Closing/Installation of the Trailing Edge Access-Panels of the Vertical Stabilizer

TASK 55-33-13-410-002-A
Closing/Installation of the Trailing Edge Access-Panels of the Vertical Stabilizer

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.

WARNING: BEFORE YOU START WORK, YOU MUST PUT ON A SAFETY HARNESS AND ATTACH IT TO THE ACCESS PLATFORM. WITHOUT A SAFETY HARNESS, YOU CAN FALL. THIS CAN KILL YOU OR CAUSE YOU INJURY.

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

ZONE: 325

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 12M (40 FT) - ADJUSTABLE
No specific	1	SCRAPER - NON METALLIC
No specific	1	WARNING NOTICE(S)
No specific	Torque wrench: range to between 0.3 and 0.27 m.daN (26.55 and 23.89 lbf.in )
No specific	Torque wrench: range to between 0.35 and 0.3 m.daN (30.97 and 26.55 lbf.in )

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.06AAA1)	Polysulfide Sealant_General Purpose Brushable -
(Material No.06AAB1)	Polysulfide Sealant-General Purpose Fillet -
(Material No.06AEA1)	Polysulfide Sealant-Low Adhesion Brushable -
(Material No.06LCB1)	Non Hardening Jointing Putty-Medium Temp. Area Chromate Free -
(Material No.08BBC1)	Non Aqueous Cleaner-- Naphta based and Alcohol -
(Material No.14DBB1)	Release Agent-- Liquid Wax -
(Material No.14SBA1)	Textile-Lint free Cotton -

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
325	VERTICAL STABILIZER TRAILING EDGE
325BL, 325BR, 325CL, 325CR, 325DL, 325EL, 325ER
325FR, 325GR
325DR

D. Referenced Information

REFERENCE	DESIGNATION
TASK 20-28-00-912-802-A	Electrical Bonding - General Maintenance Procedure
TASK 20-28-00-912-803-A	Bonding Surface Preparation
TASK 29-00-00-864-001-A	Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action
TASK 29-10-00-863-001-A	Pressurize the Green Hydraulic System with a Hydraulic Ground Power-Cart
TASK 29-10-00-863-002-A	Pressurize the Yellow Hydraulic System with a Hydraulic Ground Power-Cart
TASK 29-10-00-863-003-A	Pressurize the Blue Hydraulic System with a Hydraulic Ground Power-Cart
TASK 29-10-00-863-003-A-01	Pressurize the Blue Hydraulic System with the Blue Electric Pump
TASK 29-23-00-863-001-A	Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump
Trailing Edge Access-Panels ** ON A/C NOT FOR ALL
Trailing Edge Access-Panels - Clearances and Sealant Application ** ON A/C NOT FOR ALL
Trailing Edge Access-Panels of the Vertical Stabilizer ** ON A/C NOT FOR ALL
Trailing Edge Access-Panels - Clearances and Sealant Application ** ON A/C NOT FOR ALL
Trailing Edge Access-Panels ** ON A/C NOT FOR ALL
Trailing Edge Access-Panels ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 55-33-13-860-051-A

A. Aircraft Maintenance Configuration
(1) Make sure that the Green, Blue and Yellow hydraulic systems are depressurized (Ref. AMM TASK 29-00-00-864-001).
(2) Make sure that the rudder pedals are in the neutral position.
(3) Make sure that the WARNING NOTICE(S) is(are) in position to tell persons not to operate the flight controls.
(4) Make sure that the ACCESS PLATFORM 12M (40 FT) - ADJUSTABLE is in position below zone 325.

