W DOC AIRBUS | AMM A320F

Repair to the Leading Edge Pressure-Relief Panel After it has Operated

TASK 57-41-37-350-004-A
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.
MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAN CAUSE DAMAGE TO THE EQUIPMENT.
1. Reason for the Job
Self 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)
 B. Consumable Materials
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 -
 C. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
522XB, 522YB, 622XB, 622YB
522AB, 622AB
 D. Expendable Parts
FIG.ITEM
DESIGNATION
IPC-CSN
140
SEAL
AIPC 57-41-37-04-210
 E. Referenced Information
REFERENCE
DESIGNATION
SRM 514211
SRM 514411
SRM 574118
SRM 574126
F Leading Edge Pressure-Relief Panels - Details
F Leading Edge Pressure-Relief Panel 522AB(622AB) - Location and Detail ** ON A/C NOT FOR ALL
F Typical Leading Edge Pressure-Relief Panel End Step Tolerance - Details ** ON A/C NOT FOR ALL
F Typical Leading Edge Pressure-Relief Panel End Step Tolerance - Details ** ON A/C NOT FOR ALL
F Leading Edge Pressure-Relief Panels 522XB(622XB) and 522YB(522YB) - Location and Detail ** ON A/C NOT FOR ALL
F Leading Edge Pressure-Relief Panels - Seal Location
F Leading Edge Pressure-Relief Panel - Trailing Edge Gap-Seal - Location and Detail ** ON A/C NOT FOR ALL
3. Job Set-up
Subtask 57-41-37-941-056-A ** ON A/C NOT FOR ALL
A. Job Set-up
   (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 panel 522AB( 622AB).
Subtask 57-41-37-941-056-B ** ON A/C NOT FOR ALL
A. Job Set-up
   (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 522XB( 622XB) and 522YB( 622YB).
Subtask 57-41-37-865-063-A
B. Open, safety and tag this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/SLT/CTL AND MONG/SYS15CVB06
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/SLT/CTL AND MONG/SYS15CVB01
** ON A/C ALL
121VUFLIGHT CONTROLS/SLT/CTL/SYS27CVR21
4. Procedure
Subtask 57-41-37-350-054-E ** ON A/C NOT FOR ALL
A. Repair of the Leading Edge Pressure-Relief Panel 522AB(622AB) After it has Operated
   (1) Remove the bolts (80).
   (2) Carefully remove the pressure-relief panel 522AB(622AB) (79).
   (3) When you remove the pressure-relief panel (79), a part of the landing (73) will fall. Make a note of the position of this and keep it landing for later assembly.
NOTE: The two parts of the landings (71), (77) and (88) are connected with lanyards.
   (4) Remove the nuts (70) and the bolts (87) SRM 514211.
   (5) Remove the landing (88).
   (6) Remove the nuts (72) and the bolts (85) SRM 514211.
   (7) Remove the landing (71).
   (8) Remove the nuts (76) and the bolts (75) SRM 514211.
   (9) Remove the landing (77).
   (10) Remove bolts (74) and (84) SRM 514211.
   (11) Remove the landing (73).
   (12) Remove and discard the rivets (78) SRM 514211.
   (13) Remove and discard the forward angle (82).
   (14) Remove and discard the rivets (83) SRM 514211.
   (15) Remove and discard the forward angle (86).
   (16) 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 (81)
  • the landings (71), (73), (77) and (88)
  • the landing (71), (73), (77) and (88) interfaces and the adjacent areas.
   (17) Examine the two parts of the landings (71), (73), (77) and (88) for damage, discard those that are damaged.
   (18) Assemble the landings (71), (73), (77) and (88) 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).
   (19) Examine the pressure-relief panel (79) for damage. Discard it if it is damaged.
   (20) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (82) SRM 574118.
   (21) Install the rivets (132) SRM 514211.
   (22) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the forward angle (82) and the forward sub-spar (81).
   (23) Put the forward angle (82) in position on the forward sub-spar (81). Install the rivets (78) SRM 514211.
   (24) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (86) SRM 574118.
   (25) Install the rivets (132) SRM 514211.
   (26) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the forward angle (86) and the forward sub-spar (81).
   (27) Put the forward angle (86) in position on the forward sub-spar (81). Install the rivets (83) SRM 514211.
   (28) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (71) and the aircraft structure.
   (29) Put the landing (71) in position.
   (30) Install the bolts (85) and the nuts (72) SRM 514211.
   (31) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (73) and the aircraft structure.
   (32) Put the landing (73) in position.
