DOC AIRBUS | AMM A320FRepair to the Leading Edge Pressure-Relief Panel After it has Operated
TASK 57-41-37-350-001-A
Repair to the Leading Edge Pressure-Relief Panel After it has Operated
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Expendable Parts
D. Referenced Information
3. Job Set-up
Subtask 57-41-37-941-053-A
Subtask 57-41-37-350-051-D ** ON A/C NOT FOR ALL
Subtask 57-41-37-865-058-A
[Rev.10 from 2021]
2026.04.01 12:53:01 UTC
Repair to the Leading Edge Pressure-Relief Panel After it has Operated
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.
1. Reason for the JobSelf explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE |
| No specific | AR | CUP - SUCTION |
| No specific | AR | GUN - SEALANT, EXTRUSION |
| No specific | AR | SAFETY CLIP - CIRCUIT BREAKER |
| No specific | 1 | SCRAPER |
| No specific | AR | SCRAPER - NON METALLIC |
| No specific | AR | SPATULA - NON METALLIC |
| No specific | AR | TAPE - MASKING |
| No specific | AR | WARNING NOTICE(S) |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.06AAB1) | Polysulfide Sealant-General Purpose Fillet - |
| (Material No.06ABA1) | Polysulfide Sealant-Fuel Tank Brushable - |
| (Material No.06ABB1) | Polysulfide Sealant-Fuel Tank Fillet - |
| (Material No.06ABB2) | Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius |
| (Material No.08BAA9) | Non Aqueous Cleaner-General - - |
| (Material No.14CDB1) | Testing Medium-Fuel Leak Detection White Powder - |
| (Material No.14DAB1) | Release Agent-- Water Base - |
| (Material No.14SBA1) | Textile-Lint free Cotton - |
| FIG.ITEM | DESIGNATION | IPC-CSN |
|---|---|---|
| 140 | SEAL | AIPC 57-41-37-01-150 |
| REFERENCE | DESIGNATION |
|---|---|
| SRM 514211 | |
| SRM 514411 | |
| SRM 574118 | |
| SRM 574126 | |
 Leading Edge Pressure-Relief Panel - Trailing Edge Gap-Seal - Location and Detail ** ON A/C NOT FOR ALL | |
Subtask 57-41-37-941-053-A
A. Safety Precautions
(1) Put WARNING NOTICE(S) in position to tell persons not to operate the slat and the pneumatic systems.
(2) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the applicable pressure-relief panels:
For the LH wing:
Subtask 57-41-37-865-057-A (1) Put WARNING NOTICE(S) in position to tell persons not to operate the slat and the pneumatic systems.
(2) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the applicable pressure-relief panels:
For the LH wing:
- below the panels 521AB and 521CB
- below the panels 621AB and 621CB.
B. Open, safety and tag this(these) circuit breaker(s):
4. Procedure| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 | 5CV | B06 |
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 | 5CV | B01 |
| ** ON A/C ALL | |||
| 121VU | FLIGHT CONTROLS/SLT/CTL/SYS2 | 7CV | R21 |
Subtask 57-41-37-350-051-D ** ON A/C NOT FOR ALL
A. Repair of the Leading Edge Pressure-Relief Panel 521AB(621AB) After it has Operated
(1) Remove the bolts (10).
(2) Carefully remove the pressure-relief panel 521AB(621AB) (9).
(3) When you remove the pressure-relief panel (9) a part of the landings (1), (3) and (6) will fall. Make a note of the related position of these landings and keep them for later assembly.
(4) Remove the bolts (28).
(5) Carefully remove the pressure-relief panel 521CB(621CB) (30).
(6) Remove the nuts (2) and the bolts (16) SRM 514211.
(7) Remove the part of the landing (1) that is attached to the aircraft structure.
(8) Remove the nuts (5) and the bolts (7) SRM 514211.
(9) Remove the part of the landing (6) that is attached to the aircraft structure.
(10) Remove the nuts (4) and the bolts (8) SRM 514211.
(11) Remove the part of the landing (3) that is attached to the aircraft structure.
(12) Remove and discard the rivets (15) SRM 514211.
(13) Remove and discard the forward angle (14).
(14) Remove and discard the rivets (11) SRM 514211.
(15) Remove and discard the rivets (34) SRM 514211.
(16) Remove and discard the forward angle (12).
(19) Assemble the landings (1), (3) and (6) as follows:
(a) Put the two parts of the applicable landing together.
(b) Install the spacers (122) and the washers (121).
(c) Install the shear rivets (120) SRM 514211.
(d) Make sure that the two parts of the landings can move on the spacers (122).
(20) Examine the pressure-relief panels (9) and (30) for damage. Discard those that are damaged.
(21) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (14) SRM 574118.
(22) Install the rivets (132) SRM 514211.
(23) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the forward angle (14) and the forward sub-spar (13).
(24) Put the forward angle (14) in position on the forward sub-spar (13) and install the rivets (15) SRM 514211.
(25) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (12) SRM 574118.
(27) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the forward angle (12) and the forward sub-spar (13) and (32).
(28) Put the forward angle (12) in position on the forward sub-spar (13) and (32). Install the rivets (11) and (34) SRM 514211.
(29) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (6) and the aircraft structure.
