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R **ON A/C 106-149, 155-199, 208-299, 301-399, 401-499,
72-56-00-991-301-A Fig. 402B
**ON A/C 001-049, 052-099, 101-105, 151-154, 201-207,
72-56-00-991-302 Fig. 403
**ON A/C 051-051,
72-56-00-991-302-B Fig. 403A R **ON A/C 106-149, 155-199, 208-299, 301-399, 401-499,
72-56-00-991-302-A Fig. 403B
**ON A/C ALL
3. Job Set-up
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Subtask 72-56-00-860-051
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 flame arrestor and the flange assembly are removed (Ref. TASK 72-56-00-000-001).
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4. Procedure
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**ON A/C 001-049, 052-099, 101-105, 151-154, 201-207,
(Ref. Fig. 402/TASK 72-56-00-991-301)
**ON A/C 051-051,
(Ref. Fig. 402A/TASK 72-56-00-991-301-B) R **ON A/C 106-149, 155-199, 208-299, 301-399, 401-499,
(Ref. Fig. 402B/TASK 72-56-00-991-301-A)
**ON A/C 001-049, 052-099, 101-105, 151-154, 201-207,
(Ref. Fig. 403/TASK 72-56-00-991-302)
**ON A/C 051-051,
(Ref. Fig. 403A/TASK 72-56-00-991-302-B) R **ON A/C 106-149, 155-199, 208-299, 301-399, 401-499,
(Ref. Fig. 403B/TASK 72-56-00-991-302-A)
**ON A/C 001-049, 051-099, 101-105, 151-154, 201-207,
Subtask 72-56-00-420-052
A. Installation of the Oil Inlet Cover (80) NOTE : For Turbine Frame with Tangential Non Symetrical Section Struts or
____
with Radial Struts only.
(1) Lubricate a new O-ring (60) with engine oil (Material No. CP2442).
(2) Install the O-ring (60) on the nipple (50), with the TOOL SET SEAL FITTING AGB-TGB (856A2794G01).
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(3) Install the nipple (50) on the oil inlet cover (80) at 7:00 o'clock position, aft looking forward. Tighten by hand to seat.
(4) TORQUE the nipple (50) to between 180 and 195 lbf.in (2.03 and 2.20 m.daN).
(5) Safety the nipple (50) to the oil inlet cover (80) with lockwire
0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in.
(0.8 mm) dia (Material No. CP8002).
(6) Lubricate a new O-ring (20) with engine oil (Material No. CP2442).
(7) Install the O-ring (20) in the front groove on the oil inlet cover (80).
(8) Position a new Gasket seal (10) on the oil inlet cover (80).
(9) Lubricate the threads of the bolts (20) with graphite grease (Material No. CP2101).
(10) Install the oil inlet cover (80) with the ADAPTER, PULLER - OIL INLET COVER (856A3419G02), in the LPT frame. Match the position of the oil inlet cover flange with the oil scavenge tube which comes out at the bottom of the No. 5 bearing support.
(11) Attach the oil inlet cover (80) to the No. 5 bearing support with bolts (30).
(12) TORQUE the bolts (30) to between 110 and 120 lbf.in (1.24 and 1.35 m.daN).
(13) Safety bolts with lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8 mm) dia (Material No. CP8002).
R **ON A/C 106-149, 155-199, 208-299, 301-399, 401-499,
Subtask 72-56-00-420-052-A
A. Installation of the Oil Inlet Cover (80)
NOTE : For Turbine Frame with Tangential Symetrical Section Struts only.
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(1) Lubricate a new O-ring (190) with engine oil (Material No. CP2442).
(2) Install the O-ring (190) on the nipple (180), with the TOOL SET SEAL FITTING AGB-TGB (856A2794G01).
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(3) Install the nipple (180) on the oil inlet cover (160) at 7:00 o'clock position, aft looking forward. Tighten by hand to seat.
(4) TORQUE the nipple (180) to between 180 and 195 lbf.in (2.03 and 2.20 m.daN). 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(110)
