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1. The axial length is less than 0.256 inch (6.5 mm)
_ and the radial length is less than 0.728 inch
(18.5 mm).
2. The damage is not in Areas A and B.
_
b) A maximum service extention of 50 cycles/75 hours is permitted if no cracks start from the damaged area and go into Areas A and B.
2) Look for cracks or tears.
a) No maximum number in Areas A and B if the damage is less than 0.128 inch (3.25 mm) radially and 0.0394 inch (1 mm) axially.
b) No maximum number in Area C if the damage is less than
0.256 inch (6.5 mm) radially and 0.079 inch (2 mm) axially.
c) A maximum service extension of 10 cycles/15 hours is permitted if the damage is more than the limits for the Areas A, B and C.
3) Look for nicks, dents and scratches on the concave or convex surfaces. a) No maximum number in Areas A and B if the diameter is
less than 0.09 inch (2.5 mm).
1. Protrusions are permitted if they do not go through
_ the metal.
b) A maximum service extension of 10 cycles/15 hours is permitted if the diameter is less than 0.157 inch (4 mm).
c) No maximum number in Area C if the diameter is less than 0.197 inch (5 mm).
1. Protrusions are permitted if they do not go through
_ the metal. d) A maximum service extension of 50 cycles/75 hours is permitted if the diameter is less than 0.295 inch
(7.5 mm).
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72-00-00
ALL ú ú C01 Page 613 ú Nov 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
LPC Blades and Vanes (1st- thru 4th-Stage) - Inspection
_______________________________________________________
4) Look for nicks, dents and scratches on the leading edge and the trailing edge. a) No maximum number if the axial length is than 0.079
inch (2 mm). 5) Look for vanes which have disengaged from the inner shroud. a) This damage is not serviceable. 6) Look for distortion of the leading and trailing edges. a) No maximum limit if the damage is less than 0.709 inch (18 mm) radially and 0.256 inch (6.5 mm) axially.
(e) Carefully put the borescope in the borescope port (S0) (Fig. 602
NOTE: This port is found between the outlet guide vanes (OGV)
____ at the 3:30 o'clock position
(f) While you turn the rotor manually, examine the trailing edges of the 3rd-stage blades and the leading edges of the 4th-stage blades. 1) Use the same damage limits given for the 2nd-stage rotor
blades.
S 846-048-C00
(5) If the borescope inspection is complete, remove and store the borescope equipment and do the procedure to put the airplane back to its usual condition.
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ALL ú ú C01 Page 614 ú Jul 15/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
HPC Blades (1st- thru 9th-Stages) - Inspection
______________________________________________
TASK 72-00-00-216-049-C00
4. HPC Blades (1st- thru 9th-Stages) - Inspection______________________________________________
A. References
(1) AMM 75-31-00/201, Variable Stator Vane Actuator System
B. Access
(1) Location Zones
506 No. 1 Engine
606 No. 2 Engine
C. Do the HPC Blade Inspection.
S 846-012-C00
(1)
If not already done, do the procedure to prepare for the borescope inspection.
S 866-013-C00
(2)
Put the VSV's in the fully open position (AMM 75-31-00/201).
(a) You can use the actuator cart for the stator vanes or dry motor the engine.
S 036-014-C00
CAUTION:_______THE BORESCOPE PLUGS ARE NOT INTERCHANGEABLE. IF YOU
INTERCHANGE THE PLUGS, ENGINE DAMAGE CAN OCCUR.
(3) Remove and identify the applicable borescope plugs from along the compressor case between the 4 and 5 o'clock positions (Fig. 605).
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本文链接地址：737-300 400 500 AMM 飞机维护手册 ENGINE 发动机 1(19)
