(2)
Apply BMS 3-27 corrosion preventive compound on bolt shanks, washers, and all mating surfaces.
(3)
Apply BMS 3-28 anti-seize compound on bolt threads and nut threads.
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27-41-11 Page 410 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/99
C. Raise horizontal stabilizer to position mounting lugs parallel to center section clevis.
D. Move stabilizer inward and position to align front and rear spar fittings.
CAUTION: TAKE PRECAUTION NOT TO DAMAGE ADJACENT STRUCTURE BY SUDDEN OR UNCONTROLLED MOVEMENTS OF HORIZONTAL STABILIZER.
E. Attach stabilizer outboard section to center section as follows:
(1)
Apply a light film of grease to bore and flange surfaces of bushings in rear spar joint fittings and to attachment bolts (1) and washers.
(2)
With stabilizer hoisted into position and with front and rear spar joints properly mated, install bolts (1) (heads facing aft), washers (8), and nuts (7) in rear spar joints.
(3)
Temporarily insert bolts (9) in forward spar joints.
(4)
Measure gaps between bushing faces of male and female lugs at rear spar joint. Maximum allowable gap for each clevis (sum of two gaps) is 0.014 inch. If gap is greater than maximum do one of these:
(a)
Install a CRES laminated shim to make sure the clearance is correct before you reinstall the bolt.
(b)
Replace flanged bushings with new bushings of flange thickness necessary to obtain correct gap limit.
(5)
On airplanes without nut retainers, tighten nuts (7) at rear spar joints 3300 to 4300 pound-inches. Align bolts (1) with serrated cutouts in bolt lock (2) without exceeding specified torque. Install bolt lock and secure with locking bolt washer (3) and locking bolt (4) and tighten to 660-980 pound-inches. Install lock wire securely between locking bolt and bolt lock.
NOTE: Due to the configuration of the rear spar fail-safe lug, the bolts (1) may be loose while the airplane is on the ground.
(6)
On airplanes with nut retainers, tighten nuts (7) at rear spar joints 480 to 600 pound-inches. Fill cavity of nut retainers (4) with sealant and push onto nut. After installing cotter pin, apply a fillet seal around bolt next to nut retainer.
NOTE: Due to the configuration of the rear spar fail-safe lug, the bolts (1) may be loose while the airplane is on the ground.
(7)
Fit shims (16) to gaps between spar lug (11) and clevis lugs (10) of front spar joint. Peel lamination as required to provide fit-up of 0.005-inch maximum gap per side (maximum of
0.010 gap per clevis).
(8)
Apply a light film of grease to bore and flange surfaces of bushings in front spar joint fittings, to attachment bolts (9), washers, and shims.
(9)
Install shims (16), bolts (9), washers (14, 15, 18), and nuts (12) in front spar joints. Tighten nuts at front spar joints 800 to 1,000 pound-inches.
(10)
Measure gap between washers (14) and (15) at front spar fittings. Fit shims (17) as required to maintain a 0.003- to 0.012-inch gap.
(11)
Back off nuts at front spar joints to align with nearest pair of cotter pin holes and install cotter pins.
F. Remove sling and sling attachment fittings from horizontal stabilizer and install original fasteners in sling attachment fitting holes.
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May 01/98 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-41-11 Page 411
G. If applicable, attach elevator to stabilizer (Ref 27-31-11, Removal/Installation).
H. Connect elevator tab hydraulic line located aft of stabilizer rear spar (Fig. 403).
I. If step G was not applicable, connect elevator control pushrod to elevator as follows:
(1)
Move elevators by hand to neutral position.
(2)
Insert bolt with head inboard through control pushrod and elevator lug (Fig. 402).
(3)
Torque first locknut to 500-600 pound-inches, then torque second locknut to 150-220 pound-inches.
CAUTION: AFTER SETTING TORQUE ON SECOND LOCKNUT, DO NOT ATTEMPT TO RESET TORQUE ON FIRST LOCKNUT.
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