DOC AIRBUS | AMM A320FSpecial Detailed Inspection (X-Ray) of Outer Wing, Bottom Skin masked by Pylon Reinforcing Plate
TASK 57-20-00-280-804-A
Special Detailed Inspection (X-Ray) of Outer Wing, Bottom Skin masked by Pylon Reinforcing Plate
Refer to the MPD TASK: 572030-01
SPECIAL DETAILED INSPECTION (X-RAY) OF OUTER WING, BOTTOM SKIN MASKED BY PYLON REINFORCING PLATE.
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Work Zones and Access Panels
D. Referenced Information
3. Job Set-up
Subtask 57-20-00-941-118-A
Subtask 57-20-00-280-063-A
Subtask 57-20-00-410-118-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.02 06:30:38 UTC
Special Detailed Inspection (X-Ray) of Outer Wing, Bottom Skin masked by Pylon Reinforcing Plate
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
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 DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.
1. Reason for the JobRefer to the MPD TASK: 572030-01
SPECIAL DETAILED INSPECTION (X-RAY) OF OUTER WING, BOTTOM SKIN MASKED BY PYLON REINFORCING PLATE.
NOTE: The effectivity of this task is "ALL". To know if this task is applicable to your aircraft, refer to the MPD task applicability.
2. Job Set-up InformationA. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | ACCESS PLATFORM 2M (6 FT) |
| No specific | 1 | FLASHLIGHT |
| No specific | 1 | MIRROR - INSPECTION, FLEXIBLE |
| No specific | AR | SAFETY BARRIER(S) |
| No specific | AR | SAFETY CLIP - CIRCUIT BREAKER |
| No specific | AR | TIE WRAP |
| No specific | AR | WARNING NOTICE(S) |
| 98D27803500001 | 1 | LOCKING TOOL ZERO POS |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.08BAA9) | Non Aqueous Cleaner-General - - |
| (Material No.14SBA1) | Textile-Lint free Cotton - |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 500 | LEFT WING |
| 600 | RIGHT WING |
| 521BZ, 540BB, 540CB, 540DZ, 621BZ, 640BB, 640CB, 640DZ |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 28-16-42-000-001-A | Removal of the Fuel Recirculation Check-valve |
| TASK 28-16-42-400-001-A | Installation of the Fuel Recirculation Check-valve |
| TASK 54-50-00-000-001-A | Removal of the Pylons |
| TASK 54-50-00-000-802-A | Removal of the Pylons |
| TASK 54-50-00-400-001-A | Installation of the Pylons |
| TASK 54-50-00-400-802-A | Installation of the Pylons |
| TASK 57-27-11-000-001-A | Removal of the Access Panel |
| TASK 57-27-11-000-005-A | Removal of the Access Panel |
| TASK 57-27-11-000-007-A | Removal of the Closing Panel |
| TASK 57-27-11-400-001-A | Installation of the Access Panel |
| TASK 57-27-11-400-005-A | Installation of the Access Panel |
| TASK 57-27-11-400-005-B | Installation of the Access Panel |
| TASK 57-27-11-400-005-C | Installation of the Access Panel |
| TASK 57-27-11-400-005-D | Installation of the Access Panel |
| TASK 57-27-11-400-005-E | Installation of the Access Panel |
| TASK 57-27-11-400-007-A | Installation of the Closing Panel |
| TASK 71-00-00-000-042-A | Removal of the Power Plant |
| TASK 71-00-00-000-042-A-01 | Removal of the Power Plant with the Engine Positioner TWW 75E (MIAG) |
| TASK 71-00-00-000-042-A-03 | Removal of the Power Plant with Jacxson Tool |
| TASK 71-00-00-400-042-A | Installation of the Power Plant |
| TASK 71-00-00-400-042-A-01 | Installation of the Power Plant with the Engine Positioner TWW 75E (MIAG) |
| TASK 71-00-00-400-042-A-03 | Installation of the Power Plant with Jacxson Tool |
| TASK 71-00-20-000-040-A | Removal of the Power Plant |
| TASK 71-00-20-000-040-A-01 | Removal of the Power Plant with the Engine Positioner TWW 75E (MIAG) |
| TASK 71-00-20-400-040-A | Installation of the Power Plant |
| TASK 71-00-20-400-040-A-01 | Installation of the Power Plant with the Engine Positioner TWW 75E (MIAG) |
| TASK 71-00-51-000-802-A | Removal of the Power Plant (Bootstrap Method) |
| TASK 71-00-51-000-802-A-01 | Removal of the Power Plant (JacXson Method) |
| TASK 71-00-51-400-802-A | Installation of the Power Plant (Bootstrap Method) |
| TASK 71-00-51-400-802-A-01 | Installation of the Power Plant (JacXson Method) |
| SRM 511100 | |
| SRM 512200 | |
| SRM 514200 | |
| NTM 572030 | |
Pylon Reinforcing Plate - BracketsSubtask 57-20-00-941-118-A
A. Safety Precautions
(1) Install the 98D27803500001 LOCKING TOOL ZERO POS on the flap/slat control lever.
(2) In the cockpit:
Subtask 57-20-00-865-088-A (1) Install the 98D27803500001 LOCKING TOOL ZERO POS on the flap/slat control lever.
(2) In the cockpit:
- Put the WARNING NOTICE(S) in position to tell persons not to operate the flaps or slats.
- Put the WARNING NOTICE(S) in position to tell persons not to start the engines.
- Make sure that the ENG 1 MASTER 1 and ENG 2 MASTER 2 control switches are in the OFF position.
B. Open, safety and tag this(these) circuit breaker(s):
Subtask 57-20-00-010-122-A ** ON A/C NOT FOR ALL | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| FOR FIN: 1000EM1 (ENGINE1) | |||
| 49VU | ENGINE/1/FADEC A/AND EIU 1 | 2KS1 | A04 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | ENGINE/ENG1/FADEC B/AND EIU 1 | 4KS1 | R41 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | ENGINE/ENG1/FADEC B/AND EIU 1 | 4KS1 | R40 |
| ** ON A/C ALL | |||
| FOR FIN: 1000EM2 (ENGINE2) | |||
| 49VU | ENGINE/2/FADEC A/AND EIU 2 | 2KS2 | A05 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | ENGINE/ENG2/FADEC B | 4KS2 | Q40 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | ENGINE/ENG2/FADEC B/AND EIU2 | 4KS2 | Q40 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | ENGINE/ENG2/FADEC B/AND EIU2 | 4KS2 | R41 |
C. Get Access
(1) Put the ACCESS PLATFORM 2M (6 FT) in position at zone 521(621).
(2) Remove the applicable access panels (Ref. AMM TASK 57-27-11-000-001):
(a) For the left wing: 540BB and 540CB
(b) For the right wing: 640BB and 640CB.
(3) Remove the applicable access panel (Ref. AMM TASK 57-27-11-000-005):
(a) For the left wing: 521BZ
(b) For the right wing: 621BZ.
(4) Remove the applicable access panel (Ref. AMM TASK 57-27-11-000-007):
(a) For the left wing: 540DZ
(b) For the right wing: 640DZ.
(5) Remove the engine (Ref. AMM TASK 71-00-20-000-040).
(6) Remove the pylons (Ref. AMM TASK 54-50-00-000-001).
(7) Remove the fuel recirculation check-valve (Ref. AMM TASK 28-16-42-000-001).
(8) If necessary, remove the applicable bracket(s) (22), (34), (36), (47) and/or (64) as follows:
(a) Remove the screw (26) and the clamps (27) and (25) from the bracket (22).
(b) Remove the nuts (23) and the bracket (22).
(c) Remove the screw (67) and the clamps (59) and (51) from the bracket (64).
