(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. 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. TASK 25-00-00-330-002).
EFF : ALL
25-10-00Page 808
5. Close up
________ Subtask 25-10-00-410-051
A. Installation of the Lateral Panels and Equipment
(1) If necessary, install the reading lights 17LE, 18LE, 19LE, 21LE, 22LE (Ref. TASK 33-12-15-400-001) and 25LE, 26LE (Ref. TASK 33-12-12-400-001).
Subtask 25-10-00-865-053
B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 1LE, 2LE, 4LE, 5LE.
EFF : ALL
25-10-00Page 809
TASK 25-10-00-330-003
Repair of the Flight-Compartment Rear Panels
1. Reason for the Job
__________________
Self Explanatory
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
25-00-00-330-002 Repairs to Nonstructural Components (not in the Cargo Compartments) 25-00-00-330-003 Repairs to Surface Damage of Composite Components (not in the Cargo Compartments) 25-10-00-991-003 Fig. 803
3. Job set up
__________
Subtask 25-10-00-010-052
A. Removal of the Rear Panels
(1)
If necessary, remove the panel from the aircraft.
(2)
List of the rear/panels.
(Ref. Fig. 803/TASK 25-10-00-991-003)
-------------------------------------------------------------------------------
|PANEL | | | IPC | ITEM|IDENT | DESCRIPTION | MATERIAL | CROSS REF. | REMARKS -------------------------------------------------------------------------------
1 |212JW | PANEL-UPPER | Foam | 25130119 | -------------------------------------------------------------------------------2 |212HW | PANEL ASSY-SIDE | Sandwich | 25130119 | -------------------------------------------------------------------------------3 | | PANEL ASSY | Laminate | 25130112 | -------------------------------------------------------------------------------4 | | PANEL ASSY-SIDE | Sandwich | 25130122 | -------------------------------------------------------------------------------5 | | PANEL-FRONT | Sandwich | 25130122 | -------------------------------------------------------------------------------
EFF : ALL
25-10-00Page 810
Flight-Compartment Rear Panels
Figure 803/TASK 25-10-00-991-003
EFF : ALL 25-10-00 Page 811
Feb 01/98
CES
-------------------------------------------------------------------------------
|PANEL | | | IPC | ITEM|IDENT | DESCRIPTION | MATERIAL | CROSS REF. | REMARKS -------------------------------------------------------------------------------
6 | | PANEL ASSY-SIDE | Sandwich | 25130122 | -------------------------------------------------------------------------------7 | | PANEL ASSY | Sandwich | 25130113 | -------------------------------------------------------------------------------8 |212KW | PANEL ASSY | Sandwich | 25130112 | -------------------------------------------------------------------------------
4. Procedure
_________
Subtask 25-10-00-330-052
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. 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. TASK 25-00-00-330-002).
5. Close up
________
Subtask 25-10-00-410-052
A. Installation of the Rear Panels
(1) If necessary, install the panels in the aircraft.
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機(jī)維護(hù)手冊(cè) AMM EQUIPMENT/FURNISHINGS 設(shè)備1(94)
