DOC AIRBUS | AMM A320FInstallation of the Vertical Stabilizer Leading-Edge
TASK 55-32-11-400-001-A
Installation of the Vertical Stabilizer Leading-Edge
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 55-32-11-860-055-A
Subtask 55-32-11-420-051-B ** ON A/C NOT FOR ALL
Subtask 55-32-11-410-052-A
[Rev.10 from 2021]
2026.04.01 02:05:52 UTC
Installation of the Vertical Stabilizer Leading-Edge
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:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
CAUTION:
MAKE SURE YOU DO NOT DAMAGE THE ANTENNA.
ZONE: 322
1. Reason for the JobSelf explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | 1 | COUNTERSINK TOOL |
| No specific | 1 | CRANE HEIGHT 15 M (50 FT) |
| No specific | 1 | DRILL - CORE BIT DIA 32 MM (1.26 IN) |
| No specific | AR | DRILL - ELECTRIC OR PNEUMATIC |
| No specific | 1 | MARKER - FELT TIP |
| No specific | 1 | PUMP - VACUUM |
| No specific | 1 | SCRAPER - NON METALLIC |
| No specific | Torque wrench: range to between 0.5 and 0.4 m.daN (44.25 and 35.40 lbf.in )  | |
| 98A55308440001 | 1 | SLING-UNIVERSAL,TAILPLANE |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.05PAC1) | Double Sided Adhesive Tape-- Foam Base - |
| (Material No.06AAA1) | Polysulfide Sealant_General Purpose Brushable - |
| (Material No.06AAB1) | Polysulfide Sealant-General Purpose Fillet - |
| (Material No.06AEA1) | Polysulfide Sealant-Low Adhesion Brushable - |
| (Material No.08BAA9) | Non Aqueous Cleaner-General - - |
| (Material No.08BBC1) | Non Aqueous Cleaner-- Naphta based and Alcohol - |
| (Material No.14DBB1) | Release Agent-- Liquid Wax - |
| (Material No.14JEA1) | Sealing Profile-Vaccum Bag Sealant - - |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 322 | VERTICAL STABILIZER LEADING EDGE |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 11-00-00-400-022-A | Installation of the Hoisting-Point Cover Patches |
| TASK 20-28-00-912-802-A | Electrical Bonding - General Maintenance Procedure |
| TASK 29-00-00-864-001-A | Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action |
| SRM 517512 | |
| SRM 553211 | |
Vertical Stabilizer Leading-EdgeSubtask 55-32-11-860-055-A
A. Aircraft Maintenance Configuration
(1) Make sure that the warning notices are in position to tell persons not to operate the flight controls.
(2) Make sure that the Green, Blue and Yellow system is depressurized (Ref. AMM TASK 29-00-00-864-001).
(3) Make sure that the access platform is in position.
Subtask 55-32-11-865-053-A (1) Make sure that the warning notices are in position to tell persons not to operate the flight controls.
(2) Make sure that the Green, Blue and Yellow system is depressurized (Ref. AMM TASK 29-00-00-864-001).
(3) Make sure that the access platform is in position.
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
Subtask 55-32-11-560-050-A ** ON A/C NOT FOR ALL | 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 |
| 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/THS/ACTR/MOT2 | 19CE2 | B04 |
| 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 |
| 121VU | AUTO FLT/RUDDER/TRIM/IND | 15CC | M20 |
| 121VU | AUTO FLT/FAC2/28VDC | 5CC2 | M19 |
| 121VU | AUTO FLT/FAC2/26VAC | 14CC2 | M18 |
| 121VU | FLIGHT CONTROLS/SEC3/SPLY | 21CE3 | Q19 |
| 121VU | FLIGHT CONTROLS/SEC2/SPLY | 21CE2 | Q18 |
| 121VU | FLIGHT CONTROLS/THS ACTR/MOT3 | 19CE3 | Q17 |
| 121VU | FLIGHT CONTROLS/THS ACTR/MOT1 | 19CE1 | Q16 |
| 121VU | FLIGHT CONTROLS/ELAC2/NORM/SPLY | 15CE2 | R20 |
C. Preparation for the Installation
(1) Do a check of the condition of the sealant on the mating surfaces of the leading edge panel (3), the ribs and the spar box:
(a) Remove the sealant from the mating surfaces of the leading edge panel (3), the ribs and the spar box with the SCRAPER - NON METALLIC.
(b) Apply Polysulfide Sealant-Low Adhesion Brushable - (Material No.06AEA1) on the mating surfaces along the leading edge ribs and the spar box. Do not apply the sealant on the bonding points.
(c) Apply the Release Agent-- Liquid Wax - (Material No.14DBB1) on the mating surfaces of the leading edge panel (3). Do not apply the release agent on the bonding points.