(d) Remove the nuts (65) and the bracket (64).
(e) Remove the screws (38) and the clamps (25) and (27) from the bracket (36).
(f) Remove the nuts (32), the screws (40) and the washers (41) from the bracket (28).
(g) Remove the clamps (42) from the bracket (28).
(h) Remove the screws (31) and the clamps (30) from the bracket (28).
(i) Remove the screws (43), the washers (44) and the bracket (28).
(j) Cut and discard the tie wraps (39).
(k) Remove the nuts (33), the screws (37), the spacers (35) and the brackets (34) and (36).
(l) Remove the nuts (48).
(m) Remove the screw (55), the washer (54) and the spacer (52) from the bracket (53).
(n) Remove the screw (60), the washer (50) and the clamps (51) and (59).
(o) Cut and discard the tie wraps (56).
(p) Remove the screw (57), the washer (58), the bracket (53), the spacer (61) and the clamps (51) and (59).
(q) If necessary, remove the screws (20), (62) and (45).
(9) If necessary, remove the air dam (9) as follows:
(a) Remove the nuts (10), (12) and (14) and the air dam (9).
(b) If necessary, remove the screws (1), (3), (5) and (7).
(c) Safety the cables (16), (17), (18) and (19) to the aircraft structure.
Subtask 57-20-00-010-122-B ** ON A/C NOT FOR ALL (1) Put the ACCESS PLATFORM 2M (6 FT) in position at zone 521(621).
(2) Remove the applicable access panels (Ref. AMM TASK 57-27-11-000-001):
(a) For the left wing: 540BB and 540CB
(b) For the right wing: 640BB and 640CB.
(3) Remove the applicable access panel (Ref. AMM TASK 57-27-11-000-005):
(a) For the left wing: 521BZ
(b) For the right wing: 621BZ.
(4) Remove the applicable access panel (Ref. AMM TASK 57-27-11-000-007):
(a) For the left wing: 540DZ
(b) For the right wing: 640DZ.
(5) Remove the engine (Ref. AMM TASK 71-00-20-000-040).
(6) Remove the pylons (Ref. AMM TASK 54-50-00-000-001).
(7) Remove the fuel recirculation check-valve (Ref. AMM TASK 28-16-42-000-001).
(8) If necessary, remove the applicable bracket(s) (22), (34), (36), (47) and/or (64) as follows:
(a) Remove the screw (26) and the clamps (27) and (25) from the bracket (22).
(b) Remove the nuts (23) and the bracket (22).
(c) Remove the screw (67) and the clamps (59) and (51) from the bracket (64).
(d) Remove the nuts (65) and the bracket (64).
(e) Remove the screws (38) and the clamps (25) and (27) from the bracket (36).
(f) Remove the nuts (32), the screws (40) and the washers (41) from the bracket (28).
(g) Remove the clamps (42) from the bracket (28).
(h) Remove the screws (31) and the clamps (30) from the bracket (28).
(i) Remove the screws (43), the washers (44) and the bracket (28).
(j) Cut and discard the tie wraps (39).
(k) Remove the nuts (33), the screws (37), the spacers (35) and the brackets (34) and (36).
(l) Remove the nuts (48).
(m) Remove the screw (55), the washer (54) and the spacer (52) from the bracket (53).
(n) Remove the screw (60), the washer (50) and the clamps (51) and (59).
(o) Cut and discard the tie wraps (56).
(p) Remove the screw (57), the washer (58), the bracket (53), the spacer (61) and the clamps (51) and (59).
(q) If necessary, remove the screws (20), (62) and (45).
(9) If necessary, remove the air dam (9) as follows:
(a) Remove the nuts (10), (12) and (14) and the air dam (9).
(b) If necessary, remove the screws (1), (3), (5) and (7).
(c) Safety the cables (16), (17), (18) and (19) to the aircraft structure.
C. Get Access
(1) Put the ACCESS PLATFORM 2M (6 FT) in position at zone 521(621).
(2) Remove the applicable access panels (Ref. AMM TASK 57-27-11-000-001):
(a) For the left wing: 540BB and 540CB
(b) For the right wing: 640BB and 640CB.
(3) Remove the applicable access panel (Ref. AMM TASK 57-27-11-000-005):
(a) For the left wing: 521BZ
(b) For the right wing: 621BZ.
(4) Remove the applicable access panel (Ref. AMM TASK 57-27-11-000-007):
(a) For the left wing: 540DZ
(b) For the right wing: 640DZ.
(5) Remove the engine (Ref. AMM TASK 71-00-51-000-802).
(6) Remove the pylons (Ref. AMM TASK 54-50-00-000-802).
(7) Remove the fuel recirculation check-valve (Ref. AMM TASK 28-16-42-000-001).
(8) If necessary, remove the applicable bracket(s) (22), (34), (36), (47) and/or (64) as follows:
(a) Remove the screw (26) and the clamps (27) and (25) from the bracket (22).
(b) Remove the nuts (23) and the bracket (22).
(c) Remove the screw (67) and the clamps (59) and (51) from the bracket (64).
(d) Remove the nuts (65) and the bracket (64).
(e) Remove the screws (38) and the clamps (25) and (27) from the bracket (36).
(f) Remove the nuts (32), the screws (40) and the washers (41) from the bracket (28).
(g) Remove the clamps (42) from the bracket (28).
(h) Remove the screws (31) and the clamps (30) from the bracket (28).
(i) Remove the screws (43), the washers (44) and the bracket (28).
(j) Cut and discard the tie wraps (39).
(k) Remove the nuts (33), the screws (37), the spacers (35) and the brackets (34) and (36).
(l) Remove the nuts (48).
(m) Remove the screw (55), the washer (54) and the spacer (52) from the bracket (53).
(n) Remove the screw (60), the washer (50) and the clamps (51) and (59).
(o) Cut and discard the tie wraps (56).
(p) Remove the screw (57), the washer (58), the bracket (53), the spacer (61) and the clamps (51) and (59).
(q) If necessary, remove the screws (20), (62) and (45).
(9) If necessary, remove the air dam (9) as follows:
(a) Remove the nuts (10), (12) and (14) and the air dam (9).
(b) If necessary, remove the screws (1), (3), (5) and (7).
(c) Safety the cables (16), (17), (18) and (19) to the aircraft structure.
Subtask 57-20-00-010-122-D ** ON A/C NOT FOR ALL (1) Put the ACCESS PLATFORM 2M (6 FT) in position at zone 521(621).
(2) Remove the applicable access panels (Ref. AMM TASK 57-27-11-000-001):
(a) For the left wing: 540BB and 540CB
(b) For the right wing: 640BB and 640CB.
(3) Remove the applicable access panel (Ref. AMM TASK 57-27-11-000-005):
(a) For the left wing: 521BZ
(b) For the right wing: 621BZ.
(4) Remove the applicable access panel (Ref. AMM TASK 57-27-11-000-007):
(a) For the left wing: 540DZ
(b) For the right wing: 640DZ.
(5) Remove the engine (Ref. AMM TASK 71-00-51-000-802).
(6) Remove the pylons (Ref. AMM TASK 54-50-00-000-802).
(7) Remove the fuel recirculation check-valve (Ref. AMM TASK 28-16-42-000-001).
(8) If necessary, remove the applicable bracket(s) (22), (34), (36), (47) and/or (64) as follows:
(a) Remove the screw (26) and the clamps (27) and (25) from the bracket (22).
(b) Remove the nuts (23) and the bracket (22).
(c) Remove the screw (67) and the clamps (59) and (51) from the bracket (64).
(d) Remove the nuts (65) and the bracket (64).
(e) Remove the screws (38) and the clamps (25) and (27) from the bracket (36).
