DOC AIRBUS | AMM A320FInstallation of the Inboard and Outboard-Flap Tab Hinge-Fairings
TASK 57-55-11-400-005-A
Installation of the Inboard and Outboard-Flap Tab Hinge-Fairings
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 57-55-11-941-068-A ** ON A/C NOT FOR ALL
Subtask 57-55-11-420-074-A ** ON A/C NOT FOR ALL
Subtask 57-55-11-942-058-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 03:53:57 UTC
Installation of the Inboard and Outboard-Flap Tab Hinge-Fairings
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
WARNING:
MAKE SURE THAT THE FLIGHT CONTROL SAFETY-LOCKS AND THE WARNING NOTICES ARE IN POSITION.
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) |
| No specific | 1 | SCRAPER - NON METALLIC |
| No specific | AR | WARNING NOTICE(S) |
| No specific | Torque wrench: range to between 0.45 and 0.35 m.daN (39.82 and 30.97 lbf.in )  | |
| No specific | Torque wrench: range to between 0.8 and 0.7 m.daN (70.80 and 61.95 lbf.in ) | |
| No specific | Torque wrench: range to between 1.8 and 1.6 m.daN (13.27 and 11.80 lbf.ft ) | |
| 98D27803500001 | 1 | LOCKING TOOL ZERO POS |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.05RAB9) | Adhesive Film Tape-- Aluminium Foil - |
| (Material No.06AAB1) | Polysulfide Sealant-General Purpose Fillet - |
| (Material No.06LCG9) | Non Hardening Jointing Putty-Medium Temp. Area - - |
| (Material No.08BAA9) | Non Aqueous Cleaner-General - - |
| (Material No.14SBA1) | Textile-Lint free Cotton - |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 537 | FLAP TAB HINGE 3A |
| 538 | FLAP TAB HINGE 3B |
| 539 | FLAP TAB HINGE 3C |
| 581 | FLAP N° 1 |
| 587 | FLAP N° 2 |
| 637 | FLAP TAB HINGE 3A |
| 638 | FLAP TAB HINGE 3B |
| 639 | FLAP TAB HINGE 3C |
| 681 | FLAP N° 1 |
| 687 | FLAP N° 2 |
| 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 27-50-00-866-009-A | Retraction of the Flaps on the Ground |
| TASK 27-50-00-866-009-A-01 | Retraction of the Flaps/Slats on the Ground |
| TASK 27-54-00-710-001-A | Operational Test of the Flap System |
| TASK 57-55-11-000-005-A | Removal of the Inboard and Outboard-Flap Tab Hinge-Fairings |
Hinge 1A Fairings - Location and DetailSubtask 57-55-11-941-068-A ** ON A/C NOT FOR ALL
A. Safety Precautions
(1) Make sure that the WARNING NOTICE(S) are in position in the cockpit to tell persons not to operate the flaps or slats.
(2) Make sure that the safety barriers are in position.
Subtask 57-55-11-860-053-A ** ON A/C NOT FOR ALL (1) Make sure that the WARNING NOTICE(S) are in position in the cockpit to tell persons not to operate the flaps or slats.
(2) Make sure that the safety barriers are in position.
B. Aircraft Maintenance Configuration
(1) Make sure that you fully retracted the flaps (Ref. AMM TASK 27-50-00-866-009).
(2) Make sure that the 98D27803500001 LOCKING TOOL ZERO POS is installed on the slat/flap control lever.
(3) Make sure that you removed the applicable flap tab hinge-fairings (Ref. AMM TASK 57-55-11-000-005).
(4) Make sure that the ACCESS PLATFORM 3M (10 FT) is in position below the applicable flap track 2, 3 or 4 at zone 531 (631), 532 (632) or 533 (633).
Subtask 57-55-11-865-063-A ** ON A/C NOT FOR ALL (1) Make sure that you fully retracted the flaps (Ref. AMM TASK 27-50-00-866-009).
(2) Make sure that the 98D27803500001 LOCKING TOOL ZERO POS is installed on the slat/flap control lever.
(3) Make sure that you removed the applicable flap tab hinge-fairings (Ref. AMM TASK 57-55-11-000-005).
(4) Make sure that the ACCESS PLATFORM 3M (10 FT) is in position below the applicable flap track 2, 3 or 4 at zone 531 (631), 532 (632) or 533 (633).
C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
4. Procedure| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 | 6CV | B07 |
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 | 6CV | B02 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2 | 8CV | Q21 |
Subtask 57-55-11-420-074-A ** ON A/C NOT FOR ALL
A. Preparation for Installation
(1) Carefully remove the remaining sealant from the fairing and the rear fairing with a SCRAPER - NON METALLIC.
