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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Elevator Forward Control Quadrant Assembly Installation
Figure 402 (Sheet 7 of 7)/27-31-61-990-802
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-31-61
Page 411
Oct 10/2003
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
TASK 27-31-61-400-801
3. Elevator Forward Control Quadrant Assembly Installation
(Figure 401, Figure 402)
A. References
Reference Title
22-11-92-400-801 Pitch Force Transducer Installation (P/B 401)
27-31-00-700-807 Manual Mode - Test (P/B 501)
27-31-00-820-801 Elevator Control Cables EA and EB and Pitch Force Transducers -
Adjustment (P/B 501)
27-31-00-840-802 Put the Elevator Systems A and B Back to the Condition Before the
Pressure Removal (P/B 201)
B. 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
SPL-1569 Clamp - Control Cable
(Part #: A20005-9, Supplier: 81205, A/P Effectivity: 737-100, -200,
-200C, -300, -400, -500, -600, -700, -700C, -700ER, -700QC, -800, -900,
-900ER, -BBJ)
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-1680 Protractor - Assembly, Control Column
(Part #: 4MIT65B80307-1, Supplier: 81205, A/P Effectivity: 737-100,
-200, -200C, -300, -400, -500, -600, -700, -700C, -700ER, -700QC, -800,
-900, -900ER, -BBJ)
(Part #: A27021-29, Supplier: 81205, A/P Effectivity: 737-100, -200,
-200C, -300, -400, -500, -600, -700, -700C, -700ER, -700QC, -800, -900,
-900ER, -BBJ)
C. Consumable Materials
Reference Description Specification
A00225 Compound - Two Part Hole Filling, Polysulfide BMS5-16
G01912 Lockwire - Monel (0.032 In. Dia.) NASM20995N~
C32
(QQ-N-281)
D. Location Zones
Zone Area
112 Area Forward of Nose Landing Gear Wheel Well
211 Flight Compartment - Left
212 Flight Compartment - Right
318 Tail Cone Compartment - Right
E. Access Panels
Number Name/Location
112A Forward Access Door
318BR Tailcone Access Door
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
F. Forward Control Quadrant Installation
(Figure 402)
SUBTASK 27-31-61-480-003
(1) Use the control column assembly protractor, SPL-1680 to set the control column to 6.9 +/- 0.8
degrees forward of a vertical line from the floor (Figure 402)(View A-A).
SUBTASK 27-31-61-420-001
(2) Install the mass balance weight [5] to the forward quadrant assembly [1]:
(a) Put the mass balance weight [5] in position.
(b) Install the bolts [11] and washers [12].
(c) Install the lockwire, G01912.
SUBTASK 27-31-61-480-004
(3) Install the rig pin E-1 in the left side of the forward quadrant assembly.
SUBTASK 27-31-61-420-002
(4) Install the forward quadrant assembly [1]:
(a) Set the control wheels to the neutral position.
(b) Put the forward quadrant assembly [1] it its position.
(c) Move the control columns inboard and at the same time align the spines of the elevator
forward control quadrant assembly [1] with the forward quadrant connectors [14].
(d) Install inboard couplings [16] with the bolts [13], washers [17], and nuts [18].
NOTE: Make sure that you use the correct bolts.
(e) Do these steps to make the clearances equal at each end of each inboard coupling:
1) Tighten the bolts [13] to 50 inch-pounds (5.7 newton-meters) of torque.
2) Tighten the bolt [13] and then the other to 50-70 pound-inches (5.7-7.9 newton-meters) in
approximately 10 pound-inch (1.1 newton-meters) increments until you get the
clearances equal to +/- 0.03 inch (+/- 0.76 millimeter) of each other.
SUBTASK 27-31-61-820-001
(5) Adjust the shim below the bearing housings:
(a) Make sure the clearance between lower chord of the floor beam and each side of the
forward quadrant assembly [1] is 0.06 inch (1.5 millimeters) minimum through the full
travel.
(b) Make sure the total clearance (sum of the clearances of the two side of forward quadrant
assembly) between the bearing and forward quadrant connector is 0.01-0.02 inch (0.25-0.51
millimeter).
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737-600-700-800-900 AIRCRAFT MAINTENANCE MANUAL飞机维护手册3(78)
