B. Concave surfaces of airfoil missing material,  25 cycles from cracking or burn-through, up to 0.75 in.
 (19.0 mm) diameter per vane
 C. Convex surfaces of airfoil missing material from  25 cycles cracking or burn-through, up to 0.75 in. (19.0 mm) diameter per vane
 D. Inner and outer platforms missing material, from  25 cycles cracking or burn-through, up to 0.5 in. (12.7 mm) diameter per segment
 E. Trailing edge missing material up to 0.75 in. (19 25 cycles if HPT
 mm)in axial direction  blades are within limits
 F. Baffle missing material, any amount.  10 cycles
 8. HPT rotor blade R (Ref. Fig. 609/TASK 72-00-00-991-320)
 A. Trailing edge cracks in Area A less than 0.2 in. 40 cycles
 (5.08 mm) long
 B. Convex airfoil cracks within 0.5 in. (12.7 mm) of  25 cycles trailing edge (10 blades maximum) in Area B less than 0.3 in. (7.62 mm) long
 C. Trailing edge cracks in Areas B and C less than 40 cycles
 0.30 in. (7.62 mm) long
 D. Radial tip cracks on the convex side not within 50 cycles
 0.5 in. (12.7 mm) of the trailing edge, less than
 0.35 in. (8.9 mm) long
 E. Radial tip cracks on the concave side not within 50 cycles
 0.5 in. (12.7 mm) of the trailing edge, less than

 1.0 in. (25.4 mm) long

 F. Leading edge cracks in Area A less than 0.1 in. 10 cycles
 (2.54 mm) long
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G. Axial nose or gill hole cracks in Areas B and C  10 cycles
 less than 0.05 in. (1.27 mm) long
 H. Radial nose or gill hole cracks in Area B less  10 cycles
 than 0.06 in. (1.52 mm) long
 J. Radial nose or gill hole cracks in Area C less  10 cycles
 than 0.03 in. (0.76 mm) long
 K. Missing material at trailing edge tip and Area A  50 cycles
 up to 0.5 in. x 0.75 in. (12.7 mm x 19 mm)
 L. Leading edge missing material in areas A and B.  25 cycles
 Any amount provided cavity 2 is not exposed (any
 number of blades)
 M. Airfoil distortion or evidence of burning or  25 cycles
 melting (10 blades maximum)
 N. Airfoil tip bent, curled, or missing material if  10 cycles
 the missing material below the tip shelf is less
 than 0.05 in. (1.27 mm) in diameter
 P. Airfoil convex and concave surface nicks or dents  25 cycles
 in Areas A, B and C if no cracks or missing
 material
 9. HPT shroud and stage 1 low pressure turbine (LPT)
 nozzle
 A. HPT shrouds
 (1) Circumferential cracks that connect and are  25 cycles
 more than 1 in. (25.3999 mm) long.
 (2) Circumferential cracks more than 0.25 in.  25 cycles
 (6.3499 mm) long that connect to axial cracks
 in Area B.
 (3) Burn through of shroud rub land  25 cycles
 B. Stage 1 LPT nozzle

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(1) Cracks in all areas up to 1.4 in. (35 mm)  10 cycles
 long provided not found on 2 adjacent airfoil
 segments
 (2) One crack permitted on each airfoil, from  100 cycles
 leading edge to trailing edge, if there is no
 missing material.
 (3) Burns, erosion, corrosion and missing metal  5 cycles
 up to 1 in.2 (645.16 mm2) per airfoil and no
 cracks extending from distressed area
 (4) Cracks in outer and inner platforms up to 1.0  100 cycles
 in. (25 mm) provided not found on 2 adjacent
 airfoil segments
 10. LPT Rotor
 A. LPT blades (all stages)
 (1) Blade pretwist
 - Total gap, for stage 1, up to 0.1 in. (2.54  5 cycles
　
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