Flame Arrestor and Flange Assembly
Figure 401B/TASK 72-56-00-991-300-A
F 『R EEFF : 106-149, 155-199, 208-299, 301-399, E Page 40672-56-00
E E401-499, Aug 01/05 E E ECES ER **ON A/C 106-149, 155-199, 208-299, 301-399, 401-499,
F 『
E C F M E
E E
E 56-5B E
E E
Subtask 72-56-00-020-050-A
A. Removal of the Flame Arrestor
(1) Remove the six bolts (20) which attach the flame arrestor (30) to the oil inlet cover through the flange assembly (160).
Subtask 72-56-00-020-051-A
B. Removal of the Flange Assembly NOTE : This procedure is for Turbine Frame with Tangential Symetrical
____
Section Struts only.
(1) Remove the sixteen bolts (150) which attach the flow path fairing to the outer circle of the flange assembly (160) through the plate lock (170).
(2) Remove the twenty four bolts (70) which attach the mid circle of the flange assembly (160) to the LPT frame hub rear flange.
(3) Remove the flange assembly (160) from the LPT frame.
(4) Remove and discard the gasket seal (80).
F 『R EEFF : 106-149, 155-199, 208-299, 301-399, E Page 40772-56-00
E E401-499, Aug 01/05 E E ECES E E 56-5B E
F 『
E C F M E
E E
E E **ON A/C ALL
TASK 72-56-00-400-001
Installation of the Flame Arrestor and Flange Assembly
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 Torque Wrench : range 36.00 to 220.00 lbf.in
(0.40 to 2.60 m.daN)
B. Consumable Materials
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. CP2101 USA MIL-T-5544 graphite grease (Ref. 70-30-00)
C. Expendable Parts
-------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN -------------------------------------------------------------------------------
80 gasket seal 72-56-00 02A-010 80 gasket seal 72-56-00 02B-010
F 『 EEFF : ALL E Page 40872-56-00
E E May 01/05 ERE
ECES E
F 『
E C F M E
E E
E 56-5B E
E E
D. Referenced Information
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
78-11-11-000-041 Removal of the Core Nozzle Assembly
78-11-11-400-041 Installation of the Core Nozzle Assembly
78-11-12-000-041 Removal of the Centerbody
78-11-12-400-041 Installation of the Centerbody
**ON A/C 001-049, 052-099, 101-105, 151-154, 201-207,
72-56-00-991-300 Fig. 401
**ON A/C 051-051,
72-56-00-991-300-B Fig. 401A
R **ON A/C 106-149, 155-199, 208-299, 301-399, 401-499,
72-56-00-991-300-A Fig. 401B
**ON A/C ALL
3. Job Set-up
__________
Subtask 72-56-00-860-050
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 core nozzle is removed (Ref. TASK 78-11-11-000-041).
F 『 EEFF : ALL E Page 40972-56-00
E E Aug 01/05 E E ECES E
F 『
E C F M E
E E
E 56-5B E
E E
(4) Make sure that the centerbody is removed (Ref. TASK 78-11-12-000-041).
4. Procedure
_________
**ON A/C 001-049, 052-099, 101-105, 151-154, 201-207,
(Ref. Fig. 401/TASK 72-56-00-991-300)
**ON A/C 051-051,
(Ref. Fig. 401A/TASK 72-56-00-991-300-B) R **ON A/C 106-149, 155-199, 208-299, 301-399, 401-499,
(Ref. Fig. 401B/TASK 72-56-00-991-300-A)
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 2(105)
