(2)
Aft compartment access door 3701
Feb 20/90 27-31-12 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
G09266
Access Panel Location 500
27-31-12Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/84
(3)
Stabilizer access panels 9105, 9107, 9108, and 9109 for left stabilizer
(4)
Stabilizer access panels 9205, 9207, 9208 and 9209 for right stabilizer
(5)
Elevator tab lock mechanism upper and lower access panels 9143 and 9142 on left elevator or 9243 and 9242 on right elevator
(6)
Tab pushrod access panel 9313 on left elevator or 9413 on right elevator
(7)
Elevator hinge fitting upper and lower access panels 9128 thru 9141 for left elevator
(8)
Elevator hinge fitting upper and lower access panels 9228 thru 9241 for right elevator and elevator control pushrod aft bolt access panel 3806 left or 3807 right (panel is located in tail cone adjacent to bolthead)
C. Set horizontal stabilizer B dimension at 41.57 +0.05 inches using trammel bar (Fig. 407).
D. Install rigging pin E-5 in aft control quadrant (Fig. 406).
4. Remove Elevator
A. Detach elevator control pushrod from elevator (Fig. 401 and 406). Remove bolts through circular access opening in tail cone adjacent to bolthead.
B. Disconnect tab pushrods and tab lockout mechanism as follows (Fig. 409):
(1)
Remove elevator tab lock linkage bolt retainer shield to obtain access for removal of frame attach bolts.
(2)
Remove tab pushrod aft mounting bolt (two places).
(3)
Remove two bolts securing aft end of frame to elevator front spar.
(4)
At stabilizer trailing edge ribs No. 1 thru 4, remove elevator to stabilizer gap seals (Fig. 402).
(5)
Remove six bolts securing aft portion of each balance panels from elevator (Fig. 407).
(6)
Remove elevator hinge fitting bolt and hinge link bolts and bushing from No. 3 and 4 hinges (Fig. 405).
(7)
Secure elevator hoisting adapter to elevator front spar at hinge fitting No. 3 and 4 locations (Fig. 403).
(8)
Attach sling to elevator hoisting adapter and take up slack in line.
(9)
Remove elevator hinge fitting bolts 1, 2, 5, and 6 from elevator hinge (Fig. 404 and 405). On airplanes incorporating SB 51-1011, disconnect ground strap approximately 7 inches inboard of hinge fitting No. 6.
(10)
Remove elevator from airplane.
NOTE: Weight of elevator with tab and balance panels installed is approximately 180 pounds.
(11)
If a different elevator is to be installed, perform the following steps:
(a)
Detach hoisting adapter from elevator front spar.
(b)
Install elevator to stabilizer gap seals adjacent to hinge fittings and along edge of elevator nose at stabilizer trailing edge ribs No. 1 thru 6 (Fig. 402).
500
Feb 20/89 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-12 Page 403
5. Prepare for Installation
CAUTION: ELEVATOR CONTROL PUSHROD, PUSHROD BOLT, AND ROD END BOLT ARE DUAL LOAD PATH COMPONENTS. INSPECT INNER AND OUTER RODS/BOLTS FOR DAMAGE PRIOR TO INSTALLATION.
A. Check elevator hinge bearings, hinge bearing bolts, and elevator control linkage for allowable wear (Ref Elevators - I/C).
B. If new elevator is being installed, perform the following steps on new elevator. If original elevator is being installed, proceed to step 5.E.
C. Remove the following access panels (Fig. 401): Elevator tab lock mechanism upper and lower access panels (panels are located at elevator inboard leading edge), tab pushrod access panels, and elevator hinge fitting upper and lower access panels.
D. Remove elevator to stabilizer gap seals adjacent to hinge fitting and along edge of elevator nose at stabilizer trailing edge ribs No. 1 thru 4 (Fig. 402).
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