(f) Remove the nuts (32), the screws (40) and the washers (41) from the bracket (28).
(g) Remove the clamps (42) from the bracket (28).
(h) Remove the screws (31) and the clamps (30) from the bracket (28).
(i) Remove the screws (43), the washers (44) and the bracket (28).
(j) Cut and discard the tie wraps (39).
(k) Remove the nuts (33), the screws (37), the spacers (35) and the brackets (34) and (36).
(l) Remove the nuts (48).
(m) Remove the screw (55), the washer (54) and the spacer (52) from the bracket (53).
(n) Remove the screw (60), the washer (50) and the clamps (51) and (59).
(o) Cut and discard the tie wraps (56).
(p) Remove the screw (57), the washer (58), the bracket (53), the spacer (61) and the clamps (51) and (59).
(q) If necessary, remove the screws (20), (62) and (45).
(9) If necessary, remove the air dam (9) as follows:
(a) Remove the nuts (10), (12) and (14) and the air dam (9).
(b) If necessary, remove the screws (1), (3), (5) and (7).
(c) Safety the cables (16), (17), (18) and (19) to the aircraft structure.
C. Get Access
(1) Put the ACCESS PLATFORM 2M (6 FT) in position at zone 521(621).
(2) Remove the applicable access panels (Ref. AMM TASK 57-27-11-000-001):
(a) For the left wing: 540BB and 540CB
(b) For the right wing: 640BB and 640CB.
(3) Remove the applicable access panel (Ref. AMM TASK 57-27-11-000-005):
(a) For the left wing: 521BZ
(b) For the right wing: 621BZ.
(4) Remove the applicable access panel (Ref. AMM TASK 57-27-11-000-007):
(a) For the left wing: 540DZ
(b) For the right wing: 640DZ.
(5) Remove the engine (Ref. AMM TASK 71-00-00-000-042).
(6) Remove the pylons (Ref. AMM TASK 54-50-00-000-001).
(7) Remove the fuel recirculation check-valve (Ref. AMM TASK 28-16-42-000-001).
(8) If necessary, remove the applicable bracket(s) (22), (34), (36), (47) and/or (64) as follows:
(a) Remove the screw (26) and the clamps (27) and (25) from the bracket (22).
(b) Remove the nuts (23) and the bracket (22).
(c) Remove the screw (67) and the clamps (59) and (51) from the bracket (64).
(d) Remove the nuts (65) and the bracket (64).
(e) Remove the screws (38) and the clamps (25) and (27) from the bracket (36).
(f) Remove the nuts (32), the screws (40) and the washers (41) from the bracket (28).
(g) Remove the clamps (42) from the bracket (28).
(h) Remove the screws (31) and the clamps (30) from the bracket (28).
(i) Remove the screws (43), the washers (44) and the bracket (28).
(j) Cut and discard the tie wraps (39).
(k) Remove the nuts (33), the screws (37), the spacers (35) and the brackets (34) and (36).
(l) Remove the nuts (48).
(m) Remove the screw (55), the washer (54) and the spacer (52) from the bracket (53).
(n) Remove the screw (60), the washer (50) and the clamps (51) and (59).
(o) Cut and discard the tie wraps (56).
(p) Remove the screw (57), the washer (58), the bracket (53), the spacer (61) and the clamps (51) and (59).
(q) If necessary, remove the screws (20), (62) and (45).
(9) If necessary, remove the air dam (9) as follows:
(a) Remove the nuts (10), (12) and (14) and the air dam (9).
(b) If necessary, remove the screws (1), (3), (5) and (7).
(c) Safety the cables (16), (17), (18) and (19) to the aircraft structure.
Subtask 57-20-00-110-110-A (1) Put the ACCESS PLATFORM 2M (6 FT) in position at zone 521(621).
(2) Remove the applicable access panels (Ref. AMM TASK 57-27-11-000-001):
(a) For the left wing: 540BB and 540CB
(b) For the right wing: 640BB and 640CB.
(3) Remove the applicable access panel (Ref. AMM TASK 57-27-11-000-005):
(a) For the left wing: 521BZ
(b) For the right wing: 621BZ.
(4) Remove the applicable access panel (Ref. AMM TASK 57-27-11-000-007):
(a) For the left wing: 540DZ
(b) For the right wing: 640DZ.
(5) Remove the engine (Ref. AMM TASK 71-00-00-000-042).
(6) Remove the pylons (Ref. AMM TASK 54-50-00-000-001).
(7) Remove the fuel recirculation check-valve (Ref. AMM TASK 28-16-42-000-001).
(8) If necessary, remove the applicable bracket(s) (22), (34), (36), (47) and/or (64) as follows:
(a) Remove the screw (26) and the clamps (27) and (25) from the bracket (22).
(b) Remove the nuts (23) and the bracket (22).
(c) Remove the screw (67) and the clamps (59) and (51) from the bracket (64).
(d) Remove the nuts (65) and the bracket (64).
(e) Remove the screws (38) and the clamps (25) and (27) from the bracket (36).
(f) Remove the nuts (32), the screws (40) and the washers (41) from the bracket (28).
(g) Remove the clamps (42) from the bracket (28).
(h) Remove the screws (31) and the clamps (30) from the bracket (28).
(i) Remove the screws (43), the washers (44) and the bracket (28).
(j) Cut and discard the tie wraps (39).
(k) Remove the nuts (33), the screws (37), the spacers (35) and the brackets (34) and (36).
(l) Remove the nuts (48).
(m) Remove the screw (55), the washer (54) and the spacer (52) from the bracket (53).
(n) Remove the screw (60), the washer (50) and the clamps (51) and (59).
(o) Cut and discard the tie wraps (56).
(p) Remove the screw (57), the washer (58), the bracket (53), the spacer (61) and the clamps (51) and (59).
(q) If necessary, remove the screws (20), (62) and (45).
(9) If necessary, remove the air dam (9) as follows:
(a) Remove the nuts (10), (12) and (14) and the air dam (9).
(b) If necessary, remove the screws (1), (3), (5) and (7).
(c) Safety the cables (16), (17), (18) and (19) to the aircraft structure.
D. Preparation of the Inspection Area
(1) Make sure that the inspection area is sufficiently clean to do a satisfactory inspection of the area.
(2) If not, clean the inspection area with Non Aqueous Cleaner-General - - (Material No.08BAA9) and the Textile-Lint free Cotton - (Material No.14SBA1) .
4. Procedure(1) Make sure that the inspection area is sufficiently clean to do a satisfactory inspection of the area.
(2) If not, clean the inspection area with Non Aqueous Cleaner-General - - (Material No.08BAA9) and the Textile-Lint free Cotton - (Material No.14SBA1) .
Subtask 57-20-00-280-063-A
A. Inspection
(1) If necessary, use the FLASHLIGHT and the MIRROR - INSPECTION, FLEXIBLE to do this inspection.
(2) Do a special detailed inspection (X-Ray) of the outer-wing bottom skin that the pylon reinforcing plate masks. Do this inspection for damage or discontinuities NTM 572030.
(3) Make a report of the damage after the NTM inspection:
(a) Corrosion damage:
If you find corrosion, refer to the Structural Repair Manual SRM 512200 for the corrosion types, inspection, removal and subsequent corrosion protection.
(b) Other damage (scratches, cracks, gouges, dents, creases):
If you find this type of damage, refer to the Structural Repair Manual SRM 511100 for damage types, classification and corrective action.
(c) If the damage is not included in the list in step (2), you must contact AIRBUS to get the applicable repair procedure.
