3. Job Set-up
__________
Subtask 71-21-11-860-054
A. Aircraft Maintenance Configuration
(1) On the center pedestal, on the ENG panel 115VU, make sure that a warning notice is in position to tell persons not to start the engine.
(2) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a warning notice is in position to tell persons not to energize the FADEC 1(2).
(3) Make sure that the access platform is in position.
(4) Make sure that the slats are retracted and install TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER (98D27803500001) on the flap and slat control lever.
(5) Make sure that RODS - FWD ENG MOUNT (98D71203003000) is installed on the engine.
Subtask 71-21-11-010-066
B. Get Access
(1) Make sure that the fan cowl doors are open (Ref. TASK 71-13-00-010-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR
F 『 EEFF : ALL E Page 41771-21-11
E E May 01/01 ERE ECES E
F 『
E C F M E
E E
E 56-5B E
E E
(2) Make sure that the thrust reverser doors are open to the 45 degrees position (Ref. TASK 78-36-00-010-040): FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
Subtask 71-21-11-040-057
C. Make sure that the thrust reverser is unserviceable (Ref. TASK 78-30-00-481-041).
4. Procedure
_________
(Ref. Fig. 403/TASK 71-21-11-991-909)
Subtask 71-21-11-420-062
A. Installation of the forward engine mount bolt one at a time:
R (1) Apply Silicone Lubricant (Material No. CP5063) to the bolt (85) threads, the washer (90) and the nut (120).
(2) Install the bolt (85), the washer (90) and the nut (120).
NOTE : You must install the washer (90) under bolt (85).
____
(3) Turn the nut (120) until it lightly touch the lower face of the forward mount surface. Put the retainer (125) on the nut (120) and set the retainer in the correct assembled position. Remove the retainer from this position and hold the nut (120) with a wrench.
R (4) TORQUE the bolt (85) to between 320 and 350 lbf.ft (43.38 and 47.45
R m.daN): this is applicable if the nut (120) does not turn. Safety with lockwire 0.032 in. (0.8 mm) dia. (Material No. CP8001), corrosion lockwire 0.047 in. (1.2 mm) dia., or safety cable 0.032 in.
(0.8 mm) dia. (Material No. CP8006).
NOTE : You can use lockwire or safety cable ranging from 0.032 in.
____ (0.8 mm) dia. to 0.047 in. (1.2 mm) dia. to safety the bolt (85).
F 『 EEFF : ALL E Page 41871-21-11
E E Nov 01/01 E E ECES E
F 『
E C F M E
E E
E 56-5B E
E E
R (5) Install the bolt (100), the washer (105), the retainer (125), the R washer (115) and the nut (110) to engine mount (95).
R (6) TORQUE the bolt (100) to between 24 and 36 lbf.in (0.27 and 0.40 R m.daN).
R 5. Close-up
________
R Subtask 71-21-11-080-053
R A. Remove the RODS - FWD ENG MOUNT (98D71203003000) from the engine.
R Subtask 71-21-11-410-065
R B. Close the thrust reverser cowl doors (Ref. TASK 78-36-00-410-040): R FOR 1000EM1 R 451AL, 452AR R FOR 1000EM2 R 461AL, 462AR
R Subtask 71-21-11-440-054
R C. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
R Subtask 71-21-11-410-066
R D. Close Access
R (1) Make sure that the work area is clean and clear of tool(s) and other R items.
R (2) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): R FOR 1000EM1 R 437AL, 438AR R FOR 1000EM2 R 447AL, 448AR
R (3) Remove the warning notice(s).
R (4) On the panel 114VU remove the locking tool from the flap and slat R control lever.
F 『 EEFF : ALL E Page 41971-21-11
E E May 01/99 E E ECES E
F 『
E C F M E
E E
E 56-5B E
E E
TASK 71-21-11-000-042
Removal of the Forward Engine Mount Links and Cross Beam Assembly without
Engine Removal
1. Reason for the Job
__________________
Self Explanatory
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------
No specific warning notice
No specific access platform 1.5 m (4 ft. 11 in.)
98D27803500001 1 TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER
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 动力装置 POWER PLANT 1(127)
