BLADE
CONFORM TO ORIGINAL AFTER BLENDING MUST NOT
CONTOUR AS SHOWN BE LESS THAN ORIGINAL
DOTTED LINES INDICATE THICKNESS
ORIGINAL CONTOUR OF BLADE
S-M56-MM-1120-(1)-00-C
Leading and Trailing Edge Blending
Figure 802
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72-31-02
ALL ú ú C02.1 Page 804 ú Jul 12/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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(c)
If the repair is more than the engraved red line on the template, replace the blade (AMM 72-31-02/401).
(d)
Repairs to the leading edge are permitted if they are on the line or forward of the line.
S 328-005-C00
(4) Do a blending repair of the damage with a soft file or a silicone carbide abrasive stone, grade C150L8V, used dry.
NOTE: For major blending repairs, use strips of silicone carbide
____ abrasive cloth, grade 150J for prefinishing or grade 180J for blend finishing.
(a)
Do the blending repair in a longitudinal direction parallel with the length of the blades.
(b)
The leading and trailing edge radius of the area you repaired must agree with the initial contour (Fig. 802).
(c)
When blending an area that includes a radius keep the radius as near as possible to initial radius.
(d)
The finish on a blended area must be as near as possible to the initial finish.
(e)
Remove the material to a minimum of 0.03 inch (0.76 mm) below the damage. 1) Do a fluorescent-penetrant inspection to make sure the
damage is fully removed (AMM 70-40-01/201).
S 208-009-C00
(5) Do the procedure to put the airplane back to its usual condition.
NOTE: The fan rotor balance could be affected if the moment-weight
____ of a blade has changed more than 50 gram-inches (127 gram-cm). When a significant amount of base material has been removed during the fan blade blend repair or if the engine imbalance was close to the limits, make sure the engine imbalance is not more than the limits. A vibration survey (AMM 71-00-00/501, Test No. 7) can be performed at the operator's discretion. The results from the vibration survey will determine if a dynamic fan trim balance is necessary or if the installation is correct (AMM 72-31-00/501).
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ú ALL ú
ú ú ú C01.101 ú BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details. Page 805Jul 12/02
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
BOOSTER BLADES AND VANES - REMOVAL/INSTALLATION
_______________________________________________
1. General
_______
A. This procedure gives the steps for the removal and installation of the lst-stage booster vane assembly (referred to as vane assembly).
B. You can get access to the The vane assembly through the inlet cowl after the removal of the spinner, all fan blades, and the splitter fairing.
TASK 72-31-03-004-001-C00
2. Remove 1st-Stage Booster Vane Assembly
______________________________________
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