(3)
Aft acoustical panels
(4)
Acoustical panels on the extension ring.
C. Access to the forward acoustical panels are through the fan inlet. Access to the mid acoustical panels is also through the fan inlet, but it is also necessary to remove some of the fan blades. To get access to the aft acoustical panels and the acoustical panels on the extension ring, you must open the applicable fan cowl panel and the thrust reverser.
D. There are two different forward acoustical panels; a hardwall design (engines with CFMI SB 72-766) and a perforated design (engines without CFMI SB 72-766). A mixed configuration of the forward panels is not in conformance with noise regulations.
E. To stay in the noise limits, the total perforated skin area that can be blocked from repairs to acoustical panels in the inlet cowl, fan frame, thrust reverser and fan duct shall not be more than 600 square inches for each engine. For the perforated fan frame forward, mid and aft acoustical panels, the total perforated area than can be blocked shall not be more than 5 square inches.
NOTE: For more information on these limits, refer to the Structural
____
Repair Manual SRM 54-10-01 and SRM 54-30-01.
F. Do the procedure in CMM 78-31-33 Repair 2-1 to modify the outer ring segment to replace the bonded acoustic panel with the compression molded acoustic panel. The bonded acoustic panel uses 8 holes and the compression molded acoustic panel uses 12 holes. The compression molded panel comes with only two pilot holes. Four new holes in the outer ring segment must be drilled to install the compression molded panel.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
72-33-02
ALL ú ú C02 Page 401 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
G. All screws and riveted self locking nuts that are locked with the sealant RTV (CP2242) must be replaced at the first shop opportunity.
TASK 72-33-02-004-001-C00
2. Forward Acoustical Panel Removal
________________________________
A. Equipment
(1) Protective Mats (two required) - Rubber
Manufacturer's Association, Grade SC43,
neoprene sponge, 1 inch thick, approximately 3
x 4 feet with warning streamers attached.
B. Access
(1) Location Zones
501/601 Inlet and Cowl
506/606 Engine
C. Remove the Forward Acoustical Panel
S 864-002-C00
(1) Make sure the start levers are in the CUTOFF position.
(a) Install the DO-NOT-OPERATE tags.
S 844-003-C00
CAUTION: MAKE SURE THE EDGES OF THE MATS ARE TIED TOGETHER OR TAPED, TO
_______ PREVENT DAMAGE TO THE INLET COWL. TOOLS, PARTS, OR UNWANTED MATERIALS CAN FALL ON THE INLET COWL AND CAN CAUSE DAMAGE.
(2) Install the protective mats in the inlet.
(a) Make sure you give protection to the bottom half of the inlet cowl.
S 024-004-C00
(3) Remove the forward acoustical panel as follows (Fig. 401):
CAUTION: IF YOU USE A PNEUMATIC OR ELECTRICAL SCREWDRIVER TO LOOSEN
_______ AND REMOVE THE ACOUSTICAL PANEL SCREWS, MAKE SURE THE SPEED IS NOT MORE THAN 200 RPM. IF THE SPEED IS MORE THAN 200 RPM, DAMAGE TO THE EQUIPMENT CAN OCCUR.
(a)
Remove the eight screws that attach the acoustical panel to the fan case.
(b)
If you find a screw which has no torque feel when it is removed, discard and replace it with a new screw.
(c)
Lift the larger end of the panel out from the fan case while you slide the smaller end out from under the adjacent panel.
S 034-005-C00
(4) If it is necessary, remove the snap-fit fillet skin from the panel and keep the skin for the installation.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
72-33-02
ALL ú ú C02 Page 402 ú Nov 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737-300 400 500 AMM 飞机维护手册 ENGINE 发动机 2(46)
