DOC AIRBUS | AMM A320FInstallation of the Static Port Blanking-Plate
TASK 53-19-42-400-001-A
Installation of the Static Port Blanking-Plate
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 53-19-42-865-051-A
Subtask 53-19-42-860-050-A ** ON A/C NOT FOR ALL
(1) Remove the remaining sealant from the mating surface of the fuselage with the SCRAPER - NON METALLIC.
(2) Clean the mating surface of the fuselage with Non Aqueous Cleaner-General - - (Material No.08BAA9) and the Textile-Lint free Cotton - (Material No.14SBA1) .
(3) Remove the remaining sealant from the screws (1) and (2) with the SCRAPER - NON METALLIC.
(4) Clean the screws (1) and (2) with Non Aqueous Cleaner-General - - (Material No.08BAA9) and the Textile-Lint free Cotton - (Material No.14SBA1) .
(5) Remove the remaining sealant from the component interface with the SCRAPER - NON METALLIC.
(6) Clean the component interface with Non Aqueous Cleaner-General - - (Material No.08BAA9) and the Textile-Lint free Cotton - (Material No.14SBA1) .
(7) Do an inspection of the component interfaces and the adjacent area.
Subtask 53-19-42-220-051-A ** ON A/C NOT FOR ALL
Subtask 53-19-42-420-050-A ** ON A/C NOT FOR ALL
Subtask 53-19-42-865-052-A
Subtask 53-19-42-942-050-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 01:52:16 UTC
Installation of the Static Port Blanking-Plate
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
ZONE: 120
1. Reason for the JobSelf explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE |
| No specific | AR | PIN - NON METALLIC |
| No specific | 1 | SCRAPER - NON METALLIC |
| No specific | 1 | SPATULA - TOOTHED |
| No specific | AR | TAPE - MASKING |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.06AAB1) | Polysulfide Sealant-General Purpose Fillet - |
| (Material No.06ACB1) | Polysulfide Sealant-Low Density Multi Purpose Fillet - |
| (Material No.06AEB2) | Polysulfide Sealant-Low Adhesion Fillet Structure |
| (Material No.08BAA9) | Non Aqueous Cleaner-General - - |
| (Material No.14DBB1) | Release Agent-- Liquid Wax - |
| (Material No.14SBA1) | Textile-Lint free Cotton - |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 120 | AVIONICS COMPARTMENT |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 34-21-00-790-001-A | Low-Range Leak Test of the Standby Pneumatic Circuits |
| TASK 34-22-25-790-001-A | Low range Leak Test of the Standby Pneumatic circuits |
Installation of the Static Port Blanking-PlateSubtask 53-19-42-865-051-A
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.
A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 49VU | ANTI ICE/PROBES/AOA/1 | 4DA1 | D04 |
| 49VU | ANTI ICE/PROBES/PHC/1 | 2DA1 | D03 |
| 49VU | ANTI ICE/PROBES/PITOT/1 | 3DA1 | D02 |
| 122VU | ANTI ICE/PROBES/PHC/3 | 2DA3 | Y16 |
| 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/PHC/2 | 2DA2 | Y12 |
| 122VU | ANTI ICE/PROBES/2/STATIC | 5DA2 | Y11 |
| 122VU | ANTI ICE/PROBES/3/PITOT | 3DA3 | Z16 |
| 122VU | ANTI ICE/PROBES/3/AOA | 4DA3 | Z15 |
| 122VU | ANTI ICE/PROBES/3/STATIC | 5DA3 | Z14 |
| 122VU | ANTI ICE/PROBES/1/STATIC | 5DA1 | Z13 |
| 122VU | ANTI ICE/PROBES/1/TAT | 1DA1 | Z12 |
B. Aircraft Maintenance Configuration
(1) Make sure that the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE is in position at zone 120.
Subtask 53-19-42-110-050-A ** ON A/C NOT FOR ALL (1) Make sure that the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE is in position at zone 120.
WARNING:
DO NOT GET THE FLUID ON YOUR SKIN OR IN YOUR EYES. IF YOU DO:
C. Cleaning - FLUSH IT AWAY WITH CLEAN WATER
- GET MEDICAL AID.
(1) Remove the remaining sealant from the mating surface of the fuselage with the SCRAPER - NON METALLIC.
(2) Clean the mating surface of the fuselage with Non Aqueous Cleaner-General - - (Material No.08BAA9) and the Textile-Lint free Cotton - (Material No.14SBA1) .
