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Subtask 72-00-00-010-147
D. Open the thrust reverser doors (Ref. TASK 78-36-00-010-040):
FOR 1000EM1
451AL, 452AR
FOR 1000EM2
461AL, 462AR
4. Procedure
_________
R (Ref. Fig. 606/TASK 72-00-00-991-308, 607/TASK 72-00-00-991-309, 608/TASK R 72-00-00-991-321, 609/TASK 72-00-00-991-320)
Subtask 72-00-00-210-101
A. Over-serviceable-limit Extensions
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CONDITION MAX EXTENSION
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1. Fan and booster
A. Spinner front cone
(1) Damaged surface protection greater than 50 50 cycles percent of total surface
B. Fan blade
(1) Fully missing molydag on inner faces of the 250 cycles platforms
(2) Flaking of Cu.Ni.In coating on blade dovetail Examine blades for pressure faces (contact areas), up to 10 serviceability. percent if there is no indication of wear on (Ref. TASK 72-21-base material 00-210-006) 1200
cycles after relubrication. Repeat extension is permitted
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R HPT Blade Inspection (Only Applicable /P Engines) Figure 609/TASK 72-00-00-991-320
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(3) Flaking of Cu.Ni.In coating on blade dovetail Examine blades for
pressure faces (contact areas), more than 10 serviceability.
percent and less than 50 percent if there is (Ref. TASK 72-21-
no indication of wear on base material 00-210-006) 400
cycles after
relubrication.
Repeat extension is
not permitted
(4) Shingling at mid span shrouds Turn the shingled
blades to the 12
o'clock position
and unshingle with
hand force or by
using a piece of
wood. Examine
blades for
serviceability
(Ref. TASK 72-21-
00-210-009) Remove
and send the
shingled blades to
a shop for a
dimensional and an
F.P.I. inspection
in less than 50
cycles
(5) Nicks, dents, scratches and sheared edges on 50 cycles
midspan shroud surfaces up to 0.035 in. (0.89
mm) deep if defects are not in the midspan
shroud to airfoil fillet radius
(6) Missing or damaged hard coating on midspan 50 cycles
shroud pressure faces more than 20 percent
but less than 40 percent of coated area
C. Fan disk
(1) Wear greater than 50 percent of area on disk 100 cycles
dovetail pressure faces
D. Booster rotor blade for:
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(1) Piece missing:
any number in area G, at leading edge and 50 cycles/75 hours
trailing edge tip corners, 0.8 in. (20 mm)
radial and 0.5 in. (12.5 mm) axial
(2) Cracks and tears in area G, 0.8 in. (20 mm) 50 cycles/75 hours
from tip : any number less than 0.8 in. (20
mm) radial and less than 0.492 in. (12.5 mm)
axial
(3) Wear or local distortion of T/E and L/E tips 100 cycles/150
if less than 15 blades 0.984 in. (25 mm) hours
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