DOC AIRBUS | AMM A320FSpecial Detailed Inspection (ENDOSCOPE) of Fuselage Internal Structure, from FR 12 to FR 14, Under Heat Exchanger Panels
TASK 53-11-00-200-802-A
Special Detailed Inspection (ENDOSCOPE) of Fuselage Internal Structure, from FR 12 to FR 14, Under Heat Exchanger Panels
Refer to the MPD TASK: 531198-01
SPECIAL DETAILED INSPECTION (ENDOSCOPE) OF FUSELAGE INTERNAL STRUCTURE, FROM FR 12 TO FR 14, UNDER HEAT EXCHANGER PANELS.
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Work Zones and Access Panels
D. Referenced Information
3. Job Set-up
Subtask 53-11-00-941-093-A
Subtask 53-11-00-280-050-A
Subtask 53-11-00-390-059-A
[Rev.10 from 2021]
2026.04.02 06:28:46 UTC
Special Detailed Inspection (ENDOSCOPE) of Fuselage Internal Structure, from FR 12 to FR 14, Under Heat Exchanger Panels
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
CAUTION:
USE ONLY THE GROUND SERVICE NETWORK TO SUPPLY ELECTRICITY BECAUSE THE AVIONICS VENTILATION SYSTEM IS NOT SERVICEABLE. IF YOU ENERGIZE THE AIRCRAFT ELECTRICAL CIRCUITS WITHOUT THE VENTILATION SYSTEM YOU WILL CAUSE DAMAGE TO ELECTRICAL EQUIPMENT.
1. Reason for the JobRefer to the MPD TASK: 531198-01
SPECIAL DETAILED INSPECTION (ENDOSCOPE) OF FUSELAGE INTERNAL STRUCTURE, FROM FR 12 TO FR 14, UNDER HEAT EXCHANGER PANELS.
NOTE: The effectivity of this task is 'ALL'. To know if this task is applicable to your aircraft, refer to the MPD task applicability and the weight variant data given in the SRM introduction.
2. Job Set-up InformationA. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | PLUG - BLANKING |
| No specific | 1 | STEPLADDER 0.5 M (1.6 FT) |
| No specific | AR | WARNING NOTICE(S) |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.08BAA9) | Non Aqueous Cleaner-General - - |
| (Material No.14SBA1) | Textile-Lint free Cotton - |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 125 | LATERAL AVIONIC COMPARTMENT |
| 126 | LATERAL AVIONIC COMPARTMENT |
| 221 | FWD CAB UTILITY AREA |
| 222 | FWD CAB UTILITY AREA |
| 223 | FWD CAB OVERHEAD COMPARTMENT |
| 224 | FWD CAB OVERHEAD COMPARTMENT |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 21-26-00-710-001-A | Operational Check of the Avionics Equipment Ventilation-System via MCDU |
| TASK 21-26-00-710-001-A-01 | Operational Check of the Avionics Equipment Ventilation (without the CFDS) |
| TASK 21-26-42-200-001-A | Inspection/Check of the Skin Heat Exchanger (the Inlet Ducts and the Extraction Duct) |
| TASK 21-26-42-200-002-A | Inspection/Check of the Skin Heat Exchanger (Outlet Duct) |
| TASK 21-26-45-000-001-A | Removal of the Skin Heat Exchanger |
| TASK 21-26-45-400-001-A | Installation of the Skin Heat Exchanger |
| TASK 24-41-00-861-002-A | Energize the Aircraft Electrical Circuits from the External Power |
| TASK 24-41-00-861-002-A-01 | Energize the Aircraft Electrical Circuits from the APU |
| TASK 24-41-00-861-002-A-02 | Energize the Aircraft Electrical Circuits from Engine 1(2) |
| TASK 24-41-00-862-002-A | De-energize the Aircraft Electrical Circuits Supplied from the External Power |
| TASK 24-41-00-862-002-A-01 | De-energize the Aircraft Electrical Circuits Supplied from the APU |
| TASK 24-41-00-862-002-A-02 | De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) |
| TASK 25-23-42-000-001-A | Removal of the Ceiling Panels - Forward Utility Area |
| TASK 25-23-42-400-001-A | Installation of the Ceiling Panels - Forward Utility Area |
| TASK 25-80-00-000-001-A | Removal of the Insulation Blankets |
| TASK 25-80-00-400-001-A | Installation of the Insulation Blankets |
| TASK 51-78-00-916-001-A | Application of Temporary Protection System (TPS) |
| SRM 512300 | |
| SRM 512400 | |
| SRM 517713 | |
| NTM 519000 | |
| SRM 511100 | (for corrective action) |
| SRM 512200 | (for corrective action) |
| TASK 25-31-00-00 | FORWARD GALLEY - DESCRIPTION AND OPERATION |
| TASK 25-41-00-00 | FORWARD LAVATORIES - DESCRIPTION AND OPERATION |
Inspection (ENDOSCOPE) of the Fuselage Internal Structure from FR12 to FR14, Under Heat Exchanger PanelsSubtask 53-11-00-941-093-A
A. Safety Precautions
(1) In the cockpit, put a WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on these overhead panels:
Subtask 53-11-00-010-118-A (1) In the cockpit, put a WARNING NOTICE(S) in position to tell persons not to operate the pushbutton switches on these overhead panels:
- 21VU (EMER ELEC PWR),
- 35VU (ELEC).
