G10888
Control Column Support Bearing Installation 500
27-31-181 Figure 401 Nov 15/67
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
5. Install Control Column Support Bearing
A. Position replacement bearing at right angles to housing. Slide bearing into housing slots and turn into position (Fig. 401).
B. Position bearing housing and shims against structure and install four mounting bolts with heads inboard. Place a washer under heads of two lower mounting bolts and a washer under each of four nuts, then secure.
C. Align forward control quadrant, then insert connector through bearing housing to engage splines on quadrant.
D. Install inboard coupling and coupling retaining bolts. Tighten bolts within range of driving torque, then alternately tighten bolts 50 to 70 pound-inches in approximately 10 pound-inch increments to achieve gaps equal within 0.03 inch at each end of coupling clamp.
NOTE: Substitution of next bolt length and use of washers must be identical at each end of coupling clamp.
E. Check clearance between shoulder of connector and inner race of bearing. Clearance must be
0.01 to 0.03 inch to prevent connector from binding against bearing. Measure clearance with shoulder of opposite connector against bearing.
F. If necessary, adjust clearance between shoulder of connector and inner race of bearing by adding or removing shim under bearing housing.
G. Remove forward control quadrant supports.
H. Install control column (Ref 27-31-51, R/I).
I. Remove rigging pins E-1 and E-5.
J. Rotate control columns forward and aft through full travel and check for roughness or binding.
K. Adjust elevator control cables and check control column forces per 27-31-0, A/T.
L. Restore airplane to normal hydraulic configuration (Ref 27-31-0, MP).
500
Oct 20/84 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-181 Page 403
ELEVATOR OUTPUT TORQUE TUBE - REMOVAL/INSTALLATION
1. 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 士0.25 Aft Control Quadrant
B. Elevator Rigging and Restraining Fixture F80063-501 (Preferred) or F80063-500 (Optional).
C. Trammel Bar - F80055-1
D. Scale - 0 to 6 inches, graduated in tenths and hundredths of an inch
E. Alignment pins - 0.620 +0.004/-0.000-inch diameter, 0.96 +0.03/-0.00-inch long - (2 required)
F. Grease - MIL-G-23827 (Ref 20-30-21)
2. Prepare for Removal
A. Remove elevator systems A and B hydraulic power (Ref 27-31-0 MP).
B. Open aft compartment access door 3701 (Ref Chapter 12).
C. Remove tail cone from airplane (Ref Chapter 53, Tail Cone - R/I).
D. Remove autopilot actuators and mounting bracket (Ref 22-11-261 R/I).
E. Set horizontal stabilizer at 3 units of trim.
F. Install rigging pin E-5 in aft control quadrant (Fig. 401).
3. Remove Output Torque Tube
A. Detach forward ends of left and right elevator control pushrods from output torque tube crank (Fig. 401).
CAUTION: DO NOT PERMIT INNER RACE OF OUTPUT TORQUE TUBE AND ELEVATOR MAST FITTING BEARINGS TO ROTATE TO A POSITION WHERE ROLLERS MAY DROP OUT THROUGH HOLE IN INNER RACE. IF ELEVATOR CONTROL PUSHRODS ARE REMOVED FROM AIRPLANE, IDENTIFY ENDS AS FORE OR AFT PRIOR TO REMOVAL. IF PUSHRODS ARE DISASSEMBLED, SUITABLY IDENTIFY EACH INDIVIDUAL ITEM TO AVOID MISMATCHING PARTS DURING REASSEMBLY.
B. Remove left and right power control unit upper mounting bolts from output torque tube. Allow power units to rotate away from aft bulkhead until input crank bottoms.
C. Remove two pivot bolts attaching output torque tube to inboard pivot brackets at aft bulkhead.
D. Support output torque tube and remove two pivot bolts attaching torque tube to outboard pivot brackets at aft bulkhead.
E. Remove output torque tube from airplane.
4. Prepare for Installation
A. Check for allowable wear at output torque tube installation points and at eight connections between inner and outer torque tubes (Ref Elevator Output Torque Tube - I/C).
B. Remove elevator systems A and B hydraulic power (Ref 27-31-0 MP).
C. Check that horizontal stabilizer is set at 3 units of trim.
500
May 01/99 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-191 Page 401
