R NOTE : It is permitted to have polish marks on the inner skin surface.
____
 A. Crack  No crack permitted Replace centerbody (Ref. TASK 78-11-12-000-041) and (Ref. TASK 78-11-12-400-041).
 2. Examine the remaining
 areas of the
 centerbody and welded
 joints for:

R NOTE : It is permitted to have polish marks on the inner skin surface.
____
 A. Crack  1 in. (25.4 mm) maximum. Stop-drill ends with 0.125 in. (3.2 mm) drill. Monitor at "A" check. For
 F 『 EEFF : ALL E Page 60278-11-12
 E E May 01/04 E E ECES E

 F  『
 E  C F M  E
 E  E
 E  56-5B  E
 E  E

 -------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS -------------------------------------------------------------------------------
B. Gouge or scratch
C. Dent
D. Missing or damaged rivets
6 in. (152.4 mm) maximum total of all cracks
 4 in. (101.6 mm) minimum separation from other cracks
0.010
 in. (0.25 mm) maximum depth.

1.5 in. (38.1 mm) maximum length.

 Gouges up to a maximum of 0.12 in. (3.05 mm) in size.

2.5
 in. (63.5 mm) maximum diameter.

0.25 in. (6.3 mm) maximum depth.
 0.25 in. (6.3 mm) minimum radius
Maximum of 5 percent missing or damaged rivets. There must be at least one good rivet between any two that are missing or damaged.
 permanent repair (Ref. CMM 781105).
Monitor at "A" check. Forpermanent repair (Ref. CMM 781105).
Clean out damage with a
0.190 in. (4.8 mm) drill.
OK for flight. Reform tosmooth contour at next shop visit.
For permanent repair (Ref.CMM 781105).
 F 『 EEFF : ALL E Page 60378-11-12
 E E May 01/04 ERE
ECES E F 『 E C F M E E E E 56-5B E F 『 E C F M E E E E 56-5B E

 Centerbody
 Figure 601/TASK 78-11-12-991-301- 12 (SHEET 1)
 F EEFF :  ALL  『E 78-11-12 Page 604 
E  E  Feb 01/98
 E  E
 ECES  E

 Centerbody
 Figure 601/TASK 78-11-12-991-301- 22 (SHEET 2)
 F EEFF :  ALL  『E 78-11-12 Page 605 
E  E  Feb 01/98
 E  E
 ECES  E

 F 『
 E C F M E
 E E
 E 56-5B E
 E E

 5. Close-up
________
 Subtask 78-11-12-869-051
 A. Make sure that the work area is clean and clear of tool(s) and other items.
 Subtask 78-11-12-942-050
 B. Remove the warning notice(s). R
 F 『 EEFF : ALL E Page 60678-11-12
 E E Aug 01/05 E E ECES E F 『 E C F M E E E E 56-5B E

 Centerbody
 Figure 602/TASK 78-11-12-991-302

 F 『 EEFF : ALL E Page 60778-11-12
 E E Aug 01/05 ERE
ECES E

 F 『
 E C F M E
 E E
 E 56-5B E
 E E
 THRUST REVERSER - DESCRIPTION AND OPERATION

___________________________________________
 1. General
_______ (Ref. Fig. 001) The fan thrust reverser is located immediatly downstream of the fan frame. An adaptor ring attached to the rear engine fan frame interfaces between the engine and the reverser itself.
 A. Direct thrust configuration In direct thrust configuration, the cowling masks the blocker doors, thus providing fan flow ducting with minimized thrust loss.
 B. Reverse thrust configuration In reverse thrust configuration, the blocker doors are deployed in order to obstruct the fan duct ; the fan flow is rejected laterally through the reverser with a forward velocity component which provides the reverse thrust. The reverse mode is controlled and indicated in the cockpit (Ref. 78-31-00). The reverse mode is hydraulically actuated after cockpit command. The reverse thrust mode is only operative on ground
 2. Description
___________ (Ref. Fig. 002, 003) To give access to the engine, the reverser consists of two half-fan ducts cowls (D - ducts) hinged at pylon and latched at the bottom. The cowl opening system is used for maintenance purpose only. It is hydraulically actuated and composed of an actuator on each cowl, a hydraulic junction box and the associated pipings (Ref. 78-36-00). The thrust reverser includes:
 - two blocker doors on each cowl, acoustic linings, a pressure relief system and fire walls (Ref. 78-32-00).

 - LP turbine case and core compartment cooling systems (Ref. 75-00-00).

 - a thrust reverser system composed of :
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機維護手冊 AMM EXHAUST 1(21)