BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757
MAINTENANCE MANUAL

 C. References
 (1)  
06-42-00/201, Empennage Access Doors and Panels

 (2)  
24-22-00/201, Electrical Power - Control

 (3)  
29-11-00/201, Main (Left, Right, and Center) Hydraulic Systems

 D.
Access

 (1)  
Location Zones 211/212 Control Cabin 324 Vertical Stabilizer - Rear Spar to Trailing Edge

 (2)  
Access Panel
 324BL Aft Side of Rear Spar and Rudder Hinge

 E.
Prepare for Adjustment

 S 865-012
 (1)  
Supply electrical power (Ref 24-22-00).

 S 865-013

 (2)  
Open this circuit breaker on the overhead panel, P11, and attach a DO-NOT-CLOSE tag:

 (a)  
11J16, RUDDER POS

 S 495-014
 (3)  
Move the towing lever to the tow position and install the towing lever lockpin in the nose gear (Fig. 501).

 S 015-016

 (4)  
Open access panel 324BL (Ref 06-42-00).

 S 865-019
 WARNING: KEEP PERSONS AND EQUIPMENT AWAY FROM ALL CONTROL SURFACES WHEN
_______ HYDRAULIC POWER IS SUPPLIED. AILERONS, ELEVATORS, RUDDER, FLAPS, SLATS, SPOILERS, AND STABILIZER ARE FULLY POWERED SURFACES. INJURY TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR WHEN HYDRAULIC POWER IS SUPPLIED.
 (5)  Supply pressure to the left, right, and center hydraulic systems (Ref 29-11-00).
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757 MAINTENANCE MANUAL
 S 225-017
 (6)  Operate the rudder trim switch on the aft electronic control panel, P8, until the rudder is in its neutral position. Do this check:
 NOTE: Do not operate the rudder trim during the adjustment
____
 procedure.

 (a)  Make sure the rudder trailing edge is not more than 0.05 inch
 (1.3 mm) away from the zero line on the index plate (Fig. 501).
 S 225-045
 (7)  Make sure the control rod length is 10.50 |0.03 inches
 (266.7 +/- 0.7 mm).
 S 035-020
 (8)  
Remove the lockwire from the control rod.

 F.
Rudder Position Transmitter - Adjustment (Procedure 1)

 NOTE: Three procedures are supplied to adjust the rudder position
____
 transmitter.

 Procedure 1 uses a commercially available power supply, a digital voltmeter (DVM), and breakout box equipment.
 Procedure 2 uses airplane power and a DVM with the breakout box equipment.
 Procedure 3 uses the EICAS computer and communication between the control cabin and the rudder control surface.
 S 495-021
 (1)  
Do these steps to connect the breakout box equipment:

 (a)  
Disconnect airplane electrical connector D1742 from the position transmitter.

 (b)  
Connect the breakout box and the -19 cable assembly to the transmitter.

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MAINTENANCE MANUAL

 (c)  
Connect the digital voltmeter (DVM) to the breakout box at pins 4 (SIG HI) and 5 (SIG LO).

 (d)  
Connect the power supply to the breakout box at pins 1 (LO) and 2 (HI) and adjust it to 26 |0.02 volts ac RMS.

 S 825-022
 (2)  
Do these steps to adjust the position transmitter:

 (a)  
Loosen the bolts that hold the position transmitter in its bracket.

 (b)  
Turn the transmitter in its bracket until the output voltage (shown on the DVM) is 0 |0.080 volts ac RMS.

 (c)  
Tighten the bolts that hold the transmitter and do this check:

 1)  Make sure the output voltage stays at 0 |0.080 volts ac RMS.

 (d)  
　
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