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).
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(3) Make sure that the access platform is in position.
Subtask 78-11-11-010-054
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
(2) Make sure that the thrust reverser doors are open: (Ref. TASK 78-36-00-010-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
Subtask 78-11-11-040-052
C. Make sure that the thrust reverser is unserviceable (Ref. TASK 78-30-00-481-041).
4. Procedure
_________
R **ON A/C 001-049, 054-099, 101-149, 152-199, 211-299, 401-499,
(Ref. Fig. 401/TASK 78-11-11-991-301)
**ON A/C 051-053, 151-151, 201-210,
(Ref. Fig. 401A/TASK 78-11-11-991-301-A)
**ON A/C 301-399,
(Ref. Fig. 401B/TASK 78-11-11-991-301-B)
R **ON A/C 001-049, 054-099, 101-149, 152-199, 211-299, 301-399, 401-499,
(Ref. Fig. 402/TASK 78-11-11-991-302)
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**ON A/C 051-053, 151-151, 201-210,
(Ref. Fig. 402A/TASK 78-11-11-991-302-A)
**ON A/C ALL
Subtask 78-11-11-480-050
A. Installation of a sling
(1) Install the HANDLING SLING (RSE1133) on the core nozzle assembly (5).
(2) Lift the core nozzle assembly (5) to the flight attitude. R **ON A/C 001-049, 054-099, 101-149, 152-199, 211-299, 301-399, 401-499,
Subtask 78-11-11-420-050
B. Installation of the core nozzle assembly.
(1) Carefully move the core nozzle assembly forward over the centerbody.
(2) Align the core nozzle assembly (5) with the aft engine flange. Make sure that the cutouts in the nozzle flange are aligned with the cutouts in the engine flange.
(3) Apply anti-seize compound (Material No. CP5063) to the bolt (25) threads and the washers (30)
NOTE : Put the countersunk side of the washer against the head of the
____
bolt.
(4) Attach the core nozzle (5) to the engine flange with the bolts (25), washers (30), and nuts (10) (88 locations). Do not torque the nuts at this time.
(5) Install the turbine rear frame drain tube (20). (Ref. TASK 71-73-49-400-005)
(6) Adjust the core nozzle assembly (5) position so it is aligned for the best exhaust gas flowpath.
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(7) TORQUE the nuts (10) to between 50 and 70 lbf.in (0.56 and 0.79 m.daN).
NOTE : Start with the nuts at the 3 o'clock and 9 o'clock positions.
____ Then torque the nuts in sequence on opposite sides of the engine.
R **ON A/C 051-053, 151-151, 201-210,
Subtask 78-11-11-420-050-A
B. Installation of the core nozzle assembly.
(1) Carefully move the core nozzle assembly forward over the centerbody.
(2) Align the core nozzle assembly (5) with the aft engine flange. Make sure that the cutouts in the nozzle flange are aligned with the cutouts in the engine flange.
(3) Apply anti-seize compound (Material No. CP5063) to the bolt (25) threads and the washers (30)
NOTE : Put the countersunk side of the washer against the head of the
____
bolt.
(4) Attach the core nozzle (5) to the engine flange with the bolts (25), the supports (35), and the nuts (10). (18 locations) Do not torque the nuts at this time.
NOTE : The supports (35) are to be installed on the engine flange at
____ holes locations (2), (3), (5), (12), (13), (15), (24), (30), (36), (43), (49), (53), (61), (67), (74), (76), (77) and (87).
(5) Install the bracket (15) at the bottom of the engine flange (holes 44 and 45) with the bolts (25), washers (30), and nuts (10). Do not torque the nuts at this time.
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本文链接地址：A320飞机维护手册 AMM EXHAUST 1(16)
