DOC AIRBUS | AMM A320FInstallation of the Logo Light
TASK 33-47-11-400-002-A
Installation of the Logo Light
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Work Zones and Access Panels
D. Referenced Information
3. Job Set-up
Subtask 33-47-11-860-065-A
Subtask 33-47-11-420-056-A
Subtask 33-47-11-942-052-A
[Rev.10 from 2021]
2026.04.01 00:56:09 UTC
Installation of the Logo Light
WARNING:
ISOLATE THE ELECTRICAL CIRCUITS FROM THE RELATED EQUIPMENT AND THE ENVIRONMENT.
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.06AAC1) | Polysulfide Sealant-General Purpose Interfay - |
| (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.14DBB1) | Release Agent-- Liquid Wax - |
| (Material No.14SBA1) | Textile-Lint free Cotton - |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 334 | THS TRAILING EDGE |
| 344 | THS TRAILING EDGE |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 20-28-00-912-802-A | Electrical Bonding - General Maintenance Procedure |
| TASK 20-28-00-912-803-A | Bonding Surface Preparation |
| 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 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 3LY/4LYSubtask 33-47-11-860-065-A
A. Aircraft Maintenance Configuration
(1) In the cockpit, on overhead control and indicating panel 25VU, make sure that the switch 3LA NAV & LOGO is in the OFF position.
(2) Make sure that the aircraft electrical circuits are de-energized
(Ref. AMM TASK 24-41-00-862-002).
Subtask 33-47-11-865-060-A (1) In the cockpit, on overhead control and indicating panel 25VU, make sure that the switch 3LA NAV & LOGO is in the OFF position.
(2) Make sure that the aircraft electrical circuits are de-energized
(Ref. AMM TASK 24-41-00-862-002).
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
Subtask 33-47-11-210-052-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 122VU | LIGHTING/LOGO/L | 2LY | V03 |
| 122VU | LIGHTING/LOGO/R | 1LY | V02 |
C. Preparation for Installation
(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 in the cockpit pedestal center.
(3) Make sure that the 98D27903500000 PIN-SIDE STICK LOCKING is installed in the captain side sticks.
(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.
(7) Make sure that the parts retained from the removed component are clean and in the correct conditions.
(8) Do a visual inspection of the component interface and/or adjacent area.
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 in the cockpit pedestal center.
(3) Make sure that the 98D27903500000 PIN-SIDE STICK LOCKING is installed in the captain side sticks.
(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.
(7) Make sure that the parts retained from the removed component are clean and in the correct conditions.
(8) Do a visual inspection of the component interface and/or adjacent area.
Subtask 33-47-11-420-056-A
A. Installation of the Logo Light
(1) For Ground Based Augmentation System (GBAS) Landing System (GLS) filament-light technology:
(a) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(b) Install the bonding lead (8), the washer (7) and the screw (6).
(c) Tighten the screw (6).
(d) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
(e) Remove the CAP-BLANKING from each electrical connector and receptacle.
(f) Connect the electrical connector (5).
(g) Apply a layer of Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) to the spar box skin that will touch the logo light housing (4).
(h) Apply a layer of Release Agent-- Liquid Wax - (Material No.14DBB1) to the surface of the logo light housing (4) that will touch the spar box skin.
(i) Put the logo light housing (4) in position.
(j) Install the screws (3) with wet sealant application of Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) or Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) .
(k) TORQUE the screws (3) to between 0.28 and 0.22 m.daN (24.78 and 19.47 lbf.in ).
(l) Put the frame assembly (2) in position on the logo light housing (4).
(m) Install the screws (1) with wet sealant application of Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) or Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) .
(n) TORQUE the screws (1) to between 0.28 and 0.22 m.daN (24.78 and 19.47 lbf.in ).
(o) 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 frame assembly contour and the spar-box skin surface.
(p) If the sealant cure time is not sufficient before the aircraft flight, do the procedure that follows:
1 Make sure that the sealant is not tacky.
2 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.
4 Put overlap strips of the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) around the frame 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.).
5 Make sure that the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) :
7 If the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) is damaged, then:
9 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) .
10 Make sure that there is no damage to the sealant.
(2) For GLS LEDs-light unit-technology:
(a) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(b) Install the bonding lead (7) and the screw (6).
(c) Tighten the screw (6).
(d) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
(e) Remove the CAP-BLANKING from each electrical connector and receptacle.
(f) Connect the electrical connector (5).
(g) Apply a layer of Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) to the spar box skin that will touch the logo light housing (3).
(h) Apply a layer of Release Agent-- Liquid Wax - (Material No.14DBB1) to the surface of the logo light housing (3) that will touch the spar box skin.
(i) Put the logo light housing (3) in position.
(j) Install the screws (4) with wet sealant application of Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) or Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) .
(k) TORQUE the screws (4) to between 0.28 and 0.22 m.daN (24.78 and 19.47 lbf.in ).
(l) Put the lens assembly (1) in position on the logo light housing (3).
(m) Install the screws (2) with wet sealant application of Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) or Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) .
(n) TORQUE the screws (2) to between 0.28 and 0.22 m.daN (24.78 and 19.47 lbf.in ).
(o) 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 frame assembly contour and the spar-box skin surface.
(p) If the sealant cure time is not sufficient before the aircraft flight, do the procedure that follows:
1 Make sure that the sealant is not tacky.
2 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.
4 Put overlap strips of the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) around the lens assembly (1) 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.).
5 Make sure that the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) :
7 If the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) is damaged, then:
9 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) .
