DOC AIRBUS | AMM A320FInspection of the Inlet Cone and the Inlet Cone Fairing [IAE]
TASK 72-38-11-200-010-B
Inspection of the Inlet Cone and the Inlet Cone Fairing
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 72-38-11-941-053-A ** ON A/C NOT FOR ALL
Subtask 72-38-11-210-052-A ** ON A/C NOT FOR ALL
Subtask 72-38-11-942-052-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 13:00:42 UTC
Inspection of the Inlet Cone and the Inlet Cone Fairing
WARNING:
BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.
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 | AR | ACCESS PLATFORM 1M(3 FT) |
| No specific | 1 | CUTTER - THIN BLADE |
| No specific | AR | MAT - WORK |
| No specific | 1 | SCRAPER - NON METALLIC |
| No specific | AR | WARNING NOTICE(S) |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.V01-060) | acetone, analar grade (CH3)2CO |
| (Material No.V01-124) | isopropyl alcohol, technical grade |
| (Material No.V02-006) | sealing tape |
| (Material No.V05-019) | waterproof silicon carbide abrasive paper |
| (Material No.V05-020) | waterproof silicon carbide abrasive paper |
| (Material No.14SBA1) | Textile-Lint free Cotton - |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 400 | POWER PLANT, NACELLES AND PYLONS |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 72-38-11-000-010-A | Removal of the Inlet Cone |
| TASK 72-38-11-300-010-A | Repair of the Inlet Cone Fairing - VRS1714 |
| TASK 72-38-11-300-011-A | Repair of the Inlet Cone - VRS1432 |
| TASK 72-38-11-400-010-A | Installation of the Inlet Cone |
Inlet Cone Assembly/Inlet Cone FairingSubtask 72-38-11-941-053-A ** ON A/C NOT FOR ALL
A. Safety Precautions
(1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).
(4) Put the support equipment in position.
(a) Put the ACCESS PLATFORM 1M(3 FT) in position to give access to the engine for the inspection.
(5) Put the MAT - WORK in position in the intake cowl.
4. Procedure(1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).
(4) Put the support equipment in position.
(a) Put the ACCESS PLATFORM 1M(3 FT) in position to give access to the engine for the inspection.
(5) Put the MAT - WORK in position in the intake cowl.
NOTE: Make sure that the red warning pennants of the workmat can be seen external of the aircraft.
NOTE: Make sure the workmat has sufficient dimensions to give full protection to the lower half of the intake cowl surface.
Subtask 72-38-11-210-052-A ** ON A/C NOT FOR ALL
A. Inspection of the Inlet Cone
(1) Examine the external surface of the inlet cone for erosion, cracks, delamination, scores, gouges, grooves, missing and/or peeling of the polyurethane/epoxy varnish layer.
(a) If it has surface erosion but the polyurethane layer is not damaged, accept it.
(b) If it shows missing or peeling of the polyurethane layer:
(e) If it is cracked, reject it.
(f) If it has scores, gouges or grooves less than 0.015 in. (0.3810 mm) in depth, accept it.
(g) If it has scores, gouges or grooves more than 0.015 in. (0.3810 mm) in depth, reject it.
(2) Examine the tip of the inlet cone to make sure that the tip is not missing or damaged, or that there is no sign of bond failure.
(a) If the tip on one engine is damaged or missing, or has the sign of bond failure, do the following:
1 Remove the damaged tip and the remaining compound without any damage to the parent material, and rub down the area that is to be repaired using the SCRAPER - NON METALLIC and/or the CUTTER - THIN BLADE, the waterproof silicon carbide abrasive paper (Material No.V05-019) and/or the waterproof silicon carbide abrasive paper (Material No.V05-020) .
2 Clean the tip locating hole and four adhesive cure hole areas with a clean Textile-Lint free Cotton - (Material No.14SBA1) made moist with theV01-060 acetone, analar grade (CH3)2CO V01-124 isopropyl alcohol, technical grade
3 Apply the sealing tape (Material No.V02-006) over the tip locating hole and the four adhesive cure hole areas.
4 Apply hand pressure on the tape to complete the bounding.
5 Accept the missing tip with the procedure above applied for a maximum of five flight cycles.
6 After the installation of the sealing tape, replace the inlet cone within the fly-on limit given (Ref. AMM TASK 72-38-11-000-010) and (Ref. AMM TASK 72-38-11-400-010).
(b) If the tip is damaged or missing on more than one engine, replace the inlet cone (Ref. AMM TASK 72-38-11-000-010) and (Ref. AMM TASK 72-38-11-400-010).
(3) Examine the fairing mating surface around the six bolt holes adjacent to the dowel pins.
(a) If it has depressions less than 0.001 in. (0.025 mm) in depth, accept it.
(b) If it has depressions more than 0.001 in. (0.025 mm) in depth, reject it.
Subtask 72-38-11-210-057-A ** ON A/C NOT FOR ALL (1) Examine the external surface of the inlet cone for erosion, cracks, delamination, scores, gouges, grooves, missing and/or peeling of the polyurethane/epoxy varnish layer.
(a) If it has surface erosion but the polyurethane layer is not damaged, accept it.
(b) If it shows missing or peeling of the polyurethane layer:
- If the total area of missing or peeling of the polyurethane layer is within 50 percent of the total area, repair it within 6000 hours, 4500 flights or 20 months, whichever occurs first (Ref. AMM TASK 72-38-11-300-011).
