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__________ Subtask 72-56-00-941-051
A. Safety Precautions
(1) On the center pedestal, on the ENG panel 115VU:
(a) Put a warning notice to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a warning notice to tell persons not to energize the FADEC 1(2).
Subtask 72-56-00-010-053
B. Get Access
(1) Open the fan cowl doors: (Ref. TASK 71-13-00-010-040)
FOR 1000EM1
437AL, 438AR
FOR 1000EM2
447AL, 448AR
(2) Put the access platform in position. Subtask 72-56-00-040-051
C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-56-00-010-054
D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040)
FOR 1000EM1
451AL, 452AR
FOR 1000EM2
461AL, 462AR
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4. Procedure
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R (Ref. Fig. 601/TASK 72-56-00-991-305)
Subtask 72-56-00-210-051
A. Visual inspection of the Turbine Frame Assembly:
-------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS -------------------------------------------------------------------------------
1. Forward and aft outer
flanges for :
- Cracks connecting Not serviceable
bolt holes
- Cracks extending One crack 0.20 in. (5.1
from bolt holes to mm) max. per hole with a
outer edge of minimum 5-hole
flange. separation between
cracks.
- Cracks extending Five cracks 0.20 in.
from bolt holes (5.1 mm) max. per flange
toward casing skin. with a minimum 10-hole
separation between cracks. Axial cracks only.
- Cracks in other Five cracks per flange
areas of flange. 0.20 in. (5.1 mm) long
with a minimum 5 in.
(127 mm) separation
between any other
cracks.
- Nicks, scores and Five per flange 1 in.
scratches. (25.4 mm) long, 0.01 in.
(0.25 mm) dup, after removal of high metal with 1 in. (25.4 mm) minimum separation.
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R R Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 15 (SHEET 1)
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R R Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 25 (SHEET 2)
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R R Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 35 (SHEET 3)
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R R Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 45 (SHEET 4)
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R R Turbine Frame Struts Figure 601/TASK 72-56-00-991-305- 55 (SHEET 5)
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-------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS -------------------------------------------------------------------------------
2. Engine mounting lug areas, airframe attach points only for :
- Cracks out of bolt holes
- Cracks in welds or in other areas of engine mounting lug area.
- Nicks, scores and scratches.
3. All other areas of outer casing skin for :
- Cracks
- Nicks, scores and scratches.
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