Subtask 55-33-13-865-057-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/ELAC1/NORM/SPLY	15CE1	B11
49VU	FLIGHT CONTROLS/THS/ACTR/MOT2	19CE2	B09
49VU	FLIGHT CONTROLS/SEC1/NORM/SPLY	21CE1	B08
49VU	AUTO FLT/FAC1/28VDC	5CC1	B04
49VU	AUTO FLT/FAC1/26VAC	14CC1	B03
** ON A/C NOT FOR ALL
49VU	FLIGHT CONTROLS/ELAC1/NORM/SPLY	15CE1	B06
49VU	FLIGHT CONTROLS/THS/ACTR/MOT2	19CE2	B04
49VU	FLIGHT CONTROLS/SEC1/NORM/SPLY	21CE1	B03
49VU	AUTO FLT/FAC1/28VDC	5CC1	H10
49VU	AUTO FLT/FAC1/26VAC	14CC1	H09
** ON A/C ALL
105VU	FLIGHT CONTROLS/ELAC2/STBY SPLY	16CE2	A02
105VU	FLT CTL/ELAC1/STBY SPLY	16CE1	A01
105VU	FLT CTL/SEC1/STBY SPLY	22CE	B01
121VU	AUTO FLT/RUDDER/TRIM/IND	15CC	M20
121VU	AUTO FLT/FAC2/28VDC	5CC2	M19
121VU	AUTO FLT/FAC2/26VAC	14CC2	M18
121VU	FLIGHT CONTROLS/SEC3/SPLY	21CE3	Q19
121VU	FLIGHT CONTROLS/SEC2/SPLY	21CE2	Q18
121VU	FLIGHT CONTROLS/THS ACTR/MOT3	19CE3	Q17
121VU	FLIGHT CONTROLS/THS ACTR/MOT1	19CE1	Q16
121VU	FLIGHT CONTROLS/ELAC2/NORM/SPLY	15CE2	R20

4. Procedure
Subtask 55-33-13-420-051-A ** ON A/C NOT FOR ALL

A. Closing and Installation of the Trailing Edge Access-Panels of the Vertical Stabilizer

Trailing Edge Access-Panels ** ON A/C NOT FOR ALL

NOTE: The vertical-stabilizer trailing-edge access-panels (1) are referred to in this procedure as "trailing edge access-panels” (1).

(1) Do a check of the condition of the sealant on the mating surfaces of the rudder hinge arms and the spar box flanges.
(2) Replace the sealant (21):
(a) Remove the sealant (21) from the mating surfaces of the rudder hinge arms and the spar box flanges with the SCRAPER - NON METALLIC.
(b) Clean the mating surfaces of the trailing edge access-panel (1), the rudder hinge arms and the spar box flanges with Non Aqueous Cleaner-- Naphta based and Alcohol - (Material No.08BBC1) and the Textile-Lint free Cotton - (Material No.14SBA1) .
(c) Apply Release Agent-- Liquid Wax - (Material No.14DBB1) on the mating surfaces of the trailing edge access-panel (1).
1 For access panels 325EL and 325ER:
a Do not apply release agent on the bonding points.
(d) Apply Polysulfide Sealant-Low Adhesion Brushable - (Material No.06AEA1) (21) on the mating surfaces of the rudder hinge arms and the spar box flanges.
1 For access panels 325EL and 325ER:
a Do not apply sealant on the bonding points.
(3) For access panels 325EL and 325ER:
(a) Prepare the surface of the bonding points at the studs (3), (5), (6), (7), (9) and (10) (Ref. AMM TASK 20-28-00-912-803).
(4) Close trailing edge access-panels 325BL, 325BR, 325CL, 325CR and 325DL (1):

NOTE: The closing procedure is given for one trailing edge access-panel (1). The closing procedure for the other trailing edge access-panels (1) is almost the same.

(a) Apply Non Hardening Jointing Putty-Medium Temp. Area Chromate Free - (Material No.06LCB1) on the fastener holes of the rudder hinge arms.
(b) Remove the quick-release pin (14).
(c) Slowly move the trailing edge access-panel (1) to the closed position until you can install the quick-release pin (14) in the pin stowage hole (13).
(d) Fully close the trailing edge access-panel (1).
(e) TORQUE the studs (2), (3) and (4) to between 0.3 and 0.27 m.daN (26.55 and 23.89 lbf.in )

CAUTION: BE CAREFUL WHEN YOU REMOVE OR INSTALL THESE ACCESS PANELS. IF YOU LET THEM FALL, DAMAGE CAN OCCUR TO THEM OR TO THE AIRCRAFT STRUCTURE.

