(c) If the stage 7 borescope hole (S8) is not fully open, inspect the aft part of the compressor through the stage 8 borescope hole (S9). If the stage 8 borescope hole (S9) is not fully open, try to do the inspection through the stage 6 borescope port (S7).
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Subtask 72-31-00-290-051
B. Inspect the blades to the limits that follow:
(Ref. Fig. 608/TASK 72-31-00-991-310)
NOTE : If you find airfoil damage, we recommend that you do a borescope
____ inspection of the stage 5 booster blades and the abradable (Refer to CFM SB 72-03910).
NOTE : The depth of a defect such as a nick is measured along the axis of
____
the damage unless otherwise noted.
R NOTE : Unless otherwise identified, all damage limits for high pressure
____ R compressor blades are the same for the different blade R configurations.
-------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS -------------------------------------------------------------------------------
1. Stages 1-4 compressor
blades:
A. Cracks Any number of radial See limit extensions cracks within 0.30 in. (Ref. TASK 72-00-00-200-
(7.6 mm) of the leading 025) or repair (Ref. TASK or trailing edge, up to 72-31-00-300-004).
0.25 in. (6.4 mm) in length are serviceable
Any number of radial cracks more than 0.30 in. (7.6 mm) from the leading or trailing edge, up to 0.10 in.
(2.5 mm) in length are serviceable
Any number of chord-wise See limit extensions cracks, up to 0.30 in. (Ref. TASK 72-00-00-200-
(7.6 mm) from the tip, 025) or repair (Ref. TASK up to 0.2 in. (5.1 mm) 72-31-00-300-004). in length are serviceable
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-------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS -------------------------------------------------------------------------------
B. Missing or chipped erosion coating
C. Tears on the leading and trailing edge found in Dim. B (upper 75% of the airfoil)
D. Nicks, missing material and erosion on the leading and trailing edge found in Dim. B (upper 75% of the airfoil)
E. Dents on the leading or trailing edge found in Dim. B (upper 75% of the airfoil)
F. Nicks and tears on the leading and trailing edge tip corners in Dim. A
G. Dents on the leading and trailing edge tip corners in Dim. A
H. Missing material and erosion at the leading and trailing edge tip corners
Any amountNot serviceable
Any number if the damage is less than 0.04 in.
(1.0 mm)
Any amount if the damage is less than 0.04 in.
(1.0 mm) in depth or up to 0.06 in. (1.5 mm) deflection from theoriginal contour
Any number if less than
0.25 in. (6.4 mm) in depth
Any number if less than
0.04 in. (1.0 mm) in depth or 0.06 in. (1.5 mm) deflection from the original contour
Any number for each stage up to 0.30 x 0.30 in.(7.6 x 7.6 mm) if downstream damage isserviceableSee repair (Ref. TASK 72-31-00-300-004).
See limit extensions(Ref. TASK 72-00-00-200-025) or repair (Ref. TASK72-31-00-300-004).
See limit extensions(Ref. TASK 72-00-00-200-025) or repair (Ref. TASK72-31-00-300-004).
See limit extensions(Ref. TASK 72-00-00-200-025).
See limit extensions(Ref. TASK 72-00-00-200-025) or repair (Ref. TASK72-31-00-300-004).
See limit extensions(Ref. TASK 72-00-00-200-025).
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R J. Curl on the end of Up to 25% of chord,
R the airfoil maximum radial length of
R 0.30 in. (7.6 mm) when
R it does not engage the
R stationary parts during
R operation
R K. Nicks, dents and Any amount if less than
R scratches on the 0.003 in. (0.10 mm) in
R airfoil root depth. Scratches
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