(30) Put the landing (6) in position.
(31) Install the bolts (7) and the nuts (5) SRM 514211.
(32) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (3) and the aircraft structure.
(33) Put the landing (3) in position and install the bolts (8) and the nuts (4) SRM 514211.
(34) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (1) and the aircraft structure.
(35) Put the landing (1) in position.
(36) Install the bolts (16) and the nuts (2) SRM 514211.
(37) Examine the seals (140) around the pressure-relief panels (9) and (30) for damage and correct condition. Replace damaged seals as follows:
(a) Remove the damaged length of seal (140) with a SCRAPER - NON METALLIC.
(b) Clean the applicable area of the panel with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with. Non Aqueous Cleaner-General - - (Material No.08BAA9)
(c) Cut to length a new AIPC 57-41-37-01-150 SEAL (140).
(d) Put the new seal (140) in position on the panel.
(e) Cut the corners of the new seal (140) to make a continuous surface at the corner joints.
(f) Remove the protective back from the new seal (140) and install the seal on the panel.
(g) Use a suitable SCRAPER to remove the seal from the holes X. The diameter of the hole X is between 5.75 mm (0.2264 in.) and 6.25 mm (0.2461 in.).
(38) Make sure that the work area is clean and clear of tools and other items.
(39) Put the pressure-relief panel (9) in position and install the bolts (10).
(40) Put the pressure-relief panel (30) in position and install the bolts (28).
(41) Measure the into/out of wind step tolerances of the pressure-relief panels (9) and (30) across the line of flight. These must be as follows:
(a) For the panel leading edge:
(a) For the panel ends:
(a) Calculate the necessary thickness of the spacer (123) required to make the step correct.
(b) Get the correct thickness of spacer (123) SRM 574126.
(c) Remove the applicable bolts (10) and/or (28) and the applicable pressure-relief panel (9) and/or (30).
(d) Put the spacer (123) in position on the applicable landing.
(e) Drill the applicable landing and the spacer (123) to a diameter between 3.27 mm (0.1287 in.) and 3.35 mm (0.1319 in.) SRM 514411.
(f) Remove the sharp edges from the applicable landing and the spacer (123).
(g) Put the spacer (123) in position on the applicable landing and install the rivets (124) SRM 514211.
(h) Install the applicable pressure-relief panel (9) and/or (30) with the bolts (10) and/or (28).
(i) Do again step (41) and step (42).
(44) Measure the clearance between the D-nose skin and the leading edges of the pressure-relief panels (9) and (30). The clearance must be between 0.5 mm (0.0197 in.) and 4.5 mm (0.1772 in.).
(45) Measure the clearance at the inboard and outboard edges of the pressure-relief panels (9) and (30). The clearance must be between 0.5 mm (0.0197 in.) and 5.5 mm (0.2165 in.).
(46) At the trailing edges of the pressure-relief (9) and (30), measure the clearance between:
Subtask 57-41-37-350-051-E ** ON A/C NOT FOR ALL (1) Remove the bolts (10).
(2) Carefully remove the pressure-relief panel 521AB(621AB) (9).
(3) When you remove the pressure-relief panel (9) a part of the landings (1), (3) and (6) will fall. Make a note of the related position of these landings and keep them for later assembly.
(4) Remove the bolts (28).
(5) Carefully remove the pressure-relief panel 521CB(621CB) (30).
(6) Remove the nuts (2) and the bolts (16) SRM 514211.
(7) Remove the part of the landing (1) that is attached to the aircraft structure.
(8) Remove the nuts (5) and the bolts (7) SRM 514211.
(9) Remove the part of the landing (6) that is attached to the aircraft structure.
(10) Remove the nuts (4) and the bolts (8) SRM 514211.
(11) Remove the part of the landing (3) that is attached to the aircraft structure.
(12) Remove and discard the rivets (15) SRM 514211.
(13) Remove and discard the forward angle (14).
(14) Remove and discard the rivets (11) SRM 514211.
(15) Remove and discard the rivets (34) SRM 514211.
(16) Remove and discard the forward angle (12).
NOTE: The forward angle (12) and the forward angle (33) is the same item. The forward angle (12) or (33) attaches the two pressure relief panels 521AB(621AB) and 521CB(621CB) to the aircraft structure.
(17) Clean these items with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) : - the forward sub-spar (13) and (32)
- the landings (1), (3) and (6)
- the landing (1), (3) and (6) interfaces and the adjacent areas.
(19) Assemble the landings (1), (3) and (6) as follows:
(a) Put the two parts of the applicable landing together.
(b) Install the spacers (122) and the washers (121).
(c) Install the shear rivets (120) SRM 514211.
(d) Make sure that the two parts of the landings can move on the spacers (122).
(20) Examine the pressure-relief panels (9) and (30) for damage. Discard those that are damaged.
(21) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (14) SRM 574118.
(22) Install the rivets (132) SRM 514211.
(23) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the forward angle (14) and the forward sub-spar (13).
(24) Put the forward angle (14) in position on the forward sub-spar (13) and install the rivets (15) SRM 514211.
(25) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (12) SRM 574118.
NOTE: The forward angle (12) and the forward angle (33) is the same item. The forward angle (12) or (33) attaches the two pressure relief panels 521AB(621AB) and 521CB(621CB) to the aircraft structure.
