DOC AIRBUS | AMM A320FRepair of the Flight-Compartment Ceiling Panels
TASK 25-10-00-330-001-A
Repair of the Flight-Compartment Ceiling Panels
1. Reason for the Job
Self explanatory
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 25-10-00-865-050-A
Subtask 25-10-00-330-050-A
Subtask 25-10-00-410-050-A
[Rev.10 from 2021]
2026.03.31 23:27:39 UTC
Repair of the Flight-Compartment Ceiling Panels
1. Reason for the Job
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | SAFETY CLIP - CIRCUIT BREAKER |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 211 | COCKPIT |
| 212 | COCKPIT |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 25-00-00-330-002-A | Repairs of Non-structural Components (not in the Cargo Compartments) |
| TASK 25-00-00-330-003-A | Repairs of Surface Damage of Composite Components (not in the Cargo Compartments) |
| TASK 25-13-41-000-001-A | Removal of the Ceiling Panels |
| TASK 25-13-41-400-001-A | Installation of the Ceiling Panels |
Flight-Compartment Ceiling PanelsSubtask 25-10-00-865-050-A
A. Open, safety and tag this(these) circuit breaker(s):
Subtask 25-10-00-010-050-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 49VU | LIGHTING/EMER LT/CKPT/DOME | 1LE | H08 |
| ** ON A/C NOT FOR ALL | |||
| 49VU | LIGHTING/EMER LT/CKPT/DOME | 1LE | H06 |
| ** ON A/C ALL | |||
| 122VU | LIGHTING/CKPT/DOME | 3LE | Y06 |
B. Removal of the Ceiling Panels
(1) If necessary remove the panel from the aircraft (Ref. AMM TASK 25-13-41-000-001).
(2) List of the ceiling panels.
4. Procedure(1) If necessary remove the panel from the aircraft (Ref. AMM TASK 25-13-41-000-001).
(2) List of the ceiling panels.
| ITEM | PANEL IDENT | DESCRIPTION | MATERIAL | IPC CROSS REF. | REMARKS |
|---|---|---|---|---|---|
| 1 | 211GC | COVER ASSY | Laminate | 25130103 | Non repairable |
| 2 | 211HC | PANEL ASSY | Sandwich | 25130103 | |
| 3 | 211JC | PANEL ASSY | Sandwich | 25130101 | |
| 4 | 211FC 212FC | PANEL ASSY PANEL ASSY | Sandwich Sandwich | 25130101 25130102 | |
| 5 | 211DC 212DC | DOOR ASSY DOOR ASSY | Laminate Laminate | 25130101 25130102 | Non repairable Non repairable |
| 6 | 211EC 212EC | PANEL ASSY PANEL ASSY | Joggling Joggling | 25130101 25130102 | |
| 7 | 211CC 212CC | PANEL ASSY PANEL ASSY | Joggling Joggling | 25130101 25130102 | |
| 8 | 211BC 212BC | PANEL ASSY PANEL ASSY | Sandwich Sandwich | 25130101 25130102 | |
| 9 | 211AC 212AC | PANEL ASSY PANEL ASSY | Sandwich Sandwich | 25130101 25130102 | |
Subtask 25-10-00-330-050-A
A. Damage to the Lining Panel
(1) Superficial Damage
(a) If the damage diameter is less than or equal to 50 mm (1.9685 in.) and if the honeycomb core is not damaged, do the repair of the panel (Ref. AMM TASK 25-00-00-330-003).
(2) Significant Damage
(a) If the honeycomb core is damaged and/or if the damage diameter is more than 50 mm (1.9685 in.) or if the honeycomb structure is debonded, do the repair of the panel (Ref. AMM TASK 25-00-00-330-002).
5. Close-up(1) Superficial Damage
(a) If the damage diameter is less than or equal to 50 mm (1.9685 in.) and if the honeycomb core is not damaged, do the repair of the panel (Ref. AMM TASK 25-00-00-330-003).
(2) Significant Damage
(a) If the honeycomb core is damaged and/or if the damage diameter is more than 50 mm (1.9685 in.) or if the honeycomb structure is debonded, do the repair of the panel (Ref. AMM TASK 25-00-00-330-002).
Subtask 25-10-00-410-050-A
A. Installation of the Ceiling Panels
(1) If necessary, install the panel in the aircraft (Ref. AMM TASK 25-13-41-400-001).
Subtask 25-10-00-865-051-A (1) If necessary, install the panel in the aircraft (Ref. AMM TASK 25-13-41-400-001).