31-24-31
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
4) Turn the sensor until the mark on the shaft aligns with the mark on the sensor.
NOTE: No special position of the aligned marks is
____
necessary.
5) Turn the sensor to get a display of 0000.
6) Tighten the clamp screws to 30-35 pound-inches.
WARNING: MAKE SURE PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL
_______ SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATORS, FLAPS, SPOILERS, LANDING GEAR, AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(d)
Supply power to hydraulic system A and B (AMM 29-15-00/201).
(e)
Put the aileron in the positions shown in the table.
(f)
At each position, make sure the portable tester display agrees with the value in the table.
~............................................................ | AILERON POSITION | PORTABLE TESTER | | | DISPLAY | .............................................................. | Point B aligned with point A | 7741 to 0037 | .............................................................. | 4.00" above index | 7173 to 7276 | .............................................................. | 4.00" below index | 0502 to 0605 | 2..............................….............................1
F. Put the Airplane in its Usual Condition
S 865-038
(1)
Put the TEST--NORMAL switch to the NORMAL position.
(2)
Put the POWER switch on the portable tester to the OFF position.
(3)
Disconnect the portable tester from the flight data recorder system.
(4)
Close the forward access door, 1103.
(5)
Remove the hydraulic power (AMM 29-15-00/201).
S 865-039
S 085-040
S 415-042
S 865-043
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31-24-31
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737-300/400/500MAINTENANCE MANUAL
S 865-044
(6) Remove the electrical power if it is not necessary (AMM 24-22-00/201).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. BEJ 101-113 ú
31-24-31
ú ú 11 Page 505 ú Nov 15/98
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A
737-300/400/500MAINTENANCE MANUAL
CONTROL WHEEL POSITION SENSOR - REMOVAL/INSTALLATION
____________________________________________________
1. General_______
A. There are two tasks in this procedure. There is one task for the removal and one task for the installation of the position sensor for the control wheel.
B. For these tasks it is necessary to open the forward access door, 1103.
TASK 31-24-32-004-001
2. Control Wheel Position Sensor Removal_____________________________________
A. Standard Tools and Equipment
(1)
Rigging Pin E-1 - 0.311 +0.000/-0.002-inch diameter, 6 inches long (MS20392-4)
(2)
Rigging Pin A/S-1A - 0.311 +0.000/-0.002-inch diameter, 5.5-inch minimum length (MS20392-4)
B. References
(1) 27-11-00/201, Aileron and Aileron Trim Control System.
C. Access
(1)
Location Zone
202 Lower Nose Compartment
(2)
Access Panel
1103 Forward Access Door
D. Prepare for Removal
S 864-002
(1)
Remove the pressure from the aileron hydraulic system (Ref 27-11-00/201).
S 864-003
(2)
Open these circuit breakers:
(a)
P6 Panel
1) FLIGHT CONTROL circuit breakers
(b)
P18 Panel
1) FLIGHT RECORDER AC
2) FLIGHT RECORDER DC
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