DOC AIRBUS | AMM A320FInstallation of the Fan Exit Fairing (Splitter) [PW11]
TASK 72-21-06-400-801-A
Installation of the Fan Exit Fairing (Splitter)
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Work Zones and Access Panels
D. Referenced Information
3. Job Set-up
Subtask 72-21-06-941-052-A ** ON A/C NOT FOR ALL
Subtask 72-21-06-420-050-A ** ON A/C NOT FOR ALL
Subtask 72-21-06-860-051-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 02:48:49 UTC
Installation of the Fan Exit Fairing (Splitter)
WARNING:
BE CAREFUL WHEN YOU DO WORK ON THE ENGINE AND THE ADJACENT COMPONENTS AFTER ENGINE SHUTDOWN. THE ENGINE, THE ENGINE OIL AND THE ADJACENT COMPONENTS 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.
ZONE: 400
1. Reason for the JobSelf explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | 1 | MAT - PROTECTIVE |
| No specific | Torque wrench: range to between 40 and 36 lbf.in (0.45 and 0.41 m.daN )  | |
| 636-1100-3GSE | 1 | INLET COWL PROTECT COVER |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.P03-001) | lubricant, aircraft turbine engine (synthetic base) |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 400 | POWER PLANT, NACELLES AND PYLONS |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 71-00-00-860-833-A | Procedure to Prevent Engine Motoring |
| TASK 72-11-03-400-801-A | Installation of the Fan Blades |
Fan Exit Fairing (Splitter) - InstallationSubtask 72-21-06-941-052-A ** ON A/C NOT FOR ALL
A. Safety Precautions
(1) Make sure that you did the procedure to prevent engine motoring
(Ref. AMM TASK 71-00-00-860-833).
4. Procedure(1) Make sure that you did the procedure to prevent engine motoring
(Ref. AMM TASK 71-00-00-860-833).
Subtask 72-21-06-420-050-A ** ON A/C NOT FOR ALL
A. Installation of the Fan Exit Fairing (Splitter)
(2) Removal of the protection covers:
(3) Install the splitter (1) on the fan exit stator as follows:
(a) Install the splitter (1) completely on the stator.
(b) Apply theP03-001 lubricant, aircraft turbine engine (synthetic base)
(c) Attach the splitter (1) with the 16 screws (2).
(d) TORQUE the 16 screws (2) to between 40 and 36 lbf.in (0.45 and 0.41 m.daN ) equally in an opposite pattern until the same torque indication holds.
(4) Remove the MAT - PROTECTIVE from the inlet cowl.
(5) Install the fan blades (Ref. AMM TASK 72-11-03-400-801).
(6) Examine the assembly for foreign objects, damage and correct assembly.
5. Close-upCAUTION:
WIPE CLEAN ALL PARTS AND TOOLS AS NECESSARY TO REMOVE UNWANTED DEBRIS AND PREVENT DAMAGE TO THE ENGINE.
(1) Put the 636-1100-3GSE INLET COWL PROTECT COVER or equivalent and the MAT - PROTECTIVE in the inlet cowl. (2) Removal of the protection covers:
CAUTION:
REMOVE THE PROTECTION COVERS FROM THE OPENINGS AS NECESSARY TO PREVENT ENGINE DAMAGE.
(a) Make sure that you remove all the COVER - PROTECTION as necessary to prevent damage to the engine. (3) Install the splitter (1) on the fan exit stator as follows:
(a) Install the splitter (1) completely on the stator.
(b) Apply the
(c) Attach the splitter (1) with the 16 screws (2).
(d) TORQUE the 16 screws (2) to between 40 and 36 lbf.in (0.45 and 0.41 m.daN )
equally in an opposite pattern until the same torque indication holds. (4) Remove the MAT - PROTECTIVE from the inlet cowl.
(5) Install the fan blades (Ref. AMM TASK 72-11-03-400-801).
(6) Examine the assembly for foreign objects, damage and correct assembly.
Subtask 72-21-06-860-051-A ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the WARNING NOTICE(S).
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the WARNING NOTICE(S).