(3)
VTVM Fluke (Digital)
E. Prepare for the Transducer Adjustment
S 865-003
(1)
Supply electrical power (Ref 24-22-00/201).
S 865-004
(2)
Do this task to fully adjust the elevator rigging before you can adjust the transducers: "Adjustment - Elevator and Tab Control System" (Ref 27-31-00/501).
S 865-005
(3)
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a)
P6 Circuit Breaker Panel
1) AFCS B MACH TRIM AC
2) AFCS B MACH TRIM DC
3) AFDS MCP CRS-2
4) AFCS B SNSR EXC AC
5) AFCS B FCC DC
6) AFCS B ENGAGE INTLK
7) AFDS B WARN LIGHT BAT
(b)
P18 Circuit Breaker Panel 1) AFCS A MACH TRIM AC 2) AFCS A MACH TRIM DC 3) AFDS MCP DC 4) Airplanes with mechanical aileron force limiter:
AFDS AIL FORCE LIM
5) AFCS A SNSR EXC AC
6) AFCS A FCC DC
7) AFCS A ENGAGE INTLK
8) AFCS A WARN LIGHT BAT
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22-11-92
ALL ú ú 01 Page 502 ú Jul 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500
MAINTENANCE MANUAL
HORIZONTAL
STABILIZER
SEE B
POWER
CONTROL
UNIT
SEE A
ELEVATOR
AFT CONTROL QUADRANT RIGGING PIN E5 (RIGHT AFT
CABIN QUADRANT)
FLOOR FWD
ELEVATOR CONTROL
PUSHROD ASSEMBLY
B
SHOULDER BOLT
(RIGGING PIN E2
LEFT QUADRANT) PITCH
CONTROL
QUADRANT
RIGGING
PIN E1 (LEFT SHOULDER BOLT
FORWARD QUADRANT) HOLE (RIGGING
PIN E2 OR E3)
MOUNTING BOLT (ADJUSTMENT END) SHOULDER BOLT WASHER AND NUT FOR COARSE ADJUSTMENT LOCKNUTS
PITCH FORCE (ROD END)
WASHER AND TRANSDUCER
MOUNTING BOLT NUT FOR SEE C
FWD
A
TABWASHER
FINE
ADJUSTMENT
NUT
PITCH FORCE
TRANSDUCER DETAIL
C
Pitch Force Transducer Adjustment
Figure 501
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22-11-92
ALL ú ú 01 Page 503 ú Nov 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
S 015-007
(4)
Open the forward access door, 1103, to get access to the transducer (Ref 12-31-11/201).
S 015-006
(5)
Open the tail cone access door, 3802 (Ref 12-31-41/201).
F. Pitch Force Transducer Adjustment (Fig. 501)
S 035-008
(1) Remove the adjustable end of the transducers for adjustment:
(a) Install the rig pin E1 in the left forward quadrant and the rigging pin E5 in the right aft quadrant.
NOTE: The rig pins E1 and E5 must go through easily and
____
freely.
(b)
Remove the mass balance weights from the control columns (Ref 27-31-61/401).
(c)
Disconnect the transducer cables from the airplane wiring.
(d)
Remove the mounting bolt, washer, and nut from the adjustable end of each transducer.
(e)
Remove the shoulder bolts, washers, and nuts from the quadrant assemblies.
(f)
Install the rig pin E2 in the left quadrant and rig pin E3 in the right quadrant.
NOTE: You will find the labels of the rig pin positions on
____ the quadrant assemblies. The rig pins E2 and E3 must go through easily and freely.
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