DOC AIRBUS | AMM A320FRemoval of the Windshield
TASK 56-11-11-000-001-A-01
Removal of the Windshield
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Work Zones and Access Panels
D. Referenced Information
3. Job Set-up
Subtask 56-11-11-010-061-A ** ON A/C NOT FOR ALL
4. Procedure
Subtask 56-11-11-020-054-A
[Rev.10 from 2021]
2026.04.01 02:06:56 UTC
Removal of the Windshield
WARNING:
YOU MUST MAKE SURE THAT YOU CAN HOLD THE COMPONENT BEFORE YOU REMOVE/INSTALL IT. THE COMPONENT IS HEAVY. IF IT FALLS, IT CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
WARNING:
BEFORE YOU START WORK, YOU MUST PUT ON A SAFETY HARNESS AND ATTACH IT TO THE ACCESS PLATFORM. WITHOUT A SAFETY HARNESS, YOU CAN FALL. THIS CAN KILL YOU OR CAUSE YOU INJURY.
CAUTION:
DO NOT USE SHARP AND/OR METALLIC TOOLS OR OBJECTS TO REMOVE/INSTALL THE WINDSHIELD OR A WINDOW. DO NOT USE A LEVER AGAINST THE EDGE OF THE WINDSHIELD OR WINDOW. IF YOU DO NOT OBEY THESE INSTRUCTIONS, YOU WILL CAUSE DAMAGE TO THE WINDSHIELD OR WINDOW.
CAUTION:
BEFORE YOU INSTALL/REMOVE THE GSE-TOOL, READ THE INSTRUCTIONS IN THE APPLICABLE GSE INSTRUCTION MANUAL. WHILE YOU OPERATE THIS TOOL, CAREFULLY OBEY THEM. IF YOU DO NOT OBEY THE INSTRUCTIONS, DAMAGE TO EQUIPMENT CAN OCCUR.
1. Reason for the JobNOTE: Two persons are necessary for this procedure.
NOTE: There are alternative procedures for the removal of the windshield. This task gives one of the procedures. The other procedures are given in the related task of this page block.
2. Job Set-up InformationA. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE |
| No specific | AR | CAP - BLANKING |
| No specific | AR | SAFETY CLIP - CIRCUIT BREAKER |
| 98A53003500000 | 1 | REMOVAL TOOL OF PHILLIPS TORQUE |
| 98F56103000000 | 1 | R I FRONT WINDOW TOOL |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.06AAB1) | Polysulfide Sealant-General Purpose Fillet - |
| (Material No.08BAA9) | Non Aqueous Cleaner-General - - |
| (Material No.13GAB8) | Low density compound-- Low temperature curing Legacy 2 |
| No specific | UMS * SEA3750-21 |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 211 | COCKPIT |
| 212 | COCKPIT |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 25-13-41-000-802-A | Removal of the Flight-Deck Eye-Position Ball-Mount Assembly |
| TASK 30-45-44-000-001-A | Removal of the Spray Nozzle |
| TASK 30-45-52-000-002-A | Removal of the Wiper Arm |
| TASK 30-81-21-000-001-A | Removal of the Lighted Icing Indicator |
Windshield - Component LocationSubtask 56-11-11-010-061-A ** ON A/C NOT FOR ALL
A. Get Access
(1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at zone 210, in front of the windshield.
(2) Remove the wiper arm (Ref. AMM TASK 30-45-52-000-002).
(3) Make sure that you correctly filled the fastener holes with sealant at the upper horizontal frame.
If you did not correctly fill them with sealant, apply Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) or ( UMS * SEA3750-21) to make the upper horizontal frame flat in the area against the seal. This will prevent pressure leaks.
Subtask 56-11-11-010-061-C ** ON A/C NOT FOR ALL (1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at zone 210, in front of the windshield.
(2) Remove the wiper arm (Ref. AMM TASK 30-45-52-000-002).
(3) Make sure that you correctly filled the fastener holes with sealant at the upper horizontal frame.
If you did not correctly fill them with sealant, apply Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) or ( UMS * SEA3750-21) to make the upper horizontal frame flat in the area against the seal. This will prevent pressure leaks.
NOTE: UMS P/N SEA3750-21 is a fast-cure sealant alternative. If you use SEA3750-21, the application time is 20-30 minutes and three hours are necessary for the sealant to be dry. When the sealant is dry, you can apply TAP 2512-1-0400 (PCN 912-0286) to prevent departure delays.
NOTE: If you use the PR1436GB1/2, the application time is 30 minutes and the cure time is 30 hours.
If you use the PR1436GB2, the application time is 2 hours and the cure time is 48 hours.
If you use the PR1436GB2, the application time is 2 hours and the cure time is 48 hours.
A. Get Access
(1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at zone 210, in front of the windshield.
