REPAIR COMPRESSOR ROTOR BLADES - TM-55-2840-254-23-2

REPAIR COMPRESSOR ROTOR BLADES - TM-55-2840-254-23-2_422

INSTALL COMPRESSOR ROTOR BLADES - TM-55-2840-254-23-2_424

TM-55-2840-254-23-2 Engine Aircraft Gas Turbine Model T63-A-720 P/N6887191 Manual
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TM 55-2840-254-23 2-34 REPAIR COMPRESSOR ROTOR BLADES (Continued) 2-34 e. Inspect repaired areas of blades (8) as follows: (1) Use micrometer caliper. Measure blade wall thickness (9). Minimum blade wall thickness shall be 0.030 inch. (2) Inspect blade corners (10). Repaired areas within 0.120 inch of corners (10) shall be blended to a smooth radius. There shall be no sharp edges. (3) If damage to impeller assembly (6) ex- ceeds limits after repair, replace engine. INSPECT FOLLOW-ON MAINTENANCE: None END OF TASK 2-316

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