A320飞机维护手册 AMM ENGINE 发动机 1(53)

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 LPT blades distorted leading edges, due to
 overtemperature
 (3) Stage 1, 2, 3 blades
 - Area E:  5 cycles or 10
 Any amount of impact damage/rubbing  hours
 provided there is no missing material or
 cracks
 - Other areas:  5 cycles or 10
 Any amount of impact damage such as  hours
 bending, nicks and/or dents is allowed
 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  25 cycles or 50
 allowed  hours
 - Blades tip shroud protrusion not to exceed  10 cycles or 25
 0.04 in. (1.01 mm)  hours
 - Area E:
 Any amount of impact damage such as nicks  5 cycles or 10
 and/or dents is allowed provided there is no  hours
 missing material or cracks

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- Other areas:
 Any amount of impact damage. One complete  5 cycles or 10
 airfoil and any number of tip shrouds with  hours
 associated airfoil tips may be missing
 provided engine vibration is not excessive
 - Blades tip shrouds shingled or unlatched  5 cycles or 10
 provided rotor turns freely and engine  hours in shingled
 vibration is not excessive  condition.
 B. Nozzle segments
 (1) Cracks 0.8 in. (20 mm) long each, 2 per vane,  10 cycles
 total length of 1.6 in. (40 mm)
 (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
 12. 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

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(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
 13. Turbine frame
 A. Forward and aft flanges  10 cycles
 (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

 (2) Skin crack 0.25 in. (6.35 mm) maximum.

 C. Threaded parts and bosses  10 cycles
 (1) One crack 0.5 in. (12.7 mm) long providing
 there is no fluid or air leakage

 D. Stud on the aft face of the inner hub.
 (1) Missing/broken/loose stud(s):
 - One (1) or two (2) studs:  500hrs/500cyc

 - Three (3) studs:
 *If not adjacent to each other: 500hrs/500cyc

 

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