(2) Make sure that the anchor nuts at the leading edge ribs and along the spar box are in good condition.
(3) Clean the mating surfaces with Non Aqueous Cleaner-- Naphta based and Alcohol - (Material No.08BBC1) .
Subtask 55-32-11-560-050-B ** ON A/C NOT FOR ALL (1) Do a check of the condition of the sealant on the mating surfaces of the leading edge panel (3), the ribs and the spar box:
(a) Remove the sealant from the mating surfaces of the leading edge panel (3), the ribs and the spar box with the SCRAPER - NON METALLIC.
(b) Apply Polysulfide Sealant-Low Adhesion Brushable - (Material No.06AEA1) on the mating surfaces along the leading edge ribs and the spar box. Do not apply the sealant on the bonding points.
(c) Apply the Release Agent-- Liquid Wax - (Material No.14DBB1) on the mating surfaces of the leading edge panel (3). Do not apply the release agent on the bonding points.
(2) Make sure that the anchor nuts at the leading edge ribs and along the spar box are in good condition.
(3) Clean the mating surfaces with Non Aqueous Cleaner-- Naphta based and Alcohol - (Material No.08BBC1) .
C. Preparation for the Installation
(1) Do a check for the condition of the sealant on the mating surfaces of the leading edge panel (3), the ribs and the spar box:
(a) Remove the sealant from the mating surfaces of the leading edge panel (3), the ribs and the spar box with the SCRAPER - NON METALLIC.
(b) Apply Polysulfide Sealant-Low Adhesion Brushable - (Material No.06AEA1) on the mating surfaces along the leading edge ribs and the spar box. Do not apply the sealant on the bonding points.
(c) Apply the Release Agent-- Liquid Wax - (Material No.14DBB1) on the mating surfaces of the leading edge panel (3). Do not apply the release agent on the bonding points.
(2) Make sure that the anchor nuts at the leading edge ribs and along the spar box are in good condition.
(3) Clean the mating surfaces with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(4) If necessary, do a check of the steel cover (13) for good condition and replace it SRM 553211.
(5) Install the vacuum equipment:
(a) Attach the Sealing Profile-Vaccum Bag Sealant - - (Material No.14JEA1) (11) around the steel cover (13) and at approximately 30 mm (1.1811 in.) from its edge.
(b) Install a sheet (15) made of MARKER - FELT TIP on the steel cover (13) with Double Sided Adhesive Tape-- Foam Base - (Material No.05PAC1) .
(c) Attach the vacuum valve (5) to the vacuum foil (16).
(d) Put the vacuum foil (16) in position on the steel cover (13). Make sure that there is an overlap of approximately 30 mm (1.1811 in.) with the seal tape (11).
(e) Connect the PUMP - VACUUM to the vacuum valve (5).
(f) Operate the vacuum pump as necessary. Refer to the ambient temperature values shown in the table that follows:
(6) Remove the vacuum pump:
(a) Disconnect the vacuum pump from the vacuum valve (5).
(b) Remove the vacuum foil (16).
(c) Remove the vacuum valve (5) from the vacuum foil (16).
(d) Remove the porous felt (15).
(e) Remove the seal tape (11).
(f) Clean the steel cover (13) and the adjacent area with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(7) Drill the steel cover (13):
(a) Use the DRILL - ELECTRIC OR PNEUMATIC 4.8 mm (0.1890 in.) to carefully drill the steel cover (13) from the inner side of the leading edge.
(b) Use the COUNTERSINK TOOL to increase the diameter of the holes around the applicable leading edge panel (3), (7) or (8) to 9 mm (0.3543 in.).
(c) Use the DRILL - CORE BIT DIA 32 MM (1.26 IN) to increase the diameter of the holes of the hoist fittings to 32 mm (1.2598 in.).
(8) Apply a bead of Polysulfide Sealant_General Purpose Brushable - (Material No.06AAA1) on all the butt joints and around the holes.
4. Procedure(1) Do a check for the condition of the sealant on the mating surfaces of the leading edge panel (3), the ribs and the spar box:
(a) Remove the sealant from the mating surfaces of the leading edge panel (3), the ribs and the spar box with the SCRAPER - NON METALLIC.
(b) Apply Polysulfide Sealant-Low Adhesion Brushable - (Material No.06AEA1) on the mating surfaces along the leading edge ribs and the spar box. Do not apply the sealant on the bonding points.
(c) Apply the Release Agent-- Liquid Wax - (Material No.14DBB1) on the mating surfaces of the leading edge panel (3). Do not apply the release agent on the bonding points.
(2) Make sure that the anchor nuts at the leading edge ribs and along the spar box are in good condition.
(3) Clean the mating surfaces with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(4) If necessary, do a check of the steel cover (13) for good condition and replace it SRM 553211.