B. Get Access
(1) Remove the galleys and lavatories between FR12 and FR14, if installed.
To do this, refer to the para. Component Location in the applicable ATA 25 Description/Operation: for the galleys (Ref. AMM D/O 25-31-00-00), for the lavatories (Ref. AMM D/O 25-41-00-00). In this paragraph, you will find the cross-references of the removal/installation tasks.
(2) Remove the necessary ceiling panels between FR12 and FR14 to get access to the inspection areas (Ref. AMM TASK 25-23-42-000-001).
(3) Remove the applicable air conditioning ducts between FR12 and FR14, as necessary.
(4) Put the PLUG-BLANKING in each disconnected line end.
(5) Loosen the clamps from the electrical harness and move the harness away from the work area. Protect the harness to prevent contact with debris.
(6) Remove the necessary insulation blankets between FR12 and FR14 to get access to the inspection areas (Ref. AMM TASK 25-80-00-000-001).
(7) Remove the inlet and outlet ducts of the skin heat-exchanger (Ref. AMM TASK 21-26-42-200-001) (Ref. AMM TASK 21-26-42-200-002).
(8) Put the PLUG-BLANKING in each disconnected line end.
(9) Put a STEPLADDER 0.5 M (1.6 FT) in position.
Subtask 53-11-00-110-137-A (1) Remove the galleys and lavatories between FR12 and FR14, if installed.
To do this, refer to the para. Component Location in the applicable ATA 25 Description/Operation: for the galleys (Ref. AMM D/O 25-31-00-00), for the lavatories (Ref. AMM D/O 25-41-00-00). In this paragraph, you will find the cross-references of the removal/installation tasks.
(2) Remove the necessary ceiling panels between FR12 and FR14 to get access to the inspection areas (Ref. AMM TASK 25-23-42-000-001).
(3) Remove the applicable air conditioning ducts between FR12 and FR14, as necessary.
(4) Put the PLUG-BLANKING in each disconnected line end.
(5) Loosen the clamps from the electrical harness and move the harness away from the work area. Protect the harness to prevent contact with debris.
(6) Remove the necessary insulation blankets between FR12 and FR14 to get access to the inspection areas (Ref. AMM TASK 25-80-00-000-001).
(7) Remove the inlet and outlet ducts of the skin heat-exchanger (Ref. AMM TASK 21-26-42-200-001) (Ref. AMM TASK 21-26-42-200-002).
(8) Put the PLUG-BLANKING in each disconnected line end.
(9) Put a STEPLADDER 0.5 M (1.6 FT) in position.
C. Preparation of the Inspection Area
(1) Remove the sealant and/or paint from the inspection area if this is necessary for the Non-destructive Testing Manual (NTM) task.
(2) Make sure that the inspection area is sufficiently clean to do a satisfactory inspection of the area.
(3) If not, clean the inspection area with Non Aqueous Cleaner-General Non Aqueous Cleaner-General - - (Material No.08BAA9) and Textile-Lint free Cotton - (Material No.14SBA1) .
(4) If there is a TPS layer and if it does not let you do a satisfactory inspection, remove the TPS layer (Ref. AMM TASK 51-78-00-916-001).
(5) Identify the middle of the skin heat-exchanger panels to engage an endoscope where inspection holes are necessary.
(7) Clean the area and remove all debris.
4. Procedure(1) Remove the sealant and/or paint from the inspection area if this is necessary for the Non-destructive Testing Manual (NTM) task.
(2) Make sure that the inspection area is sufficiently clean to do a satisfactory inspection of the area.
(3) If not, clean the inspection area with Non Aqueous Cleaner-General Non Aqueous Cleaner-General - - (Material No.08BAA9) and Textile-Lint free Cotton - (Material No.14SBA1) .
(4) If there is a TPS layer and if it does not let you do a satisfactory inspection, remove the TPS layer (Ref. AMM TASK 51-78-00-916-001).
(5) Identify the middle of the skin heat-exchanger panels to engage an endoscope where inspection holes are necessary.
WARNING:
WHEN YOU DRILL, MACHINE, BLEND, GRIND OR SAND PARTS, USE PROTECTIVE CLOTHING, GLOVES, DUST MASK AND GOGGLES. BE CAREFUL NOT TO BREATHE THE DUST OR LET IT TOUCH YOUR SKIN. DUST AND PARTICLES ARE DANGEROUS FOR YOUR HEALTH.
CAUTION:
STOP THE DRILLING OPERATION IMMEDIATELY WHEN THE DRILL IS THROUGH THE PANEL. USE A STOP-DRILL OR SLEEVE OR OTHER PENETRATION LIMITING DEVICE TO PREVENT DAMAGE TO THE SKIN PLATE.
(6) Drill the inspection holes of dia. 10 mm (0.39 in.) in the skin heat-exchanger panels. (7) Clean the area and remove all debris.