(5) Install trailing edge access-panels 325EL, 325ER and 325DR (1):

NOTE: The installation procedure is given for one trailing edge access-panel (1). The installation procedure for the other trailing edge access-panels (1) is almost the same.

(a) Apply Polysulfide Sealant_General Purpose Brushable - (Material No.06AAA1) on the studs (2), (3), (4), (5), (6) and (8) and, if applicable, on the studs (7), (9) and (10).
(b) Put the trailing edge access-panel (1) in position and hold it.
(c) Install the studs (2), (3), (4), (5), (6) and (8) and, if applicable, the studs (7), (9) and (10) but do not fully tighten them at this time.
(d)

Trailing Edge Access-Panels - Clearances and Sealant Application ** ON A/C NOT FOR ALL

1 Measure clearances A between the trailing edge access-panels (1).
2 Make sure that clearances A are 1.0 +3.0 mm or -0.0 mm (0.0394 +0.1181 in. or +0.0000 in.).
(e) TORQUE the studs (2), (3), (4), (5), (6) and (8) and, if applicable, the studs (7), (9) and (10) to between 0.3 and 0.27 m.daN (26.55 and 23.89 lbf.in )

.
(f) Replace the sealant (22):
1 Carefully remove the sealant (22) from the spar box with the SCRAPER - NON METALLIC.
2 Clean the surfaces of the spar box with Non Aqueous Cleaner-- Naphta based and Alcohol - (Material No.08BBC1) and the Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) .
3 Fill the space between the spar box and the trailing edge access-panel (1) with the Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) (22).
(g) For trailing edge access-panels 325EL and 325ER:
1 Do the electrical resistance measurement and the final protection of the bonding points at the studs (3), (5), (6), (7), (9) and (10) (Ref. AMM TASK 20-28-00-912-802).

Subtask 55-33-13-420-051-B ** ON A/C NOT FOR ALL

A. Closing and Installation of the Trailing Edge Access-Panels of the Vertical Stabilizer

Trailing Edge Access-Panels of the Vertical Stabilizer ** ON A/C NOT FOR ALL

NOTE: The vertical-stabilizer trailing-edge access-panels (1) are referred to in this procedure as "trailing edge access-panels” (1).

(1) Do a check of the condition of the sealant on the mating surfaces of the rudder hinge arms and the spar box flanges.
(2) If necessary, replace the sealant (21):
(a) Remove the sealant (21) from the mating surfaces of the rudder hinge arms and the spar box flanges with the SCRAPER - NON METALLIC.
(b) Clean the mating surfaces of the trailing edge access-panel (1), the rudder hinge arms and the spar box flanges with Non Aqueous Cleaner-- Naphta based and Alcohol - (Material No.08BBC1) and the Textile-Lint free Cotton - (Material No.14SBA1) .
(c) Apply Release Agent-- Liquid Wax - (Material No.14DBB1) on the mating surfaces of the trailing edge access-panel (1).
1 For access panels 325EL and 325ER:
a Do not apply release agent on the bonding points.
(d) Apply the Polysulfide Sealant-Low Adhesion Brushable - (Material No.06AEA1) (21) on the mating surfaces of the rudder hinge arms and the spar box flanges.
1 For access panels 325EL and 325ER:
a Do not apply sealant on the bonding points.
(3) For access panels 325EL and 325ER:
(a) Prepare the surface of the bonding points at the screws (6) (Ref. AMM TASK 20-28-00-912-803).
(4) Close trailing edge access-panels 325BL, 325BR, 325CL, 325CR and 325DL (1):

NOTE: The closing procedure is given for one trailing edge access-panel (1). The closing procedure for the other trailing edge access-panels (1) is almost the same.

