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
F 『 EEFF : ALL E Page 68672-00-00
E E Aug 01/05 E E ECES E -------------------------------------------------------------------------------CONDITION MAX EXTENSION -------------------------------------------------------------------------------
F 『
E C F M E
E E
E 56-5B E
E E
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
F 『 EEFF : ALL E Page 68772-00-00
E E Aug 01/05 ERE
ECES E -------------------------------------------------------------------------------CONDITION MAX EXTENSION -------------------------------------------------------------------------------
F 『
E C F M E
E E
E 56-5B E
E E
(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
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：A320飞机维护手册 AMM ENGINE 发动机 1(60)