(26) Install the rivets (132) SRM 514211. (27) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the forward angle (12) and the forward sub-spar (13) and (32).
(28) Put the forward angle (12) in position on the forward sub-spar (13) and (32). Install the rivets (11) and (34) SRM 514211.
(29) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (6) and the aircraft structure.
(30) Put the landing (6) in position.
(31) Install the bolts (7) and the nuts (5) SRM 514211.
(32) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (3) and the aircraft structure.
(33) Put the landing (3) in position and install the bolts (8) and the nuts (4) SRM 514211.
(34) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (1) and the aircraft structure.
(35) Put the landing (1) in position.
(36) Install the bolts (16) and the nuts (2) SRM 514211.
(37) Examine the seals (140) around the pressure-relief panels (9) and (30) for damage and correct condition. Replace damaged seals as follows:
(a) Remove the damaged length of seal (140) with a SCRAPER - NON METALLIC.
(b) Clean the applicable area of the panel with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with. Non Aqueous Cleaner-General - - (Material No.08BAA9)
(c) Cut to length a new AIPC 57-41-37-01-150 SEAL (140).
(d) Put the new seal (140) in position on the panel.
(e) Cut the corners of the new seal (140) to make a continuous surface at the corner joints.
(f) Remove the protective back from the new seal (140) and install the seal on the panel.
(g) Use a suitable SCRAPER to remove the seal from the holes X. The diameter of the hole X is between 5.75 mm (0.2264 in.) and 6.25 mm (0.2461 in.).
(38) Make sure that the work area is clean and clear of tools and other items.
(39) Put the pressure-relief panel (9) in position and install the bolts (10).
(40) Put the pressure-relief panel (30) in position and install the bolts (28).
(41) Measure the into/out of wind step tolerances of the pressure-relief panels (9) and (30) across the line of flight. These must be as follows:
(a) For the panel leading edge:
- maximum 0.6 mm (0.0236 in.) above wing surface (into wind)
- maximum 1.2 mm (0.0472 in.) below wing surface (out of wind).
- maximum 0.6 mm (0.0236 in.) below wing surface (into wind)
- maximum 2.0 mm (0.0787 in.) above wing surface (out of wind). Typical Leading Edge Pressure-Relief Panel End Step Tolerance - Details ** ON A/C NOT FOR ALL Typical Leading Edge Pressure-Relief Panel End Step Tolerance - Details ** ON A/C NOT FOR ALL
(a) For the panel ends:
- maximum 2.0 mm (0.0787 in.) above or below the adjacent panel end (DIM X)
- maximum 2.0 mm (0.0787 in.) above or below the adjacent wing surface (DIM Y).
(a) Calculate the necessary thickness of the spacer (123) required to make the step correct.
(b) Get the correct thickness of spacer (123) SRM 574126.
(c) Remove the applicable bolts (10) and/or (28) and the applicable pressure-relief panel (9) and/or (30).
(d) Put the spacer (123) in position on the applicable landing.
(e) Drill the applicable landing and the spacer (123) to a diameter between 3.27 mm (0.1287 in.) and 3.35 mm (0.1319 in.) SRM 514411.
(f) Remove the sharp edges from the applicable landing and the spacer (123).
(g) Put the spacer (123) in position on the applicable landing and install the rivets (124) SRM 514211.
(h) Install the applicable pressure-relief panel (9) and/or (30) with the bolts (10) and/or (28).
(i) Do again step (41) and step (42).
(44) Measure the clearance between the D-nose skin and the leading edges of the pressure-relief panels (9) and (30). The clearance must be between 0.5 mm (0.0197 in.) and 4.5 mm (0.1772 in.).
(45) Measure the clearance at the inboard and outboard edges of the pressure-relief panels (9) and (30). The clearance must be between 0.5 mm (0.0197 in.) and 5.5 mm (0.2165 in.).
(46) At the trailing edges of the pressure-relief (9) and (30), measure the clearance between:
- the wing-skin and the edges of the panel (that are parallel to the panel leading edges), the clearance must be between 0.5 mm (0.0197 in.) and 5.5 mm (0.2165 in.)
- the wing-skin and the edges of the panel cut-outs (that are not parallel to the leading edges), the clearance must be between 0.5 mm (0.0197 in.) and 7.0 mm (0.2756 in.).
A. Repair of the Leading Edge Pressure-Relief Panel 521AB(621AB) After it has Operated
(1) Remove the bolts (10).
(2) Carefully remove the pressure-relief panel 521AB(621AB) (9).
(3) When you remove the pressure-relief panel (9) a part of the landings (1), (3) and (6) will fall. Make a note of the related position of these landings and keep them for later assembly.
(4) Remove the bolts (28).
(5) Carefully remove the pressure-relief panel 521CB(621CB) (30).
(6) Remove the nuts (2) and the bolts (16) SRM 514211.
(7) Remove the part of the landing (1) that is attached to the aircraft structure.
(8) Remove the nuts (5) and the bolts (7) SRM 514211.
(9) Remove the part of the landing (6) that is attached to the aircraft structure.
(10) Remove the nuts (4) and the bolts (8) SRM 514211.
(11) Remove the part of the landing (3) that is attached to the aircraft structure.
