(a)
The forward, mid, and aft acoustical panels on the engine fan case.
(b)
The acoustic panels on the fan aft extension ring.
(2)
Make an inspection of the forward and mid-acoustical panels through the inlet.
(3)
Make an inspection of the aft and extension ring acoustical panels through the fan aft extension ring.
B. References
(1) AMM 72-33-02/401, Acoustical Panels
C. Access
(1) Location Zones
506 No. 1 Engine
606 No. 2 Engine
D. Make an Inspection of the Forward, Middle and Aft Acoustical Panels (Fig. 601)
S 846-020-C00
(1)
If not already done, do the procedure to prepare for the inspection.
S 216-021-C00
(2)
Examine the acoustical panels for damage as follows:
NOTE: Refer to the CFMI Engine Shop Manual (ESM) 72-23-08 for
____ the repair of damage on these acoustical panels.
For the forward acoustic panels, there are two types: perforated (equivalent to the mid and aft acoustic panels), and hardwall. The hardwall acoustical panels are installed on engines with CFMI SB 72-766. The inspection limits for these hardwall acoustical panels are the same as the perforated acoustic panels.
(a) Two missing panels:
1) Permitted if there is a minimum of one serviceable panel between these two missing panels.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
72-33-00
ALL ú ú C01 Page 612 ú Nov 15/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
ACOUSTICAL PANELS INSPECTION
____________________________
2) A maximum service extension of 100 flight hours is
permitted for this condition.
(b)
Loose panels that can move in all directions:
1) A maximum service extension of 100 flight hours is
permitted for this condition.
(c)
Loose bolts: 1) Tighten the bolts.
(d)
Distortion of the panels: 1) This damage is permitted.
(e)
Subsurface linear impressions or wrinkles: 1) This damage is permitted.
(f)
Voids in the panels:
1) Up to 5 are permitted, if they are separated by a minimum of 2.0 inch (50.8 mm), have a maximum diameter of 0.12 inch
(3.0 mm) or less, and have a maximum depth of 0.012 inch
(0.3 mm) or less.
(g)
Defects in the protective coating (original Tedlar film or paint) such as: 1) Missing coating, cracks, dents, nicks, tears, or flaking:
a) Remove the loose material with a sharp blade.
(h)
Defects in the panel skin:
1) On the forward and aft accoustical panels only, defects such as dents, nicks, tears, and impact marks that are up to 5.0 sq. in. (32 sq. cm) and that do not go through the panel skin are permitted: a) Remove the loose material with a sharp blade. b) Examine the panel for delamination every 60 cycles /100
flight hours.
c) If the defect is more than 5.0 sq. in. (32 sq. cm) and/or delamination is observed, replace the panel (AMM 72-33-02/401).
2) On the middle accoustical panels only, defects such as
dents, nicks, tears, and impact marks that do not go
through the panel skin are permitted, without a limit on
the surface area of the defect:
a) Examine the panel for an extension of the defect
through the panel skin every 60 cycles/100 flight hours.
NOTE: Defects on the middle panels that are up to
5.0 sq. in. (32 sq. cm) and that do not go through the panel skin are repairable. Refer to the procedure in the CFMI Engine Shop Manual (ESM), 72-23-08. Middle panels with defects that are larger than 5.0 sq. in. (32 sq. cm) are not repairable. It is the customer's option whether to leave these panels in place or to replace them.
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 ENGINE 發動機 2(22)
