(4) Install the headed pin in the connecting link and actuation ring segment.
(5) Apply Graphite grease (Material No. CP2101) to the threads and friction surface of the bolts.
(6) Install the bolts. TORQUE the bolts to between 55 and 70 lbf.in (0.62 and 0.79 m.daN).
(7) Make sure that the straight pin is correctly installed in the actuation ring. Use lockwire through the inspection hole of the connecting link to feel for the pin.
F 『 EEFF : ALL E Page 81672-32-00
E E Feb 01/98 E E ECES E
F 『
E C F M E
E E
E 56-5B E
E E
(8) Do a visual check:
CAUTION : BLADE DAMAGE CAN OCCUR IF THE LEVER ARMS ARE NOT CORRECTLY
_______
ENGAGED.
(a) Make sure all of the lever arms are correctly engaged in the connecting link bushings.
(9) Wirelock the bolts:
CAUTION : MAKE SURE THE D-HEAD BOLT IS SEATED IN THE RECESS OF THE
_______
CONNECTING LINK.
(a) Use the Lockwire 0.032 in. (0.8 mm) dia (Material No. CP8001).
(10) Apply Graphite grease (Material No. CP2101) to the threads of the D-head bolt.
(11) Install the tie rod in the connecting link with the D-head bolt and nut. The bolt head goes aft for IVG and forward for stages 1, 2, and
3.
(12) Install the nut and TORQUE to between 105 and 115 lbf.in (1.18 and
1.29 m.daN).
NOTE : Do not adjust the tie rod.
____
5. Close-up
________
Subtask 72-32-00-410-060
A. Close Access
(1) Make sure that the work area is clean and clear of tool(s) and other items.
(2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040) FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
Subtask 72-32-00-440-055
B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
F 『 EEFF : ALL E Page 81772-32-00
E E Feb 01/98 E E ECES E Subtask 72-32-00-410-061
F 『
E C F M E
E E
E 56-5B E
E E
C. Close Access
(1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR.
(2) Remove the warning notice(s).
(3) Remove the access platform(s).
F 『 EEFF : ALL E Page 81872-32-00
E E Feb 01/98 E E ECES E HPC REAR STATOR ASSEMBLY - DESCRIPTION AND OPERATION
F 『
E C F M E
E E
E 56-5B E
E E
____________________________________________________
1. General
_______ (Ref. Fig. 001) The compressor rear stator consists of the rear casing halves, 3 stages of fixed vanes, and interstage honeycomb seals. The halves are attached together at the 3 and 9 o'clock splitline with bolts. The rear stator assembly is found inside the front stator assembly and is cantilever mounted to the rear stator support. The outer flange of the rear stator support is installed between the front stator of the compressor and the combustion case. The rear flange has rabbets for close tolerance concentricity with the combustion case. The forward end is radially restrained by manifold supports attached to the front case to maintain concentricity.
2. Description
___________
A. Casing The rear casing halves are a matched set machined from an incoloy forging. The casings have internally machined circumferential slots that retain stages 6, 7, and 8 stator vane segments. Stage 6, 7, 8, and 9 rub lands are hard-coated. The casing contains ports for borescope inspection of internal area.
B. Vanes The vanes in stages 6,7, and 8 are made into segments consisting of several vanes each. These segments are installed in circumferential slots in the casing. Each stage of vanes has shrouds with removable honeycomb seal segments attached to the inner platforms.
F 『 EEFF : ALL E Page 172-33-00
E E Feb 01/98 E E ECES E F 『 E C F M E E E E 56-5B E
Compressor Rear Stator Assembly
Figure 001
F 『 EEFF : ALL E Page 272-33-00
E E Feb 01/98 E E ECES E
F 『
E C F M E
E E
E 56-5B E
E E
COMBUSTION SECTION - DESCRIPTION AND OPERATION
______________________________________________
1. General
_______ (Ref. Fig. 001) The combustion of fuel takes place in the combustor installed in the compressor rear frame. The controlled release of energy of combustion through the turbine nozzles drive the engine rotors. (HP rotor for self sustaining operation and the LP rotor to develop airflow through the fan exhaust nozzle and to provide gases to the core engine exhaust nozzle for additional thrust).
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(37)