Subtask 53-11-00-280-050-A
A. Inspection
(1) Do a special detailed inspection (ENDOSCOPE) of the fuselage internal structure from FR12 to FR14, below the heat exchanger panels. Refer to Non-destructive Testing Manual NTM 519000.
(2) Make a report of the damage after the NTM inspection:
(a) Corrosion damage:
Subtask 53-11-00-350-050-A (1) Do a special detailed inspection (ENDOSCOPE) of the fuselage internal structure from FR12 to FR14, below the heat exchanger panels. Refer to Non-destructive Testing Manual NTM 519000.
(2) Make a report of the damage after the NTM inspection:
(a) Corrosion damage:
- If you find corrosion damage, remove the skin heat-exchanger panels (Ref. AMM TASK 21-26-45-000-001). Refer to Structural Repair Manual SRM 512200 for types of corrosion, inspection, removal and corrosion protection.
- If you find this type of damage, remove the skin heat-exchanger panels (Ref. AMM TASK 21-26-45-000-001). Refer to Structural Repair Manual SRM 511100 for damage classification and corrective action.
B. Repair of the holes:
(1) Repair of the inspection holes:
Subtask 53-11-00-860-058-A (1) Repair of the inspection holes:
- If there is no damage in the inner part of the skin heat-exchanger panels, it is not necessary to remove the skin heat-exchanger panels to repair the inspection holes SRM 517713.
- If there is a damage in the inner part of the skin heat-exchanger panels, remove the skin heat-exchanger panels to repair the inspection holes SRM 517713.
C. Test Preparation:
(1) Install the skin heat-exchanger panels, if removed (Ref. AMM TASK 21-26-45-400-001).
(2) Remove the PLUG-BLANKING from each disconnected line end.
(3) Install the inlet and outlet ducts of the skin heat-exchanger (Ref. AMM TASK 21-26-42-200-001) (Ref. AMM TASK 21-26-42-200-002).
Subtask 53-11-00-861-053-A (1) Install the skin heat-exchanger panels, if removed (Ref. AMM TASK 21-26-45-400-001).
(2) Remove the PLUG-BLANKING from each disconnected line end.
(3) Install the inlet and outlet ducts of the skin heat-exchanger (Ref. AMM TASK 21-26-42-200-001) (Ref. AMM TASK 21-26-42-200-002).
D. Aircraft Maintenance Configuration
(1) Remove the WARNING NOTICE(S).
(2) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
Subtask 53-11-00-710-050-A (1) Remove the WARNING NOTICE(S).
(2) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
E. Operational Test:
(1) Operate the A/C Avionics Equipment Ventilation-System (Ref. AMM TASK 21-26-00-710-001).
(2) Make sure that there is no leakage from the closed inspection holes with your hand.
5. Close-up(1) Operate the A/C Avionics Equipment Ventilation-System (Ref. AMM TASK 21-26-00-710-001).
(2) Make sure that there is no leakage from the closed inspection holes with your hand.
Subtask 53-11-00-390-059-A
A. Sealant or Paint Application
(1) If the NTM procedure asked to remove the sealant and/or paint from the inspection area, apply sealant (refer to SRM 512400) or paint (refer to SRM 512300) on the inspection area.
Subtask 53-11-00-410-118-A (1) If the NTM procedure asked to remove the sealant and/or paint from the inspection area, apply sealant (refer to SRM 512400) or paint (refer to SRM 512300) on the inspection area.
B. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Install the insulation blankets between FR12 and FR14 (Ref. AMM TASK 25-80-00-400-001).
(3) Put the harness in position and tighten the clamps.
(4) Remove the PLUG-BLANKING from each disconnected line end.
(5) Install the air conditioning ducts between FR12 and FR14.
(6) Install the ceiling panels between FR12 and FR14 (Ref. AMM TASK 25-23-42-400-001).
(7) Install the galleys and lavatories between FR12 and FR14, if removed.
To do this, refer to the para. Component Location in the applicable ATA 25 Description/Operation: for the galleys (Ref. AMM D/O 25-31-00-00), for the lavatories (Ref. AMM D/O 25-41-00-00). In this paragraph, you will find the cross-references of the removal/installation tasks.
Subtask 53-11-00-942-101-A (1) Make sure that the work area is clean and clear of tools and other items.
(2) Install the insulation blankets between FR12 and FR14 (Ref. AMM TASK 25-80-00-400-001).
(3) Put the harness in position and tighten the clamps.
(4) Remove the PLUG-BLANKING from each disconnected line end.
(5) Install the air conditioning ducts between FR12 and FR14.
(6) Install the ceiling panels between FR12 and FR14 (Ref. AMM TASK 25-23-42-400-001).
(7) Install the galleys and lavatories between FR12 and FR14, if removed.
To do this, refer to the para. Component Location in the applicable ATA 25 Description/Operation: for the galleys (Ref. AMM D/O 25-31-00-00), for the lavatories (Ref. AMM D/O 25-41-00-00). In this paragraph, you will find the cross-references of the removal/installation tasks.
C. 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 stepladder.
Subtask 53-11-00-862-056-A (1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the stepladder.
D. Aircraft Maintenance Configuration
(1) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
(1) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).