(12) Remove and discard the rivets (15) SRM 514211.
(13) Remove and discard the forward angle (14).
(14) Remove and discard the rivets (11) SRM 514211.
(15) Remove and discard the rivets (34) SRM 514211.
(16) Remove and discard the forward angle (12).
(19) Assemble the landings (1), (3) and (6) as follows:
(a) Put the two parts of the applicable landing together.
(b) Install the spacers (122) and the washers (121).
(c) Install the shear rivets (120) SRM 514211.
(d) Make sure that the two parts of the landings can move on the spacers (122).
(20) Examine the pressure-relief panels (9) and (30) for damage. Discard those that are damaged.
(21) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (14) SRM 574118.
(22) Install the rivets (132) SRM 514211.
(23) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the forward angle (14) and the forward sub-spar (13).
(24) Put the forward angle (14) in position on the forward sub-spar (13) and install the rivets (15) SRM 514211.
(25) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (12) SRM 574118.
(27) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the forward angle (12) and the forward sub-spar (13) and (32).
(28) Put the forward angle (12) in position on the forward sub-spar (13) and (32). Install the rivets (11) and (34) SRM 514211.
(29) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (6) and the aircraft structure.
(30) Put the landing (6) in position.
(31) Install the bolts (7) and the nuts (5) SRM 514211.
(32) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (3) and the aircraft structure.
(33) Put the landing (3) in position and install the bolts (8) and the nuts (4) SRM 514211.
(34) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (1) and the aircraft structure.
(35) Put the landing (1) in position.
(36) Install the bolts (16) and the nuts (2) SRM 514211.
(37) Examine the seals (140) around the pressure-relief panels (9) and (30) for damage and correct condition. Replace damaged seals as follows:
(a) Remove the damaged length of seal (140) with a SCRAPER - NON METALLIC.
(b) Clean the applicable area of the panel with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(c) Cut to length a new AIPC 57-41-37-01-150 SEAL (140).
(d) Put the new seal (140) in position on the panel.
(e) Cut the corners of the new seal (140) to make a continuous surface at the corner joints.
(f) Remove the protective back from the new seal (140) and install the seal on the panel.
(g) Use a suitable SCRAPER to remove the seal from the holes X. The diameter of the hole X is between 5.75 mm (0.2264 in.) and 6.25 mm (0.2461 in.).
(38) Make sure that the work area is clean and clear of tools and other items.
(39) Apply release agent, Release Agent-- Water Base - (Material No.14DAB1) to the trailing edge of the pressure-relief panel (9).
(40) Put the pressure-relief panel (9) in position and install the bolts (10).
(41) Apply release agent, Release Agent-- Water Base - (Material No.14DAB1) to the trailing edge of the pressure-relief panel (30).
(42) Put the pressure-relief panel (30) in position and install the bolts (28).
(43) Measure the into/out of wind step tolerances of the pressure-relief panels (9) and (30) across the line of flight. These must be as follows:
(a) For the panel leading edge:
(a) For the panel ends:
(a) Calculate the necessary thickness of the spacer (123) required to make the step correct.
(b) Get the correct thickness of spacer (123) SRM 574126.
(c) Remove the applicable bolts (10) and/or (28) and the applicable pressure-relief panel (9) and/or (30).
(d) Put the spacer (123) in position on the applicable landing.
(e) Drill the applicable landing and the spacer (123) to a diameter between 3.27 mm (0.1287 in.) and 3.35 mm (0.1319 in.) SRM 514411.
(f) Remove the sharp edges from the applicable landing and the spacer (123).
(g) Put the spacer (123) in position on the applicable landing and install the rivets (124) SRM 514211.
(h) Install the applicable pressure-relief panel (9) and/or (30) with the bolts (10) and/or (28).
(i) Do again step (41) and step (42).
(46) Measure the clearance between the D-nose skin and the leading edges of the pressure-relief panels (9) and (30). This must be between 0.5 mm (0.0197 in.) and 4.5 mm (0.1772 in.).
(47) Measure the clearance at the inboard and outboard edges of the pressure-relief panels (9) and (30). This must be between 0.5 mm (0.0197 in.) and 5.5 mm (0.2165 in.).
(48) At the trailing edges of the pressure-relief panels (9) and (30), measure:
Subtask 57-41-37-350-051-G ** ON A/C NOT FOR ALL (1) Remove the bolts (10).
(2) Carefully remove the pressure-relief panel 521AB(621AB) (9).
(3) When you remove the pressure-relief panel (9) a part of the landings (1), (3) and (6) will fall. Make a note of the related position of these landings and keep them for later assembly.
(4) Remove the bolts (28).
(5) Carefully remove the pressure-relief panel 521CB(621CB) (30).
(6) Remove the nuts (2) and the bolts (16) SRM 514211.
(7) Remove the part of the landing (1) that is attached to the aircraft structure.
(8) Remove the nuts (5) and the bolts (7) SRM 514211.
(9) Remove the part of the landing (6) that is attached to the aircraft structure.
(10) Remove the nuts (4) and the bolts (8) SRM 514211.
(11) Remove the part of the landing (3) that is attached to the aircraft structure.
(12) Remove and discard the rivets (15) SRM 514211.
