(c) Examine the inner and outer platforms on the 2nd-stage HPT turbine nozzle for the
conditions that follow:
Condition Maximum Serviceable Limit
Cracks in the platform area between the vanes Cracks 0.150 inch (3.81 mm) in length are permitted with no
quantity limit. Two cracks 0.60 inch (15.24 mm) in length are
permitted on each platform segment if the cracks are at least
0.30 inch (7.62 mm) apart. Refer to the
Continue-In-Operation Limits.
Nicks, scores, scratches and dents on the platform
surfaces
All of this type of damage is permitted if it is less than 0.030
inch (0.76 mm) in depth.
Craze cracks Permitted.
NOTE: Craze cracks are cracks that do not break the
surface layer.
Cracks in the outer plat- form trailing edge Cracks less than 0.12 inch (3.05 mm) in length are permitted
without a quantity limit. Two cracks less than 0.40 inch (3.05
mm) in length are permitted on each segment.
(d) Examine the 2nd-stage shroud rub surface on the 2nd-stage HPT nozzle for the
conditions that follow (Figure 616):
Condition Maximum Serviceable Limit
Signs of wear and erosion This type of damage is permitted if it does not go all the way
through the surface. Refer to the Continue-In-Operation
Limits.
Axial cracks Permitted, two on each segment if the cracks are less than
0.50 inch (12.7 mm) in length. One crack on each segment
is permitted if the crack is less than 1.00 inch (25.4 mm).
Refer to the Continue-In-Operation Limits.
Bradelloy fallout Permitted, if the damage is not fully through the material.
Refer to the Continue-In-Operation Limits.
SUBTASK 72-00-00-416-197-G00
(14) Do the steps that follow to install the borescope plugs B2-1 through B2-6, B3-1 and B3-2
(Figure 601):
CAUTION
MAKE SURE THAT THE BORESCOPE PLUGS ARE INSTALLED IN THE
CORRECT PORT LOCATIONS. ENGINE DAMAGE CAN OCCUR IF A
BORESCOPE PLUG IS NOT INSTALLED IN THE CORRECT LOCATION.
(a) Apply a light layer of anti-seize compound on the threads and the pressure faces of the
plugs.
(b) Install the plugs in the ports.
NOTE: Turn the plunger of the B3-1 plug to engage the internal hole in the impingement
ring and the HPT Stage 1 Nozzle. These holes are a short distance aft of the
B1-3 borescope port in the Compressor Rear Frame (CRF).
(c) Tighten the plugs to the torque values shown in Table 601.
1) Install lockwire.
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-00-00
NoC
Page 698.1
D633T1B7 Aug 22/2017
ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details
EFFECTIVITY
ABX 001-007, 011, 012, 016-019, 021, 022, 025, 101,
109, 114, 115, 314-999
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