5. Close-up(1) If necessary, use the FLASHLIGHT and the MIRROR - INSPECTION, FLEXIBLE to do this inspection.
(2) Do a special detailed inspection (X-Ray) of the outer-wing bottom skin that the pylon reinforcing plate masks. Do this inspection for damage or discontinuities NTM 572030.
(3) Make a report of the damage after the NTM inspection:
(a) Corrosion damage:
If you find corrosion, refer to the Structural Repair Manual SRM 512200 for the corrosion types, inspection, removal and subsequent corrosion protection.
(b) Other damage (scratches, cracks, gouges, dents, creases):
If you find this type of damage, refer to the Structural Repair Manual SRM 511100 for damage types, classification and corrective action.
(c) If the damage is not included in the list in step (2), you must contact AIRBUS to get the applicable repair procedure.
Subtask 57-20-00-410-118-A ** ON A/C NOT FOR ALL
A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) If removed, install the air dam (9) as follows:
(a) If you removed the screws (1), (3), (5) and (7), do the steps that follow:
1 Discard the screws (1), (3), (5) and (7) and the nuts (10), (12) and (14).
2 Do a special detailed inspection (ROTO) of the holes.
3 If you find signs of damage, contact Airbus.
4 Perform the first oversizing.
5 Deburr all the holes once drilled.
6 Release the cables (16), (17), (18) and (19) from the aircraft structure.
7 Put the air dam (9) in position and install the new screws (2), (4), (6) and (8) and the new nuts (11), (13) and (15), refer to SRM 514200.
8 Refer to the installation drawing in the SRM identification section for the new fastener references.
9 Tighten the nuts (11), (13) and (15).
(b) If you did not remove the screws (1), (3), (5) and (7), do the steps that follow:
1 Release the cables (16), (17), (18) and (19) from the aircraft structure.
2 Put the air dam (9) in position and install the nuts (10), (12) and (14).
3 Tighten the nuts (10), (12) and (14).
(3) If removed, install the applicable bracket(s) (22), (34), (36), (47) and/or (64) as follows:
(a) If you removed the screws (20), (62) and (45), do the steps that follow:
1 Discard the screws (20), (62) and (45) and the nuts (23), (48) and (65).
2 Do a special detailed inspection (ROTO) of the holes.
3 If you find signs of damage, contact Airbus.
4 Perform the first oversizing.
5 Deburr all the holes once drilled.
6 Put the bracket (22) in position and install the new screws (21) and the new nuts (24), refer to SRM 514200.
7 Refer to the installation drawing in the SRM identification section for the new fastener references.
8 Tighten the new nuts (24).
9 Put the clamps (25) and (27) in position on the bracket (22) and install the screw (26).
10 Tighten the screw (26).
11 Put the bracket (64) in position and install the new screws (63) and the new nuts (66), refer to SRM 514200.
12 Refer to the installation drawing in the SRM identification section for the new fastener references.
13 Tighten the new nuts (66).
14 Put the clamps (51) and (59) in position on the bracket (64) and install the screw (67).
15 Tighten the screw (67).
16 Put the brackets (34) and (36) in position and install the spacers (35), the screws (37) and the nuts (33).
17 Tighten the nuts (33).
18 Put the bracket (28) in position and install the washers (44) and the screws (43).
19 Tighten the screws (43).
20 Install the new TIE WRAP (39).
21 Put the clamps (30) in position on the bracket (28) and install the screws (31).
22 Tighten the screws (31).
23 Install the clamps (42) on the bracket (28).
24 Install the washers (41), the screws (40) and the nuts (32) on the bracket (34).
25 Put the clamps (25) and (27) in position on the bracket (36) and install the screws (38).
26 Tighten the screws (38).
27 Put the bracket (47) in position and install the new screws (46) and the new nuts (49), refer to SRM 514200.
28 Refer to the installation drawing in the SRM identification section for the new fastener references.
29 Tighten the new nuts (49).
30 Install the spacer (52), the bracket (53), and washer (54) and the screw (55).
31 Tighten the screw (55).
32 Put the clamps (51) and (59) in position on the bracket (47) and install the washer (50) and the screw (60).
33 Tighten the screw (60).
34 Put the clamps (51) and (59) in position on the aircraft structure and install the spacer (61), the bracket (53), the washer (58) and the screw (57).
35 Tighten the screw (57).
36 Install the new TIE WRAP (56).
(b) If you did not remove the screws (20), (62) and (45), do the steps that follow:
1 Put the bracket (22) in position and install the screws (20) and the nuts (23).
2 Tighten the nuts (23).
3 Put the clamps (25) and (27) in position on the bracket (22) and install the screw (26).
4 Tighten the screw (26).
5 Put the bracket (64) in position and install the screws (62) and the nuts (65).
6 Tighten the nuts (65).
7 Put the clamps (51) and (59) in position on the bracket (64) and install the screw (67).
8 Tighten the screw (67).
9 Put the brackets (34) and (36) in position and install the spacers (35), the screws (37) and the nuts (33).
10 Tighten the nuts (33).
11 Put the bracket (28) in position and install the washers (44) and the screws (43).
12 Tighten the screws (43).
13 Install the new TIE WRAP (39).
14 Put the clamps (30) in position on the bracket (28) and install the screws (31).
15 Tighten the screws (31).
16 Install the clamps (42) on the bracket (28).
17 Install the washers (41), the screws (40) and the nuts (32) on the bracket (34).
18 Put the clamps (25) and (27) in position on the bracket (36) and install the screws (38).
19 Tighten the screws (38).
20 Put the bracket (47) in position and install the screws (45) and the nuts (48).
21 Tighten the nuts (48).
22 Install the spacer (52), the bracket (53), and washer (54) and the screw (55).
23 Tighten the screw (55).
24 Put the clamps (51) and (59) in position on the bracket (47) and install the washer (50) and the screw (60).
25 Tighten the screw (60).
26 Put the clamps (51) and (59) in position on the aircraft structure and install the spacer (61), the bracket (53), the washer (58) and the screw (57).
27 Tighten the screw (57).
28 Install the new TIE WRAP (56).
(4) Install the fuel recirculation check-valve (Ref. AMM TASK 28-16-42-400-001).
(5) Install the pylons (Ref. AMM TASK 54-50-00-400-001).
(6) Install the engine (Ref. AMM TASK 71-00-20-400-040).
(7) Install the applicable access panel (Ref. AMM TASK 57-27-11-400-007):
(a) For the left wing: 540DZ
(b) For the right wing: 640DZ.
(8) Install the applicable access panel (Ref. AMM TASK 57-27-11-400-005):
(a) For the left wing: 521BZ
(b) For the right wing: 621BZ.
(9) Install the applicable access panels (Ref. AMM TASK 57-27-11-400-001):
(a) For the left wing: 540BB and 540CB
(b) For the right wing: 640BB and 640CB.
(10) Remove the access platform(s).
Subtask 57-20-00-410-118-B ** ON A/C NOT FOR ALL (1) Make sure that the work area is clean and clear of tools and other items.
(2) If removed, install the air dam (9) as follows:
(a) If you removed the screws (1), (3), (5) and (7), do the steps that follow:
1 Discard the screws (1), (3), (5) and (7) and the nuts (10), (12) and (14).
2 Do a special detailed inspection (ROTO) of the holes.
3 If you find signs of damage, contact Airbus.
4 Perform the first oversizing.
5 Deburr all the holes once drilled.
6 Release the cables (16), (17), (18) and (19) from the aircraft structure.
7 Put the air dam (9) in position and install the new screws (2), (4), (6) and (8) and the new nuts (11), (13) and (15), refer to SRM 514200.
