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provided there is no missing material or cracks exceeding 50 percent of chord width
(4) Stage 4 blades
- Any amount of tip shroud interlock wear allowed
- Blade tip shroud protrusion not to exceed
0.04 in. (1.01 mm)
- Area E:
Any amount of impact damage such as nicks and/or dents is allowed provided there is no missing material or cracks
- Other areas:
Any amount of impact damage. One complete airfoil and any number of tip shrouds with associated airfoil tips may be missing provided engine vibration is not excessive
- Blade tip shrouds shingled or unlatched provided rotor turns freely and engine vibration is not excessive
B. Nozzle segments
(1) Cracks in the leading and trailing edges for stages 2 through 4.
- One crack maximum not more than 1 in. (25.4mm) with no crack on the opposite side of the same airfoil.
- If there are three additional airfoils with cracks, any number not more than 0.5 in. (12.7mm) on the same segment with no crack on the opposite side or if there is a crack on the opposite side, cumulative length must be less than 0.5 in. (12.7mm).
25 cycles or 50hours
10 cycles or 25hours
5 cycles or 10hours
5 cycles or 10hours
5 cycles or 10hours in shingledcondition.
50 cycles
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(2) Nicks, dents, tears, missing pieces up to 2 10 cycles in.2 (1290.32 mm2) on nonadjacent vanes provided there are no cracks extending from distressed areas
C. Stage 4 shroud abradable material
(1) Worn, jagged or crushed sealing surface 10 cycles exceeding 50 percent of the honeycomb height provided sectors of the shroud abradable material are not missing
11. LPT Casing
A. Forward and aft flanges
(1) One crack connecting 2 bolt holes without 10 cycles penetrating pressure vessel outer skin
(2) One crack into skin 0.4 in. (10.16 mm) long 10 cycles maximum
B. External surface of the casing
(1) One crack 0.4 in. (10.16 mm) long maximum 10 cycles
C. Cooling air tube and manifold assemblies 10 cycles
(1) One separated circumferential tube
(2) 3 in. (76.2 mm) cumulative cooling air
manifold crack
(3) One separated cooling air tube support
D. Thread ports and bosses
(1) One crack 0.5 in. (12.7 mm) maximum providing 10 cycles there is no leakage
12. Turbine frame
A. Forward and aft flanges 10 cycles
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(1) One circumferential crack connecting two bolt
holes
(2) One crack into skin 0.5 in. (12.7 mm) maximum
B. Engine mounting lug areas airframe attach points 10 cycles
only
(1) One crack out of one mount lug bolt hole 0.25
in. (6.35 mm) maximum