(5) Install the vacuum equipment:
(a) Attach the Sealing Profile-Vaccum Bag Sealant - - (Material No.14JEA1) (11) around the steel cover (13) and at approximately 30 mm (1.1811 in.) from its edge.
(b) Install a sheet (15) made of MARKER - FELT TIP on the steel cover (13) with Double Sided Adhesive Tape-- Foam Base - (Material No.05PAC1) .
(c) Attach the vacuum valve (5) to the vacuum foil (16).
(d) Put the vacuum foil (16) in position on the steel cover (13). Make sure that there is an overlap of approximately 30 mm (1.1811 in.) with the seal tape (11).
(e) Connect the PUMP - VACUUM to the vacuum valve (5).
(f) Operate the vacuum pump as necessary. Refer to the ambient temperature values shown in the table that follows:
| TEMPERATURE | TIME |
|---|---|
| 18 deg.C (64.40 deg.F) | for 48 hours |
| 20 deg.C (68.00 deg.F) | for 30 hours |
| 23 deg.C (73.40 deg.F) | for 24 hours |
(a) Disconnect the vacuum pump from the vacuum valve (5).
(b) Remove the vacuum foil (16).
(c) Remove the vacuum valve (5) from the vacuum foil (16).
(d) Remove the porous felt (15).
(e) Remove the seal tape (11).
(f) Clean the steel cover (13) and the adjacent area with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(7) Drill the steel cover (13):
(a) Use the DRILL - ELECTRIC OR PNEUMATIC 4.8 mm (0.1890 in.) to carefully drill the steel cover (13) from the inner side of the leading edge.
(b) Use the COUNTERSINK TOOL to increase the diameter of the holes around the applicable leading edge panel (3), (7) or (8) to 9 mm (0.3543 in.).
(c) Use the DRILL - CORE BIT DIA 32 MM (1.26 IN) to increase the diameter of the holes of the hoist fittings to 32 mm (1.2598 in.).
(8) Apply a bead of Polysulfide Sealant_General Purpose Brushable - (Material No.06AAA1) on all the butt joints and around the holes.
Subtask 55-32-11-420-051-B ** ON A/C NOT FOR ALL
A. Installation of the Vertical Stabilizer Leading-Edge
(2) Put the CRANE HEIGHT 15 M (50 FT) in position.
(3) Attach the 98A55308440001 SLING-UNIVERSAL,TAILPLANE to the lift lugs and to the crane.
(4) Install the leading edge panel (3).
(a) Prepare the electrical bonding of the leading edge panel (3) at the applicable screws (4) (Ref. AMM TASK 20-28-00-912-802).
(b) Apply Polysulfide Sealant-Low Adhesion Brushable - (Material No.06AEA1) on the screws (4).
(c) Put the leading edge panel (3) in position.
(d) Install the screws (4).
(e) TORQUE the screws (4) to between 0.5 and 0.4 m.daN (44.25 and 35.40 lbf.in ).
(f) Complete the bonding procedure of the leading edge panel (3) at the applicable screws (4) (Ref. AMM TASK 20-28-00-912-802).
(5) Make sure that clearance A between the leading edge panels (3), (7) and (8) is 1 +3 mm or -0 mm (0.0394 +0.1181 in. or +0.0000 in.).
(6) Remove the sling.
(7) Remove the lift lugs.
(8) Install the plastic plugs in the lift points. The plastic plugs must be flush with the contour of the leading edge.
(9) Install the new self-adhesive disks on the hoisting points (Ref. AMM TASK 11-00-00-400-022).
Subtask 55-32-11-420-051-E ** ON A/C NOT FOR ALL NOTE: The installation procedure of the leading edge panels (3), (7) and (8) is the same.
(1) Make sure that the work area is clean and clear of tools and other items.(2) Put the CRANE HEIGHT 15 M (50 FT) in position.
(3) Attach the 98A55308440001 SLING-UNIVERSAL,TAILPLANE to the lift lugs and to the crane.
(4) Install the leading edge panel (3).
(a) Prepare the electrical bonding of the leading edge panel (3) at the applicable screws (4) (Ref. AMM TASK 20-28-00-912-802).
(b) Apply Polysulfide Sealant-Low Adhesion Brushable - (Material No.06AEA1) on the screws (4).
(c) Put the leading edge panel (3) in position.
(d) Install the screws (4).
(e) TORQUE the screws (4) to between 0.5 and 0.4 m.daN (44.25 and 35.40 lbf.in )
. (f) Complete the bonding procedure of the leading edge panel (3) at the applicable screws (4) (Ref. AMM TASK 20-28-00-912-802).
(5) Make sure that clearance A between the leading edge panels (3), (7) and (8) is 1 +3 mm or -0 mm (0.0394 +0.1181 in. or +0.0000 in.).
(6) Remove the sling.