8 Refer to the installation drawing in the SRM identification section for the new fastener references.
9 Tighten the nuts (11), (13) and (15).
(b) If you did not remove the screws (1), (3), (5) and (7), do the steps that follow:
1 Release the cables (16), (17), (18) and (19) from the aircraft structure.
2 Put the air dam (9) in position and install the nuts (10), (12) and (14).
3 Tighten the nuts (10), (12) and (14).
(3) If removed, install the applicable bracket(s) (22), (34), (36), (47) and/or (64) as follows:
(a) If you removed the screws (20), (62) and (45), do the steps that follow:
1 Discard the screws (20), (62) and (45) and the nuts (23), (48) and (65).
2 Do a special detailed inspection (ROTO) of the holes.
3 If you find signs of damage, contact Airbus.
4 Perform the first oversizing.
5 Deburr all the holes once drilled.
6 Put the bracket (22) in position and install the new screws (21) and the new nuts (24), refer to SRM 514200.
7 Refer to the installation drawing in the SRM identification section for the new fastener references.
8 Tighten the new nuts (24).
9 Put the clamps (25) and (27) in position on the bracket (22) and install the screw (26).
10 Tighten the screw (26).
11 Put the bracket (64) in position and install the new screws (63) and the new nuts (66), refer to SRM 514200.
12 Refer to the installation drawing in the SRM identification section for the new fastener references.
13 Tighten the new nuts (66).
14 Put the clamps (51) and (59) in position on the bracket (64) and install the screw (67).
15 Tighten the screw (67).
16 Put the brackets (34) and (36) in position and install the spacers (35), the screws (37) and the nuts (33).
17 Tighten the nuts (33).
18 Put the bracket (28) in position and install the washers (44) and the screws (43).
19 Tighten the screws (43).
20 Install the new TIE WRAP (39).
21 Put the clamps (30) in position on the bracket (28) and install the screws (31).
22 Tighten the screws (31).
23 Install the clamps (42) on the bracket (28).
24 Install the washers (41), the screws (40) and the nuts (32) on the bracket (34).
25 Put the clamps (25) and (27) in position on the bracket (36) and install the screws (38).
26 Tighten the screws (38).
27 Put the bracket (47) in position and install the new screws (46) and the new nuts (49), refer to SRM 514200.
28 Refer to the installation drawing in the SRM identification section for the new fastener references.
29 Tighten the new nuts (49).
30 Install the spacer (52), the bracket (53), and washer (54) and the screw (55).
31 Tighten the screw (55).
32 Put the clamps (51) and (59) in position on the bracket (47) and install the washer (50) and the screw (60).
33 Tighten the screw (60).
34 Put the clamps (51) and (59) in position on the aircraft structure and install the spacer (61), the bracket (53), the washer (58) and the screw (57).
35 Tighten the screw (57).
36 Install the new TIE WRAP (56).
(b) If you did not remove the screws (20), (62) and (45), do the steps that follow:
1 Put the bracket (22) in position and install the screws (20) and the nuts (23).
2 Tighten the nuts (23).
3 Put the clamps (25) and (27) in position on the bracket (22) and install the screw (26).
4 Tighten the screw (26).
5 Put the bracket (64) in position and install the screws (62) and the nuts (65).
6 Tighten the nuts (65).
7 Put the clamps (51) and (59) in position on the bracket (64) and install the screw (67).
8 Tighten the screw (67).
9 Put the brackets (34) and (36) in position and install the spacers (35), the screws (37) and the nuts (33).
10 Tighten the nuts (33).
11 Put the bracket (28) in position and install the washers (44) and the screws (43).
12 Tighten the screws (43).
13 Install the new TIE WRAP (39).
14 Put the clamps (30) in position on the bracket (28) and install the screws (31).
15 Tighten the screws (31).
16 Install the clamps (42) on the bracket (28).
17 Install the washers (41), the screws (40) and the nuts (32) on the bracket (34).
18 Put the clamps (25) and (27) in position on the bracket (36) and install the screws (38).
19 Tighten the screws (38).
20 Put the bracket (47) in position and install the screws (45) and the nuts (48).
21 Tighten the nuts (48).
22 Install the spacer (52), the bracket (53), and washer (54) and the screw (55).
23 Tighten the screw (55).
24 Put the clamps (51) and (59) in position on the bracket (47) and install the washer (50) and the screw (60).
25 Tighten the screw (60).
26 Put the clamps (51) and (59) in position on the aircraft structure and install the spacer (61), the bracket (53), the washer (58) and the screw (57).
27 Tighten the screw (57).
28 Install the new TIE WRAP (56).
(4) Install the fuel recirculation check-valve (Ref. AMM TASK 28-16-42-400-001).
(5) Install the pylons (Ref. AMM TASK 54-50-00-400-001).
(6) Install the engine (Ref. AMM TASK 71-00-20-400-040).
(7) Install the applicable access panel (Ref. AMM TASK 57-27-11-400-007):
(a) For the left wing: 540DZ
(b) For the right wing: 640DZ.
(8) Install the applicable access panel (Ref. AMM TASK 57-27-11-400-005):
(a) For the left wing: 521BZ
(b) For the right wing: 621BZ.
(9) Install the applicable access panels (Ref. AMM TASK 57-27-11-400-001):
(a) For the left wing: 540BB and 540CB
(b) For the right wing: 640BB and 640CB.
(10) Remove the access platform(s).
A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) If removed, install the air dam (9) as follows:
(a) If you removed the screws (1), (3), (5) and (7), do the steps that follow:
1 Discard the screws (1), (3), (5) and (7) and the nuts (10), (12) and (14).
2 Do a special detailed inspection (ROTO) of the holes.
3 If you find signs of damage, contact Airbus.
4 Perform the first oversizing.
5 Deburr all the holes once drilled.
6 Release the cables (16), (17), (18) and (19) from the aircraft structure.
7 Put the air dam (9) in position and install the new screws (2), (4), (6) and (8) and the new nuts (11), (13) and (15), refer to SRM 514200.
8 Refer to the installation drawing in the SRM identification section for the new fastener references.
9 Tighten the nuts (11), (13) and (15).
(b) If you did not remove the screws (1), (3), (5) and (7), do the steps that follow:
1 Release the cables (16), (17), (18) and (19) from the aircraft structure.
2 Put the air dam (9) in position and install the nuts (10), (12) and (14).
3 Tighten the nuts (10), (12) and (14).
(3) If removed, install the applicable bracket(s) (22), (34), (36), (47) and/or (64) as follows:
(a) If you removed the screws (20), (62) and (45), do the steps that follow:
1 Discard the screws (20), (62) and (45) and the nuts (23), (48) and (65).
2 Do a special detailed inspection (ROTO) of the holes.
3 If you find signs of damage, contact Airbus.
4 Perform the first oversizing.
5 Deburr all the holes once drilled.
6 Put the bracket (22) in position and install the new screws (21) and the new nuts (24), refer to SRM 514200.
7 Refer to the installation drawing in the SRM identification section for the new fastener references.
8 Tighten the new nuts (24).
9 Put the clamps (25) and (27) in position on the bracket (22) and install the screw (26).
10 Tighten the screw (26).
11 Put the bracket (64) in position and install the new screws (63) and the new nuts (66), refer to SRM 514200.
12 Refer to the installation drawing in the SRM identification section for the new fastener references.
13 Tighten the new nuts (66).
14 Put the clamps (51) and (59) in position on the bracket (64) and install the screw (67).
15 Tighten the screw (67).
16 Put the brackets (34) and (36) in position and install the spacers (35), the screws (37) and the nuts (33).
17 Tighten the nuts (33).
18 Put the bracket (28) in position and install the washers (44) and the screws (43).
19 Tighten the screws (43).
20 Install the new TIE WRAP (39).
21 Put the clamps (30) in position on the bracket (28) and install the screws (31).
22 Tighten the screws (31).
23 Install the clamps (42) on the bracket (28).
24 Install the washers (41), the screws (40) and the nuts (32) on the bracket (34).
25 Put the clamps (25) and (27) in position on the bracket (36) and install the screws (38).
26 Tighten the screws (38).
27 Put the bracket (47) in position and install the new screws (46) and the new nuts (49), refer to SRM 514200.
28 Refer to the installation drawing in the SRM identification section for the new fastener references.
29 Tighten the new nuts (49).
30 Install the spacer (52), the bracket (53), and washer (54) and the screw (55).
31 Tighten the screw (55).
32 Put the clamps (51) and (59) in position on the bracket (47) and install the washer (50) and the screw (60).
33 Tighten the screw (60).
34 Put the clamps (51) and (59) in position on the aircraft structure and install the spacer (61), the bracket (53), the washer (58) and the screw (57).
