F 『
E C F M E
E E
E E -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
72-23-00-991-302 Fig. 403
3. Job Set-up
__________
Subtask 72-23-00-860-062
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) 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. Procedure
_________
(Ref. Fig. 403/TASK 72-23-00-991-302)
Subtask 72-23-00-420-061
A. Install the Mid Acoustical Panels as follows:
CAUTION : COATING SCREWS IS MANDATORY.
_______ R R (1) Coat with graphite grease (Material No. CP2101) screw threads and
R contact faces under screw heads.
R R (2) Do a visual inspection of the mid acoustical panel cup (Ref. TASK 72-R 23-00-280-006).
R (3) If panel cup is found pierced (Ref. TASK 72-23-00-400-044).
F 『 EEFF : ALL E Page 41972-23-00
E E May 01/05 E E ECES E
F 『
E C F M E
E E
E 56-5B E
E E
R (4) Install the panel assy on the forward case, and attach it with 3 short screws (100) and 3 long screws (101).
CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO APPROACH ALL
_______ ACOUSTICAL PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW DRIVERS.
NOTE : The longest screws have to be re-installed at the aft end of
____
panel.
R (5) Measure the self locking nut torque of each nut when you start to R tighten the screw.
R CAUTION : DO NOT EXCEED THE SPEED OF 200 RPM TO TORQUE ALL ACOUSTICAL
_______ R PANEL SCREWS BY USING PNEUMATIC OR ELECTRICAL SCREW R DRIVERS.
R NOTE : Whenever possible, start to torque with the screws in the
____ R center of the acoustical panels.
R NOTE : Make sure that the screws are not damaged, replace them if
____ R necessary.
R
R (a) If the self locking nut torque is less than 4.5 lbf.in (0.05
R m.daN), (Ref. TASK 72-23-00-400-043).
R
R (b) If the self locking nut torque is within 4.5 lbf.in (0.05 m.daN)
R and 31 lbf.in (0.35 m.daN), torque the screws to between 84 and
R 93 lbf.in (0.94 and 1.05 m.daN)
R
R (c) If the self locking nut torque is more than 31 lbf.in (0.35
R m.daN) but less than 49 lbf.in (0.55 m.daN), torque the screws at
R the running torque value and add 44 lbf.in (0.5 m.daN).
R (d) If the self locking torque is more than 49 lbf.in (0.55 m.daN),
R remove the engine (Ref. TASK 71-00-00-000-042) and do the engine
R shop repair procedure to replace the self locking nut (Ref. ESM
R 722302300008).
R
F 『 EEFF : ALL E Page 42072-23-00
E E May 01/05 E E ECES E 5. Close-up
F 『
E C F M E
E E
E 56-5B E
E E
________ Subtask 72-23-00-410-078
A. Close Access
(1) Install the fan rotor blades at the locations recorded at the removal (Ref. TASK 72-21-00-400-007).
(2) Install the spinner rear cone (Ref. TASK 72-21-00-400-006).
(3) Install the spinner front cone (Ref. TASK 72-21-00-400-005).
(4) Make sure that the work area is clean and clear of tool(s) and other items.
(5) Remove the access platform(s).
(6) Remove the warning notice(s).
F 『 EEFF : ALL E Page 42172-23-00
E E May 01/05 ERE
ECES E TASK 72-23-00-000-026 Removal of the Aft Acoustical Panels
F 『
E C F M E
E E
E 56-5B E
E E
1. Reason for the Job
__________________
Self Explanatory
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
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 ENGINE 发动机 1(123)
