(b)  
Install bolt (11) through hinge plates (20) and elevator hinge (1). Install bolt with head outboard at hinge No. 3, 4, 5, and 6. Install bolt with head inboard at hinge No. 6 if clearances between structures and hinge fitting prevent installation from outboard side. Place a washer (9) under bolthead and a washer (9) under nut (8). For elevator hinge No. 6, place bonding jumper (5) and washer under nut and a washer under bolthead. At hinge No. 6 clean surface to provide electrical bonding. Also, hinge should be assembled so that lubrication fitting on elevator hinge is down (below hinge centerline) when installed.

WARNING:  DO NOT GET SOLVENT IN YOUR MOUTH OR EYES, OR ON YOUR SKIN. DO NOT BREATHE THE FUMES FROM SOLVENTS. SOLVENTS ARE HAZARDOUS MATERIALS. REFER TO PRODUCT MATERIAL SAFETY DATA SHEETS (MSDS) AND LOCAL REQUIREMENTS FROM PROPER HANDLING PROCEDURES.

(c)  
At all four hinges, tighten nut (8) 60 to 85 pound-inches. Align nut with cotter pin hole without exceeding 140 pound-inches, then install cotter pin (10).

(2)  
Position hinge assembly at elevator front spar (3) with boltheads oriented per step (l) and temporarily install three plate bolts (19) at hinge location No. 3 or 4, or two plate bolts (19) at hinge location No. 5 or 6.

(3)  
Check that hinge fits flush with shear plate (2) at elevator front spar (3) within 0.015 inch. If not, add or remove shim (4) as required.

(4)  
If shim is required, proceed as follows:

500 
May 01/98  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-21 Page 409 

NOTE:  Maximum allowable shim thickness is 0.033 inch.
(a)  
Trim shim as required to fit between elevator hinge (l) and shear plate (2).

(b)  
Withdraw plate bolts (19) and remove hinge assembly from airplane.

(c)  
Thoroughly clean both faces of shim and face of shear plate using cleaning solvent.

(d)  
Bond required thickness of shim to shear plate at elevator front spar using adhesive.

(5)  
If step E.(4) was not accomplished, withdraw plate bolts (19) and remove hinge assembly from airplane.

(6)  
Thoroughly clean face of shim using cleaning solvent, then apply primer and allow to dry before installing hinge.

(7)  
Position hinge assembly at elevator front spar (3) and secure to stabilizer trailing edge rib

(21)
as follows:

NOTE:  When positioning hinge assembly, check that head of hinge bearing bolt (11) faces outboard at hinge No. 3 thru 6 (No. 6 can be inboard).

(a)  
At hinge location No. 3 or 4, install three plate bolts (19) with heads inboard. Place washer (22) under nut (23) and tighten nut 50 to 70 pound-inches (detail C).

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G09433
500  Elevator Hinge Seal Adjustment 
Nov 15/67  Figure 402  27-31-21 
Page 411 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

(b)  
At hinge location No. 5, install two plate bolts (19) with heads inboard. Place washer

(22) under nut (23) and tighten nut to 50-70 pound-inches torque. (See detail D.)

(c)  
At hinge location No. 6, install two plate bolts (19) with heads outboard. Place washer

(22) under nut (23) and tighten nut to 50-70 pound-inches torque. (See detail D.)
(8)  
Install four-hinge mounting bolts (7) with washers (6). At elevator hinge No. 6 location, clean surface to provide electrical bonding and place other end of bonding jumper (5) under washer at lower outboard bolt.

(9)  
Secure hinge assembly to elevator front spar by tightening hinge mounting bolts (7) to 70-80 pound-inches.

(10)
At hinge location No. 3, 4, or 5, see figure 402 and install hinge seals (24, details C and D, figure 401) as follows:

(a)  
Position seal each side of hinge assembly and loosely instal1 two bolts and washers up through each seal.

(b)  
Adjust seal to maintain 0.01 (+0.06/-0.00)-inch clearance between seal and hinge fitting.

(c)  
Tighten seal retaining bolts.

(11)
Perform test procedure. Refer to Elevator Hinges, Adjustment/Test.

F.  Restore Airplane to Normal Configuration.
(1)  
Replace elevator hinge access plates.

(2)  
Remove tags from control columns.

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