35 Tighten the screw (57).
36 Install the new TIE WRAP (56).
(b) If you did not remove the screws (20), (62) and (45), do the steps that follow:
1 Put the bracket (22) in position and install the screws (20) and the nuts (23).
2 Tighten the nuts (23).
3 Put the clamps (25) and (27) in position on the bracket (22) and install the screw (26).
4 Tighten the screw (26).
5 Put the bracket (64) in position and install the screws (62) and the nuts (65).
6 Tighten the nuts (65).
7 Put the clamps (51) and (59) in position on the bracket (64) and install the screw (67).
8 Tighten the screw (67).
9 Put the brackets (34) and (36) in position and install the spacers (35), the screws (37) and the nuts (33).
10 Tighten the nuts (33).
11 Put the bracket (28) in position and install the washers (44) and the screws (43).
12 Tighten the screws (43).
13 Install the new TIE WRAP (39).
14 Put the clamps (30) in position on the bracket (28) and install the screws (31).
15 Tighten the screws (31).
16 Install the clamps (42) on the bracket (28).
17 Install the washers (41), the screws (40) and the nuts (32) on the bracket (34).
18 Put the clamps (25) and (27) in position on the bracket (36) and install the screws (38).
19 Tighten the screws (38).
20 Put the bracket (47) in position and install the screws (45) and the nuts (48).
21 Tighten the nuts (48).
22 Install the spacer (52), the bracket (53), and washer (54) and the screw (55).
23 Tighten the screw (55).
24 Put the clamps (51) and (59) in position on the bracket (47) and install the washer (50) and the screw (60).
25 Tighten the screw (60).
26 Put the clamps (51) and (59) in position on the aircraft structure and install the spacer (61), the bracket (53), the washer (58) and the screw (57).
27 Tighten the screw (57).
28 Install the new TIE WRAP (56).
(4) Install the fuel recirculation check-valve (Ref. AMM TASK 28-16-42-400-001).
(5) Install the pylons (Ref. AMM TASK 54-50-00-400-802).
(6) Install the engine (Ref. AMM TASK 71-00-51-400-802).
(7) Install the applicable access panel (Ref. AMM TASK 57-27-11-400-007):
(a) For the left wing: 540DZ
(b) For the right wing: 640DZ.
(8) Install the applicable access panel (Ref. AMM TASK 57-27-11-400-005):
(a) For the left wing: 521BZ
(b) For the right wing: 621BZ.
(9) Install the applicable access panels (Ref. AMM TASK 57-27-11-400-001):
(a) For the left wing: 540BB and 540CB
(b) For the right wing: 640BB and 640CB.
(10) Remove the access platform(s).
Subtask 57-20-00-410-118-D ** ON A/C NOT FOR ALL (1) Make sure that the work area is clean and clear of tools and other items.
(2) If removed, install the air dam (9) as follows:
(a) If you removed the screws (1), (3), (5) and (7), do the steps that follow:
1 Discard the screws (1), (3), (5) and (7) and the nuts (10), (12) and (14).
2 Do a special detailed inspection (ROTO) of the holes.
3 If you find signs of damage, contact Airbus.
4 Perform the first oversizing.
5 Deburr all the holes once drilled.
6 Release the cables (16), (17), (18) and (19) from the aircraft structure.
7 Put the air dam (9) in position and install the new screws (2), (4), (6) and (8) and the new nuts (11), (13) and (15), refer to SRM 514200.
8 Refer to the installation drawing in the SRM identification section for the new fastener references.
9 Tighten the nuts (11), (13) and (15).
(b) If you did not remove the screws (1), (3), (5) and (7), do the steps that follow:
1 Release the cables (16), (17), (18) and (19) from the aircraft structure.
2 Put the air dam (9) in position and install the nuts (10), (12) and (14).
3 Tighten the nuts (10), (12) and (14).
(3) If removed, install the applicable bracket(s) (22), (34), (36), (47) and/or (64) as follows:
(a) If you removed the screws (20), (62) and (45), do the steps that follow:
1 Discard the screws (20), (62) and (45) and the nuts (23), (48) and (65).
2 Do a special detailed inspection (ROTO) of the holes.
3 If you find signs of damage, contact Airbus.
4 Perform the first oversizing.
5 Deburr all the holes once drilled.
6 Put the bracket (22) in position and install the new screws (21) and the new nuts (24), refer to SRM 514200.
7 Refer to the installation drawing in the SRM identification section for the new fastener references.
8 Tighten the new nuts (24).
9 Put the clamps (25) and (27) in position on the bracket (22) and install the screw (26).
10 Tighten the screw (26).
11 Put the bracket (64) in position and install the new screws (63) and the new nuts (66), refer to SRM 514200.
12 Refer to the installation drawing in the SRM identification section for the new fastener references.
13 Tighten the new nuts (66).
14 Put the clamps (51) and (59) in position on the bracket (64) and install the screw (67).
15 Tighten the screw (67).
16 Put the brackets (34) and (36) in position and install the spacers (35), the screws (37) and the nuts (33).
17 Tighten the nuts (33).
18 Put the bracket (28) in position and install the washers (44) and the screws (43).
19 Tighten the screws (43).
20 Install the new TIE WRAP (39).
21 Put the clamps (30) in position on the bracket (28) and install the screws (31).
22 Tighten the screws (31).
23 Install the clamps (42) on the bracket (28).
24 Install the washers (41), the screws (40) and the nuts (32) on the bracket (34).
25 Put the clamps (25) and (27) in position on the bracket (36) and install the screws (38).
26 Tighten the screws (38).
27 Put the bracket (47) in position and install the new screws (46) and the new nuts (49), refer to SRM 514200.
28 Refer to the installation drawing in the SRM identification section for the new fastener references.
29 Tighten the new nuts (49).
30 Install the spacer (52), the bracket (53), and washer (54) and the screw (55).
31 Tighten the screw (55).
32 Put the clamps (51) and (59) in position on the bracket (47) and install the washer (50) and the screw (60).
33 Tighten the screw (60).
34 Put the clamps (51) and (59) in position on the aircraft structure and install the spacer (61), the bracket (53), the washer (58) and the screw (57).