   (33) Install the bolts (74) and (84) SRM 514211.
   (34) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (77) and the aircraft structure.
   (35) Put the landing (77) in position.
   (36) Install the bolts (75) and the nuts (76) SRM 514211.
   (37) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (88) and the aircraft structure.
   (38) Put the landing (88) in position.
   (39) Install the bolts (87) and the nuts (70) SRM 514211.
   (40) Examine the seals (140) around the pressure-relief panel (79) for damage and correct condition. Replace damaged seals as follows:
F Leading Edge Pressure-Relief Panels - Seal Location ** ON A/C NOT FOR ALL
     (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 57-41-37-04-210 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.).
   (41) Make sure that the work area is clean and clear of tools and other items.
   (42) Put the pressure-relief panel (79) in position and install the bolts (80).
   (43) Measure the into/out of wind step tolerances of the pressure-relief panel (79) 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).
     (b) For the panel trailing edge:
   (44) Measure the step tolerances of the pressure-relief panel ends across the line of flight. These must be as follows:
     (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).
   (45) If an into/out of wind step or an end step is not in tolerance, continue as follows:
     (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 bolts (80) and the pressure-relief panel (79).
     (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 pressure-relief panel (79) with the bolts (80).
     (i) Do again step (43) and step (44).
   (46) Measure the gap between the D-nose skin and the leading edge of the pressure-relief panel (79). The gap must be between 0.5 mm (0.0197 in.) and 4.5 mm (0.1772 in.).
   (47) Measure the gap at the inboard and outboard edges of the pressure-relief panel (79). The gap must be between 0.5 mm (0.0197 in.) and 5.5 mm (0.2165 in.).
   (48) At the trailing edge of the pressure-relief panel (79), measure the gap between:
  • the wing-skin and the edge of the panel (that is parallel to the panel leading edge), the gap must be between 0.5 mm (0.0197 in.) and 5.5 mm (0.2165 in.)
  • the wing-skin and the edge of the panel cut-outs (that are not parallel to the panel leading edge), the gap must be between 0.5 mm (0.0197 in.) and 7.0 mm (0.2756 in.).
Subtask 57-41-37-350-054-F ** ON A/C NOT FOR ALL
A. Repair of the Leading Edge Pressure-Relief Panel 522AB(622AB) After it has Operated
   (1) Remove the bolts (80).
   (2) Carefully remove the pressure-relief panel 522AB(622AB) (79).
   (3) When you remove the pressure-relief panel (79), a part of the landing (73) will fall. Make a note of the position of this and keep it landing for later assembly.
NOTE: The two parts of the landings (71), (77) and (88) are connected with lanyards.
   (4) Remove the nuts (70) and the bolts (87) SRM 514211.
   (5) Remove the landing (88).
   (6) Remove the nuts (72) and the bolts (85) SRM 514211.
   (7) Remove the landing (71).
   (8) Remove the nuts (76) and the bolts (75) SRM 514211.
   (9) Remove the landing (77).
   (10) Remove bolts (74) and (84) SRM 514211.
   (11) Remove the landing (73).
   (12) Remove and discard the rivets (78) SRM 514211.
   (13) Remove and discard the forward angle (82).
   (14) Remove and discard the rivets (83) SRM 514211.
   (15) Remove and discard the forward angle (86).
   (16) 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 (81)
  • the landings (71), (73), (77) and (88)
  • the landing (71), (73), (77) and (88) interfaces and the adjacent areas.
   (17) Examine the two parts of the landings (71), (73), (77) and (88) for damage. Discard those that are damaged.
   (18) Assemble the landings (71), (73), (77) and (88) 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).
   (19) Examine the pressure-relief panel (79) for damage. Discard it if it is damaged.
   (20) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (82) SRM 574118.
   (21) Install the rivets (132) SRM 514211.
   (22) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the forward angle (82) and the forward sub-spar (81).
   (23) Put the forward angle (82) in position on the forward sub-spar (81). Install the rivets (78) SRM 514211.
   (24) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (86) SRM 574118.
   (25) Install the rivets (132) SRM 514211.
   (26) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the forward angle (86) and the forward sub-spar (81).
   (27) Put the forward angle (86) in position on the forward sub-spar (81). Install the rivets (83) SRM 514211.
   (28) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (71) and the aircraft structure.
   (29) Put the landing (71) in position.
   (30) Install the bolts (85) and the nuts (72) SRM 514211.
   (31) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (73) and the aircraft structure.
   (32) Put the landing (73) in position.
   (33) Install the bolts (74) and (84) SRM 514211.
