGHT CONTROLS/THS/ACTR/MOT2 | 19CE2 | B04 |
| ** ON A/C ALL | |||
| 105VU | FLT CTL/ELAC1/STBY SPLY | 16CE1 | A01 |
| 121VU | FLIGHT CONTROLS/THS ACTR/MOT3 | 19CE3 | Q17 |
| 121VU | FLIGHT CONTROLS/THS ACTR/MOT1 | 19CE1 | Q16 |
D. Aircraft Maintenance Configuration
(1) Put the aircraft back to its initial configuration.
(2) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
(1) Put the aircraft back to its initial configuration.
(2) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).