(4)
Borescope Fiber Light Cable
B. References
(1)
AMM 71-00-00/501, Power Plant
(2)
AMM 72-00-00/601, HPC Blades (1st- thru 9th-Stages)
C. Access
(1) Location Zones
506 No. 1 Engine
606 No. 2 Engine
D. Blending Limits (Fig. 801)
S 228-016-C00
(1) Tears, nicks, dents, missing material and erosion on the leading and trailing edge of stages 1-4 compressor blade found in the upper 75% of the airfoil.
NOTE: Multiple blends in the same area are acceptable as long as
____ the cumulative material removed from the original contour does not exceed the repairable limit.
(a)
No maximum number of tears. 1) Maximum depth is 0.060 in. (1,52 mm).
(b)
No maximum number of nicks, missing material and erosion. 1) Maximum depth is 0.060 in. (1,52 mm).
(c)
No maximum number of dents. 1) Maximum depth is 0.060 in. (1,52 mm).
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S 228-017-C00
(2) Tears, nicks, dents, missing material and erosion on the leading and trailing edge of stages 5-9 compressor blade found in Dimension B.
NOTE: Multiple blends in the same area are acceptable as long as
____ the cumulative material removed from the original contour does not exceed the repairable limit.
(a) No maximum number of tears, nicks, missing material and erosion. 1) Maximum depth is 0.060 in. (1,52 mm). 2) No maximum number of dents. 3) Maximum depth is 0.060 in. (1,52 mm).
S 228-018-C00
(3) Tears, nicks, dents, missing material and erosion on the leading and trailing edge of stages 5-9 compressor blade found in Area A.
NOTE: Multiple blends in the same area are acceptable as long as
____ the cumulative material removed from the original contour does not exceed the repairable limit.
(a)
No maximum number of tears, nicks, missing material and erosion. 1) Maximum depth is 0.080 in. (2,03 mm).
(b)
No maximum number of dents. 1) Maximum depth is 0.080 in. (2,03 mm). 2) Maximum deflection from original contour 0.080 inch
(2,03 mm).
E. Blending of HPC Rotor Blades
S 228-009-C00
CAUTION: DO NOT INSTALL OR REMOVE THE TOOL TIP FROM THE DRIVE SHAFT HEAD
_______ WITH THE DRIVE SHAFT HEAD IN THE 0-DEGREE POSITION. IF YOU REMOVE THE TOOL TIP WITH THE DRIVE SHAFT HEAD IN THE 0-DEGREE POSITION, THE DRIVE BELT WILL DISENGAGE.
(1) Measure the damaged area (Fig. 802, 804) as follows:
(a) Position the drive shaft head (2) to the 90-degree position. Install the measureing grid tip (5) (Fig. 804) onto the drive shaft head (2) (Fig. 802, Sheet 2) and tighten the lockscrew. This will prevent damage to the rotor blades or the blend tool.
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0.30 0.10
(7.62) (2.54)
AIRFOIL ROOT RADIUS AREA
HPC ROTOR BLADE
TRANSVERSE AXIS
NOTE: ALL DIMENSIONS ARE IN INCHES WITHGMM-1095620-04-A
MILLIMETERS IN PARENTHESES.
High Pressure Compressor Rotor Borescope Inspection
Figure 801 (Sheet 1)
G36080
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