(13) Remove and discard the forward angle (14).
(14) Remove and discard the rivets (11) SRM 514211.
(15) Remove and discard the rivets (34) SRM 514211.
(16) Remove and discard the forward angle (12).
NOTE: The forward angle (12) and the forward angle (33) is the same item. The forward angle (12) or (33) attaches the two pressure relief panels 521AB(621AB) and 521CB(621CB) to the aircraft structure.
(17) Clean these items with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) : - the forward sub-spar (13) and (32)
- the landings (1), (3) and (6)
- the landing (1), (3) and (6) interfaces and the adjacent areas.
(19) Assemble the landings (1), (3) and (6) as follows:
(a) Put the two parts of the applicable landing together.
(b) Install the spacers (122) and the washers (121).
(c) Install the shear rivets (120) SRM 514211.
(d) Make sure that the two parts of the landings can move on the spacers (122).
(20) Examine the pressure-relief panels (9) and (30) for damage. Discard those that are damaged.
(21) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (14) SRM 574118.
(22) Install the rivets (132) SRM 514211.
(23) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the forward angle (14) and the forward sub-spar (13).
(24) Put the forward angle (14) in position on the forward sub-spar (13) and install the rivets (15) SRM 514211.
(25) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (12) SRM 574118.
NOTE: The forward angle (12) and the forward angle (33) is the same item. The forward angle (12) or (33) attaches the two pressure relief panels 521AB(621AB) and 521CB(621CB) to the aircraft structure.
(26) Install the rivets (132) SRM 514211. (27) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the forward angle (12) and the forward sub-spar (13) and (32).
(28) Put the forward angle (12) in position on the forward sub-spar (13) and (32). Install the rivets (11) and (34) SRM 514211.
(29) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (6) and the aircraft structure.
(30) Put the landing (6) in position.
(31) Install the bolts (7) and the nuts (5) SRM 514211.
(32) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (3) and the aircraft structure.
(33) Put the landing (3) in position and install the bolts (8) and the nuts (4) SRM 514211.
(34) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (1) and the aircraft structure.
(35) Put the landing (1) in position.
(36) Install the bolts (16) and the nuts (2) SRM 514211.
(37) Examine the seals (140) around the pressure-relief panels (9) and (30) for damage and correct condition. Replace damaged seals as follows:
(a) Remove the damaged length of seal (140) with a SCRAPER - NON METALLIC.
(b) Clean the applicable area of the panel with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(c) Cut to length a new AIPC 57-41-37-01-150 SEAL (140).
(d) Put the new seal (140) in position on the panel.
(e) Cut the corners of the new seal (140) to make a continuous surface at the corner joints.
(f) Remove the protective back from the new seal (140) and install the seal on the panel.
(g) Use a suitable SCRAPER to remove the seal from the holes X. The diameter of the hole X is between 5.75 mm (0.2264 in.) and 6.25 mm (0.2461 in.).
(38) Make sure that the work area is clean and clear of tools and other items.
(39) Apply release agent, Release Agent-- Water Base - (Material No.14DAB1) to the trailing edge of the pressure-relief panel (9).
(40) Put the pressure-relief panel (9) in position and install the bolts (10).
(41) Apply release agent, Release Agent-- Water Base - (Material No.14DAB1) to the trailing edge of the pressure-relief panel (30).
(42) Put the pressure-relief panel (30) in position and install the bolts (28).
(43) Measure the into/out of wind step tolerances of the pressure-relief panels (9) and (30) across the line of flight. These must be as follows:
(a) For the panel leading edge:
- maximum 0.6 mm (0.0236 in.) above wing surface (into wind)
- maximum 1.2 mm (0.0472 in.) below wing surface (out of wind).
- maximum 0.6 mm (0.0236 in.) below wing surface (into wind)
- maximum 2.0 mm (0.0787 in.) above wing surface (out of wind). Typical Leading Edge Pressure-Relief Panel End Step Tolerance - Details ** ON A/C NOT FOR ALL Typical Leading Edge Pressure-Relief Panel End Step Tolerance - Details ** ON A/C NOT FOR ALL
(a) For the panel ends:
- maximum 2.0 mm (0.0787 in.) above or below the adjacent panel end (DIM X)
- maximum 2.0 mm (0.0787 in.) above or below the adjacent wing surface (DIM Y).
(a) Calculate the necessary thickness of the spacer (123) required to make the step correct.
(b) Get the correct thickness of spacer (123) SRM 574126.
(c) Remove the applicable bolts (10) and/or (28) and the applicable pressure-relief panel (9) and/or (30).
(d) Put the spacer (123) in position on the applicable landing.
(e) Drill the applicable landing and the spacer (123) to a diameter between 3.27 mm (0.1287 in.) and 3.35 mm (0.1319 in.) SRM 514411.
(f) Remove the sharp edges from the applicable landing and the spacer (123).
(g) Put the spacer (123) in position on the applicable landing and install the rivets (124) SRM 514211.
(h) Install the applicable pressure-relief panel (9) and/or (30) with the bolts (10) and/or (28).
(i) Do again step (41) and step (42).
(46) Measure the clearance between the D-nose skin and the leading edges of the pressure-relief panels (9) and (30). This must be between 0.5 mm (0.0197 in.) and 4.5 mm (0.1772 in.).