(a) Apply Non Hardening Jointing Putty-Medium Temp. Area Chromate Free - (Material No.06LCB1) on the fastener holes of the rudder hinge arms.
(b) Remove the quick-release pin (12).
(c) Slowly move the trailing edge access-panel (1) to the closed position until you can install the quick-release pin (12) in the pin stowage hole (11).
(d) Fully close the trailing edge access-panel (1).
(e) TORQUE the quick-release fasteners (2) and (3) and, if applicable, the quick-release fasteners (4) to between 0.35 and 0.30 m.daN (30.97 and 26.55 lbf.in )

CAUTION: BE CAREFUL WHEN YOU REMOVE OR INSTALL THESE ACCESS PANELS. IF YOU LET THEM FALL, DAMAGE CAN OCCUR TO THEM OR TO THE AIRCRAFT STRUCTURE.

(5) Install trailing edge access-panels 325EL, 325ER, 325FR and 325GR (1):

NOTE: The installation procedure is given for one trailing edge access-panel (1). The installation procedure for the other trailing edge access-panels (1) is almost the same.

(a) Apply Polysulfide Sealant_General Purpose Brushable - (Material No.06AAA1) on the screws (5), (7) and (8) and, if applicable, on the screws (6).
(b) Put the trailing edge access-panel (1) in position and hold it.
(c) Install the screws (5), (7) and (8) and, if applicable, the screws (6) but do not fully tighten them at this time.
(d)

Trailing Edge Access-Panels - Clearances and Sealant Application ** ON A/C NOT FOR ALL

1 Measure clearances A between the trailing edge access-panels (1).
2 Make sure that clearances A are 1 +5 mm or -0 mm (0.0394 +0.1969 in. or +0.0000 in.).
(e) TORQUE the screws (5), (7) and (8) and, if applicable, the screws (6) to between 0.35 and 0.30 m.daN (30.97 and 26.55 lbf.in )

Subtask 55-33-13-420-051-C ** ON A/C NOT FOR ALL

A. Closing and Installation of the Trailing Edge Access-Panels of the Vertical Stabilizer

Trailing Edge Access-Panels ** ON A/C NOT FOR ALL

NOTE: The vertical-stabilizer trailing-edge access-panels (1) are referred to in this procedure as "trailing edge access-panels” (1).

(1) Do a check of the condition of the sealant on the mating surfaces of the rudder hinge arms and the spar box flanges.
(2) Replace the sealant (21):
(a) Remove the sealant (21) from the mating surfaces of the rudder hinge arms and the spar box flanges with the SCRAPER - NON METALLIC.
(b) Clean the mating surfaces of the trailing edge access-panel (1), the rudder hinge arms and the spar box flanges with Non Aqueous Cleaner-- Naphta based and Alcohol - (Material No.08BBC1) and the Textile-Lint free Cotton - (Material No.14SBA1) .
(c) Apply Release Agent-- Liquid Wax - (Material No.14DBB1) on the mating surfaces of the trailing edge access-panel (1).
1 For access panels 325EL and 325ER:
a Do not apply release agent on the bonding points.
(d) Apply Polysulfide Sealant-Low Adhesion Brushable - (Material No.06AEA1) (21) on the mating surfaces of the rudder hinge arms and the spar box flanges.
1 For access panels 325EL and 325ER:
a Do not apply sealant on the bonding points.
(3) For access panels 325EL and 325ER:
(a) Prepare the surface of the bonding points at the screws (6) (Ref. AMM TASK 20-28-00-912-803).
(4) Close trailing edge access-panels 325BL, 325BR, 325CL, 325CR and 325DL (1):

NOTE: The closing procedure is given for one trailing edge access-panel (1). The closing procedure for the other trailing edge access-panels (1) is almost the same.

