CAUTION: IF THE NUTS ARE NOT TORQUED PROPERLY, THE PUSH RODS CAN BECOME DETACHED AND CAUSE DAMAGE TO THE ELEVATORS AND STABILIZERS.
F. Connect tab push rods to elevator tab. Place head of inboard bolt facing inboard and head of outboard bolt facing outboard. Do not install nut and washer until tab alignment is assured.
(1) If castellated nuts are used, torque nuts 30 to 50 inch-pounds. Ensure the torque remains at 30 to 50 inch-pounds after alignment of the cotter pin holes. If self-locking, non-castellated nuts are used, run-on torque must be between 3.5 and 30 inch-pounds. Replace any self-locking nut that does not meet this requirement. Torque nut 50 to 80 inch-pounds.
G. Remove rigging pin E-5 from aft control quadrant.
H. Adjust elevator tab and test tab linkage (Ref 27-31-0 A/T). 6A. Install Elevator Tab (Airplanes with Composite Elevators)
A. Manually rotate all hinge fittings through full travel in both directions and check that movement is smooth and without binding.
B. Install tab on hinge fittings at elevator rear spar and tighten bolts to 15 pound-inches.
C. Deflect tab through full travel in both directions and check that movement is smooth and without binding.
D. At inboard and outboard tab hinge fittings, secure bonding jumpers to elevator tab and seal with BMS 5-95 sealant. Clean mating surfaces. Use the milliohmmeter to make sure that the maximum electrical resistance of the bonding jumper connection is 0.010 ohms.
E. Connect tab push rods to elevator tab; ensure bushings are installed and bolts face each other. Do not install nut, washer and cotter key until tab alignment is assured.
F. Remove rigging pin E-5 from aft quadrant.
G. Adjust elevator tab and test tab linkage (Ref 27-31-0 A/T).
7. Restore Airplane to Normal Configuration
A. Restore airplane to normal hydraulic configuration (Ref 27-31-0).
B. Close access doors and install all access panels.
522 Rigging Pin E-5 Location
May 01/99 Figure 403 27-31-31
Page 407
G09441
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
TAB WEIGHT (POUNDS) NUMBER OF ADJUST WEIGHTS REQUIRED
6.30 TO 6.40 6.41 TO 6.60 6.61 TO 6.80 6.81 TO 7.00 7.01 TO 7.20 7.21 TO 7.40 7.41 TO 7.60 0 1 2 3 4 5 6
AIRPLANES WITH METAL ELEVATOR TABS
TAB WEIGHT (POUNDS) NUMBER OF ADJUST WEIGHTS REQUIRED
5.00 TO 5.10 5.11 TO 5.30 5.31 TO 5.50 5.51 TO 5.70 5.71 TO 5.90 5.91 TO 6.10 6.11 TO 6.30 0 1 2 3 4 5 6
AIRPLANES WITH FIBERGLASS ELEVATOR TABS
TAB WEIGHT (POUNDS) NUMBER OF ADJUST WEIGHTS REQUIRED
5.00 TO 5.10 5.11 TO 5.30 5.31 TO 5.50 5.51 TO 5.70 5.71 TO 5.90 5.91 TO 6.10 6.11 TO 6.30 0 1 2 3 4 5 6
AIRPLANES WITH GRAPHITE/COMPOSITE ELEVATOR TABS ELEVATOR TABS - INSPECTION/CHECK
Elevator Tab Adjust Weight Requirements 500
27-31-31 Figure 404 May 01/99
Page 408
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
1. General
A. This data consists of illustrations and wear limits charts. There will be no procedure given in this section for gaining access to, or removing and replacing the component after inspection for wear. Refer to component removal/installation for this information.
2. Elevator Tabs Fasteners Inspection
A. On fasteners which attach the elevator hinge bracket to the elevator rear spar, tighten fastener until seated. Loosen fastener and re-tighten to within torque range 65-75 pound-inches.
CAUTION: DO NOT EXCEED 90 POUND-INCHES OR DAMAGE TO FASTENER MAY RESULT.
B. On fasteners which attach the mast fitting assembly to the elevator tab, tighten fastener until seated. Torque range for fastener is 20-25 pound-inches.
3. Elevator Tabs Wear Limits
A. Figure 601 covers aluminum/fiberglass elevator tab wear limits and Fig. 602 covers
graphite/composite elevator tab wear limits.
G42336
500 Elevator Tab Wear Limits
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