(47) Measure the clearance at the inboard and outboard edges of the pressure-relief panels (9) and (30). This must be between 0.5 mm (0.0197 in.) and 5.5 mm (0.2165 in.).
(48) At the trailing edges of the pressure-relief panels (9) and (30), measure:
- the clearance between the wing-skin and the edges of the panels.
A. Repair of the Leading Edge Pressure-Relief Panel 521AB(621AB) After it has Operated
(1) Remove the bolts (10).
(2) Carefully remove the pressure-relief panel 521AB(621AB) (9).
(3) When you remove the pressure-relief panel (9) a part of the landings (1), (3) and (6) will fall. Make a note of the related position of these landings and keep them for later assembly.
(4) Remove the bolts (28).
(5) Carefully remove the pressure-relief panel 521CB(621CB) (30).
(6) Remove the nuts (2) and the bolts (16) SRM 514211.
(7) Remove the part of the landing (1) that is attached to the aircraft structure.
(8) Remove the nuts (5) and the bolts (7) SRM 514211.
(9) Remove the part of the landing (6) that is attached to the aircraft structure.
(10) Remove the nuts (4) and the bolts (8) SRM 514211.
(11) Remove the part of the landing (3) that is attached to the aircraft structure.
(12) Remove and discard the rivets (15) SRM 514211.
(13) Remove and discard the forward angle (14).
(14) Remove and discard the rivets (11) SRM 514211.
(15) Remove and discard the rivets (34) SRM 514211.
(16) Remove and discard the forward angle (12).
(19) Assemble the landings (1), (3) and (6) as follows:
(a) Put the two parts of the applicable landing together.
(b) Install the spacers (122) and the washers (121).
(c) Install the shear rivets (120) SRM 514211.
(d) Make sure that the two parts of the landings can move on the spacers (122).
(20) Examine the pressure-relief panels (9) and (30) for damage. Discard those that are damaged.
(21) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (14) SRM 574118.
(22) Install the rivets (132) SRM 514211.
(23) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the forward angle (14) and the forward sub-spar (13).
(24) Put the forward angle (14) in position on the forward sub-spar (13) and install the rivets (15) SRM 514211.
(25) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (12) SRM 574118.
(27) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the forward angle (12) and the forward sub-spar (13) and (32).
(28) Put the forward angle (12) in position on the forward sub-spar (13) and (32). Install the rivets (11) and (34) SRM 514211.
(29) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the landing (6) and the aircraft structure.
(30) Put the landing (6) in position.
(31) Install the bolts (7) and the nuts (5) SRM 514211.
(32) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the landing (3) and the aircraft structure.
(33) Put the landing (3) in position and install the bolts (8) and the nuts (4) SRM 514211.
(34) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the landing (1) and the aircraft structure.
(35) Put the landing (1) in position.
(36) Install the bolts (16) and the nuts (2) SRM 514211.
(37) Examine the seals (140) around the pressure-relief panels (9) and (30) for damage and correct condition. Replace damaged seals as follows:
(a) Remove the damaged length of seal (140) with a SCRAPER - NON METALLIC.
(b) Clean the applicable area of the panel with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with. Non Aqueous Cleaner-General - - (Material No.08BAA9)
(c) Cut to length a new AIPC 57-41-37-01-150 SEAL (140).
(d) Put the new seal (140) in position on the panel.
(e) Cut the corners of the new seal (140) to make a continuous surface at the corner joints.
(f) Remove the protective back from the new seal (140) and install the seal on the panel.
(g) Use a suitable SCRAPER to remove the seal from the holes X. The diameter of the hole X is between 5.75 mm (0.2264 in.) and 6.25 mm (0.2461 in.).
(38) Make sure that the work area is clean and clear of tools and other items.
(39) Put the pressure-relief panel (9) in position and install the bolts (10).
(40) Put the pressure-relief panel (30) in position and install the bolts (28).
(41) Measure the into/out of wind step tolerances of the pressure-relief panels (9) and (30) across the line of flight. These must be as follows:
(a) For the panel leading edge:
(a) For the panel ends:
(a) Calculate the necessary thickness of the spacer (123) required to make the step correct.
(b) Get the correct thickness of spacer (123) SRM 574126.
(c) Remove the applicable bolts (10) and/or (28) and the applicable pressure-relief panel (9) and/or (30).
(d) Put the spacer (123) in position on the applicable landing.
(e) Drill the applicable landing and the spacer (123) to a diameter between 3.27 mm (0.1287 in.) and 3.35 mm (0.1319 in.) SRM 514411.
(f) Remove the sharp edges from the applicable landing and the spacer (123).
(g) Put the spacer (123) in position on the applicable landing and install the rivets (124) SRM 514211.
(h) Install the applicable pressure-relief panel (9) and/or (30) with the bolts (10) and/or (28).
(i) Do again step (41) and step (42).
(44) Measure the clearance between the D-nose skin and the leading edges of the pressure-relief panels (9) and (30). The clearance must be between 0.5 mm (0.0197 in.) and 4.5 mm (0.1772 in.).
(45) Measure the clearance at the inboard and outboard edges of the pressure-relief panels (9) and (30). The clearance must be between 0.5 mm (0.0197 in.) and 5.5 mm (0.2165 in.).
