72-33-02
 ALL  ú ú N01 Page 845 ú Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
FAN EXIT LINER SEGMENTS (OUTER)- REMOVAL/INSTALLATION
_____________________________________________________
 1.  General_______
 A.  This procedure gives the tasks to remove and install the (outer) fan exit liner segments. These fan exit liner segments will be referred to as the outer liner segments.
 B.  The nine outer liner segments are found on the outer rear circumference of the intermediate case, aft of the fan case. The outer liner segments are referred to as follows:
 Liner PWA Segment Part Number
 No. 1 PN 50G522 or PN 51G899-01 No. 2 PN 50G520 or PN 51G897-01 No. 3 PN 50G519 or PN 51G896-01 No. 4 PN 50G524 or PN 51G901-01 No. 5 PN 50G521 or PN 51G898-01 No. 6 PN 50G524 or PN 51G901-01 No. 7 PN 50G518 or PN 51G895-01 No. 8 PN 50G517 or PN 51G894-01 No. 9 PN 50G523 or PN 51G900-01
 C.  You can open each half of the thrust reverser to get access to the outer liner segments.
 TASK 72-34-01-004-001-N00
 2.  Remove the Fan Exit Liner Segments (Outer)__________________________________________
 A.  Equipment
 (1)
No. 10 Torq-set Drive

 B.  
References

 (1)
AMM 71-11-04/201, Fan Cowl Panels

 (2)
AMM 71-11-06/201, Core Cowl Panels

 (3)
AMM 78-31-00/201, Thrust Reverser System

 C.  
Access

 (1)  
Location Zone
 412 Engine 1 - LPC Intermediate Case
 422 Engine 2 - LPC Intermediate Case
 432 Engine 3 - LPC Intermediate Case
 442 Engine 4 - LPC Intermediate Case

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 72-34-01
 ALL  ú ú N01 Page 401 ú Jun 10/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////

SCHEMATIC REAR VIEW OF THE INTERMEDIATE CASE
ENGINES WITH PW SB 72-205. ENGINES WITHOUT PW SB 72-205;THE CLEARANCE BETWEEN BRACKET ASSEMBLIES IS NOT ALIGNED WITH THE STRUTS.

Fan Exit Liner Segment (Outer) Installation Figure 401 (Sheet 1)
C16473
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 72-34-01
 ALL  ú ú N01 Page 402 ú Jun 10/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
THE SEALANT BETWEEN THE OUTER LINING SEGMENT AND THE OUTER BIFURCATION FAIRING MUST BE SMOOTH AND NOT MORE THAN 0.010 INCH (0.254 mm) ABOVE THE
ADJACENT SURFACES
OUTER BIFURCATION FAIRING (TWO LOCATIONS)
SCREW (70 LOCATIONS)
SCREW (31 LOCATIONS)
SCREW (31 LOCATIONS)
SCREW (69 LOCATIONS)
B

SCREW (22 LOCATIONS)
THE SEALANT ALL AROUND THE STRUT MUST HAVE A RADIUS OF 0.250-0.500 INCH (6.4-12.7 mm)
THE SEALANT BETWEEN THE LINER AND BRACKET ASSEMBLIES MUST BE SMOOTH AND NOT MORE THAN 0.020 INCH
(0.508 mm) ABOVE THE ADJACENT SURFACES
THE SEALANT BETWEEN THE LINER AND OUTER BASES OF THE FAN EXIT VANES MUST BE SMOOTH AND NOT MORE THAN 0.010 INCH
(0.254 mm) ABOVE THE ADJACENT SURFACES
THE SEALANT BETWEEN THE LINERS, FORWARD OF THE STRUT, MUST BE SMOOTH AND NOT MORE THAN 0.010 INCH (0.254 mm) 2 ABOVE THE ADJACENT SURFACES. SEALANT THAT PUSHES THROUGH TO THE OTHER SIDE CAN BE IRREGULAR.
D
BRACKET
ASSEMBLY

NO SEALANT IS PERMITTED HERE (8 LOCATIONS)
C
OUTER BASES
OF THE FAN
EXIT VANE
ASSEMBLY
2  ENGINES WITH PW SB 72-205; THE LIMIT FOR ENGINES WITHOUT PW SB 72-205 IS 0.020 INCH
(0.508 mm).
Fan Exit Liner Segment (Outer) Installation
Figure 401 (Sheet 2)

STRUT
THE SEALANT AROUND THE STRUT THAT PUSHES THROUGH THE CLEARANCE CAN BE IRREGULAR
THE SEALANT BETWEEN THE BRACKET ASSEMBLIES MUST BE SMOOTH AND NOT MORE THAN 0.010 INCH (0.254 mm) ABOVE THE ADJACENT SURFACES. THE SEALANT THAT PUSHES THROUGH TO THE OTHER SIDE CAN BE IRREGULAR. (10 LOCATIONS)
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