72-33-00
 ALL  ú ú C02 Page 613 ú Nov 15/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
ACOUSTICAL PANELS INSPECTION
____________________________
 3)  On the forward, middle, and aft panels, defects such as tears, cracks, and punctures that are up to 1.0 sq. in. (6,5 sq. cm) and that go through the panel skin are permitted for 60 cycles/100 flight hours: a) Remove the loose material with a sharp blade. b) If the defect is larger than 1.0 sq. in. (6,5 sq. cm),
 replace the panel (AMM 72-33-02/401).
 E.  Make an Inspection of the Fan Aft Extension Ring Acoustical Panels
 S 846-010-C00
 (1)  
If not already done, do the procedure to prepare for the inspection.

 S 216-009-C00

 (2)  
ENGINES WITH THE BONDED ACOUSTICAL PANELS;
 Examine the acoustical panels for damage as follows:

 NOTE: Refer to the CMM 78-31-33 for the repair of
____
 damage on these acoustical panels.

 (a)  
Cracks 1) All cracks except edge cracks are not permitted. 2) All edge cracks are permitted if you repair them.

 (b)  
Nicks, Gouges, Scratches and Corrosion

 1)  All damage that does not go through the clad surfaces are permitted if it is repaired.

 (c)  
Dents

 1)  All dents are permitted if these limits are obeyed: a) The depth of the dent is 0.05 inch (1.3 mm) or less. b) The maximum diameter of the dent is 3.0 inch (80 mm) or
 less.
 c)  There are no dents larger than 1/32 inch (0.8 mm) deep for each 1.0 inch inch (25.4 mm) of average dent diameter.
 d)  All dents must be smooth and without sharp creases, gouges, or cracks. e) You do not see an indication of pulled or loose fasteners.
 (d)  Holes or Punctures 1) This damage is permitted if these limits are obeyed: a) The damage is not more than 0.25 inch (6.4 mm) in diameter.
 b)  The separation is not less than 1.0 inch (25.4 mm) from other damage, the nearest hole (other than perforations) or the material edge.
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 72-33-00
 ALL  ú ú C02 Page 614 ú Nov 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
ACOUSTICAL PANELS INSPECTION
____________________________
 c)  Not more than one hole for every 15.0 square inches
 (96.8 square cm) of the panel.
 NOTE: Keep all foreign materials, water and sunlight
____ away from the hole. To do this, seal the damage with aluminum foil tape (speed tape) 3M-Y436 or equivalent. Repair the damage at the next "C" check.
 (e)  Delamination
 1)  Dalamination of the panel is permitted if these limits are obeyed: a) The delamination is not more than 2.0 inch (50 mm) for
 every 1.0 square foot (0.93 square meters). b) The damage is a minimum of 1.0 inch (25.4 mm) from other damage, fastener or part edge. c) The delamination from the edge is not more than 0.10 inch (2.5 mm).
 NOTE: Keep all foreign materials, water and sunlight
____ away from the delamination. To do this, seal the damage with aluminum foil tape (speed tape) 3M-Y436 or equivalent. Repair the damage at the next "C" check.
 S 216-011-C00
 (3)  
ENGINES WITH THE COMPRESSION MOLDED ACOUSTICAL PANELS; Examine the acoustical panels for damage as follows:

 (a)  
Edge chips that are not more than 0.03 inch (0.76 mm) in depth and 0.10 inch (2.54 mm) in length are permitted.

 (b)  
Fiber break out around drilled and countersunk holes are permitted if they are less than 0.03 inch (0.76 mm) in depth and 0.10 inch (2.54 mm) in length.

 (c)  
Acoustical panels that are loose in all directions must be replaced before 100 flight hours.

 (d)  
If the damage is more than the above limits, replace the acoustical panel (AMM 72-33-02/401).
　
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