A320飞机维护手册 AMM ENGINE 发动机 1(144)

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 0.5 in. (12.7 mm) along the trailing edge, with maximum deflection from
 original contour dimension Y = 0.25 in.
 (6.35 mm) . A maximum of 5 blades
 can have tip curl up to dimension Z1 = 1 in.
 (25.4 mm) across the blade tip and up to dimension Z = 1 in.
 (25.4 mm) along the trailing edge with maximum deflection from
 original contour dimension Y = 0.3 in.
 (7.62 mm) . No more than 3 blades to
 these increased limits
 can be adjacent.
 (3) Nicks and dents  No limited quantity if not deeper than 0.04 in. (1.02 mm) and no longer than 0.25 in. (6.35 mm)  Do blending procedure(Ref. TASK 72-21-00-320-003)Do a spot fluorescent-penetrant inspection (Ref. TASK 70-51-00-230-002)
 J. Nicks, dents and scratches on surface of blade platform  For scratches: no limited quantity,if not deeper than 0.02 in. (0.5 mm) and not longer Do blending procedure(Ref. TASK 72-21-00-320-003)

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(excluding fillet  than 0.40 in. (10.16
 and recess area)  mm).
 For nicks and dents, no
 limit on diameter after
 removal of high metal,
 K. Pits  No limited quantity if  Replace pair of blades
 not deeper than 0.005  (Ref. TASK 72-21-00-300-
in. (0.13 mm). No limits  002)
 as regards diameter or
 spacing,
 L. Nicks, dents and  No limited quantity if  Do blending procedure
 scratches on  not deeper than 0.010  (Ref. TASK 72-21-00-320-
midspan shroud  in. (0.25 mm). No  003)
 (Area C)  limited length for
 scratches, and 0.5 in.
 (12.7 mm) diameter for
 dents. None permitted in
 midspan shroud to
 airfoil fillet radius.
 M. Wear due to  Any amount 0.005 in.  Replace pair of blades
 shingling on  (0.13 mm) deep  (Ref. TASK 72-21-00-300-
midspan shroud  002)
 (Area C)
 N. High metal caused  Any amount after
 by shingling on  smoothing of high metal
 midspan shroud
 (Area C)
 5. Abradable for:
 (Ref. Fig. 601/TASK
 72-23-00-991-308)
 A. Cracks  Any amount
 B. Rubs  Any amount
 C. Crater (length<5x  Cumulated damage more  For defect above those
 width) and damage  than 160 in.2 (1032,25  limits :

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other than crack cm2) with no one area local reconditioning :
 rub and  larger than 30 in.2 (Ref. TASK 72-23-00-300-
circumferential (193,54 cm2) and : 040)
 defect a) The maximum axial circular patch : R width (parallel to (Ref. TASK 72-23-00-300-R engine axis) is less 043)
 than 2.5 in. (63.5 mm) refer to limits :
 b) The minimum distance (Ref. TASK 72-00-00-200-
between the areas is 005)
 equal to the maximum
 dimension of the nearest
 damaged area.
 c) The fan case parent
 metal does not show
 through.

 D. Grooves  All damage is permitted For defect above those (orientated within if : limits : 0 deg. and 80 deg. a) The maximum width of local reconditioning : from engine axis one groove is not more (Ref. TASK 72-23-00-300-and length>5x than 0.32 in. (8.12 mm). 040) width) b) A maximum of total refer to limits :
 width of 1.25 in. (31.75 (Ref. TASK 72-00-00-200-mm) of groove is with a 005) minimum separation of
 0.1 in. (2.54 mm). c) The fan case parent metal does not show through.

 E. Circumferential  All damage is permitted For defect above those defect (360 deg. if : limits : or orientated a) The maximum axial local reconditioning : within 80 deg. to width (parallel to (Ref. TASK 72-23-00-300-90 deg. from engine axis) of one or 040) engine axis cumulated defect is less refer to limits :
　
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