(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).
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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 72-53-00-040-052
C. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041). Subtask 72-53-00-010-058
D. Open the thrust reverser doors: (Ref. TASK 78-36-00-010-040)
FOR 1000EM1
451AL, 452AR
FOR 1000EM2
461AL, 462AR
4. Procedure
_________ (Ref. Fig. 601/TASK 72-53-00-991-300, 602/TASK 72-53-00-991-301) Subtask 72-53-00-020-051
A. Remove the borescope plugs found immediately in front of the aft flange of the combustion case.
Subtask 72-53-00-290-052
B. Do a borescope inspection.
(1) Connect the fiber light cable to the BORESCOPE KIT (856A1320P04/P05) and to the port on the BORESCOPE - LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08).
NOTE : Use the MONITOR, RESOLUTION BORESCOPE (856A1323G01) to make
____ sure the borescope and the light source are serviceable. See the Non-Destructive Test Manual for this procedure. (Ref. NDTM 72-00-00).
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Stage 1 LPT Nozzle and HPT Shroud Inspection
Figure 601/TASK 72-53-00-991-300
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Stage 1 LPT Nozzle Segment
Figure 602/TASK 72-53-00-991-301
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(2) Put the rigid borescope of the BORESCOPE KIT (856A1320P04/P05), and to the port into turn on the light source of BORESCOPE - LIGHT SOURCE SET (856A1322P02/P03/P04/P07/P08).
(3) Inspect the stage 1 LPT nozzle and use the limits that follow :
-------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS -------------------------------------------------------------------------------
1. Stage 1 LPT nozzle for:
A. Cracks in leading edge.
B. Cracks in trailing edge.
C. Cracks on concave/convex side of airfoil between inner and outer platform.
D. Crack in radius in between airfoil L.E./T.E. and outer platform.
E. Burns, erosion and corrosion
F. Nicks, scores, scratches, dents or deposits on concave/convex surface or trailing edgeAny number, that are not more than 0.6 in. (15.24 mm) long.
Any number, that are not more than 0.8 in. (20.32 mm) long.
Any number, that are not more than 1 in. (25.4 mm) long. If there is a separation of 0.25 in.between adjacent crack.
One on each airfoil, not more than 1.2 in. (30 mm) long with a minimum of 0.4 in. (10 mm) from any adjacent crack.
Any amount, if there is no missing material (no perforation of the airfoil cavity).
Any amount, not through, provided there are no cracks out of distressed area.
See limit extensions(Ref. TASK 72-00-00-200-025).
See limit extensions(Ref. TASK 72-00-00-200-025).
See limit extensions(Ref. TASK 72-00-00-200-025).
See limit extensions(Ref. TASK 72-00-00-200-025).
See limit extensions(Ref. TASK 72-00-00-200-025).
See limit extensions(Ref. TASK 72-00-00-200-025).
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-------------------------------------------------------------------------------INSPECT/CHECK MAXIMUM REMARKS SERVICEABLE LIMITS -------------------------------------------------------------------------------
G. Nicks, dents, Any amount, if cracks See limit extensions tears in leading criteria are in the (Ref. TASK 72-00-00-200-edge. limits. 025).
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