35 Tighten the screw (57).
36 Install the new TIE WRAP (56).
(b) If you did not remove the screws (20), (62) and (45), do the steps that follow:
1 Put the bracket (22) in position and install the screws (20) and the nuts (23).
2 Tighten the nuts (23).
3 Put the clamps (25) and (27) in position on the bracket (22) and install the screw (26).
4 Tighten the screw (26).
5 Put the bracket (64) in position and install the screws (62) and the nuts (65).
6 Tighten the nuts (65).
7 Put the clamps (51) and (59) in position on the bracket (64) and install the screw (67).
8 Tighten the screw (67).
9 Put the brackets (34) and (36) in position and install the spacers (35), the screws (37) and the nuts (33).
10 Tighten the nuts (33).
11 Put the bracket (28) in position and install the washers (44) and the screws (43).
12 Tighten the screws (43).
13 Install the new TIE WRAP (39).
14 Put the clamps (30) in position on the bracket (28) and install the screws (31).
15 Tighten the screws (31).
16 Install the clamps (42) on the bracket (28).
17 Install the washers (41), the screws (40) and the nuts (32) on the bracket (34).
18 Put the clamps (25) and (27) in position on the bracket (36) and install the screws (38).
19 Tighten the screws (38).
20 Put the bracket (47) in position and install the screws (45) and the nuts (48).
21 Tighten the nuts (48).
22 Install the spacer (52), the bracket (53), and washer (54) and the screw (55).
23 Tighten the screw (55).
24 Put the clamps (51) and (59) in position on the bracket (47) and install the washer (50) and the screw (60).
25 Tighten the screw (60).
26 Put the clamps (51) and (59) in position on the aircraft structure and install the spacer (61), the bracket (53), the washer (58) and the screw (57).
27 Tighten the screw (57).
28 Install the new TIE WRAP (56).
(4) Install the fuel recirculation check-valve (Ref. AMM TASK 28-16-42-400-001).
(5) Install the pylons (Ref. AMM TASK 54-50-00-400-802).
(6) Install the engine (Ref. AMM TASK 71-00-51-400-802).
(7) Install the applicable access panel (Ref. AMM TASK 57-27-11-400-007):
(a) For the left wing: 540DZ
(b) For the right wing: 640DZ.
(8) Install the applicable access panel (Ref. AMM TASK 57-27-11-400-005):
(a) For the left wing: 521BZ
(b) For the right wing: 621BZ.
(9) Install the applicable access panels (Ref. AMM TASK 57-27-11-400-001):
(a) For the left wing: 540BB and 540CB
(b) For the right wing: 640BB and 640CB.
(10) Remove the access platform(s).
A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) If removed, install the air dam (9) as follows:
(a) If you removed the screws (1), (3), (5) and (7), do the steps that follow:
1 Discard the screws (1), (3), (5) and (7) and the nuts (10), (12) and (14).
2 Do a special detailed inspection (ROTO) of the holes.
3 If you find signs of damage, contact Airbus.
4 Perform the first oversizing.
5 Deburr all the holes once drilled.
6 Release the cables (16), (17), (18) and (19) from the aircraft structure.
7 Put the air dam (9) in position and install the new screws (2), (4), (6) and (8) and the new nuts (11), (13) and (15), refer to SRM 514200.
8 Refer to the installation drawing in the SRM identification section for the new fastener references.
9 Tighten the nuts (11), (13) and (15).
(b) If you did not remove the screws (1), (3), (5) and (7), do the steps that follow:
1 Release the cables (16), (17), (18) and (19) from the aircraft structure.
2 Put the air dam (9) in position and install the nuts (10), (12) and (14).
3 Tighten the nuts (10), (12) and (14).
(3) If removed, install the applicable bracket(s) (22), (34), (36), (47) and/or (64) as follows:
(a) If you removed the screws (20), (62) and (45), do the steps that follow:
1 Discard the screws (20), (62) and (45) and the nuts (23), (48) and (65).
2 Do a special detailed inspection (ROTO) of the holes.
3 If you find signs of damage, contact Airbus.
4 Perform the first oversizing.
5 Deburr all the holes once drilled.
6 Put the bracket (22) in position and install the new screws (21) and the new nuts (24), refer to SRM 514200.
7 Refer to the installation drawing in the SRM identification section for the new fastener references.
8 Tighten the new nuts (24).
9 Put the clamps (25) and (27) in position on the bracket (22) and install the screw (26).
10 Tighten the screw (26).
11 Put the bracket (64) in position and install the new screws (63) and the new nuts (66), refer to SRM 514200.
12 Refer to the installation drawing in the SRM identification section for the new fastener references.
13 Tighten the new nuts (66).
14 Put the clamps (51) and (59) in position on the bracket (64) and install the screw (67).
15 Tighten the screw (67).
16 Put the brackets (34) and (36) in position and install the spacers (35), the screws (37) and the nuts (33).
17 Tighten the nuts (33).
18 Put the bracket (28) in position and install the washers (44) and the screws (43).
19 Tighten the screws (43).
20 Install the new TIE WRAP (39).
21 Put the clamps (30) in position on the bracket (28) and install the screws (31).
22 Tighten the screws (31).
23 Install the clamps (42) on the bracket (28).
24 Install the washers (41), the screws (40) and the nuts (32) on the bracket (34).
25 Put the clamps (25) and (27) in position on the bracket (36) and install the screws (38).
26 Tighten the screws (38).
27 Put the bracket (47) in position and install the new screws (46) and the new nuts (49), refer to SRM 514200.
28 Refer to the installation drawing in the SRM identification section for the new fastener references.
29 Tighten the new nuts (49).
30 Install the spacer (52), the bracket (53), and washer (54) and the screw (55).
31 Tighten the screw (55).
32 Put the clamps (51) and (59) in position on the bracket (47) and install the washer (50) and the screw (60).
33 Tighten the screw (60).
34 Put the clamps (51) and (59) in position on the aircraft structure and install the spacer (61), the bracket (53), the washer (58) and the screw (57).
35 Tighten the screw (57).
36 Install the new TIE WRAP (56).
(b) If you did not remove the screws (20), (62) and (45), do the steps that follow:
1 Put the bracket (22) in position and install the screws (20) and the nuts (23).
2 Tighten the nuts (23).
3 Put the clamps (25) and (27) in position on the bracket (22) and install the screw (26).
4 Tighten the screw (26).
5 Put the bracket (64) in position and install the screws (62) and the nuts (65).
6 Tighten the nuts (65).
7 Put the clamps (51) and (59) in position on the bracket (64) and install the screw (67).
8 Tighten the screw (67).
9 Put the brackets (34) and (36) in position and install the spacers (35), the screws (37) and the nuts (33).
10 Tighten the nuts (33).
11 Put the bracket (28) in position and install the washers (44) and the screws (43).
12 Tighten the screws (43).
13 Install the new TIE WRAP (39).
14 Put the clamps (30) in position on the bracket (28) and install the screws (31).
15 Tighten the screws (31).
16 Install the clamps (42) on the bracket (28).
17 Install the washers (41), the screws (40) and the nuts (32) on the bracket (34).
18 Put the clamps (25) and (27) in position on the bracket (36) and install the screws (38).
19 Tighten the screws (38).
20 Put the bracket (47) in position and install the screws (45) and the nuts (48).
21 Tighten the nuts (48).
22 Install the spacer (52), the bracket (53), and washer (54) and the screw (55).
23 Tighten the screw (55).
24 Put the clamps (51) and (59) in position on the bracket (47) and install the washer (50) and the screw (60).
25 Tighten the screw (60).
26 Put the clamps (51) and (59) in position on the aircraft structure and install the spacer (61), the bracket (53), the washer (58) and the screw (57).
27 Tighten the screw (57).
28 Install the new TIE WRAP (56).
(4) Install the fuel recirculation check-valve (Ref. AMM TASK 28-16-42-400-001).
(5) Install the pylons (Ref. AMM TASK 54-50-00-400-001).
(6) Install the engine (Ref. AMM TASK 71-00-00-400-042).
(7) Install the applicable access panel (Ref. AMM TASK 57-27-11-400-007):
(a) For the left wing: 540DZ
(b) For the right wing: 640DZ.
(8) Install the applicable access panel (Ref. AMM TASK 57-27-11-400-005):
(a) For the left wing: 521BZ
(b) For the right wing: 621BZ.
