G09075
Elevator Tab Wear Limits  539 
27-31-31 Page 602  Figure 601 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Nov 15/72 

505  Graphite/Composite Elevator Tab Wear Limits 
Feb 20/90  Figure 602 (Sheet 1)  27-31-31 
Page 603 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Graphite/Composite Elevator Tab Wear Limits  505 
27-31-31  Figure 602 (Sheet 2)  Feb 20/90 
Page 604 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

ELEVATOR BALANCE PANELS - REMOVAL/INSTALLATION
1.  General
A.  The following procedure describes the removal and installation of an individual balance panel and its associated seals. This procedure may be used for all balance panels except where otherwise stated. A replacement balance panel must meet weight requirement per Chapter 51 of the Structural Repair Manual.
2.  Equipment and Materials
A.  Rigging Pins Kit - F70207-3, -52, -61, or -84:
REF NO.  F70207-( )  DIAMETER (INCHES)  LENGTH (INCHES)  FUNCTION 
E-5  -11  0.309-0.311  6.7 +0.25  AFT CONTROL QUADRANT 

B.  Scale - 0 to 6 inches graduated in tenths and hundredths of an inch
3.  Prepare for Removal
A.  Remove elevator systems A and B hydraulic power (Ref 27-31-0 MP).
B.  Open or remove the following access doors and panels.
(1)  
Tail cone access door 3802.

(2)  
Stabilizer access panels 9107, 9108 and 9109 for left elevator balance panels, or 9207, 9208 and 9209 for right elevator balance panels.

C.  Install rigging pin E-5 in aft control quadrant (Fig. 401).
4.  Remove Elevator Balance Panel
A.  Remove bolts securing bulb seals (2, Fig. 402) at inboard and outboard ends of balance  panel (3). Remove the seals.
B.  Remove 11 bolts (5) attaching forward end of balance panel (3) to idler hinge (9).
CAUTION:  PROVIDE SUPPORT TO BALANCE PANEL (3) DURING BOLT REMOVAL TO PREVENT EXCESSIVE LOADING OF REMAINING BOLTS. ALSO, AVOID DAMAGE TO IDLER HINGE SEAL (10) DURING BOLT REMOVAL.
501 
Feb 20/88  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-41 Page 401 

G09307G09313
Rigging Pin E-5 Location  500 
27-31-41  Figure 401  Jun 20/85 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

500  Elevator Balance Panel Installation 
Aug 15/73  Figure 402 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-41 Page 403 

C.  Remove six bolts (4) attaching aft end of balance panel (3) to elevator nose (11). Remove balance panel and balance panel hinge seal (6) from airplane.
NOTE:  On some balance panel installations, it may be necessary to remove balance weights in order to gain access to aft mounting bolts (4).
D.  Remove screws securing flat seals (7) at inboard and outboard ends of idler hinge (9). Remove the seals.
E.  Remove 15 nuts and bolts attaching idler hinge (9) to stabilizer support beam (8). Remove idler hinge and idler hinge seal (10) from airplane.
5.  Install Elevator Balance Panel
A.  Check for allowable wear at balance panel hinge. Refer to Elevator Balance Panels -Inspection/Check; then install idler hinge (9, Fig. 402) and idler hinge seal (10) to stabilizer support beam (8).
B.  Install flat seals (7) at inboard and outboard ends of idler hinge (9) as follows:
(1)  
Loosely install bolts up through flat seal (7), idler hinge seal (10) and idler hinge (9).

(2)  
Position each flat seal until 0.01 +0.06/-0.000-inch clearance exists between seal and stabilizer trailing edge rib (1).

(3)  
Before tightening bolts, deflect idler hinge (9) to ensure idler hinge seal (10) remains slack for any elevator position. Tighten flat seal bolts.

C.  Install balance panel as follows:
(1)  
Position balance panel (3) inside balance bay.

(2)  
Loosely install six bolts (4) up through elevator nose (11) into hinge half at aft end of balance panel.

(3)  
Carefully insert balance panel hinge seal (6) between elevator nose (11) and hinge half.

(4)  
Maintain 0.05士 0.02 inch clearance between elevator nose and hinge half, then tighten bolts (4) (Detail A, Fig. 402).
　
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