(5)  
Hone internal diameter of bushing to diameter of 1.2530 to 1.2540 inches with machine finish 63 microinches AA. Use standard Sunnan hone.

E.  Machine new bushing flanges.
(1)  
Remove -101 tool frame assembly from rear spar.

(2)  
After completion of bushing replacement per par. D, measure and record the distance between the new bushing flange face and clevis or lug in the same marked location. Subtract the previous measurement from this new measurement to obtain the amount of material to remove from the flange.

(3)  
Set up flange machining operation as shown in Section A-A and proceed as follows:

(a)  
Rotate -310 micrometer barrel assembly counterclockwise from bottomed out position to the "40" mark (or 10 graduations = 0.10 inch travel).

(b)  
With -107 facing cutter in place, rotate cutter by hand and advance -313 collar clamp assembly until cutter makes contact with highest point on new bushing flange. Tighten setscrew in -313 collar clamp assembly to hold -306 arbor firmly.

(c)  
Rotate micrometer barrel clockwise back to bottomed setting (this will give an additional 0.10 inch of clearance).

500 
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C20824
Vertical Fin to Body Rear Spar  500 
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Page 804  Figure 801 (Sheet 1) 
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500  Vertical Fin to Body Rear Spar Attach Fitting Bushing Replacement 
Jan 20/82  Figure 801 (Sheet 1)  55-30-11 
Page 805 
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C25489
Vertical Fin to Body Rear Spar  500 
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Page 806  Figure 801 (Sheet 3) 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

(d)  
Proceed to spotface by backing off (counterclockwise) -310 barrel assembly until amount of material determined in step (2) is removed.

NOTE: Make readings periodically to prevent overtravel.

(e)  
Reverse set-up to spotface opposing flange to engineering specified dimension of

2.165 +0.001 inches between bushing faces of fin rear spar lug.

(f)  
Finish spotface surfaces per Fig. 803.

F.  Seal bushings as follows:
(1)  Fillet seal around flange outside diameter and void at end of bushing with sealant. Apply primer topcoat over sealant.
G.  Install vertical stabilizer (fin) (Ref 55-30-0).
4.  Replace Vertical Fin and Body Section Front Spar Lug or Clevis Individual Bushing (Fig. 802)
A.  Remove vertical stabilizer (fin) (Ref 55-30-0).
B.  Prepare tooling for reaming operation (potting of reamer bushings).
(1)  
See View 1, View 2, and View 3 for lug to set up potting of P40-16-3/8 and P-80-16-.8780 reamer bushings. Install -211 and -214 spacers at clevis or lug locations.

(2)  
Clamp -201 tool frame assembly with C-clamp to body clevis or fin lug at replacement location and use -204 clamping pin as shown and -215 and -218 spacers as shown in Section A-A.

(3)  
Apply potting compound around P-40-16-3/8 and P-80-16-.8780 bushings after -209 potting pins and bushings are in place. Lock the 5/16-inch socket set screws to clevis or lug and apply putty to ensure set screws will not back off.

NOTE:  If bushings are to be replaced in lug and clevis at same location, the tool need only to be potted to the spar lug or clevis, then use for its mate.

(4)
Remove -201 tool assembly after potting compound is cured and firmly set.

C.  Ream oversize hole in clevis or lug.
(1)  
Remove existing defective bushing using -125 removal tool.

(2)  
Clean and deburr holes and adjacent surface thoroughly.

(3)  
Mask or shield structure to prevent contamination with abrasive materials during abrasive blast cleaning or with shot during shot peening.

CAUTION: FOREIGN PARTICLES MAY CAUSE CORROSION TO STRUCTURE.
500 
Jan 20/82  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  55-30-11 Page 807 

C26092 C25349 C21601
Vertical Fin to Body Rear Spar  500 
55-30-11  Attach Fitting Bushing Replacement  Jan 20/82 
Page 808  Figure 802 (Sheet 1) 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 
　
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