(2) Remove the wiper arm (Ref. AMM TASK 30-45-52-000-002).
(3) Make sure that the upper horizontal frame (specially the spot-facing areas at the fastener locations), that touches the three lips of the windshield silicone seal, is flat.
(4) If the upper horizontal frame is not flat, do the steps that follow to prevent pressure leaks:
(a) Clean the fastener countersinks with Non Aqueous Cleaner-General - - (Material No.08BAA9) to remove the used sealant.
(b) Apply the Low density compound-- Low temperature curing Legacy 2 (Material No.13GAB8) to get a correct flat surface.
Subtask 56-11-11-865-063-A (1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at zone 210, in front of the windshield.
(2) Remove the wiper arm (Ref. AMM TASK 30-45-52-000-002).
(3) Make sure that the upper horizontal frame (specially the spot-facing areas at the fastener locations), that touches the three lips of the windshield silicone seal, is flat.
(4) If the upper horizontal frame is not flat, do the steps that follow to prevent pressure leaks:
(a) Clean the fastener countersinks with Non Aqueous Cleaner-General - - (Material No.08BAA9) to remove the used sealant.
(b) Apply the Low density compound-- Low temperature curing Legacy 2 (Material No.13GAB8) to get a correct flat surface.
NOTE: You can use RESIN EC3524 B/A as an alternative to the low-density compound. The sealant-kit manufacturer's instructions give the sealant cure time and the mixing ratio.
WARNING:
MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER RADAR ARE OPENED, SAFETIED AND TAGGED.
B. Open, safety and tag this(these) circuit breaker(s):| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 49VU | LIGHTING/STBY/COMP/LIGHT | 1LF | H04 |
| ** ON A/C NOT FOR ALL | |||
| 49VU | LIGHTING/STBY/COMP/LIGHT | 1LF | H02 |
| ** ON A/C ALL | |||
| 121VU | COM NAV/RADAR/1 | 5SQ1 | K13 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | COM NAV/RADAR/2 | 5SQ2 | K14 |
| ** ON A/C ALL | |||
| 122VU | ANTI ICE/WINDOWS/R | 4DG2 | W14 |
| 122VU | ANTI ICE/WHC/2 | 5DG2 | W13 |
| 122VU | ANTI ICE/WINDOWS/L | 4DG1 | X14 |
| 122VU | ANTI ICE/WHC/1 | 5DG1 | X13 |
| 123VU | ANTI ICE/L/WHSLD | 1DG1 | AF10 |
| 123VU | ANTI ICE/R/WHSLD | 1DG2 | AF03 |
Subtask 56-11-11-020-054-A
A. Removal of the Components
(1) Remove the spray nozzles (Ref. AMM TASK 30-45-44-000-001).
(2) Remove the nuts (45).
(3) Remove and discard the O-ring (49).
(4) Release the stud assemblies (6).
(5) Loosen the fastener (8) and remove lining panel 211LW (7).
(7) Remove vertical lining panel 211MW (1).
Subtask 56-11-11-020-055-C (1) Remove the spray nozzles (Ref. AMM TASK 30-45-44-000-001).
(2) Remove the nuts (45).
(3) Remove and discard the O-ring (49).
(4) Release the stud assemblies (6).
(5) Loosen the fastener (8) and remove lining panel 211LW (7).
NOTE: Lining panel 211LW prevents damage to the sensors.
(6) Remove the screws (2) and the washers (9). (7) Remove vertical lining panel 211MW (1).
B. Removal of the Retainers
(1) If there are fasteners that you cannot easily remove, do the procedure with the 98A53003500000 REMOVAL TOOL OF PHILLIPS TORQUE given in Para. (3).
(2) Removal of the retainers:
(a) Disconnect the sensor (15).
(b) Put the CAP-BLANKING on each disconnected electrical connector and receptacle.
(c) Remove the sealant from the heads of the screws (20), (21) and (22).
(d) Remove the screws (20), (21) and (22).
(e) Remove the protection plate (19).
(f) Remove the icing indicator (26) (Ref. AMM TASK 30-81-21-000-001).
(g) Remove the nuts (11), the washers (10) and the screws (24) and (32).
(i) Remove the flight-deck eye-position ball-mount assembly (Ref. AMM TASK 25-13-41-000-802).
(j) Remove the screws (27) and (23) and the washers (25) and (30).
(k) Remove the center retainer (18).
(l) Remove the screws (13) and the washers (28).
(m) Remove the upper retainers (31) and the lower retainers (12).
(3) Removal of the fasteners:
(a) Install the 98A53003500000 REMOVAL TOOL OF PHILLIPS TORQUE for the fasteners that you must remove:
1 Install the spacer (30) on the captive nut (37) of the removed fastener.
2 Install the slider (33) on the spacer (30).
3 Install the crossbeam (34) on the slider (33).
4 Install the pin (32).
5 Align the spindle (35) with the fastener (36) that you must remove.
6 Tighten the pad screw (31).
(b) Remove the fastener (36).
