(3)  
F80063-501 - Elevator Rigging and Restraining Tool

 B.  
References

 (1)  
27-31-00/201, Elevator and Tab Control System

 C.  
Access

 (1)  
Location Zone
 704 Tail Cone
 711 Elevator and Tab, LH
 712 Elevator and Tab, RH

 (2)  
Access Panels
 3801 Tail Cone Access Door, LH
 3802 Tail Cone Access Door, RH

 D.  
Procedure

 S 864-001
 (1)  
Use the trammel bar to set the B dimension at 41.57 |0.01 inches (Fig. 402).

 S 864-002

 (2)  
Do this task: "Remove Elevator Hydraulic Systems A and B" (Ref 27-31-00/201).

 (3)  
Open the access panels 3801 and 3802.

 (4)  
Install the rig pin E-5 in the aft control quadrant.

 S 014-003
 S 494-004
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
SEE  A  LINES HYDRAULIC FLEXIBLE  TUBE TORQUE OUTPUT 
TOOL RESTRAINING RIGGING AND  UNIT CONTROL POWER SEE B  BOLT UPPER MOUNTING 
UNIT CONTROL POWER  BOLT LOWER MOUNTING BRACKET MOUNTING 
INPUT CRANK 
CLEVIS SLEEVE  FWD  A  E-5 RIG PIN 
INPUT ROD 
FWD 
B
Elevator Power Control Unit Installation Figure 401 

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 S 024-005
 (5)  Remove the elevator PCU:
 WARNING: RELEASE THE CONNECTION SLOWLY AND LET THE PRESSURE
_______ DECREASE BEFORE YOU COMPLETELY REMOVE THE HYDRAULIC LINE. IF YOU DISCONNECT THE HYDRAULIC LINE WHEN IT HAS PRESSURE, A SPRAY OF HYDRAULIC FLUID CAN CAUSE INJURY TO PERSONS.
 (a)  
Disconnect the two flexible hydraulic lines from the elevator PCU. 1) Install caps and plugs on the open PCU ports and the

 hydraulic lines.

 (b)  
Disconnect the input rod from the input crank.

 (c)  
Remove the lower mounting bolt from the mounting bracket.

 (d)  
Remove the upper mounting bolt from the output torque tube.

 (e)  
Remove the elevator PCU from the airplane.

"B"
TRAMMEL BAR
DIM 1
____NOTE:  THE STABILIZER TRIM JACKSCREW IS SHOWN ZERO DEGREES WITH THE STABILIZER LEADING EDGE AT  FWD 
1  THE "B" DIMENSION IS MEASURED BETWEEN THE CENTER OF THE UPPER AND LOWER GIMBAL PINS 

Stabilizer Trim Jackscrew Setting
Figure 402

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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

737-300/400/500
MAINTENANCE MANUAL

POWER
CONTROL
UNIT

AREA OF INTERFERENCE
SEE A FWD
REACTION
LINK

0.08 INCH 
AREA TO  BREAK SHARP EDGES  MAXIMUM 
BE CUT  0.05 INCH MINIMUM 
0.50 INCH 
RADIUS 
(2 LOCATIONS) 
6.77 
INCHES 
REACTION  6.05 
LINK  INCHES 

RIGHT SIDE 125 ON REWORKED AREA
A
Elavator Power Control Unit Reaction link Inspection Figure 403
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