(3) Remove the remaining sealant from the screws (1) and (2) with the SCRAPER - NON METALLIC.
(4) Clean the screws (1) and (2) with Non Aqueous Cleaner-General - - (Material No.08BAA9) and the Textile-Lint free Cotton - (Material No.14SBA1) .
(5) Remove the remaining sealant from the component interface with the SCRAPER - NON METALLIC.
(6) Clean the component interface with Non Aqueous Cleaner-General - - (Material No.08BAA9) and the Textile-Lint free Cotton - (Material No.14SBA1) .
(7) Do an inspection of the component interfaces and the adjacent area.
D. Check of the Clearances
(1) Put the static port blanking-plate (3) in position on the fuselage structure.
(2) At zone D, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.25 mm or +0.25 mm (0.0217 -0.0098 in. or +0.0098 in.).
(3) At zone E, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.35 mm or +0.35 mm (0.0217 -0.0138 in. or +0.0138 in.).
(4) If necessary, remove the unwanted layers from the laminated shim (4) to adjust the thickness of the static port blanking-plate (3).
Subtask 53-19-42-390-051-A ** ON A/C NOT FOR ALL (1) Put the static port blanking-plate (3) in position on the fuselage structure.
(2) At zone D, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.25 mm or +0.25 mm (0.0217 -0.0098 in. or +0.0098 in.).
(3) At zone E, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.35 mm or +0.35 mm (0.0217 -0.0138 in. or +0.0138 in.).
(4) If necessary, remove the unwanted layers from the laminated shim (4) to adjust the thickness of the static port blanking-plate (3).
NOTE: The laminated shim (4) of the static port blanking-plate (3) has 16 layers. The thickness of each layer is 0.05 mm (0.0020 in.). Thus, the total thickness of the laminated shim (4) is 0.8 mm (0.0315 in.).
(5) Remove the static port blanking-plate (3) from the fuselage structure.E. Application of Sealants
(2) Let the release agent dry.
(a) Fill the space between the laminated shim (4) and the bottom edge of the nine-hole area with the Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) (sealant C).
(b) Make sure that the clearance between the bottom edge of the nine-hole area and the sealant is 1 mm (0.0394 in.) to 2 mm (0.0787 in.).
(c) Apply a bead of Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) (sealant C) on the inner side of the middle hole of the laminated shim (4).
(4) On the component interface, apply the TAPE - MASKING on the middle holes of the static port blanking-plate (3).
(5) Apply the Polysulfide Sealant-Low Adhesion Fillet Structure (Material No.06AEB2) (sealant B) on the mating surface between the laminated shim (4) and the fuselage structure with the SPATULA - TOOTHED.
(a) Make streaks with the spatula while you apply the sealant.
(7) Remove the TAPE - MASKING from the middle holes of the static port blanking-plate (3) with the PIN - NON METALLIC.
(8) Apply the Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) (sealant C) below the heads of the screws (1) and (2).
4. ProcedureWARNING:
DO NOT GET THE FLUID ON YOUR SKIN OR IN YOUR EYES. IF YOU DO:
- FLUSH IT AWAY WITH CLEAN WATER
- GET MEDICAL AID.
CAUTION:
MAKE SURE THAT NO SEALANT GOES INTO THE MIDDLE HOLES OF THE BLANKING PLATE. SEALANT IN THE HOLES CAN CAUSE DAMAGE TO THE STATIC PROBE AND CAN CAUSE THE PROBE TO GIVE INCORRECT DATA.
(1) Apply the Release Agent-- Liquid Wax - (Material No.14DBB1) on the mating surface of the fuselage structure and on the countersunk surface of the blanking plate holes that will be in contact with fasteners.(2) Let the release agent dry.
NOTE: 15 minutes are necessary for the release agent to dry.
(3) For the middle hole of the laminated shim (4): (a) Fill the space between the laminated shim (4) and the bottom edge of the nine-hole area with the Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) (sealant C).
(b) Make sure that the clearance between the bottom edge of the nine-hole area and the sealant is 1 mm (0.0394 in.) to 2 mm (0.0787 in.).
(c) Apply a bead of Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) (sealant C) on the inner side of the middle hole of the laminated shim (4).
(4) On the component interface, apply the TAPE - MASKING on the middle holes of the static port blanking-plate (3).
