-(Ref. TASK 25-00-00-340-029).
(3) For the repair of floor panel
(Ref. ASRM 53-02-00-208).
Subtask 25-00-00-210-056
B. General Procedure
(1) Identify the damage type.
(a) Damage to the edge(s).
(Ref. Fig. 819/TASK 25-00-00-991-033)
EFF : ALL 25-00-00Page A805
Aug 01/05
R
CES
CC Honeycomb Linings, Protection Patch - General Information
Figure 818/TASK 25-00-00-991-048
EFF : ALL 25-00-00Page A806 Aug 01/05 R CES
CC Honeycomb Linings - Example of Edge Damage Figure 819/TASK 25-00-00-991-033
R EFF : CES ALL 25-00-00 Page A807 Aug 01/05
(b)
Damage through the panel.
(Ref. Fig. 820/TASK 25-00-00-991-034)
(c)
Damage not through the panel.
(Ref. Fig. 821/TASK 25-00-00-991-035)
(2)
Measure the damaged area.
L: Length of the damage (biggest dimension)
W: Width of the damage
D: Diameter of the damage
(3)
Select the appropriate repair method. (Ref. Fig. 822/TASK 25-00-00-991-027)
(a)
Do the repair within 100 flight hours if the "damage not through" has:
-
a maximum diameter of 30 mm (1.18 in.)
or
-
a maximum length of 200 mm (7.87 in.) and a maximum width of 25 mm (0.98 in.).
(b)
Do the repair immediately if:
-
the damage goes through the panel.
-
the edge(s) is damaged.
-
the dimension(s) are more than the limits for the repair within 100 flight hours.
NOTE : Repair of dents (without cracks) in the skin of the view
____ side of the lining panel is not required, except in . If the area of the edge filler is damaged it is classified as a damage to the edge.
(c)
The total damaged area of a lining panel must be less than 25% of its surface.
(d)
If the damage is more than the permitted limits, replace the panel (Ref. TASK 25-00-00-340-019).
EFF : ALL 25-00-00Page A808
Aug 01/05
R
CES
CC Honeycomb Linings - Example of Damage Through Figure 820/TASK 25-00-00-991-034
R EFF : CES ALL 25-00-00 Page A809 Aug 01/05
CC Honeycomb Linings - Example of Damage Not Through Figure 821/TASK 25-00-00-991-035
R EFF : CES ALL 25-00-00 Page A810 Aug 01/05
General Damage/Repair Identification Chart Figure 822/TASK 25-00-00-991-027
R EFF : CES ALL 25-00-00 Page A811 Aug 01/05
Subtask 25-00-00-020-085
C. Removal of the Damaged Lining(s)
(1) Remove the damaged linings if necessary for the selected repair procedure.
(a)
FWD cargo compartment:
-
(Ref. TASK 25-54-11-000-001)
-
(Ref. TASK 25-54-12-000-001)
-
(Ref. TASK 25-54-12-000-002)
-
(Ref. TASK 25-54-12-000-003)
(b)
AFT cargo compartment:
-
(Ref. TASK 25-55-11-000-001)
-
(Ref. TASK 25-55-11-000-002)
-
(Ref. TASK 25-55-11-000-003)
-
(Ref. TASK 25-55-12-000-001)
-
(Ref. TASK 25-55-12-000-002)
-
(Ref. TASK 25-55-12-000-003)
Subtask 25-00-00-210-064
D. Do an inspection of the component interface and/or the adjacent area.
(1)
Examine the support struts behind the removed linings and replace them if necessary:
(a)
FWD cargo compartment
-(Ref. ASRM 532300)
(b)
AFT cargo compartment
-
(Ref. TASK 53-43-11-000-001)
-
(Ref. TASK 53-43-11-400-001)
-
(Ref. ASRM 534300)
(2)
Make sure that all the equipment components are not damaged and in correct condition.
EFF : ALL 25-00-00Page A812
Aug 01/05
R
CES Subtask 25-00-00-340-097
E. Repair of the Damaged Lining(s)
(1) Do the repair of the damaged lining(s) as described in the tasks that follow:
-Filler Repair Method (Damage Not Through) - All Cargo Compartment Linings with Honeycomb Core (Ref. TASK 25-00-00-340-004)
-Patch and Filler Repair Method (Damage Not Through) - All Cargo Compartment Linings with Honeycomb Core (Ref. TASK 25-00-00-340-005)
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：A320飞机维护手册 AMM EQUIPMENT/FURNISHINGS 设备1(72)