The inlet cone must be examined every 600 flight hours, 750 flight cycles or 100 days in order to make sure that the parent material is not exposed. If the parent material is exposed, reject it. - If the total area of missing or peeling of the polyurethane layer is more than 50 percent of total area, replace it within 6000 hours, 4500 flights or 20 months, whichever occurs first.
The inlet cone must be examined every 600 flight hours, 750 flight cycles or 100 days in order to make sure that the parent material is not exposed. If the parent material is exposed, reject it.
- If the total area of missing or peeling of the epoxy varnish layer is within 1.58 sqin (10.2 sqcm), repair it within 600 flight hours, 750 flight cycles or 100 days, whichever occurs first (Ref. AMM TASK 72-38-11-300-011).
- If the total area of missing or peeling of the epoxy varnish layer is more than 1.58 sqin (10.2 sqcm), replace it within 600 flight hours, 750 flight cycles or 100 days, whichever occurs first.
(e) If it is cracked, reject it.
(f) If it has scores, gouges or grooves less than 0.015 in. (0.3810 mm) in depth, accept it.
(g) If it has scores, gouges or grooves more than 0.015 in. (0.3810 mm) in depth, reject it.
(2) Examine the tip of the inlet cone to make sure that the tip is not missing or damaged, or that there is no sign of bond failure.
(a) If the tip on one engine is damaged or missing, or has the sign of bond failure, do the following:
1 Remove the damaged tip and the remaining compound without any damage to the parent material, and rub down the area that is to be repaired using the SCRAPER - NON METALLIC and/or the CUTTER - THIN BLADE, the waterproof silicon carbide abrasive paper (Material No.V05-019) and/or the waterproof silicon carbide abrasive paper (Material No.V05-020) .
2 Clean the tip locating hole and four adhesive cure hole areas with a clean Textile-Lint free Cotton - (Material No.14SBA1) made moist with the
3 Apply the sealing tape (Material No.V02-006) over the tip locating hole and the four adhesive cure hole areas.
4 Apply hand pressure on the tape to complete the bounding.
5 Accept the missing tip with the procedure above applied for a maximum of five flight cycles.
6 After the installation of the sealing tape, replace the inlet cone within the fly-on limit given (Ref. AMM TASK 72-38-11-000-010) and (Ref. AMM TASK 72-38-11-400-010).
(b) If the tip is damaged or missing on more than one engine, replace the inlet cone (Ref. AMM TASK 72-38-11-000-010) and (Ref. AMM TASK 72-38-11-400-010).
(3) Examine the fairing mating surface around the six bolt holes adjacent to the dowel pins.
(a) If it has depressions less than 0.001 in. (0.025 mm) in depth, accept it.
(b) If it has depressions more than 0.001 in. (0.025 mm) in depth, reject it.
B. Examine the Inlet Cone Fairing for Cracks and Indentations.
(1) Cracks in one bolt hole location.
(a) If the cracks are not within 1.58 in. (40 mm) of the front edge of the fairing, and not within 0.98 in. (25 mm) of the rear edge, accept them. The cracks must be examined after each flight until it is replaced.
(b) If any crack is within 1.58 in. (40 mm) of the front edge of the fairing, or within 0.98 in. (25 mm) of the rear edge, reject it.
(c) If material is missing or if released material is held by attaching bolt of the fairing, reject it.
(2) If it has cracks in more than one bolt hole location, reject it.
(3) If it has dents up to 0.005 in. (0.12 mm) in depth, accept it.
(4) If it has nicks and scratches up to 0.003 in. (0.07 mm) in depth, accept it.
Subtask 72-38-11-210-058-A ** ON A/C NOT FOR ALL (1) Cracks in one bolt hole location.
(a) If the cracks are not within 1.58 in. (40 mm) of the front edge of the fairing, and not within 0.98 in. (25 mm) of the rear edge, accept them. The cracks must be examined after each flight until it is replaced.
(b) If any crack is within 1.58 in. (40 mm) of the front edge of the fairing, or within 0.98 in. (25 mm) of the rear edge, reject it.
(c) If material is missing or if released material is held by attaching bolt of the fairing, reject it.
(2) If it has cracks in more than one bolt hole location, reject it.
(3) If it has dents up to 0.005 in. (0.12 mm) in depth, accept it.
(4) If it has nicks and scratches up to 0.003 in. (0.07 mm) in depth, accept it.
C. Examine the Seal Strips on the Fairing.
(2) If the seal strips are missing, repair them (Ref. AMM TASK 72-38-11-300-010).
5. Close-upNOTE: This task is only for SBE 72-0318 Inlet Cone Fairing.
(1) If the seal strips are torn or are unbonded, repair them (Ref. AMM TASK 72-38-11-300-010) within 50 hours or 10 flights. (2) If the seal strips are missing, repair them (Ref. AMM TASK 72-38-11-300-010).
Subtask 72-38-11-942-052-A ** ON A/C NOT FOR ALL
A. Remove the Support Equipment
(1) Remove the workmat from the intake cowl.
(2) Remove the access platform(s).
(3) Remove the WARNING NOTICE(S).
(1) Remove the workmat from the intake cowl.
(2) Remove the access platform(s).
(3) Remove the WARNING NOTICE(S).