-------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS -------------------------------------------------------------------------------
C. Radial cracks Any amount.
(convex or
concave) within
0.50 in. (12.7 mm)
of trailing edge.
D. Bent, curled or Any amount above tip
missing material. shelf.
E. Missing thermal Any amount.
barrier coating.
3. Concave and convex
surfaces for:
A. Nicks or dents, Any number 0.25 in.
area A. (6.35 mm) long.
B. Nicks or dents, Any number, 0.1 in.
area B. (2.54 mm) long.
C. Nicks or dents, 3 permitted, 0.05 in.
area C. (1.27 mm) long. Nicks
and dents must be
separated by 0.125 in.
(3.17 mm) minimum.
D. Cracks,other Not serviceable.
areas.
E. Missing thermal Any amount.
barrier coating.
4. Blade airfoil for:
A. Distortions or Not serviceable.
evidence of
burning or
melting.
B. Missing thermal Any amount.
barrier coating.
See limit extensions(Ref. TASK 72-00-00-200-025).
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(11) When the inspection is completed, turn off the BORESCOPE - LIGHT SOURCE SET (856A1322 P03, P04 or P07) and remove the FIBERSCOPE SET (856A1321 P01 or P03) and guide tube.
(12) Install the spark igniter (Ref. TASK 74-21-30-400-002).
(13) Tools used to rotate the core as follows:
(14) Remove the tools used to rotate the core as follows:
NOTE : If the breaker bar is installed see steps (a) and (b). If the
____ drive motor is installed see steps (c) and (d).
(a) Remove the 0.75 in. (19.05 mm) square drive socket and 2 ft. (0.6 mm) breaker bar from the core rotation drive pad.
(b) Install the handcranking drive pad cover (Ref. TASK 72-63-00-400-002).
(c) Remove the drive motor from the starter pad of the AGB.
(d) Install the starter (Ref. TASK 80-11-10-400-002).
5. Close-up
________
Subtask 72-52-00-410-058
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 72-52-00-440-054
B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
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C. Close Access
(1) Close the fan cowls (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR.
(2) Remove the access platform(s).
(3) Remove the warning notice(s).
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E E May 01/05 E E ECES E HPT SHROUD AND STAGE 1 LPT NOZZLE ASSEMBLY - DESCRIPTION AND OPERATION
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1. General
_______
(Ref. Fig. 001)
A. HPT shroud and stage 1 LPT nozzle assembly
(1) The high pressure turbine (HPT) shroud and stage 1 low pressure turbine (LPT) nozzle assembly is located inside the aft end of the combustion case. It forms the interface between the core section and the LPT module of the engine. The forward flange of the assembly is rabbeted and bolted to the inner surfaces of the combustion case. The aft flange is bolted between the combustion case aft flange and the LPT stator forward flange.
(2) The shroud/nozzle support has a thermal response matched to the rotor to provide good tip clearance control and structural stability. An air cavity between the shroud/nozzle support and the combustion case directs mixed 5th and 9th stage compressor bleed air onto the support and the outer, or backside, of the shrouds. This cooling air maintains closer clearances between the shrouds and the rotor blades.
(3) The stage 1 LPT nozzles direct the core engine exhaust gas onto the stage one LPT blades. An air cavity between the stage one nozzle support and the combustion case directs 5th stage compressor bleed air through the nozzle vanes for cooling. After passing through the vanes, the air pressurizes and cools the cavity between the aft side of the HPT rotor and the forward side of the LPT rotor. 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(72)