(7) Remove the lift lugs.
(8) Install the plastic plugs in the lift points. The plastic plugs must be flush with the contour of the leading edge.
(9) Install the new self-adhesive disks on the hoisting points (Ref. AMM TASK 11-00-00-400-022).
NOTE: If the self-adhesive disks are missing, there is no problem to operate the aircraft for a temporary period.
(10) Apply Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) around the leading edge panel (3). Make sure that the leading edge panel (3) is flush with the spar box. A. Installation of the Vertical Stabilizer Leading-Edge
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Put the CRANE HEIGHT 15 M (50 FT) in position.
(3) Attach the 98A55308440001 SLING-UNIVERSAL,TAILPLANE to the lift lugs and to the crane.
(4) Install the leading edge panel (3):
(a) Prepare the electrical bonding of the leading edge panel (3) at the applicable screws (4) (Ref. AMM TASK 20-28-00-912-802).
(b) Apply the Polysulfide Sealant-Low Adhesion Brushable - (Material No.06AEA1) on the screws (4).
(c) Put the leading edge panel (3) in position.
(d) Install the screws (4).
(e) TORQUE the screws (4) to between 0.5 and 0.4 m.daN (44.25 and 35.40 lbf.in ).
(f) Complete the bonding procedure of the leading edge panel (3) at the applicable screws (4) (Ref. AMM TASK 20-28-00-912-802).
(5) Make sure that clearance A between the leading edge panels (3), (7) and (8) is 1 +3 mm or -0 mm (0.0394 +0.1181 in. or +0.0000 in.).
(6) Remove the sling.
(7) Remove the lift lugs.
(8) Install the plastic plugs in the lift points. The plastic plugs must be flush with the contour of the leading edge.
(9) Install the new self-adhesive disks on the hoisting points (Ref. AMM TASK 11-00-00-400-022).
Subtask 55-32-11-420-052-A ** ON A/C NOT FOR ALL 5. Close-up(1) Make sure that the work area is clean and clear of tools and other items.
(2) Put the CRANE HEIGHT 15 M (50 FT) in position.
(3) Attach the 98A55308440001 SLING-UNIVERSAL,TAILPLANE to the lift lugs and to the crane.
(4) Install the leading edge panel (3):
(a) Prepare the electrical bonding of the leading edge panel (3) at the applicable screws (4) (Ref. AMM TASK 20-28-00-912-802).
(b) Apply the Polysulfide Sealant-Low Adhesion Brushable - (Material No.06AEA1) on the screws (4).
(c) Put the leading edge panel (3) in position.
(d) Install the screws (4).
(e) TORQUE the screws (4) to between 0.5 and 0.4 m.daN (44.25 and 35.40 lbf.in )
. (f) Complete the bonding procedure of the leading edge panel (3) at the applicable screws (4) (Ref. AMM TASK 20-28-00-912-802).
(5) Make sure that clearance A between the leading edge panels (3), (7) and (8) is 1 +3 mm or -0 mm (0.0394 +0.1181 in. or +0.0000 in.).
(6) Remove the sling.
(7) Remove the lift lugs.
(8) Install the plastic plugs in the lift points. The plastic plugs must be flush with the contour of the leading edge.
(9) Install the new self-adhesive disks on the hoisting points (Ref. AMM TASK 11-00-00-400-022).
NOTE: If the self-adhesive disks are missing, there is no problem to operate the aircraft for a temporary period.
(10) Apply Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) around the leading edge panel (3). Make sure that the leading edge panel (3) is flush with the spar box. Subtask 55-32-11-410-052-A
A. Close Access
(1) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(2) Remove the crane.
(3) Remove the WARNING NOTICE(S).
(4) Remove the access platform(s).
Subtask 55-32-11-865-052-A (1) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(2) Remove the crane.
(3) Remove the WARNING NOTICE(S).
(4) Remove the access platform(s).
B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
| 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 |
| 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/THS/ACTR/MOT2 | 19CE2 | B04 |
| 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 |
| 121VU | AUTO FLT/RUDDER/TRIM/IND | 15CC | M20 |
| 121VU | AUTO FLT/FAC2/28VDC | 5CC2 | M19 |
| 121VU | AUTO FLT/FAC2/26VAC | 14CC2 | M18 |
| 121VU | FLIGHT CONTROLS/SEC3/SPLY | 21CE3 | Q19 |
| 121VU | FLIGHT CONTROLS/SEC2/SPLY | 21CE2 | Q18 |
| 121VU | FLIGHT CONTROLS/THS ACTR/MOT3 | 19CE3 | Q17 |
| 121VU | FLIGHT CONTROLS/THS ACTR/MOT1 | 19CE1 | Q16 |
| 121VU | FLIGHT CONTROLS/ELAC2/NORM/SPLY | 15CE2 | R20 |