(c) Remove the 98A53003500000 REMOVAL TOOL OF PHILLIPS TORQUE.
Subtask 56-11-11-020-056-A (1) If there are fasteners that you cannot easily remove, do the procedure with the 98A53003500000 REMOVAL TOOL OF PHILLIPS TORQUE given in Para. (3).
(2) Removal of the retainers:
(a) Disconnect the sensor (15).
(b) Put the CAP-BLANKING on each disconnected electrical connector and receptacle.
(c) Remove the sealant from the heads of the screws (20), (21) and (22).
(d) Remove the screws (20), (21) and (22).
(e) Remove the protection plate (19).
(f) Remove the icing indicator (26) (Ref. AMM TASK 30-81-21-000-001).
(g) Remove the nuts (11), the washers (10) and the screws (24) and (32).
NOTE: The screws (24) and (32) have different lengths.
(h) Put marks on the screws (24) and (32) to get the correct position for the installation procedure.(i) Remove the flight-deck eye-position ball-mount assembly (Ref. AMM TASK 25-13-41-000-802).
(j) Remove the screws (27) and (23) and the washers (25) and (30).
(k) Remove the center retainer (18).
(l) Remove the screws (13) and the washers (28).
(m) Remove the upper retainers (31) and the lower retainers (12).
(3) Removal of the fasteners:
(a) Install the 98A53003500000 REMOVAL TOOL OF PHILLIPS TORQUE for the fasteners that you must remove:
1 Install the spacer (30) on the captive nut (37) of the removed fastener.
2 Install the slider (33) on the spacer (30).
3 Install the crossbeam (34) on the slider (33).
4 Install the pin (32).
5 Align the spindle (35) with the fastener (36) that you must remove.
6 Tighten the pad screw (31).
(b) Remove the fastener (36).
(c) Remove the 98A53003500000 REMOVAL TOOL OF PHILLIPS TORQUE.
C. Removal of the Windshield Panel
(2) Operate the suction cups of the 98F56103000000 R I FRONT WINDOW TOOL (50) and (54) to hold the windshield panel (14) with the 98F56103000000 R I FRONT WINDOW TOOL.
(4) Move the windshield panel (14) against the center post with the knurled nut (53) and with the 98F56103000000 R I FRONT WINDOW TOOL (54) in position.
(5) Remove the 98F56103000000 R I FRONT WINDOW TOOL.
(6) Install the vacuum handles (55) on the outer side of the windshield panel (14).
(8) Remove the windshield panel (14).
(9) When you remove the windshield, record the data in the IN-SERVICE WINDOW REMOVAL DATA GATHERING form to help Airbus continue to monitor it.
CAUTION:
DO NOT USE A SUCTION CUP TO HOLD THE INNER SURFACE OF THE WINDSHIELD PANEL IF THE PANEL HAS A SOFT (SELF-HEALING) LINER (SUPPLIER SPS). THE SUCTION CUP WILL CAUSE DAMAGE TO THE SOFT LINER.
DO NOT TRY TO REMOVE THE SOFT LINER.
THE SOFT LINER IS A PART OF THE WINDSHIELD PANEL.
(1) Install the 98F56103000000 R I FRONT WINDOW TOOL (50) and (54) on the upper part of the windshield with the pins (52). (2) Operate the suction cups of the 98F56103000000 R I FRONT WINDOW TOOL (50) and (54) to hold the windshield panel (14) with the 98F56103000000 R I FRONT WINDOW TOOL.
NOTE: Two persons are necessary to remove the windshield from its frame.
(3) Adjust the knurled screws (51) to loosen the windshield panel (14) from the lower side. (4) Move the windshield panel (14) against the center post with the knurled nut (53) and with the 98F56103000000 R I FRONT WINDOW TOOL (54) in position.
(5) Remove the 98F56103000000 R I FRONT WINDOW TOOL.
(6) Install the vacuum handles (55) on the outer side of the windshield panel (14).
NOTE: Two persons are necessary to remove the windshield panel (14):
- One person in the aircraft to push the windshield panel (14) with one hand on the top section, near the center post
- One person out of the aircraft to get the windshield panel (14) when it moves out of its frame at the center post.
(7) If you want to install the same windshield panel (14), keep it in its container in the removal area for the installation procedure. - One person in the aircraft to push the windshield panel (14) with one hand on the top section, near the center post
- One person out of the aircraft to get the windshield panel (14) when it moves out of its frame at the center post.
(8) Remove the windshield panel (14).
(9) When you remove the windshield, record the data in the IN-SERVICE WINDOW REMOVAL DATA GATHERING form to help Airbus continue to monitor it.