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TASK 27-31-00-820-801
6. Elevator Control Cables EA and EB and Pitch Force Transducers - Adjustment
(Figure 501, Figure 502, Figure 503)
A. General
(1) Use this task to adjust the elevator control cables and pitch force transducers.
(2) Before you do cable adjustment, permit a minimum of one hour at a constant ambient
temperature of +/- 5 degrees F (+/- 2.8 degrees C) for the airframe temperature to become
stable.
(a) The cable tension values will not be correct when there are temperature differences along
the cable run.
B. References
Reference Title
22-11-92-820-801 Pitch Force Transducer Adjustment (DFCS BITE Test) (P/B 501)
27-31-00-700-801 Null Procedure - Mach Trim Actuator (P/B 201)
27-31-00-800-802 Remove Pressure from the Elevator Hydraulic Systems A and B
(P/B 201)
27-31-00-840-802 Put the Elevator Systems A and B Back to the Condition Before the
Pressure Removal (P/B 201)
C. Tools/Equipment
NOTE: When more than one tool part number is listed under the same "Reference" number, the
tools shown are alternates to each other within the same airplane series. Tool part numbers
that are replaced or non-procurable are preceded by "Opt:", which stands for Optional.
Reference Description
COM-1554 Tensiometer - Cable (40-600 LB)
(Part #: ACM-600, Supplier: 13331, A/P Effectivity: 737-ALL)
(Part #: T60 1001-C9-1A, Supplier: 0N8U4, A/P Effectivity: 737-ALL)
SPL-1585 Kit - Rigging Pins, All Systems
(Part #: F70207-109, Supplier: 81205, A/P Effectivity: 737-600, -700,
-700C, -700ER, -700QC, -800, -900, -900ER, -BBJ)
SPL-1677 Assembly - Trammel Bar, Stabilizer Trim Actuator
(Part #: F80055-1, Supplier: 81205, A/P Effectivity: 737-100, -200,
-200C, -300, -400, -500, -600, -700, -700C, -700ER, -700QC, -800, -900,
-900ER, -BBJ)
D. Location Zones
Zone Area
112 Area Forward of Nose Landing Gear Wheel Well
210 Subzone - Control Compartment - Body Station 178.00 to Body
Station 259.50
311 Area Aft of Pressure Bulkhead - Left
312 Area Aft of Pressure Bulkhead - Right
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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E. Access Panels
Number Name/Location
112A Forward Access Door
311BL Stabilizer Trim Access Door
318BR Tailcone Access Door
F. Prepare for the Adjustment
SUBTASK 27-31-00-860-016
(1) Do this task: Remove Pressure from the Elevator Hydraulic Systems A and B,
TASK 27-31-00-800-802.
SUBTASK 27-31-00-860-017
(2) Do this task: Null Procedure - Mach Trim Actuator, TASK 27-31-00-700-801.
SUBTASK 27-31-00-010-031
(3) Open this access panel:
Number Name/Location
112A Forward Access Door
SUBTASK 27-31-00-010-032
(4) Open this access panel:
Number Name/Location
311BL Stabilizer Trim Access Door
SUBTASK 27-31-00-010-001
(5) Remove this access panel:
Number Name/Location
318BR Tailcone Access Door
SUBTASK 27-31-00-860-018
(6) Use the bar, SPL-1677 to set the "B" dimension at 4 units of trim (39.89 +/- 0.01 inches or 1013.2
+/- 0.3 mm) (Figure 502).
SUBTASK 27-31-00-480-010
(7) Use a 40 - 600 lb cable tensiometer, COM-1554 to get the tension measurement, (Table 501).
G. Elevator Control Cables EA and EB and Pitch Force Transducers Adjustment
SUBTASK 27-31-00-020-001
(1) Remove the nuts [3], washers [2], and bolts [1] from the adjustable end of the two pitch force
transducers (Figure 501).
NOTE: The bolts [1] will be installed when you complete the adjustment of the pitch force
transducers.
SUBTASK 27-31-00-710-001
(2) Adjust the elevator control cables EA and EB and the pitch force transducers:
(a) Install the rig pin E-5 from the rig pin kit, SPL-1585 in the elevator aft quadrant (Figure 503).
1) Make sure you can move the rig pin freely.
2) If it is necessary, move the elevator by hand until you can install the rig pin E-5.
(b) Install the rig pin E-1 from the rig pin kit, SPL-1585 in the elevator left forward quadrant
(Figure 501).
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-31-00
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Oct 10/2006
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
1) Make sure you can move the rig pin E-1 freely.
(c) Remove the nuts [6], washers [5], and bolts [4] from the two elevator forward quadrants.
NOTE: The bolts [4] will be installed when you complete the adjustment of the pitch force
transducers.
(d) Install the rig pins E-2 and E-3 from the rig pin kit, SPL-1585 through the installation holes of
　
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