(5) Apply the Polysulfide Sealant-Low Adhesion Fillet Structure (Material No.06AEB2) (sealant B) on the mating surface between the laminated shim (4) and the fuselage structure with the SPATULA - TOOTHED.
(a) Make streaks with the spatula while you apply the sealant.
NOTE: Streaks on the sealant are important because they show that there is a good bonding and a satisfactory creep.
(6) Make sure that the sealant is applied on all the surface of the laminated shim (4).(7) Remove the TAPE - MASKING from the middle holes of the static port blanking-plate (3) with the PIN - NON METALLIC.
(8) Apply the Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) (sealant C) below the heads of the screws (1) and (2).
Subtask 53-19-42-420-050-A ** ON A/C NOT FOR ALL
A. Installation of the Static Port Blanking-Plate
(1) Put the static port blanking-plate (3) in position on the fuselage structure.
(2) Install the screws (1) and (2) and tighten them.
Subtask 53-19-42-220-050-A ** ON A/C NOT FOR ALL (1) Put the static port blanking-plate (3) in position on the fuselage structure.
(2) Install the screws (1) and (2) and tighten them.
B. Check of the Clearances
(1) At zone D, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.25 mm or +0.25 mm (0.0217 -0.0098 in. or +0.0098 in.).
(2) At zone E, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.35 mm or +0.35 mm (0.0217 -0.0138 in. or +0.0138 in.).
(3) Make sure that peripheral clearance J1 between the fuselage structure and the static port blanking-plate (3) is 3.1 -1 mm or +1 mm (0.1220 -0.0394 in. or +0.0394 in.).
(4) Make sure that the distance between the heads of the screws (1) and (2) and the static port blanking-plate (3) is between -0.05 mm (-0.0020 in.) and -0.35 mm (-0.0138 in.).
Subtask 53-19-42-220-050-B ** ON A/C NOT FOR ALL (1) At zone D, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.25 mm or +0.25 mm (0.0217 -0.0098 in. or +0.0098 in.).
(2) At zone E, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.35 mm or +0.35 mm (0.0217 -0.0138 in. or +0.0138 in.).
(3) Make sure that peripheral clearance J1 between the fuselage structure and the static port blanking-plate (3) is 3.1 -1 mm or +1 mm (0.1220 -0.0394 in. or +0.0394 in.).
(4) Make sure that the distance between the heads of the screws (1) and (2) and the static port blanking-plate (3) is between -0.05 mm (-0.0020 in.) and -0.35 mm (-0.0138 in.).
B. Check of the Clearances
(1) At zone D, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.25 mm or +0.25 mm (0.0217 -0.0098 in. or +0.0098 in.).
(2) At zone E, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.35 mm or +0.35 mm (0.0217 -0.0138 in. or +0.0138 in.).
(3) Make sure that peripheral clearance J1 between the fuselage structure and the static port blanking-plate (3) is 3 -1.5 mm or +1.5 mm (0.1181 -0.0591 in. or +0.0591 in.).
(4) Make sure that the distance between the heads of the screws (1) and (2) and the static port blanking-plate (3) is between -0.05 mm (-0.0020 in.) and -0.35 mm (-0.0138 in.).
Subtask 53-19-42-220-050-P ** ON A/C NOT FOR ALL (1) At zone D, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.25 mm or +0.25 mm (0.0217 -0.0098 in. or +0.0098 in.).
(2) At zone E, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.35 mm or +0.35 mm (0.0217 -0.0138 in. or +0.0138 in.).
(3) Make sure that peripheral clearance J1 between the fuselage structure and the static port blanking-plate (3) is 3 -1.5 mm or +1.5 mm (0.1181 -0.0591 in. or +0.0591 in.).
(4) Make sure that the distance between the heads of the screws (1) and (2) and the static port blanking-plate (3) is between -0.05 mm (-0.0020 in.) and -0.35 mm (-0.0138 in.).
B. Check of the Clearances
(1) At zone D, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.25 mm or +0.25 mm (0.0217 -0.0098 in. or +0.0098 in.).
(2) At zone E, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.35 mm or +0.35 mm (0.0217 -0.0138 in. or +0.0138 in.).
(3) Make sure that peripheral clearance J1 between the fuselage structure and the static port blanking-plate (3) is 3 -1.5 mm or +1.5 mm (0.1181 -0.0591 in. or +0.0591 in.).
Subtask 53-19-42-220-050-AM ** ON A/C NOT FOR ALL (1) At zone D, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.25 mm or +0.25 mm (0.0217 -0.0098 in. or +0.0098 in.).
