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

__________ Subtask 72-56-00-941-051
 A. Safety Precautions
 (1) On the center pedestal, on the ENG panel 115VU:

 (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.

 (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 72-56-00-010-053
 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) Put the access platform in position. Subtask 72-56-00-040-051

 C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-56-00-010-054

 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 60272-56-00
 E E Nov 01/00 ERE
ECES E

 F 『
 E C F M E
 E E
 E 56-5B E
 E E

 4. Procedure
_________
R (Ref. Fig. 601/TASK 72-56-00-991-305)
 Subtask 72-56-00-210-051
 A. Visual inspection of the Turbine Frame Assembly:
 -------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS -------------------------------------------------------------------------------
1. Forward and aft outer
 flanges for :

 - Cracks connecting  Not serviceable
 bolt holes

 - Cracks extending  One crack 0.20 in. (5.1
 from bolt holes to mm) max. per hole with a
 outer edge of minimum 5-hole
 flange. separation between

 cracks.

 - Cracks extending  Five cracks 0.20 in.
 from bolt holes (5.1 mm) max. per flange
 toward casing skin. with a minimum 10-hole

 separation between cracks. Axial cracks only.

 - Cracks in other Five cracks per flange

 areas of flange.  0.20 in. (5.1 mm) long
 with a minimum 5 in.
 (127 mm) separation
 between any other
 cracks.

 - Nicks, scores and  Five per flange 1 in.
 scratches. (25.4 mm) long, 0.01 in.

 (0.25 mm) dup, after removal of high metal with 1 in. (25.4 mm) minimum separation.
 F 『 EEFF : ALL E Page 60372-56-00
 E E Nov 01/00 E E 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 F 『 E C F M E E E E 56-5B 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

R R  Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 15 (SHEET 1)
 F EEFF : E E ECES  ALL  『E 72-56-00EEE Page 604 Nov 01/00

R R  Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 25 (SHEET 2)
 F EEFF : E E ECES  ALL  『E 72-56-00EEE Page 605 Nov 01/00

R R  Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 35 (SHEET 3)
 F EEFF : E E ECES  ALL  『E 72-56-00EEE Page 606 Nov 01/00

R R  Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 45 (SHEET 4)
 F EEFF : E E ECES  ALL  『E 72-56-00EEE Page 607 Nov 01/00

R R  Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 55 (SHEET 5)
 F EEFF : E E ECES  ALL  『E 72-56-00EEE Page 608 Nov 01/00

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

 -------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS -------------------------------------------------------------------------------
2. Engine mounting lug areas, airframe attach points only for :
 - Cracks out of bolt holes

 - Cracks in welds or in other areas of engine mounting lug area.

 - Nicks, scores and scratches.

3. All other areas of outer casing skin for :
 - Cracks

- Nicks, scores and scratches.

　
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(113)