   (34) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (77) and the aircraft structure.
   (35) Put the landing (77) in position.
   (36) Install the bolts (75) and the nuts (76) SRM 514211.
   (37) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the mating faces of the landing (88) and the aircraft structure.
   (38) Put the landing (88) in position.
   (39) Install the bolts (87) and the nuts (70) SRM 514211.
   (40) Examine the seals (140) around the pressure-relief panel (79) for damage and correct condition. Replace damaged seals as follows:
F Leading Edge Pressure-Relief Panels - Seal Location ** ON A/C NOT FOR ALL
     (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 57-41-37-04-210 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.).
   (41) Make sure that the work area is clean and clear of tools and other items.
   (42) Apply release agent, Release Agent-- Water Base - (Material No.14DAB1) to the trailing edge of the pressure-relief panel (79).
   (43) Put the pressure-relief panel (79) in position and install the bolts (80).
   (44) Measure the into/out of wind step tolerances of the pressure-relief panel (79) 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).
     (b) For the panel trailing edge:
   (45) Measure the step tolerances of the pressure-relief panel ends across the line of flight. These must be as follows:
     (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).
   (46) If an into/out of wind step or an end step is not in tolerance, continue as follows:
     (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 bolts (80) and the pressure-relief panel (79).
     (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 pressure-relief panel (79) with the bolts (80).
     (i) Do again step (43) and step (44).
   (47) Measure the gap between the D-nose skin and the leading edge of the pressure-relief panel (79). The gap must be between 0.5 mm (0.0197 in.) and 4.5 mm (0.1772 in.).
   (48) Measure the gap at the inboard and outboard edges of the pressure-relief panel (79). The gap must be between 0.5 mm (0.0197 in.) and 5.5 mm (0.2165 in.).
   (49) At the trailing edge of the pressure-relief panel (79), measure:
  • the gap between the wing-skin and the edge of the panel.
The gap must not be less than 0.5 mm (0.0197 in.).
Subtask 57-41-37-350-054-H ** ON A/C NOT FOR ALL
A. Repair of the Leading Edge Pressure-Relief Panel 522AB(622AB) After it has Operated
   (1) Remove the bolts (80).
   (2) Carefully remove the pressure-relief panel 522AB(622AB) (79).
   (3) When you remove the pressure-relief panel (79), a part of the landing (73) will fall. Make a note of the position of this and keep it landing for later assembly.
NOTE: The two parts of the landings (71), (77) and (88) are connected with lanyards.
   (4) Remove the nuts (70) and the bolts (87) SRM 514211.
   (5) Remove the landing (88).
   (6) Remove the nuts (72) and the bolts (85) SRM 514211.
   (7) Remove the landing (71).
   (8) Remove the nuts (76) and the bolts (75) SRM 514211.
   (9) Remove the landing (77).
   (10) Remove bolts (74) and (84) SRM 514211.
   (11) Remove the landing (73).
   (12) Remove and discard the rivets (78) SRM 514211.
   (13) Remove and discard the forward angle (82).
   (14) Remove and discard the rivets (83) SRM 514211.
   (15) Remove and discard the forward angle (86).
   (16) 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 (81)
  • the landings (71), (73), (77) and (88)
  • the landing (71), (73), (77) and (88) interfaces and the adjacent areas.
   (17) Examine the two parts of the landings (71), (73), (77) and (88) for damage, discard those that are damaged.
   (18) Assemble the landings (71), (73), (77) and (88) 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).
   (19) Examine the pressure-relief panel (79) for damage. Discard it if it is damaged.
   (20) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (82) SRM 574118.
   (21) Install the rivets (132) SRM 514211.
   (22) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the forward angle (82) and the forward sub-spar (81).
   (23) Put the forward angle (82) in position on the forward sub-spar (81). Install the rivets (78) SRM 514211.
   (24) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (86) SRM 574118.
   (25) Install the rivets (132) SRM 514211.
   (26) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the forward angle (86) and the forward sub-spar (81).
   (27) Put the forward angle (86) in position on the forward sub-spar (81). Install the rivets (83) SRM 514211.
   (28) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the landing (71) and the aircraft structure.
   (29) Put the landing (71) in position.
   (30) Install the bolts (85) and the nuts (72) SRM 514211.
   (31) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the landing (73) and the aircraft structure.
   (32) Put the landing (73) in position.
   (33) Install the bolts (74) and (84) SRM 514211.
   (34) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the landing (77) and the aircraft structure.
   (35) Put the landing (77) in position.
