NOTE: On airplanes with hydraulic rudder feel and centering unit, with both hydraulic systems A and B on, and rudder pedals are operated at a rapid rate and/or pedal stops are contacted; the feel system pressure differential light may flicker, but check that light does not remain ON.
(8)
Repeat step (7) with captain’s right pedal.
(9)
Move rudder to neutral position.
(10)
Rotate rudder trim control knob in both directions until indicator is a 10. Check that rudder travel is per Section A-A, Fig. 402, in each direction from neutral.
(11)
If disconnected, connect pushrod to nose wheel steering outboard of captain’s forward quadrant.
(12)
Remove hydraulic power, if no longer required (Ref 27-21-0).
(13)
Install access panels.
503
May 01/99 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-82 Page 405
RUDDER FEEL AND CENTERING UNIT - INSPECTION/CHECK
EFFECTIVITY
Airplanes with Mechanical Rudder Feel System
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 for inspection after wear. Refer to component removal/installation for this information.
2. Rudder Feel and Centering Unit Wear Limits
G27249
526 Rudder Feel and Centering Unit Wear Limits
Aug 15/69 Figure 601 (Sheet 1) 27-21-82
Page 601
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
G09935
Rudder Feel and Centering Unit Wear Limits 501
27-21-82 Figure 601 (Sheet 2) Aug 15/69
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
RUDDER POWER CONTROL UNIT - REMOVAL/INSTALLATION
EFFECTIVITY
AIRPLANES PRE-SB 27-1252
1. General
A. The rudder power control unit is located in the lower area of the vertical fin (Fig. 401).
B. For replaceable autopilot components of the rudder power control unit, refer to Chapter 22, Auto Flight. Filter element replacement is accomplished at overhaul.
2. Equipment and Materials
A. Rigging Pins Kit - F70207-3, -52, -61, or -84:
REF NO. F70207-( ) DIAMETER (INCHES) LENGTH (INCHES) FUNCTION
R-5 -11 0.309-0.311 6.7 +0.25 Feel and Centering Mechanism
B. Fire Resistant Hydraulic Fluid -BMS 3-11 or Skydrol Assembly Lube - MCS 352 (Ref 20-30-21)
C. Rudder Lock, PCU Removed - F80150-1
D. Torque Wrench, Rudder PCU Attachment - C27025-1
3. Prepare for Removal
A. Remove rudder systems A, B, and standby hydraulic power (Ref 27-21-0 MP).
B. Remove access panels 9512 and 9514 (Ref Chapter 12, Access Doors and Panels).
C. Remove lower section of rudder hinge cover and seal from right side.
D. Open TE access door 9510 and install rigging pin R-5. (Refer to 27-21-91 A/T for location.)
E. Open yaw damper circuit breakers on P6.
4. Remove Rudder Power Control Unit
CAUTION: DO NOT REMOVE THE UNIONS AND REDUCER FITTINGS FROM THE PCU PORTS WHEN DISCONNECTING THE HYDRAULIC LINES BECAUSE THAT WILL INCREASE THE POSSIBILITIES FOR CROSS CONNECTION OF THE LINES DURING INSTALLATION..
A. Disconnect the hydraulic lines from the PCU. Install plugs in hydraulic lines and caps on port fittings.
B. Disconnect electrical connector.
May 01/03 27-21-91 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
K15088 F17760 F97151
Rudder Power Control Unit Installation 520
27-21-91 Page 402 Figure 401 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/99
500 Rudder Power Control Unit Installation
Aug 01/95 Figure 401 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-91 Page 403
Rudder Power Control Unit Installation 500
27-21-91 Page 404 Figure 401 (Sheet 3) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/01
C. Remove main input rod (vernier control rod).
CAUTION: MAKE SURE TO REMOVE THE VERNIER CONTROL ROD BEFORE THE POWER CONTROL UNIT. FAILURE TO REMOVE THE VERNIER CONTROL ROD FIRST CAN CAUSE DAMAGE TO THE ROD.
D. Remove rod end bolt connecting rod assembly to rudder (Fig. 401).
E. Remove clevis bolt connecting forward manifold assembly to structure.
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