Installation of the Pressure Relief Panels

TASK 57-41-37-400-002-A
Installation of the Pressure Relief Panels

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.

MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAN CAUSE DAMAGE TO THE EQUIPMENT.

ZONE: 521
ZONE: 522
ZONE: 621
ZONE: 622

1. Reason for the Job
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE
No specific	AR	SAFETY BARRIER(S)
No specific	1	SCRAPER - NON METALLIC
No specific	AR	WARNING NOTICE(S)
No specific	Torque wrench: range to between 0.5 and 0.45 m.daN (44.25 and 39.82 lbf.in )
98D27803000000	1	LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.06AAB1)	Polysulfide Sealant-General Purpose Fillet -
(Material No.06ABA1)	Polysulfide Sealant-Fuel Tank Brushable -
(Material No.08BAA9)	Non Aqueous Cleaner-General - -
(Material No.14DBB1)	Release Agent-- Liquid Wax -
(Material No.14SBA1)	Textile-Lint free Cotton -
No specific	talcum powder

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
521	INBOARD FIXED L.E STRUCTURE
522	OUTBOARD FIXED L.E STRUCTURE
621	INBOARD FIXED L.E STRUCTURE
622	OUTBOARD FIXED L.E STRUCTURE
521AB, 521CB, 521EB, 522CB, 621AB, 621CB, 621EB, 622CB
522XB, 522YB, 622XB, 622YB
522AB, 622AB

D. Referenced Information

REFERENCE	DESIGNATION
TASK 27-80-00-866-004-A	Extending the Slats on the Ground
TASK 27-80-00-866-005-A	Retracting the Slats on the Ground
TASK 27-80-00-866-007-A	Manual Extension of the Slats
TASK 27-80-00-866-008-A	Manual Retraction of the Slats
TASK 57-41-37-000-004-A	Removal of the Pressure Relief Panels
TASK 57-41-37-350-001-A	Repair to the Leading Edge Pressure-Relief Panel After it has Operated
Pressure-Relief Panels - Location and Details ** ON A/C NOT FOR ALL
Typical Leading Edge Panels - Tolerances
Pressure-Relief Panels - Location and Details ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 57-41-37-941-063-A

A. Safety Precautions
(1) Make sure that the SAFETY BARRIER(S) are in position.
(2) Make sure that the slats are fully extended (Ref. AMM TASK 27-80-00-866-004) or (Ref. AMM TASK 27-80-00-866-007).
(3) Make sure that the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION is installed on the flap/slat control lever.
(4) Make sure that the WARNING NOTICE(S) is(are) in position in the cockpit to tell persons not to operate the slats.
(5) Make sure that the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE is in position below the applicable pressure-relief panel.

Subtask 57-41-37-865-073-A

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

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

4. Procedure
Subtask 57-41-37-210-058-C ** ON A/C NOT FOR ALL

A. Preparation for Installation
(1) Do an inspection of the sealant between the trailing edge of the panel and the forward edge of the wing skin.
(2) If there is damage to the sealant, do the steps that follow:
(a) Use a SCRAPER - NON METALLIC and a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean:

the trailing edge of the panel
the forward edge of the bottom wing skin.

(b) Apply Release Agent-- Liquid Wax - (Material No.14DBB1) to the trailing edge of the panel.

Subtask 57-41-37-420-055-C ** ON A/C NOT FOR ALL

B. Installation of the Pressure Relief Panels 521AB( 621AB), 521CB( 621CB), 521EB( 621EB), 522XB( 622XB), 522YB( 622YB) and 522CB( 622CB)

NOTE: On many pressure relief panels, the screws that hold the panel have different lengths. The record that you made during the removal procedure will help you install the screws correctly.

(1) For the pressure relief panel 521AB( 621AB):
(a) Hold the pressure relief panel (1) and install the screws (2).
(b) TORQUE the screws (2) to between 0.5 and 0.45 m.daN (44.25 and 39.82 lbf.in )

.
(2) For the pressure relief panel 521CB( 621CB):
(a) Hold the pressure relief panel (6) and install the screws (7).
(b) TORQUE the screws (7) to between 0.5 and 0.45 m.daN (44.25 and 39.82 lbf.in )

.
(3) For the pressure relief panel 521EB( 621EB):
(a) Hold the pressure relief panel (3) and install the screws (4) and (5).
(b) TORQUE the screws (4) and (5) to between 0.5 and 0.45 m.daN (44.25 and 39.82 lbf.in )

.
(4) For the pressure relief panel 522XB( 622XB):
(a) Hold the pressure relief panel (8) and install the screws (9) and (10).
(b) TORQUE the screws (9) and (10) to between 0.5 and 0.45 m.daN (44.25 and 39.82 lbf.in )

.
(5) For the pressure relief panel 522YB( 622YB):
(a) Hold the pressure relief panel (11) and install the screws (12).
(b) TORQUE the screws (12) to between 0.5 and 0.45 m.daN (44.25 and 39.82 lbf.in )

.
(6) For the pressure relief panel 522CB( 622CB):
(a) Hold the pressure relief panel (13) and install the screws (14) and (15).
(b) TORQUE the screws (14) and (15) to between 0.5 and 0.45 m.daN (44.25 and 39.82 lbf.in )

Subtask 57-41-37-420-055-D ** ON A/C NOT FOR ALL

B. Installation of the Pressure Relief Panels 521AB( 621AB), 521CB( 621CB), 521EB( 621EB), 522AB( 622AB) and 522CB( 622CB)

NOTE: On many pressure relief panels, the screws that hold the panel have different lengths. The record that you made during the removal procedure will help you install the screws correctly.

