SUBTASK 72-31-02-328-003-G00
CAUTION
DO NOT CAUSE TOO MUCH HEAT DURING THE BLEND REPAIR. TOO
MUCH HEAT CAN MAKE THE PART WEAK.
(2) Use a fine file, an abrasive cloth, or an abrasive stone to do the blend repair.
NOTE: If the damage is very large or deep, use a slow speed power tool first. Then, blend by
hand to make the area smooth.
(a) Always blend in a longitudinal direction (parallel with the length of the blade).
(b) See Figure 801 for the Limits for the Blended Fan Rotor Blades.
SUBTASK 72-31-02-328-004-G00
(3) Do the steps that follow to blend the leading and trailing edges of the fan rotor blades
(Figure 802):
(a) Blend to remove material a minimum of 0.030 inch (0.76 mm) below the damaged area.
(b) If the repair area has a radius (Figure 802), the blended radius must be as close as
possible to the initial radius.
(c) The contour of the blended blade must be the same as the initial contour of the blade.
1) Optional: Use the fan blade template, SPL-12874 to do a check of the leading edge
blended contour.
NOTE: Stage 1 Fan Blade and all airfoil design is very important to the leading
edge shape. Damage to the leading edge will have an effect on
performance. The on-wing blending of the local airfoil leading edge shape
does not fully repair fan blade performance to when the blade was new. You
can get a small specific fuel consumption (SFC) improvement but a small
decrease in EGT margin can result.
NOTE: You can get near maximum Stage 1 fan blade performance without any
EGT margin effect by the on-wing repair of the airfoil leading edge shape
and the inspection of the airfoil leading edge contour by the use of template
SPL-12874. The position of the leading edge shape as related to the airfoil
contour is very important. Blending of the airfoil leading edge without the
use of the SPL-12874 inspection template can result in an unsatisfactory
leading edge with an incorrect relation between the airfoil leading edge and
the airfoil contour.
SUBTASK 72-31-02-238-028-G00
(4) Do the spot fluorescent penetrant test to make sure the defect is fully removed
(PAGEBLOCK 70-11-06/201).
NOTE: If the blade has been inspected before with nonfluorescent color dye penetrant,
contamination by the dye will prevent accurate fluorescent penetrant inspection.
(a) The fluorescent penetrant test must occur before a maximum of 50 flight hours or 10
flight cycles (whichever comes first) and include the procedures that follow:
1) The instructions in this blend repair task are followed, and the repair is in the limits
(PAGEBLOCK 72-31-02/601).
2) Visually do an inspection after the blend repair with a 10X magnifier and a white
light. No cracks are permitted.
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-31-02
NoC
Page 802
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,
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