(2) Clean the component interface and/or the adjacent area with a Textile-Lint free Cotton - (Material No.14SBA1) , made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(3) Do an inspection of the component interfaces and the adjacent area.
(4) Make sure that the parts retained from the removed component are clean and in the correct condition.
Subtask 57-55-11-420-071-E ** ON A/C NOT FOR ALL (1) Carefully remove the remaining sealant from the fairing and the rear fairing with a SCRAPER - NON METALLIC.
(2) Clean the component interface and/or the adjacent area with a Textile-Lint free Cotton - (Material No.14SBA1) , made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(3) Do an inspection of the component interfaces and the adjacent area.
(4) Make sure that the parts retained from the removed component are clean and in the correct condition.
B. Installation of the Inboard and Outboard-Flap Tab Hinge-Fairings
(1) Install the inboard-flap tab hinge-fairing at the hinge 1A position as follows:
(a) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(b) Hold the front fairing (2) and connect the bonding strap (7) with the bolt (5), the washers (6) and (8) and the nut (9).
(c) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
(d) TORQUE the nut (9) to between 0.8 and 0.7 m.daN (70.80 and 61.95 lbf.in ).
(e) Apply Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) on the threads of the screws (3).
(f) Install the front fairing (2) with the screws (3).
(g) TORQUE the screws (3) to between 0.8 and 0.7 m.daN (70.80 and 61.95 lbf.in ).
(h) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(i) Hold the rear fairing (1) and connect the bonding strap (7) with the bolt (5), the washers (6) and (8) and the nut (9).
(j) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
(k) TORQUE the nut (9) to between 0.8 and 0.7 m.daN (70.80 and 61.95 lbf.in ).
(l) Apply Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) on the threads of the screws (4).
(m) Put the rear fairing (1) in position and loosely install the screws (4) and (10).
(n) Adjust the rear fairing (1) until dimension X is 5 -1 mm or +3 mm (0.1969 -0.039 in. or -0.039 in.).
(o) TORQUE the screws (4) and (10) to between 0.8 and 0.7 m.daN (70.80 and 61.95 lbf.in ).
(p) Apply the new Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) (11) on the screws (10).
(q) Apply a bead of Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) between:
(a) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(b) Hold the front fairing (23) and connect the bonding strap (27) with the bolt (29), the washers (26) and (28) and the nut (25).
(c) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
(d) TORQUE the nut (25) to between 0.45 and 0.35 m.daN (39.82 and 30.97 lbf.in ).
(e) Put the front fairing (23) in position and install the bolts (24) and the screws (31).
(f) TORQUE the screws (31) to between 1.8 and 1.6 m.daN (13.27 and 11.80 lbf.ft ).
(g) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(h) Hold the rear fairing (22) and connect the bonding strap (27) with the bolt (29), the washers (26) and (28) and the nut (25).
(i) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
(j) TORQUE the nut (25) to between 0.45 and 0.35 m.daN (39.82 and 30.97 lbf.in ).
(k) Put the rear fairing (22) in position and install the screws (21) and (32).
(l) Adjust the rear fairing (22) until dimension Y is 5 -1 mm or +3 mm (0.1969 -0.039 in. or -0.039 in.).
(m) TORQUE the screws (32) to between 1.8 and 1.6 m.daN (13.27 and 11.80 lbf.ft ).
(n) TORQUE the screws (21) to between 0.8 and 0.7 m.daN (70.80 and 61.95 lbf.in ).
(o) Apply the new Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) (30) on the screws (21).
(p) Apply a bead of Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) between:
(b) Tighten the screws (55) and (62).
(c) Apply the new Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) (63) on the screws (62).
(d) Put the rear fairing (53) in position and loosely install the screws (52) and (54).
(e) Adjust the rear fairing (53) until dimension Z is 5 -1 mm or +3 mm (0.1969 -0.039 in. or -0.039 in.).
(f) Tighten the screws (52) and (54).
(g) Apply the new Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) (63) on the screws (52).
(h) Apply a bead of Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) between:
Subtask 57-55-11-865-065-A ** ON A/C NOT FOR ALL (1) Install the inboard-flap tab hinge-fairing at the hinge 1A position as follows:
(a) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(b) Hold the front fairing (2) and connect the bonding strap (7) with the bolt (5), the washers (6) and (8) and the nut (9).
(c) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
(d) TORQUE the nut (9) to between 0.8 and 0.7 m.daN (70.80 and 61.95 lbf.in )
. (e) Apply Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) on the threads of the screws (3).