(9) Install the applicable access panels (Ref. AMM TASK 57-27-11-400-001):
(a) For the left wing: 540BB and 540CB
(b) For the right wing: 640BB and 640CB.
(10) Remove the access platform(s).
Subtask 57-20-00-865-089-A (1) Make sure that the work area is clean and clear of tools and other items.
(2) If removed, install the air dam (9) as follows:
(a) If you removed the screws (1), (3), (5) and (7), do the steps that follow:
1 Discard the screws (1), (3), (5) and (7) and the nuts (10), (12) and (14).
2 Do a special detailed inspection (ROTO) of the holes.
3 If you find signs of damage, contact Airbus.
4 Perform the first oversizing.
5 Deburr all the holes once drilled.
6 Release the cables (16), (17), (18) and (19) from the aircraft structure.
7 Put the air dam (9) in position and install the new screws (2), (4), (6) and (8) and the new nuts (11), (13) and (15), refer to SRM 514200.
8 Refer to the installation drawing in the SRM identification section for the new fastener references.
9 Tighten the nuts (11), (13) and (15).
(b) If you did not remove the screws (1), (3), (5) and (7), do the steps that follow:
1 Release the cables (16), (17), (18) and (19) from the aircraft structure.
2 Put the air dam (9) in position and install the nuts (10), (12) and (14).
3 Tighten the nuts (10), (12) and (14).
(3) If removed, install the applicable bracket(s) (22), (34), (36), (47) and/or (64) as follows:
(a) If you removed the screws (20), (62) and (45), do the steps that follow:
1 Discard the screws (20), (62) and (45) and the nuts (23), (48) and (65).
2 Do a special detailed inspection (ROTO) of the holes.
3 If you find signs of damage, contact Airbus.
4 Perform the first oversizing.
5 Deburr all the holes once drilled.
6 Put the bracket (22) in position and install the new screws (21) and the new nuts (24), refer to SRM 514200.
7 Refer to the installation drawing in the SRM identification section for the new fastener references.
8 Tighten the new nuts (24).
9 Put the clamps (25) and (27) in position on the bracket (22) and install the screw (26).
10 Tighten the screw (26).
11 Put the bracket (64) in position and install the new screws (63) and the new nuts (66), refer to SRM 514200.
12 Refer to the installation drawing in the SRM identification section for the new fastener references.
13 Tighten the new nuts (66).
14 Put the clamps (51) and (59) in position on the bracket (64) and install the screw (67).
15 Tighten the screw (67).
16 Put the brackets (34) and (36) in position and install the spacers (35), the screws (37) and the nuts (33).
17 Tighten the nuts (33).
18 Put the bracket (28) in position and install the washers (44) and the screws (43).
19 Tighten the screws (43).
20 Install the new TIE WRAP (39).
21 Put the clamps (30) in position on the bracket (28) and install the screws (31).
22 Tighten the screws (31).
23 Install the clamps (42) on the bracket (28).
24 Install the washers (41), the screws (40) and the nuts (32) on the bracket (34).
25 Put the clamps (25) and (27) in position on the bracket (36) and install the screws (38).
26 Tighten the screws (38).
27 Put the bracket (47) in position and install the new screws (46) and the new nuts (49), refer to SRM 514200.
28 Refer to the installation drawing in the SRM identification section for the new fastener references.
29 Tighten the new nuts (49).
30 Install the spacer (52), the bracket (53), and washer (54) and the screw (55).
31 Tighten the screw (55).
32 Put the clamps (51) and (59) in position on the bracket (47) and install the washer (50) and the screw (60).
33 Tighten the screw (60).
34 Put the clamps (51) and (59) in position on the aircraft structure and install the spacer (61), the bracket (53), the washer (58) and the screw (57).
35 Tighten the screw (57).
36 Install the new TIE WRAP (56).
(b) If you did not remove the screws (20), (62) and (45), do the steps that follow:
1 Put the bracket (22) in position and install the screws (20) and the nuts (23).
2 Tighten the nuts (23).
3 Put the clamps (25) and (27) in position on the bracket (22) and install the screw (26).
4 Tighten the screw (26).
5 Put the bracket (64) in position and install the screws (62) and the nuts (65).
6 Tighten the nuts (65).
7 Put the clamps (51) and (59) in position on the bracket (64) and install the screw (67).
8 Tighten the screw (67).
9 Put the brackets (34) and (36) in position and install the spacers (35), the screws (37) and the nuts (33).
10 Tighten the nuts (33).
11 Put the bracket (28) in position and install the washers (44) and the screws (43).
12 Tighten the screws (43).
13 Install the new TIE WRAP (39).
14 Put the clamps (30) in position on the bracket (28) and install the screws (31).
15 Tighten the screws (31).
16 Install the clamps (42) on the bracket (28).
17 Install the washers (41), the screws (40) and the nuts (32) on the bracket (34).
18 Put the clamps (25) and (27) in position on the bracket (36) and install the screws (38).
19 Tighten the screws (38).
20 Put the bracket (47) in position and install the screws (45) and the nuts (48).
21 Tighten the nuts (48).
22 Install the spacer (52), the bracket (53), and washer (54) and the screw (55).
23 Tighten the screw (55).
24 Put the clamps (51) and (59) in position on the bracket (47) and install the washer (50) and the screw (60).
25 Tighten the screw (60).
26 Put the clamps (51) and (59) in position on the aircraft structure and install the spacer (61), the bracket (53), the washer (58) and the screw (57).
27 Tighten the screw (57).
28 Install the new TIE WRAP (56).
(4) Install the fuel recirculation check-valve (Ref. AMM TASK 28-16-42-400-001).
(5) Install the pylons (Ref. AMM TASK 54-50-00-400-001).
(6) Install the engine (Ref. AMM TASK 71-00-00-400-042).
(7) Install the applicable access panel (Ref. AMM TASK 57-27-11-400-007):
(a) For the left wing: 540DZ
(b) For the right wing: 640DZ.
(8) Install the applicable access panel (Ref. AMM TASK 57-27-11-400-005):
(a) For the left wing: 521BZ
(b) For the right wing: 621BZ.
(9) Install the applicable access panels (Ref. AMM TASK 57-27-11-400-001):
(a) For the left wing: 540BB and 540CB
(b) For the right wing: 640BB and 640CB.
(10) Remove the access platform(s).
B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 57-20-00-942-119-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| FOR FIN: 1000EM1 (ENGINE1) | |||
| 49VU | ENGINE/1/FADEC A/AND EIU 1 | 2KS1 | A04 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | ENGINE/ENG1/FADEC B/AND EIU 1 | 4KS1 | R41 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | ENGINE/ENG1/FADEC B/AND EIU 1 | 4KS1 | R40 |
| ** ON A/C ALL | |||
| FOR FIN: 1000EM2 (ENGINE2) | |||
| 49VU | ENGINE/2/FADEC A/AND EIU 2 | 2KS2 | A05 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | ENGINE/ENG2/FADEC B | 4KS2 | Q40 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | ENGINE/ENG2/FADEC B/AND EIU2 | 4KS2 | Q40 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | ENGINE/ENG2/FADEC B/AND EIU2 | 4KS2 | R41 |
C. Removal of the Equipment
(1) Remove the SAFETY BARRIERS.
(2) Remove the 98D27803500001 LOCKING TOOL ZERO POS from the flap/slat control lever.
(3) Remove the WARNING NOTICE(S).
(4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(1) Remove the SAFETY BARRIERS.
(2) Remove the 98D27803500001 LOCKING TOOL ZERO POS from the flap/slat control lever.
(3) Remove the WARNING NOTICE(S).
(4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.