A320飞机维护手册 AMM EXHAUST 2(57)

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 Subtask 78-32-11-480-050
 E. Install the SAFETY SLEEVE - PIVOTING DOOR ACTUATOR (HIX3005) on the blocker door actuator (Ref. TASK 78-32-41-480-001).
 Subtask 78-32-11-210-052
R F. Do a visual inspection of the inner panels as follows:
 -------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS -------------------------------------------------------------------------------
1. Examine the inner barrel for:
 A. Delamination
1.5 in. (38.1 mm) maximum length.
 7.4 in. (188 mm) minimum separation, between other delaminations, holes or cracks.
Five delaminations maximum per half door.
Monitor at "A" check.
It is recommended that alldelaminations be repairedno later than airplane "C"check.
If more than fivedelaminations, replace the half door (Ref. TASK 78-32-11-000-002) and (Ref. TASK 78-32-11-400-002) .
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B. Crack

C. Gouge, nick and scratch
D. Hole
1 in. (25.4 mm) maximum  Seal damaged area from
 length in any direction.  entrance of moisture with
 aerodynamic tape (Material
 No. CP2517).
 7.4 in. (188 mm) minimum  Monitor at "A" check.
 separation, between
 other cracks, holes and
 delaminations.
 Five cracks maximum per  If the cracks are not in
 half door.  the serviceable limits,
 replace the half door
 (Ref. TASK 78-32-11-000-
002) and (Ref. TASK 78-32-
11-400-002) .
0.008 in. (0.20 mm)  Monitor at "A" check.
maximum depth over a 8  If gouges, nicks or
 in. (203.2 mm) length.  scratches are not in the
 serviceable limits,
 replace the half door
 (Ref. TASK 78-32-11-000-
002) and (Ref. TASK 78-32-
11-400-002).
1 in. (25.4 mm) maximum  Seal damaged area from
 diameter  entrance of moisture with
 aerodynamic tape (Material
 No. CP2517).
 7.4 in. (188 mm) minimum  Monitor at "A" check.
 separation, between
 other holes, cracks and
 delaminations.
 Five holes maximum per  If the holes are not in
 half door.  the serviceable limits,
 replace the half door
 (Ref. TASK 78-32-11-000-
002) and (Ref. TASK 78-32-
11-400-002) .

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E. Corrosion
2. Examine heat shields part for:
 A. Crack
B. Gouge, nick and scratch
C. Missing rivets
R D. Bulges, gaps
 (1) At trailing edge

(2) Heatshield area other than trailing edge

 E. Heat coloration
No limit

None permitted
0.008 in. (0.20 mm) maximum depth over a 8 in. (203.2 mm) length.
Ten percent missing per row of rivets
No Limit
Permitted if there is no crack or hole
Monitor at "A" check.
 Do a new surface treatment
 at "C" check, (Ref. SPM
 70-62-12).

If cracked repair before
 flight.

Monitor at "A" check.

Missing rivets must be
separated by four good
 rivets. Missing end rivets
 not permitted. Monitor at
 "A" check.

Allowable if there is no
crack or hole.
 Record location and
 inspect at airplane "A"
 check.

Permitted if there is no
crack or hole.

 Permitted if there is no
 crack or hole.

Permitted if there is no
 other damage.

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