(a) Apply Non Hardening Jointing Putty-Medium Temp. Area Chromate Free - (Material No.06LCB1) on the fastener holes of the rudder hinge arms.
(b) Remove the quick-release pin (12).
(c) Slowly move the trailing edge access-panel (1) to the closed position until you can install the quick-release pin (12) in the pin stowage hole (11).
(d) Fully close the trailing edge access-panel (1).
(e) TORQUE the studs (2) and (3) and, if applicable, the studs (4) to between 0.35 and 0.3 m.daN (30.97 and 26.55 lbf.in )

CAUTION: BE CAREFUL WHEN YOU REMOVE OR INSTALL THESE ACCESS PANELS. IF YOU LET THEM FALL, DAMAGE CAN OCCUR TO THEM OR TO THE AIRCRAFT STRUCTURE.

(5) Install trailing edge access-panels 325EL, 325ER and 325DR (1):

NOTE: The installation procedure is given for one trailing edge access-panel (1). The installation procedure for the other trailing edge access-panels (1) is almost the same.

Trailing Edge Access-Panels - Clearances and Sealant Application ** ON A/C NOT FOR ALL

Subtask 55-33-13-420-051-D ** ON A/C NOT FOR ALL

A. Closing and Installation of the Trailing Edge Access-Panels of the Vertical Stabilizer

Trailing Edge Access-Panels ** ON A/C NOT FOR ALL

NOTE: The vertical-stabilizer trailing-edge access-panels (1) are referred to in this procedure as "trailing edge access-panels” (1).

(1) Do a check of the condition of the sealant on the mating surfaces of the rudder hinge arms and the spar box flanges.
(2) If necessary, replace the sealant (21):
(a) Remove the sealant (21) from the mating surfaces of the rudder hinge arms and the spar box flanges with the SCRAPER - NON METALLIC.
(b) Clean the mating surfaces of the trailing edge access-panel (1), the rudder hinge arms and the spar box flanges with Non Aqueous Cleaner-- Naphta based and Alcohol - (Material No.08BBC1) and the Textile-Lint free Cotton - (Material No.14SBA1) .
(c) Apply Release Agent-- Liquid Wax - (Material No.14DBB1) on the mating surfaces of the trailing edge access-panel (1).
1 For access panels 325EL and 325ER:
a Do not apply release agent on the bonding points.
(d) Apply Polysulfide Sealant-Low Adhesion Brushable - (Material No.06AEA1) (21) on the mating surfaces of the rudder hinge arms and the spar box flanges.
1 For access panels 325EL and 325ER:
a Do not apply sealant on the bonding points.
(3) For access panels 325EL and 325ER:
(a) Prepare the surface of the bonding points at the studs (5), (6) and (7) (Ref. AMM TASK 20-28-00-912-803).
(4) Close trailing edge access-panels 325BL, 325BR, 325CL, 325CR and 325DL (1):

NOTE: The closing procedure is given for one trailing edge access-panel (1). The closing procedure for the other trailing edge access-panels (1) is almost the same.

(a) Apply Non Hardening Jointing Putty-Medium Temp. Area Chromate Free - (Material No.06LCB1) on the fastener holes of the rudder hinge arms.
(b) Remove the quick-release pin (11).
(c) Slowly move the trailing edge access-panel (1) to the closed position until you can install the quick-release pin (11) in the pin stowage hole (10).
(d) Fully close the trailing edge access-panel (1).
(e) TORQUE the studs (2) and (3) and, if applicable, the studs (4) to between 0.3 and 0.27 m.daN (26.55 and 23.89 lbf.in )

CAUTION: BE CAREFUL WHEN YOU REMOVE OR INSTALL THESE ACCESS PANELS. IF YOU LET THEM FALL, DAMAGE CAN OCCUR TO THEM OR TO THE AIRCRAFT STRUCTURE.

(5) Install trailing edge access-panels 325EL, 325ER and 325DR (1):

NOTE: The installation procedure is given for one trailing edge access-panel (1). The installation procedure for the other trailing edge access-panels (1) is almost the same.