(2) At zone E, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.35 mm or +0.35 mm (0.0217 -0.0138 in. or +0.0138 in.).
(3) Make sure that peripheral clearance J1 between the fuselage structure and the static port blanking-plate (3) is 3 -1.5 mm or +1.5 mm (0.1181 -0.0591 in. or +0.0591 in.).
NOTE: Peripheral clearance J1 is given in concession NZ-005526547.
(4) Make sure that the distance between the heads of the screws (1) and (2) and the static port blanking-plate (3) is between -0.05 mm (-0.0020 in.) and -0.35 mm (-0.0138 in.).B. Check of the Clearances
(1) At zone D, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.25 mm or +0.25 mm (0.0217 -0.0098 in. or +0.0098 in.).
(2) At zone E, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.35 mm or +0.35 mm (0.0217 -0.0138 in. or +0.0138 in.).
(3) Make sure that peripheral clearance J1 between the fuselage structure and the static port blanking-plate (3) is 3 -1.5 mm or +1.5 mm (0.1181 -0.0591 in. or +0.0591 in.).
Subtask 53-19-42-390-050-A ** ON A/C NOT FOR ALL (1) At zone D, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.25 mm or +0.25 mm (0.0217 -0.0098 in. or +0.0098 in.).
(2) At zone E, make sure that out-of-flush dimension A1 between the fuselage structure and the static port blanking-plate (3) is 0.55 -0.35 mm or +0.35 mm (0.0217 -0.0138 in. or +0.0138 in.).
(3) Make sure that peripheral clearance J1 between the fuselage structure and the static port blanking-plate (3) is 3 -1.5 mm or +1.5 mm (0.1181 -0.0591 in. or +0.0591 in.).
NOTE: Peripheral clearance J1 is given in concession NZ-005644029.
(4) Make sure that the distance between the heads of the screws (1) and (2) and the static port blanking-plate (3) is between -0.05 mm (-0.0020 in.) and -0.35 mm (-0.0138 in.).C. Application of the Aerodynamic Sealant
(1) Fill the remaining space between the static port blanking-plate (3) and the fuselage structure with Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) or Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) .
(2) Make the contour of the sealant around the static port blanking-plate (3) smooth.
(3) Let the sealant dry.
Subtask 53-19-42-790-050-A ** ON A/C NOT FOR ALL Subtask 53-19-42-790-050-B ** ON A/C NOT FOR ALL 5. Close-up(1) Fill the remaining space between the static port blanking-plate (3) and the fuselage structure with Polysulfide Sealant-Low Density Multi Purpose Fillet - (Material No.06ACB1) or Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) .
(2) Make the contour of the sealant around the static port blanking-plate (3) smooth.
(3) Let the sealant dry.
Subtask 53-19-42-865-052-A
WARNING:
CLOSE THE PHC CIRCUIT BREAKERS 2DA1(2,3) BEFORE YOU CLOSE THE 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 INJURY TO MAINTENANCE PERSONNEL AND/OR DAMAGE TO EQUIPMENT.
A. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 49VU | ANTI ICE/PROBES/AOA/1 | 4DA1 | D04 |
| 49VU | ANTI ICE/PROBES/PHC/1 | 2DA1 | D03 |
| 49VU | ANTI ICE/PROBES/PITOT/1 | 3DA1 | D02 |
| 122VU | ANTI ICE/PROBES/PHC/3 | 2DA3 | Y16 |
| 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/PHC/2 | 2DA2 | Y12 |
| 122VU | ANTI ICE/PROBES/2/STATIC | 5DA2 | Y11 |
| 122VU | ANTI ICE/PROBES/3/PITOT | 3DA3 | Z16 |
| 122VU | ANTI ICE/PROBES/3/AOA | 4DA3 | Z15 |
| 122VU | ANTI ICE/PROBES/3/STATIC | 5DA3 | Z14 |
| 122VU | ANTI ICE/PROBES/1/STATIC | 5DA1 | Z13 |
| 122VU | ANTI ICE/PROBES/1/TAT | 1DA1 | Z12 |
B. Put the aircraft back to its initial configuration.
(1) Install the protective covers on the static probes.
(2) Make sure that the work area is clean and clear of tools and other items.
(3) Remove the access platform(s).
(1) Install the protective covers on the static probes.
(2) Make sure that the work area is clean and clear of tools and other items.
(3) Remove the access platform(s).