(1) For the pressure relief panel 521AB( 621AB):
(a) Hold the pressure relief panel (1) and install the screws (2).
(b) TORQUE the screws (2) to between 0.5 and 0.45 m.daN (44.25 and 39.82 lbf.in )

.
(2) For the pressure relief panel 521CB( 621CB):
(a) Hold the pressure relief panel (6) and install the screws (7).
(b) TORQUE the screws (7) to between 0.5 and 0.45 m.daN (44.25 and 39.82 lbf.in )

.
(4) For the pressure relief panel 522AB( 622AB):
(a) Hold the pressure relief panel (8) and install the screws (9) and (10).
(b) TORQUE the screws (9) and (10) to between 0.5 and 0.45 m.daN (44.25 and 39.82 lbf.in )

.
(5) For the pressure relief panel 522CB( 622CB):
(a) Hold the pressure relief panel (11) and install the screws (12) and (13).
(b) TORQUE the screws (12) and (13) to between 0.5 and 0.45 m.daN (44.25 and 39.82 lbf.in )

Subtask 57-41-37-420-055-E ** ON A/C NOT FOR ALL

B. Installation of the Pressure Relief Panels 521AB( 621AB), 521CB( 621CB), 521EB( 621EB), 522AB( 622AB) and 522CB( 622CB)

NOTE: On many pressure relief panels, the screws that hold the panel have different lengths. The record that you made during the removal procedure will help you install the screws correctly.

(1) For the pressure relief panel 521AB( 621AB):
(a) Hold the pressure relief panel (1) and install the screws (2).
(b) TORQUE the screws (2) to between 0.5 and 0.45 m.daN (44.25 and 39.82 lbf.in )

.
(2) For the pressure relief panel 521CB( 621CB):
(a) Hold the pressure relief panel (6) and install the screws (7).
(b) TORQUE the screws (7) to between 0.5 and 0.45 m.daN (44.25 and 39.82 lbf.in )

Subtask 57-41-37-390-055-A ** ON A/C NOT FOR ALL

C. Sealant
(1) If the sealant between the trailing edge of the panel and the forward edge of the wing skin was removed, do the steps that follow:
(a) Apply Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) or Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) to the interface between the trailing edge of the panel and the forward edge of the wing skin (Ref. AMM TASK 57-41-37-350-001).
(b) Let the sealant go hard then carefully remove the applicable panel (Ref. AMM TASK 57-41-37-000-004).
(c) Apply talcum powder to the sealant mating surfaces and install the panel (refer to Para. 4B.).
(2) Make sure that the work area is clean and clear of tools and other items.

Subtask 57-41-37-866-051-A

D. Retraction of the Slats
(1) Retract the slats (Ref. AMM TASK 27-80-00-866-005) or (Ref. AMM TASK 27-80-00-866-008).

Subtask 57-41-37-220-050-B ** ON A/C NOT FOR ALL

E. Dimensional Checks
(1) Measure the into/out of wind step tolerances of the pressure-relief panels across the line of flight. These must be as follows:
(a) For the panel leading edge:

maximum 0.3 mm (0.0118 in.) above wing surface (into wind)
maximum 0.6 mm (0.0236 in.) below wing surface (out of wind).

(b) For the panel trailing edge:

maximum 0.3 mm (0.0118 in.) below wing surface (into wind)
maximum 1.0 mm (0.0394 in.) above wing surface (out of wind).

(2) 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).

(3) Measure the clearance between the D-nose skin and the leading edges of the pressure-relief panels. The clearance must be between 0.5 mm (0.0197 in.) and 4.5 mm (0.1772 in.).
(4) Measure the clearance at the inboard and outboard edges of the pressure-relief panels. The clearance must be between 0.5 mm (0.0197 in.) and 3.5 mm (0.1378 in.).
(5) Measure the clearance at the trailing edges of the pressure-relief panels between:

the wing-skin and the edges of the panels (that are parallel to the panel leading edges), the clearance must be between 0.5 mm (0.0197 in.) and 4.5 mm (0.1772 in.)
the wing-skin and the edges of the panel cut-outs (that are not parallel to the panel leading edges), the clearances must be between 0.5 mm (0.0197 in.) and 5.5 mm (0.2165 in.).

Subtask 57-41-37-220-050-C ** ON A/C NOT FOR ALL

E. Dimensional Checks
(1) Measure the into/out of wind step tolerances of the pressure-relief panels 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:

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).

(2) 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 1.2 mm (0.0472 in.) above or below the adjacent panel end (DIM X)
maximum 1.2 mm (0.0472 in.) above or below the adjacent wing surface (DIM Y).

(3) Measure the clearance between the D-nose skin and the leading edges of the pressure-relief panels. The clearance must be between 0.5 mm (0.0197 in.) and 4.5 mm (0.1772 in.).
(4) Measure the clearance at the inboard and outboard edges of the pressure-relief panels. The clearance must be between 0.5 mm (0.0197 in.) and 5.5 mm (0.2165 in.).
(5) Measure the clearance at the trailing edges of the pressure-relief panels between:

the wing-skin and the edges of the panels (that are parallel to the panel leading edges), the minimum clearance must be 0.5 mm (0.0197 in.)
the wing-skin and the edges of the panel cut-outs (that are not parallel to the panel leading edges), the clearances must be between 0.5 mm (0.0197 in.) and 7.0 mm (0.2756 in.).

5. Close-up
Subtask 57-41-37-410-072-A

A. Close Access
(1) Remove the access platform(s).

Subtask 57-41-37-865-074-A

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	FLIGHT CONTROLS/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 57-41-37-942-060-A

C. Removal of Equipment
(1) Remove the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION from the flap/slat control lever.
(2) Remove the WARNING NOTICE(S).
(3) Remove the SAFETY BARRIERS.
(4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

[Rev.10 from 2021] 2026.04.01 02:13:12 UTC