(a) Apply Polysulfide Sealant_General Purpose Brushable - (Material No.06AAA1) on the studs (2), (3) and (4) and, if applicable, on the studs (5), (6) and (7).
(b) Put the trailing edge access-panel (1) in position and hold it.
(c) Install the studs (2), (3) and (4) and, if applicable, the studs (5), (6) and (7) but do not fully tighten them at this time.
(d)

Trailing Edge Access-Panels - Clearances and Sealant Application ** ON A/C NOT FOR ALL

1 Measure clearances A between the trailing edge access-panels (1).
2 Make sure that clearances A are 1 +5 mm or -0 mm (0.0394 +0.1969 in. or +0.0000 in.).
(e) TORQUE the studs (2), (3) and (4) and, if applicable, the studs (5), (6) and (7) to between 0.3 and 0.27 m.daN (26.55 and 23.89 lbf.in )

.
(f) If necessary, replace the sealant (22):
1 Carefully remove the sealant (22) from the spar box with the SCRAPER - NON METALLIC.
2 Clean the surfaces of the spar box with Non Aqueous Cleaner-- Naphta based and Alcohol - (Material No.08BBC1) and the Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) .
3 Fill the space between the spar box and the trailing edge access-panel (1) with the Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) (22).
(g) For trailing edge access-panels 325EL and 325ER:
1 Do the electrical resistance measurement and the final protection of the bonding points at the studs (5), (6) and (7) (Ref. AMM TASK 20-28-00-912-802).

5. Close-up
Subtask 55-33-13-942-054-A

A. Close Access
(1) Pressurize the Green, Blue and Yellow hydraulic systems (Ref. AMM TASK 29-23-00-863-001) or (Ref. AMM TASK 29-10-00-863-001), (Ref. AMM TASK 29-10-00-863-002) and (Ref. AMM TASK 29-10-00-863-003).
(2) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(3) Remove the WARNING NOTICE(S).
(4) Remove the access platform(s).

Subtask 55-33-13-865-058-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/ELAC1/NORM/SPLY	15CE1	B11
49VU	FLIGHT CONTROLS/THS/ACTR/MOT2	19CE2	B09
49VU	FLIGHT CONTROLS/SEC1/NORM/SPLY	21CE1	B08
49VU	AUTO FLT/FAC1/28VDC	5CC1	B04
49VU	AUTO FLT/FAC1/26VAC	14CC1	B03
** ON A/C NOT FOR ALL
49VU	FLIGHT CONTROLS/ELAC1/NORM/SPLY	15CE1	B06
49VU	FLIGHT CONTROLS/THS/ACTR/MOT2	19CE2	B04
49VU	FLIGHT CONTROLS/SEC1/NORM/SPLY	21CE1	B03
49VU	AUTO FLT/FAC1/28VDC	5CC1	H10
49VU	AUTO FLT/FAC1/26VAC	14CC1	H09
** ON A/C ALL
105VU	FLIGHT CONTROLS/ELAC2/STBY SPLY	16CE2	A02
105VU	FLT CTL/ELAC1/STBY SPLY	16CE1	A01
105VU	FLT CTL/SEC1/STBY SPLY	22CE	B01
121VU	AUTO FLT/RUDDER/TRIM/IND	15CC	M20
121VU	AUTO FLT/FAC2/28VDC	5CC2	M19
121VU	AUTO FLT/FAC2/26VAC	14CC2	M18
121VU	FLIGHT CONTROLS/SEC3/SPLY	21CE3	Q19
121VU	FLIGHT CONTROLS/SEC2/SPLY	21CE2	Q18
121VU	FLIGHT CONTROLS/THS ACTR/MOT3	19CE3	Q17
121VU	FLIGHT CONTROLS/THS ACTR/MOT1	19CE1	Q16
121VU	FLIGHT CONTROLS/ELAC2/NORM/SPLY	15CE2	R20

[Rev.10 from 2021] 2026.04.01 02:05:58 UTC