(a) Put a warning notice to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
F 『 EEFF : ALL E Page 66572-54-00
E E Nov 01/04 ERE
ECES E
F 『
E C F M E
E E
E 56-5B E
E E
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a warning notice to tell persons not to energize the FADEC 1(2).
Subtask 72-54-00-010-088
B. Get Access
(1) Open the fan cowl doors (Ref. TASK 71-13-00-010-040):
FOR 1000EM1
437AL, 438AR
FOR 1000EM2
447AL, 448AR
(2) Let the temperature of parts decrease to ambient temperature.
Subtask 72-54-00-040-064
C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041).
Subtask 72-54-00-010-089
D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040):
FOR 1000EM1
451AL, 452AR
FOR 1000EM2
461AL, 462AR
F 『 EEFF : ALL E Page 66672-54-00
E E Nov 01/04 ERE
ECES E 4. Procedure
F 『
E C F M E
E E
E 56-5B E
E E
_________ Subtask 72-54-00-210-056
A. Inspect the Turbine Case for the Following
-------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS -------------------------------------------------------------------------------
1. Aft flange.
A. Cracks that connect bolt holes.
B. Cracks that extend from bolt holes to outer edge of flange.
C. Cracks that extend from bolt holes toward casing skin.
D. Cracks in other areas of flange.
E. Nicks, scores and scratches.
F. Cracks in flange/case skin radius.
2. Casing skin for:Not serviceable
5 cracks with a minimum5 hole separationbetween cracks.
Not serviceable.
5 cracks per flange 0.25 in. (6.35 mm) long with a minimum 5 in. (127 mm) separation between any other cracks.
Any number 1 in. (25.4mm) long 0.01 in. (0.25 mm) deep after removal of high metal with 1 in.
(25.4 mm) minimum separation.
Not serviceable.
See limit extensions(Ref. TASK 72-00-00-200-025).
F 『 EEFF : ALL E Page 66772-54-00
E E Nov 01/04 ERE
ECES E
F 『
E C F M E
E E
E 56-5B E
E E
-------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS -------------------------------------------------------------------------------
A. Cracks in parent Any number 0.04 in. (1 See limit extensions
metal mm) long and 2 in. (50.8 (Ref. TASK 72-00-00-200-
mm) minimum apart. 025).
B. Nicks and Any number 0.01 in.
scratches. (0.25 mm) deep after
removal of high metal.
C. Dents Any number, smooth
contour, 0.02 in. (0.5
mm) deep.
3. All threaded ports
and bosses for:
A. Damaged threads. One full thread
cumulative or continuous
may be removed after
chasing threads.
B. Cracks in weld of One per port in boss See limit extensions
ports and bosses. 0.04 in. (1 mm) long. (Ref. TASK 72-00-00-200-
025).
4. Ring sector support
for:
A. Cracks Any number if attachment
parts are secured.
5. Angle brackets for:
A. Broken bracket. Not serviceable.
B. Cracks in all Any amount providing
other areas. cooling air tubes and
attaching fasteners are
secured.
6. Cooling air tube
supports for:
F 『 EEFF : ALL E Page 66872-54-00
E E Nov 01/04 ERE
ECES E
F 『
E C F M E
E E
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機維護手冊 AMM ENGINE 發動機 2(95)