(46) At the trailing edges of the pressure-relief (9) and (30), measure the clearance between:
Subtask 57-41-37-390-050-A ** ON A/C NOT FOR ALL (1) Remove the bolts (10).
(2) Carefully remove the pressure-relief panel 521AB(621AB) (9).
(3) When you remove the pressure-relief panel (9) a part of the landings (1), (3) and (6) will fall. Make a note of the related position of these landings and keep them for later assembly.
(4) Remove the bolts (28).
(5) Carefully remove the pressure-relief panel 521CB(621CB) (30).
(6) Remove the nuts (2) and the bolts (16) SRM 514211.
(7) Remove the part of the landing (1) that is attached to the aircraft structure.
(8) Remove the nuts (5) and the bolts (7) SRM 514211.
(9) Remove the part of the landing (6) that is attached to the aircraft structure.
(10) Remove the nuts (4) and the bolts (8) SRM 514211.
(11) Remove the part of the landing (3) that is attached to the aircraft structure.
(12) Remove and discard the rivets (15) SRM 514211.
(13) Remove and discard the forward angle (14).
(14) Remove and discard the rivets (11) SRM 514211.
(15) Remove and discard the rivets (34) SRM 514211.
(16) Remove and discard the forward angle (12).
NOTE: The forward angle (12) and the forward angle (33) is the same item. The forward angle (12) or (33) attaches the two pressure relief panels 521AB(621AB) and 521CB(621CB) to the aircraft structure.
(17) Clean these items with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) : - the forward sub-spar (13) and (32)
- the landings (1), (3) and (6)
- the landing (1), (3) and (6) interfaces and the adjacent areas.
(19) Assemble the landings (1), (3) and (6) as follows:
(a) Put the two parts of the applicable landing together.
(b) Install the spacers (122) and the washers (121).
(c) Install the shear rivets (120) SRM 514211.
(d) Make sure that the two parts of the landings can move on the spacers (122).
(20) Examine the pressure-relief panels (9) and (30) for damage. Discard those that are damaged.
(21) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (14) SRM 574118.
(22) Install the rivets (132) SRM 514211.
(23) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the forward angle (14) and the forward sub-spar (13).
(24) Put the forward angle (14) in position on the forward sub-spar (13) and install the rivets (15) SRM 514211.
(25) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (12) SRM 574118.
NOTE: The forward angle (12) and the forward angle (33) is the same item. The forward angle (12) or (33) attaches the two pressure relief panels 521AB(621AB) and 521CB(621CB) to the aircraft structure.
(26) Install the rivets (132) SRM 514211. (27) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the forward angle (12) and the forward sub-spar (13) and (32).
(28) Put the forward angle (12) in position on the forward sub-spar (13) and (32). Install the rivets (11) and (34) SRM 514211.
(29) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the landing (6) and the aircraft structure.
(30) Put the landing (6) in position.
(31) Install the bolts (7) and the nuts (5) SRM 514211.
(32) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the landing (3) and the aircraft structure.
(33) Put the landing (3) in position and install the bolts (8) and the nuts (4) SRM 514211.
(34) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the landing (1) and the aircraft structure.
(35) Put the landing (1) in position.
(36) Install the bolts (16) and the nuts (2) SRM 514211.
(37) Examine the seals (140) around the pressure-relief panels (9) and (30) for damage and correct condition. Replace damaged seals as follows:
(a) Remove the damaged length of seal (140) with a SCRAPER - NON METALLIC.
(b) Clean the applicable area of the panel with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with. Non Aqueous Cleaner-General - - (Material No.08BAA9)
(c) Cut to length a new AIPC 57-41-37-01-150 SEAL (140).
(d) Put the new seal (140) in position on the panel.
(e) Cut the corners of the new seal (140) to make a continuous surface at the corner joints.
(f) Remove the protective back from the new seal (140) and install the seal on the panel.
(g) Use a suitable SCRAPER to remove the seal from the holes X. The diameter of the hole X is between 5.75 mm (0.2264 in.) and 6.25 mm (0.2461 in.).
(38) Make sure that the work area is clean and clear of tools and other items.
(39) Put the pressure-relief panel (9) in position and install the bolts (10).
(40) Put the pressure-relief panel (30) in position and install the bolts (28).
(41) Measure the into/out of wind step tolerances of the pressure-relief panels (9) and (30) across the line of flight. These must be as follows:
(a) For the panel leading edge:
- maximum 0.6 mm (0.0236 in.) above wing surface (into wind)
- maximum 1.2 mm (0.0472 in.) below wing surface (out of wind).
- maximum 0.6 mm (0.0236 in.) below wing surface (into wind)
- maximum 2.0 mm (0.0787 in.) above wing surface (out of wind). Typical Leading Edge Pressure-Relief Panel End Step Tolerance - Details ** ON A/C NOT FOR ALL Typical Leading Edge Pressure-Relief Panel End Step Tolerance - Details ** ON A/C NOT FOR ALL
(a) For the panel ends:
- maximum 2.0 mm (0.0787 in.) above or below the adjacent panel end (DIM X)
- maximum 2.0 mm (0.0787 in.) above or below the adjacent wing surface (DIM Y).
