Rigging Pin E-5 Location  500 
27-31-61  Figure 402  Feb 20/85 
Page 404 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

C.  If installing new elevator forward control quadrant assembly, or if pitch transducers (5, Fig. 401) have been removed, install pitch transducers on control quadrants per Chapter 22, Pitch Control Wheel Steering Force Transducer - R/I. Part of installation may be accomplished prior to installation of quadrant in airplane.
5.  Install Elevator Forward Control Quadrant
A.  Position and support elevator forward control quadrant (7, Fig. 401) in lower nose compartment.
B.  Install rigging pin E-1 in left forward control quadrant.
C.  Using a bubble protractor, position each control column 6.9 +0.8 degrees forward of a perpendicular line from floor of airplane (Fig. 403.)
D.  With both control wheels at neutral, slide control columns inboard and simultaneously engage teeth on both connectors (13, Fig. 401) with mating faces on control quadrant (7).
E.  Position inboard coupling (8) on control quadrant and install coupling bolts (9). Tighten bolts within range of driving torque, then alternately tighten bolts to 50-70 pound-inches torque in approximately 10 pound-inch increments to achieve gaps equal within 0.03 inch at each end of coupling clamp.
NOTE:  Check bolt length to ensure that proper bolt is installed. Improper length bolts can cause interference, which prevents achieving full control wheel and control column travel. Substitution of next bolt length and use of washers must be identical at each end of coupling clamp.
F.  Repeat step E for opposite control column.
G.  Adjust shims (11) under left and right bearing housings (10) as required to obtain following clearances:
(1)  
Quadrant assembly is to be centered between floor beam lower chords so that each quadrant will clear respective floor beam lower chord by 0.06 inch minimum through full travel of quadrants.

(2)  
Total clearance (sum of clearances of both quadrants) between bearing (12) inner race shoulder and connector (13) shoulder shal1 be 0.01 to 0.02 inch. Measure clearance at either quadrant with connector shoulder against bearing at other quadrant.

(2a) Total side play of control column assembly is 0.01 to 0.03 inch.

(3)  
Outboard end of stop on left elevator forward quadrant shall clear inboard face of E-1 rig pinhole bracket by 0.07-inch minimum and 0.24 inch maximum.

500 
Oct 20/86  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-61 Page 405 

G09396
Control Column Adjustment  500 
27-31-61  Figure 403  May 01/99 
Page 406 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

H.  Secure cable support fairlead to each quadrant.
I.  Install ring assembly (3) and dust seal (4). Adjust dust cover (2) as required to position edge of dust seal extended slightly upward against dust cover.
J.  Remove rigging pin E-1 from forward control quadrant.
K.  Rotate control columns forward and aft through full travel and check for roughness or binding.
L.  Connect control cables EA and EB to quadrants and install retainer pins. Remove cable clamps.
M.  Remove rigging pin E-5.
N.  Reconnect electrical connectors at pitch transducer (5).
O.  Connect brake release cable to arm on stabilizer trim brake.
P.  With rigging pin E-1 installed, install rigging pin ST-1.
WARNING:  WITH RIGGING PIN ST-1 INSTALLED IN BRAKE MECHANISM, DO NOT MOVE ELEVATOR CONTROL COLUMN. IF CONTROL COLUMN IS MOVED 50% OR MORE OF FULL TRAVEL, LEAF SPRINGS ON CONTROL COLUMN TORQUE TUBE WILL BE PERMANENTLY DEFORMED AND MUST BE REPLACED. A DEFORMED LEAF SPRING MAY RESULT IN UNWANTED ENGAGEMENT OF COLUMN ACTUATED STABILIZER TRIM BRAKE.
Q.  Check that bolt connecting stabilizer trim brake pushrod (6) to fork on forward control quadrant torque tube can be easily inserted.
R.  If bolt cannot be inserted, adjust length of pushrod (6) until bolt fits freely. Secure bolt.
S.  Remove rigging pins E-1 and ST-1.
T.  Adjust control cables and test manual mode operation (column travel and elevator and tab deflection) per 27-31-0, A/T.
U.  Close circuit breakers.
V.  Close access doors and replace access panels.
W.  Restore airplane to normal hydraulic configuration (Ref 27-31-0).
501 
Feb 20/85  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-61 Page 407 

ELEVATOR INPUT TORQUE TUBE - REMOVAL/INSTALLATION
　
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