(f) Install the front fairing (2) with the screws (3).
(g) TORQUE the screws (3) to between 0.8 and 0.7 m.daN (70.80 and 61.95 lbf.in )
. (h) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(i) Hold the rear fairing (1) and connect the bonding strap (7) with the bolt (5), the washers (6) and (8) and the nut (9).
(j) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
(k) TORQUE the nut (9) to between 0.8 and 0.7 m.daN (70.80 and 61.95 lbf.in )
. (l) Apply Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) on the threads of the screws (4).
(m) Put the rear fairing (1) in position and loosely install the screws (4) and (10).
(n) Adjust the rear fairing (1) until dimension X is 5 -1 mm or +3 mm (0.1969 -0.039 in. or -0.039 in.).
(o) TORQUE the screws (4) and (10) to between 0.8 and 0.7 m.daN (70.80 and 61.95 lbf.in )
. (p) Apply the new Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) (11) on the screws (10).
(q) Apply a bead of Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) between:
- The flap and the front fairing (2)
- The tab and the rear fairing (1)
- The tab trailing edge and the rear fairing (1).
(a) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(b) Hold the front fairing (23) and connect the bonding strap (27) with the bolt (29), the washers (26) and (28) and the nut (25).
(c) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
(d) TORQUE the nut (25) to between 0.45 and 0.35 m.daN (39.82 and 30.97 lbf.in )
. (e) Put the front fairing (23) in position and install the bolts (24) and the screws (31).
(f) TORQUE the screws (31) to between 1.8 and 1.6 m.daN (13.27 and 11.80 lbf.ft )
.(g) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(h) Hold the rear fairing (22) and connect the bonding strap (27) with the bolt (29), the washers (26) and (28) and the nut (25).
(i) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
(j) TORQUE the nut (25) to between 0.45 and 0.35 m.daN (39.82 and 30.97 lbf.in )
. (k) Put the rear fairing (22) in position and install the screws (21) and (32).
(l) Adjust the rear fairing (22) until dimension Y is 5 -1 mm or +3 mm (0.1969 -0.039 in. or -0.039 in.).
(m) TORQUE the screws (32) to between 1.8 and 1.6 m.daN (13.27 and 11.80 lbf.ft )
.(n) TORQUE the screws (21) to between 0.8 and 0.7 m.daN (70.80 and 61.95 lbf.in )
. (o) Apply the new Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) (30) on the screws (21).
(p) Apply a bead of Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) between:
- The flap and the front fairing (23)
- The tab and the rear fairing (22)
- The tab trailing edge and the rear fairing (22).
NOTE: The installation procedure for the hinge 3A, 3B and 3C fairings is almost the same.
(a) Put the front fairing (61) in position and install the screws (55) and (62). (b) Tighten the screws (55) and (62).
(c) Apply the new Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) (63) on the screws (62).
(d) Put the rear fairing (53) in position and loosely install the screws (52) and (54).
(e) Adjust the rear fairing (53) until dimension Z is 5 -1 mm or +3 mm (0.1969 -0.039 in. or -0.039 in.).
(f) Tighten the screws (52) and (54).
(g) Apply the new Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) (63) on the screws (52).
(h) Apply a bead of Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) between:
- The flap and the front fairing (61)
- The tab and the rear fairing (53)
- The tab trailing edge and the rear fairing (53).
C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 57-55-11-860-056-A ** ON A/C NOT FOR ALL | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 | 6CV | B07 |
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 | 6CV | B02 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2 | 8CV | Q21 |
D. Aircraft Configuration
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the 98D27803500001 LOCKING TOOL ZERO POS from the flap/slat control-lever.
Subtask 57-55-11-710-056-A ** ON A/C NOT FOR ALL (1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the 98D27803500001 LOCKING TOOL ZERO POS from the flap/slat control-lever.
E. Test
(1) Do an operational test of the flap system (Ref. AMM TASK 27-54-00-710-001) to make sure that the hinge fairings operate correctly.
5. Close-up(1) Do an operational test of the flap system (Ref. AMM TASK 27-54-00-710-001) to make sure that the hinge fairings operate correctly.
Subtask 57-55-11-942-058-A ** ON A/C NOT FOR ALL
A. Removal of Equipment
(1) Remove the access platform(s).
(2) Remove the WARNING NOTICE(S).
(3) Remove the safety barriers.
(4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(1) Remove the access platform(s).
(2) Remove the WARNING NOTICE(S).
(3) Remove the safety barriers.
(4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.