(a) Calculate the necessary thickness of the spacer (123) required to make the step correct.
(b) Get the correct thickness of spacer (123) SRM 574126.
(c) Remove the applicable bolts (10) and/or (28) and the applicable pressure-relief panel (9) and/or (30).
(d) Put the spacer (123) in position on the applicable landing.
(e) Drill the applicable landing and the spacer (123) to a diameter between 3.27 mm (0.1287 in.) and 3.35 mm (0.1319 in.) SRM 514411.
(f) Remove the sharp edges from the applicable landing and the spacer (123).
(g) Put the spacer (123) in position on the applicable landing and install the rivets (124) SRM 514211.
(h) Install the applicable pressure-relief panel (9) and/or (30) with the bolts (10) and/or (28).
(i) Do again step (41) and step (42).
(44) Measure the clearance between the D-nose skin and the leading edges of the pressure-relief panels (9) and (30). The clearance must be between 0.5 mm (0.0197 in.) and 4.5 mm (0.1772 in.).
(45) Measure the clearance at the inboard and outboard edges of the pressure-relief panels (9) and (30). The clearance must be between 0.5 mm (0.0197 in.) and 5.5 mm (0.2165 in.).
(46) At the trailing edges of the pressure-relief (9) and (30), measure the clearance between:
- the wing-skin and the edges of the panel (that are parallel to the panel leading edges), the clearance must be between 0.5 mm (0.0197 in.) and 5.5 mm (0.2165 in.)
- the wing-skin and the edges of the panel cut-outs (that are not parallel to the leading edges), the clearance must be between 0.5 mm (0.0197 in.) and 7.0 mm (0.2756 in.).
B. Seal Installation
Leading Edge Pressure-Relief Panel - Trailing Edge Gap-Seal - Location and Detail ** ON A/C NOT FOR ALL
(2) Apply TAPE - MASKING around the edges of the area to be filled.
(3) Use a SPATULA - NON METALLIC or GUN - SEALANT, EXTRUSION to insert Polysulfide Sealant-Fuel Tank Fillet - (Material No.06ABB1) or Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) into the applicable prepared area.
(4) Use a non-metallic scraper to remove unwanted sealant before it cures.
(5) Let the sealant cure (refer to the manufacturers instructions).
(6) Make sure the surface of the seal is flush with the surfaces of the applicable pressure-relief panel (9) and/or (30) and the wing skin.
(7) Remove the masking tape from the area around the seal.
(8) Remove the applicable bolts (10) and/or (28).
(9) Remove the applicable pressure-relief panel (9) and/or (30). Use a CUP - SUCTION if necessary.
(10) Examine the seal to make sure that:
(a) Use a SCRAPER - NON METALLIC to remove the seal.
(b) Do again steps (1) thru (11).
(12) Apply talcum powder Testing Medium-Fuel Leak Detection White Powder - (Material No.14CDB1) to the mating surface of the seal.
(13) Install the applicable pressure-relief panel (9) and/or (30) with the applicable bolts (10) and/or (28).
5. Close-up Leading Edge Pressure-Relief Panel - Trailing Edge Gap-Seal - Location and Detail ** ON A/C NOT FOR ALL NOTE: The procedure that follows can be done at the subsequent servicing interval.
NOTE: Seal only the clearance between the trailing edge of the pressure-relief panels and the wing skin.
(1) Fully degrease the area to be filled with a Textile-Lint free Cotton - (Material No.14SBA1) , made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) . (2) Apply TAPE - MASKING around the edges of the area to be filled.
(3) Use a SPATULA - NON METALLIC or GUN - SEALANT, EXTRUSION to insert Polysulfide Sealant-Fuel Tank Fillet - (Material No.06ABB1) or Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) into the applicable prepared area.
(4) Use a non-metallic scraper to remove unwanted sealant before it cures.
(5) Let the sealant cure (refer to the manufacturers instructions).
(6) Make sure the surface of the seal is flush with the surfaces of the applicable pressure-relief panel (9) and/or (30) and the wing skin.
(7) Remove the masking tape from the area around the seal.
(8) Remove the applicable bolts (10) and/or (28).
(9) Remove the applicable pressure-relief panel (9) and/or (30). Use a CUP - SUCTION if necessary.
(10) Examine the seal to make sure that:
- there is a full strip of sealant along the trailing edge of the panel opening
- there are no bubbles or spaces in the sealant
- no parts of the seal are loose.
(a) Use a SCRAPER - NON METALLIC to remove the seal.
(b) Do again steps (1) thru (11).
(12) Apply talcum powder Testing Medium-Fuel Leak Detection White Powder - (Material No.14CDB1) to the mating surface of the seal.
(13) Install the applicable pressure-relief panel (9) and/or (30) with the applicable bolts (10) and/or (28).
Subtask 57-41-37-865-058-A
A. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 57-41-37-942-053-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 | 5CV | B06 |
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 | 5CV | B01 |
| ** ON A/C ALL | |||
| 121VU | FLIGHT CONTROLS/SLT/CTL/SYS2 | 7CV | R21 |
B. Removal of Equipment
(1) Remove the access platform(s).
(2) Remove the WARNING NOTICE(S).
(3) 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 ground support and maintenance equipment, the special and standard tools and all other items.