W DOC AIRBUS | AMM A320F

Repair of the External Surface Damage of the Inlet Cone Assembly (Front Segment) [PW11]

TASK 72-11-01-300-804-A
Repair of the External Surface Damage of the Inlet Cone Assembly (Front Segment)

WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE AFTER SHUTDOWN. THE ENGINE CAN STAY HOT FOR A LONG TIME. IF YOU DO NOT OBEY THIS INSTRUCTION, INJURY CAN OCCUR.
WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
WARNING: WHEN YOU DO WORK WITH COMPOSITE MATERIALS, USE PERSONAL PROTECTION EQUIPMENT AND A LOCAL MECHANICAL EXHAUST VENTILATION OR AN APPROVED RESPIRATOR. YOU MUST NOT BREATHE THE PARTICLES FROM THE REPAIR OF COMPOSITE MATERIALS OR LET THE PARTICLES TOUCH YOU. THE PARTICLES CAN CAUSE INJURY OR IRRITATION TO YOU, AND DAMAGE TO EQUIPMENT.
ZONE: 430
ZONE: 440
1. Reason for the Job
Use this procedure to fill-repair the surface damage on the inlet cone cover external surface. Do repairs only in the fiberglass layer.
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
1
ACCESS PLATFORM 1M(3 FT)
No specific
1
KNIFE- RAZOR
No specific
1
MAT - PROTECTIVE
636-1100-3GSE
1
INLET COWL PROTECT COVER
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.P05-005)
lint-free cotton cloth
(Material No.P05-055)
Emery Cloth
(Material No.P05-094)
aluminum oxide paper
(Material No.P05-138)
aluminum oxide cloth
(Material No.P05-153)
abrasive paper, silicon carbide
(Material No.P05-204)
aluminum oxide abrasive cloth
(Material No.P05-253)
paper, abrasive
(Material No.P08-002)
Liquid Epoxy
(Material No.P08-012)
Epoxy Resin Curing Agent
(Material No.P08-039)
Epoxy Adhesive Paste
(Material No.P11-078)
alcohol, isopropyl
 C. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
430
ENG 1 AIR INTAKE, FAN AND ACCESS GEARBOX
440
ENG 2 AIR INTAKE, FAN AND ACCESS GEARBOX
 D. Referenced Information
REFERENCE
DESIGNATION
TASK 71-00-00-860-833-A
Procedure to Prevent Engine Motoring
TASK 72-11-01-000-801-A
Removal of the Inlet Cone
TASK 72-11-01-300-801-A
Repair of the Inlet Cone
TASK 72-11-01-400-801-A
Installation of the Inlet Cone
F Inlet Cone Cover External Surface
3. Job Set-up
Subtask 72-11-01-941-057-A ** ON A/C NOT FOR ALL
A. Safety Precautions
   (1) Do the procedure to prevent engine motoring
(Ref. AMM TASK 71-00-00-860-833).
   (2) Put an ACCESS PLATFORM 1M(3 FT) in position.
   (3) Put the 636-1100-3GSE INLET COWL PROTECT COVER or the MAT - PROTECTIVE in the intake cowl.
4. Procedure
Subtask 72-11-01-320-051-A ** ON A/C NOT FOR ALL
A. Repair of the External Surface Damage of the Inlet Cone Assembly (Front Segment)
CAUTION: WIPE CLEAN ALL PARTS AND TOOLS AS NECESSARY TO REMOVE UNWANTED DEBRIS AND PREVENT DAMAGE TO THE ENGINE.
CAUTION: DO NOT REPAIR MORE THAN THE FIBERGLASS LAYER. REPLACE THE CONE SEGMENT IF THERE IS DAMAGE TO MORE THAN THE FIBERGLASS LAYER. IF YOU DO NOT OBEY THIS CAUTION, DAMAGE TO ENGINE COMPONENTS CAN OCCUR.
CAUTION: WHEN YOU USE A RAZOR KNIFE TO REMOVE THE DAMAGED PROTECTIVE COAT, BE CAREFUL NOT TO CAUSE MORE DAMAGE TO THE FIBERGLASS LAYER.
   (1) Find the inlet cone (1) located on the fan rotor.
F Inlet Cone Cover External Surface ** ON A/C NOT FOR ALL
   (2) Remove the inlet cone, if necessary (Ref. AMM TASK 72-11-01-000-801).
   (3) Use a KNIFE- RAZOR to cut the loose or lifted fluoroelastomer layer around the damaged area.
F Inlet Cone Cover External Surface ** ON A/C NOT FOR ALL
NOTE: Small scattered surface damage (includes chips, scratches and dents) that does not extend through the outer fiberglass layer can be repaired.
   (4) Abrade the repair area with Emery Cloth (Material No.P05-055) , aluminum oxide cloth (Material No.P05-138) or aluminum oxide abrasive cloth (Material No.P05-204) to remove the damaged fiberglass and make sure that all loose or lifted fluoroelastomer is removed around the outer area of the repair.
