DOC AIRBUS | AMM A320FVisual Inspection of the Fan Hub Assembly [PW11]
TASK 72-11-06-210-802-A
Visual Inspection of the Fan Hub Assembly
Use this procedure to do a visual inspection of the fan hub.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Work Zones and Access Panels
C. Referenced Information
3. Job Set-up
Subtask 72-11-06-941-051-A ** ON A/C NOT FOR ALL
Subtask 72-11-06-210-050-A ** ON A/C NOT FOR ALL
Subtask 72-11-06-942-052-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 13:02:13 UTC
Visual Inspection of the Fan Hub Assembly
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.
1. Reason for the JobUse this procedure to do a visual inspection of the fan hub.
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 | FLASHLIGHT |
| No specific | 1 | MAGNIFYING GLASS POWER 10X |
| No specific | 1 | MAT - PROTECTIVE |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 430 | ENG 1 AIR INTAKE, FAN AND ACCESS GEARBOX |
| 440 | ENG 2 AIR INTAKE, FAN AND ACCESS GEARBOX |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 70-27-00-910-804-A | SPOP 208 - Degreasing of Parts by Solvent Wiping |
| TASK 70-28-00-910-801-A | SPOP 532 - Blending and Buffing of Titanium Parts |
| 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 72-11-01-400-801-A | Installation of the Inlet Cone |
Fan Hub Inspection LocationsSubtask 72-11-06-941-051-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 the intake cowl.
4. Procedure(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 the intake cowl.
Subtask 72-11-06-210-050-A ** ON A/C NOT FOR ALL
A. Visual Inspection of the Fan Hub Assembly
(2) Remove the inlet cone from the fan hub assembly (Ref. AMM TASK 72-11-01-000-801).
(3) Do a visual inspection of the inlet cone flange hole and mating face, counterweight flange scallops, holes, inner and outer surfaces and inlet cone flange scallops on the fan hub assembly for nicks, dents and scratches, as follows:
(a) Use a FLASHLIGHT and a MAGNIFYING GLASS POWER 10X.
(b) Make sure that there are no cracks.
(c) If necessary, clean the areas to be inspected by SPOP 208, wipe method (Ref. AMM TASK 70-27-00-910-804).
(d) Remove any raised material and sharp edges by SPOP 532 (Ref. AMM TASK 70-28-00-910-801). Remove raised material by manual blending only.
(e) Superficial imperfections on any surface are permitted and are not considered damage.
(a) Provide the Damage Inspection Report to Pratt & Whitney.
(5) Install the inlet cone (Ref. AMM TASK 72-11-01-400-801).
(6) Remove the MAT - PROTECTIVE from the intake cowl.
(7) Examine the assembly for foreign objects, damage and correct assembly.
Table 1: Fan Hub Assembly - Visual Inspection
5. Close-upCAUTION:
WIPE CLEAN ALL PARTS AND TOOLS AS NECESSARY TO REMOVE UNWANTED DEBRIS AND PREVENT DAMAGE TO THE ENGINE.
(1) Put the MAT - PROTECTIVE in the intake cowl. (2) Remove the inlet cone from the fan hub assembly (Ref. AMM TASK 72-11-01-000-801).
(3) Do a visual inspection of the inlet cone flange hole and mating face, counterweight flange scallops, holes, inner and outer surfaces and inlet cone flange scallops on the fan hub assembly for nicks, dents and scratches, as follows:
(a) Use a FLASHLIGHT and a MAGNIFYING GLASS POWER 10X.
(b) Make sure that there are no cracks.
(c) If necessary, clean the areas to be inspected by SPOP 208, wipe method (Ref. AMM TASK 70-27-00-910-804).
(d) Remove any raised material and sharp edges by SPOP 532 (Ref. AMM TASK 70-28-00-910-801). Remove raised material by manual blending only.
(e) Superficial imperfections on any surface are permitted and are not considered damage.
NOTE: Definition:
superficial imperfection - An imperfection which disrupts the surface and appears smooth-edged, but does not penetrate the surface roughness texture. This condition is so slight, considered less than a shallow imperfection, that a stylus need not be used to evaluate it.
(4) If any damage is found, complete the Damage Inspection Report. superficial imperfection - An imperfection which disrupts the surface and appears smooth-edged, but does not penetrate the surface roughness texture. This condition is so slight, considered less than a shallow imperfection, that a stylus need not be used to evaluate it.
(a) Provide the Damage Inspection Report to Pratt & Whitney.
(5) Install the inlet cone (Ref. AMM TASK 72-11-01-400-801).
(6) Remove the MAT - PROTECTIVE from the intake cowl.
(7) Examine the assembly for foreign objects, damage and correct assembly.
Table 1: Fan Hub Assembly - Visual Inspection
| EXAMINE | DAMAGE | DISPOSITION |
|---|---|---|
| Area 1 (Counterweight flange scallop and adjacent area (excluding Area 7), 5 locations) | Any non-superficial damage | Not permitted. Contact Pratt & Whitney. |
| Area 2 (Inlet cone flange scallop and adjacent area (excluding Area 7 and Area 9), 10 locations) | Any non-superficial damage | Not permitted. Contact Pratt & Whitney. |
| Area 3 (Bolt hole (including chamfer and inner diameter) and adjacent area on the inlet cone flange lug (excluding Area 2 and Area 9), 5 locations) | Any non-superficial damage | Not permitted. Contact Pratt & Whitney. |
| Area 4 (Counterweight flange outward surface (excluding Area 1, Area 2 and Area 6)) | Any damage 0.002 in. (0.05 mm) deep or less | Permitted |
| | Any damage more than 0.002 in. (0.05 mm) deep | Not permitted. Contact Pratt & Whitney. |
| Area 5 (Inlet cone mating face (excluding Area 2, Area 3, Area 8 and Area 9)) | Any damage 0.003 in. (0.08 mm) deep or less | Permitted |
| | Any damage more than 0.003 in. (0.08 mm) deep | Not permitted. Contact Pratt & Whitney. |
| Area 6 (Counterweight holes, 30 locations) | Any damage 0.003 in. (0.08 mm) deep or less | Permitted |
| | Any damage more than 0.003 in. (0.08 mm) deep | Not permitted. Contact Pratt & Whitney. |
| Area 7 (Counterweight flange inward surface (excluding Area 6)) | Any damage 0.003 in. (0.08 mm) deep or less | Permitted |
| | Any damage more than 0.003 in. (0.08 mm) deep | Not permitted. Contact Pratt & Whitney. |
| Area 8 (Corner radius of the outer slot that is adjacent to the bolt hole, 10 locations) | Any damage 0.002 in. (0.05 mm) deep or less | Permitted |
| | Any damage more than 0.002 in. (0.05 mm) deep | Not permitted. Contact Pratt & Whitney. |
| Area 9 (Inlet cone flange lug inward surface (excluding Area 3)) | Any non-superficial damage | Not permitted. Contact Pratt & Whitney. |
Subtask 72-11-06-942-052-A ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
(1) Remove the access platform(s).
(2) Make sure that the work area is clean and clear of tools and other items.
(1) Remove the access platform(s).
(2) Make sure that the work area is clean and clear of tools and other items.