(2)
AMM 73-11-02/601, Fuel Filter Cartridge
B. Access
(1) Location Zones
506 Left Engine
606 Right Engine
C. Do the Inspection of the LPT Rotor Blades (1st thru 3rd Stage).
S 846-045-C00
(1)
If not already done, do the procedure: Prepare for the Borescope Inspection.
S 016-047-C00
(2)
Remove the applicable borescope plug (Fig. 608).
(a)
The borescope ports S17, S21 and S22 are found along the turbine case at the 5 o'clock position.
(b)
The borescope port S20 is found at the 3 o'clock position on the turbine case.
S 296-049-C00
(3)
Put the rigid borescope, with a 90° right angle viewer and 60° field of vision, in the borescope port.
S 296-050-C00
(4)
Examine the rotor blades with a borescope as given below:
WARNING:_______BE CAREFUL WHEN YOU TURN THE FAN ROTOR. MAKE SURE YOU ARE IN A STABLE POSITION. ALSO, YOU MUST WEAR HEAVY PROTECTIVE GLOVES TO PREVENT DAMAGE TO YOUR HANDS. IF YOU DO NOT OBEY THESE INSTRUCTIONS, INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.
(a)
Examine the LPT rotor blades while you turn the fan rotor in a smooth, stable movement.
(b)
To examine the airfoil as the blades turn, you must change the probe depth in the LPT case.
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72-00-00
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
Low Pressure Turbine (LPT) Rotor Blade (1st thru 3rd Stage) - Inspection
________________________________________________________________________
(c) Turn the probe (azimuth) at the same time you change the depth
of the probe.
1) This will permit the maximum view for a given turn speed.
NOTE:____ It can be necessary the make more than one complete
rotation of the LPT as the length of the blade
increases. Also, to fully view the platform and the
root areas, it can be necessary to put the full
probe length into the LPT case.
(d) When you examine the leading edges or concave side of the
blades, it is recommended that you turn the rotor so the blades
come to the borescope, and not away from it.
(e) When you examine the trailing edges or convex side of the
blades, it is recommended that you reverse the rotation of the
rotor so the blades come to the borescope, and not away from
it.
S 296-051-C00
(5) Examine the 1st through 3rd Stage Rotor Blades as follows (Fig. 608):
NOTE: If you think there is damage, you can look at the damage
____ with the retro-angle viewer. For the blade tip and blade platforms, you can use the fore-oblique angle viewer.
(a) Cracks (Fig. 608). 1) Cracks in area E of the airfoil surface are not serviceable.
2) Cracks in other areas of the airfoil surfaces are not serviceable. a) If not serviceable, a maximum service extension of 5
cycles or 10 hours is permitted if the crack is not more than 50 percent of the chord width. 3) Cracks in the blade platform are not serviceable.
a) If not serviceable, a maximum service extension of 5 cycles or 10 hours is permitted if the crack is not more than 50 percent of the chord width.
4) Cracks in the tip shrouds are not serviceable.
a) If not serviceable, a maximum service extension of 5 cycles or 10 hours is permitted if the crack is not more than 50 percent of the chord width.
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