(a) Put a warning notice to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a warning notice to tell persons not to energize the FADEC 1(2).
Subtask 72-41-00-010-055
B. Get Access
(1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040)
FOR 1000EM1
437AL, 438AR
FOR 1000EM2
447AL, 448AR
F 『 EEFF : ALL E Page 80272-41-00
E E Feb 01/98 E E ECES E
F 『
E C F M E
E E
E 56-5B E
E E
(2) Put the access platform in position.
Subtask 72-41-00-040-053
C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041).
Subtask 72-41-00-010-057
D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040)
FOR 1000EM1
451AL, 452AR
FOR 1000EM2
461AL, 462AR
4. Procedure
_________
Subtask 72-41-00-350-051
A. Blend the part
CAUTION : DO NOT PERMIT THE REMOVED MATERIAL, TOOLS, OR CONSUMABLES TO
_______ FALL INTO THE COMBUSTION CASE. ENGINE DAMAGE CAN OCCUR.
(1) Blend the part with a fine file, durite G422 (Material No. CP2189) or durite G421 (Material No. CP2191) or abrasive stone. Remove as small an amount of the parent metal as possible.
Subtask 72-41-00-230-053
B. Do a fluorescent penetrant inspection of all the blend areas. No cracks are permitted. (Ref. TASK 70-51-00-230-002)
5. Close-up
________
Subtask 72-41-00-410-055
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
F 『 EEFF : ALL E Page 80372-41-00
E E Feb 01/98 E E ECES E Subtask 72-41-00-440-053
F 『
E C F M E
E E
E 56-5B E
E E
B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-41-00-410-057
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 access platform(s).
(3) Remove the warning notice(s).
F 『 EEFF : ALL E Page 80472-41-00
E E Feb 01/98 E E ECES E
F 『
E C F M E
E E
E 56-5B E
E E
COMBUSTION CHAMBER ASSEMBLY - DESCRIPTION AND OPERATION
_______________________________________________________
1. General
_______ R R (Ref. Fig. 001, 002) R The combustion case contains the combustion chamber, which is a short, R annular structure. The combustion chamber consists of outer and inner cowls, R 20 primary swirl nozzles, dome, and outer and inner liners. The liners and R cowls are bolted to the dome. R The function of the combustion chamber is to supply a uniform combustion R pattern for low thermal stress. R The staged burning valve, controlled by FADEC, adapts the function of the R combustion chamber to the engine requirements by the use of either 10 or 20 R open fuel nozzles.
2. Description
___________ R R (Ref. Fig. 001, 002)
R A. Dome R The dome consists of both cast and machined components. Twenty primary R swirl nozzles and 20 secondary swirl nozzles with venturies and sleeves R are used to provide mixing of air and fuel. The entire surface of the R dome is cooled by a film of cooling air.
B. Cowl The inner and outer cowls are designed to provide uniform and stable airflow profiles to the combustion chamber.
C. Liners The outer and inner liners are of an integral design with panel overhangs which contain closely spaced cooling holes that provide film cooling. Dilution holes are employed in the liners to provide additional mixing and cooling air which lowers the gas temperature at the turbine inlet. The outer liner contains 2 ferrules for the spark igniters.
F 『 EEFF : ALL E Page 172-42-00
E E Aug 01/04 E E ECES E F 『 E C F M E E E E 56-5B E
Combustion Chamber
Figure 001
F 『 EEFF : ALL E Page 272-42-00
E E Feb 01/98 E E ECES E F 『 E C F M E E E E 56-5B E
Combustion Chamber Section
Figure 002
F 『 EEFF : ALL E Page 372-42-00 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(41)
