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G44662 W01483
500 Elevator Power Control Unit Wear Limits
Feb 15/73 Figure 601 (Sheet 3) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-101 Page 603
Elevator Power Control Unit Wear Limits 500
27-31-101 Page 604 Figure 601 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/03
ELEVATOR TAB LOCK ACTUATOR - REMOVAL/INSTALLATION
1. General
A. The following procedure describes the removal and installation of the elevator tab lock actuator. Further disassembly of the tab lock actuator should be accomplished using procedures given in the overhaul manual.
2. Equipment and Materials
A. Hydraulic Fluid - BMS 3-11 (Ref 20-30-21)
B. 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 +0.25 AFT CONTROL QUADRANT
3. Prepare for Removal
A. Remove elevator systems A and B hydraulic power (Ref 27-31-0 MP).
B. Remove stabilizer access panels 9105 (left) and 9205 (right).
C. Install rigging pin E-5 in aft quadrant.
4. Remove Elevator Tab Lock Actuator (Fig. 401)
A. Remove hydraulic pressure line from elevator tab lock actuator. Cap and plug open port and hydraulic line.
CAUTION: RELEASE HYDRAULIC PRESSURE CONNECTION SLOWLY AND ALLOW SYSTEM PRESSURE TO RELIEVE BEFORE COMPLETELY REMOVING LINE. BE PREPARED TO CATCH SPILLED HYDRAULIC FLUID.
B. Remove actuator upper and lower mounting bolts.
C. Remove actuator from airplane.
500
Feb 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-111 Page 401
G09781
Elevator Tab Lock Actuator Installation 500
27-31-111Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/80
5. Prepare for Installation
A. Remove elevator systems A and B hydraulic power (Ref 27-31-0, MP).
B. Check that rigging pin E-5 is installed in aft quadrant.
C. Check for allowable wear at elevator tab lock actuator attach points (Ref 27-31-121, I/C).
D. Remove cap and plug from actuator and hydraulic pressure line.
E. Ensure that actuator and hydraulic pressure line are filled with hydraulic fluid. Connect hydraulic pressure line to actuator.
CAUTION: EXERCISE CARE TO AVOID TRAPPING AIR IN HYDRAULIC SYSTEM WHILE MAKING CONNECTION.
6. Install Elevator Tab Lock Actuator
A. Insert actuator upper mounting bolt with head facing inboard. Place washer under nut and bolthead and special washer on inboard side of actuator mounting terminal (Fig. 401). Install bushing in inboard bellcrank flange if removed.
B. Insert actuator lower mounting bolt with head facing outboard. Place washer under nut only.
C. Remove rigging pin E-5.
D. Provide elevator system A hydraulic power for left tab lock actuator or system B power for right tab lock actuator (Ref 27-31-0, MP).
E. Visually check hydraulic connection to actuator for signs of leakage.
F. Restore airplane to normal hydraulic configuration (Ref 27-31-0, MP).
G. Test elevator tab (manual mode and power mode) per 27-31-0, A/T.
7. Restore Airplane to Normal
A. Close or replace all access doors and panels.
B. Service hydraulic reservoirs, if required (Ref Chapter 12).
Aug 01/96 27-31-111 Page 403 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
ELEVATOR TAB LOCK LINKAGE - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Trammel Bar - F80055-1
B. Scale - 0 to 6 inches, graduated in inches, tenths and hundredths of an inch
C. 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 +0.25 AFT CONTROL QUADRANT
2. Prepare for Removal
A. Remove elevator system A and B hydraulic power (Ref 27-31-0 MP).
B. Remove or open following access panels (Ref Chapter 12):
(1)
Stabilizer jackscrew compartment access door.
(2)
Tail cone access panel 3802.
(3)
Stabilizer access panel 9105 on left stabilizer or 9205 on right stabilizer.
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