10 Make sure that there is no damage to the sealant.
Subtask 33-47-11-370-054-A (1) For Ground Based Augmentation System (GBAS) Landing System (GLS) filament-light technology:
(a) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(b) Install the bonding lead (8), the washer (7) and the screw (6).
(c) Tighten the screw (6).
(d) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
(e) Remove the CAP-BLANKING from each electrical connector and receptacle.
(f) Connect the electrical connector (5).
(g) Apply a layer of Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) to the spar box skin that will touch the logo light housing (4).
(h) Apply a layer of Release Agent-- Liquid Wax - (Material No.14DBB1) to the surface of the logo light housing (4) that will touch the spar box skin.
(i) Put the logo light housing (4) in position.
(j) Install the screws (3) with wet sealant application of Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) or Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) .
(k) TORQUE the screws (3) to between 0.28 and 0.22 m.daN (24.78 and 19.47 lbf.in )
.(l) Put the frame assembly (2) in position on the logo light housing (4).
(m) Install the screws (1) with wet sealant application of Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) or Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) .
(n) TORQUE the screws (1) to between 0.28 and 0.22 m.daN (24.78 and 19.47 lbf.in )
.(o) 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 frame assembly contour and the spar-box skin surface.
(p) If the sealant cure time is not sufficient before the aircraft flight, do the procedure that follows:
1 Make sure that the sealant is not tacky.
2 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.
3 Apply the applicable length strip of Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) between the edge of the frame assembly (2) and the spar-box skin surface.4 Put overlap strips of the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) around the frame 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.).
5 Make sure that the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) :
- Is not applied on the glazing section of the frame assembly (2)
- Does not affect the logo light transmission.
7 If the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) is damaged, then:
- Replace the damaged Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) .
- Do an operational test of the logo lights (Ref. AMM TASK 33-47-00-710-002).
9 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) .
10 Make sure that there is no damage to the sealant.
(2) For GLS LEDs-light unit-technology:
(a) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(b) Install the bonding lead (7) and the screw (6).
(c) Tighten the screw (6).
(d) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
(e) Remove the CAP-BLANKING from each electrical connector and receptacle.
(f) Connect the electrical connector (5).
(g) Apply a layer of Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) to the spar box skin that will touch the logo light housing (3).
(h) Apply a layer of Release Agent-- Liquid Wax - (Material No.14DBB1) to the surface of the logo light housing (3) that will touch the spar box skin.
(i) Put the logo light housing (3) in position.
(j) Install the screws (4) with wet sealant application of Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) or Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) .
(k) TORQUE the screws (4) to between 0.28 and 0.22 m.daN (24.78 and 19.47 lbf.in )
.(l) Put the lens assembly (1) in position on the logo light housing (3).
(m) Install the screws (2) with wet sealant application of Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) or Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) .
(n) TORQUE the screws (2) to between 0.28 and 0.22 m.daN (24.78 and 19.47 lbf.in )
.(o) 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 frame assembly contour and the spar-box skin surface.
(p) If the sealant cure time is not sufficient before the aircraft flight, do the procedure that follows:
1 Make sure that the sealant is not tacky.
2 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.
3 Apply the applicable length strip of Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) between the edge of the lens assembly (1) and the spar-box skin surface. 4 Put overlap strips of the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) around the lens assembly (1) 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.).
5 Make sure that the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) :
- Is not applied on the glazing section of the lens assembly (1)
- Does not affect the logo light transmission.
7 If the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) is damaged, then:
- Replace the damaged Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) .
- Do an operational test of the logo lights (Ref. AMM TASK 33-47-00-710-002).
9 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) .
10 Make sure that there is no damage to the sealant.
B. Painting
(a) Apply Top Coat Polyurethane-- Decorative External Structure (Material No.04JMD3) or Top Coat Polyurethane_- - External Structure (Material No.04JAA3) on the heads of the screws (1).
(2) For the GLS LED-light technology:
(a) Apply Top Coat Polyurethane-- Decorative External Structure (Material No.04JMD3) or Top Coat Polyurethane_- - External Structure (Material No.04JAA3) on the heads of the screws (2).
Subtask 33-47-11-865-061-A NOTE: It is recommended to do these steps, but it is not necessary if there is no time for the paint to dry.
(1) For the GLS filament-light technology: (a) Apply Top Coat Polyurethane-- Decorative External Structure (Material No.04JMD3) or Top Coat Polyurethane_- - External Structure (Material No.04JAA3) on the heads of the screws (1).
(2) For the GLS LED-light technology:
(a) Apply Top Coat Polyurethane-- Decorative External Structure (Material No.04JMD3) or Top Coat Polyurethane_- - External Structure (Material No.04JAA3) on the heads of the screws (2).
C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 33-47-11-710-052-A 5. Close-up| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 122VU | LIGHTING/LOGO/L | 2LY | V03 |
| 122VU | LIGHTING/LOGO/R | 1LY | V02 |
Subtask 33-47-11-942-052-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 33-47-11-081-050-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 cockpit pedestal center.
(2) Remove the 98D27903500000 PIN-SIDE STICK LOCKING from the captain side sticks.
Subtask 33-47-11-860-066-A (1) Remove the 98D27403500000 PITCH TRIM CONTROL LOCKING from the cockpit pedestal center.
(2) Remove the 98D27903500000 PIN-SIDE STICK LOCKING from the captain side sticks.
C. Aircraft Maintenance Configuration
(1) Put the aircraft back to its initial configuration.
(1) Put the aircraft back to its initial configuration.