   (36) Install the bolts (75) and the nuts (76) SRM 514211.
   (37) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the landing (88) and the aircraft structure.
   (38) Put the landing (88) in position.
   (39) Install the bolts (87) and the nuts (70) SRM 514211.
   (40) Examine the seals (140) around the pressure-relief panel (79) for damage and correct condition. Replace damaged seals as follows:
F Leading Edge Pressure-Relief Panels - Seal Location ** ON A/C NOT FOR ALL
     (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 57-41-37-04-210 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.).
   (41) Make sure that the work area is clean and clear of tools and other items.
   (42) Put the pressure-relief panel (79) in position and install the bolts (80).
   (43) Measure the into/out of wind step tolerances of the pressure-relief panel (79) 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).
     (b) For the panel trailing edge:
   (44) Measure the step tolerances of the pressure-relief panel ends across the line of flight. These must be as follows:
     (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).
   (45) If an into/out of wind step or an end step is not in tolerance, continue as follows:
     (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 bolts (80) and the pressure-relief panel (79).
     (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 pressure-relief panel (79) with the bolts (80).
     (i) Do again step (43) and step (44).
   (46) Measure the gap between the D-nose skin and the leading edge of the pressure-relief panel (79). The gap must be between 0.5 mm (0.0197 in.) and 4.5 mm (0.1772 in.).
   (47) Measure the gap at the inboard and outboard edges of the pressure-relief panel (79). The gap must be between 0.5 mm (0.0197 in.) and 5.5 mm (0.2165 in.).
   (48) At the trailing edge of the pressure-relief panel (79), measure the gap between:
  • the wing-skin and the edge of the panel (that is parallel to the panel leading edge), the gap must be between 0.5 mm (0.0197 in.) and 5.5 mm (0.2165 in.)
  • the wing-skin and the edge of the panel cut-outs (that are not parallel to the panel leading edge), the gap must be between 0.5 mm (0.0197 in.) and 7.0 mm (0.2756 in.).
Subtask 57-41-37-350-054-I ** ON A/C NOT FOR ALL
A. Repair of the Leading Edge Pressure-Relief Panels 522XB(622XB) and 522YB(622YB) After it has Operated
   (1) Remove the bolts (80), (89) and (90).
   (2) Carefully remove the pressure-relief panels 522XB( 622XB) (92) and 522YB( 622YB) (79).
   (3) When you remove the pressure-relief panels (79) and (92), a part of the landing (73) will fall. Make a note of the position of this and keep it landing for later assembly.
NOTE: The two parts of the landings (71), (77) and (88) are connected with lanyards.
   (4) Remove the nuts (70) and the bolts (87) SRM 514211.
   (5) Remove the landing (88).
   (6) Remove the nuts (72) and the bolts (85) SRM 514211.
   (7) Remove the landing (71).
   (8) Remove the nuts (76) and the bolts (75) SRM 514211.
   (9) Remove the landing (77).
   (10) Remove bolts (74) and (84) SRM 514211.
   (11) Remove the landing (73).
   (12) Remove and discard the rivets (78) SRM 514211.
   (13) Remove and discard the forward angle (82).
   (14) Remove and discard the rivets (83) SRM 514211.
   (15) Remove and discard the forward angle (86).
   (16) Remove and discard the rivets (93) SRM 514211.
   (17) Remove and discard the forward angle (91).
   (18) Clean these items with the Textile-Lint free Cotton - (Material No.14SBA1) made moist with the Non Aqueous Cleaner-General - - (Material No.08BAA9) :
  • the forward sub-spar (81)
  • the landings (71), (73), (77) and (88)
  • the landing (71), (73), (77) and (88) interfaces and the adjacent areas.
   (19) Examine the two parts of the landings (71), (73), (77) and (88) for damage. Discard those that are damaged.
   (20) Assemble the landings (71), (73), (77) and (88) 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).
   (21) Examine the pressure-relief panels (79) and (92) for damage. Discard them if they are damaged.
   (22) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (82) SRM 574118.
   (23) Install the rivets (132) SRM 514211.
   (24) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the forward angle (82) and the forward sub-spar (81).
   (25) Put the forward angle (82) in position on the forward sub-spar (81).
   (26) Install the rivets (78) SRM 514211.
   (27) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (86) SRM 574118.
   (28) Install the rivets (132) SRM 514211.
   (29) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the forward angle (86) and the forward sub-spar (81).
   (30) Put the forward angle (86) in position on the forward sub-spar (81). Install the rivets (83) SRM 514211.
   (31) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (91) SRM 574118.
