RUDDER INDEX PLATE - REMOVAL/INSTALLATION
1. General
A. The rudder index plate is installed with screws in inserts on top of tail cone at airplane centerline.
B. Airplanes with Centerline Position Indicator Rivet
(1) On some airplanes, a single indicator rivet is installed just aft of rudder index plate. The rivet is installed on body buttock line 0.00 to within 0.015 inch. On airplanes with centerline position indicator rivet, remove and install rudder index plate per Par. 2.
C. Airplanes without Centerline Position Indication Rivet
(1) On airplanes without centerline position indicator rivet, remove and install rudder index plate per Par. 3.
D. On all airplanes, if an out-of-trim condition exists, rudder index plate may be adjusted per 27-09-400, Flight Controls Trim Correction - A/T.
2. Rudder Index Plate Removal/Installation on Airplanes with Centerline Position Indicator Rivet
A. Remove Rudder Index Plate (Fig. 401)
(1)
If existing tail cone will be reinstalled, place a piece of tape on tail cone next to rudder index plate and mark exact position of index plate tab.
(2)
Remove screws and washers and remove index plate.
B. Install Rudder Index Plate
(1)
On existing tail cone, install new index plate with washers and screws such that index plate tab aligns with mark on tape. Remove tape from tail cone.
(2)
If new tail cone has been installed, install index plate with washers and screws such that left edge of tab is 0.05 +0.01 inch right of centerline of indicator rivet.
3. Rudder Index Plate Removal/Installation on Airplanes without Centerline Indicator Rivet
A. Equipment and Materials
(1)
Shock Absorber (Bungee) Cord - 1/4 or 3/8 inch diameter, MIL-C-5651, Type I (Ref 20-30-51)
(2)
Nylon Lacing Tape 0.090 inch thick - MIL-T-43435 (Ref 20-30-51)
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Feb 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-161 Page 401
B. Remove Rudder Index Plate (Fig. 401)
(1)
If existing tail cone will be reinstalled, place a piece of tape on tail cone next to rudder index plate and mark exact position of index plate tab.
(2)
Remove screws and washers and remove index plate.
C. Prepare to Install Rudder Index Plate
(1)
Faired position of rudder is found by using a bungee cord arrangement as shown on Fig.
401. Two cords of equal length, each having a loop at one end, are tied together at opposite end. Strung on each side of rudder and fin, 1oops are hooked around pitot tubes, giving cords a fair amount of tension to ensure cords do not sag.
(2)
By viewing rudder and cords from behind rudder trailing edge, moving rudder slowly back and forth by hand, it is possible to determine rudder location left and right where cord is separating from rudder and fin surface. Project rudder trailing edge onto tail cone and mark at these two locations. Halfway distance between marks is airplane centerline.
D. Install Rudder Index Plate (Fig. 401)
(1)
On existing tail cone, install new index plate with washers and screws such that index plate tab aligns with mark on tape. Remove tape from tail cone.
(2)
If new tail cone has been installed, install index plate with washers and screws such that left edge of tab is 0.08 +0.01 inch left of airplane centerline (Configuration A) or install index plate with washers and screws such that right edge of tab is 0.58 +0.02/-0.01 inch from centerline of right mounting screw (Configuration B).
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27-21-161 Page 402 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/90
500 Rudder Index Plate Installation
Feb 01/95 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-161 Page 403
ELEVATOR AND TAB CONTROL SYSTEM -DESCRIPTION AND OPERATION
1. General
A. The elevators provide primary pitch control of the airplane about its lateral axis and respond to control column inputs through two independent hydraulic systems. In the event of dual hydraulic failure, a manual reversion mode will allow the elevators to be driven directly through a mechanical control system. Aerodynamic elevator tabs are provided to assist elevator movement during manual reversion mode. Air loads on the system are further reduced by aerodynamic balance panels attached to each elevator.
B. The elevator control system is activated by fore and aft motion of the captain's and first officer's control columns. A torque tube, with a forward control quadrant mounted at each end, interconnects the control columns. A pair of elevator control cables attach to each forward control quadrant. The elevator up cables (EB) are secured at the quadrants and then routed aft under the floor to the aft control quadrants (Fig. 1). The elevator down cables (EA) are routed forward from the control quadrants, around a pair of pulleys, then aft along the fuselage to the aft control quadrants. The control cables are rigged over pulleys to minimize flexing and prevent chafing. The aft quadrants are mounted on the input torque tube in the empennage, aft of the stabilizer rear spar. The elevator hydraulic power control units for left and right elevators are linked between the input torque tube and the output torque tube and provide power to rotate the elevators during power mode.
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