     (a) Limit the local surface damage to 2.000 in. (50.800 mm) maximum diameter, separated by 2.000 in. (50.800 mm) minimum and five locations maximum. Repair area(s) is/are specified in (Ref. AMM TASK 72-11-01-300-801).
   (5) Lightly abrade the repair area with aluminum oxide paper (Material No.P05-094) , P05-153abrasive paper, silicon carbide or P05-253paper, abrasive.
NOTE: Be careful not to cause damage to the Kevlar TM layers below the fiberglass.
NOTE: You can make minor chips and scratches smooth. It is not necessary to remove this damage.
   (6) Clean the surface that you made rough with a clean lint-free cotton cloth (Material No.P05-005) and P11-078alcohol, isopropyl.
   (7) Wait a minimum of 15 minutes to let the area dry fully before you continue to Step 8.
   (8) Do a visual inspection of the external surfaces of the repair area(s).
     (a) Damage through the fiberglass layer into the Kevlar TM is not repairable.
       1 The fluoroelastomer coating is black with a rubber or elastic feel.
       2 The fiberglass layer is whitish green and has a plastic feel.
       3 The Kevlar TM is yellow-brown and has a fuzzy texture and feel.
     (b) Cracks or crazing found on the external surfaces are not repairable by this procedure. Inlet cone covers that show cracks or crazing must not be installed again.
     (c) Material delamination found on the external surfaces are not repairable by this procedure. Inlet cone covers that show delamination must not be installed again.
     (d) If there is only surface damage through the fiberglass, it is not necessary to apply the epoxy, just recoat the surface. Continue to Step 15.
     (e) If there is damage through the fiberglass but not into the Kevlar TM it is necessary to apply the epoxy. Continue to the next step.
   (9) Prepare one of the filling compounds at a room temperature of 60 deg.F (16 deg.C) to 90 deg.F (32 deg.C).
     (a) Mix 100 parts of Liquid Epoxy (Material No.P08-002) by weight with 25 parts of Epoxy Resin Curing Agent (Material No.P08-012) .
     (b) Mix 100 parts of Epoxy Adhesive Paste (Material No.P08-039) Part-A by weight with 30 parts of Epoxy Adhesive Paste Part-B.
NOTE: The two materials have a pot life of 20 to 30 minutes at 75 deg.F (24 deg.C) maximum.
   (10) Fill the damaged area with filling compound until the filled surface is above the adjacent fiberglass layer.
   (11) Cure the adhesive by one of the procedures that follow:
     (a) Cure for 24 hours minimum at a room temperature of 60 deg.F (16 deg.C) to 90 deg.F (32 deg.C).
     (b) Cure for 2 hours minimum at 150 deg.F (66 deg.C) to 200 deg.F (93 deg.C).
   (12) Lightly abrade the filled layer to make the surface contour level with the adjacent fiberglass layer with aluminum oxide paper (Material No.P05-094) , P05-153abrasive paper, silicon carbide or P05-253paper, abrasive.
   (13) Clean the abraded surface with a lint-free cotton cloth (Material No.P05-005) moist with P11-078alcohol, isopropyl.
   (14) Wait a minimum of 15 minutes to let the area dry fully before you continue to the next step.
   (15) Apply the protective coat to the repaired area (Ref. AMM TASK 72-11-01-300-801).
   (16) Install the inlet cone, if necessary (Ref. AMM TASK 72-11-01-400-801).
   (17) Examine the assembly for foreign objects, damage, and correct assembly.
5. Close-up
Subtask 72-11-01-942-053-A ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
   (1) Remove the 636-1100-3GSE INLET COWL PROTECT COVER or MAT - PROTECTIVE from the inside of the fan case.
   (2) Remove the access platform(s).
   (3) Make sure that the work area is clean and clear of tools and other items.
[Rev.10 from 2021] 2026.04.01 02:47:44 UTC
"Aviabrain" 2025