   (32) Install the rivets (132) SRM 514211.
   (33) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the forward angle (91) and the forward sub-spar (81).
   (34) Put the forward angle (91) in position on the forward sub-spar (81).
   (35) Install the rivets (93) SRM 514211.
   (36) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the landing (71) and the aircraft structure.
   (37) Put the landing (71) in position.
   (38) Install the bolts (85) and the nuts (72) SRM 514211.
   (39) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the landing (73) and the aircraft structure.
   (40) Put the landing (73) in position.
   (41) Install the bolts (74) and (84) SRM 514211.
   (42) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the landing (77) and the aircraft structure.
   (43) Put the landing (77) in position.
   (44) Install the bolts (75) and the nuts (76) SRM 514211.
   (45) Apply Polysulfide Sealant-Fuel Tank Fillet 120 degre Celsius (Material No.06ABB2) to the mating faces of the landing (88) and the aircraft structure.
   (46) Put the landing (88) in position.
   (47) Install the bolts (87) and the nuts (70) SRM 514211.
   (48) Examine the seals (140) around the pressure-relief panels (79) and (92) for damage and correct condition. Replace damaged seals as follows:
F Leading Edge Pressure-Relief Panels - Seal Location ** ON A/C NOT FOR ALL
     (a) Remove the damaged length of seal (140) with a SCRAPER - NON METALLIC.
     (b) Clean the applicable area of the panel with the Textile-Lint free Cotton - (Material No.14SBA1) made moist with the Non Aqueous Cleaner-General - - (Material No.08BAA9)
     (c) Cut to length a new AIPC 57-41-37-04-210 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.).
   (49) Make sure that the work area is clean and clear of tools and other items.
   (50) Apply release agent, Release Agent-- Water Base - (Material No.14DAB1) to the trailing edge of the pressure-relief panels (79) and (92).
   (50) Put the pressure-relief panels (79) and (92) in position and install the bolts (80).
   (51) Measure the into/out of wind step tolerances of the pressure-relief panels (79) and (92) 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).
     (b) For the panel trailing edge:
   (52) Measure the step tolerances of the pressure-relief panel ends across the line of flight. These must be as follows:
     (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).
   (53) If an into/out of wind step or an end step is not in tolerance, continue as follows:
     (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 bolts (80), (89) and (90) and the pressure-relief panels (79) and (92).
     (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 pressure-relief panels (79) and (92) with the bolts (80), (89) and (90).
     (i) Do again step (51) and step (52).
   (54) Measure the gap between the D-nose skin and the leading edge of the pressure-relief panels (79) and (92). The gap must be between 0.5 mm (0.0197 in.) and 4.5 mm (0.1772 in.).
   (55) Measure the gap at the inboard and outboard edges of the pressure-relief panels (79) and (92). The gap must be between 0.5 mm (0.0197 in.) and 5.5 mm (0.2165 in.).
   (56) At the trailing edge of the pressure-relief panels (79) and (92), measure:
  • the gap between the wing-skin and the edge of the panel.
The gap must not be less than 0.5 mm (0.0197 in.).
Subtask 57-41-37-390-053-A ** ON A/C NOT FOR ALL
B. Seal Installation
F Leading Edge Pressure-Relief Panel - Trailing Edge Gap-Seal - Location and Detail ** ON A/C NOT FOR ALL
NOTE: Seal only the gap between the trailing edge of the pressure-relief panels and the wing skin.
   (1) Degrease the area to be filled fully 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 gap 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 gap.
   (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 pressure-relief panel (79) and the wing skin.
   (7) Remove the masking tape from the area around the seal.
   (8) Remove the bolts (80).
   (9) Remove the pressure-relief panel (79). 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.
   (11) If there are bubbles or spaces in the sealant, or the seal does not make a full strip, or the seal is loose do as follows:
  • use a SCRAPER - NON METALLIC to remove the seal
  • repeat steps (1) thru (11).
   (12) Apply Testing Medium-Fuel Leak Detection White Powder - (Material No.14CDB1) to the mating surface of the seal.
   (13) Install the pressure-relief panel (79) with the bolts (80).
5. Close-up
Subtask 57-41-37-865-064-A
A. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/SLT/CTL AND MONG/SYS15CVB06
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/SLT/CTL AND MONG/SYS15CVB01
** ON A/C ALL
121VUFLIGHT CONTROLS/SLT/CTL/SYS27CVR21
Subtask 57-41-37-942-056-A
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.
[Rev.10 from 2021] 2026.04.02 06:31:03 UTC
"WTRUIB" 2025